Encyclopedia Astronautica
Index


1.5KS35000.
  • Thiokol solid rocket engine. 156 kN.

1.8KS7800.

  • Multiple-source American solid rocket engine. 35 kN.

105-KS-45,220.

  • Alternate designation for Star 75 Solid rocket engine.

118-KS-19,050.

  • Alternate designation for Star 63D Solid rocket engine.

11B91.

  • Government designation of RD-0410 Nuclear-LH2 rocket engine.

11B97.

  • Korolev nuclear electric/xenon rocket engine. 450 mN. Engine for Interorbital Tug for launch by Energia. Developed 1978-1986. Isp=3000s. Powered by nuclear reactor providing 50-150 kWt for 3 to 5 years operation.

11D111.

  • Government designation of NK-33 Lox-Kerosene rocket engine.

11D112.

  • Government designation of NK-43 Lox-Kerosene rocket engine.

11D113.

  • Government designation of NK-39 Lox-Kerosene rocket engine.

11D114.

  • Government designation of NK-31 Lox-Kerosene rocket engine.

11D119.

  • Government designation of RD-264 N2O4-UDMH rocket engine.

11D121.

  • Korolev GOX/Kerosene rocket engine. 68.650 kN. N-1 stage 1 (block A) roll control engine. Developed 1969-74. Gimbaling +/- 45 degree. Propellants are fed from main engine (NK-15, NK-33) turbopumps. Isp=313s. Chamber Pressure: 71.60 bar.

11D122.

  • Government designation of RD-0120 Lox-LH2 rocket engine.

11D122A.

  • Government designation of RD-0120M Lox-LH2 rocket engine.

11D123.

  • Article Number of RD-120 Lox-Kerosene rocket engine. Also applied to the RD-134R and RD-146 variants.

11D130F.

  • Article Number of RD-302 LF2-Ammonia rocket engine.

11D14.

  • Article Number of the RD-303 LF2-Ammonia rocket engine.

11D23.

  • Kosberg N2O4/UDMH rocket engine. 230.5 kN. Study 1968. Engine used in Block 1 and Block 11 stages of LK-700 manned lunar lander.

11D24.

  • Government designation of RD-0225 N2O4-UDMH rocket engine.

11D25.

  • Government designation of RD-861 N2O4-UDMH rocket engine.

11D25G.

  • Government designation of RD-861G N2O4-UDMH rocket engine.

11D26.

  • Alternate designation for RD-219 Nitric acid-UDMH rocket engine.

11D33.

  • Government designation of S1.5400 Lox-Kerosene rocket engine.

11D33M.

  • Government designation of S1.5400A Lox-Kerosene rocket engine.

11D414.

  • Government designation of KDU-414 Nitric acid-UDMH rocket engine.

11D416.

  • Isayev N2O4/UDMH rocket engine. 16.4 kN. Study 1968. Three of these engines used for midcourse corrections and soft lunar landing in Block 11 and Block 1V stages of LK-700 manned spacecraft.

11D417.

  • Government designation of KTDU-417 Nitric acid-UDMH rocket engine.

11D417B.

  • Government designation of KTDU-417-B N2O4-UDMH rocket engine.

11D423.

  • Izotov N2O4/UDMH rocket engine. 134 kN. LK-700S manned lunar lander ascent stage engine. Development ended 1968. Isp=326s. Based UR-100 stage 2 engine. Gas generator cycle; 2 large turbine exhaust pipes.

11D425.

  • Government designation of KTDU-425 N2O4-UDMH rocket engine.

11D425A.

  • Government designation of KTDU-425A N2O4-UDMH rocket engine.

11D426.

  • Government designation of KDU-426 N2O4-UDMH rocket engine.

11D428.

  • Melnikov N2O4/UDMH rocket engine. 0.110 kN. Yantar-2K orbital propulsion. In Production. Orbital propulsion system of the Yantar-2K military satellite, including one 11D430, four 11D431, four 11D446, and eight 11D428. Up to 40,000 ignitions.

11D43.

  • Glushko N2O4/UDMH rocket engine. 1642 kN. Developed 1960-64. Isp=316s. Low-expansion ratio gimbaled variant for Proton stage 1 concept. Configuration 4 x 8D43 clustered with 4 x 11D43 abandoned in favor of 6 x Glushko 11D48 in final Proton design.

11D430.

  • Melnikov N2O4/UDMH rocket engine. 29.430 kN. Yantar-2K orbital propulsion. In Production. Orbital propulsion system of the Yantar-2K military satellite, including one 11D430, four 11D431, four 11D446, and eight 11D428. Up to 50 ignitions. Isp=307s. Chamber Pressure: 9.00 bar.

11D431.

  • Melnikov N2O4/UDMH rocket engine. 6 N. Yantar-2K orbital propulsion. In Production. Orbital propulsion system of the Yantar-2K military satellite, including one 11D430, four 11D431, four 11D446, and eight 11D428. Up to 150,000 ignitions.

11D442.

  • Government designation of KRD-442 N2O4-UDMH rocket engine.

11D445.

  • Melnikov N2O4/UDMH rocket engine. 0.065 kN. Yantar-2K descent propulsion. In Production. Propulsion system of the Yantar-2K military satellite descent capsule. Up to 10,000 ignitions. Thrust from 0,065 - 0,012 kN.

11D446.

  • Melnikov N2O4/UDMH rocket engine. 0.052 kN. Yantar-2K orbital propulsion. In Production. Orbital propulsion system of the Yantar-2K military satellite, including one 11D430, four 11D431, four 11D446, and eight 11D428. Up to 40,000 ignitions.

11D458.

  • Isayev N2O4/UDMH rocket engine. 0.392 kN. In Production. Isp=252s. Small attitude control thruster in Briz upper stage propulsion system S5.98M. Total summmary impulse 14,112 kg-s. Minimum impulse 4 kg-s. Specific impulse also reported as 275 sec.

11D48.

  • Government designation of RD-253-11D48 N2O4-UDMH rocket engine.

11D49.

  • Isayev Nitric acid/UDMH rocket engine. 157.5 kN. Kosmos-3M stage 2. Engine has one main and four steering nozzles. Thrust 157.5 + 4 x 25 kN. Precessor was 11D47 in R-14 (derivative ?) stage 2. Isp=303s. First flight 1964.

11D51.

  • Government designation of NK-15 Lox-Kerosene rocket engine.

11D511.

  • Government designation of RD-107-11D511 Lox-Kerosene rocket engine.

11D511P.

  • Government designation of RD-107-11D511P Lox-Kerosene rocket engine.

11D511PF.

  • Government designation of RD-117PF Lox-Kerosene rocket engine.

11D512.

  • Government designation of RD-108-11D512 Lox-Kerosene rocket engine.

11D512P.

  • Government designation of RD-108-11D512P Lox-Kerosene rocket engine.

11D513.

  • Government designation of RD-8 Lox-Kerosene rocket engine.

11D51F.

  • Kuznetsov Lox/Kerosene rocket engine. 1918 kN. N1F 1965 - A. Study 1965. As described in N1 improvement study, 1965. Block A engine thrust increased. Isp=331s.

11D51M.

  • Kuznetsov Lox/Kerosene rocket engine. 2843 kN. N1M 1965 - A. Study 1965. As described in N1 improvement study, 1965. Huge modification of Block A engines - sea level thrust increased from 175 tonnes thrust to 250 tonnes. Isp=346s.

11D520.

  • Government designation of RD-170 Lox-Kerosene rocket engine.

11D521.

  • Government designation of RD-171 Lox-Kerosene rocket engine.

11D52F.

  • Kuznetsov Lox/Kerosene rocket engine. 1961 kN. N1F 1965 - B. Study 1965. As per N1 improvement study, 1965. Engine thrust increased from 150 t each to 200 t. Isp=347s.

11D52M.

  • Kuznetsov Lox/Kerosene rocket engine. 2745 kN. N1M 1965 - B. Study 1965. As per N1 improvement study, 1965. Thrust increased to 280 tonnes per engine. Isp=330s.

11D52V.

  • Government designation of NK-15V Lox-Kerosene rocket engine.

11D52VM.

  • Government designation of NK-15VM Lox-LH2 rocket engine.

11D53.

11D53F.

  • Kuznetsov Lox/Kerosene rocket engine. 612 kN. N1F 1965 - V. Study 1965. As per N1 improvement study, 1965. Engine thrust increased and stretched propellant tanks resulting in 20% longer burn time. Isp=346s.

11D53M.

  • Kuznetsov Lox/Kerosene rocket engine. 735 kN. N1M 1965 - V. Study 1965. As per N1 improvement study, 1965. Further increase in thrust of Block V engines. Isp=347s. Used on N-IM 1965 launch vehicle.

11D54.

  • Article Number of the NK-9V-11D54 and NK-19 Lox-Kerosene rocket engine. Reused for the RD-54 Lox-LH2 rocket engine.

11D55.

  • Government designation of RD-0110 Lox-Kerosene rocket engine.

11D56.

  • Government designation of RD-56 Lox-LH2 rocket engine.

11D56M.

  • Government designation of RD-56M Lox-LH2 rocket engine.

11D57.

  • Government designation of RD-57 Lox-LH2 rocket engine.

11D57M.

  • Government designation of RD-57M Lox-LH2 rocket engine.

11D58.

  • Government designation of RD-58 Lox-Kerosene rocket engine.

11D58M.

  • Government designation of RD-58M Lox-Kerosene rocket engine.

11D58MF.

  • Government designation of RD-58MF Lox-Kerosene rocket engine.

11D58S.

  • Government designation of RD-58S Lox-Kerosene rocket engine.

11D58Z.

  • Government designation of RD-58Z Lox-Kerosene rocket engine.

11D614.

  • Government designation of RD-216 Nitric acid-UDMH rocket engine.

11D62.

  • Government designation of KTDU-35 Nitric acid-UDMH rocket engine.

11D68.

  • Government designation of S5.51 N2O4-UDMH rocket engine.

11D69.

  • Alternate designation for RD-218 Nitric acid-UDMH rocket engine.

11D79.

  • Stepanov N2O4/UDMH rocket engine. 44 kN. Blok D SOZ. In Production. Thrust 1.1-4.5 tf variable.

120-KS-23,520.

  • Alternate designation for Star 63F Solid rocket engine.

12KS10000.

  • Bristol solid rocket engine. 45 kN.

14.8-KS-1,708.

  • Alternate designation for Star 13B Solid rocket engine.

14D14.

  • Government designation of RD-253-14D14 N2O4-UDMH rocket engine.

14D23.

14D30.

  • Government designation of S5.98M N2O4-UDMH rocket engine.

14D451M.

  • Government designation of RD-0124 Lox-Kerosene rocket engine.

15.3-KS-1,320.

  • Alternate designation for Star 13A Solid rocket engine.

15D12.

  • Government designation of RD-857 N2O4-UDMH rocket engine.

15D13.

  • Article Number of 8D423 N2O4-UDMH rocket engine.

15D13.

  • Klimov N2O4/UDMH rocket engine. 131.4 kN. Study 1968. Main engine for midcourse Block 1V ascent/trans-earth injection stage of LK-700 manned spacecraft. See also 11D423.

15D151.

  • NII-125 solid rocket engine. Combined missile (RT-20P) stage 1. Out of production. Launch thrust 588 kN. Designed for first stage of combined missile and SLBM; flight tested, no production. First flight 1967.

15D169.

  • Yuzhnoye solid rocket engine. 142 kN.

15D169.

  • Article Number of RD-862 N2O4-UDMH rocket engine.

15D2.

15D206.

  • Yuzhnoye solid rocket engine. RT-23 early models stage I. Out of Production. The case-bound T9-BK composite solid propellant charge had a star shape channel. The case was of organic fibre-wound plastic material.

15D23.

  • KBMash solid rocket engine. 892 kN. RT-2 Stage 1. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/aluminium propellant. Chamber pressure 40 kgf/cm2.

15D23P.

  • TsKB-7 solid rocket engine. 980 kN. RT-2P Stage 1. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/ammonium butyl propellant. Chamber pressure 56 kgf/cm2.

15D24.

  • TsKB-7 solid rocket engine. 431 kN. RT-2 Stage 2. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/aluminium propellant. Chamber pressure 40 kgf/cm2. Average thrust 33 tonnes.

15D24P.

  • TsKB-7 solid rocket engine. 437.3 kN. RT-2P Stage 2. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/ammonium butyl propellant. Chamber pressure 48 kgf/cm2.

15D25.

  • KBMash solid rocket engine. 137 kN. RT-2 Stage 3. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/aluminium propellant.

15D27.

  • Arsenal solid rocket engine. 432 kN.

15D305.

  • Yuzhnoye, Tsurilnikov solid rocket engine. RT-23 stage I. Out of Production. Case-bound OPAL composite solid propellant charge with a star shape channel. The case was of organic fibre-wound plastic material.

15D339.

  • Yuzhnoye. Tsurilnikov solid rocket engine. RT-23 stage II. Out of Production. The case-bound START composite solid propellant charge had a cylindrical-conical umbrella shape channel. The case was of organic fibre-wound plastic material.

15D94.

  • TsKB-7 solid rocket engine. 180.4 kN. RT-2P Stage 3. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/ammonium butyl propellant. Chamber pressure 48 kgf/cm2.

15D95.

  • Government designation of RD-0232 N2O4-UDMH rocket engine.

15KS25000.

  • Bristol solid rocket engine. 111 kN.

15Zh58A.

  • MITT solid rocket engine. 980 kN.

15Zh58B.

  • MITT solid rocket engine. 490 kN.

15Zh58V.

  • MITT solid rocket engine. 245 kN.

16 in gun.

  • US Navy gun for launch of rocket-boosted projectile. 1,470,981 kN. Development ended 1966. The proposed Martlet gun-launched small satellite launcher used a converted 16 inch naval gun to propell the rocket sabot. Isp=43s.

16.8-KS-7,870.

  • Alternate designation for Star 26C Solid rocket engine.

17.6-KS-2,460.

  • Alternate designation for Star 17 Solid rocket engine.

17.8-KS-7,500.

  • Alternate designation for Star 26 Solid rocket engine.

17.8-KS-7,784.

  • Alternate designation for Star 26B Solid rocket engine.

17D11.

  • Korolev Lox/Kerosene rocket engine. 86.3 kN. Buran OMS and verniers. Out of Production. Buran orbital propulsion system, including 2 x 17D12, 38 x 17D15, 8 x RDMT-200K Isp=362s.

17D12.

  • Korolev Lox/Kerosene rocket engine. 86.3 kN. Out of Production. Isp=362s. Version of RD-58 for Buran orbital propulsion system 17D11. Used synthetic kerosene ('Sintin') for higher specific impulse.

17D15.

  • Korolev GOX/Sintin rocket engine. 4 kN. Buran OMS large verniers. Out of Production. Isp=295s. Large verniers for Buran orbital propulsion system 17D11. Uses synthetic kerosene ('Sintin') for high specific impulse. Oxygen is gaseous in system.

17D58E.

  • Government designation of RDMT-12 N2O4-UDMH rocket engine.

17D58E.

  • Isayev N2O4/UDMH rocket engine.13 N. In Production. Isp=247s. Small attitude control thruster used in Briz, Briz-M upper stage propulsion system S5.98M.

17D61.

  • Melnikov N2O4/UDMH rocket engine. 2.943 kN. Ikar stage 4 for Soyuz-Ikar. Design 1999. Isp=325s. Derived from propulsion module of Yantar spysat, with over 30 flights to 1998. Increased versatility compared to Block L due to capability for 50 restarts.

17KS12000.

  • Alternate designation for Nihka Solid rocket engine.

19.4-KS-3,600.

  • Alternate designation for Star 17A Solid rocket engine.

2.4KS5600.

2.5KS18000.

  • Multiple-source solid rocket engine. 80 kN. Typical ideal dV=259 m/s; gravity and drag losses = 25 m/s.

2.67-KS-459.

  • Alternate designation for Star 5C Solid rocket engine.

2.80-KS-439.

  • Alternate designation for Star 5C-CB Solid rocket engine.

200 inch solid segment x 4.

  • Notional solid rocket engine. 11,120 kN. Study 1960. Isp=285s. 4 used as first stage of NASA all-solid Nova design. Extended high-expansion nozzles.

200 inch solid segment x 6.

  • Notional solid rocket engine. 28,017 kN. NASA Nova study 1960. Isp=263s. 5 used as first stage of solid Nova design.

21AL-2600.

  • Aerojet Nitric acid/Amine rocket engine. Nike Ajax. Launch thrust 11.7 kN. Development begun January 1946. Regeneratively cooled. Development and production First flight 1953.

22.6KS1245.

  • Multiple-source American solid rocket engine. 5.5 kN.

23KS11000.

  • Aerojet solid rocket engine. 49 kN.

23KS20000.

  • Bristol Aerospace solid rocket engine. 89 kN. Two-finned version.

25AL-1000.

  • Aerojet Nitric acid/Amine rocket engine. A-20 ATO. Launch thrust 4.41 kN. Development begun May 1942. Production version of GALCIT unit. First flight 1944.

25XALD-1000.

  • Aerojet Nitric acid/Amine rocket engine. JATO, Droppable for P-38, B-24, and B-25J. Thrust 4.41 kN. Development begun May 1942. Droppable version of XLR1, packaged compactly with parachute. First flight 1944.

26KS20000.

  • Bristol Aerospace solid rocket engine. 75.7 kN. Four-finned version.

27.5-KS-6,100.

  • Alternate designation for Star 20 Solid rocket engine.

280 inch solid.

  • Notional solid rocket engine. 46,208 kN. Study 1963. Operational date would have been February 1973 Isp=265s. Used on Nova MM 14B launch vehicle.

28-KS-4,825.

  • Alternate designation for Star 24C Solid rocket engine.

29.6-KS-4,170.

  • Alternate designation for Star 24 Solid rocket engine.

293-P.

  • Kartukov solid rocket engine. P-70 Ametist. Out of Production.

3.0KS4000.

30.1-KS-5,500.

  • Alternate designation for Star 20B Solid rocket engine.

300 inch solid.

  • Notional solid rocket engine. 63,595 kN. Study 1963. Operational date would have been April 1973 Isp=263s. Used on Nova MM 14A launch vehicle.

300LR-200.

  • Aerojet Nitric acid/Amine rocket engine. XP-79 Launch thrust .882 kN. Development begun January 1943. Planned successor to XCALT-6000, developed under 'Project X' for the Northrop XP-79 Flying Wing rocket fighter. First flight 1945.

30AL-1000.

  • Aerojet Nitric acid/Amine rocket engine. GAPA. Launch thrust 4.41 kN. Development begun March 1947. Boeing surface-to-air missile, which would evolve into Bomarc and reach IOC in 1959.

30-KS-8000.

  • Manufacturer's designation of Alcor Solid rocket engine.

32.02-KS-38.

  • Alternate designation for Star 5A Solid rocket engine.

325 in solid.

  • Notional solid rocket engine in GD Nova studies. 69,047 kN. Study 1963. Isp=263s. Recoverable motors; separation at 1,972 m/s at 53,000 m altitude; splashdown using retrorockets under 3 61 m diameter parachutes 610 km downrange.

34.35-KS-6,010.

  • Alternate designation for Star 27 Solid rocket engine.

38ALDW-1500.

  • Aerojet Nitric acid/Amine rocket engine. ATO Seaplanes. Launch thrust 6.66 kN. Development begun July 1943. Regeneratively cooled. Also a few 45ALDW-1500 were built. Droppable version. First flight 1945.

3D65.

  • Government designation of RD-866 N2O4-UDMH rocket engine.

3-DS-47000.

  • Hercules solid rocket engine. 209 kN.

4.4KS4800.

40ALD-3000.

  • Aerojet Nitric acid/Amine rocket engine. B-29 droppable ATO. Launch thrust 13.33 kN. Development begun October 1943. Droppable version, pressure fed, regeneratively cooled, supplied with 331 kg of propellant. First flight 1945.

40XAL-4000.

  • Aerojet Nitric acid/Amine rocket engine. PB2Y-3 ATO. Launch thrust 17.6 kN. Development begun July 1943. Gasoline engine driven pumps. Also 40ALD-6000 and 60ALD-8000 versions First flight 1945.

45AL-2600.

  • Aerojet Nitric acid/Amine rocket engine. Aerobee B. Launch thrust 11.7 kN. Development begun June 1948. Manufacture of complete Aerobee systems First flight 1955.

45-KS-18,500.

  • Alternate designation for Star 31 Solid rocket engine.

45LR-35000.

  • Aerojet Nitric acid/UDMH rocket engine. Bomarc. Out of Production. Launch thrust 159.583 kN. Development begun 1953. Pressure-fed, uncooled, ceramic-lined engine. First flight 1959.

49-KS-7,955.

  • Alternate designation for Star 30E Solid rocket engine.

4D10.

  • Isayev N2O4/UDMH rocket engine. 255 kN. R-27 / RSM-25 (SS-N-6). Out of Production. First engine system to be submerged in propellant tank. One main engine chamber plus unknown number (probably 4) of steering thrusters. Thrust 226 + 29 kN.

5 mlbf.

  • Notional lox/lh2 rocket engine. 41,361 kN. OOST, ROOST studies 1963. Isp=410s. First flight 1977.

5 mlbf RP-4.

  • Notional Lox/Kerosene rocket engine. 24,459 kN. Study 1963. Operational date would have been July 1977. Recoverable stage. 10% plug nozzle. Isp=299s. Used on Nova-1 DAC launch vehicle.

5.5KS6100.

5.6KS5400.

  • Multiple-source American solid rocket engine. 24 kN.

5.9-KS-565.

  • Alternate designation for Star 6B Solid rocket engine.

500 Ibf Centrojet.

  • Manufacturer's designation of Centrojet Nitric acid-Amine rocket engine.

51-KS-7,340.

  • Alternate designation for Star 30C Solid rocket engine.

51T6 Motor.

  • Fakel solid rocket engine.

51T6B ZhRD.

  • Fakel N2O4/UDMH rocket engine.

54-KS-6,070.

  • Alternate designation for Star 30BP Solid rocket engine.

5D22.

  • SKB-350 solid rocket engine.

5D25.

  • Government designation of S5.44 Nitric acid-Amine rocket engine.

5S47.

  • SKB-350 solid rocket engine.

63-KS-10,625.

  • Alternate designation for Star 37FM Solid rocket engine.

66-KS-8,550.

  • Alternate designation for Star 37XFP Solid rocket engine.

7.5-KS-1,250.

  • Alternate designation for Star 12 Solid rocket engine.

7.5-KS-1,630.

  • Alternate designation for Star 12A Solid rocket engine.

87.2-KS-17,335.

87.2-KS-17,735.

  • Alternate designation for Star 48B Solid rocket engine.

8D21.

  • Article Number of RD-301 LF2-Ammonia rocket engine.

8D411K.

  • Government designation of RD-0210 N2O4-UDMH rocket engine.

8D412K.

  • Government designation of RD-0211 N2O4-UDMH rocket engine.

8D415K.

  • Kosberg Lox/Kerosene rocket engine. 1471 kN. Designed for use in N-1. Development canceled in 1960 when Korolev turned to Kuznetsov for R-9 and N-1 engines after continuous rows with Glushko over performance and propellant types. First flight 1966.

8D419.

  • Manufacturer's designation of 8D423 N2O4-UDMH rocket engine.

8D420.

  • Government designation of RD-270 N2O4-UDMH rocket engine.

8D420M.

  • Government designation of RD-270M N2O4-Pentaborane rocket engine.

8D423.

  • Izotov N2O4/UDMH rocket engine. 131 kN. Production from 1964. Isp=325s. Single chamber engine for UR-100 stage 2. Gas generator cycle with two large turbine exhaust pipes. First flight 1965.

8D43.

  • Kosberg N2O4/UDMH rocket engine. 559 kN. UR-500 stage 1 original concept. Hardware. Isp=316s. In early Proton design would be clustered with 4 x Glushko 11D43. Abandoned in favor of 6 x Glushko 11D48, but later developed into the RD-0208 and RD-0210.

8D43 + 11D43.

  • Kosberg N2O4/UDMH rocket engine. 2247.450 kN. Design 1962. Isp=310s. Originally the first stage of the Proton was designed for 4 x fixed 11D43 and 4 x gimballed Kosberg 8D43; replaced by 6 x 11D48 from Glushko in final Proton design.

8D44.

  • Government designation of RD-0203 N2O4-UDMH rocket engine.

8D45.

  • Government designation of RD-0202 N2O4-UDMH rocket engine.

8D46.

  • Government designation of RD-0205 N2O4-UDMH rocket engine.

8D47.

  • Government designation of RD-0206 N2O4-UDMH rocket engine.

8D48.

  • Government designation of RD-0213 N2O4-UDMH rocket engine.

8D49.

  • Government designation of RD-0212 N2O4-UDMH rocket engine.

8D515.

  • Government designation of RD-217 Nitric acid-UDMH rocket engine.

8D52.

  • Government designation of RD-103 Lox-Alcohol rocket engine.

8D52M.

  • Government designation of RD-103M Lox-Alcohol rocket engine.

8D63.

  • Government designation of RD-851 Nitric acid-UDMH rocket engine.

8D67.

  • Government designation of RD-0207 N2O4-UDMH rocket engine.

8D71.

  • Article Number of RD-103 Lox-Alcohol rocket engine and RD-105 Lox-Kerosene rocket engine.

8D710.

  • Government designation of RD-119 Lox-UDMH rocket engine.

8D711.

  • Government designation of RD-109 Lox-UDMH rocket engine.

8D712.

  • Government designation of RD-218 Nitric acid-UDMH rocket engine.

8D713.

  • Government designation of RD-219 Nitric acid-UDMH rocket engine.

8D714.

  • Government designation of RD-0105 Lox-Kerosene rocket engine.

8D715.

  • Government designation of RD-0106 Lox-Kerosene rocket engine.

8D715K.

  • Government designation of RD-0107 Lox-Kerosene rocket engine.

8D715P.

  • Government designation of RD-0108 Lox-Kerosene rocket engine.

8D716.

  • Government designation of RD-111 Lox-Kerosene rocket engine.

8D719.

  • Government designation of RD-0109 Lox-Kerosene rocket engine.

8D72?.

  • Government designation of RD-106 Lox-Kerosene rocket engine.

8D721.

  • Government designation of RD-224 Nitric acid-UDMH rocket engine.

8D723.

  • Article Number of RD-250 and RD-251 N2O4-UDMH rocket engines.

8D725.

  • Glushko N2O4/UDMH rocket engine. 117 kN. Developed 1963-1970. 10 to 12 tonne thrust engine developed for an unstated military requirement. Isp=325s.

8D726.

  • Korolev Lox/Kerosene rocket engine. 66.7 kN. GR-1 Stage 3, N-11GR - V. Development based on S1.5400. Isp=350s.

8D727.

  • Government designation of RD-108-8D727 Lox-Kerosene rocket engine.

8D727K.

  • Government designation of RD-108-8D727K Lox-Kerosene rocket engine.

8D727K, 8D727P.

  • Alternate designation for RD-108-8D727 Lox-Kerosene rocket engine.

8D728.

  • Government designation of RD-107-8D728 Lox-Kerosene rocket engine.

8D74.

  • Government designation of RD-107-8D74 Lox-Kerosene rocket engine.

8D74-1958.

8D74-1959.

8D74K.

  • Government designation of RD-107-8D74K Lox-Kerosene rocket engine.

8D74PS.

  • Government designation of RD-107-8D74PS Lox-Kerosene rocket engine.

8D75.

  • Government designation of RD-108-8D75 Lox-Kerosene rocket engine.

8D75-1958.

8D75-1959.

8D75K.

  • Government designation of RD-108-8D75K Lox-Kerosene rocket engine.

8D75PS.

  • Government designation of RD-108-8D75PS Lox-Kerosene rocket engine.

8D76.

  • Government designation of RD-107-8D76 Lox-Kerosene rocket engine.

8D77.

  • Government designation of RD-108-8D77 Lox-Kerosene rocket engine.

8D811.

  • Government designation of RD-0214 N2O4-UDMH rocket engine.

9.00-KS-755.

  • Alternate designation for Star 10 Solid rocket engine.

9.0KS1800.

9KS11000.

  • Bristol Aerospace solid rocket engine. 49 kN.

9KS1660.

  • Bristol Aerospace solid rocket engine. 7.4 kN.

9KS2150.

A-10.

  • Thiel Lox/Alcohol rocket engine. 2306.8 kN. Study 1942. Planned for use in A-10. Unique dual-thrust chamber / single nozzle design, which was later shown to be not feasible technically. Isp=247s.

A1P-1.

  • Aerojet solid rocket engine. Polaris stage 1.

A1P-2.

  • Aerojet solid rocket engine. Polaris stage 2.

A2P-1.

  • Aerojet solid rocket engine. Polaris stage 1.

A-350 Booster.

  • SKB-350 N2O4/UDMH rocket engine.

A-350 Sustainer.

  • SKB-350 N2O4/UDMH rocket engine.

A3P-1.

  • Aerojet solid rocket engine. Polaris stage 1.

A-4.

  • Thiel Lox/Alcohol rocket engine. 311.8 kN. Isp=239s. Used on V-2 missile. Work began June 1936. Interim design, but went into production. Used 18 x 1.5 tonne thrust chambers, feeding common mixing chamber. Tested from 1939, mass production 1943-1945.

A-6.

  • Rocketdyne Lox/Alcohol rocket engine. 414.3 kN. Out of production. Isp=265s. Used on Redstone launch vehicle. First flight 1953. Developed from the XLR43-NA-1, an American version of the V-2 single-chamber engine tested in 1945.

A6-12.

  • Dushkin rocket engine. 39 kN. V-600. Developed 1955-62. Thrust variable 1500 - 4000 kgf.

A-7.

  • Rocketdyne Lox/Hydyne rocket engine. 416.2 kN. Out of Production. Version of Redstone engine for Jupiter-C test vehicle, with Hydyne fuel and 140 seconds burn time. Flew 1956-1959. Gas generator, pump-fed. Thrust 370 kN at sea level. Isp=265s.

A-9.

  • Thiel Lox/Alcohol rocket engine. 288.7 kN. Single chamber engine for V-2 series C, A9. Tested 1942-45. Isp=255s. Never went into production in Germany, but formed the basis for successful post-war American and French rocket engines.

AABS.

  • Rocketdyne Lox/Kerosene rocket engine. 17.779 kN. Aerospike Annular Booster and Sustainer. Pressure-fed. Booster thrust 3000 to 4000 lb vac; sustainer 1500-2000 lb vac, 257 sec specific impulse. Isp=285s.

ABL Snark JATO.

  • Hercules solid rocket engine.

Acheron.

  • French solid rocket engine.

Acid/Aniline 4000 Ibf thrust.

  • Aerojet Nitric acid/Amine rocket engine. Launch thrust 17.6 kN. Development begun December 1946. Engine design and testing

AEC.

  • Rocketdyne lox/lh2 rocket engine. 66.695 kN. Advanced Expander Cycle Engine. Expander regenerator, pump-fed. Isp=481s.

Aerobee.

  • Aerojet Nitric acid/Amine rocket engine. Aerobee. Development begun December 1947. Research with high altitude vehicle as carriers of scientific information.

Aerobee 100.

  • Aerojet solid rocket engine. 11.570 kN. Aerobee 100.

Aerobee Jr.

  • Aerojet Nitric acid/aniline rocket rocket engine. 11.5 kN.

Aerojet 2.

  • Aerojet N2O4/MMH rocket engine. 2 N. In Production. Mixture Ratio(O/F): 1.65. Isp=265s.

Aerojet 21.

  • Aerojet N2O4/MMH rocket engine. 0.021 kN. In Production. Mixture Ratio(O/F): 1.60. Isp=285s.

Aerojet 445.

  • Aerojet N2O4/MMH rocket engine. 0.445 kN. In Production. Mixture Ratio(O/F): 1.65. Isp=309s.

Aerojet 50kW.

  • Redmond electric/xenon rocket engine. Effort 2001-2003 developed a 50 kW Hall thruster in parallel to NASA's in-house development of the NASA-457M thruster.

Aerojet 62.

  • Aerojet N2O4/MMH rocket engine. 0.062 kN. In Production. Mixture Ratio(O/F): 1.65. Isp=287s.

Aerojet Sr.

  • Alternate designation for Algol 1 Solid rocket engine.

Aerojet SRB.

  • Aerojet solid rocket engine. 1270 kN. In production. Isp=275s. First flight 2002.

Aerospike Annular Booster.

  • Rocketdyne lox/lh2 rocket engine. 1111.662 kN. Aerospike Typical Annular Booster . Pressure-fed. Thrust from 50,000 to 250,000 lbs at altitude. Isp=450s.

Aerotojet.

  • Alternate designation for XCALR-2000A-1 Nitric acid-Amine rocket engine.

Aestus.

  • Friedrichshafen N2O4/MMH rocket engine. 29 kN. In production. Isp=324s. Upper stage engine for Ariane 5 developed 1988 - 1995. Original version could not be restarted; version for EPS L10 stage for Ariane 5V allowed multiple restarts. First flight 1996.

Aestus DASA/Rocketdyne.

  • Rocketdyne rocket engine. Dasa (Germany)/Rocketdyne Non-Toxic Shuttle OMS. Gas generator, pump-fed. Name later reapplied to storable propellant engine for Ariane 5.

Aestus-2.

  • Rocketdyne / DASA N2O4/MMH rocket engine. 60 kN. Production. Restartable upper-stage engine, began test firings at Lampoldshausen in February 2000.

Agate.

  • SEREB solid rocket engine. 190 kN.

Agnes.

  • CFTH-HB solid rocket engine.

Agni.

  • DRDO solid rocket engine. 700 kN.

Agni St2.

  • DRDO solid rocket engine.

Agni3.

  • DRDO solid rocket engine. 1040 kN.

Agni3 S2.

  • DRDO solid rocket engine. 314 kN.

Air Turborocket.

  • Aerojet air augmented rocket rocket engine. Development begun 1950.

AirLaunch Propane Engine.

  • Air Launch Lox/Propane rocket engine. 106.8 kN. Flow calibration, ignition and initial short duration tests completed in 2005 of this upper stage rocket engine with application to future small spacecraft launchers.

AJ10-101.

  • Aerojet Nitric acid/UDMH rocket engine. 34.3 kN. Isp=270s. Derivative of Vanguard second stage for use with Thor IRBM to produce satellite launch vehicle. First tests February 21, 1958. Flown through 1960.

AJ10-104.

  • Aerojet Nitric acid/UDMH rocket engine. 35.1 kN. Isp=278s. Stainless steel version of the basic Able engine, uprated to increase thrust 34.7 kN to 37.0 kN and to increase the duration 2-1/2 times First flight 1960.

AJ10-118.

  • Aerojet Nitric acid/UDMH rocket engine. 33.8 kN. Out of Production. Isp=271s. Engine originally developed for the Vanguard launch vehicle, and then for use on the Able and Delta upper stages and as the Apollo Service module engine. Flown 1957-1962.

AJ10-118D.

  • Aerojet Nitric acid/UDMH rocket engine. 33.7 kN. Isp=278s. Used on Delta B, Delta C, Delta D upper stages. First flight 1962.

AJ10-118E.

  • Aerojet Nitric acid/UDMH rocket engine. 35.1 kN. Isp=278s. Used on Delta E, Delta G, Delta J, Delta L, Delta M, Delta N upper stages. First flight 1965.

AJ10-118F.

  • Aerojet Nitric acid/UDMH rocket engine. 41.4 kN. Isp=306s. Used on Delta upper stage for Delta 0100, Delta 1000, N-2 boosters. First flight 1972.

AJ10-118G.

  • Aerojet Nitric acid/UDMH rocket engine. 43.414 kN. Delta G. Isp=314s.

AJ10-118H.

  • Aerojet Nitric acid/UDMH rocket engine. 43.414 kN. Delta H. Isp=319s.

AJ10-118J.

  • Aerojet Nitric acid/UDMH rocket engine. Delta J.

AJ10-118K.

  • Aerojet N2O4/Aerozine-50 rocket engine. 43.4 kN. Isp=321s. Pressure-fed engine, optimized for altitude operation, used in Delta K stage from 1989. Not regeneratively cooled; used a rubber modified silica phenolic ablative at the combustion flame front.

AJ10-131.

  • Aerojet N2O4/Aerozine-50 rocket engine. 9.8 kN. Subscale Apollo SPS. Subscale Apollo SPS

AJ10-137.

  • Aerojet N2O4/Aerozine-50 rocket engine. 97.5 kN. Apollo SPS. Out of Production. Pressure-fed engine. Used as Apollo SM engine. Isp=312s.

AJ10-138.

  • Aerojet N2O4/Aerozine-50 rocket engine. 35.6 kN. Out of production. Originally developed for Vanguard and Able. Two used, thrust uprated from 3540 kgf to 3628 kgf, with higher specific impulse, in Transtage. Isp=311s. Flown 1964-1980.

AJ10-190.

  • Manufacturer's designation of OME N2O4-MMH rocket engine.

AJ10-196.

  • Aerojet rocket engine. 40.1 kN. Liquid Throttling Engine. Liquid Throttling Engine

AJ10-198.

  • Aerojet rocket engine. 13.330 kN. Kick Stage. Kick Stage

AJ10-24.

  • Aerojet Nitric acid/aniline rocket engine. 17.8 kN.

AJ10-25.

  • Aerojet Nitric acid/aniline rocket engine. 17.8 kN.

AJ10-27.

  • Aerojet Nitric acid/aniline rocket engine. 17.8 kN.

AJ10-28.

  • Aerojet Nitric acid/JP-X rocket engine. 156 kN. SNORT Sled. Development begun early 1950s. 35,000 Ibf thrust, 2-10 second duration. JP-X was a jet fuel / hydrazine mixture.

AJ10-33.

  • Aerojet Nitric acid/UDMH rocket engine. 509 kN. SMART Sled. Development begun early 1950s. 114,000 Ibf thrust, uncooled, ceramic lined, 3 chamber system

AJ10-34.

  • Aerojet Nitric acid/aniline rocket engine. 17.8 kN.

AJ10-40.

  • Aerojet Nitric acid/UDMH rocket engine. 34.690 kN. Isp=270s. Minor modification of the Vanguard aluminum tube thrust chamber to meet the Able requirements. accomplished in the record time of only three months.

AJ10-51.

  • Aerojet rocket engine. 666 kN. Sled. Thrust variable to 33% indicated.

AJ11-21.

  • Aerojet rocket engine. 18.240 kN. Aerobee 150 & 170.

AJ11-6.

  • Aerojet Nitric acid/aniline rocket engine. 17.8 kN. Typical ideal dV=3839 m/s; gravity and drag losses = 1012 m/s.

AJ23-127.

  • Aerojet lox/lh2 rocket engine. 1010 kN. Booster. The AJ23 was a series of high-performance staged combusion engine designs. None ever made it to production. The -127 featured a gas generator cycle, 56 atm

AJ23-130.

  • Manufacturer's designation of LR87-3 Lox-Kerosene rocket engine.

AJ23-131.

  • Manufacturer's designation of LR91-3 Lox-Kerosene rocket engine.

AJ23-132.

  • Manufacturer's designation of LR87-5 N2O4-Aerozine-50 rocket engine.

AJ23-133.

  • Manufacturer's designation of LR91-5 N2O4-Aerozine-50 rocket engine.

AJ23-134.

  • Manufacturer's designation of LR87-7 N2O4-Aerozine-50 rocket engine.

AJ23-135.

  • Manufacturer's designation of LR91-7 N2O4-Aerozine-50 rocket engine.

AJ23-136.

  • Manufacturer's designation of LR87-9 N2O4-Aerozine-50 rocket engine.

AJ23-137.

  • Manufacturer's designation of LR91-9 N2O4-Aerozine-50 rocket engine.

AJ23-138.

  • Manufacturer's designation of LR87-11 AJ23-138 N2O4-Aerozine-50 rocket engine.

AJ23-139.

  • Manufacturer's designation of LR87-11 rocket engine.

AJ23-140.

  • Manufacturer's designation of LR91-11 N2O4-Aerozine-50 rocket engine.

AJ23-141.

  • Aerojet lox/lh2 rocket engine. 222.410 kN. Upper Stage. MIST - Staged Combustion.

AJ23-142.

  • Aerojet lox/lh2 rocket engine. 424.6 kN. Booster. ARES - Staged Combustion

AJ23-143.

  • Aerojet lox/lh2 rocket engine. 2213.850 kN. Booster. Pre-Development, Staged Combustion, 204 atm

AJ23-144.

  • Aerojet lox/lh2 rocket engine. 3020 kN. Booster (Pre-Development, Staged Combustion, 4000 psi). Pre-Development, Staged Combustion, 272 atm

AJ23-145.

  • Aerojet lox/lh2 rocket engine. 3020 kN. Booster (Pre-Development, Staged Combustion, 4000 psi, LOX/RJ-5 or LH2, Single Stage). Pre-Development, Staged Combustion, 272 atm, LOX/RJ-5 or LH2, Single Stage

AJ23-146.

  • Manufacturer's designation of M-1 Lox-LH2 rocket engine.

AJ23-147.

  • Aerojet lox/lh2 rocket engine. 994.3 kN. Booster. Gas generator cycle, 55 atm

AJ24-1.

  • Manufacturer's designation of YLR45-AJ-1 Nitric acid-Kerosene rocket engine.

AJ-260-1/3.

  • Aerojet solid rocket engine. 10,105 kN. Design concept 1960's. Isp=275s. Used on Saturn INT-05B launch vehicle.

AJ-260-2.

  • Aerojet solid rocket engine. 17,695.3 kN. Study 1965. Isp=263s. 260 inch solid rocket booster half length. The version tested and also proposed for use as a first stage with the Saturn IVB.

AJ-260X.

  • Aerojet solid rocket engine. 35,390.7 kN. Study 1967. Full length version of 260 inch motor tested in 1960's. Proposed for use in various Saturn and Nova configurations. Isp=263s.

AJ-260X 1/3.

  • Aerojet solid rocket engine. 11,143 kN. Design concept 1960's. Isp=263s.

AJ26-62.

  • Aeroject designation for refurbished Kuznetsov NK-33 rocket engine.

AJ60-91.

  • Aerojet rocket engine. 72.324 kN. Aerobee 350. Aerobee motor. Four Chambers

AJ60-92.

  • Aerojet rocket engine. 22.565 kN. Aerobee 200.

AJ-60C.

  • Aerojet lox/lh2 rocket engine. 280 kN. Design 2000. Isp=470s. Design announced on 3 October 2000 for a new cryogenic upper-stage engine aimed at the very large commercial spacecraft market.

Ajax.

  • Bell solid rocket engine. 11.6 kN.

Alcor.

  • Aerojet solid rocket engine. Originally developed for the Air Force as a third Stage for the Athena sounding rocket; in some applications known as Zebra. One of its main attractions was a very high mass fraction First flight 1960.

Alcor 1B.

  • Aerojet solid rocket engine. 42 kN.

Alfa.

  • Aeritalia solid rocket engine. 250 kN.

Algol 1.

  • Aerojet solid rocket engine. 470.9 kN. Isp=236s. This rocket started as a Polaris test motor with a 40 inch diameter, which at the time was the largest solid motor ever tested. First flight 1960.

Algol 2.

  • CSD solid rocket engine. 564.2 kN. Isp=255s. Used on Scout A, Scout B, Scout X-3, Scout X-4; proposed as strap-on for Titan 3BAS2. First flight 1962.

Algol 3.

  • CSD solid rocket engine. 471.9 kN. Isp=284s. Used on Advanced Scout, Scout D, Scout F, Scout G. First flight 1972.

Algol 3A.

  • CSD solid rocket engine. 464.7 kN. In Production. Isp=259s.

Algol ID.

  • CSD solid rocket engine. 440 kN.

Algol IIB.

  • CSD solid rocket engine. 400 kN.

Algol IIC.

  • CSD solid rocket engine. 436 kN.

Altair 1.

  • Alternate designation for X-248 Solid rocket engine.

Altair 1A.

  • Alternate designation for X-248A Solid rocket engine.

Altair 2.

  • Alternate designation for X-258 Solid rocket engine.

Altair 3.

AMPS-1.

  • Rocketdyne lox/lh2 rocket engine. 80.032 kN. Advanced Maneuvering Propulsion System Booster. Pressure-fed. Isp=468s.

Antares 1A.

  • Alternate designation for X-254 Solid rocket engine.

Antares 2.

  • Alternate designation for X-259 Solid rocket engine.

Antares 3.

  • Government designation of Star 31 Solid rocket engine.

Antares 3A.

  • Alternate designation for X-259A Solid rocket engine.

Apogee Motor.

  • Manufacturer's designation of DFH-2 AKM Solid rocket engine.

AR1.

  • Rocketdyne h2o2/kerosene rocket engine. 22.260 kN. Engine for FJ-4F naval interceptor.

AR2-3.

  • Rocketdyne h2o2/kerosene rocket engine. 29.341 kN. Future-X Demonstrator Engine. Gas generator, pump-fed. Heritage technology in evaluation for current applications. X-37 Reusable Upper Stage Vehicle. Isp=245s.

Arcon.

  • ARC solid rocket engine. 4.5 kN.

Arcon booster.

  • ARC solid rocket engine. 14 kN.

Ares.

  • Aerojet N2O4/Aerozine-50 rocket engine. 440 kN. SSTO ICBM. Development 1968. Isp=370s. Advanced Rocket Engine System - single shaft turbopump, integrated single pressure vessel in a staged combustion cycle configuration.

Arrow.

  • GCR solid rocket engine. 10 kN.

ASE.

  • Rocketdyne lox/lh2 rocket engine. 88.926 kN. Advanced Space Engine. Staged combusion, pump-fed. Isp=473s.

Asp II.

  • Cooper solid rocket engine. 26 kN.

ASROC.

  • Multiple-source solid rocket engine.

Astris.

  • German N2O4/Aerozine-50 rocket engine. 23.3 kN. Isp=310s. Used on Europa launch vehicle. First flight 1964.

Astrobee D.

  • Aerojet solid rocket engine. 8.9 kN.

Astrobee F.

  • Aerojet solid rocket engine. 36.4 kN.

Atar 9K.

  • SNECMA turbojet engine. 48 kN. Out of Production. Isp=2020s.

ATCRE.

  • Notional lox/lh2 rocket engine. 1280 kN. Study 1985. Isp=490s. Used on Sanger II launch vehicle.

ATE.

  • Rocketdyne N2O4/MMH rocket engine. 20 kN. Developed 1990's. Advance technology engine for maneuvering stages. Isp=347s.

ATS 5 cm.

  • EOS electric/cesium rocket engine. 0.089 mN. Flown in 1968-1969. Isp=6700s. Thruster for the ATS-4 and ATS-5 tests; consisted of two contact ionization engines using cesium propellant.

ATS 8 cm.

  • EOS electric/cesium rocket engine. 4.5 mN. Flown in 1974. Isp=6700s.Thruster for the ATS-6 test; consisted of two electron bombardment engines using cesium propellant. The thruster anode diameter was 8 cm, and a cesiated tungsten neutralizer was used.

Aurore.

  • SNECMA solid rocket engine. 10.5 kN.

AUS 51.

  • Manufacturer's designation of RSA-3-3 Solid rocket engine.

B-2C.

  • Rocketdyne Lox/Kerosene rocket engine. Atlas A. Launch thrust 1374 kN. Atlas Booster. Gas generator, pump-fed. Thrust and specific impulse values are at sea level. First flight 1958.

BA-3200.

  • Beal H2O2/Kerosene rocket engine. 14,100 kN. Development 1990's. Pressure-fed engine with composite ablative chamber and nozzle. Helium pressurant. Thrust declines to 70% of initial value before shutdown. Isp=259s.

BA-44.

  • Beal H2O2/Kerosene rocket engine. 196 kN. Development 1990's. Pressure-fed restartable engine with composite ablative chamber and nozzle. Helium pressurant. Thrust declines to 50% of initial value before shutdown. Isp=300s.

BA-810.

  • Beal H2O2/Kerosene rocket engine. 3600 kN. Development 1990's. Pressure-fed engine with composite ablative chamber and nozzle. Helium pressurant. Thrust declines to 50% of initial value before shutdown. Isp=282s.

Bantam.

  • Bristol solid rocket engine.

Bantam 2.

  • Bristol solid rocket engine.

Bantam 3.

  • Bristol solid rocket engine.

BB7.

  • Bristol Aerospace solid rocket engine. 1 kN.

BE-3.

  • WRE solid rocket engine. 34 kN.

BE-3B1.

  • Hercules solid rocket engine. 34 kN.

Belier II.

  • Sud solid rocket engine. 20 kN.

Belisama.

  • CFTH-HB solid rocket engine. 24 kN.

Bell 8048.

  • Bell Nitric acid/UDMH rocket engine. 68.9 kN. Out of production. Isp=276s. Used on Agena A, derived from Rascal engine. Regeneratively cooled; used drilled holes to create the same effect as more costly stacked spaghetti rubes. First flight 1959.

Bell 8081.

  • Bell Nitric acid/UDMH rocket engine. 71.2 kN. Out of production. Isp=285s. Used on Agena B stage atop Thor and Atlas. First flight 1960.

Bell 8096.

  • Bell Nitric acid/UDMH rocket engine. 71.2 kN. Out of production. Isp=292s. Used in Agena stage on top of Thor, Atlas, and Titan launch vehicles. First flight 1963.

Bell 8247.

  • Bell Nitric acid/UDMH rocket engine. 71.2 kN. Out of Production. Isp=291s. Version of Agena engine for the Gemini-Agena Target Vehicle. Minimum capability of five restarts and a demonstrated capability of fifteen restarts. First flight 1963.

Black Arrow-3.

  • British solid rocket engine. 29.4 kN. Out of production. Isp=278s. Used on Black Arrow launch vehicle. First flight 1969.

Booster Engine One.

  • Alternate designation for XLR43-NA-1 Lox-Alcohol rocket engine.

BORD 1.

  • Manufacturer's designation of P320 Lox-LH2 rocket engine.

BPT-2000.

  • Redmond electric/xenon rocket engine. 120 mN. In Production. Hall effect thruster. Nominal power input 2200 W at 350 V. Isp=1765s.

BPT-4000.

  • Redmond electric/xenon rocket engine. 270 mN. In Production. Hall effect thruster. Nominal power input 4500 W at 350 V. Isp=1950s.

BPT-600k.

  • Redmond electric/xenon rocket engine. 0.030 kN. In Development, 2005-2006. Isp=1800s. Began as 1995 contract for 600kWe Hall thruster electric propulsion system designed for future interplanetary manned spacecraft.

Bullpup.

  • Multi-source solid rocket engine. 111 kN.

Burlak Stage 1.

  • Russian N2O4/UDMH rocket engine. 360 kN. Burlak stage 1. Development ended 1992. Isp=320s. Air launched from Tu-160 at 13,500 m, Mach 1.7 release conditions.

Burlak Stage 2.

  • N2O4/UDMH rocket engine. 98 kN. Burlak stage 2. Development ended 1992. Isp=330s. Air launched from Tu-160 at 13,500 m, Mach 1.7 release conditions.

Burner 2A.

  • Government designation of Star 26B Solid rocket engine.

C3-1.

  • Hercules solid rocket engine.

C3-2.

  • Herculessolid rocket engine.

C4-1.

  • Hercules solid rocket engine.

C4-2.

  • Hercules solid rocket engine.

Cajun.

  • Thiokol solid rocket engine. 36 kN.

Canopus.

  • IIAE solid rocket engine.

Castor 120.

  • Thiokol solid rocket engine. 1650 kN. Isp=280s. Motor similar in size to the Peacekeeper missile stage 1 motor; filled the gap between Castor 4A and the large segmented motors. First flight 1989.

Castor 2.

  • Alternate designation for TX-354-3 Solid rocket engine.

Castor 4.

  • Thiokol solid rocket engine. 407.2 kN. Series of motors used as Delta strap-on boosters and as first and upper stages for low-cost all-solid-propellant designs. Isp=261s. First flight 1975.

Castor 4A.

  • Thiokol solid rocket engine. 478.3 kN. Out of production. Isp=266s. Castor 4A improved Delta performance by 11% by replacing the old fuel with HTPB propellant. Used in Delta 6900; Atlas IIAS; Castor 4A. First flight 1982.

Castor 4AXL.

  • Thiokol solid rocket engine. 599.8 kN. In production. Isp=269s. Strap-on booster version, first tested May 1992. Its 30% performance increase would improve performance of Atlas and other vehicles. First flight 2001.

Castor 4B.

  • Alternate designation for Castor 4BXL Solid rocket engine.

Castor 4B.

  • Thiokol solid rocket engine. 430.6 kN. Out of production. The Castor 4B, which incorporated thrust vector control in the series for the first time, was developed for ESA's Maxus (first flown in 1991). Isp=281s. First flight 1982.

Castor 4BXL.

  • Thiokol solid rocket engine. 429 kN. In Production. Isp=267s. ORBEX version, combined the 4XL motor with 4B's TVC system (6 degree).

CD Module.

  • Notional lox/lh2 rocket engine. 7361 kN. Study 1969. Isp=420s. CD Modules - conceptual engines of various thrusts, according to design - were clustered in Martin Marietta Nova designs

Centrojet.

  • Aerojet Nitric acid/Amine rocket engine. R&D. Launch thrust 2.25 kN. Work begun June 1943. Torque to rotate the main shaft of the propellant pumps was developed by the canted engine nozzles themselves at the aft end of the shaft. Abandoned 1945.

Chamber/single nozzle.

  • Notional lox/lh2 rocket engine. 13,231 kN. Study 1963. Isp=455s. Before moving to favored plug nozzle designs, Bono at Douglas considered having multiple combustion chambers exhaust into a single large nozzle to obtained Improved Specific Impulse.

Chariot.

  • Bell exotic LF2/Hydrazine rocket engine. 155.9 kN. Titan 3 upper stage. Developed 1960's. Engine developed for high-energy replacement of Titan 3 transtage in late 1950's / early 1960's. Not flown due to toxicity of propellants.

Chick.

  • RO solid rocket engine. 60 kN.

Cirrus I.

  • DRG solid rocket engine. 5 kN.

Cirrus II.

  • DRG solid rocket engine. 18 kN.

Co-axial turboramjet.

  • Notional lh2-fuelled ramjet engine. 250 kN. Study 1985. Isp=1200s. Used on Sanger II launch vehicle.

Cobra.

  • Pratt and Whitney lox/lh2 rocket engine. 4500 kN. Design 2003. Proposed as a long-life, moderate-to high-thrust, reusable booster engine that incorporated a safe, low-cost, low-risk, LH2/LOX single burner, using a fuel-rich, staged combustion cycle.

Cold Gas Thruster Module.

  • Parker Bertea nitrogen cold gas thruster. 0.111 kN. In Production. Isp=68s. Designed to provide triaxial attitude control for small launch vehicles. The module comprised three cold gas thrusters operated by integral independent solenoid valves.

Corporal.

  • Firestone Nitric acid/Aniline-Furfuyrl alcohol rocket engine. 89 kN.

Corporal E.

  • Douglas/JPL Nitric acid/Aniline-Furfuyrl alcohol rocket engine. 89 kN.

CSXT.

  • CSXT solid rocket engine.

Cuckoo 4.

  • RO solid rocket engine.

Cuckoo IA.

  • RO solid rocket engine. 80 kN.

Cuckoo IB.

  • RO solid rocket engine. 80.9 kN.

Cuckoo II.

  • RO solid rocket engine. 36.5 kN.

Cygnus 15.

  • Thiokol solid rocket engine. 22 kN.

Cygnus 20.

  • Thiokol solid rocket engine. 30 kN.

Cygnus 5.

  • Thiokol solid rocket engine. 2.3 kN.

CZ-1C-3.

  • Chinese N2O4/UDMH rocket engine. 107.9 kN. Development ended 1988. Isp=287s. Used on CZ-1C launch vehicle.

CZ-1D-3.

  • Fourth Academy solid rocket engine. Out of production. Motor for proposed CZ-1D launch vehicle. Isp=291s. First flight 1995.

D-1.

  • Kosberg isopropylnitrate monopropellant rocket engine. 39 kN. Developed 1955-56. Second thrust level at 50%. Explosion of D-1 on test bench in 1956 forced stop of work with mono-propellant OT-152. Sea level thrust 39 kN.

D-100-II.

  • TsNIIMASH electric/xenon rocket engine. 65 mN. Development. Isp=1600s. Hall effect thruster with anode layer, designed for satellite orbital raising. Taken to engineering model stage.

D-18T.

  • Lotarev turbofan engine. 229.4 kN. Used on An-225 launch aircraft for Interim HOTOL, MAKS concepts. Development ended 1988. Isp=9000s.

D-2.

  • Polyarniy Lox/Kerosene rocket engine. 1373 kN. R-3. Out of Production. Competing engine for 3000 km range IRBM design to study problems of long-range rockets. Developed from April 1947 until cancellation. Isp=288s.

D-20.

  • TsNIIMASH electric/xenon rocket engine. 1.5 mN. Development. Isp=1400s. Hall effect thruster with anode layer, designed for satellite station-keeping and attitude control. Taken to engineering model stage.

D-38.

  • Manufacturer's designation of TAL-38 Electric-Xenon rocket engine.

D50.

  • Yuzhnoye electric/xenon rocket engine. 48 mN. Development. Isp=1700s. Hall engine electric jet propulsion system intended for use by spacecraft for inter-orbital transfer, orbit correction, and stabilization.

D-50G1.

  • Manufacturer's designation of LR39 Lox-Alcohol rocket engine.

D-5-1.

  • Lockheed solid rocket engine.

D-5-2.

  • Lockheed solid rocket engine.

D-54.

  • Manufacturer's designation of RD-54 Lox-LH2 rocket engine.

D-55.

  • Manufacturer's designation of TAL-WSF Electric-Xenon rocket engine.

D-57.

  • Alternate designation for RD-57 Lox-LH2 rocket engine.

D-68.

  • Alternate designation for RD-68 Nitric acid-UDMH rocket engine.

D-68M.

  • Alternate designation for RD-855 N2O4-UDMH rocket engine.

D-68M.

  • Alternate designation for RD-68M N2O4-UDMH rocket engine.

D-69.

  • Alternate designation for RD-69 Nitric acid-UDMH rocket engine.

D-69M.

  • Alternate designation for RD-856 and RD-69M N2O4-UDMH rocket engine.

D-7.

  • Kosberg isopropylnitrate monopropellant rocket engine. 11.8 kN. Missile by Toropov. Out of Production. Intended for air-air missile by I I Toropov. Uncooled thrust chamber. Sea level thrust 11.8 kN.

Demon.

  • WRE solid rocket engine.

DF-1.

  • CALT Liquid oxygen/Alcohol rocket engine. 270 kN.

DF-11.

  • Sanjiang solid rocket engine. 93.2 kN.

DF-15.

  • China ARMT solid rocket engine.

DF-21-1.

  • Shanxi solid rocket engine.

DF-21-2.

  • Shanxi solid rocket engine.

DF-31-1.

  • Shanxi solid rocket engine.

DF-31-2.

  • Shanxi solid rocket engine.

DF-31-3.

  • Shanxi solid rocket engine.

DFH-2 AKM.

  • Fourth Academy solid rocket engine. 43.460 kN. DFH series apogee kick motor. Out of Production. Isp=287s. First flight 1984. First use in China of glass fibre wound cases, carbon/carbon nozzle throat insert material, contoured divergent nozzle.

DMT-600.

  • Isayev N2O4/UDMH rocket engine. 0.600 kN. In Production. Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 6,000 ignitions Isp=300s.

DMT-600 MMH.

  • Isayev N2O4/MMH rocket engine. 0.600 kN. Hermes. In Production. Version of DMT-600 using MMH in place of UDMH, adaptation to western market (was discussed for European Hermes space plane project). 6,000 ignitions Isp=305s.

DOK-10.

  • Isayev monopropellant rocket engine. 10 N. In Production. Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by an iridium-based catalyst, which heated to increase stability. 40,000 ignitions Isp=229s.

DOK-50.

  • Isayev monopropellant rocket engine. 0.050 kN. In Production. Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by an iridium-based catalyst, which heated to increase stability. 40,000 ignitions Isp=229s.

Dolphin.

  • Starstruck Lox/Solid hybrid rocket engine. 155 kN.

DOT-25.

  • Isayev monopropellant rocket engine. 0.025 kN. In Production. Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by a wire catalyst, which is electrically heated to 620 K. 60,000 ignitions Isp=234s.

DOT-5.

  • Isayev monopropellant rocket engine. 5 N. In Production. Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by a wire catalyst, which is electrically heated to 620 K. 550,000 ignitions Isp=230s.

DS.

  • MITT solid rocket engine.

DST-100.

  • Isayev N2O4/UDMH rocket engine. 0.100 kN. In Production. Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 10,000 ignitions Isp=276s.

DST-100A.

  • Isayev N2O4/UDMH rocket engine. 0.100 kN. In Production. Bi-propellant hypergolic engine, pressure-fed. Larger nozzle and reduced chamber pressure to increase performance and lifetime in comparison to DST-100. 450,0000 ignitions. Isp=304s.

DST-200.

  • Isayev N2O4/UDMH rocket engine. 0.200 kN. In Production. Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 10,000 ignitions Isp=280s.

DST-200A.

  • Isayev N2O4/UDMH rocket engine. 0.20 kN. In Production. Bi-propellant hypergolic engine, pressure-fed. Larger nozzle and reduced chamber pressure to increase performance and lifetime compared to DST-200. 100,0000 ignitions. Isp=300s.

DST-25.

  • Isayev N2O4/UDMH rocket engine. 0.025 kN. In Production. Bi-propellant hypergolic (self-igniting) engine, pressure-fed. 300,000 ignitions Isp=285s.

Dual Mode-Liquid Apogee Engine.

  • TRW MON/Hydrazine rocket engine. 0.454 kN. In Production. Isp=314s. First Flight: April 1991. Burn Time 24,000 sec total, with a 3600 sec maximum single burn. Hypergolic ignition via 28 V current to an on/off bi-propellant torque motor valve.

Dushkin 3M9.

  • Dushkin solid rocket engine. 3M9 Kub. Out of Production.

E-1.

  • Rocketdyne Lox/Kerosene rocket engine. 1885 kN. Study 1957. Developed by USAF in late 1950's. Cancelled and decision to go direct to 1,500,000 lbf F-1 as next step. Booster applications. Gas generator, pump-fed. Isp=290s.

ED-140.

  • Glushko rocket engine. 68 kN. Glushko built this experimental engine, the next phase of the German Lilliput concept, in 1951. Configuration led to the successful RD-107 engines of the R-7.

EKR Ramjet.

  • Bondaryuk ramjet engine. 6.130 kN. EKR Stage 2. Study 1953. Isp=1580s. Study for an experimental winged cruise missile. Not developed but formed basis for Burya and Buran missiles.

Emilie.

  • CFTH-HB solid rocket engine.

End Hall Thruster.

  • UM-NASA electric/lh2 rocket engine. 1 kW arcjet, ran on H2, N2, or a mixture, at about 12A, 1 kW, peak around 600s Isp, (20-30% efficiency). Isp=600s.

EPKM.

  • Fourth Academy solid rocket engine. 189.994 kN. Isp=292s. Chinese kick stage for use on CZ-2E for launch of Asiasat-2 and Echostar-1. Diameter increased to 1.7 m in comparison to basic 1.4 m diameter motor. Spin stabilised. First flight 1990.

ESEX Arcjet.

  • Redmond electric/ammonia rocket engine. 2 N. In Production. Isp=800s. Electric Propulsion Space Experiment) program begun 1989 under the then Air Force Astronautics Lab. Flew once in 1999 on board the ARGOS satellite.

Excalibur.

  • Bristol solid rocket engine.

Expansion-Deflection 10k.

  • Rocketdyne N2O4/Aerozine-50 rocket engine. Launch thrust 44.463 kN. Expansion-Deflection Booster (10,000 lb thrust). Pressure-fed. Thrust and specific impulse values are at sea level.

Expansion-Deflection 50k.

  • Rocketdyne N2O4/Aerozine-50 rocket engine. Launch thrust 222.326 kN. Expansion-Deflection Booster (50,000 Ib thrust). Pressure-fed. Thrust and specific impulse values are at sea level.

F-1.

  • Rocketdyne Lox/Kerosene rocket engine. 7740.5 kN. Isp=304s. Largest liquid rocket engine ever developed and flown. Severe combustion stability problems were solved during development and it never failed in flight. First flight 1967.

F100-100.

  • Pratt and Whitney turbofan engine. 63.9 kN. In Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=1552s.

F101.

  • Pratt and Whitney turbofan engine. 75.6 kN. In Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=1980s.

F-1A.

  • Rocketdyne Lox/Kerosene rocket engine. 9189.6 kN. Study 1968. Designed for booster applications. Gas generator, pump-fed. Isp=310s.

Falcon.

  • Hughes solid rocket engine.

Falcon SLV-1.

  • Michoud Lox/Solid hybrid rocket engine. 1400 kN. First stage. Study 2005. Part of the USAF FALCON program to assess hybrid propulsion applications for a responsive small launch vehicle.

Falcon SLV-2.

  • Michoud hybrid rocket Lox/Solid engine. 133 kN. Upper stages. Study 2005. Part of the USAF FALCON program to assess hybrid propulsion applications for a responsive small launch vehicle.

Fastrac.

  • Huntsville Lox/Kerosene rocket engine. 269 kN. Development ended 1996. Isp=310s. Used on X-34A launch vehicle. Intended to demonstrate lower cost in a reusable simple turbopump rocket engine.

FastTrack.

  • Notional Lox/Kerosene rocket engine. 44.1 kN. Design concept. NASA Marshall Space Flight Center prototype experimental engine that led to Fastrac low-cost engine for X-34. Isp=348s.

FFAR.

  • Multiple-source American solid rocket engine. 3.6 kN.

FFK.

  • ERNO solid rocket engine.

FLEXEM.

  • Rocketdyne exotic ClF3/Hydrazine rocket engine. 48.905 kN. Flexible Energy Management. Pressure-fed. Sustainer 267-4000 lb thrust vacuum, specific impulse 260 seconds. Isp=275s.

FSW Retromotor.

  • Fourth Academy solid rocket engine. 40.660 kN. In Production. Isp=280s. Retrorocket designed for deorbit of FSW recoverable satellite. First flight 1975.

FW-4D.

  • Thiokol solid rocket engine. 25 kN. Isp=287s. Kick stage motor for Delta E, Delta L. First flight 1965.

FW-4S TEM640.

  • Thiokol solid rocket engine. 27.4 kN. Isp=280s. Used on Advanced Scout, Scout B, Scout D, Scout F, Scout G. First flight 1965.

FY-25.

  • Beijing Wan Yuan rocket engine. In Production. Chinese liquid apogee insertion motor. 1800 seconds rated firing time. First flight 1994.

G-1.

  • Rocketdyne exotic LF2/Hydrazine rocket engine. 53.5 kN. Atlas upper stage. Developed 1960's. Engine developed for replacement of Agena upper stage in late 1950's. Not flown due to toxicity of propellants. NOMAD Upper Stage System. Pressure-fed. Isp=357s.

G-26.

  • Manufacturer's designation of XLR83-NA-1 Lox-Kerosene rocket engine.

G-38.

  • Manufacturer's designation of LR83-NA-1 Lox-Kerosene rocket engine.

Gamma 2.

  • Bristol Siddley H2O2/Kerosene rocket engine. 68.2 kN. Out of production. Isp=265s. Used on Black Arrow launch vehicle. First flight 1969.

Gamma 201.

  • Saunders-Roe H2O2/Kerosene rocket engine. 75 kN.

Gamma 301.

  • Saunders-Roe H2O2/Kerosene rocket engine. 75 kN.

Gamma 8.

  • Bristol Siddley H2O2/Kerosene rocket engine. 234.8 kN. Out of production. Isp=265s. Used on Black Arrow launch vehicle. First flight 1969.

Garvey Aerospike.

  • Garvey Lox/Alcohol rocket engine. Development ended 2005. Launch thrust .044 kN. Single-chamber, liquid-propellant, annular aerospike engine.

GCRC.

  • GCR solid rocket engine. 11.6 kN. Isp=230s. Used on Vanguard launch vehicle. First flight 1957.

GDU-10.

  • Alternate designation for RD-109 Lox-UDMH rocket engine.

GEM 40.

  • Hercules solid rocket engine. 499.2 kN. Air-ignited versions have nozzle ratio of 16:1, specific impulse of 283.4 sec. Isp=274s. Used on Delta 7925 launch vehicle. First flight 1990.

GEM 46.

  • Hercules solid rocket engine. 608.1 kN. Air-ignited versions have nozzle ratio of 24.8:1, specific impulse of 284 sec. Isp=274s. First flight 1998.

GEM 60.

  • Hercules solid rocket engine. 851.5 kN. In production. Isp=275s. Used as strap-on boosters for Delta 3 , Delta IV Medium. First flight 2002.

General Technology.

  • Rocketdyne N2O4/MMH rocket engine. 17.779 kN. General Technology . Pressure-fed. Isp=295s.

GF-02.

  • Fourth Academy solid rocket engine. 181 kN. CZ-1 launch vehicle. Out of production. Isp=254s. First upper stage, zero-G, vacuum-start solid rocket motor developed in China. Inserted China's first satellite into orbit on 24 April 1970.

Glushko C.

  • Glushko storable lqiuid rocket engine. 29,400 kN. Study 1970. Glushko studied liquid propellant engines of 'several thousand tonnes thrust' in the period 1963-1970. Largest thrust chamber ever tested in Russia was Glushko's RD-270 of 680 tf.

Goldfinch.

  • Royal Ordnance solid rocket engine. Out of production. Used on Skylark launch vehicle.

Goldfinch II.

  • BAJ solid rocket engine.

Goldfinch IIA.

  • BAJ solid rocket engine. 175 kN.

Goose II.

  • RO solid rocket engine. 22 kN.

Gosling.

  • RO solid rocket engine. 152 kN.

Gosling 4.

  • RO solid rocket engine. 137 kN.

H-1.

  • Rocketdyne Lox/Kerosene rocket engine. 947.7 kN. Saturn l/lB. Designed for booster applications. Gas generator, pump-fed. Isp=289s. First flight 1961.

H-1-3.

  • Nissan solid rocket engine. 77 kN. Isp=291s. Used on H-1 launch vehicle. First flight 1986.

H1500.

  • Notional Lox/Solid hybrid rocket engine. 931.3 kN. Design 1988. Isp=284s. Used on Industrial Launch Vehicle launch vehicle.

H-1b.

  • Rocketdyne Lox/Kerosene rocket engine. 1030.2 kN. Isp=296s. First flight 1966.

H-1c.

  • Rocketdyne Lox/Kerosene rocket engine. 1130 kN. Study Saturn IB-A, Saturn IB-B, 1965. Isp=296s.

H-2/J-1-1.

  • Nissan solid rocket engine. 1556.6 kN. In Production. Used in J-1-1. Isp=273s.

H-2-0.

  • Nissan solid rocket engine. 1540 kN. Isp=273s. Used as strap-on booster on H-2, first stage on J-1. First flight 1994.

Hall Electric Thruster.

  • TsNIIMASH / Rocketdyne electric/xenon rocket engine. 3 N. Development. Isp=1600s. Satellite orbit raising and station-keeping applications. Electric, pressure-fed. Variable 80 mN - 3.0 N thrust, specific impulse 1600 to 3500 seconds.

Helios Stage 1.

  • Notional lox/lh2 rocket engine. 1667 kN. Study 1960. Engines for booster stage with Lox tanks only to take nuclear second stage to stratosphere. Isp=400s. Helios A, B, C studies.

Hercules.

  • Hercules solid rocket engine. 15,565.8 kN. In development. Isp=286s. Planned replacement for shuttle solid rocket boosters after Challenger disaster. A billion dollars spent in development, but contract terminated. NASA decided to stay with Thiokol RSRM.

Hermes A-1.

  • GE Nitric acid/Tonka rocket engine. 71 kN.

Hermes A-3A.

  • GE Nitric acid/Tonka rocket engine. 80 kN.

Hermes A-3B.

  • GE Nitric acid/Tonka rocket engine. 100 kN.

HG-3.

  • Rocketdyne lox/lh2 rocket engine. 1400.7 kN. Study 1967. Isp=451s. High-performance high-pressure chamber engine developed from J-2. Considered for upgrades to Saturn V launch vehicle upper stages. Technology led to Space Shuttle Main Engines.

HG-3-SL.

  • Rocketdyne lox/lh2 rocket engine. 1387 kN. Study 1966. Isp=450s. High-performance high-pressure chamber engine developed from the J-2, fitted with lower-expansion nozzle for sea level use on Saturn INT-17. Technology led to Space Shuttle Main Engines.

HIBEX.

  • Boeing solid rocket engine.

HIMES.

  • Mitsubishi lox/lh2 rocket engine. 137.3 kN. Design 1999. Isp=452s. Used on H-2 HIMES launch vehicle.

HiPAT.

  • Redmond N2O4/MMH rocket engine. 0.445 kN. In Production. High performance liquid apogee thruster. Isp=323s.

HIVHAC.

  • NASA Cleveland electric/xenon rocket engine. 430 mN. Isp=2800s. HIVHAC offered mission benefits compared to the 4000s NEXT engine for deep space missions.

HM-10.

  • SEP, Ottobrunn lox/lh2 rocket engine. 61.8 kN. Developed 1990's. Engine for potential Ariane 5 upper stage. Isp=443s.

HM-16.

  • Mitsubishi solid rocket engine.

HM7-A.

  • SEP, Ottobrunn lox/lh2 rocket engine. 61.7 kN. Development begun 1973. Out of production. Isp=443s. Used on Ariane 1 launch vehicle. First flight 1979.

HM7-B.

  • SEP, Ottobrunn lox/lh2 rocket engine. 70 kN. Isp=447s. Increased performance version of the HM-7 engine for the Ariane 2 and 3. Combustion chamber pressure raised from 30 to 35 bar and nozzle extended. First flight 1984.

Hopi 2.4KS5600.

  • RPI solid rocket engine. 28 kN.

Hopi 3.0KS4000.

  • RPI solid rocket engine. 18 kN.

Hopi 9.0KS1800.

  • RPI solid rocket engine. 7.7 kN.

HOTROC.

  • NOTS solid rocket engine. 63.2 kN.

HP-1.

  • Notional lox/lh2 rocket engine. 6536 kN. Study 1963. Operational date would have been December 1974. Isp=451s. Used in Martin Nova studies MM 24G, MM 33.

HPAG.

  • NOTS solid rocket engine. 12.5 kN.

HTR.

  • Nammo Lox/Solid hybrid rocket engine. 30 kN.

Hustler APU.

  • Aerojet isopropylnitrate monopropellant rocket engine. B-58. Development begun 1953. APU for the Hustler 'controlled bomb pod', which was really a long range air to surface strategic missile

HVAR.

  • CIT solid rocket engine. 25 kN. HVAR.

Hydac.

  • Aerojet solid rocket engine. 58.7 kN.

Hyperion.

  • eAC hybrid N2O/Solid rocket engine. 6 kN.

HYSR.

  • LMSS Lox/Solid hybrid rocket engine. 270 kN.

IAI-Arrow-1.

  • IAI solid rocket engine.

IAI-Arrow-2-1500.

  • IAI solid rocket engine.

IAI-Arrow-2-500.

  • IAI solid rocket engine.

IAPS.

  • Hughes electric/mercury rocket engine. Isp=2500s. Ion Auxiliary Propulsion System work took place in the 1974-1983. Flight ready article prepared, but not flown due to budget cuts.

Icarus.

  • ERAU solid rocket engine. 16 kN.

Icarus St2.

  • ERAU solid rocket engine. 4.1 kN.

Improved Electrothermal Hydrazine Thruster.

  • Alternate designation for MR-502 Hydrazine rocket engine.

Integrated Powerhead Demonstrator.

  • Manufacturer's designation of IPD Lox-LH2 rocket engine.

Ion.

  • Notional electric/mercury rocket engine. 0.275 kN. Study 1981. Conceptual ion engine design of the 1970's for a shuttle-sized upper stage. Isp=5300s.

IPD.

  • Rocketdyne lox/lh2 rocket engine. 1100 kN. Development ended 2006. Integrated Powerhead Demonstrator, end goal was flight-rated, full-flow, hydrogen-fueled, staged combustion rocket engine in the 1.1-million-newton thrust class.

Iris.

  • BPD solid rocket engine. 29.4 kN. Out of production. Isp=291s. Used on CZ-1M launch vehicle.

Isayev 218.

  • Isayev Nitric acid/Amine rocket engine. 218 (S-25 system). Out of Production. Launch thrust 166 kN.

Isayev DOS-3/4.

  • Isayev Nitric acid/UDMH rocket engine. 3.920 kN. DOS-3/4. Out of Production.

Isayev P-15.

  • Isayev Nitric acid/Amine rocket engine. 11.9 kN. P-15 Termit. Out of Production. Designation unknown. Thrust range 11.895-5.43 kN.

Isayev Polet/IS.

  • Isayev N2O4/UDMH rocket engine. 3.920 kN. Polet/IS. Out of Production.

Isayev R-17.

  • Isayev Nitric acid/Kerosene rocket engine. 131.2 kN. R-17. Out of production. Designation unknown. First flight 1961.

Isayev TKS attitude.

  • Isayev N2O4/UDMH rocket engine. 0.390 kN. TKS, Almaz. In Production.

Isayev V-750V.

  • Isayev Nitric acid/Amine rocket engine. 30.4 kN. SAM-missile V-750V. Out of Production. Designation unknown.

Izotov LK-700.

  • Izotov N2O4/UDMH rocket engine. 131 kN. LK-700. Developed 1966-69.

Izotov UR-100 stage 2 vernier.

  • Izotov N2O4/UDMH rocket engine. 58 kN. UR-100 stage II vernier. Out of Production.

J-2.

  • Rocketdyne lox/lh2 rocket engine. 1033.1 kN. Study 1961. Isp=421s. Used in Saturn IVB stage in Saturn IB and Saturn V, and Saturn II stage in Saturn V. Gas generator, pump-fed. First flight 1966.

J-2S.

  • Rocketdyne lox/lh2 rocket engine. 1138.5 kN. Developed 1965-1969. Isp=436s. J-2 version proposed for Saturn follow-on vehicles, using results of the J-2X technology program. The engine was simplified while offering improved performance.

J-2S Linear Aerospike.

  • Alternate designation for XRS-2200 Lox-LH2 rocket engine.

J-2-SL.

  • Rocketdyne lox/lh2 rocket engine. 996.7 kN. Study 1966. Sea level version of J-2 with reduced expansion ratio proposed for Saturn II first stage use. Isp=390s.

J-2T-200K.

  • Rocketdyne lox/lh2 rocket engine. 889.3 kN. Study 1965. Proposed for later versions of Saturn V. Toroidal aerospike plug nozzle version of J-2. Isp=435s.

J-2T-250K.

  • Rocketdyne lox/lh2 rocket engine. 1111.6 kN. Study 1967. Proposed for later versions of Saturn V. Toroidal aerospike plug nozzle version of J-2. Isp=441s.

J-2X.

  • Rocketdyne lox/lh2 rocket engine. 1310 kN. Ares I launch vehicle second stage. In development 2006-2016. Isp=448s. Began as an update to the J-2 engine of the 1960s, but final design was all-new, 20% more thrust, but double the weight.

J57-19.

  • Pratt and Whitney turbojet engine. 53.8 kN. Out of production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=5142s. Used on B-52 launch aircraft for X-15A. First flight 1959.

J57-8.

  • Pratt and Whitney turbojet engine. 45.4 kN. Out of production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=1414s. Used on Caleb launch vehicle. First flight 1960.

J58.

  • Pratt and Whitney turbojet engine. Out of Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=2084s.

J75-17.

  • Pratt and Whitney turbojet engine. 71.6 kN. Out of Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=1800s.

J79- 5.

  • GE turbojet engine. 45.8 kN. Out of Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=2020s.

J79-17.

  • GE turbojet engine. 52.8 kN. Out of Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=2020s.

J85-GE-5.

  • GE turbojet engine. 34.3 kN. Carries SpaceShipOne to release point 65 km from Mohave Airport base, then releases it at 15 km altitude at 215 kph. Wing area 43.5 sq m. Isp=2000s.

J93-3.

  • GE turbojet engine. 86.7 kN. Out of Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=2084s.

Javelin 3.

  • Aerojet solid rocket engine. 93 kN.

JCR.

  • Nissan solid rocket engine.

Jericho II.

  • Sud solid rocket engine. 20 kN.

JIC.

  • Aerojet rocket engine. 10.680 kN. JIC. Classified application

JP-5/H2O2.

  • Notional H2O2/Kerosene rocket engine. 63 kN. Study 1993. Isp=335s. Engine for Black Horse winged, single stage to orbit launch vehicle using aerial refueling.

JT9D-3A.

  • Pratt and Whitney turbofan engine. 208.8 kN. Out of Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=10939s.

Judi-I 1.9KS2150.

  • RPI solid rocket engine. 9 kN.

Judi-III 1.9KS2100.

  • RPI solid rocket engine. 9 kN.

K10S.

  • ISAS solid rocket engine.

K150.

  • ISAS solid rocket engine. 19 kN.

K160.

  • ISAS solid rocket engine.

K220.

  • ISAS solid rocket engine.

K250-100.

  • ISAS solid rocket engine. 34 kN.

K250-200.

  • ISAS solid rocket engine. 34 kN.

K250-300.

  • ISAS solid rocket engine. 43 kN.

K250-8.

  • ISAS solid rocket engine. 34 kN.

K250H.

  • ISAS solid rocket engine.

K420(1/3).

  • ISAS solid rocket engine. 45 kN.

K420-1200.

  • ISAS solid rocket engine. 110 kN.

K420-1400.

  • ISAS solid rocket engine. 110 kN.

K420-1800.

  • ISAS solid rocket engine. 110 kN.

K420-500.

  • ISAS solid rocket engine. 110 kN.

K420H.

  • ISAS solid rocket engine. 110 kN.

Kappa 1.

  • ISAS solid rocket engine. 10 kN.

Kappa 4.

  • ISAS solid rocket engine. 10 kN.

Kappa 4 Booster.

  • ISAS solid rocket engine. 105 kN.

Kartukov LL.

  • Kartukov solid rocket engine. 14.7 kN. LL-1, LL-2, LL-3. Developed 1946-48.

Kartukov P-15M.

  • Kartukov solid rocket engine. P-15M. Out of Production. Launch thrust 284 kN.

Kartukov P-35.

  • Kartukov solid rocket engine. 294 kN. P-35. Out of Production.

Kartukov P-5.

  • Kartukov solid rocket engine. 179 kN. P-5. Out of Production.

Kartukov P-6.

  • Kartukov solid rocket engine. P-6. Out of Production.

Kartukov Soyuz SAS.

  • Kartukov solid rocket engine. 785 kN. Soyuz 7K-OK, Soyuz 7KT-OK, Soyuz 7K-T. Out of Production. Thrust 76 tf at cutout - 80.1tf at ignition.

Kartukov Soyuz T - TM SAS 17k.

  • Kartukov solid rocket engine. 171 kN. Soyuz T, Soyuz TM. In Production. Thrust 10 tf at cutout - 17.5 at ignition.

Kartukov Soyuz T - TM SAS 73k.

  • Kartukov solid rocket engine. 715 kN. Soyuz T, Soyuz TM. In Production. Thrust 45 tf at cutout - 73 tf at ignition.

KDU-414.

  • Isayev Nitric acid/UDMH rocket engine. 1.961 kN. Molniya 1, Mars 1, Venera 1, Zond 2-3 maneuvering engine. Out of Production. Spacecraft maneuvering engine. Isp=272s.

KDU-426.

  • Isayev N2O4/UDMH rocket engine. 3.089 kN. Soyuz-T orbital correction engine. In Production. Pressure-fed engine. Used as long duration engine for correction orbits of satellites. Isp=292s.

Kestrel.

  • SpaceX Lox/Kerosene rocket engine. 30.7 kN. Upper stages. Hardware. Isp=320s. Pintle architecture, designed to be a high efficiency, low pressure vacuum engine. Fed only by tank pressure, ablatively cooled First flight 2006.

KEW-1.

  • Rocketdyne N2O4/MMH rocket engine. 0.029 kN. Kinetic Energy Propulsion (7 Ib thrust). Pressure-fed. ASAT Strap-down test, XSS / DICE Microsatellite, GBI Ground-Based Interceptor, THAAD Theater High Altitude Area Defense. Isp=266s.

KEW-2.

  • Rocketdyne N2O4/MMH rocket engine. 0.215 kN. Kinetic Energy Propulsion (50 Ib thrust). Pressure-fed. ASAT Strap-down test, XSS / DICE Microsatellite, GBI Ground-Based Interceptor, THAAD Theater High Altitude Area Defense. Isp=275s.

KEW-3.

  • Rocketdyne N2O4/MMH rocket engine. 0.441 kN. Kinetic Energy Propulsion (100 Ib thrust). Pressure-fed. ASAT Strap-down test, XSS / DICE Microsatellite, GBI Ground-Based Interceptor, THAAD Theater High Altitude Area Defense. Isp=283s.

KEW-4.

  • Rocketdyne N2O4/MMH rocket engine. 2.216 kN. Kinetic Energy Propulsion (500 Ib thrust). Pressure-fed. ASAT Strap-down test, XSS / DICE Microsatellite, GBI Ground-Based Interceptor, THAAD Theater High Altitude Area Defense. Isp=235s.

Kisha I 4.4KS4800.

  • PRI solid rocket engine. 21 kN.

Kiva 5.5KS6100.

  • RPI solid rocket engine. 27 kN.

KM-D.

  • Nissan solid rocket engine.

KM-H.

  • Nissan solid rocket engine.

KRD-417.

  • Alternate designation for KTDU-417 Nitric acid-UDMH rocket engine.

KRD-442.

  • Isayev N2O4/UDMH rocket engine. 4.38 / 0.17 kN. Orbital propulsion for FGB-derived modules for Mir and ISS. In Production. Main and low-thrust mode. Operation of turbopump without chamber used to pump propellants into tanks from Progress tankers.

KRD-604.

  • Dushkin Nitric acid/Solid hybrid rocket engine. Out of Production. The KRD-604 engine was developed in the late 1930s by OKB Dushkin. It was a combined (powder+liquid) engine, characterized by a new technical approach.

KRD-61.

  • Isayev N2O4/UDMH rocket engine. 18.8 kN. Luna Ye-8. Out of Production. Spacecraft maneuvering engine for ascent stage of Luna moon sample return missions. Isp=313s. First flight 1969.

KRD-79.

  • Isayev N2O4/UDMH rocket engine. 3.090 kN. Salyut 6, 7and Mir orbital propulsion maneuvering engine. In Production. Probably derived from engine of propulsion system KDU-426. Pressure fed engine.

KRR-300.

  • Dushkin rocket engine. 98 kN. G-300. Developed 1955-62. Thrust variable 0.1 / 3.0 / 10 tf.

KS-50.

  • Glushko Lox/Kerosene rocket engine. Experimental. Development 1948. Subscale versions of a radical new engine design. This featured a flat-plate injector, cylindrical combustion chamber, and a 60 atmosphere chamber pressure.

KSR-3.

  • Korean Lox/Kerosene rocket engine. In development. Launch thrust 122.5 kN. Pressure-fed indigenous design. First flight 2002.

KT1-3.

  • Shanxi solid rocket engine.

KTDU-35.

  • Isayev Nitric acid/UDMH rocket engine. 4.09 kN. Out of Production. Isp=280s. Soyuz, Salyut 4 maneuvering engine. KTDU-53 version in L-1 circumlunar spacecraft; KTDU-66 in Salyut 1 space station. Thrusts 4.09 kN main + 4.03 kN secondary. First flight 1966.

KTDU-414.

  • Manufacturer's designation of KDU-414 Nitric acid-UDMH rocket engine.

KTDU-417.

  • Isayev Nitric acid/UDMH rocket engine. 18.920 kN. Luna 15-24 descent stage. Out of Production. Isp=314s. Comprised turbopump-fed high-thrust engine with plus KTDU-417-B low-thrust engine. Eleven ignitions for lunar orbit insertion and orbit corrections.

KTDU-417-B.

  • Isayev N2O4/UDMH rocket engine. 3.430 kN. Luna 15-24 used this low thrust engine in system KTDU-417 for soft-landing on the moon. Out of Production. Isp=254s. Pressure-fed engine; could be throttled to 2.06 kN.

KTDU-425.

  • Isayev N2O4/UDMH rocket engine. 18.850 kN. Mars 2 and 3 maneuver engine. Out of Production. Pump-fed engine. Could be throttled to 7.05 kN / 9.5 MPa / 2850 m/s. . Chamber pressure 133,2 - 95 bar. Isp=312s.

KTDU-425A.

  • Isayev N2O4/UDMH rocket engine. 18.890 kN. Mars 4-7, Venera 9-16, Vega 1-2, and Phobos 1-2 maneuvering engine. Out of Production. Could be throttled to 9.86/9.5/2870. Chamber pressure 149 - 95 bar. Isp=315s. First flight 1973.

KTDU-53.

  • Isayev Nitric acid/UDMH rocket engine. 4.089 kN. Zond 4-7 maneuvering engine. Out of Production. Spacecraft maneuvering engine, derivative of KTDU-35 without back-up engine. Isp=280s.

KTDU-5A.

  • Isayev Nitric acid/Amine rocket engine. 45.5 kN. Used on Luna E-6 probes. Out of Production. Isp=287s. First turbopump engine with surface tension propellant management devices in tanks, allowing re-ignition in zero-G.

KTDU-66.

  • Isayev Nitric acid/UDMH rocket engine. 4.090 kN. Out of Production. Isp=280s. Maneuvering engine for Salyut 1, derivative of KTDU-35. Longer burn time of 1000 s. Comprised single-chamber main engine plus dual-chamber back-up engine. Thrusts 4.09 + 4.03 kN

KTDU-80.

  • Isayev N2O4/UDMH rocket engine. 6.190 kN. Soyuz TM, Progress M. In Production. Isp=326s. Propulsion system included 4 spherical tanks for a total of 880 kg propellant. Developed from NII Mash experimental thruster. 3 thrust levels by 4 valves.

KVD-1, D-56.

  • Alternate designation for RD-56 Lox-LH2 rocket engine.

KVD-1M.

  • Alternate designation for RD-56M Lox-LH2 rocket engine.

KVD-1M LNG.

  • Alternate designation for RD-56M LNG Lox-LNG rocket engine.

L-1 Linear Aerospike Booster.

  • Rocketdyne Lox/Kerosene rocket engine. Launch thrust 889.36 kN. Gas generator, pump-fed. Thrust and specific impulse values are at sea level.

L-2 Linear Aerospike Booster.

  • Rocketdyne Lox/Kerosene rocket engine. Launch thrust 444.63 kN. Gas generator, pump-fed. Thrust and specific impulse values are at sea level.

L480S.

  • ISAS solid rocket engine. 7.8 kN.

L-5.00H.

  • Notional lox/lh2 rocket engine. 30,684 kN. Study 1963. Isp=428s. Used on Nova GD-H launch vehicle.

L-5.25H.

  • Notional lox/lh2 rocket engine. 27,350 kN. Study 1963. Isp=410s. Engines for recoverable booster engine package 'half stage' of a 1 1/2 stage arrangement. Used on Nova GD-H launch vehicle.

L500.

  • ISAS solid rocket engine. 69 kN.

L-6.55.

  • Notional Lox/Kerosene rocket engine. 31,010 kN. Study 1963. Engines used in recoverable stage of ballistic shape; separation at 3,420 m/s at 93,900 m altitude; splashdown using retrorockets under 7 parachutes 1340 km downrange. Isp=330s.

L6H.

  • Notional lox/lh2 rocket engine. 122,748 kN. Study 1963. Operational date would have been June 1976. Used in booster stage (engines only). Isp=439s. Used on Nova MM 34 launch vehicle.

L7.

  • MBB N2O4/MMH rocket engine. 27.4 kN. In Production. Isp=320s. Used on Ariane 5 launch vehicle. First flight 1996.

L-7.70.

  • Notional Lox/Kerosene rocket engine. 37,007 kN. Study 1963. Engines used in recoverable stage; separation at 3,365 m/s at 89,300 m altitude; splashdown using retrorockets under 8 46 m diameter parachutes 1300 km downrange. Isp=335s.

L735.

  • ISAS solid rocket engine. 410 kN.

L735(1/3).

  • ISAS solid rocket engine. 118 kN.

LACE/LE-5.

  • Mitsubishi air augmented Liquid Air/LH2 rocket engine. 147.1 kN. Design 1999. Isp=1200s. Used on H-2 HIMES launch vehicle.

LAPAN.

  • LAPAN solid rocket engine.

LAPSTAR-300.

  • WRE solid rocket engine. 80 kN.

LAPSTAR-52.

  • WRE solid rocket engine.

Lapwing.

  • Bristol solid rocket engine. 4.5 kN.

Launch Vehicle Third Stage Motor.

  • Manufacturer's designation of GF-02 Solid rocket engine.

LE-3.

  • Rocketdyne N2O4/Aerozine-50 rocket engine. 53.340 kN. MHI(Japan)/Rocketdyne Upper Stage. Pressure-fed. Isp=285s.

LE-5.

  • Mitsubishi lox/lh2 rocket engine. 103 kN. Isp=450s. Used on H-1 launch vehicle. First flight 1986.

LE-5A.

  • Mitsubishi lox/lh2 rocket engine. 121.5 kN. Isp=452s. Used on H-2 launch vehicle. First flight 1994.

LE-5B.

  • Mitsubishi lox/lh2 rocket engine. 137 kN. In production. Isp=447s. Improved model of the LE-5A for second stage of the H-II rocket; used hydrogen for the cooling of the thrust chamber, then as the gas to drive the turbine. First flight 2001.

LE-7.

  • Mitsubishi lox/lh2 rocket engine for H-2 upper stage. 1078 kN. Staged combustion turbopump. No throttle capability. Isp=446s. First flight 1994.

LE-7A.

  • Mitsubishi lox/lh2 rocket engine. 1098 kN. In production. Isp=438s. Improved model of the original LE-7 for the first stage of the H-II rocket with a two stage combustion cycle system. First flight 2001.

LGIT.

  • UM electric rocket engine. 20 mN. Isp=1400s. Linear Gridless Ion Thruster, a two-stage device designed to incorporate the efficient ionization process of gridded ion thrusters and the high thrust density of Hall thrusters.

LH2 2000/3000 Ibf thrust.

  • Aerojet lox/lh2 rocket engine. Launch thrust 13.33 kN. Development begun July 1946. Engine R&D, hydrogen production

LH2-80k.

  • Notional lox/lh2 rocket engine. 355.7 kN. Study 1959. Isp=425s. Used on Nova 4L launch vehicle.

Liberty.

  • Liberty Lox/Kerosene rocket engine. Development 1994-2006. Pressure-fed engine. Price $ 12,000 in 1995. Used on Scorpius launch vehicle.

Liberty-1.

  • Notional Lox/Kerosene rocket engine. 245.2 kN. Development ended 1988. Pressure-fed engine. Isp=270s. Used on Liberty launch vehicle.

Liberty-2.

  • Notional N2O4/MMH rocket engine. 17.8 kN. Development ended 1988. Pressure-fed engine. Isp=300s. Used on Liberty launch vehicle.

Lilliput.

  • Manufacturer's designation of KS-50 Lox-Kerosene rocket engine.

LK-1.

  • IAI solid rocket engine. 774 kN. In production. Isp=272s. Lengthened version of Shavit rocket motor. Lower stage used 9:1 nozzle. 23.6:1 nozzle for upper stage use inceased Isp to 279 seconds, First flight 1995.

Lobster.

  • RO solid rocket engine.

Loki.

  • GCR solid rocket engine. 15 kN.

Low Power Hydrazine Arcjet.

  • Alternate designation for MR-508 Hydrazine rocket engine.

LPC A-1.

  • American solid rocket engine. 690 kN.

LPC-415.

  • Boeing solid rocket engine.

LPCE.

  • Alternate designation for TR-106 Lox-LH2 rocket engine.

LR10.

  • Reaction Motors rocket engine. Viking RTV-N-12.

LR101-11.

  • Rocketdyne Lox/Kerosene rocket engine. 5.3 kN. In Production. Isp=246s. Verniers for RS-27 powerplant, used on Delta boosters 1974-1992.

LR101-NA-7.

  • Rocketdyne N2O4/MMH rocket engine. 5.148 kN. Upper Stage Target Engine Systems. Pressure-fed. Derived from Atlas vernier. Isp=251s.

LR103.

  • American liquid rocket engine. Designation allocated, but no information available.

LR105-3.

  • Rocketdyne Lox/Kerosene rocket engine. 375 kN. Out of Production. Early version of Atlas Sustainer. Gas generator, pump-fed. Isp=308s.

LR105-5.

  • Rocketdyne Lox/Kerosene rocket engine. 386.4 kN. Atlas E, F. Atlas Sustainer. Gas generator, pump-fed. Separate turbopumps for each booster engine. Isp=316s. First flight 1960.

LR105-7.

  • Rocketdyne Lox/Kerosene rocket engine. 386.4 kN. Atlas space launchers. Out of production. Atlas Sustainer. Gas generator, pump-fed. Evolved from MA-2 ICBM system. Isp=316s. First flight 1963.

LR107.

  • Hughes liquid rocket engine.

LR109.

  • American liquid rocket engine. Designation allocated, but no information available.

LR10-RM-1.

  • Government designation of LR10 rocket engine.

LR111.

  • American liquid rocket engine. Designation allocated, but no information available.

LR115.

  • Government designation of RL-10A-1 Lox-LH2 rocket engine.

LR117.

  • American liquid rocket engine. Designation allocated, but no information available.

LR119.

  • Government designation of RL-10A-3 Lox-LH2 rocket engine.

LR12.

  • American liquid rocket engine. Designation allocated, but no information available.

LR121.

  • Rocketdyne liquid rocket engine. NF-104A .

LR123.

  • American liquid rocket engine. Designation allocated, but no information available.

LR125.

  • American liquid rocket engine. Designation allocated, but no information available.

LR127.

  • American liquid rocket engine. Designation allocated, but no information available.

LR129.

  • Pratt and Whitney lox/lh2 rocket engine. Engine developed for boost/glide aerospace craft; later modified into unsuccessful competitor for Space Shuttle main engine.

LR14.

  • American liquid rocket engine. Designation allocated, but no information available.

LR16.

  • Aerojet rocket engine.

LR17.

  • Curtiss-Wright Lox/Gasoline rocket engine. RATO rocket for XB-45. Launch thrust 17.6 kN. Assisted take-off power. Single thrust chamber, both regeneratively cooled and film-cooled with water, spark plug ignition, turbine-pump fed.

LR18.

  • American liquid rocket engine. Designation allocated, but no information available.

LR19.

  • Curtiss-Wright Lox/Gasoline rocket engine. Launch thrust 44.1 kN. Experimental unit for either missiles or piloted aircraft. Single thrust chamber, regnenerativey cooled and film cooled with water-alcohol mixture.

LR2.

  • Reaction Motors liquid rocket engine.

LR21.

  • Curtiss-Wright Lox/Gasoline rocket engine. Launch thrust 266.83 kN. Turbine pump-fed, single thrust chamber unit intended for cancelled missile application. Engine designed to fit into the envelope dimensions of the German V-2!

LR22.

  • Reaction Motors liquid rocket engine.

LR26.

  • Reaction Motors liquid rocket engine.

LR27.

  • Curtiss-Wright liquid rocket engine. planned for XF-91; cancelled.

LR28.

  • American liquid rocket engine. Designation allocated, but no information available.

LR29.

  • Curtiss-Wright liquid rocket engine. cancelled project.

LR2-RM-6.

  • Fairchild liquid rocket engine. 2.8 kN.

LR30.

  • Reaction Motors Lox/Ammonia rocket engine. 222.6 kN. D-558-3. Capable rocket engine planned for use in D-558-3 and X-15. Cancelled in favour of XLR-99.

LR31.

  • Kellogg liquid rocket engine. cancelled project.

LR32.

  • Reaction Motors liquid rocket engine. XH-15 blade-tip engine .

LR33.

  • Reaction Motors liquid rocket engine. cancelled project. Engine development halted, component work continued.

LR34.

  • American liquid rocket engine. Designation allocated, but no information available.

LR35.

  • Reaction Motors liquid rocket engine. Hiroc RTV-A-2. Engine development halted, component work continued.

LR36.

  • American liquid rocket engine. Designation allocated, but no information available.

LR37.

  • Curtiss-Wright Lox/Gasoline rocket engine. 0.225 kN. Small experimental engine for ram-rocket tests. Single thrust chamber, regneratively cooled with gasoline, film cooling also used, spark plug ignition. Test article only built.

LR38.

  • American liquid rocket engine. Designation allocated, but no information available.

LR39.

  • Reaction Motors Lox/Alcohol rocket engine. 0.225 kN. Small experimental engine. Single thrust chamber, water cooled, equipped only with spark plug igntion system and propellant flow valves. Test article only built.

LR4.

  • American liquid rocket engine. Designation allocated, but no information available.

LR40.

  • Reaction Motors H2O2/Kerosene rocket engine. 35.690 kN. F8U-1 supercruise engine, 1957. Engine exploded during an early ground test, killing two company mechanics. This accident caused Reaction Motors to pull out of the project.

LR41.

  • North American liquid rocket engine.

LR42.

  • North American liquid rocket engine.

LR44.

  • Thiokol liquid rocket engine. Sparrow AAM-N-6, White Lance GAM-79.

LR46.

  • American liquid rocket engine. Designation allocated, but no information available.

LR47.

  • Kellogg liquid rocket engine. RATO rocket planned for cancelled B-47C (B-56).

LR48.

  • Reaction Motors liquid rocket engine.

LR49.

  • Aerojet rocket engine.

LR50-GE-1.

  • Government designation of X-405 Lox-Kerosene rocket engine.

LR51.

  • Aerojet rocket engine.

LR52-AJ-1.

  • Government designation of AJ10-118 Nitric acid-UDMH rocket engine.

LR54.

  • Rocketdyne H2O2/Kerosene rocket engine. 26.4 kN. After the failure of the Reaction Motors XLR-40 for use in the F8U-1 fighter, Vought elected to continue the project using the XLR-54 . Project never reached flight status

LR55.

  • American liquid rocket engine. Designation allocated, but no information available.

LR56.

  • Aerojet storable liquid engine. F8U-3F. Aerojet was considered as the supplier for a liquid rocket superperformance engine for the F8U-3. It is not known to have reached test stage.

LR57.

  • American liquid rocket engine. Designation allocated, but no information available.

LR58.

  • Thiokol liquid rocket engine. Bullpup AGM-12B, Bulldog AGM-83.

LR58-RM-1.

  • Government designation of LR58 rocket engine.

LR59-AJ-1.

  • Government designation of 45LR-35000 Nitric acid-UDMH rocket engine.

LR6.

  • Reaction Motors liquid rocket engine. Lark SAM-N-2, CTV-N-9.

LR60.

  • American liquid rocket engine. Designation allocated, but no information available.

LR61.

  • American liquid rocket engine. Designation allocated, but no information available.

LR62.

  • Thiokol liquid rocket engine. Bullpup AGM-12C/E.

LR62-RM-1.

  • Government designation of LR62 rocket engine.

LR64.

LR65.

  • Bell rocket engine for the X-9 Shrike, an experimental prototype of the Rascal air-to-ground missile.

LR66-AJ-2.

  • Government designation of AJ10-196 rocket engine.

LR67.

  • Bell rocket engine. Rascal GAM-63. Harry Meyers made a major contribution to the development of Bell's Rascal engines. The engine was made of aluminum, using the "spaghetti tube" concept of brazed tubes for thrust chamber cooling.

LR67-B-1.

  • Government designation of LR67 rocket engine.

LR69.

  • American liquid rocket engine. Designation allocated, but no information available.

LR73.

  • Aerojet storable liquid engine.

LR73-AJ-1.

  • Government designation of LR73 rocket engine.

LR75.

  • American liquid rocket engine. Designation allocated, but no information available.

LR77.

  • American liquid rocket engine. Designation allocated, but no information available.

LR79-7.

  • Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Out of production. Designed for booster applications. Gas generator, pump-fed. Isp=282s. First flight 1957.

LR79--NA-7.

  • Government designation of LR79-7 Lox-Kerosene rocket engine.

LR81-B-1.

  • Government designation of Bell 8048 Nitric acid-UDMH rocket engine.

LR83-NA-1.

  • Rocketdyne Lox/Kerosene rocket engine. 683 kN. Development ended 1958. Isp=282s. Planned production version of the engine for the booster of the Navaho G-38 intercontinental cruise missile.

LR85.

  • American liquid rocket engine. Buck Duck GAM-71.

LR87 Alumizine.

  • Aerojet N2O4/Alumizine rocket engine. 1960's USAF development effort for a Titan storable engine using a metallized fuel (for greater impulse density) and gelled propellants (to facilitate in-space starts after a period of coasting).

LR87 LH2.

  • Aerojet lox/lh2 rocket engine. 667 kN. Development ended 1961. Version of the Titan engine, and first large Lox/LH2 engine fired in the world. 52 static tests. But NASA selected Rocketdyne instead to develop the J-2 engine for Saturn from scratch.

LR87+.

  • Aerojet N2O4/Aerozine-50 rocket engine. 1634.4 kN. Study 1965. Nominal improved LR87 in booster studies. Isp=293s. Used on Martin Astrorocket launch vehicle.

LR87-11.

  • Aerojet N2O4/Aerozine-50 rocket engine. 1218.8 kN. Out of production. Isp=302s. Powered Titan 3 and 4 first stages. Replaced the -9 model, first flown 1968. First flight 1964.

LR87-11 AJ23-138.

  • Aerojet N2O4/Aerozine-50 rocket engine. Launch thrust 1008.31 kN. Version of LR-87-11 tuned for launch pad ignition when used on Titan 3B. First flight 1966.

LR87-3.

  • Aerojet Lox/Kerosene rocket engine. 733.9 kN. Study 1957. Titan 1 booster engine. Surplus Flight Engines were available for various uses in the 1960's. Isp=290s. First flight 1959.

LR87-5.

  • Aerojet N2O4/Aerozine-50 rocket engine. 1096.8 kN. Out of Production. Isp=297s. Used on Titan 2 launch vehicle. Engines refurbished for space launcher versions from decommissioned missiles between 1974-1982.

LR87-7.

  • Aerojet N2O4/Aerozine-50 rocket engine. 1086.1 kN. Study 1961. Version of LR-87-5 used on Gemini Titan 2 launch vehicle. Isp=296s. Proposed for unflown Titan 3L2, Titan 3L4 boosters. First flight 1962.

LR87-9.

  • Aerojet N2O4/Aerozine-50 rocket engine. Launch thrust 956.1 kN. Variant of LR-87 used on early versions of Titan III B,C First flight 1966.

LR89-5.

  • Rocketdyne Lox/Kerosene rocket engine. 822.5 kN. Atlas E, F. Designed for booster applications. Gas generator, pump-fed. Separate turbopumps for each booster engine. Isp=290s. First flight 1960.

LR89-7.

  • Rocketdyne Lox/Kerosene rocket engine. 948 kN. Atlas space launchers. Out of production. Designed for booster applications. Gas generator, pump-fed. Shared turbopumps for booster engines. Evolved from MA-2 ICBM system. Isp=294s. First flight 1963.

LR8-RM-5.

  • Reaction Motors Lox/Alcohol rocket engine for rocketplanes. Out of Production. Launch thrust 26.67 kN. Advanced version of the LR-11, 4 chambers. Engine in the X-1E was modified in 1958 to increase chamber pressure to 20 atm and burn Hydyne fuel.

LR91-11.

  • Aerojet N2O4/Aerozine-50 rocket engine. 467 kN. Out of production. Isp=316s. Second stage engine for Titan 3 and 4. First flight 1968.

LR91-3.

  • Aerojet Lox/Kerosene rocket engine. 355.9 kN. Development begun 1957. Titan 1 Stage 2 major production version. Isp=308s. Proposed for second stage of Juno V-A, Super-Jupiter in 1959. Flown 1959-1965.

LR91-5.

  • Aerojet N2O4/Aerozine-50 rocket engine. 444.8 kN. Titan 2 ICBM Stage 2. Out of Production. Isp=315s. Scaled down version of stage 1 engine featuring fixed single chamber. Gas generator cycle. First flight 1962.

LR91-7.

  • Aerojet N2O4/Aerozine-50 rocket engine. 444.8 kN. Study 1961. Version used on Stage 2 of Gemini Titan 2 Launch Vehicle. Isp=316s. Proposed for unflown Titan 3L2, Titan 3L4 boosters. First flight 1962.

LR91-9.

  • Aerojet N2O4/Aerozine-50 rocket engine. 448.605 kN. Titan III B, C, D. Out of Production. Version used in earlier versions of Titan 3 upper stages. Isp=316s. First flight 1965.

LR93.

  • American liquid rocket engine. Designation allocated, but no information available.

LR95.

  • American liquid rocket engine. Designation allocated, but no information available.

LR97.

  • American liquid rocket engine. Designation allocated, but no information available.

LS-A.

  • Mitsubishi solid rocket engine. 10 kN.

LS-A Booster.

  • Mitsubishi solid rocket engine. 60 kN.

LS-C-2.5.

  • Mitsubishi solid rocket engine.

LS-C-4.

  • Mitsubishi solid rocket engine.

Lupus.

  • WRE solid rocket engine.

Lynx.

  • NAWC solid rocket engine.

M-1.

  • Aerojet lox/lh2 rocket engine. 5335.9 kN. Study 1961. Isp=428s. Engine developed 1962-1966 for Uprated Saturn and Nova million-pound payload boosters to support manned Mars missions. Reached component test stage before cancellation.

M-10.

  • Nissan solid rocket engine. 737 kN.

M-100-100.

  • Russian solid rocket engine.

M-100-300.

  • Russian solid rocket engine.

M112.

  • Aerojet solid rocket engine. 13 kN.

M-13.

  • Nissan solid rocket engine. 1262.4 kN. Isp=263s. Used on Mu-3S launch vehicle. First flight 1969.

M14.

  • Nissan solid rocket engine. 3780.3 kN. Isp=276s. Used on M-V launch vehicle. First flight 1997.

M-20.

  • Nissan solid rocket engine. 285 kN.

M-22.

  • Nissan solid rocket engine. 285 kN.

M-23-J.

  • Nissan solid rocket engine. 524.8 kN. In development. Isp=282s. Used on J-1 launch vehicle. First flight 1996.

M-23-Mu.

  • Nissan solid rocket engine. 524 kN. Isp=285s. Used on Mu-3S launch vehicle. First flight 1969.

M24.

  • Nissan solid rocket engine. 1245.3 kN. Isp=288s. Used on M-V launch vehicle. First flight 1997.

M-30.

  • Nissan solid rocket engine. 128 kN.

M33-20-4.

  • Thiokol solid rocket engine. 286 kN. Isp=247s. Used as apogee kick motor on Delta D, LT Thor Agena D, Scout X-1, Scout X-2, Scout X-3, Scout X-4, TA Thor Agena B, TA Thor Agena D. First flight 1960.

M34.

  • Nissan solid rocket engine. 294.2 kN. Isp=301s. Used on M-V launch vehicle. First flight 1997.

M-3A.

  • Nissan solid rocket engine. 61 kN.

M-3B-J.

  • Nissan solid rocket engine. 132.1 kN. In development. Isp=294s. Used on J-1 launch vehicle. First flight 1996.

M-3B-Mu.

  • Nissan solid rocket engine. 132.1 kN. Isp=294s. Used on Mu-3S launch vehicle. First flight 1969.

M-40.

  • Nissan solid rocket engine. 26.5 kN.

M55/TX-55/Tu-122.

  • Thiokol solid rocket engine. 792 kN. In production. Isp=262s. Proposed as strap-on booster for Saturn IB-C, Saturn INT-14, Saturn INT-15, Saturn INT-19 variants. First flight 2000.

M55A1.

  • Thiokol solid rocket engine. 792 kN.

M56A-1.

  • Aerojet solid rocket engine. 228.5 kN. Out of Production. Used in Aries. Isp=297s.

M57A1.

  • Hercules solid rocket engine. 76 kN.

M5E1.

  • Hercules solid rocket engine. 195.6 kN. Nike booster motor. The interstage adapter was bolted to the front of the Nike in sounding rocket applications and lip-fit into the second stage nozzle.

M-6.

  • Hercules solid rocket engine. 365 kN. Taurus rocket motor originally developed for the Army Honest John tactical missile. In sounding rocket applications the interstage adapter was bolted to the front of the Taurus.

MA-1.

  • Manufacturer's designation of XLR89-1 Lox-Kerosene rocket engine.

MA-2.

  • Manufacturer's designation of assembly of XLR89-5 Lox-Kerosene rocket engines.

MA-3.

  • Manufacturer's designation of assembly of LR89-5 and LR105-5 Lox-Kerosene rocket engines.

MA-5.

  • Manufacturer's designation of assembly of LR89-7 and LR105-7 Lox-Kerosene rocket engines.

MA-5A.

  • Manufacturer's designation of assembly of RS-56-OBA and RS-56-OSA Lox-Kerosene rocket engines.

MA-5A.

  • Rocketdyne Lox/Kerosene rocket engine. 2100 kN. Out of Production. Isp=296s. Atlas Engine System, an updated version of the MA-5, included replacments with selected RS-27 components for sea-level Isp increase of 4 secs. First flight 1991.

Mage 1.

  • SEP solid rocket engine. 19.4 kN. Out of production. Orbital circularization motor. Isp=295s. First flight 1979.

Mage 2.

  • SEP solid rocket engine. 45.5 kN. Orbital circularization motor for Advanced Scout, Ariane 2/3. Isp=293s. First flight 1984.

MAI Hall thruster.

  • MAI electric rocket engine. 1.35 kW Hall thruster

Mammouth.

  • French solid rocket engine. 190 kN. 1900 kg 'Plastolite' propellant. Empty mass estimated. Originally developed as the booster for the SSBT missile. Isp=180s. Used on Agate launch vehicle. First flight 1961.

MARC 13A1.

  • ARC solid rocket engine. 17 kN.

MARC 14A1.

  • ARC solid rocket engine. 12 kN.

MARC 14B1.

  • ARC solid rocket engine. 84 kN.

MARC 2B1.

  • ARC solid rocket engine. 1.5 kN.

MARC 2C2.

  • ARC solid rocket engine. 1.5 kN.

MARC 42A1.

  • ARC solid rocket engine. 12.2 kN.

MARC 60A.

  • ARC solid rocket engine. 1.5 kN.

Martlet 4-1.

  • Bull solid rocket engine. 67.7 kN. Development ended 1966. Isp=300s. Used on Martlet 4 launch vehicle.

Martlet 4-2.

  • Bull solid rocket engine. 20.6 kN. Development ended 1966. Isp=300s. Used on Martlet 4 launch vehicle.

Martlet 4-3.

  • Bull solid rocket engine. 5.390 kN. Development ended 1966. Isp=300s. Used on Martlet 4 launch vehicle.

Matador M-16.

  • American turbojet engine, cruise motor for Matador M-16.

Mayfly-300.

  • WRE solid rocket engine. 62 kN.

Mayfly-600.

  • WRE solid rocket engine. 190 kN.

MB-1.

  • Thiokol solid rocket engine. 156 kN.

MB-1.

  • Manufacturer's designation of LR79-7 Lox-Kerosene rocket engine.

MB-3.

  • Manufacturer's designation of MB-3-1 Lox-Kerosene rocket engine.

MB-3 Press Mod.

  • Rocketdyne Lox/Kerosene rocket engine. 755.1 kN. Test 1962. Isp=285s. Used on Sea Horse launch vehicle.

MB-3-1.

  • Rocketdyne Lox/Kerosene rocket engine. 760.6 kN. Out of production. Designed for booster applications. Gas generator, pump-fed. Isp=285s. Boosted Delta A, B, C, Thor Able-Star. First flight 1960.

MB-3-3.

  • Rocketdyne Lox/Kerosene rocket engine. 866.7 kN. Out of Production. License built in Japan for H-1. Isp=290s. First flight 1964.

MB-35.

  • Rocketdyne lox/lh2 rocket engine. 156 kN. Design 2004. Isp=467s. Mitsubishi / Boeing joint project for an engine for Delta IV cryogenic upper stages. Expander bleed, pump-fed.

MB-3-J.

  • Rocketdyne Lox/Kerosene rocket engine. Out of production. Launch thrust 755.89 kN. N Booster . Gas generator, pump-fed. Joint MHI (Japan) / Rocketdyne project, evolved from MB-3. Thrust and specific impulse values are at sea level. First flight 1975.

MB-45.

  • Rocketdyne lox/lh2 rocket engine. 200 kN. Design 2004. Isp=467s. Mitsubishi / Boeing joint project for an engine for Delta IV cryogenic upper stages, announced February 2000.

MB-60.

  • Rocketdyne lox/lh2 rocket engine. 266.7 kN. Design 2004. Isp=467s. Mitsubishi / Boeing joint project for an engine for Delta IV cryogenic upper stages. Expander bleed, pump-fed.

MBB-ATC500.

  • MBB lox/lh2 rocket engine. 441.3 kN. Study 1969. Isp=460s. Used on Beta launch vehicle.

MB-XX.

  • Alternate designation for MB-60 Lox-LH2 rocket engine.

MD-620.

  • Dassault N2O4/UDMH rocket engine.

Melanie.

  • SEPR solid rocket engine. 11.1 kN. Out of production. 22 kg propellant. Empty mass estimated. Isp=227s. Used on Berenice launch vehicle. First flight 1962.

Melusine.

  • CFTH-HB solid rocket engine.

Merlin 1A.

  • SpaceX Lox/Kerosene rocket engine. 378.040 kN. First stages. Hardware. Isp=300s. Completed development in early 2005. Pintle injector concept. Replaced by Merlin 1C. First flight 2006.

Merlin 1C.

  • SpaceX Lox/Kerosene rocket engine. 614.7 kN. First stages. Hardware. Isp=304s. Regeneratively cooled; turbo-pump also provided high pressure kerosene for the hydraulic actuators. Actuated turbine exhaust nozzle provided roll control. First flight 2008.

Merlin 1V.

  • SpaceX Lox/Kerosene rocket engine. 411.4 kN. Hardware. Isp=342s. Upper stage version of the Merlin developed for the Falcon 9 second stage. Based on the Merlin 1C and using a regeneratively cooled combustion chamber. First flight 2009.

Meteor-1.

  • PIHM solid rocket engine. 14 kN.

Meteor-2.

  • Polish solid rocket engine. 24 kN.

MG-18.

  • LPC solid rocket engine.

Microcosm 22N.

  • Microcosm Lox/Kerosene rocket engine. 22.250 kN. First stages. Hardware. Pressure-fed, ablatively cooled engine using liquid oxygen and jet fuel as propellants. Flown 1999/2001.

Microcosm 356N.

  • Microcosm Lox/Kerosene rocket engine. 356 kN. First stages. Hardware. Funded under AFRL SBIR Phase 1 contract of 2006. Ablative chamber, LOX/Jet A propellant engines designed for very low-cost, robust design margins.

Microcosm 89N.

  • Microcosm Lox/Kerosene rocket engine. 89 kN. First stages. Hardware. In 2005 tests were conducted of this low-cost ablative composite rocket engine for responsive launch vehicle applications.

MIHT-1.

  • MIHT solid rocket engine. 980.6 kN. Start-1. In production. Used in Start-1. Estimated values. Isp=263s. First flight 1993.

MIHT-2.

  • solid rocket engine. 490.3 kN. Start-2. In production. Used in Start-2. Estimated values. Isp=280s. First flight 1993.

MIHT-3.

  • MIHT solid rocket engine. 245.2 kN. Start-3. In production. Used in Start-3. Estimated values. Isp=280s. First flight 1993.

MIHT-4.

  • MIHT solid rocket engine. 9.8 kN. Start-4. In production. Used in Start-4. Estimated values. Isp=295s. First flight 1993.

Mk 104.

  • Thiokol solid rocket engine.

Mk 17.

  • Thiokol solid rocket engine. 17.7 kN.

Mk 30.

  • ARC solid rocket engine.

Mk 36.

  • Thiokol solid rocket engine.

Mk 39.

  • TexasI solid rocket engine.

Mk 72.

  • CSD solid rocket engine.

Mk7.

  • Multiple-source solid rocket engine. 9.8 kN.

MLRS.

  • Multiple-source solid rocket engine.

MMR-06.

  • GMS solid rocket engine.

Model 39.

  • Alternate designation for A-4 Lox-Alcohol rocket engine.

Model 39a.

  • Alternate designation for A-9 Lox-Alcohol rocket engine.

MPD.

  • UM-NASA electric rocket engine. 1.35 kW Hall thruster

MR-103.

  • Redmond hydrazine monopropellant rocket engine. 1.12 N. Attitude control thruster for Voyager, GPS, Intelsat 5, MMAS 3000, 4000,. 5000, and 7000, Mars Observer, ACTS, and Magellan. In Production. Isp=227s. First flight 1974.

MR-104.

  • Redmond hydrazine monopropellant rocket engine. 0.441 kN. Attitude control and velocity corrections, Voyager, Magellan, DMSP, Tiros N, Landsat. In Production. Isp=239s. First flight 1977.

MR-106.

  • Redmond hydrazine monopropellant rocket engine. 0.027 kN. Spacecraft and upper stage attitude control and velocity corrections, PAM A/S,. Radarsat, GPS Block 2R, HAS/Peace Courage, Titan Centaur, Atlas Centaur. In Production. Isp=232s.

MR-107.

  • Redmond hydrazine monopropellant rocket engine. 0.257 kN. Spacecraft and upper stage attitude control and dV corrections, Delta 2, Titan 2, PAM D, SICBM, HAS/Peace Courage, Atlas roll control module, STEP, Pegasus. Isp=236s. First flight 1990.

MR-111.

  • Redmond hydrazine monopropellant rocket engine. 4.4 N. Attitude control, Intelsat 5, ERBS, ACTS, Radarsat, MMAS 4000, 5000, and. 7000, Wind/Polar Landsat, and Mars Observer. In Production. Isp=229s. First flight 1980.

MR-12.

  • Russian solid rocket engine.

MR-120.

  • Redmond Hydrazine rocket engine. 0.090 kN. Small ICBM. In Production. Developed as an attitude control thruster for the small ICBM. Isp=229s.

MR-125.

  • LLNL solid rocket engine. 0.400 kN.

MR-20.

  • Russian solid rocket engine.

MR-25.

  • Russian solid rocket engine.

MR-50.

  • Redmond hydrazine monopropellant rocket engine. 0.022 kN. Attitude control for SMS, Viking, Metosat, GOES, Voyager, GPS, Intelsat 5,. Scatha, MMAS 5000, Delta Star, Magellan, Wind/Polar. In Production. Isp=228s. First flight 1974.

MR-501B.

  • Redmond Hydrazine rocket engine. 369 mN. BSAT-2 communications satellite. In Production. Electrothermal hydrazine thruster (EHT). 493 W input power at 24 V DC. Isp=303s.

MR-502.

  • Redmond hydrazine monopropellant rocket engine. 500 mN. Communications satellite N-S stationkeeping, MMAS 5000. In Production. Isp=304s. First flight 1991.

MR-508.

  • Redmond hydrazine monopropellant rocket engine. 230 mN. Communications satellite N-S stationkeeping, MMAS 7000. In Production. Isp=502s. First flight 1993.

MR-509.

  • Redmond Hydrazine rocket engine. 254 mN. In Production. Low-power arcjet system. Input power 1800 W at 65 V DC. Isp=502s.

MR-510.

  • Redmond Hydrazine rocket engine. 254 mN. In Production. Arcjet system. Isp=600s.

MR-512.

  • Redmond Hydrazine rocket engine. 254 mN. In Production. Low-voltage bus arcjet system. Input power 1780 W at 35 V DC. Isp=502s.

MRE-15/OMV.

  • TRW hydrazine monopropellant rocket engine. 0.089 kN. In Production. Isp=225s. Mono-propellant Hydrazine Thrusters.

MRE-5/Compton Observatory.

  • TRW N2O4/MMH rocket engine. 0.025 kN. In Production. Isp=240s. Mono-propellant Hydrazine Thrusters. First flight 1991.

MRM-103.

  • Redmond Hydrazine rocket engine. 0.22 N. In Production. Steady-state thrust 0.22 N. Isp=224s.

MRM-106.

  • Redmond Hydrazine rocket engine. 0.027 kN. In Production. Steady-state thrust 9 N. Isp=231s.

MRM-122.

  • Redmond Hydrazine rocket engine. 0.142 kN. In Production. Steady-state thrust 51 N. Isp=228s.

MR-UR-100 BR.

  • Yuzhnoye N2O4/UDMH rocket engine.

MSBS 501.

  • Aerospatiale solid rocket engine. 900 kN.

MSBS 502.

  • Aerospatiale solid rocket engine. 300 kN.

MSBS 503.

  • Aerospatiale solid rocket engine. 100 kN.

MT 27.

  • SNECMA solid rocket engine. 10 kN.

MT-135.

  • Nissan solid rocket engine. 12 kN.

MTV Motor.

  • SpaceDev N2O/Solid hybrid rocket engine. Upper stages. Small hybrid rocket motor designed for use in the Maneuver and Transfer Vehicle, an upper stage orbital transfer motor. Tested 2001.

Multi-Use Thruster.

  • Alternate designation for MUT MON-UDMH rocket engine.

Musca.

  • WRE solid rocket engine. 10 kN.

Mustard.

  • Notional lox/lh2 rocket engine. 2157.4 kN. Study 1968. Isp=405s. Used on Mustard launch vehicle.

MUT.

  • Rocketdyne MON/UDMH rocket engine. 5.635 kN. Satellite maneuvering motor. Developed 2005. Isp=292s. New technology motor with improved thrust/weight ratio and use of mixed oxides of nitrogen oxidiser with a much lower freezing point than N2O4.

M-V-4.

  • Nissan solid rocket engine. 52 kN. Isp=298s. Used on M-V launch vehicle. First flight 1997.

MX-774.

  • Convair Lox/Alcohol rocket engine. 35 kN.

NA 802 Soleil C.

  • SEREB N2O4/UDMH rocket engine. 120 kN.

NA 803 Soleil.

  • SEREB N2O4/UDMH rocket engine. 156 kN.

NA-704 Mark II.

  • Manufacturer's designation of LR41 rocket engine.

NA-704 Mark III.

  • Manufacturer's designation of XLR43-NA-1 Lox-Alcohol rocket engine.

NA801.

  • Manufacturer's designation of Mammouth rocket engine.

NA802.

  • Manufacturer's designation of Soleil rocket engine.

NA803.

NAA 75-110.

  • Manufacturer's designation of A-6 Lox-Alcohol rocket engine.

NAL-16.

  • Mitsubishi solid rocket engine. 10 kN.

NAL-25.

  • Mitsubishi solid rocket engine.

NAL-7.

  • Mitsubishi solid rocket engine.

NAL-735.

  • NASDA solid rocket engine. 250 kN.

NASA-173GT.

  • NASA Cleveland electric rocket engine. Two-Stage Hybrid Hall/Ion Thruster

NASA-400M.

  • NASA Cleveland electric/krypton rocket engine. 1 N. Isp=4000s. Developed to investigate high-power, high specific impulse Hall thruster operation in 2004.

NASA-457M.

  • NASA Cleveland electric/xenon rocket engine. Isp=2326s. 50 kW Hall thruster developed 2001-on.

Neptune.

  • ONERA solid rocket engine. 20 kN.

Nerva.

  • DoE nuclear/lh2 rocket engine. 266 kN. Study 1968. Early version of Nerva engine proposed for use in Saturn and RIFT configurations in 1961. Isp=800s.

Nerva 12 GW.

  • Notional nuclear/lh2 rocket engine. Study 1959. Used on Hyperion launch vehicle.

NERVA 1mlbf.

  • Notional nuclear/lh2 rocket engine. 8963 kN. DAC Helios, DAC Helios ISI studies 1963. Isp=850s.

Nerva 2.

  • DoE nuclear/lh2 rocket engine. 867.4 kN. Developed 1950-74. Isp=825s.

Nerva Alpha.

  • DoE nuclear/lh2 rocket engine. 71.7 kN. Study 1972. The final Nerva Alpha flight engine reference configuration as documented at the end of its development. Isp=860s.

Nerva Gamma.

  • DoE nuclear/lh2 rocket engine. 81 kN. Study 1972. Isp=975s. The final Nerva Gamma flight engine was an improved version of the Alpha, a small engine that could be launched together with its stage and a payload in a single space shuttle launch.

Nerva NTR.

  • DoE nuclear/lh2 rocket engine. 333.4 kN. Study 1991. Late 1980's update of 1960's Nerva design. Isp=925s.

NERVA/Lox Mixed Cycle.

  • Notional nuclear/lh2 rocket engine. 24,126 kN. Study 1963. Isp=810s. Used on RITA C launch vehicle.

NEXT.

  • UM-NASA electric/xenon rocket engine. 237 mN. Isp=4100s. NASA Evolutionary Xenon Thruster, 40 cm diameter ion engine, double the beam extraction area of the NSTAR engine. Developed 1998-2003.

Nihka.

  • Bristol Aerospace solid rocket engine. 50.5 kN. Upper stages. Out of production. Isp=284s. Used on Black Brant 10 launch vehicle. First flight 1981.

NII 612 kgf.

  • NII Mash N2O4/UDMH rocket engine. 6 kN. experimental 612.25 kgf / 0.071 tf / 0.031tf. Developed. Experimental thruster, 3 thrust levels by 4 valves: 6000 N, 0.7 N, 0.3 N. Specific impulse 326 - 286 sec. Isp=286s.

NK-15.

  • Kuznetsov Lox/Kerosene rocket engine. 1544 kN. N-1 stage 1 (block A). Development ended 1964. On the basis of NK-9 the NK-15 was developed for the N-1 launcher. 30 were used on the Block A (Stage 1) of the N-1. Isp=318s. First flight 1969.

NK-15F.

  • Kuznetsov Lox/Kerosene rocket engine. 2180 kN. Development 1966-1972. Isp=350s. Engine had only a very short nozzle, the 24 engines around the periphery were to expand along a common central plug on the first stage of a studied N1 variant.

NK-15V.

  • Kuznetsov Lox/Kerosene rocket engine. 1648 kN. Development ended 1964. Isp=325s. Developed from the NK-9. 8 engines, featuring high-expansion nozzles, used on N1 Stage 2. First flight 1969.

NK-15VM.

  • Kuznetsov lox/lh2 rocket engine. 1960 kN. N-1 stage 2 (block B) replacement. Design 1972. Derivative of NK-15 with kerosene replaced by hydrogen. Canceled before hot-tests.

NK-19.

  • Alternate designation for NK-9V-11D54 Lox-Kerosene rocket engine.

NK-19.

  • Kuznetsov Lox/Kerosene rocket engine. N-1 stage 4. Development ended 1964. Based on NK-9 engine. Originally developed for the modernized second stage of the R-9 (abandoned). Also to have been used on GR-1 / 8K713 Stage 2. First flight 1969.

NK-19, NK-21.

  • Alternate designation for NK-9V rocket engine.

NK-21.

  • Alternate designation for NK-9V-11D53 Lox-Kerosene rocket engine.

NK-21.

  • Kuznetsov Lox/Kerosene rocket engine. N-1 stage 3 (block V). Out of production. Based on NK-9 engine. Propellants kerosene T-1 / LOX. 4 engines used in N-1 stage 3 (block V). Isp=318s. Used on N1 launch vehicle. First flight 1969.

NK-231.

  • Kuznetsov turbofan engine. 226.5 kN. Tu-160. Development ended 1992. Turbofan engine used in Tu-160. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=1980s.

NK-31.

  • Kuznetsov Lox/Kerosene rocket engine. 402 kN. Isp=353s. Upgraded version of engines for N-1 stage 4, with multiple ignition capability and increased operational lifetime. Mothballed in 1974. Proposed for Black Colt launch vehicle in 1993.

NK-33.

  • Kuznetsov Lox/Kerosene rocket engine. 1638 kN. N-1F, Kistler stage 1, Taurus II stage 1. Isp=331s. Modified version of original engine with multiple ignition capability. Never flown and mothballed in 1975 after the cancellation of the N1. Resurrected for Kistler, then for Taurus.

NK-33 LH2 Mod.

NK-33 LH2 Mod + 4 x LACE.

  • Kuznetsov air augmented rocket engine. 980.7 kN. N1-MOK. Study 1974. Isp=430s. Ultimate derivative of NK-9. Propellants changed to LH2/LOX, 16 x modified NK-33 engines + 4 Liquid Air Cycle Engine Liquid Air/LH2 boosters.

NK-35.

  • Alternate designation for NK-15VM Lox-LH2 rocket engine.

NK-35.

  • Kuznetsov lox/lh2 rocket engine. 1960 kN. Design 1972. Derivative of the NK-15 with kerosene replaced by hydrogen. The engine was canceled before hot-tests. Proposed for the UR-700M Mars booster in 1972, but this was not approved either.

NK-39.

  • Kuznetsov Lox/Kerosene rocket engine. 402 kN. N-1F stage 3. Development ended 1971. Isp=352s. Modified version of original engine with multiple ignition capability. Never flown and mothballed after the cancellation of the N1.

NK-43.

  • Kuznetsov Lox/Kerosene rocket engine. 1755 kN. N-1F, Kistler stage 2. Design 1975. Isp=346s. Modified version of original engine with multiple ignition capability. Never flown and mothballed after the cancellation of the N1. Resurrected for Kistler.

NK-9.

  • Kuznetsov Lox/Kerosene rocket engine. 441.3 kN. R-9, GR-1 stage 1. Isp=327s. Reached phase of stand testing in 1965, but then RD-111 selected. Later planned for 1st Stage of GR-1, but that rocket also cancelled.

NK-9V.

  • Kuznetsov Lox/Kerosene rocket engine. 441.3 kN. N-1 stage 2 / N-1 stage 3 / R-9 Stage 2. Developed for 2nd stage of the R-9 ICBM (alternative to RD-111 engine by OKB-456). NK-9 with increased expansion ratio. Isp=340s. First flight 1965.

NK-9V-11D53.

  • Kuznetsov Lox/Kerosene rocket engine. 449 kN. N-1 stage 3 (block V). Out of Production. Modification of NK-9 engine for the N-1 lunar rocket. May be identical to NK-21 (stage 3). Isp=340s.

NK-9V-11D54.

  • Kuznetsov Lox/Kerosene rocket engine. 392 kN. N-1 stage 4 (block G). Out of Production. Modification of NK-9 engine for the N-1 lunar rocket. May be identical to NK-19 (stage 4). Isp=340s.

Nodong.

  • North Korean Nitric acid/UDMH rocket engine. 144 kN. In production. Isp=255s. Used in North Korean missiles and Taepodong 1 satellite launcher. Derived from Isayev designs developed for Scud missiles and SLBM's of the Makeyev bureau. First flight 1998.

Nomad.

  • Government designation of G-1 LF2-Hydrazine rocket engine.

None.

  • Indicates that the stage shown is a propellant tank. The engine on another stage is drawing propellants from this tank. Performance shown is for that of the engine on the other stage. First flight 1964.

Northrop sled 4000 Ibf thrust.

  • Aerojet rocket engine. Northrop sled. Launch thrust 17.6 kN. Development begun 1948.

NOTS 100A.

  • NOTS solid rocket engine. Used on Blue Scout Junior launch vehicle. First flight 1960.

NOTS 124-C.

  • NOTS solid rocket engine.

NOTS 3SM.

  • NOTS solid rocket engine. 0.700 kN.

NOTS 401A.

  • NOTS solid rocket engine.

NOTS 8.

  • NOTS solid rocket engine. 5.1 kN.

NOTS Mod 551-B.

  • NOTS solid rocket engine.

NOTS-1.

  • NOTS solid rocket engine. 53.4 kN. Out of production. Isp=204s. Used on Caleb launch vehicle. First flight 1960.

NOTS-3.

  • NOTS solid rocket engine. 2.260 kN. Out of production. Isp=250s. Used on Caleb launch vehicle. First flight 1960.

NOTS-4.

  • NOTS solid rocket engine. 0.700 kN. Out of production. Isp=250s. Used on Caleb launch vehicle. First flight 1960.

NPS-2.

  • Rocketdyne nuclear/lh2 rocket engine. Nuclear Deep Space. Nuclear. Liquid hydrogen turbopumps, feed systems, and nozzles developed for KIWI-A, KIWI-B, Nerva, Pheobus IA, MFS-1, MFS-2, MFS-3, and Rover nuclear development systems.

NRL Viking.

  • Martin Lox/Alcohol rocket engine. 93 kN.

NSPO Booster.

  • Taiwan-NSPO solid rocket engine.

NSPO Sustainer.

  • Taiwan-NSPO solid rocket engine.

NSTAR.

  • NASA Cleveland electric/xenon rocket engine. 92 mN. Isp=3100s. Solar Electric Propulsion Technology Application Readiness program developed this 2.3 kW ion engine as primary propulsion for the Deep Space 1 comet and asteroid rendezvous probe, flew 1998.

Nuclear 12 Gw.

  • Notional nuclear/lh2 rocket engine. 2892 kN. Helios A, Helios C study 1960. Nuclear second stage. Isp=830s.

Nuclear 14 Gw.

  • Notional nuclear/lh2 rocket engine. 3334 kN. Study 1960. Nuclear second stage Isp=830s. Used on Helios B launch vehicle.

OME.

  • Aerojet N2O4/MMH rocket engine. 26.7 kN. Study 1972. Isp=316s. Engine used in Shuttle Orbiter Orbital Maneuvering System pods, for orbit insertion, maneuvering, and re-entry initiation. First flight 1981.

OMV Variable Thrust Engine.

  • TRW N2O4/MMH rocket engine. 0.578 kN. In Production.

OPI Methane Engine.

  • Orion Propulsion Lox/LCH4 rocket engine. 0.445 kN. Reaction control thruster for future manned spacecraft. Developed from 2001; tested 2005.

Orbitec Methane Engine.

  • Orbital Technologies Corporation Lox/LCH4 rocket engine. 0.133 kN. Reaction control thruster. Tested 2005. Used vortex-cooled combustion process to eliminate combustion chamber heating.

Orbus 1.

  • CSD solid rocket engine. 88 kN.

Orbus 21.

  • Manufacturer's designation of SRM-1 Solid rocket engine.

Orbus 6.

  • Manufacturer's designation of SRM-2 Solid rocket engine.

Oreste.

  • ATEF solid rocket engine.

Oriole.

  • Astrotech solid rocket engine.

Orion.

  • Aerojet solid rocket engine. 13 kN. Improved Orion motor was a bi-phase propellant system with thrust levels of 84.5 kN during the first four seconds of motor burn, trailing off to 13.3 kN at burnout at 25 seconds.

Orion 38.

  • Manufacturer's designation of Pegasus-3 Solid rocket engine.

Orion 50.

  • Manufacturer's designation of Pegasus-2 Solid rocket engine.

Orion 50S.

  • Manufacturer's designation of Pegasus-1 Solid rocket engine.

Orion 50SXLG.

  • OSC solid rocket engine.

Orion-1.

  • IIAE solid rocket engine.

Orion-2.

  • IIAE solid rocket engine.

Otrag.

  • Otrag N2O4/Kerosene rocket engine. 27.5 kN. First and upper stages of low-cost booster. Out of production. Isp=297s. Pressure-fed, using cheapest possible propellants. Injection pressure: 40-15 bar; thrust control: 100-40 %. First flight 1977.

Ottobrunn 300N.

  • Ottobrunn lox/lh2 rocket engine. 300 N. Upper stages. Developed 2000. Isp=415s - highest value ever achieved in Europe for an engine of such small size.

P230.

  • SNPE solid rocket engine. 6472.3 kN. In production. Isp=286s. Used on Ariane 5 launch vehicle. First flight 1996.

P241.

  • SEP solid rocket engine. 6470 kN. In development. Isp=275s. First flight 2002.

P320.

  • Rocketdyne, Friedrichshafen lox/lh2 rocket engine. Development. Launch thrust 129 kN. BORD 1/P320 BOELKOW (Germany)/Rocketdyne Technology. Pressure-fed.

P4.

  • SNPE solid rocket engine. 176.5 kN. Out of Production. Isp=273s. Used on Diamant B launch vehicle. First flight 1970.

P4-1 Booster.

  • Rocketdyne Lox/Kerosene rocket engine. 2.441 kN. AQM-37. Target System Booster. Pressure-fed. Isp=232s. First flight 1963.

P4-1 Sustainer.

  • Rocketdyne Lox/Kerosene rocket engine. 0.470 kN. AQM-37. Target System Sustainer. Pressure-fed. Isp=262s. First flight 1963.

P5 Hall thruster.

  • UM-USAF electric/xenon rocket engine. 246 mN. Isp=2326s. 5 kW Hall thruster for research purposes.

P6.

  • SNPE solid rocket engine for Diamant launcher. 29.4 kN. Out of production. Isp=211s. First flight 1965.

P-7.

  • Rocketdyne N2O4/Aerozine-50 rocket engine. Launch thrust 222.31 kN. Aspen Booster. Pressure-fed. Thrust from 12,000 lb to 50,000 lb at sea level.

P78-2.

  • Hughes electric/xenon rocket engine. 0.14 mN. Flown in 1979. Isp=350s. The thruster for the Scatha experiment consisted of one electron bombardment engines using xenon propellant.

P80.

  • Fiat-Avio solid rocket engine. 3040 kN. In production. Isp=279s. Vega's first stage, introduced advanced low-cost technologies that could be reused for future evolutions of Ariane-5 boosters.

P8E-9.

  • Rocketdyne Nitric acid/UDMH rocket engine. Lance. Launch thrust 205.44 kN. Lance Booster and Sustainer System. Pressure-fed. Sustainer 4400 -14,400 lbf, 227 sec Isp. Thrust and specific impulse values are at sea level. First flight 1972.

P9.5.

  • SNPE solid rocket engine. 690 kN. Isp=263s. Strap-on booster engine for Ariane 42P, Ariane 44LP, Ariane 44P. First flight 1988.

Peacekeeper 1.

  • Thiokol solid rocket engine. 2204.5 kN. In Production. MX Stage 1. Used as first stage of Taurus launch vehicle for initial test. Isp=282s.

Pegasus XL-1.

  • Hercules solid rocket engine. 589 kN. Isp=293s. Used on Pegasus XL launch vehicle. First flight 1994.

Pegasus XL-2.

  • Hercules solid rocket engine. 153.5 kN. Isp=290s. Used on Pegasus XL launch vehicle. First flight 1994.

Pegasus-1.

  • Hercules solid rocket engine. 484.9 kN. Isp=285s. Used on Pegasus, Taurus. First flight 1989.

Pegasus-2.

  • Hercules solid rocket engine. 118.2 kN. Isp=290s. Used on Pegasus, Taurus. First flight 1989.

Pegasus-3.

  • Hercules solid rocket engine. 34.6 kN. Isp=287s. Upper stage engine for Pegasus, Pegasus XL, Taurus. First flight 1989.

PEPL-70.

  • UM-JPL electric rocket engine. 1 kW Hall thruster, SPT type

Perigee Orbit Transfer Motor.

  • Fourth Academy solid rocket engine. 222.840 kN. In Production. Isp=280s. Basic perigee kick motor for CZ-2E launch vehicle. Featured glass fibre-wound case, HTPB propellant, 3-D finocyl propellant grain, and carbon/carbon throat insert. First flight 1990.

Pershing 2 St1.

  • Thiokol, Hercules solid rocket engine. 172 kN.

Pershing 2 St2.

  • Thiokol, Hercules solid rocket engine. 134 kN.

PF N204/Alumizine-1925k.

  • Notional N2O4/Alumizine rocket engine. 18,873 kN. Study 1967. Isp=280s. Used on Saturn LCB-Alumizine-250 launch vehicle.

PF N204/Alumizine-2300k.

  • Notional N2O4/Alumizine rocket engine. 22,562 kN. Study 1967. Isp=280s. Used on Saturn LCB-Alumizine-140 launch vehicle.

PF N204/UDMH-2165k.

  • Notional N2O4/UDMH rocket engine. 21,232 kN. Study 1967. Isp=267s. Used on Saturn LCB-Storable-250 launch vehicle.

PF N204/UDMH-2912k.

  • Notional N2O4/UDMH rocket engine. 28,552 kN. Study 1967. Isp=267s. Used on Saturn LCB-Storable-140 launch vehicle.

PF RP-1.

  • Notional Lox/Kerosene rocket engine. 20,306 kN. Study 1967. Isp=275s. Used on Saturn LCB-Lox/RP-1 launch vehicle.

Plug-Nozzle J-2.

  • Rocketdyne lox/lh2 rocket engine. 6864.6 kN. Study 1993. Plug nozzle version of J-2 proposed for certain Saturn V upgrades in late 1960's. Isp=425s. Used on DC-I launch vehicle.

Plug-Nozzle Pegasus.

  • Notional lox/lh2 rocket engine. 23,928 kN. Study 1966. Isp=459s. Used on Pegasus VTOVL launch vehicle.

Plug-Nozzle Rombus.

  • Notional lox/lh2 rocket engine. 101,988 kN. Study 1964. Isp=459s. Used on Rombus launch vehicle.

Plug-Nozzle SASSTO.

  • Notional lox/lh2 rocket engine. 1574.9 kN. Study 1967. Isp=459s. Used on SASSTO launch vehicle.

Plug-Nozzle SERV.

  • Notional lox/lh2 rocket engine. 31,980.2 kN. Study 1971. Isp=455s. Used on Shuttle SERV launch vehicle.

Plug-Nozzle SSME.

  • Notional lox/lh2 rocket engine. 3728.7 kN. Study 1978. Isp=485s. Used on VTOVL launch vehicle.

Pollux.

  • Thiokol solid rocket engine.

PRD-15.

  • Kartukov solid rocket engine. 392 kN. Strela-1 missile. Out of Production.

PRD-19M.

  • Kartukov solid rocket engine. KSShch Shchuka. Out of Production.

PRD-22.

  • Kartukov solid rocket engine. 3.920 kN. SM-30. Out of Production.

PRD-33.

  • SKB-30 solid rocket engine. 1962 kN.

PRD-36.

  • Kartukov solid rocket engine. V-600. Out of Production.

PRD-52.

  • Kartukov solid rocket engine. 784 kN. DBR-1 Yastreb. Out of Production. Thrust 80 tf at ignition, 75 tf at cutout.

PRD-61.

  • Kartukov solid rocket engine. 036 Vikhr. Out of Production.

PRD-70.

  • Kartukov solid rocket engine. 400/5V11 stage I. Out of Production.

Press Fed.

  • TRW N2O4/MMH rocket engine. 17.8 kN. Design concept 1960's. 1960's designs for 'big dumb booster'. Isp=300s.

Press Fed 1000k.

  • TRW N2O4/UDMH rocket engine. 9793 kN. Study 1968. 1960's designs for 'big dumb booster'. Isp=300s. Used on LCLV launch vehicle.

Press Fed 200k.

  • TRW N2O4/UDMH rocket engine. 2028 kN. Study 1968. 1960's designs for 'big dumb booster'. Isp=306s. Used on LCLV launch vehicle.

Press Fed 25k.

  • TRW Lox/Kerosene rocket engine. 245.2 kN. Design concept 1960's. 1960's designs for 'big dumb booster'. Isp=270s.

Press Fed 5748k.

  • TRW N2O4/UDMH rocket engine. 56,368 kN. Study 1968. 1960's designs for 'big dumb booster'. Isp=267s. Used on LCLV launch vehicle.

Prithvi.

  • HAL solid rocket engine.

Program 661.

  • EOS electric/cesium rocket engine. 8.9 mN. Flew 1962-1964. Isp=7400s. Cesium contact ion propulsion system used on three sub-orbital flight tests aboard Blue Scout Junior launch vehicles.

PRS-101.

  • Redmond electric/teflon rocket engine. 1.24 mN. In Production. Pulsed plasma thruster system. Completely solid state propulsion. Up to 100 W input power at 28 V DC, thrust to power ratio 12.4 microN/W. Isp=1350s.

PSLV-1.

  • ISRO solid rocket engine. 4860 kN. Isp=264s. Used on GSLV, PSLV. First flight 1993.

PSLV-3.

  • ISRO solid rocket engine. 328.7 kN. Isp=291s. Used on PSLV launch vehicle. First flight 1993.

PSLV-4.

  • ISRO N2O4/MMH rocket engine. 7 kN. Isp=308s. Used on PSLV launch vehicle. First flight 1993.

PW 1000000 lb LH2.

  • Pratt and Whitney lox/lh2 rocket engine. 4457 kN. Study 1988. Part of launch vehicle proposed by Martin as alternative to NLS. All figures estimated based on 1,000,000 lb thrust single engine. Isp=425s.

R-101B.36000-0.

  • Isayev Nitric acid/Amine rocket engine. R-101B/R-108 SAM. Developed 1950-51. Launch thrust 83.3 kN. Single chamber engine designed for use in the R-101B and R-108 (derivative of German Wasserfall).

R-13.

  • Dushkin Nitric acid/Solid hybrid rocket engine. Out of Production. Developed in the late 1950s by OKB Dushkin. It was a combined (powder+liquid) engine, characterized by a new technical approach conceived by Dushkin in the prewar design of the KRD-604.

R-1E.

  • Marquardt N2O4/MMH rocket engine. 0.110 kN. In Production from 1981. Isp=280s. Thruster developed as the Space Shuttle Orbiter's vernier attitude control and orbit adjust thruster. There were six employed in conjunction with the 38 R-40 thrusters.

R-200.

  • Dushkin rocket engine. 9.8 kN. Out of Production. Thrust variable 0.8 tf -1.0 tf.

R-3.

  • Alternate designation for D-2 Lox-Kerosene rocket engine.

R-31.

  • Lyulka turbojet engine. 91.2 kN. MiG-25. Out of Production. Used in MiG-25. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=2073s.

R-39 St2.

  • Makeyev N2O4/UDMH rocket engine.

R-39 St3.

  • Makeyev N2O4/UDMH rocket engine.

R-40A.

  • Marquardt N2O4/MMH rocket engine. 3.870 kN. In Production. Isp=306s. Thruster developed for Shuttle Orbiter orbit control. The orbiter had 38 long scarf, short scarf, or no scarf configurations, depending on the location.

R-40B.

  • Redmond N2O4/MMH rocket engine. 4 kN. In Production. Isp=293s.

R-42.

  • Redmond N2O4/MMH rocket engine. 0.890 kN. In Production. Isp=303s.

R-4D.

  • Marquardt N2O4/MMH rocket engine. 0.490 kN. Isp=312s. Developed as attitude control thruster for the Apollo Service and Lunar Modules in 1960s. In production for numerous satellites for apogee / perigee maneuvers, orbit adjustment, and attitude control.

R-56 Blok A.

  • Notional Nitric acid/Kerosene rocket engine. 4412 kN. R-56 Blok A. Notional engines for polyblock R-56, immense booster/ICBM; planned range 16,000 km. payload 35,000 kg. Tsniimash has 1:10 structural simulation model. Isp=320s.

R-56 Blok B.

  • Notional Nitric acid/Kerosene rocket engine. 784 kN. R-56 Blok B. Notional engines for polyblock R-56, immense booster/ICBM; planned range 16,000 km. payload 35,000 kg. Tsniimash has 1:10 structural simulation model. Isp=330s.

R6-117.

  • Chelomei N2O4/UDMH rocket engine. 132 kN. LK-1 Blok A. Developed 1964-66. Developed in cooperation with OKB-117 on the basis of the latter's main engine for the UR-100 stage II.

R-6C.

  • Marquardt N2O4/MMH rocket engine. 0.033 kN. In Production. Isp=290s.Derivative of Advent communications satellite thruster for Insat 1, Arbasat 1, and Olympus and HS-393 satellites.

Raven 1.

  • RO solid rocket engine. 44.5 kN.

Raven 11.

  • RO solid rocket engine. 105 kN.

Raven 2.

  • RO solid rocket engine. 44.5 kN.

Raven 5.

  • RO solid rocket engine. 44.5 kN.

Raven 6.

  • RO solid rocket engine. 52.5 kN.

Raven 7.

  • RO solid rocket engine. 44.5 kN.

Raven 8.

  • RO solid rocket engine. 50.1 kN.

RB-211-22B.

  • Rolls Royce turbofan engine. 29.4 kN. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=9900s. Used on L1011 launch aircraft for Pegasus, Pegasus XL. First flight 1990.

RB545.

  • Rolls Royce air augmented rocket engine. 367.7 kN. Used Liquid Air/Lox/LH2. Development ended 1985. Isp=700s. Used on HOTOL launch vehicle.

RBCC.

  • Rocketdyne lox/lh2 rocket engine. Launch thrust 111.158 kN. Isp>400s. Rocket Based Combined-Cycle A5 Development Engine; integrated rocket, air-augmented rocket, ramjet, and sramjet propulsion elements into a single flowpath.

RD R-21.

  • SKB-385 N2O4/UDMH rocket engine.

RD R-27.

  • Makeyev N2O4/UDMH rocket engine.

RD R-29 (1).

  • Makeyev N2O4/UDMH rocket engine. 682 kN.

RD R-29 (2).

  • Makeyev N2O4/UDMH rocket engine.

RD R-29R (1).

  • Makeyev N2O4/UDMH rocket engine. 682 kN.

RD R-29R (2).

  • Makeyev N2O4/UDMH rocket engine.

RD R-29RM (2).

  • Makeyev N2O4/UDMH rocket engine.

RD R-29RM (3).

  • Makeyev N2O4/UDMH rocket engine.

RD RT-1-3.

  • OKB-1 solid rocket engine. 240 kN.

RD RT-15-2.

  • OKB-1 solid rocket engine. 500 kN.

RD RT-21 (1).

  • MITT solid rocket engine.

RD RT-21-2.

  • MITT solid rocket engine.

RD RT-21-3.

  • MITT solid rocket engine. 245 kN.

RD-0101.

  • Kosberg Lox/Alcohol rocket engine. 39.2 kN. E-50A aircraft by Mikoyan. Out of Production. Chamber pressure 42,7 - 22,1 bar. Specific impulse 255 - 248,5 sec. Isp=255s.

RD-0102.

  • Kosberg Lox/Kerosene rocket engine. 39.2 kN. Yak-27V aircraft by Yakovlev. Out of Production. Based on RD-0101. Two ignitions possible. Chamber pressure 41,2 - 16,4 bar. Isp=260s.

RD-0103.

  • Kosberg Lox/Kerosene rocket engine. 34.6 kN. T-3, P-1 aircraft by Sukhoy. Out of Production. Based on RD-0102. Chamber pressure 37.3 - 15.7 bar. Isp=277s.

RD-0105.

  • Kosberg Lox/Kerosene rocket engine. 49.4 kN. Luna 8K72, Vostok 8K72 upper stage. Out of production. Isp=316s. Developed jointly with OKB-1 in nine months on the basis of OKB-1'ssteering chamber from the RD-107 engine. First flight 1958.

RD-0106.

  • Kosberg Lox/Kerosene rocket engine. 304 kN. R-9 stage 2. Gas generator cycle. Isp=330s. First flight 1961.

RD-0107.

  • Kosberg Lox/Kerosene rocket engine. 297.9 kN. R-9, Molniya 8K78, Voskhod 11A57 stage 3. Out of Production. Gas generator cycle. Isp=326s.

RD-0108.

  • Kosberg Lox/Kerosene rocket engine. 297.9 kN. Voskhod 11A57, Molniya 8K78 stage 3. Isp=326s. First flight 1960.

RD-0109.

  • Kosberg Lox/Kerosene rocket engine. 54.520 kN. 8A92 Vostok stage 3, 8K72K stage 3 (block E-Vostok). Out of production. Developed in 15 months. Isp=323s. First flight 1960.

RD-0110.

  • Kosberg Lox/Kerosene rocket engine. 297.9 kN. Soyuz 11A511, Molniya-M 8K78M. Precursor RD-0107 used in 11A57 Voskhod stage 2. Modified to increase reliability. Isp=326s. First flight 1964.

RD-0110MD.

  • Kosberg Lox/LNG rocket engine. 245 kN. Developed 1994-on. Prototype engine for tests with propellants LOX/liquified natural gas. Tests performed from 30 April 1998 on, test duration 20s.

RD-0120.

  • Kosberg lox/lh2 rocket engine. 1961 kN. Energia core stage. Design 1987. Isp=455s. First operational Russian cryogenic engine system, built to the same overall performance specifications as America's SSME, but using superior Russian technology.

RD-0120-CH.

  • Kosberg Lox/LCH4 rocket engine. 1576 kN. Design concept 1990's. Proposed variant of the RD-0120 engine using liquid methane instead of hydrogen as propellant. Isp=363s.

RD-0120M.

  • Kosberg lox/lh2 rocket engine. 1961 kN. Energia-M core stage. Development ended 1993. Isp=455s. From 1987 KBKhA worked on upgrading the 11D122 (RD-0120) engine for Energia-M launcher, including the possibility to throttle the engine down to 28% thrust.

RD-0120M-CH.

  • Kosberg Lox/LCH4 rocket engine. 1720 kN. Design concept 1990's. Proposed variant of the RD-0120M engine using liquid methane instead of hydrogen as propellant. Isp=372s.

RD-0120TD.

  • Kosberg tri-propellant (lox/lh2/kerosene) rocket engine. 1317 kN. Developed 1990's. Isp=419 / 452s. Experimental version of the RD-0120 engine. Tested by supply of high-pressure kerosene from test bench or adapted existing kerosene pump for tests.

RD-0122.

  • Kosberg lox/lh2 rocket engine. 2313 kN. Energia-M core stage. Planned for Angara central stage. Developed 1990-. Isp=460s. Upgrade of RD-0120 engine for Energia-M launcher with increased thrust. Prototype from RD-0120 hardware.

RD-0124.

  • Kosberg Lox/Kerosene rocket engine. 294.3 kN. In development. Isp=359s. Engine to succeed RD-0110 in second stage of Soyuz. Used staged combustion; chamber pressure increased from 70 to 160 bar, specific impulse from 326 to 359 seconds First flight 2001.

RD-0124-14D23.

  • Kosberg Lox/Kerosene rocket engine. 298.640 kN. Propoed in 1993 for Angara stage 2 verniers, Kvant-1 stage 1 vernier. Designed 1986-1990. Isp=331s. Variant of RD-0124 with shortened nozzle for sea-level operation.

RD-0124M.

  • Kosberg Lox/Kerosene rocket engine. 294.3 kN. Developed 1998-. Proposed single chamber variant of RD-0124. Obviously same turbopumps, but one single chamber. Isp=348s.

RD-0124M1.

  • Kosberg Lox/Kerosene rocket engine. 294.3 kN. Developed 1998-. Proposed single chamber variant of RD-0124. Obviously same turbopumps, but one single chamber with larger nozzle extension compared to RD-0124M. Isp=359s.

RD-0126.

  • Kosberg lox/lh2 rocket engine. 39.2 kN. Space tugs or upper stage for Onega or Yastreb versions of Soyuz. Isp=476s. Single annular chamber with expansion-deflection nozzle, separate turbopumps. Design concept 1993. Hot-tests in 1998.

RD-0126A.

  • Kosberg lox/lh2 rocket engine. 98 kN. Upper stages. Design concept 1996-. Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump. Isp=476s.

RD-0126E.

  • Kosberg lox/lh2 rocket engine. 39.2 kN. Upper stages. Design concept 1998-. Concept for a cryogenic engine for upper stages. Single annular chamber with straight expansion nozzle, common turbopump. Isp=472s.

RD-0128.

  • Kosberg lox/lh2 rocket engine. 98 kN. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. One single chamber with bell nozzle, separate turbopumps. Isp=474s.

RD-0129.

  • Kosberg Lox/LCH4 rocket engine. Developed 1990s.

RD-012U.

  • Bondaryuk ramjet engine. 76 kN. Burya. Out of production. 1.2 m diameter ramjet to be used in Burya cruise missile. Thrust is maximum thrust at cruise altitude. Specific impulse is that at cruise design point. Isp=1500s. First flight 1957.

RD-0131.

  • Kosberg lox/lh2 rocket engine. 98 kN. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump. Isp=467s.

RD-0132.

  • Kosberg lox/lh2 rocket engine. 98 kN. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. Derived from RD-0131, but four chambers with bell nozzles, common turbopump. Isp=469s.

RD-0132M.

  • Kosberg Lox/LNG rocket engine. 98 kN. Vozdushnyy Start stage 2. Design concept 1998-. Proposed variant of RD-0132, replacing hydrogen by liquid natural gas. Initially selected for stage 2 of Vozdushnyy Start project by Kompomash.

RD-0133.

  • Kosberg lox/lh2 rocket engine. 98 kN. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. Four chambers with bell nozzles, common turbopump. Isp=467s.

RD-0134.

  • Kosberg Lox/LNG rocket engine. 2038 kN. stage 1. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle variant of RD-0139. Isp=358s.

RD-0139.

  • Kosberg Lox/LNG rocket engine. 2038 kN. stage 1. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Gas generator cycle with turbine gas injection into supersonic nozzle. Isp=341s.

RD-0140.

  • Kosberg Lox/LNG rocket engine. 2086 kN. stage 2. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Gas generator cycle with turbine gas injection into supersonic nozzle. Isp=349s.

RD-0141.

  • Kosberg Lox/LNG rocket engine. 2251 kN. stage 1. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Obviously variant of RD-0141 with larger nozzle. Isp=353s.

RD-0142.

  • Kosberg Lox/LNG rocket engine. 2353 kN. stage 2. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Obviously variant of RD-0141 with larger nozzle. Isp=369s.

RD-0143.

  • Kosberg Lox/LNG rocket engine. 343 kN. Vozdushnyy Start stage 2. Design concept 1998-. Proposed variant of RD-0124, replacing kerosene by liquid natural gas. Selected for stage 2 of Vozdushnyy Start project by Kompomash. Isp=372s.

RD-0143A.

  • Kosberg Lox/LNG rocket engine. 343 kN. Vozdushnyy Start stage 1. Design concept 1998-. Proposed single chamber variant of RD-0143. Selected for stage 1 of Vozdushnyy Start project by Kompomash. Isp=370s.

RD-0144.

  • Kosberg Lox/LNG rocket engine. 147 kN. upper stage. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Radiation cooled nozzle extension. Isp=374s.

RD-0145.

  • Kosberg Lox/LNG rocket engine. 147 kN. upper stage. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Four-chamber variant of RD-0144. Isp=374s.

RD-0146.

  • Kosberg lox/lh2 rocket engine. 98.1 kN. Centaur upper stage (Atlas); high performance upper stages for Onega, Proton, Angara launch vehicles. Design concept 1998-. Isp=463s.

RD-0149.

  • Kosberg Lox/LNG rocket engine. 49 kN. upper stage. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Variant of RD-0141 with larger nozzle. Isp=370s.

RD-0154.

  • Kosberg Lox/Kerosene rocket engine. 294.3 kN. Design concept 2007. Engine proposed to replace RD-110 in Avrora improved version of Soyuz launch vehicle. The single chamber engine had a deployable nozzle extension for improved vacuum specific impulse.

RD-0155.

  • Kosberg Lox/Kerosene rocket engine. Design concept 2007. Launch thrust 902.5 kN. Engine proposed to replace RD-107 in Onega and Avrora versions of the Soyuz launch vehicle.

RD-018.

  • Bondaryuk ramjet engine. 98 kN. Buran missile, early version. Out of Production. Isp=1500s. 1.8 m diameter ramjet engine initially considered for Buran M-42. RD-020 adpopted later during development.

RD-020.

  • Bondaryuk ramjet engine. 103 kN. Buran M-42. Development ended 1957. Isp=1500s. Ramjet for Buran cruise missile. 8,500 km cruise at Mach 3.1 at 18-20 km altitude.

RD-0200.

  • Kosberg Nitric acid/Amine rocket engine. 58.8 kN. Lavochkin SAM, flew 1960. Out of Production. First liquid rocket engine by OKB-154, evolution of Isayev S2.1200 transferred to Kosberg. Thrust range 59 - 5.9 kN. Sea level specific impulse 230 - 166 sec

RD-0201.

  • Kosberg Nitric acid/Amine rocket engine. 58.060 kN. SAM V1100 by Grushin stage 3. Out of Production. Thrust range 59 - 28 kN. Isp=260s. First flight 1960.

RD-0202.

  • Kosberg N2O4/UDMH rocket engine. 2236 kN. UR-200 stage 1. Engine unit (DU - dvigatelnaya ustanovka) consisting of 1 RD-0204 for tank pressurization and three RD-0203. Isp=311s. First flight 1963.

RD-0203.

  • Kosberg N2O4/UDMH rocket engine. 559 kN. UR-200 stage 1. Hardware. DU consisting of 4 RD-0204 gimballed motors. Staged combustion cycle. Isp=311s. First flight 1964.

RD-0204.

  • Kosberg N2O4/UDMH rocket engine. 559 kN. UR-200 stage 1. Hardware. Diameter is per chamber. Staged combustion cycle. Variant of RD-0203 with additional pressure sensor. Isp=311s. First flight 1964.

RD-0205.

  • Kosberg N2O4/UDMH rocket engine. 606.4 kN. UR-200 stage 2. Engine unit consisting of 1 RD-0206 maine engine and 4 RD-0207 vernier/steering engines. Version of 8D44 and 8D45 with extended nozzle. Developed 1961. Isp=322s. First flight 1963.

RD-0206.

  • Kosberg N2O4/UDMH rocket engine. 575.5 kN. UR-200 stage 2. Developed 1961-64. Staged combustion cycle. Isp=326s. First flight 1964.

RD-0207.

  • Kosberg N2O4/UDMH rocket engine. 30.9 kN. UR-200 stage 2 vernier. Developed 1961-64. Gas generator cycle. Four vernier thrusters. Isp=297s. First flight 1964.

RD-0208.

  • Kosberg N2O4/UDMH rocket engine. UR-200 stage 1. Developed 1961-65. Stage 1 had three RD-0208 plus one RD-0209. Further developed into RD-0210.

RD-0209.

  • Kosberg N2O4/UDMH rocket engine. UR-200 stage 1. Developed 1961-65. Engine unit consisting of 1 RD-0211 for tank pressurization and three RD-0210. Modification of RD-0208 with tank pressurization. Further developed into RD--0211. First flight 1965.

RD-0210.

  • Kosberg N2O4/UDMH rocket engine. 582.1 kN. Isp=326s. Cluster of four similar engines used in second stage of Proton - one providing tank pressurization (8D412K/RD-0211) and three (8D411K/RD-0210). Staged combustion cycle. First flight 1965.

RD-0210-HC.

  • Kosberg Lox/Kerosene rocket engine. 592 kN. Design concept 1990's. Proposed variant of RD-0210 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=342s.

RD-0211.

  • Kosberg N2O4/UDMH rocket engine. 582.1 kN. Proton stage 2. Out of Production. Variant of RD-0210 providing tank pressurization. Staged combustion cycle. Isp=326s.

RD-0212.

  • Kosberg N2O4/UDMH rocket engine. 613 kN. Proton stage 3. Engine unit consisting of 1 RD-0213 maine engine and 4 RD-0214 vernier/steering engines. 8D48 essentially similar to 8D411 and 8D412 and has the same combustion chamber. Isp=324s. First flight 1967.

RD-0213.

  • Kosberg N2O4/UDMH rocket engine. 582.1 kN. Proton stage 3. Design 1962. Version of RD-0210. Staged combustion cycle (Oxidizer pre-burner gas routed to main chamber after driving turbine). Main engine for Proton Stage 3 in system RD-0212. Isp=326s.

RD-0214.

  • Kosberg N2O4/UDMH rocket engine. 30.980 kN. Proton stage 3 vernier. In Production. Based on RD-0207. Four used as steering engines for Proton Stage 3 in system RD-0212. Isp=293s. First flight 1967.

RD-0215.

  • Kosberg N2O4/UDMH rocket engine. 2450 kN. Developed 1962-65 for heavy Chelomei launcher (UR-900?) stage 1. Isp=310s. Engine unit consisting of 1 RD-0217 for tank pressurization and three RD-0216. Hardware not hot-tested.

RD-0216.

  • Kosberg N2O4/UDMH rocket engine. 219 kN. UR-100 stage 1. Isp=313s. Staged combustion cycle. Includes tank pressurization system (RD-0217 without tank press.). First launch November 1963, manufactured until 1974, operational until 1991. First flight 1965.

RD-0217.

  • Kosberg N2O4/UDMH rocket engine. 219 kN. UR-100, UR-100K stage 1. Out of Production. Staged combustion cycle. Version of RD-0216 without tank pressurization system. Manufacturing until 1974, operational use until 1991. Isp=313s.

RD-0221.

  • Kosberg N2O4/UDMH rocket engine. 78 kN. upper stage of unnamed missile by Mishin. Developed 1965-70. Isp=330s.

RD-0225.

  • Kosberg N2O4/UDMH rocket engine. 3.923 kN. Almaz space station orbital maneuvering. Hardware. Originally designed for UR-100 follow-ons spaceships. Two engines used on Almaz space station for orbital maneuvering, Pressure fed. Isp=287s. First flight 1974.

RD-0228.

  • Kosberg N2O4/UDMH rocket engine. 755 kN. R-36M / RS-20A (SS-18 mod-1) stage 2. Out of Production. Comprises single-chamber main engine RD-0229 plus four-chamber steering engine RD-0230. Further developed to RD-0255.

RD-0229.

  • Kosberg N2O4/UDMH rocket engine. R-36M / RS-20A (SS-18 mod-1) stage 2. Out of Production. Main engine. Staged combustion cycle. Used on Ikar launch vehicle. First flight 1974.

RD-0229M.

  • Kosberg Lox/LNG rocket engine. 883 kN. Vozdushnyy Start stage 1. Developed 1997. Derivative of RD-0229 for the propellants LOX and liquid natural gas (methane). Initial candidate for stage 1 propulsion of Vozdushnyy Start project by Kompomash.

RD-0230.

  • Kosberg N2O4/UDMH rocket engine. R-36M / RS-20A (SS-18 mod-1) stage 2 vernier. Out of Production. Vernier engine. Gas generator cycle. First flight 1974.

RD-0231.

  • Kosberg N2O4/UDMH rocket engine. 29 kN. P-700 Granit. Out of Production. Staged combustion cycle. Isp=275s. First flight 1970.

RD-0232.

  • Kosberg N2O4/UDMH rocket engine. UR-100N / Rokot Stage 1. Engine unit (DU - dvigatelnaya ustanovka) consisting of 1 RD-0234 for tank pressurization and three RD-0233. First flight 1972.

RD-0232?.

  • Manufacturer's designation of RD-0232 N2O4-UDMH rocket engine.

RD-0233.

  • Kosberg N2O4/UDMH rocket engine. 520 kN. UR-100N / RS-18 (SS-19) stage 1. Out of Production. Staged combustion cycle. Isp=310s. First flight 1974.

RD-0234.

  • Kosberg N2O4/UDMH rocket engine. 520 kN. UR-100N / RS-18 (SS-19) stage 1. Out of Production. Staged combustion cycle. Modification of RD-0233 including tank pressurization system. Isp=310s. First flight 1974.

RD-0234-CH.

  • Kosberg Lox/LCH4 rocket engine. 442 kN. Developed 1996-. Proposed variant of RD-0234 engine using LOX-liquid methane instead of N2O4/UDMH as propellants. Isp=343s.

RD-0234-HC.

  • Kosberg Lox/Kerosene rocket engine. 516 kN. Developed 1996-. Proposed variant of RD-0234 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=331s.

RD-0235.

  • Kosberg N2O4/UDMH rocket engine. 240 kN. UR-100N / RS-18 (SS-19) stage 2. Main engine based on RD-0217 with larger nozzle for altitude operation. Staged combustion cycle. Isp=320s. First flight 1972.

RD-0236.

  • Kosberg N2O4/UDMH rocket engine. 15.760 kN. UR-100N / RS-18 (SS-19) stage 2 vernier. Out of Production. Developed in 1969-1974 / problems not solved until 1978. Vernier engines. Gas generator cycle. Isp=293s.

RD-0237.

  • Kosberg N2O4/UDMH rocket engine. 4.9 kN. UR-100N / RS-18 (SS-19) stage 3. MIRV service block. Open cycle. Analogous to RD-0225, pressure fed. Steering engine for space vehicles gimbaling +/- 45 degree. Isp=200s. First flight 1972.

RD-0242.

  • Kosberg N2O4/UDMH rocket engine. 123.6 kN. sea-based missile booster stage developed 1977-83. Isp=302s. First concept planned N2O4/kerosene as propellant, but changed to N2O4/UDMH. Single ignition, 297 development tests. 50 engines for sale.

RD-0242-HC.

  • Kosberg Lox/Kerosene rocket engine. 125 kN. Developed 1998-. Proposed variant of RD-0242 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=312s.

RD-0242M.

  • Kosberg N2O4/MMH rocket engine. 98.1 kN. Design concept 1998-. Isp=335s. Proposed variant of RD-0242 engine for upper stages using MMH in place of UDMH. Reusable for 6 ignitions total. Throttling to 80%.

RD-0242M1.

  • Kosberg N2O4/MMH rocket engine. 98.1 kN. Design concept 1998-. Proposed variant of RD-0242 engine for upper stages using MMH in place of UDMH (adaptation to western market ?). Reusable for 6 ignitions total. Throttling to 80%. Isp=343s.

RD-0243.

  • Kosberg N2O4/UDMH rocket engine. 825.8 kN. R-29RM stage 1. Out of Production. Isp=300s. Consisted pf single-chamber main engine RD-0244 plus four-chamber steering engines RD-0245 driven by turbine exhaust gas. Engine submerged in propellant tank.

RD-0244.

  • Kosberg N2O4/UDMH rocket engine. 682 kN. R-29RM / RSM-54 (SS-N-23) stage 1. Out of Production. Main engine in system RD-0243. Staged combustion cycle. Submerged in propellant tank. Isp=310s. First flight 1985.

RD-0244 KD.

  • Alternate designation for RD-0244-HC Lox-Kerosene rocket engine.

RD-0244-HC.

  • Kosberg Lox/Kerosene rocket engine. 690 kN. Design concept 1990's. Proposed variant of RD-0244 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=332s.

RD-0245.

  • Kosberg N2O4/UDMH rocket engine. 211 kN. R-29RM / RSM-54 (SS-N-23) stage 1 vernier. Out of Production. Four-chamber steering engine in system RD-0243 driven by turbine exhaust gas. Isp=300s. First flight 1985.

RD-0245-HC.

  • Kosberg Lox/Kerosene rocket engine. 214 kN. Design concept 1990's. Proposed variant of RD-0245 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=320s.

RD-0246.

  • Kosberg N2O4/UDMH rocket engine. Design concept. Project for further development of RD-0243.

RD-0250.

  • Kosberg N2O4/UDMH rocket engine. Further development of RD-0235 main engine for projected modification of stage 2 of classified Chelomei rocket. Development ceased during study phase. Staged combustion cycle.

RD-0251.

  • Kosberg N2O4/UDMH rocket engine. Further development of RD-0236 steering engine for projected modification of stage 2 of classified Chelomei rocket. Development ceased during study phase. Gas generator cycle.

RD-0255.

  • Kosberg N2O4/UDMH rocket engine. 755 kN. R-36M2 / RS-20V (SS-18 Mod-4) stage 2. Comprises of single-chamber main engine RD-0256 plus four-chamber steering engines RD-0257. Development based on RD-0228 with thrust increase by 11%. First flight 1986.

RD-0256.

  • Kosberg N2O4/UDMH rocket engine. R-36M2 / RS-20V (SS-18 Mod-4) stage 2. Out of Production. Main engine of system RD-0255. Staged combustion cycle. First flight 1987.

RD-0256-HC.

  • Kosberg Lox/Kerosene rocket engine. 820 kN. Design concept 1996-. Proposed variant of RD-0256 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=344s.

RD-0256-Methan.

RD-0256-Methane.

  • Kosberg Lox/LCH4 rocket engine. 836 kN. Design concept 1996-. Proposed variant of RD-0256 engine using LOX-liquid methane instead of N2O4/UDMH as propellants. Isp=353s.

RD-0257.

  • Kosberg N2O4/UDMH rocket engine. R-36M2 / RS-20V (SS-18 Mod-4) stage 2 vernier. Out of Production. Steering engine of system RD-0255. Gas generator cycle. First flight 1987.

RD-0410.

  • Kosberg nuclear/lh2 rocket engine. 35.3 kN. Experimental nuclear engine, propellant LH2. Developed 1965-94. Isp=910s. Tested at Semipalatinsk test range in 1980s and was "the only operational nuclear engine in the USSR". First flight 1985.

RD-0411.

  • Kosberg nuclear/lh2 rocket engine. 392 kN. Full-size nuclear thermal engine. Design concept 1965-94. Planned full-size nuclear thermal engine for Mars expeditions. Never progressed beyond study stage. Isp=900s.

RD-0600.

  • Kosberg laser rocket engine. Space station "Skif". Developed 1970-85. Gas dynamic laser. Working medium gaseous carbon monoxide + air + nitrogen + ethanol. Flow rate up to 100 kg/s. Tests were performed at NII TP.

RD-0650TF.

  • Alternate designation for RD-0750 Lox-Kerosene-LH2 rocket engine.

RD-0750.

  • Kosberg lox/lh2/kerosene rocket engine. 1412 kN. Alternative for Angara central stage, MAKS. Developed 1997-. Isp=455s. Tripropellant derivative of RD-0120. Some components tested in RD-0120TD technology demonstration in cooperation with Aerojet.

RD-1.

  • Glushko Nitric acid/Kerosene rocket engine. 2.940 kN. Take-off acelleration of Pe-2, La-7, Yak-3, Su-6 airplanes. Developed 1941-45. First Russian liquid propellant rocket engine. Production 1944-45. Ignition was by an ethane-air mixture. Isp=200s.

RD-100.

  • Glushko Lox/Alcohol rocket engine. 304 kN. R-1, V-1A. Isp=237s. Russian copy of the V-2 engine using Russian materials - which made it very difficult! German rocket scientists assisted in its development. First flight 1948.

RD-101.

  • Glushko Lox/Alcohol rocket engine. 404 kN. R-2 and V-2A. Isp=237s. Developed simultaneously with the RD-100 but with no German involvement. More compact, increased thrust, increased chamber pressure and higher alcohol concentration. First flight 1949.

RD-102.

  • Glushko Lox/Alcohol rocket engine. 428 kN. R-3A. Development ended 1951. Project for R-3A experimental missile. Stopped in favor of RD-103. Isp=235s.

RD-102?.

  • Alternate designation for RD-3A rocket engine.

RD-103.

  • Glushko Lox/Alcohol rocket engine. 500 kN. R-5. Out of Production. Isp=243s. Final extrapolation of the V-2 rocket engine in Russia. First flight 1953.

RD-103M.

  • Glushko Lox/Alcohol rocket engine. 500.1 kN. R-5M 8K51. Isp=248s. First flight 1953.

RD-103RD.

  • Glushko Lox/Alcohol rocket engine. M5RD. Out of Production.

RD-105.

  • Glushko Lox/Kerosene rocket engine. 627.6 kN. R-7 ICBM stage 1 (strap-on) initial project. Out of Production. Isp=302s. Single chamber engine intended for the R-7 strap-ons in mid-1950s. Subsequently replaced by the 4 chamber RD-107.

RD-106.

  • Glushko Lox/Kerosene rocket engine. 645.3 kN. R-7 ICBM stage 2 (core) initial project. Out of Production. Isp=310s. Single chamber engine intended for the R-7 sustainer. Version of RD-105 with larger nozzle. Subsequently replaced by the 4 chamber RD-108.

RD-107-11D511.

  • Glushko Lox/Kerosene rocket engine. 992 kN. Soyuz 11A511-0, Soyuz 11A511U-0. Design 2000. Diameter is per chamber. Isp=314s. First flight 1965.

RD-107-11D511P.

  • Glushko Lox/Kerosene rocket engine. 996.4 kN. Soyuz 11A511U2-0. Out of production. OKB Glushko. Used on 11A511U2 Stage 0. Propellants kerosene (RG-1) / Lox. Diameter is per chamber. Isp=314s. First flight 1982.

RD-107-8D728.

  • Glushko Lox/Kerosene rocket engine. 996 kN. Molniya 0, Molniya 8K78M-0. OKB Glushko. Used on Molniya 8K78M and 11A57 Stage 0. Propellants kerosene (RG-1 or T-1) / Lox. Diameter is per chamber. Isp=314s. First flight 1964.

RD-107-8D74.

  • Glushko Lox/Kerosene rocket engine. 971 kN. R-7 8K71, Vostok 8K72, Vostok 8K72K strap-ons. Isp=306s. First flight 1957. Used four combustion chambers fed by single turbopump to circumvent combustion instability problems with larger chambers 1950's.

RD-107-8D74-1958.

  • Glushko Lox/Kerosene rocket engine. 996 kN. Luna 8K72-0. Out of production. Diameter is per chamber. Isp=312s. First flight 1958.

RD-107-8D74-1959.

  • Glushko Lox/Kerosene rocket engine. 996 kN. Out of production. Diameter is per chamber. Isp=313s. Used on Vostok 8K72K launch vehicle. First flight 1960.

RD-107-8D74K.

  • Glushko Lox/Kerosene rocket engine. 996 kN. Developed in 1957-1960. Used in strap-ons for Molniya 8K78, R-7A 8K74, Voskhod 11A57, Vostok 8A92, Vostok 8A92M. Isp=313s. Fuel T-1 or RG-1 kerosene. First flight 1959.

RD-107-8D74PS.

  • Glushko Lox/Kerosene rocket engine. 971 kN. Sputnik 8K71PS-0. Out of Production. OKB Glushko. Used on 8K71PS Stage 0. Developed in 1956-1957. Flown 1957-1958. Propellants kerosene (RG-1) / Lox. Diameter is per chamber. Isp=306s.

RD-107-8D76.

  • Glushko Lox/Kerosene rocket engine. 971 kN. Sputnik 8A91-0. Out of Production. OKB Glushko. Used on 8A91 Stage 0. Developed in 1956-1957. Propellants kerosene (RG-1) / Lox. Diameter is per chamber. Isp=310s. First flight 1958.

RD-108-11D512.

  • Glushko Lox/Kerosene rocket engine. 997 kN. Soyuz 11A511-1, Soyuz 11A511U-1. Design 2000. Diameter is per chamber. Isp=315s. First flight 1965.

RD-108-11D512P.

  • Glushko Lox/Kerosene rocket engine. 1011 kN. Soyuz 11A511U2-1. Out of production. Isp=319s. A 1-2 second specific impulse increase was made possible by the use of synthetic fuel Sintin and a modified mixing head. First flight 1982.

RD-108-8D727.

  • Glushko Lox/Kerosene rocket engine. 977 kN. Molniya 1, Molniya 8K78M-1. OKB Glushko. Used on Molniya 8K78L, 8K78M and 11A57 Stage 1. Propellants kerosene (RG-1 or T-1) / Lox. Diameter is per chamber. Isp=316s. First flight 1964.

RD-108-8D727K.

  • Glushko Lox/Kerosene rocket engine. 976 kN. Molniya 8K78-3. Out of Production. Isp=316s.

RD-108-8D75.

  • Glushko Lox/Kerosene rocket engine. 912 kN. R-7 8K71-1, Vostok 8K72-1, Vostok 8K72K-1. OKB Glushko. Used on 8K71 R-7 Stage 1. Developed in 1954-1955. Propellants kerosene (RG-1) / Lox. Diameter is per chamber. Isp=308s. First flight 1957.

RD-108-8D75-1958.

  • Glushko Lox/Kerosene rocket engine. 941 kN. Luna 8K72-1. Out of production. Diameter is per chamber. Isp=315s. First flight 1958.

RD-108-8D75-1959.

  • Glushko Lox/Kerosene rocket engine. 941 kN. Out of production. Further development of 8D74-1958, 1958-1959. Diameter is per chamber. Isp=315s. Used on Vostok 8K72K launch vehicle. First flight 1960.

RD-108-8D75K.

  • Glushko Lox/Kerosene rocket engine. 941 kN. Molniya 8K78-1, R-7A 8K74-1, Voskhod 11A57-1, Vostok 8A92-1, Vostok 8A92M-1. Diameter is per chamber. Isp=315s. First flight 1959.

RD-108-8D75PS.

  • Glushko Lox/Kerosene rocket engine. 912 kN. Sputnik 8K71PS-1. Out of Production. Diameter is per chamber. Isp=308s. First flight 1957.

RD-108-8D77.

  • Glushko Lox/Kerosene rocket engine. 804 kN. Sputnik 8A91-1. Out of Production. Diameter is per chamber. Isp=315s. First flight 1958.

RD-109.

  • Glushko lox/udmh rocket engine. 101.6 kN. Developed 1957-60. Isp=334s. Intended for second stage of Lox/UDMH 8K73 version of R-7. Abandoned because of Korolev's refusal to use such a toxic fuel. Later basis for RD-119 used on the Kosmos space launcher.

RD-110.

  • Glushko Lox/Kerosene rocket engine. 1374 kN. Development ended 1949. Isp=285s. For R-3 IRBM, 19 ED-140 7 tonne chambers used as preburners to feed a main mixing chamber, a scale-up of the V-2 production motor. Tested, but technical problems too severe.

RD-111.

  • Glushko Lox/Kerosene rocket engine. 1628 kN. R-9 stage 1. Isp=317s. Developed for R-9 ICBM. It had special flexible pipelines and gimbals, allowing lox loading in 20 minutes. First flight 1961.

RD-112.

  • Glushko lox/udmh rocket engine. 1089 kN. ICBM stage 1 (stage 2 was RD-113). Developed 1960. Isp=344s.

RD-113.

  • Glushko lox/udmh rocket engine. 1138 kN. ICBM stage 2 (stage 1 was RD-112). Developed 1960. Upper stage version of RD-112 with larger nozzle. Isp=360s.

RD-114.

  • Glushko lox/udmh rocket engine. 1653 kN. Used in ICBM stage 1 (stage 2 was RD-115). Developed 1961-65. Isp=341s.

RD-115.

  • Glushko lox/udmh rocket engine. 1726 kN. ICBM stage 2 (stage 1 was RD-114). Developed 1961-65. Upper stage version of RD-114 with larger nozzle. Isp=357s.

RD-117.

  • Glushko Lox/Kerosene rocket engine. 1021.097 kN. Soyuz ST stage 1. In production. Update of RD-107. Little performance change from RD-107, changes may mainly relate to use of all-Russian components. Isp=310s. First flown 2001.

RD-117PF.

  • Glushko Lox/Kerosene rocket engine. manned Soyuz-launcher stage 1. Design concept. Update of RD-107. Probably version using Sintin instead of kerosene.

RD-118.

  • Glushko Lox/Kerosene rocket engine. 999.601 kN. In production. Isp=311s. Update of RD-107, used in Soyuz ST launcher. Little performance change from RD-107, changes may mainly relate to use of all-Russian components. First flight 2001.

RD-119.

  • Glushko lox/udmh rocket engine. 105.5 kN. Kosmos 1 stage 2. Out of production. Isp=352s. Derived from RD-109 motor originally intended for the second stage of a Lox/UDMH version of the R-7. First flight 1961.

RD-120.

  • Glushko Lox/Kerosene rocket engine. 833 kN. Zenit stage 2. In production. Isp=350s. High altitude engine used in the Zenit second stage. First production Russian engine to be test fired in the United States (3 test burns were made). First flight 1985.

RD-120.01.

  • Glushko Lox/Kerosene rocket engine. 784 kN. Design concept. Isp=329s.

RD-120.03.

  • Glushko Lox/Kerosene rocket engine. 882 kN. Design concept. Isp=353s.

RD-120K.

  • Glushko Lox/Kerosene rocket engine. 873 kN. Soyuz M stage 1, 2. Proposed for X-34. Isp=336s. Sea-level variant of RD-120. As of 1996 RD-120 prototype with 1.8 m diameter had been built, development time estimated for three years.

RD-120M.

  • Alternate designation for RD-182 Lox-LCH4 rocket engine.

RD-120M.

  • Glushko Lox/Kerosene rocket engine. 850.4 kN. PacAstro-2 stage 1. Out of Production. Sea-level variant of RD-120 engine, similar to RD-120K. Gimbaling +/- 6 degree in two planes. Isp=330s.

RD-123.

RD-127.

  • Yuzhnoye solid rocket engine. Maneuvering vehicle bang-bang propulsion, consisted of 25 small solid-propellant motors, probably for homing vehicles or multiple warhead dispensing applications.

RD-134.

  • Glushko Lox/Kerosene rocket engine. 343 kN. upper stage. Design concept. Isp=357s. Proposed upper stage kerosene engine. Gimbaling +/- 3 degree in two planes. Four chamber s with one common turbopump. Nozzle expansion ratio is 170/0.05=3400.

RD-134R.

  • Glushko Lox/Kerosene rocket engine. 343 kN. Angara stage 2 vernier. Design concept 1993-on. Proposed in initial study for Angara by RKK Energia in1993. Steering engines for Angara upper stage. Kerosene RG-1.

RD-135.

  • Glushko lox/lh2 rocket engine. upper stage. Developed -1976. Experimental cryogenic engine. (Ref. May be not correct.)

RD-146.

  • Glushko Lox/Kerosene rocket engine. 883 kN. Angara stage 2. Design concept 1993-on. Sea-level variant of RD-120 engine. Proposed in initial study for Angara by RKK Energia in1993. Kerosene RG-1.

RD-160.

  • Glushko Lox/LCH4 rocket engine. 19.6 kN. Upper stage. Developed 1993-1996. Isp=380s. Methane version of lox / kerosene upper stage engine RD-161. Gimbaling +/- 6 degree in two planes.

RD-161 (1).

  • Manufacturer's designation of RD-161-1 Lox-Kerosene rocket engine.

RD-161 (2).

  • Manufacturer's designation of RD-161-2 Lox-Kerosene rocket engine.

RD-161-1.

  • Glushko Lox/Kerosene rocket engine. 19.6 kN. Development ended 2000. Proposed for use on Soyuz M-3. Basic version. Engine Cycle: closed gas generator. Feed Method: turbopump. Isp=360s.

RD-161-2.

  • Glushko Lox/Kerosene rocket engine. 19.9 kN. Design concept 1990's. Proposed for use on Soyuz M-3. Version with uncooled nozzle extension. Engine Cycle: closed gas generator. Feed Method: turbopump. Isp=365s.

RD-161P.

  • Glushko H2O2/Kerosene rocket engine. 24.5 kN. Soyuz M stage 3 (block LM). Developed 1993-. Two thrust levels. Minimum 1500 kgf. Proposed for use on Soyuz M-3. Version for H2O2 fuel, concentration 96-98%. Isp=319s.

RD-167.

  • Glushko Lox/LCH4 rocket engine. 353 kN. Upper stage. Design concept 1990's. Isp=379s. Proposed upper stage engine, a methane variant of RD-134. Gimbaling +/- 3 degree in two planes. Four chambers with one common turbopump.

RD-169.

  • Glushko Lox/LCH4 rocket engine. 167 kN. Riksha-0 stage 1. Design concept 1990's. Isp=351s. LOX/Methane engine derived from RD-120. Gimbaling +/- 8 degree in two planes. In 1996 prototype development was estimated to take four years from go-ahead.

RD-170.

  • Glushko Lox/Kerosene rocket engine. 7903 kN. Energia strap-on. Developed 1973-1985. Isp=337s. First flight 1987. Used one-plane gimablling versus the two-plane gimablling required on the RD-171 of the Zenit launch vehicle. Designed for 10 reuses.

RD-171.

  • Glushko Lox/Kerosene rocket engine. 7903 kN. Zenit stage 1. In production. Isp=337s. RD-171 used two-plane gimablling versus one-plane gimablling on RD-170 developed in parallel for Energia. First flight 1985.

RD-172.

  • Glushko Lox/Kerosene rocket engine. 8354 kN. Zenit-3 stage 1 (?). Developed -1994. Uprated version of RD-171. To have been qualified for flight 1994. Isp=337s.

RD-173.

  • Glushko Lox/Kerosene rocket engine. 8181 kN. Zenit-3 stage 1 (?). Design concept 1990's. Uprated version of RD-171 with 4 chambers, 1 turbo-pump and 2 gas generators. Intended for uprated Zenit named Zenit 3 Isp=337s.

RD-174.

  • Glushko Lox/Kerosene rocket engine. 7905 kN. Angara stage I. Developed 1995-.

RD-180.

  • Glushko Lox/Kerosene rocket engine. 4152 kN. Atlas III, Atlas V stage 1. In production. Isp=337s. First flight 2000. Two-thrust-chamber derivative of the four-chamber RD-170 used on Zenit.

RD-182.

  • Glushko Lox/LCH4 rocket engine. 902 kN. Riksha (-1, -2) stage 1. Developed 1994-. Isp=353s. Methane variant of RD-120K engine. Thrust range and Isp range due to throat diameter and chamber pressure. Gimbaling +/- 6 degree in two planes.

RD-182M.

  • Glushko Lox/LNG rocket engine. 882 kN. Vozdushnyy Start stage 1. Developed 1998-. Variant of RD-182 engine for liquid natural gas (mainly CH4). Proposed initial candidate for project Vozdushnyy Start of Kompomash.

RD-183.

  • Glushko Lox/LCH4 rocket engine. 9.8 kN. Developed 1996-. Isp=360s. Main engine for apogee stage of Riksha-1 launcher project. Gimbaling +/- 10 degree in two planes. Nozzle expansion ratio is 75/0.055=1364.

RD-184.

  • Glushko Lox/LCH4 rocket engine. Developed 1996-on. Isp=322s. Attitude correction engine for apogee stage of Riksha-1 launcher project (together with RD-183). Gimbaling +/- 20 degree in two planes.

RD-185.

  • Glushko Lox/LCH4 rocket engine. 179 kN. Riksha-0 stage 2. Developed 1996-. Isp=378s. Upper stage version of RD-169 with larger nozzle. Gimbaling +/- 4 degree in two planes.

RD-190.

  • Glushko Lox/LCH4 rocket engine. 1000 kN. Riksha-0 stage 1. Developed 1996-. The RD-190 consists of 6 RD-169 engines. Each chamber can be gimbaled individually in two planes by +/- 8 degree. Isp=351s.

RD-191.

  • Glushko Lox/Kerosene rocket engine. 2079 kN. Isp=337s. Proposed for stage 1 of Angara. Single chamber from 4-chamber RD-170 would have been cheap and fast to develop. Only reached the draft project stage by 2003. Gimbaling +/- 8 degree in two planes.

RD-191M.

  • Glushko Lox/Kerosene rocket engine. 1976 kN. Angara stage I. Developed 1996-. Single chamber version of the RD-170 / RD-171. Isp=337s.

RD-192.

  • Glushko Lox/LCH4 rocket engine. 2138 kN. Isp=356s. Proposed methane-variant of RD-191. Gimbaling +/- 8 degree in two planes. In 1996 prototype development was estimated to take four years from go-ahead. Nozzle expansion ratio is 262/0.75=349.

RD-192.2.

  • Glushko Lox/LCH4 rocket engine. 1942 kN. Developed 1996-on. Isp=354s. Proposed variant of RD-192. Staged combustion cycle with fuel-rich gas generator. Gimbaling +/- 8 degree in two planes.

RD-192.3.

  • Glushko Lox/LCH4 rocket engine. 2089 kN. Developed 1996-on. Proposed variant of RD-192. Gas generator cycle. Gimbaling +/- 8 degree in two planes. Status 1998 was project based on RD-191 protoype, development estimated for four years. Isp=341s.

RD-192S.

  • Glushko Lox/LCH4 rocket engine. 2128 kN. Developed 1996-on. Isp=371s. Proposed variant of RD-192. Staged combustion cycle with oxidizer-rich gas generator. Gimbaling +/- 8 degree in two planes.

RD-1KhZ.

  • Glushko Nitric acid/Kerosene rocket engine. 2.940 kN. take-off acelleration of Pe-2R, La-7R, Yak-3, Su-6, Su-7, La-120R airplanes. Developed 1941-46. The RD-1KhZ was a variant of the RD-1 engine with chemical ignition. Production 1944-45. Isp=200s.

RD-2.

  • Glushko Nitric acid/Kerosene rocket engine. 6 kN. experimental. Developed 1945-47. The RD-2 was based on the RD-1 engine. Used chemical ignition. Isp=200s.

RD-200.

  • Glushko Nitric acid/Kerosene rocket engine. 98.508 kN. vertical sounding rocket. Developed -1951. Isp=234s.

RD-210.

  • Glushko Nitric acid/Kerosene rocket engine. 29.850 kN. vertical sounding rocket. Developed -1954. Isp=241s.

RD-211.

  • Glushko Nitric acid/Kerosene rocket engine. 642.3 kN. long-distance missile. Developed 1952-55. Original four-chamber engine design planned for use on the R-12 IRBM. Abandoned due to limited thrust and the RD-214 was developed in its place. Isp=261s.

RD-212.

  • Glushko Nitric acid/Kerosene rocket engine. 623 kN. Developed 1952-56. Isp=253s. Original four-chamber engine design planned for the booster stage of the Buran intercontinental ramjet missile. Abandoned due to limited thrust; RD-213 was developed instead.

RD-213.

  • Glushko Nitric acid/Kerosene rocket engine. 755 kN. Winged rocket M-40 (2). Development ended 1957. Two thrust levels. Ignition with propellant TG-02. Chamber pressure 233,8 / 46,6 bar. Specific impulse 223 / 231 sea level. Isp=254s.

RD-214.

  • Glushko Nitric acid/Kerosene rocket engine. 730 kN. R-12, Kosmos 11K63 stage 1. Isp=264s. Single turbopump driven by H2O2 gas generator feeding four fixed chambers. Ignition with propellant TG-02. First flight 1957.

RD-215.

  • Glushko Nitric acid/UDMH rocket engine. 864 kN. R-14, Kosmos 11K63 stage 1. Out of Production. Original intended use unknown. Two RD-215 clustered to make RD-216. Isp=291s. First flight 1966.

RD-216.

  • Glushko Nitric acid/UDMH rocket engine. 1728 kN. R-14, Kosmos 11K65 stage 1. Isp=291s. RD-216 was an assembly of 2 RD-215's with 2 combustion chambers and 2 turbines. Two sets of these were in turn used in the first stage of the R-14. First flight 1964.

RD-216M.

  • Glushko Nitric acid/UDMH rocket engine. Kosmos-3M stage I. Out of Production.

RD-217.

  • Glushko Nitric acid/UDMH rocket engine. 865 kN. R-16 stage 1. Out of Production. Original intended use unknown. Three RD-217 clustered to make RD-218. Isp=289s. First flight 1961.

RD-218.

  • Glushko Nitric acid/UDMH rocket engine. 2592 kN. R-16 stage 1. Isp=289s. Consisted of three RD-217; had 6 combustion chambers and 3 turbines; powered the R-16 ICBM. First flight 1960.

RD-219.

  • Glushko Nitric acid/UDMH rocket engine. 883 kN. R-16 stage 2. Isp=293s. Derivative of RD-217 with a truss and piping changes. Despite higher expansion ratio, engine was shorter than first stage version, with relatively low performance. Flown 1960-1972.

RD-220.

  • Glushko Nitric acid/UDMH rocket engine. 1074 kN. missile stage 1 (stage 2 used RD-221). Developed 1960-. Isp=306s.

RD-221.

  • Glushko Nitric acid/UDMH rocket engine. 1118 kN. missile stage 2 (stage 1 used RD-220). Developed 1960-. Isp=318s.

RD-222.

  • Glushko Nitric acid/UDMH rocket engine. 1634 kN. missile stage 1 (stage 2 used RD-223). Developed 1960-61. Precursor to RD-253. Isp=302s.

RD-223.

  • Glushko Nitric acid/UDMH rocket engine. 1697 kN. missile stage 2 (stage 1 used RD-222). Developed 1960-61. Precursor to RD-253. Isp=314s.

RD-224.

  • Glushko Nitric acid/UDMH rocket engine. 1778 kN. R-26 stage 1. Out of production. RD-224 is a block of 2 RD-225s. An upper stage thrust chamber was developed under designation U102-000. Isp=294s. First flight 1961.

RD-225.

  • Glushko Nitric acid/UDMH rocket engine. 889 kN. R-26 stage 1. Out of Production. Two clustered together to make RD-224. Isp=294s. First flight 1961.

RD-226 ?.

  • Alternate designation for U102-000 Nitric acid-UDMH rocket engine.

RD-250.

  • Glushko N2O4/UDMH rocket engine. 881 kN. R-36-0 stage 1, Tsyklon 2 stage 1. Out of Production. Assembly of 3 RD-250 units make RD-251. Isp=301s.

RD-251.

  • Glushko N2O4/UDMH rocket engine. 2643 kN. R-36-0 stage 1, Tsyklon 2 stage 1. In production. Assembly of 3 RD-250-type units. Isp=301s. First flight 1965.

RD-252.

  • Glushko N2O4/UDMH rocket engine. 940.5 kN. R-36-0 stage 2; Tsyklon 2 stage 2. In production. Used modified chamber from RD-219, nozzle is conventional, so performance is higher. Isp=317s. First flight 1965.

RD-253.

  • Glushko N2O4/UDMH rocket engine. 1745 kN. In Production. Version of RD-253 with thrust increased by 7%. Included an additional gas generator for tank pressurization. First flight 1986.

RD-253-11D48.

  • Glushko N2O4/UDMH rocket engine. 1635 kN. Isp=316s. Six gimballed single chamber RD-253s provide the first stage power for the UR-500 Proton launch vehicle. First flown in 1965.

RD-253-14D14.

  • Glushko N2O4/UDMH rocket engine. 1746 kN. Proton KM-1. In production. Developed in 1990s. Isp=317s. First flight 1999.

RD-253-UR-700.

  • Glushko N2O4/UDMH rocket engine. 1745 kN. Designed 1964-1968. UR-700 Stage 3. Development of RD-253 with increased expansion ratio for upper stage use.

RD-254.

  • Glushko N2O4/UDMH rocket engine. 1716 kN. N-1 upper stage, UR-700 stage 3. Study 1961. Proposed for use in N-1. High altitude version of RD-253 for 2nd stages. First flight 1974.

RD-261.

  • Glushko N2O4/UDMH rocket engine. 3032 kN. Tsyklon 3 stage 1. In production. Based on RD-251 Isp=301s. First flight 1977.

RD-262.

  • Glushko N2O4/UDMH rocket engine. 941 kN. Tsyklon 3 stage 2. In production. Based on RD-252 Isp=317s. First flight 1977.

RD-263.

  • Glushko N2O4/UDMH rocket engine. 1155 kN. R-36M / RS-20A (SS-18 Mod 1) stage 1. Out of Production. Four RD-263 engines combined into RD-264 system. Isp=318s.

RD-263F.

  • Glushko N2O4/UDMH rocket engine. Developed 1980. Project to upgrade RD-263. Upgrade was realized in RD-273 engine.

RD-264.

  • Glushko N2O4/UDMH rocket engine. 4521 kN. R-36M / RS-20A (SS-18 Mod 1) stage 1. Consists of four RD-263 engines. Isp=318s. Used on Dnepr launch vehicle. First flight 1986.

RD-268.

  • Glushko N2O4/UDMH rocket engine. 1236 kN. MR-UR-100 / RS-16 (SS-17) stage 1. Out of Production. First flight 1976. Modification of RD-263 engine. Isp=319s. First flight 1990.

RD-270.

  • Glushko N2O4/UDMH rocket engine. 6713 kN. UR-700, R-56 stage 1. Development ended 1968. Isp=322s. Developed 1962-1971, largest rocket engine ever built in the Soviet Union, answer to F-1. Tested but cancelled before combustion instability problems solved.

RD-270M.

  • Glushko exotic N2O4/Pentaborane rocket engine. 7159 kN. Isp=365s. In 1962-1970 Glushko studied use of Pentaborane 'zip' propellants in his monster RD-270 engine. Created immense toxicity problems but increased specific impulse of the engine by 42 seconds.

RD-273.

  • Glushko N2O4/UDMH rocket engine. 1238 kN. Developed 1975-82. Upgrade of RD-263 in 1982 based on RD-263F project.

RD-274.

  • Glushko N2O4/UDMH rocket engine. 4952 kN. Developed 1975-85. Upgrade of RD-264 engine with increased chamber pressure and thrust. Development stopped due to problems with turbopump shaft balance.

RD-275.

  • Manufacturer's designation of RD-253 rocket engine.

RD-275.

  • Glushko N2O4/UDMH rocket engine. 1745 kN. Proton stage 1. In Production. Uprated version of RD-253, developed in the 1980's. Isp=317s. First flight 1986.

RD-280.

  • Glushko N2O4/Aerozine-50 rocket engine. 117.6 kN. Experimental engine. Study 1961. Experimental engine using Aerozine 50 (50% UDMH + 50% hydrazine) as fuel. Isp=350s.

RD-293.

  • Yuzhnoye rocket engine. Maneuvering vehicle axial maneuvering.

RD-2MZV.

  • Dushkin Nitric acid/Kerosene rocket engine. 13.7 kN. I-270. Developed 1944-47. Thrust variable 0.1-0.3 tf / 0.35-1.4 tf.

RD-2MZV-F.

  • Dushkin Nitric acid/Kerosene rocket engine. 19.6 kN. Samolet 5. Developed 1946.

RD-3.

  • Glushko Nitric acid/Kerosene rocket engine. 9 kN. experimental. Developed 1950's. The RD-3 was a cluster of three RD-1 engines with a new common turbopump. Ignition was by an ethane-air mixture. Isp=190s.

RD-301.

  • Glushko exotic LF2/Ammonia rocket engine. 96.670 kN. Proton K stage 4. Developed 1965-77. Developed by Glushko beginning in 1965. Planned for use in Proton K-4H high energy upper stage. Motor tested but never flown. Isp=400s. First flight 1977.

RD-302.

  • Glushko exotic LF2/Ammonia rocket engine. 98 kN. Developed 1960-69. Successor to RD-303 and predecessor to RD-301. Staged combustion cycle. Isp=405s.

RD-303.

  • Glushko exotic LF2/Ammonia rocket engine. Developed 1960-65. Predecessor to RD-302 and RD-301.

RD-350.

  • Glushko exotic LF2/LH2 rocket engine. 98 kN. Design concept 1963-. Studied by Glushko as engine concept with high-energy propellants. Isp=464s.

RD-36-41.

  • Lyulka turbojet engine. 158.4 kN. T-4. Out of Production. Used in Sukhoi March 3 aircraft. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=1980s.

RD-3A.

  • Alternate designation for RD-102 Lox-Alcohol rocket engine.

RD-3A.

  • Glushko Lox/Alcohol rocket engine. R-3A. Out of Production. Project for R-3A experimental missile. Stopped in favour of RD-103.

RD-410.

  • Glushko nuclear/lh2 rocket engine. 68 kN. UR-700M concept. Developed 1960s.

RD-448, RO-7.

  • Alternate designation for RD-0109 Lox-Kerosene rocket engine.

RD-461.

  • Alternate designation for RD-0110 Lox-Kerosene rocket engine.

RD-461, 11D55, 8D715K, RO-8.

  • Alternate designation for RD-0108 Lox-Kerosene rocket engine.

RD-461, RO-9.

  • Alternate designation for RD-0107 Lox-Kerosene rocket engine.

RD-465, 8D49.

  • Alternate designation for RD-0210 N2O4-UDMH rocket engine.

RD-468.

  • Alternate designation for RD-0211 N2O4-UDMH rocket engine.

RD-473.

  • Alternate designation for RD-0212 and RD-0213 N2O4-UDMH rocket engine.

RD-502.

  • Glushko H2O2/Pentaborane rocket engine. 98.1 kN. Experimental upper stage engine. Developed 1960-66. Isp=380s. Experimental upper stage engine. Program stopped due to toxicity of propellants. Intended for Proton upper stage. First flight 1966.

RD-510.

  • Glushko H2O2/CxHy rocket engine. Developed 1965-75. First flight 1975.

RD-510T.

  • Glushko H2O2/CxHy rocket engine. Developed 1965-75. First flight 1975.

RD-511.

  • Glushko H2O2/CxHy rocket engine. Developed 1965-75. First flight 1975.

RD-54.

  • Lyulka lox/lh2 rocket engine. 392 kN. N1 concept stage III. Developed 1960-75. Isp=440s.

RD-550.

  • Glushko exotic rocket engine. 98.060 kN. Experimental upper stage engine. Developed 1963-70. Isp=400s. Propellants Lox/30% Beryllium+Pentaborane in 70% Hydrazine.

RD-56.

  • Isayev lox/lh2 rocket engine. 69.6 kN. N1 block R. Development ended 1971. Oxygen-hydrogen engine for cryogenic upper stage. Developed but never flown. Design sold to India in 1990's for GSLV. Isp=462s.

RD-56M.

  • Isayev lox/lh2 rocket engine. 73.580 kN. Proton and Angara upper stage KVRB, 12KRB upper stage for GSLV (India). In development. Isp=461s. First flight 2001.

RD-56M LNG.

  • Isayev Lox/LNG rocket engine. 73.5 kN. Vozdushnyy Start stage 2. Developed 1996-. Variant of RD-56M using liquid natural gas in place of hydrogen. First engine tests performed in 1998.

RD-57.

  • Lyulka lox/lh2 rocket engine. 392 kN. N1 Block S (N-1M). Study 1965. One to have been used in N1 Block S. In fixed chamber version, 3 to 6 to have been used in N1 Block V-III. Engine system includes roll control thruster with 1.29 kN thrust. Isp=456s.

RD-57A-1.

  • Lyulka lox/lh2 rocket engine. 395 kN. Developed 1995-98. Isp=460s. New version of RD-57M for SSTO-demonstrator proposed by Aerojet. Optimized nozzle contour for performance increase, new chamber material for weight reduction.

RD-57M.

  • Lyulka lox/lh2 rocket engine. 397 kN. Vulkan Blok V. Development ended 1976. Isp=461s. Version with extendible nozzle. Length 4.06 / 2.61 m. Specific impulse 461 / 448 sec. Area ratio 170 / 87.6.

RD-58.

  • Korolev Lox/Kerosene rocket engine. 83.4 kN. Isp=349s. High-performance upper-stage engine developed for N1 lunar crasher stage, but saw general use as restartable Block D upper stage of Proton launch vehicle. First flight 1967.

RD-58M.

  • Korolev Lox/Kerosene rocket engine. 83.4 kN. Proton 8K824K / 11S824M; 11S824F; 11S86; 11S861; 17S40 stage 4 (block DM). In production. Isp=353s. First flight 1974.

RD-58MF.

  • Korolev Lox/Kerosene rocket engine. 83.4 kN. In Production. Isp=353s. Multi-function variant of RD-58 for uprated upper stages applications (Zenit stage 3, Angara). Block-DM-SL for Sea-Launch may have used RD-58M.

RD-58S.

  • Korolev Lox/Kerosene rocket engine. 86.3 kN. Proton 8K82K / 11S861-01 stage 4 (block DM). Version 17D12 for Buran OMS. Version uses synthetic kerosene ('Sintin') for higher specific impulse. Isp=361s. First flight 1994.

RD-58Z.

  • Korolev Lox/Kerosene rocket engine. 71 kN. Zenit stage 3. Developed 1981-1990. Isp=361s.

RD-600.

  • Glushko nuclear/lh2 rocket engine. 1960 kN. Isp=2000s. Gas core nuclear engine worked developed 1962-1970 for use in second stage of two-stage interplanetary rockets.

RD-68.

  • Yuzhnoye Nitric acid/UDMH rocket engine. 380 kN. R-16 stage 1 attitude control engine. Out of Production.

RD-68M.

  • Yuzhnoye N2O4/UDMH rocket engine. 285 kN. R-36 stage 1 attitude control engine. Out of Production. 4 nozzles, maximum 42 degree gimbal angle.

RD-69.

  • Yuzhnoye Nitric acid/UDMH rocket engine. 49.2 kN. R-16 stage 2 attitude control engine. Out of Production.

RD-69M.

  • Yuzhnoye N2O4/UDMH rocket engine. 54.3 kN. R-36 stage 2 attitude control engine. Out of Production. 4 nozzles, maximum 50 degree gimbal angle.

RD-701.

  • Glushko lox/lh2/kerosene tripropellant rocket engine for air-launched MAKS spaceplane. 4003 kN. Development ended 1988. Isp=415 / 460s. First flight 2001.

RD-704.

  • Glushko Lox/Kerosene/LH2 tripropellant engine. 1966 kN. Developed 1990's. Isp=407 / 452 s. Tripropellant engine, single chamber, derived from RD-701 project. Chamber pressure 294 / 124 bar. First flight 1999.

RD-8.

  • Yuzhnoye Lox/Kerosene rocket engine. 78.4 kN. Zenit stage 2 attitude control engine. In Production. Isp=342s. Four-chamber pump-fed single-run engine operated in a staged combustion scheme with afterburning of the generator gas. Development began in 1976.

RD-802.

  • Yuzhnoye Lox/Kerosene rocket engine. 19.6 kN. Upper stages. Design concept 2007. Isp=344s. Derivative of the RD-8 Zenit-2 second stage vernier thrust engine combustion chamber for use in launch vehicle upper stages.

RD-809.

  • Yuzhnoye Lox/Kerosene rocket engine. 88 kN. Upper stages. Isp=345s. 2007 design concept for a four-chamber restartable main engine for launch vehicle upper stages.

RD-851.

  • Yuzhnoye Nitric acid/UDMH rocket engine. 32.480 kN. R-16 (SS-7) stage 1 attitude control engine . Out of Production. Four thrusters are each gimbaled in one single axis. Isp=279s.

RD-852.

  • Yuzhnoye Nitric acid/UDMH rocket engine. 48.250 kN. R-16 (SS-7) stage 2 attitude control engine. Out of Production. Four thrusters are each gimbaled in one single axis. Isp=255s.

RD-853.

  • Yuzhnoye Nitric acid/UDMH rocket engine. 467.6 kN. Stage 2, no application. Developed 1960-63. Designed for second stage, no application. Two thrust levels. Thrust 467.6 kN + 11.8 kN / 7.65 kN. Isp=300s.

RD-854.

  • Yuzhnoye N2O4/UDMH rocket engine. 75.5 kN. R-36orb (SS-X-10) orbital stage. Out of Production. Thrust vector control by 4 nozzles fed from gas generator. Isp=312s.

RD-855.

  • Yuzhnoye N2O4/UDMH rocket engine. 328 kN. Tsyklon stage 1 attitude control engine. Out of Production. Isp=292s. Four-chamber pump-fed single-run engine burned hypergolic propellants in a gas generator scheme.

RD-856.

  • Yuzhnoye N2O4/UDMH rocket engine. 54.230 kN. Tsyklon stage 2 attitude control engine. Out of Production. Isp=280s. Autonomous four-chamber pump-fed single-run engine burned hypergolic propellants in a gas generator scheme.

RD-857.

  • Yuzhnoye N2O4/UDMH rocket engine. 137.3 kN. RT-20P missile stage 2. Out of production. Isp=329s. Designed for second stage of mixed propulsion missile, only flight tests. Thrust vector control by secondary gas injection into nozzle. First flight 1967.

RD-858.

  • Yuzhnoye N2O4/UDMH rocket engine. 20.1 kN. Isp=315s. Primary engine for LK manned lunar lander. Propulsion cluster provided the variable thrust needed for a soft landing onto the lunar surface, then restarted for injection into lunar orbit. Flown 1970.

RD-859.

  • Yuzhnoye N2O4/UDMH rocket engine. 20.050 kN. LK lunar lander reserve engine. Hardware. Isp=312s. Backup engine for the LK manned lunar lander in the event the primary RD-858 engine failed. Restart within three seconds after shut down. Flight tests 1970.

RD-860.

  • Yuzhnoye N2O4/UDMH rocket engine. 5.9 kN. Upper stages. Developed 1972. Isp=320s. Engine used a novel scheme combining an existing proven combustion chamber but using a pneumatic pump for propellant supply.

RD-861.

  • Yuzhnoye N2O4/UDMH rocket engine. 78.710 kN. Tsyklon 2 and 3 stage 3; Ikar. In production. Isp=317s. Based on RD-854. Thrust vector control by 4 nozzles (thrust 98 N each) fed from a gas generator. First flight 1965.

RD-861G.

  • Yuzhnoye, Fiat Avio N2O4/UDMH rocket engine. 76.453 kN. Vega upper stage. Developed 1996-. Isp=325s. Proposed uprate of RD-861 engine. Thrust vector control by gimbal, roll control by 4 nozzles (thrust 29 N each).

RD-861K.

  • Yuzhnoye N2O4/UDMH rocket engine. 77.630 kN. Tsyklon 2 and 3 stage 3; Ikar. Developed 2005. Isp=330s. High pressure fuel was used to gimbal the engine in two planes, replacing four thrust vector engines on the basic RD-861.

RD-862.

  • Yuzhnoye N2O4/UDMH rocket engine. 142.630 kN. MR-UR-100 / RS-16 (SS-17) stage 2. Out of Production. Based on RD-857. Thrust vector control by secondary gas injection into nozzle. Roll control via special small jet nozzles. Isp=331s.

RD-863.

  • Yuzhnoye N2O4/UDMH rocket engine. 276.840 kN. MR-UR-100 / RS-16 (SS-17) stage 1 attitude control engine. Out of Production. Isp=301s.

RD-864.

  • Yuzhnoye N2O4/UDMH rocket engine. 20.2 kN. R-36M vehicle bus. Out of Production. Isp=309s. Two thrust levels. The four thruster swing out of the stage housing before use. Chamber pressure 41 / 17 bar. Specific impulse 309 / 298 sec.

RD-866.

  • Yuzhnoye N2O4/UDMH rocket engine. 5.2 kN. RT-23 MIRV-bus. Out of Production. Isp=305s. Engine consisted of two turbopumps with gas generators and two feeders; a single chamber main engine; and 16 liquid thrusters for attitude control and translation.

RD-868.

  • Yuzhnoye N2O4/UDMH rocket engine. 23.250 kN. Apogee stage. Developed 1983-. Isp=325s. In development in 1996. One main and an unknown number of control thrusters. 23.25 + 0.03 kN. Chamber pressure 91.5 / 6.9 bar. Specific impulse 325 / 230 sec.

RD-869.

  • Yuzhnoye N2O4/UDMH rocket engine. 8.580 kN. R-36M2 vehicle bus. Based on RD-864. Two thrust levels. The four thrusters swing out of the stage housing before use. Chamber pressure 41 / 17 bar. Diameter 3,0 / 4,02 m. Isp=313s. First flight 1986.

RDKS-1.

  • Russian rocket engine. Developed End 40's. Single chamber with turbopump propellant feed.

RDKS-100.

  • Dushkin Lox/Kerosene rocket engine. 980 kN. Sanger. Developed 1946-51. Isp=285s.

RDMT-0.4 X.

  • NII Mash N2O4/UDMH rocket engine. 400 mN. In Production. Experimental low-thrust thruster. Chamber from niobium alloy. Chamber pressure 41 / 17 bar. Specific impulse 313 / 302,3 sec. Isp=290s.

RDMT-0.8.

  • NII Mash nitrogen+helium cold gas thruster. 800 mN. Kosmos satellites. In Production. Low-thrust cold-gas thruster. Specific impulse 70 / 160 sec. Isp=70s.

RDMT-100.

  • NII Mash N2O4/UDMH rocket engine. 0.100 kN. Salyut, Mir, Soyuz-T and -TM, Progress, Kosmos-satellites. In Production. Low-thrust attitude control thruster. Isp=260s.

RDMT-12.

  • NII Mash N2O4/UDMH rocket engine. 12 N. Almaz, Kvant, Kristall, Spektr, Priroda. In Production. Low-thrust attitude control thruster. Predecessor was RDMT-400. Used in Isayev 17D58E engine. Isp=279s.

RDMT-135.

  • NII Mash N2O4/UDMH rocket engine. 0.135 kN. Salyut, Mir, Soyuz-T and -TM, Progress, Kosmos-satellites. In Production. Low-thrust attitude control thruster. Isp=260s.

RDMT-200.

  • NII Mash N2O4/UDMH rocket engine. 0.200 kN. Almaz. In Production. Low-thrust attitude control thruster. Isp=255s.

RDMT-200K.

  • NII Mash GOX/Kerosene rocket engine. 0.200 kN. Buran. Out of Production. Low-thrust attitude control thruster. Mass in ref. NIIMash 95 given as only 2.5 kg. Isp=265s.

RDMT-2600.

  • NII Mash GOX/Alcohol rocket engine. 2.6 kN. Developed 1980's. Experimental low-thrust thruster. Isp=270s.

RDMT-400.

  • NII Mash N2O4/UDMH rocket engine. 0.400 kN. Almaz, Kvant, Kristall, Spektr, Priroda. In Production. Low-thrust attitude control thruster. Used in Isayev 11D458 engine. Isp=255s.

RDMT-400 X.

  • NII Mash N2O4/UDMH rocket engine. 0.400 kN. Developed 1980's. Experimental low-thrust thruster. Carbon combustion chamber. Mass may be chamber only. Isp=296s.

RDMT-400A.

  • NII Mash N2O4/UDMH rocket engine. 0.400 kN. Developed 1980's. Experimental low-thrust thruster. Niobium combustion chamber with coating. Isp=290s.

RDMT-5.

  • NII Mash air cold gas thruster. 5 N. MMK. In Production. Low-thrust cold-gas thruster. Isp=70s.

RDMT-50.

  • NII Mash N2O4/UDMH rocket engine. 0.050 kN. Kosmos satellites. In Production. Low-thrust attitude control thruster. Isp=255s.

RDMT-8 X.

  • NII Mash N2O4/UDMH rocket engine. 8 N. Developed 1980's. Experimental low-thrust thruster. Isp=296s.

RDMT-XX.

  • Alternate designation for NII 612 kgf N2O4-UDMH rocket engine.

REA 10.

  • Marquardt hydrazine monopropellant rocket engine. 890 mN. In Production.

REA 16.

  • Marquardt hydrazine monopropellant rocket engine. 0.020 kN. In Production.

REA 17-12.

  • Marquardt hydrazine monopropellant rocket engine. 4.45 N. In Production.

REA 17-6.

  • Marquardt hydrazine monopropellant rocket engine. 2.22 N. In Production.

REA 20-4.

  • Marquardt hydrazine monopropellant rocket engine. 0.556 kN. In Production.

REA 22-16.

  • Marquardt hydrazine monopropellant rocket engine. 0.130 kN. In Production.

REA 22-17.

  • Marquardt hydrazine monopropellant rocket engine. 0.178 kN. In Production.

REA 22-2.

  • Marquardt hydrazine monopropellant rocket engine. 0.090 kN. In Production.

REA 22-5.

  • Marquardt hydrazine monopropellant rocket engine. 0.050 kN. In Production.

REA 39-2.

  • Marquardt hydrazine monopropellant rocket engine. 2.22 N. In Production.

Redesigned SRM.

  • Thiokol solid rocket engine. 11,520 kN. In Production. Isp=268s. Replacement shuttle solid rocket booster with redesigned field joints to prevent failure that caused the Challenger disaster.

RESA-2.

  • Rocketdyne N2O4/MMH rocket engine. 0.215 kN. Pitch Control Propulsion Module. Pressure-fed.

RESA-5.

  • Rocketdyne N2O4/MMH rocket engine. 7.109 kN. Spacecraft. Pressure-fed. Isp=280s.

RH-125.

  • ISRO VSSC solid rocket engine. 8.4 kN.

RH-125S.

  • ISRO VSSC solid rocket engine. 1.3 kN.

RH-200.

  • ISRO solid rocket engine. 16.9 kN.

RH-300.

  • ISRO solid rocket engine. 33.3 kN.

RH-300-II.

  • ISRO solid rocket engine. 39.1 kN.

RH-560.

  • ISRO/Antrix solid rocket engine. 76 kN.

RH-75.

  • ISRO solid rocket engine.

Rita II.

  • Sud/SEP solid rocket engine. 320 kN.

RJ47.

  • Wright ramjet engine. 44.6 kN. Development ended 1958. Thrust is maximum thrust at cruise altitude. Specific impulse is that at cruise design point. Isp=1200s. Used on Navaho G-38 launch vehicle.

RKDS-100.

  • Glushko Lox/Kerosene rocket engine. 980 kN. Keldysh Bomber. Design 1946. Nominal design engine for 1946 Keldysh bomber design. The Soviet Union would not produce an engine with these propellants and thrust levels until nearly 20 years later. Isp=285s.

RL-10.

  • Pratt and Whitney lox/lh2 rocket engine. 66.7 kN. Isp=410s. Early version as proposed for Nova A, Nova B, Saturn B-1, Saturn C-2, Saturn C-3, Saturn I. First flight 1961.

RL-10A-1.

  • Pratt and Whitney lox/lh2 rocket engine. 66.7 kN. Isp=425s. Version used on Atlas Centaur LV-3C, and proposed for various early Saturn launch vehicle designs. First flight 1961.

RL-10A-3.

  • Pratt and Whitney lox/lh2 rocket engine. 65.6 kN. Study 1968. Isp=444s. First flight 1967.

RL-10A-3A.

  • Pratt and Whitney lox/lh2 rocket engine. 73.4 kN. Isp=444s. Used on Centaur stage atop Atlas G, Atlas I, Atlas II, Titan 4. First flight 1984.

RL-10A-4.

  • Pratt and Whitney lox/lh2 rocket engine. 92.5 kN. Out of production. Isp=449s. Centaur stage for Atlas IIA, Atlas IIAS. First flight 1992.

RL-10A-4-1.

  • Pratt and Whitney lox/lh2 rocket engine. 99.1 kN. Out of production. Isp=451s. Used on Atlas IIIA launch vehicle. First flight 2000. Version with one of engines removed; remaining engine re-positioned to center-mount; new electro-mechanical gimbals.

RL-10A-4-2.

  • Pratt and Whitney lox/lh2 rocket engine. 99.1 kN. In production. Isp=451s. Used on Atlas IIIB launch vehicle. First flight 2002. Two engines; electro-mechanical thrust vector control actuators replaced earlier hydraulically actuated system.

RL-10A-5.

  • Pratt and Whitney lox/lh2 rocket engine. 64.7 kN. Isp=373s. Throttleable to 30% of thrust, sea level version of RL10. Four engines were built and were used on the DC-X and the upgraded DC-XA VTOVL SSTO launch vehicle demonstrators. First flight 1993.

RL-10A-5KA.

  • Pratt and Whitney lox/lh2 rocket engine. 100.488 kN. Kistler proposal. Design 1992. Isp=398s. Throttleable to 30% of thrust, sea level version of RL10 with extendable nozzle for high altitude operation.

RL-10B-2.

  • Pratt and Whitney lox/lh2 rocket engine. 110 kN. In production. Isp=462s. Used on Delta 3 , Delta IV launch vehicles. First flight 1998. Extendable exit cone for increased specific impulse; electromechanical actuators replace hydraulic systems.

RL-10B-X.

  • Pratt and Whitney lox/lh2 rocket engine. 93.4 kN. Design concept 1994. Isp=470s.

RL-10C.

  • Pratt and Whitney lox/lh2 rocket engine. 155.7 kN. In Production. Used in Delta 3 - 2. Isp=450s. First flight 1998.

RL-10C-X.

  • Pratt and Whitney lox/lh2 rocket engine. 110.8 kN. Design concept 1994. Isp=450s.

RL-50.

  • Pratt and Whitney lox/lh2 rocket engine. 290 kN. Development. Isp=472s. Advanced, high-performance upper-stage rocket engine proposed by Pratt & Whitney for both domestic and international launch vehicles.

RL-60.

  • Pratt and Whitney lox/lh2 rocket engine. 289.1 kN. Design. Isp=470s. Upper stage engine to have been developed by Pratt and Whitney with several international partners. Same dimensions as the RL-10, but over twice the thrust.

RLA-1200.

  • Glushko Lox/Kerosene rocket engine. 12,700 kN. Design 1974. Proposed engines for the RLA series launch vehicles. This version would use four chambers. 'Down-sized' to 200 tonnes thrust for Energia.

RLA-300.

  • Glushko Lox/Kerosene rocket engine. 3187 kN. Design 1974. Proposed for the RLA series launch vehicles and the UR-700M Mars booster. Following rejection of RLA, design 'down-sized' to 200 tonnes thrust for Energia and Zenit.

RLA-600.

  • Glushko Lox/Kerosene rocket engine. 6370 kN. Design 1972. Two-chamber version of RLA-300. Proposed for the RLA series launch vehicles and the UR-700M Mars booster.

RM-01.

  • Rocketdyne hydrazine monopropellant rocket engine. 44 mN. Spacecraft. Pressure-fed. Isp=91s.

RM-05.

  • Rocketdyne N2O4/MMH rocket engine. 0.020 kN. Satellite Reaction Control System. Pressure-fed. Isp=238s.

RM-100A.

  • Rocketdyne N2O4/MMH rocket engine. 0.441 kN. Spacecraft. Pressure-fed. Isp=301s.

RM-100B.

  • Rocketdyne Nitric acid/UDMH rocket engine. 0.441 kN. Satellite Reaction Control. Pressure-fed. Isp=283s.

RM-100T.

  • Rocketdyne N2O4/Aerozine-50 rocket engine. 0.441 kN. Lunar Flyer. Pressure-fed. Isp=296s.

RM-1-1.

  • Rocketdyne N2O4/MMH rocket engine. 4.4 N. Satellite Reaction Control System. Pressure-fed. Isp=245s.

RM-1100.

  • Cooper solid rocket engine. 26 kN.

RM-1-2.

  • Rocketdyne N2O4/MMH rocket engine. 4.4 N. Satellite Reaction Control. Pressure-fed. Isp=238s.

RM-1400.

  • Cooper solid rocket engine. 12.7 kN.

RM-1500H.

  • Rocketdyne lox/lh2 rocket engine. 6.660 kN. Space Shuttle Orbiter Auxiliary Propulsion. Pressure-fed. Isp=400s.

RM-1600.

  • Manufacturer's designation of RESA-5 N2O4-MMH rocket engine.

RM-25.

  • Rocketdyne N2O4/MMH rocket engine. 0.107 kN. Spacecraft. Pressure-fed. Isp=286s.

RM-25-1.

  • Rocketdyne N2O4/MMH rocket engine. 0.107 kN. Spacecraft. Pressure-fed. Isp=300s.

RM-3141.

  • GCR solid rocket engine. 8.6 kN.

RM-50.

  • Manufacturer's designation of RESA-2 N2O4-MMH rocket engine.

RM-900.

  • Rocketdyne N2O4/MMH rocket engine. 4.001 kN. Shuttle Orbiter Reaction Control. Pressure-fed. Isp=309s.

RN-6.

  • Rocketdyne nuclear/lh2 rocket engine. Nuclear Deep Space. Nuclear.

RO-1.

  • Manufacturer's designation of S2.1200 rocket engine.

RO1-154.

  • Alternate designation for RD-0200 Nitric acid-Amine rocket engine.

RO-200.

  • Alternate designation for RD-0120 Lox-LH2 rocket engine.

RO-31.

  • Kosberg nuclear/lh2 rocket engine. 392 kN. UR-700 Third Stage. Study 1967. Engine proposed for UR-700 third stage to achieve 250 tonne payload to low earth orbit. Probably closely related to RD-0411.

RO-5, RD-428.

  • Alternate designation for RD-0105 Lox-Kerosene rocket engine.

RO-97.

  • Alternate designation for RD-0126 Lox-LH2 rocket engine.

RO-97A.

  • Alternate designation for RD-0126A Lox-LH2 rocket engine.

RO-97E.

  • Alternate designation for RD-0126E Lox-LH2 rocket engine.

Rook.

  • Royal Ordnance solid rocket engine. 300 kN. Out of production. Fast-burning version of Raven. Rook was fired 70 times altogether, in 65 flights and 16 different vehicle designs.

Rotary Rocket.

  • XCOR Lox/Kerosene rocket engine. 22.250 kN. First stages. Developed in 1990's. Developed and tested by Rotary Rocket for their launcher before its cancellation.

RPD-04.

  • Dushkin Lox/Kerosene rocket engine. Out of Production.

RS-14.

  • Rocketdyne N2O4/MMH rocket engine. 1.392 kN. Minuteman Postboost Velocity Control. Pressure-fed. Isp=315s. First flight 1970.

RS-1402.

  • Rocketdyne N2O4/MMH rocket engine. 0.098 kN. Minuteman Pitch, Yaw & Roll Control. Pressure-fed. Technology engine, developed, but not produced. Led to RS-14 prodution engines. Isp=259s.

RS-1403.

  • Rocketdyne N2O4/MMH rocket engine. 0.078 kN. Minuteman Pitch, Yaw & Roll Control. Pressure-fed. Technology engine, developed, but not produced. Led to RS-14 prodution engines. Isp=230s.

RS-17.

  • Manufacturer's designation of AMPS-1 Lox-LH2 rocket engine.

RS-18.

  • Rocketdyne N2O4/Aerozine-50 rocket engine. 15.563 kN. Apollo Lunar Ascent Module Engine. Pressure-fed. Isp=310s.

RS-19.

  • Rocketdyne exotic ClF3/Hydrazine rocket engine. Launch thrust 3.108 kN. Condor Development Booster Air-to-Ground Missile. Pressure-fed. Thrust and specific impulse values are at sea level.

RS-21.

RS-2100.

  • Rocketdyne lox/lh2 rocket engine. Launch thrust 2047.6 kN. Next Generation Launch Vehicle Booster. Full flow staged combustion, pump-fed. Thrust and specific impulse values are at sea level.

RS-2101A.

  • Rocketdyne N2O4/MMH rocket engine. 1.333 kN. Mars Mariner. Pressure-fed. Derivtive of RS-14 Minuteman engine. Isp=287s. First flight 1971.

RS-2101C.

  • Rocketdyne N2O4/MMH rocket engine. 1.333 kN. Viking. Pressure-fed. Derivtive of RS-14 Minuteman engine. Isp=294s. First flight 1975.

RS-22.

  • Manufacturer's designation of FLEXEM ClF3-Hydrazine rocket engine.

RS-2200.

  • Rocketdyne lox/lh2 rocket engine. 2201 kN. Development cancelled 1999. Isp=455s. Linear Aerospike Engine developed for use on the Lockheed Reusable Launch Vehicle, the production follow-on to the X-33.

RS-23.

  • Rocketdyne N2O4/MMH rocket engine. 26.670 kN. Space Shuttle Orbiter Orbit Maneuvering System. Pressure-fed. Isp=313s. First flight 1981.

RS-24.

  • Alternate designation for SSME Lox-LH2 rocket engine.

RS-25.

  • Manufacturer's designation of SSME Lox-LH2 rocket engine.

RS-27.

  • Rocketdyne Lox/Kerosene rocket engine. 1023 kN. Out of production. Isp=295s. Consisted of RS2701A/B main engine, and twin LR101-NA-11 verniers. Introduced in 1974 on the McDonnell Douglas' Delta 2000 series launcher; replaced the MB-3. First flight 1972.

RS-27A.

  • Rocketdyne Lox/Kerosene rocket engine. 1054.2 kN. . Isp=302s. Replaced the RS-27 as the main system for the Delta and in the MA- 5A for the Atlas. RS2701B main engine, and twin LR101-NA-11 verniers. First flight 1989.

RS-27C.

  • Rocketdyne Lox/Kerosene rocket engine for Delta 7000. 1054.2 kN. Isp=302s. First flight 1990.

RS-28.

  • Rocketdyne N2O4/MMH rocket engine. 2.667 kN. Space Shuttle Orbiter Reaction Control. Pressure-fed. Isp=220s.

RS-30.

  • Manufacturer's designation of ASE Lox-LH2 rocket engine.

RS-32.

  • Manufacturer's designation of LR101-NA-7 N2O4-MMH rocket engine and LR101-11 Lox-Kerosene rocket engine.

RS-32.

  • Rocketdyne N2O4/MMH rocket engine. 1.392 kN. Upper Stage Target Engine Systems. Pressure-fed. Derived from Minuteman RS-14. Isp=288s.

RS-34.

RS-34.

  • Rocketdyne N2O4/MMH rocket engine. 11.7 kN. Peacekeeper Postboost Axial Thrust. Pressure-fed. 1 main axial thruster per postboost propulsion system. Isp=308s. First flight 1983.

RS-34 Attitude Control.

  • Rocketdyne Lox/Kerosene rocket engine. 0.304 kN. Peacekeeper Postboost Attitude Control. Pressure-fed. 8 attitude thrusters in each postboost propulsion system. Isp=255s. First flight 1983.

RS-36.

  • Manufacturer's designation of RS-36 Sustainer Lox-Kerosene rocket engine.

RS-36.

  • Rocketdyne N2O4/MMH rocket engine. 55.6 kN. HOE Homing Overlay Experiment Upper Stage Axial Propulsion System. Pressure-fed. Derivative of Lance propulsioon system. Isp=281s. First flight 1983.

RS-36 Sustainer.

  • Rocketdyne Lox/Kerosene rocket engine. 9.210 kN. HOE Homing Overlay Experiment Upper Stage Axial Propulsion System. Pressure-fed. Derivative of Lance propulsioon system. Isp=262s. First flight 1983.

RS-41.

  • Rocketdyne N2O4/MMH rocket engine. 11.960 kN. Axial Spacecraft. Pressure-fed. Isp=320s.

RS-42.

  • Rocketdyne N2O4/MMH rocket engine. 0.441 kN. Axial Spacecraft. Pressure-fed. Isp=305s.

RS-43.

  • Rocketdyne N2O4/MMH rocket engine. 0.020 kN. Attitude Control. Pressure-fed. Isp=284s.

RS-44.

  • Manufacturer's designation of AEC Lox-LH2 rocket engine.

RS-45.

  • Rocketdyne N2O4/MMH rocket engine. 4.4 N. Satellite Attitude Control and Stationkeeping. Pressure-fed. Isp=300s.

RS-47.

  • Manufacturer's designation of XLR132 N2O4-MMH rocket engine.

RS-51.

  • Rocketdyne N2O4/MMH rocket engine. 11.552 kN. Axial Spacecraft. Pressure-fed. Isp=315s.

RS-52.

  • Rocketdyne lox/lh2 rocket engine. 0.107 kN. Oxygen/Hydrogen Space Station Thruster. Pressure-fed. Technology was developed with 0.1 lb thrust resistojet by using electrically heated waste for space station propulsion. Isp=405s.

RS-56-OBA.

  • Rocketdyne Lox/Kerosene rocket engine. 1046.8 kN. Out of production. Designed for booster applications. Gas generator, pump-fed. Isp=299s. Booster engine for Atlas II, IIA, IIAS. First flight 1991.

RS-56-OSA.

  • Rocketdyne Lox/Kerosene rocket engine. 386.4 kN. Out of production. Designed for booster applications. Gas generator, pump-fed. Isp=316s. Sustainer engine for Atlas II, IIA, IIAS. First flight 1991.

RS-68.

  • Rocketdyne lox/lh2 rocket engine. 3312 kN. In production. Isp=420s. First new large liquid-fueled rocket engine developed in America in more than 25 years. Powered the Delta IV booster. First flight 2002.

RS-68 Regen.

  • Rocketdyne lox/lh2 rocket engine. Design concept -2004. Upgrade to basic RS-68 for Delta IV Heavy growth versions. Would use a regeneratively-cooled expansion nozzle, allowing it to run hotter, with higher thrust and specific impulse.

RS-68B.

  • Rocketdyne lox/lh2 rocket engine. Design concept -2004. Upgrade (details not specificed) to basic RS-68 for Delta IV Heavy growth versions.

RS-69.

  • Manufacturer's designation of XRS-2200 Lox-LH2 rocket engine.

RS-71.

  • Rocketdyne lox/lh2 rocket engine. 31.126 kN. Development ended 1999. Linear Aerospike SR-71 Experiment. Pressure-fed. Isp=430s.

RS-72.

  • Rocketdyne, Ottobrunn N2O4/MMH rocket engine. 55.4 kN. Isp=340s. Aestus engine enhanced with the addition of a Boeing-Rocketdyne XLR 32 turbo-pump.

RS-73.

  • Manufacturer's designation of MB-35, MB-45 and MB-60 Lox-LH2 rocket engine.

RS-74.

  • Rocketdyne lox/lh2 rocket engine. Launch thrust 1112 kN. Next Generation Launch Vehicle Booster. Full flow staged combustion, pump-fed. Thrust and specific impulse values are at sea level.

RS-76.

  • Rocketdyne Lox/Kerosene rocket engine. Launch thrust 4002 kN. Space Shuttle Reusable First Stage. Ox-Rich staged combustion, pump-fed. Thrust and specific impulse values are at sea level.

RS-77.

  • Rocketdyne solar/lh2 rocket engine. 0.176 kN. Solar Thermal Engine. Pressure-fed. SOTV Solar Orbit Transver Vehicle. Isp=870s.

RS-800.

  • Rocketdyne lox/lh2 rocket engine. 4110 kN. Design concept -2004. New high-thrust cryogenic engine for Delta IV Heavy growth versions.

RS-82.

  • Rocketdyne H2O2/kerosene rocket engine. 44.463 kN. Next Generation Non-Toxic Upper Stage. Gas generator, pump-fed. Isp=320s.

RS-84.

  • Rocketdyne lox/kerosene rocket engine. 5159 kN. Booster stages. Development ended 2005. Isp=335s. Design for NASA's Space Launch Initiative; borrowed extensively from Russian technology developed in the forty years since the USA abandoned the F-1.

RS-88.

  • Rocketdyne rocket engine designed and built by Rocketdyne for use on Lockheed's Pad Abort Demonstration vehicle. In 2003, NASA tested the RS-88 in a series of 14 hot-fire tests, resulting in 55 seconds of successful engine operation.

RSA-3-1.

  • South Africansolid rocket engine. 500 kN. Out of production. Built in both Israel and South Africa for RSA-3 and Shavit. Source: Missile exhibit and placards, AF Museum, South Africa. Isp=273s. First flight 1988.

RSA-3-2.

  • South African solid rocket engine. 519 kN. In production. Built in both Israel and South Africa for RSA-3 and Shavit. Source: Missile exhibit and placards, AF Museum, South Africa. Isp=284s. First flight 1988.

RSA-3-3.

  • South Africansolid rocket engine. 51 kN. In production. Israeli AUS-51 rocket motor, built in both Israel and South Africa. Isp=292s. Upper stage engine for RSA-3, RSA-4, Shavit, Shavit 1. First flight 1988.

RSA-4-1.

  • South Africansolid rocket engine. 1520 kN. Development ended 1994. Isp=263s. Used on RSA-4 launch vehicle.

RSA-4-2.

  • South African solid rocket engine. 676 kN. Development ended 1994. Isp=275s. Used on RSA-4 launch vehicle.

RSRM.

  • Thiokol solid rocket engine. 11,520 kN. Study 1996. After the Challenger disaster the redesigned solid rocket motors had a slight reduction in performance due to reliability improvements. Isp=267s.

RS-X.

  • Rocketdyne Lox/Kerosene rocket engine. 1890 kN. Design concept -1997. Employed existing Delta and Atlas MA and RS engine hardware with a new thrust chamber assembly to generate a thrust of 1890 kN for ELV applications.

RS-XXX.

  • Rocketdyne lox/lh2 rocket engine. 8230 kN. Design concept -2004. New high-thrust cryogenic engine concept for Next Generation Delta with 7 m diameter modules.

RT-2-1.

  • OKB-1 solid rocket engine. 900 kN.

RTV-100.

  • JPL solid rocket engine. 22 kN.

RTV-500.

  • JPL solid rocket engine. 80 kN.

RU-013.

  • Dushkin rocket engine. 31 kN. Developed 1955-57.

RX-250-LPN.

  • LAPAN solid rocket engine. 52 kN.

RZ.2.

  • Rolls Royce Lox/Kerosene rocket engine. 836.3 kN. Isp=282s. Used on Europa launch vehicle. First flight 1964.

S09.29.

  • Isayev Nitric acid/Amine rocket engine. 88 kN. V-300/V-303 (S-25 system). Out of Production.

S09.29.0B.

  • Manufacturer's designation of S09.29 Nitric acid-Amine rocket engine.

S09.502.

  • Isayev Nitric acid/Amine rocket engine. R-101 SAM. Developed 1949-50. Launch thrust 78.4 kN. Four chamber engine designed for use in the R-101 (derivative of German Wasserfall). Abandoned by 1950 in favour of single-chamber engine.

S1.35800.

  • Korolev Lox/Kerosene rocket engine. 30 kN. R-7 verniers. Out of Production. Thrust variable 2.5-3.1 tf

S1.5400.

  • Korolev Lox/Kerosene rocket engine. 66.7 kN for Molniya 8K78 Stage 3. Flew 1960-1965. Isp=340s. Designed by Korolev; passed to Isayev for production. Began a series of engines leading through the 8D726 for GR-1 to the Block D for the N1 and Proton.

S1.5400A.

  • Korolev Lox/Kerosene rocket engine. 67.3 kN. Molniya 8K78M-3. Isp=342s. First flight 1964.

S-155.

  • Dushkin rocket engine. 39 kN. E-50. Developed 1955-56. Thrust variable 2000 - 4000 kgf.

S-160.

  • ISAS solid rocket engine.

S2.1100.

  • Isayev rocket engine. V-1000. Out of Production. OKB-2 transferred work on the S2.1100 to OKB-117 in 1958-59. OKB-117 completed development.

S2.1150.

  • Isayev Nitric acid/Amine rocket engine. 671.2 kN. Burya booster. Out of production. Isp=250s. First flight 1957. Engines developed from R-11 S2.253 engine.

S2.1200.

  • Isayev rocket engine. Developed 1950s middle. OKB-2 transferred work on the S2.1200 to OKB-154 in 1957. The latter used the designation RO-1 for the engine.

S2.145.

  • Isayev rocket engine. 88 kN. Developed 1950s early.

S2.253.

  • Isayev Nitric acid/Kerosene rocket engine. 93.3 kN. R-11 (Scud B) 8A61. Thrust 8300 kgf at sea level. Fuel Kerosene T-1, chemical ignition by TG-02. Isp=251s. First flight 1953.

S2.253 derivative.

  • Isayev Lox/Kerosene rocket engine. 93.2 kN. EKR (experimental winged missile). Study 1953. Derivative of S2.253 was proposed for use in EKR Stage 1 (project for an experimental winged missile). Isp=250s.

S2.253A.

  • Isayev Nitric acid/Kerosene rocket engine. 93 kN. R-11FM. Out of Production. Used in R-11FM submarine version of Scud B. Fuel Kerosene T-1, chemical ignition by TG-02. Mixture ratio derived from tank content. 81 kN sea-level.

S2.713.

  • Isayev Nitric acid/Amine rocket engine. 252.2 kN. R-13 (SS-N-4). Out of Production. First engine to employ gas generator on main propellants. One main and four vernier thrusters. (Mixture derived ratio from tank content.)

S2.720.

  • Isayev Nitric acid/Amine rocket engine. 34.3 kN. Engine for SAM-missile V-755. Out of Production. Pump-fed engine. Used in engine unit of a special apparatus. Pump-fed engine. 20,4 kN sea level.

S2.721V.

  • Isayev Nitric acid/Amine rocket engine. 11.8 kN. KSR. Developed 1956-.

S2.726.

  • SKB-30 Nitric acid/Amine rocket engine. 103 kN.

S-20.

  • Avibras solid rocket engine. 36 kN.

S-210.

  • ISAS solid rocket engine.

S-23.

  • Avibrassolid rocket engine. 18 kN.

S-3.

  • Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Juno II, Saturn A-2 studies of 1959. Isp=282s. First flight 1958.

S3.42A.

  • Sevruk rocket engine. 166 kN. 217. Out of Production.

S-30.

  • IAE solid rocket engine. 20.490 kN. Development ended 1997. Isp=275s.

S-300.

  • ISAS solid rocket engine.

S-31.

  • IAE solid rocket engine. 240 kN.

S-310.

  • ISAS solid rocket engine.

S-3-20M5A.

  • Dushkin Nitric acid/Kerosene rocket engine. U-21. Developed -1959. Launch thrust 29.4 kN.

S-3D.

  • Rocketdyne Lox/Kerosene rocket engine. Launch thrust 600.1 kN. Jupiter Booster. Gas generator, pump-fed. Thrust later 150,000 lbs. Thrust and specific impulse values are at sea level. First flight 1957.

S-4.

  • Rocketdyne Lox/Kerosene rocket engine. 412.8 kN. Design ca. 1957. Version of Atlas sustainer tailored to Redstone Arsenal upper-stage requirements. Paper study only. Used on Super Jupiter launch vehicle.

S-40TM.

  • IAE solid rocket engine. 208.4 kN. Isp=272s. Used on VLS launch vehicle. First flight 1985.

S-43.

  • IAE solid rocket engine. 303 kN. Isp=265s. Used on VLS launch vehicle. First flight 1985.

S-43TM.

  • IAE solid rocket engine. 321.7 kN. Isp=276s. Used on VLS launch vehicle. First flight 1985.

S-44.

  • IAE solid rocket engine. 33.2 kN. Isp=282s. Used on VLS launch vehicle. First flight 1985.

S5.1.

  • Isayev Nitric acid/Amine rocket engine. 167 kN. SAM-missiles 217M and 218. Out of Production. Designation unknown.

S5.19.

  • Alternate designation for KDU-414 Nitric acid-UDMH rocket engine.

S5.23.

  • Alternate designation for 11D49 Nitric acid-UDMH rocket engine.

S5.23, D-25.

  • Alternate designation for RD-861 N2O4-UDMH rocket engine.

S5.3.

  • Isayev Nitric acid/Amine rocket engine. 392 kN. R-21 (SS-N-5). Out of Production. First engine to start underwater. 392 kN sea-level.

S5.35 + S5.60.

  • Alternate designation for KTDU-35 Nitric acid-UDMH rocket engine.

S5.3M.

  • Isayev Nitric acid/Amine rocket engine. 396.7 kN. R-9 (SS-8) missile stage 1. Out of Production. Proposed for R-9 missile stage 1. Four engines per stage. 396,7 kN sea-level.

S5.4.

  • Isayev Nitric acid/Amine rocket engine. 15.830 kN. Vostok/Voskhod retorfire engine; spacecraft maneuvering engine. . Out of Production. Includes 4 small lateral steering nozzles. Isp=266s.

S5.44.

  • Isayev Nitric acid/Amine rocket engine. 177 kN. SAM-missile 5Ya24. Out of Production. Could be throttled. 177-49 kN sea-level. Area ratio 118 - 44.

S5.45.

  • Isayev Nitric acid/UDMH rocket engine. 1961 kN. correction engine for Zond-1, Venera-2-8, and others. Out of Production. Pressure-fed engine. Used as correction engine for spacecraft Zond-1, Vernera-8, and others. Isp=267s.

S5.5, S5.5A.

  • Alternate designation for KTDU-5A Nitric acid-Amine rocket engine.

S5.51.

  • Isayev N2O4/UDMH rocket engine. 33.196 kN. Hardware 1969. Isp=314s. Complex engine used to maneuver the LOK to a rendezvous with the LK lander in lunar orbit, then propel the LOK out of lunar orbit. Verniers included for midcourse corrections.

S5.53.

  • Alternate designation for KTDU-53 Nitric acid-UDMH rocket engine.

S5.61.

  • Alternate designation for KRD-61 N2O4-UDMH rocket engine.

S5.66.

  • Alternate designation for KTDU-66 Nitric acid-UDMH rocket engine.

S5.79.

  • Alternate designation for KRD-79 N2O4-UDMH rocket engine.

S5.80.

  • Alternate designation for KTDU-80 N2O4-UDMH rocket engine.

S5.80.1100-0.

  • Isayev Lox/Kerosene rocket engine. 2.940 kN. Soyuz-2 Blok LM. Developed 1990s. Thrust chamber from KTDU-80 / S5.80 converted to burn Lox/Kerosene.

S5.92.

  • Isayev N2O4/UDMH rocket engine. 19.6 kN. Phobos propulsion module, later adapted as Fregat upper stage. In production. Isp=327s. Gas generator cycle. Nominal and low-thrust thrust levels.

S5.98M.

  • Isayev N2O4/UDMH rocket engine. 19.62 kN. Used on Briz and Briz-M upper stages. Isp=325s. Engine system consists of: main engine (2000 kgf, Isp=325.5s) + 4x11D458 (40 kgf, Isp=252s) + 12x17D58E (1.36 kgf, Isp=247s). 8 restarts. First flight 1990.

S-520.

  • ISAS solid rocket engine. 143.1 kN.

S-A.

  • Mitsubishi solid rocket engine.

Sabre.

  • Rolls Royce air augmented rocket engine. Used Air/Lox/LH2. Developed -1995. Isp=700s. In development for Skylon launch vehicl; descendent of RB545 developed for abandoned HOTOL space launcher.

SA-II.

  • Mitsubishi solid rocket engine.

Sanger-Bredt.

  • Notional Lox/Kerosene rocket engine. 1428.8 kN. Study 1943. Used in Sanger-Bredt. Isp=306s.

Sanger-Bredt Sled.

  • Saenger Lox/Alcohol rocket engine. 1144.1 kN. Study 1943. Isp=245s. Used on Sanger launch vehicle.

SARV Retro MK I.

  • Government designation of Star 10 Solid rocket engine.

SARV Retro, MK IV.

  • Government designation of Star 12 Solid rocket engine.

S-B.

  • Mitsubishi solid rocket engine.

SB-310.

  • ISAS solid rocket engine. 95 kN.

SB-735.

  • Nissan solid rocket engine. 327.8 kN. Isp=263s. Used on Mu-3S launch vehicle. First flight 1969.

SBIR Hybrid.

  • SpaceDev N2O/Solid hybrid rocket engine. 1100 kN. First stage. Upper-stage hybrid propulsion system, part of 2004 Phase 2 of SBIR contract from AFRL for a hybrid rocket motor-based small launch vehicle project.

S-C.

  • Mitsubishi solid rocket engine.

Scramjet.

  • Scramjet engine for X-30 SSTO. 1372.9 kN. Development ended 1992. Thrust is maximum sea level thrust; specific impulse is average during ascent. Isp=1550s. Propellant Slush LH2.

SE-1.

SE-1, 1-1, -2, and -4 Series.

  • Rocketdyne N2O4/UDMH rocket engine. SE-1, 1-1, -2, and -4 Series. Spacecraft Reaction Control. Pressure-fed. Multiple thrust levels. First flight 1959.

SE-10.

  • Rocketdyne N2O4/Aerozine-50 rocket engine. 46.670 kN. Lunar Module Descent. Pressure-fed. Thrust throttleable 1050-10,500 lbs vac. Isp=305s. First flight 1968.

SE-5-2.

  • Manufacturer's designation of SE-5-2--3 N2O4-UDMH rocket engine.

SE-5-2/-3.

  • Rocketdyne N2O4/UDMH rocket engine. 0.205 kN. SE-5-2/-3. Agena Auxiliary. Pressure-fed. SE-5-2 four engines in satellite system. SE-5-3 two engines for Agena auxiliary propuslion. Isp=272s. First flight 1963.

SE-6.

  • Rocketdyne N2O4/MMH rocket engine. 0.107 kN. Gemini Re-entry Control System. Pressure-fed. Isp=277s. First flight 1964.

SE-7-1.

  • Rocketdyne N2O4/MMH rocket engine. 0.313 kN. S-IVB Stage APS Ullage Control Engine (propellant settling). Pressure-fed. Isp=274s. First flight 1966.

SE-7-100.

  • Rocketdyne N2O4/MMH rocket engine. 0.441 kN. Gemini Orbit Attitude and Maneuvering System (100 Ib thrust). Pressure-fed. Isp=296s. First flight 1964.

SE-7-25.

  • Rocketdyne N2O4/MMH rocket engine. 0.107 kN. Gemini Orbit Attitude and Maneuvering System (25 Ib thrust). Pressure-fed. Isp=277s. First flight 1964.

SE-7-85.

  • Rocketdyne N2O4/MMH rocket engine. 0.372 kN. Gemini Orbit Attitude and Maneuvering System (85 Ib thrust). Pressure-fed. Isp=295s. First flight 1964.

SE-8.

  • Rocketdyne N2O4/MMH rocket engine. 0.411 kN. Apollo Command Module Reaction Control. Pressure-fed. Isp=274s. First flight 1966.

SE-9-3.

  • Rocketdyne N2O4/Aerozine-50 rocket engine. 0.107 kN. Titan III Transtage. Pressure-fed. System included two modules of three engines plus two additional SE-9-5 separate engines, tanks, and a pressuirzation system. Isp=295s. First flight 1964.

SE-9-5.

  • Rocketdyne N2O4/Aerozine-50 rocket engine. 0.196 kN. Titan III Transtage. Pressure-fed. System included two modules of three engines plus two additional SE-9-5 separate engines, tanks, and a pressuirzation system. Isp=300s. First flight 1964.

Sea Dragon-1.

  • Aerojet Lox/Kerosene rocket engine. 356,9 kN. Design, 1962. Isp=290s. Truax pressure fed design. Thrust, chamber pressure varied during ascent.

Sea Dragon-2.

  • Aerojet lox/lh2 rocket engine. 62,270 kN. Design, 1962. Truax pressure fed design. Diameter of extended nozzle 30 m. Specific impulse estimated from booster performance figures. Isp=320s.

Seliger 1.

  • Seliger solid rocket engine. 49 kN.

Seliger 3.

  • Seliger solid rocket engine.

Senior.

  • Manufacturer's designation of Algol 1 Solid rocket engine.

SEP 401.

  • Aerospatiale solid rocket engine. 900 kN.

SEP 402.

  • Aerospatiale solid rocket engine. 300 kN.

SEP 403.

  • Aerospatiale solid rocket engine. 100 kN.

SEP 901.

  • Sud/SEP solid rocket engine. 440 kN.

SEP 902.

  • Sud/SEP solid rocket engine. 540 kN.

SEP 903.

  • SEP solid rocket engine. 440 kN.

SEP 904.

  • Sud/SEP solid rocket engine. 450 kN.

SEPR 16.

  • SEPR rocket engine. 200 kN. AA.10 AAM. First flight 1950.

SEPR 2.

  • SEPR rocket engine. 1250 kN. SE 4100 SAM. Used turbopumps SEPR 3 and SEPR 4. First flight 1950.

SEPR 200.

  • Manufacturer's designation of Tramontane Solid rocket engine.

SEPR 25.

  • SEPR rocket engine. 4500 kN. Trident/Espadon fighter augmentation.

SEPR 43.

  • SEPR rocket engine. 1250 kN. R.04 SAM. First flight 1950.

SEPR 685-4.

  • ONERA solid rocket engine. 33 kN.

SEPR 734-1.

  • ONERA solid rocket engine. 200 kN.

SEPR 737.

  • ONERA solid rocket engine. 75 kN.

SEPR 739.

  • Manufacturer's designation of Stromboli Solid rocket engine.

SEPR 739-2.

  • ONERA solid rocket engine. 170 kN.

SEPR 740.

  • SEPR solid rocket engine. 91.7 kN. Out of production. Isp=230s. Used on Berenice, Titus. First flight 1962.

SEPR 740-3.

  • ONERA solid rocket engine. 170 kN.

SEPR P163.

  • Matra solid rocket engine. 1.4 kN.

SEPR P167.

  • SEP solid rocket engine.

SEPR P191.

  • Matra solid rocket engine. 14.8 kN.

SEPR-732.

  • Sud solid rocket engine. 200 kN.

SEPS.

  • Hughes, TRW, NASA Cleveland electric/mercury rocket engine. 128 mN Isp=3000s. Solar Electric Propulsion Stage program, started in the early 1970s, a goal to provide a primary ion propulsion system operating at a fixed power for Earth orbital applications.

SEPST.

  • JPL, Hughes, TRW electric/mercury rocket engine. 88 mN. Isp=3600s. The Solar Electric Propulsion System Technology program of 1960-1980 demonstrated a complete breadboard ion propulsion system that would be applicable to an interplanetary spacecraft.

Sergeant.

  • Multiple-source solid rocket engine. 6.660 kN. Out of Production. Used in Jupiter C, Juno 2. Isp=235s. First flight 1956.

Sert II.

  • NASA Cleveland electric/mercury rocket engine. 28 mN. Flown in 1970. Isp=4200s. The thruster for the Sert-II test consisted of two electron bombardment engines using mercury propellant.

Sert-I Cesium.

  • Hughes electric/cesium rocket engine. 5.6 naN. In Development, 1962-1964. Isp=8050s. 8 cm diameter cesium contact ion engine was designed to operate at 0.6 kW.

Sert-I Mercury.

  • NASA Cleveland electric/mercury rocket engine. 28 mN. Developed 1962-1964. Isp=4900s. 10 cm diameter mercury electron bombardment ion engine used on the first successful flight test of ion propulsion on a Scout X-4 launch vehicle.

Shaheen-2.

  • Sanjiang Nitric acid/UDMH rocket engine.

SICBM.

  • Thiokol solid rocket engine. 979 kN.

SICBM2.

  • Aerojet solid rocket engine. 267 kN.

SICBM3.

  • Hercules solid rocket engine. 88 kN.

SICBM4.

  • Martin solid rocket engine.

Sirocco.

  • SDC solid rocket engine.

SIT- 5.

  • Hughes electric/mercury rocket engine. 2.1 mN. Isp=3000s. 5 cm diameter mercury ion engine, developed 1970 for attitude control and north-south stationkeeping of geosynchronous satellites.

SK1.

  • Alternate designation for RD-0101 Lox-Alcohol rocket engine.

SK1K.

  • Alternate designation for RD-0102 Lox-Kerosene rocket engine.

Skybolt.

  • Douglas solid rocket engine. 111 kN.

Skybolt 2.

  • Douglas solid rocket engine.

Sled Technology.

  • Rocketdyne Lox/Alcohol rocket engine. 666 kN. Pressure-fed. From 35,000 to 150,000 lbf. Cook Sled, Air Force Sleds 1 and 2, RS-2 Sled, operated at Edwards and Holloman Air Force Bases.

SLV-1.

  • ISRO solid rocket engine. 502.6 kN. Isp=253s. Used on ASLV, PSLV, SLV. First flight 1979.

SLV-2.

  • ISRO solid rocket engine. 267 kN. Isp=267s. Used on ASLV, SLV. First flight 1979.

SLV-3.

  • ISRO solid rocket engine. 90.7 kN. Isp=277s. Used on ASLV, SLV. First flight 1979.

SLV-4.

  • ISRO solid rocket engine. 26.8 kN. Isp=283s. Used on ASLV, SLV. First flight 1979.

SM3 TSRM.

  • Thiokol solid rocket engine. 7 kN.

Snapshot.

  • EOS electric/cesium rocket engine. 8.5 mN. In Development, 1962-1964. Isp=5100s. Launched on Blue Scout Junior launch vehicle on Snapshot test; a contact ionization engine; thruster anode diameter was 5 cm.

Snipe.

  • RO solid rocket engine. 16 kN.

SNP Jericho.

  • Sud solid rocket engine. 20 kN.

SO-250.

  • ISAS solid rocket engine.

Soleil.

  • French solid rocket engine. 120 kN. 1500 kg Isolane propellant. Used on Topaze launch vehicle. First flight 1962.

Soleil NA803.

  • Nord solid rocket engine. 147 kN. 2200 kg Isolane propellant. Stretched version of the NA802. Used on Topaze launch vehicle. First flight 1964.

Sonda 1.

  • IAE solid rocket engine. 4.2 kN.

Sonda 1 Booster.

  • IAE solid rocket engine. 27 kN.

Sounding Rocket Motor.

  • Manufacturer's designation of T-7A Booster Solid rocket engine.

SpaB-17.

  • Manufacturer's designation of EPKM Solid rocket engine.

SpaB-54.

  • Fourth Academy solid rocket engine. In Production. Kick stage for orbital insertion of Iridium satellites Used on CZ-2C/SD launch vehicle. First flight 1997.

Space Gnat.

  • Government designation of Star 5A Solid rocket engine.

Space Shuttle Solid Rocket Motor.

SpaceDev Hybrid.

  • SpaceDev N2O/Solid hybrid rocket engine. 73.5 kN. Rocketplane boost. Out of production. Isp=250s. Used on Tier One launch vehicle. First flight 2002.

SpaceLoft.

  • UPAero solid rocket engine. 45 kN.

Sparrow.

  • Naval Prop Plant solid rocket engine.

SPB 7.35.

  • SNPE solid rocket engine. 690 kN. Isp=263s. Strap-on booster for Advanced Scout, Ariane 2/3. First flight 1984.

SPD 649-1.

  • Manufacturer's designation of LR47 rocket engine.

SPRAN-50.

  • French solid rocket engine.

SPRD-15.

  • Kartukov solid rocket engine. 402 kN. S-2 Strela-2 missile, Sopka. Out of Production. Thrust 27 tf at cutout - 41at ignition.

SPRD-30.

  • Kartukov solid rocket engine. 294 kN. P-15 Termit. Out of Production. Thrust 28 tf at cutout - 30 tf at ignition.

SPRD-99.

  • Kartukov solid rocket engine. 24.5 kN. MiG-21PFM. Out of Production.

SPT-100.

  • Stechkin electric rocket engine. 0.196 kN. Meteor, Gals. In Production. 1.35 kW Hall thruster. Thrust variable 2 to 20 kgf. Marketed in USA by Space Systems/Loral and Fakel. Isp=2500s.

SPT-100-SEP.

  • Stechkin solid rocket engine. In Production. The French company SEP is developing this uprated version of the SPT-100 in cooperation with OKB Fakel. Isp=2200s.

SPT-140.

  • Stechkin solid rocket engine. In Production.

SPT-200.

  • Stechkin solid rocket engine. 0.780 kN. In Production. Thrust variable 8 to 80 kgf Isp=3000s.

SPT-290.

  • Stechkin solid rocket engine. In Production.

SPT-50.

  • Stechkin solid rocket engine. Meteor-Priroda. In Production.

SPT-70.

  • Stechkin solid rocket engine. 0.098 kN. Yamal. In Production. Thrust variable 1 to 10 kgf Isp=2500s.

SPW-2000.

  • SNECMA, Pratt and Whitney lox/lh2 rocket engine. 230.4 kN. Design 2000. New upper-stage cryogenic engine for the upgraded Ariane-5, the Atlas-5, and other new vehicles.

SR105.

  • Aerojet solid rocket engine. 12.75" Improved FFAR .

SR109.

  • Thiokol solid rocket engine. Maverick AGM-65.

SR11.

  • Hercules solid rocket engine. LGM-30 Retro Motor . Used on Minuteman 1 launch vehicle.

SR110.

  • Aerodyne solid rocket engine. Super Loki PWN-10, PWN-11, PWN-12.

SR113.

  • Thiokol solid rocket engine. HARM AGM-88.

SR114.

  • Thiokol solid rocket engine. Maverick AGM-65.

SR115.

  • Aerojet solid rocket engine. Maverick AGM-65.

SR116.

  • Aerojet solid rocket engine. Sidewinder AIM-9J/P.

SR119.

  • Aerojet solid solid rocket engine. 1365 kN.

SR120.

  • Hercules solid rocket engine. 329 kN.

SR121.

  • Naval Propellant Plant solid rocket engine. Streaker MQM-107 Booster.

SR122.

  • Rocketdyne solid rocket engine. Also designated WPU-9/B1 (AGM-130).

SR13.

  • Lockheed solid rocket engine.

SR19.

  • Government designation of SR-19 Solid rocket engine.

SR-19.

  • Aerojet solid rocket engine. 267.7 kN. Minuteman 2 2nd stage. In production. Second stage of Minuteman 2. Surplus motors used as second stage of Minotaur launch vehicle and various SDI targets in 1980's. Isp=287s. First flight 2000.

SR45.

  • Atlantic Research solid rocket engine. Kitty PWN-6, Rooster PWN-7.

SR-47.

  • Government designation of UA1205 Solid rocket engine.

SR49.

  • Thiokol solid rocket engine. Genie AIR-2.

SR51.

  • Thiokol solid rocket engine. Titan 2 LGM-25C Retro Motor.

SR55.

  • United Technology Center solid rocket engine. Titan 2 LGM-25C Staging Motor.

SR59.

  • Atlantic Research solid rocket engine. Minuteman 1 LGM-30 Pitch Motor.

SR61.

  • Atlantic Research solid rocket engine. Minuteman 1 LGM-30 Spin Motor.

SR71.

  • Aerodyne solid rocket engine. Loki PWN-8.

SR73.

  • Aerojet solid rocket engine. Minuteman 1 LGM-30 3rd stage.

SR75.

  • Lockheed solid rocket engine. SRAM AGM-69, ASAT ASM-135.

SR9.

  • Hercules solid rocket engine. .

SRB.

  • Thiokol solid rocket engine. 11,520 kN. Isp=269s. Segmented solid rocket boosters for the compromised space shuttle design. Field joint design led to Challenger shuttle disaster. Production 1981-1985, after which superseded by RSRM's.

SRB-A.

  • Nissan solid rocket engine. 2250 kN. In production. Monolithic motor, shorter than that for H-2, using Thiokol filament wound composite structure. Isp=280s. First flight 2001.

SRM-1.

  • CSD solid rocket engine. 181.5 kN. Used in TOS; IUS-1 on Shuttle, Titan 34D. Known by manufacturer as Orbus 21. Propellant: 86% solids made up of HTPB UTP-19360A. Shape: cylindrical. Isp=296s. First flight 1982.

SRM-2.

  • CSD solid rocket engine. 78.4 kN. Used in Shuttle, Titan 34D; IUS-2. Known by manufacturer as Orbus 6. Isp=304s. First flight 1982.

SS-520.

  • ISAS solid rocket engine.

SSME.

  • Rocketdyne lox/lh2 rocket engine. 2278 kN. In production. Isp=453s. Space Shuttle Main Engines; only high-pressure closed-cycle reusable cryogenic rocket engine ever flown. . Three mounted in the base of the American space shuttle. First flight 1981.

SSME Demonstrator Booster.

  • Rocketdyne lox/lh2 rocket engine. 2445.7 kN. Pressure-fed. Isp=465s.

SSME Plus.

  • Notional lox/lh2 rocket engine. 3728.7 kN. VTOHL studies, 1978. Isp=467s.

SSME Study.

  • Notional lox/lh2 rocket engine. 1535.2 kN. Study 1967. Isp=459s.

SSUS-A Motor.

  • Thiokol solid rocket engine. In Production. A slightly modified stage 3 Minuteman 3 with TVC and roll control systems removed, provided propulsion for the Douglas Spinning Solid Upper Stage for use with Space Shuttle payloads.

ST.

  • Mitsubishi solid rocket engine.

ST-735-1.

  • ISAS solid rocket engine.

ST-735-2.

  • ISAS solid rocket engine.

Star 10.

  • Thiokol solid rocket engine. 3.353 kN. In Production. Isp=251s. SARV Retro MK I was a small, high-performance motor designed for use as a retrograde rocket for an unmanned satellite vehicle.

Star 12.

  • Thiokol solid rocket engine. 5.560 kN. In Production. Isp=252s. SARV Retro, MK IV and V was a 60-pound motor using 40 pounds of propellant. It was designed for use as a retrograde rocket for an unmanned satellite vehicle.

Star 12A.

  • Thiokol solid rocket engine. 7.247 kN. In Production. Isp=270s. Super SARV Retro was a longer, higher impulse version of the STAR 12, used as a retrograde rocket for an unmanned satellite vehicle.

Star 13.

  • Thiokol solid rocket engine. 3.8 kN. Out of Production. Isp=273s. A braking motor used by NASA for the Anchored Interplanetary Monitoring Platform program.

Star 13A.

  • Thiokol solid rocket engine. 5.874 kN. In Production. Isp=286s. Orbit insertion motor incorporated the lightweight titanium case developed for the STAR 13 with the propellant and nozzle design of the earlier TE-M-444 apogee motor.

Star 13B.

  • Thiokol solid rocket engine. 7.6 kN. Out of Production. Isp=285s. Orbit insertion motor incorporated the lightweight case developed for the STAR 13 with the propellant and nozzle design of the earlier TE-M-516 apogee motor.

Star 13C.

  • Thiokol solid rocket engine. Out of Production. Total impulse 8,252 kgf-sec. Motor propellant mass fraction 0.795. Isp=218s.

Star 13D.

  • Thiokol solid rocket engine. Out of Production. Total impulse 7,799 kgf-sec. Motor propellant mass fraction 0.81. Isp=223s.

Star 13E.

  • Thiokol solid rocket engine. Out of Production. Total impulse 6,438 kgf-sec. Motor propellant mass fraction 0.822. Isp=211s.

Star 13F.

  • Thiokol solid rocket engine. Out of Production. Total impulse 9,608 kgf-sec. Motor propellant mass fraction 0.83. Isp=240s.

Star 15.

  • Thiokol solid rocket engine. Out of Production. Total impulse 11,109 kgf-sec. Motor propellant mass fraction 0.926. Isp=228s.

Star 17.

  • Thiokol solid rocket engine. 10.9 kN. Skynet 1, NATO 1, and IMP-H & J. Out of production. Isp=286s. Used on Atlas LV-3A / Agena D launch vehicle. First flight 1963.

Star 17A.

  • Thiokol solid rocket engine. 16.014 kN. In Production. Isp=286s. Apogee kick motor, modified with 175 mm straight section added to the Star 17. The 17A was used to circularize orbits for the Skynet 1, NATO 1, and IMP-H & J satellites.

Star 20.

  • Thiokol solid rocket engine. 27.135 kN. In Production. Isp=286s. Altair III was developed as the propulsion unit for the fourth stage of the Scout launch vehicle. A filament-wound, fiberglass-epoxy case contained the CTPB propellant grain.

Star 20 Spherical.

  • Thiokol solid rocket engine. Out of Production. Total impulse 30,198 kgf-sec. Motor propellant mass fraction 0.934. Isp=234s.

Star 20A.

  • Thiokol solid rocket engine. Out of Production. Total impulse 83,839 kgf-sec. Motor propellant mass fraction 0.91. Isp=291s.

Star 20B.

  • Thiokol solid rocket engine. 24.467 kN. In Production. Isp=289s. Modified version of the STAR 20 with increased case structural capability over the. A filament-wound, fiberglass-epoxy case contained the CTPB propellant grain.

Star 24.

  • Thiokol solid rocket engine. 20 kN. Skynet 2. In Production. Isp=282s. Apogee boost motor was qualified and flown for the Skynet II, later apogee boost motor for NRL and SAMSO.

Star 24A.

  • Thiokol solid rocket engine. Out of Production. Total flown included in total for Star-24C. Total impulse 50,965 kgf-sec. Motor propellant mass fraction 0.903. Isp=282s.

Star 24B.

  • Thiokol solid rocket engine. Out of Production. Total flown included in total for Star-24C. Total impulse 57,236 kgf-sec. Motor propellant mass fraction 0.915. Isp=282s.

Star 24C.

  • Thiokol solid rocket engine. 21.466 kN. In Production. Isp=282s. Apogee motor designed and qualified for the NASA International Ultraviolet Experiment satellite.

Star 25.

  • Thiokol solid rocket engine. Out of Production. Total impulse 61,086 kgf-sec. Motor propellant mass fraction 0.917. Isp=240s.

Star 26.

  • Thiokol solid rocket engine. 39.1 kN. In Production. Upper stage motor used in the Sandia Strypi IV vehicle. Total flown included in total for Star-26C. Total impulse 62,800 kgf-sec. Motor propellant mass fraction 0.86. Isp=271s. First flight 1965.

Star 26B.

  • Thiokol solid rocket engine. 34.627 kN. In Production. Isp=271s. Upper stage motor flown on the Burner IIA spacecraft for Boeing and the U.S. Air Force.

Star 26C.

  • Thiokol solid rocket engine. 35 kN. In Production. Isp=272s. Upper stage motor used the titanium alloy case and nozzle attachment ring of the STAR 26B design to provide high propellant mass fraction and was insulated for high-spin-rate applications.

Star 27.

  • Thiokol solid rocket engine. 27 kN. Apogee motor used on CTS, GMS, BS, GPS, GOES satellites. In Production. Isp=288s.

Star 27A.

  • Thiokol solid rocket engine. In Production. Total flown included in total for Star-27E. Total impulse 89,684 kgf-sec. Motor propellant mass fraction 0.919. Isp=287s.

Star 27B.

  • Thiokol solid rocket engine. In Production. Total flown included in total for Star-27E. Total impulse 92,296 kgf-sec. Motor propellant mass fraction 0.921. Isp=288s.

Star 27C.

  • Thiokol solid rocket engine. In Production. Total flown included in total for Star-27E. Total impulse 88,555 kgf-sec. Motor propellant mass fraction 0.918. Isp=287s.

Star 27D.

  • Thiokol solid rocket engine. In Production. Total flown included in total for Star-27E. Total impulse 88,668 kgf-sec. Motor propellant mass fraction 0.921. Isp=287s.

Star 27E.

  • Thiokol solid rocket engine. In Production. Total impulse 88,301 kgf-sec. Motor propellant mass fraction 0.921. Isp=287s.

Star 30.

  • Thiokol solid rocket engine. Out of Production. Total flown included in total for Star-30A. Total impulse 136,455 kgf-sec. Motor propellant mass fraction 0.943. Isp=293s.

Star 30A.

  • Thiokol solid rocket engine. Out of Production. Total impulse 137,095 kgf-sec. Motor propellant mass fraction 0.942. Isp=294s.

Star 30B.

  • Thiokol solid rocket engine. Out of Production. Total impulse 148,816 kgf-sec. Motor propellant mass fraction 0.941. Isp=293s.

Star 30BP.

  • Thiokol solid rocket engine. 27 kN. In Production. Isp=292s. Apogee motor used for the HS 376 satellite bus. Incorporated an 89-percent-solids HTPB propellant in a 6AI-4V titanium case insulated with silica-filled EPDM rubber.

Star 30C.

  • Thiokol solid rocket engine. 32.6 kN. AS 3000. In Production. Isp=286s. Apogee motor used for the RCA G-STAR and Martin Marietta series 3000 telecom satelllites.

Star 30E.

  • Thiokol solid rocket engine. 35.4 kN. Koreasat. In Production. Isp=290s. Apogee motor used for the BAe Skynet 4 satellite, Koreasat and by the ORBEX small orbital launcher.

Star 31.

  • Thiokol solid rocket engine. 80 kN. In Production. Isp=293s. Antares III, third-generation third stage for Scout launch vehicle. Propellant: AP/HTPB/Al propellant in a filament wound Kevlar case.

Star 37.

  • Thiokol solid rocket engine. 43.5 kN. Total impulse 161,512 kgf-sec. Motor propellant mass fraction 0.899. Isp=260s. First flight 1963.

Star 37B.

  • Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 189,489 kgf-sec. Motor propellant mass fraction 0.91. Isp=291s.

Star 37C.

  • Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 275,959 kgf-sec. Motor propellant mass fraction 0.921. Isp=285s.

Star 37D.

  • Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 189,489 kgf-sec. Motor propellant mass fraction 0.91. Isp=266s.

Star 37E.

  • Thiokol solid rocket engine. 68 kN. Out of Production. Total impulse 296,635 kgf-sec. Motor propellant mass fraction 0.926. Isp=283s.

Star 37F.

  • Thiokol solid rocket engine. 55.5 kN. Out of Production. Total impulse 249,177 kgf-sec. Motor propellant mass fraction 0.928. Isp=286s.

Star 37FM.

  • Thiokol solid rocket engine. 47.9 kN. In Production. Isp=289s. Apogee kick motor for the FLTSTACOM satellite. The motor case contained the same volume as the discontinued STAR 37E.

Star 37G.

  • Thiokol solid rocket engine. Out of Production. Total impulse 304,620 kgf-sec. Motor propellant mass fraction 0.925. Isp=289s.

Star 37N.

  • Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 162,102 kgf-sec. Motor propellant mass fraction 0.898. Isp=290s.

Star 37S.

  • Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 190,590 kgf-sec. Motor propellant mass fraction 0.925. Isp=287s.

Star 37X.

  • Thiokol solid rocket engine. 51.1 kN. Out of Production. Total impulse 310,668 kgf-sec. Motor propellant mass fraction 0.928. Isp=295s.

Star 37XE.

  • Thiokol solid rocket engine. 45 kN.

Star 37XF.

  • Thiokol solid rocket engine. 45 kN. Out of Production. Total flown included in total for Star-37XF-8. Total impulse 259,123 kgf-sec. Motor propellant mass fraction 0.929. Isp=290s.

Star 37XF 8.

  • Thiokol solid rocket engine. Out of Production. Total impulse 238,809 kgf-sec. Motor propellant mass fraction 0.924. Isp=291s.

Star 37XFP.

  • Thiokol solid rocket engine. 31.5 kN. In Production. Isp=290s. Orbit insertion motor qualified for Global Positioning Satellite. Used as a replacement for the discontinued STAR 37F. Propellant: 884 kg of AP/HTPB/Al in 6Al-4V titanium case.

Star 37Y.

  • Thiokol solid rocket engine. Out of Production. Total impulse 317,856 kgf-sec. Motor propellant mass fraction 0.93. Isp=297s.

Star 40.

  • Thiokol solid rocket engine. Out of Production. Total impulse 200,882 kgf-sec. Motor propellant mass fraction 0.925. Isp=207s.

Star 48.

  • Thiokol solid rocket engine. 67.2 kN. Used in Delta 3900; Conesotga; PAM-S; PAM-D. Total flown included in total for Star-48-8. Total impulse 575,682 kgf-sec. Motor propellant mass fraction 0.946. Isp=286s. First flight 1982.

Star 48 8.

  • Thiokol solid rocket engine. Out of Production. Total impulse 587,784 kgf-sec. Motor propellant mass fraction 0.945. Isp=292s.

Star 48A l.

  • Thiokol solid rocket engine. In Production. Total impulse 709,062 kgf-sec. Motor propellant mass fraction 0.941. Isp=289s.

Star 48A s.

  • Thiokol solid rocket engine. 77.109 kN. In Production. Isp=283s. Short nozzle upper-stage motor designed to fit within the dimensional envelope of the long nozzle.

Star 48B.

  • Thiokol solid rocket engine. 66 kN. In Production. Isp=286s. Long nozzle upper-stage motor qualified for the McDonnell Payload Assist Module (PAM) Delta.

Star 48B l.

  • Thiokol solid rocket engine. In Production. Isp=292s. Lengthened version of Star 48B to provide increased payload capability. The design incorporates a longer cylindrical section in the motor case.

Star 48B s.

  • Thiokol solid rocket engine. 77.109 kN. In Production. Isp=286s. Short nozzle upper-stage motor qualified for the McDonnell Douglas Payload Assist Module (PAM) Space Transportation System (STS).

Star 48V.

  • Thiokol solid rocket engine. In Production. Developed for Conestoga's upper stage, providing some 4 degrees capability at 30 degree/sec using the same loaded casing as the 48B. First Flight: 1994.

Star 5.

  • Thiokol solid rocket engine. Out of Production. Total impulse 405 kgf-sec. Motor propellant mass fraction 0.87. Isp=189s.

Star 5A.

  • Thiokol solid rocket engine. 0.166 kN. In Production. Isp=249s. Space Gnat was designed to provide a minimum acceleration, extended burn delta-V impulse, for small payload replacement or spin-up applications.

Star 5C.

  • Thiokol solid rocket engine. 2.039 kN. Out of Production. Titan Retro designed to separate the second stage from the upper stage of the Titan IV launch vehicle.

Star 5C/CB.

  • Thiokol solid rocket engine. 1.951 kN. In Production. Isp=266s. Titan Retro designed to separate the second stage from the transtage on the Titan II missile and Titan launch vehicle. The motor was also adapted for other uses.

Star 5CB.

  • Thiokol solid rocket engine. 2 kN. In Production. Reduced Al HTPB propellant (2.1 kg) minimizes contamination when Used in a Titan 4 stage separation motor. Diameter: 121 mm. Length: 341 mm. Mass: 4.5 kg. Itotal: 5.5 kNs. Burn Time: 2.77 sec.

Star 6.

  • Thiokol solid rocket engine. Out of Production. Total flown included in total for Star-6A. Total impulse 1,395 kgf-sec. Motor propellant mass fraction 0.795. Isp=287s.

Star 62.

  • Thiokol solid rocket engine. Out of Production. Total impulse 725,491 kgf-sec. Motor propellant mass fraction 0.94. Isp=294s.

Star 63.

  • Thiokol solid rocket engine. 107.2 kN. Used in Shuttle,Titan 34D. Isp=282s. Used on Delta 7925 launch vehicle. First flight 1990.

Star 63D.

  • Thiokol solid rocket engine. 84.739 kN. In Production. Isp=283s. Perigee motor with a range of propellant loads, yielding GTO payloads from 3,080 to 4,588 pounds at a constant velocity of 8,012 feet per second.

Star 63F.

  • Thiokol solid rocket engine. 104.627 kN. In Production. Isp=297s. Provided perigee kick for the McDonnell PAM-D2 system. Another version was the Star 63D (TU-936).

Star 6A.

  • Thiokol solid rocket engine. Out of Production. Total impulse 935 kgf-sec. Motor propellant mass fraction 0.723. Isp=285s.

Star 6B.

  • Thiokol solid rocket engine. 2.510 kN. In Production. Isp=273s. Delta-V reentry motor developed as a spin-up and propulsion motor for reentry vehicles. The design incorporated an aluminum case and a plastic nozzle assembly.

Star 75.

  • Thiokol solid rocket engine. 242.8 kN. In Production. Isp=288s. A demonstration motor tested as a first step in the development of a perigee kick motor in the 4080-7940 kg propellant range.

Stepanov IS/US 1 kgf.

  • Stepanov N2O4/UDMH rocket engine. 10 N. IS/US. Out of Production.

Stepanov IS/US 16 kgf.

  • Stepanov N2O4/UDMH rocket engine. 0.157 kN. IS/US. Out of Production.

Stepanov LK/LOK 10 kgf.

  • Stepanov N2O4/UDMH rocket engine. 0.098 kN. LK/LOK attitude. Out of Production.

Stepanov LK/LOK 40 kgf.

  • Stepanov N2O4/UDMH rocket engine. 0.390 kN. LK/LOK attitude. Out of Production.

STME.

  • Rocketdyne lox/lh2 rocket engine. 2890 kN. Cancelled 1984. Isp=430s. Space Transportation Main Engine. Rocketdyne was teamed with Aerojet and Pratt & Whitney on the STME, which was to have powered the next generation of large launch vehicles.

Stonechat I.

  • RO solid rocket engine. 232 kN. Largest solid rocket motor ever produced in Britain. Motor developed for hypersonic research vehicle. Subsequently used in Falstaff test vehicle.

Stonechat II.

  • RO solid rocket engine. 242 kN.

Stonechat Mk 2.

  • Royal Ordnance solid rocket engine. Out of production. There seem to have been even larger classified versions. Used on Falstaff launch vehicle.

Stromboli.

  • SEPR solid rocket engine. 143 kN. Out of production. Isp=235s. Used on Berenice, Tacite, Titus. First flight 1962.

Super Loki.

  • Aerojet solid rocket engine. 18 kN.

Super SARV Retro.

  • Government designation of Star 12A Solid rocket engine.

T-140.

  • Pratt and Whitney electric rocket engine. 3 kW Hall thruster

T-220.

  • Pratt and Whitney / Keldysh Research Center electric rocket engine. Development began in 1997 of this 10 kW Hall thruster Program concluded in 2000 following a 1000 hour erosion characterization.

T-40.

  • Thiokol solid rocket engine. 13.3 kN.

T-55.

  • Thiokol solid rocket engine. 21 kN.

T-7 booster.

  • SIMED/Shanghai solid rocket engine.

T-7 LRE.

  • SIMED/Shanghai solid rocket engine.

T-7A Booster.

  • Fourth Academy solid rocket engine. 46 kN. T-7 sounding rocket. Out of Production. Isp=209s. China's first flight solid rocket. First flight 1965. Polysulfide binder with aluminium binder fuel in case of high strength steel with a graphite throat insert.

TAL-100.

  • TsNIIMASH electric/xenon rocket engine. 34 mN. Development. Isp=1450s. Hall effect thruster with anode layer. Export version of D-100-I thruster developed under NASA/BMDO contract. Taken to engineering model stage.

TAL-38.

  • TsNIIMASH electric/xenon rocket engine. 8 mN. Development. Isp=2500s. Hall effect thruster with anode layer. Export version of D-38, developed under NASA contract for satellite station-keeping and attitude control. Taken to engineering model stage.

Talos Mk 11 Mod 2.

  • Hercules solid rocket engine. 516 kN. Talos motor fitted with a conical adapter for mating to the second stage.

TAL-WSF.

  • TsNIIMASH electric/xenon rocket engine. 12 mN. Isp=1350s. Hall effect thruster with anode layer. Export version of D-55 thruster developed under NASA/BMDO contract for flight test under RHETT-II program. Used for satellite orbital altitude maintenance.

Taurus.

  • Hercules solid rocket engine. 457 kN.

TD-174.

  • Manufacturer's designation of LR44 rocket engine.

TD-187.

  • Manufacturer's designation of LR58 rocket engine.

TD-2.

  • CMIK Nitric acid/UDMH rocket engine. 1000 kN.

TD-232.

  • Manufacturer's designation of LR62 rocket engine.

TDU-1.

  • Manufacturer's designation of S5.4 Nitric acid-Amine rocket engine.

TE-307.

  • Thiokol solid rocket engine. 21 kN.

TE-388.

  • Thiokol solid rocket engine. 24.4 kN.

TE-416.

  • Thiokol solid rocket engine. 53 kN.

TE-473.

  • Thiokol solid rocket engine. 90 kN.

TE-M-184-3.

  • Manufacturer's designation of Star 25 Solid rocket engine.

TE-M-186-2.

  • Manufacturer's designation of Star 40 Solid rocket engine.

TE-M-195.

  • Manufacturer's designation of Star 10 Solid rocket engine.

TE-M-236.

  • Manufacturer's designation of Star 12 Solid rocket engine.

TE-M-236-3.

  • Manufacturer's designation of Star 12A Solid rocket engine.

TE-M-251.

TE-M-344-15.

  • Manufacturer's designation of Star 5C-CB Solid rocket engine.

TE-M-344-16.

  • Manufacturer's designation of Star 5C Solid rocket engine.

TE-M-345-11/12.

  • Manufacturer's designation of Star 13C Solid rocket engine.

TE-M-364-1.

  • Manufacturer's designation of Star 37 Solid rocket engine.

TE-M-364-11.

  • Manufacturer's designation of Star 37G Solid rocket engine.

TE-M-364-14.

  • Manufacturer's designation of Star 37N Solid rocket engine.

TE-M-364-15.

  • Manufacturer's designation of Star 37S Solid rocket engine.

TE-M-364-18.

  • Manufacturer's designation of Star 37C Solid rocket engine.

TE-M-364-19.

  • Manufacturer's designation of Star 37F Solid rocket engine.

TE-M-364-2.

  • Manufacturer's designation of Star 37B Solid rocket engine.

TE-M-364-3.

  • Manufacturer's designation of Star 37D Solid rocket engine.

TE-M-364-4.

  • Manufacturer's designation of Star 37E Solid rocket engine.

TE-M-375.

  • Manufacturer's designation of Star 13D Solid rocket engine.

TE-M-385.

  • Manufacturer's designation of Star 13E Solid rocket engine.

TE-M-442.

  • Manufacturer's designation of Star 26 Solid rocket engine.

TE-M-442-1.

  • Manufacturer's designation of Star 26B Solid rocket engine.

TE-M-442-2.

  • Manufacturer's designation of Star 26C Solid rocket engine.

TE-M-444.

  • Manufacturer's designation of Star 13F Solid rocket engine.

TE-M-456-2.

  • Manufacturer's designation of Star 15 Solid rocket engine.

TE-M-458.

  • Manufacturer's designation of Star 13 Solid rocket engine.

TE-M-479.

  • Manufacturer's designation of Star 17 Solid rocket engine.

TE-M-500.

  • Manufacturer's designation of Star 5 Solid rocket engine.

TE-M-516.

  • Manufacturer's designation of Star 13A Solid rocket engine.

TE-M-521-5.

  • Manufacturer's designation of Star 17A Solid rocket engine.

TE-M-541-3.

  • Manufacturer's designation of Star 6 Solid rocket engine.

TE-M-542-3.

  • Manufacturer's designation of Star 6A Solid rocket engine.

TE-M-604.

  • Manufacturer's designation of Star 24 Solid rocket engine.

TE-M-604-2.

  • Manufacturer's designation of Star 24A Solid rocket engine.

TE-M-604-3.

  • Manufacturer's designation of Star 24B Solid rocket engine.

TE-M-604-4.

  • Manufacturer's designation of Star 20B Solid rocket engine.

TE-M-616.

  • Manufacturer's designation of Star 27 Solid rocket engine.

TE-M-616-1.

  • Manufacturer's designation of Star 27A Solid rocket engine.

TE-M-616-4.

  • Manufacturer's designation of Star 27B Solid rocket engine.

TE-M-616-5.

  • Manufacturer's designation of Star 27C Solid rocket engine.

TE-M-616-8.

  • Manufacturer's designation of Star 27D Solid rocket engine.

TE-M-616-9.

  • Manufacturer's designation of Star 27E Solid rocket engine.

TE-M-640.

  • Manufacturer's designation of FW-4S TEM640 Solid rocket engine.

TE-M-640-1.

  • Manufacturer's designation of Star 20 Solid rocket engine.

TE-M-640-3.

  • Manufacturer's designation of Star 20A Solid rocket engine.

TE-M-700-18.

  • Manufacturer's designation of Star 30C Solid rocket engine.

TE-M-700-19.

  • Manufacturer's designation of Star 30E Solid rocket engine.

TE-M-700-2.

  • Manufacturer's designation of Star 30 Solid rocket engine.

TE-M-700-20.

  • Manufacturer's designation of Star 30BP Solid rocket engine.

TE-M-700-4.

  • Manufacturer's designation of Star 30A Solid rocket engine.

TE-M-700-5.

  • Manufacturer's designation of Star 30B Solid rocket engine.

TE-M-711-17.

  • Manufacturer's designation of Star 48B s Solid rocket engine.

TE-M-711-18.

  • Manufacturer's designation of Star 48B l Solid rocket engine.

TE-M-711-3.

  • Manufacturer's designation of Star 48 Solid rocket engine.

TE-M-711-8.

  • Manufacturer's designation of Star 48 8 Solid rocket engine.

TE-M-714-1.

  • Manufacturer's designation of Star 37X Solid rocket engine.

TE-M-714-16/17.

  • Manufacturer's designation of Star 37XFP Solid rocket engine.

TE-M-714-2.

  • Manufacturer's designation of Star 37Y Solid rocket engine.

TE-M-714-6.

  • Manufacturer's designation of Star 37XF Solid rocket engine.

TE-M-714-8.

  • Manufacturer's designation of Star 37XF 8 Solid rocket engine.

TE-M-731.

  • Manufacturer's designation of Star 62 Solid rocket engine.

TE-M-762.

  • Manufacturer's designation of Star 31 Solid rocket engine.

TE-M-763.

  • Manufacturer's designation of Star 13B Solid rocket engine.

TE-M-775-1.

  • Manufacturer's designation of Star 75 Solid rocket engine.

TE-M-783.

  • Manufacturer's designation of Star 37FM Solid rocket engine.

TE-M-790-1.

  • Manufacturer's designation of Star 6B Solid rocket engine.

TE-M-799.

  • Manufacturer's designation of Star 48B Solid rocket engine.

TE-M-799-1.

  • Manufacturer's designation of Star 48A s Solid rocket engine.

TE-M-863-1.

  • Manufacturer's designation of Star 5A Solid rocket engine.

TE-M-940-1.

  • Manufacturer's designation of Star 48V Solid rocket engine.

TE-M-963.

  • Manufacturer's designation of Star 63F Solid rocket engine.

Terrier Mk12 Mod 0.

  • Naval Prop Plant solid rocket engine. 257.5 kN. The Terrier MK 12 Mod 1 rocket motor was typically equipped with four 0.22 square meter fin panels arranged in a cruciform configuration.

Terrier Mk12 Mod 1.

  • Hercules solid rocket engine. 257.5 kN.

THAAD.

  • Lockheed solid rocket engine.

Theodore.

  • ATEF solid rocket engine.

Thiokol 156.

  • Thiokol solid rocket engine. 14,746.1 kN. Developed to 1966. Isp=263s.

Timberwind 250.

  • DoE nuclear/lh2 rocket engine. 2451.6 kN. Development ended 1992. Isp=1000s. Used on Timberwind launch vehicle.

Timberwind 45.

  • DoE nuclear/lh2 rocket engine. 441.3 kN. Development ended 1992. Isp=1000s. Used on Timberwind Centaur launch vehicle.

Timberwind 75.

  • DoE nuclear/lh2 rocket engine. 735.5 kN. Development ended 1992. Isp=1000s. Used on Timberwind Titan launch vehicle.

Tiny Tim.

  • Naval Prop Plant solid rocket engine. 220 kN.

TIROC.

  • Kayser N2O4/MMH rocket engine. 1 N. Satellite orientation. Isp=303s. Tangential Injection and Rotational Combustion, the world's smallest thruster burning monomethylhydrazine and nitrogen tetroxide.

Titan Retro.

  • Government designation of Star 5C-CB Solid rocket engine.

TM-50.

  • TsNIIMASH electric/xenon rocket engine. 250 mN. Development. Isp=3000s. Hall effect thruster with anode layer, designed for satellite orbital raising. Taken to engineering model stage.

Topaze.

  • SEP N2O4/UDMH rocket engine. 120.1 kN. Out of production. Isp=255s. Used on Diamant launch vehicle. First flight 1965.

Toroid FD.

  • Notional lox/lh2 rocket engine. 20,015 kN. Study 1963. Operational date would have been December 1976. Engines for recoverable stage. Isp=455s. Used on Nova MM T10RR-2 launch vehicle.

Toroidal 400k.

  • Notional lox/lh2 rocket engine. 1778 kN. Study 1967. Isp=447s. Used on Saturn V-3B launch vehicle.

Toroidal 560k.

  • Notional lox/lh2 rocket engine. 2491 kN. Design concept 1990's. Isp=447s.

TR106.

  • Manufacturer's designation of TR-106 Lox-LH2 rocket engine.

TR-106.

  • TRW lox/lh2 rocket engine. 2892 kN. Development. Innovative TRW 650K Low Cost Pintle Engine, test fired at NASA's test center in October 2000.

TR-107.

  • TRW lox/kerosene rocket engine. 4900 kN. Booster stages. TRW design for NASA's Space Launch Initiative. The engine used duct-cooling of the main combustion chamber and materials that would not interact with kerosene to minimise coking.

TR-1-10800.

  • NASDA solid rocket engine. 608 kN.

TR-1-7500.

  • NASDA solid rocket engine. 608 kN.

TR-201.

  • TRW N2O4/Aerozine-50 rocket engine. 41.9 kN. Apollo lunar module ascent stage engines. Surplus engines used on Delta P stage. Isp=301s. First flight 1972.

Tramontane.

  • SEPR solid rocket engine. 50 kN. Out of production. Isp=220s. Used on Berenice launch vehicle. First flight 1962.

Transtar.

  • Aerojet N2O4/MMH rocket engine. 16.7 kN. Development completed 1987. Isp=328s. Upper stage engine using injectors, chamber, and nozzle derived from the Shuttle OMS system, but pump-fed for increased chamber pressure and Isp. Tested; no production.

Trident Motor.

  • Philco-Ford solid rocket engine. 35 kN.

Trident St 3.

  • CSD solid rocket engine.

Truax LH2.

  • Aerojet lox/lh2 rocket engine. 147.1 kN. Test 1962. Used in Sea Horse-2. Isp=425s.

TT-200.

  • NASDA solid rocket engine.

TT-210.

  • NASDA solid rocket engine.

TT-500.

  • NASDA solid rocket engine. 116 kN.

TT-500-S2.

  • NASDA solid rocket engine. 61 kN.

TU-289.

  • Manufacturer's designation of SR49 rocket engine.

TU-715.

  • Thiokol solid rocket engine. 85 kN.

TU-716.

  • Thiokol solid rocket engine. 186 kN.

TU-758.

  • Thiokol solid rocket engine. 55.1 kN.

TU-844.

  • Manufacturer's designation of SSUS-A Motor Solid rocket engine.

TU-903.

  • Manufacturer's designation of Peacekeeper 1 Solid rocket engine.

TU-904.

  • Thiokol solid rocket engine. 1711 kN.

TU-936.

  • Manufacturer's designation of Star 63D Solid rocket engine.

TX-135.

  • Thiokol solid rocket engine. 2000 kN.

TX-174.

  • Thiokol solid rocket engine. 117 kN.

TX-175.

  • Thiokol solid rocket engine. 85 kN.

TX-20.

  • Thiokol solid rocket engine. 213 kN.

TX-238.

  • Thiokol solid rocket engine.

TX-239.

  • Thiokol solid rocket engine.

TX-261-3.

  • Thiokol solid rocket engine. 244 kN.

TX-30.

  • Thiokol solid rocket engine. 44.5 kN.

TX-33.

  • Thiokol solid rocket engine. 285 kN.

TX-354-3.

  • Thiokol solid rocket engine. 258.9 kN. Used in Scout A; Delta E; H-1-0; Castor 2. License built in Japan for H-1. Isp=262s. First flight 1960.

TX-454.

  • Thiokol solid rocket engine.

TX-481.

  • Manufacturer's designation of SR109 rocket engine.

TX-500.

  • Thiokol solid rocket engine. 2000 kN.

TX-52.

  • Thiokol solid rocket engine. 168 kN.

TX-526.

  • Manufacturer's designation of Castor 4 Solid rocket engine.

TX-633.

  • Manufacturer's designation of SR114 rocket engine.

TX-664-4.

  • Thiokol solid rocket engine. Basic Terrier mk70 motor.

TX-77.

  • Thiokol solid rocket engine. 227 kN.

TX-780.

  • Manufacturer's designation of Castor 4A Solid rocket engine.

TX-780B.

  • Manufacturer's designation of Castor 4B rocket engine.

TX-780XL.

  • Manufacturer's designation of Castor 4AXL Solid rocket engine.

TX-859.

  • Manufacturer's designation of Castor 4BXL Solid rocket engine.

U102-000.

  • Glushko Nitric acid/UDMH rocket engine. 468 kN. R-26 stage 2. Out of production. Isp=307s.

U-1250.

  • Isayev rocket engine. 12.7 kN. Developed 1945-46. Isp=208s.

U-2000.

  • Isayev rocket engine. 19.6 kN. for SAM. Out of Production.

U-400-10.

  • Isayev rocket engine. 3.920 kN. Samolet 5. Developed 1946-47.

U-400-2.

  • Isayev Nitric acid/Amine rocket engine. Shchuka. Out of Production.

UA1205.

  • CSD solid rocket engine. 5849.3 kN. Out of production. Isp=263s. Strap-on boosters for Titan 3C, 3D, 3E. Proposed for advanced Saturn IB versions. First flight 1965.

UA1206.

  • CSD solid rocket engine. 6226.9 kN. Isp=265s. Used on Titan 34D launch vehicle. First flight 1982.

UA1207.

  • CSD solid rocket engine. 7116.9 kN. Isp=272s. First flight 1989.

UA-156.

  • CSD solid rocket engine. 8924.3 kN. Tested 1968. Isp=263s. Proposed as strap-on booster for Saturn INT-27, Saturn V-25(S)B, Saturn V-25(S)U.

UM-129A.

  • Nissan solid rocket engine. 77.5 kN. In Production. Used in H-1-3. Isp=291s.

Upstage.

  • Boeing solid rocket engine.

USRM.

  • Hercules solid rocket engine. 7560.5 kN. Isp=286s.Strap-on booster for Titan 4B. First flight 1997.

V-1000.

  • Novator solid rocket engine.

Vega.

  • Sud solid rocket engine. 20 kN.

Vela.

  • WRE solid rocket engine.

Venus.

  • Sud solid rocket engine. 44 kN.

Vero P2.

  • LRBA solid rocket engine.

Vero P6.

  • LRBA solid rocket engine. 20 kN.

Veronique.

  • LRBA solid rocket engine. 40 kN.

Veronique 61.

  • LRBA Nitric acid/Turpentine rocket engine. 60 kN.

Veronique AGI.

  • LRBA Nitric acid/Turpentine rocket engine. 40 kN.

Vesta.

  • LRBA Nitic acid/Turpentine rocket engine. 140 kN.

Vexin A.

  • SEP N2O4/UDMH rocket engine. 68.6 kN. Isp=277s. Used on Europa launch vehicle. First flight 1964.

Vexin B.

  • SEP N2O4/UDMH rocket engine. 75.4 kN. Out of production. Isp=251s. Used on Diamant launch vehicle. First flight 1965.

Vexin C.

  • SEP N2O4/UDMH rocket engine. 99.1 kN. Out of production. Isp=251s. Used on Diamant B launch vehicle. First flight 1970.

Viking 2.

  • SEP N2O4/UDMH rocket engine. 693 kN. In production. Isp=281s. Used on Ariane 1, GSLV space launchers. First flight 1979.

Viking 2B.

  • SEP N2O4/UDMH rocket engine. 720 kN. Isp=278s. Used on Ariane 2/3. First flight 1984.

Viking 4.

  • SEP N2O4/UDMH rocket engine. 721 kN. Isp=296s. Used on Ariane 1, GSLV, PSLV. First flight 1979.

Viking 4B.

  • SEP N2O4/UDMH rocket engine. 805 kN. Isp=296s. Used on Ariane 4. First flight 1984.

Viking 5C.

  • SEP N2O4/UDMH rocket engine. 752 kN. Isp=278s. Used on Ariane 42L, Ariane 44L, Ariane 44LP. First flight 1988.

Vinci.

  • Snecma, Ottobrunn lox/lh2 rocket engine. 180 kN. Upper Stages. In development. Isp=467s. Advanced expander cycle cryogenic propellant rocket engine with the capability of five in-space restarts. First hot-fire tests 2005. First flight 2010.

Viper-20.

  • Multiple-source American solid rocket engine. 20 kN. Viper

Viper-25.

  • Aerojet solid rocket engine. 25 kN.

Viper-27.

  • Multiple-source American solid rocket engine. 27 kN.

Von Braun-1.

  • Notional Nitric acid/UDMH rocket engine. 3057.3 kN. Study 1952. Isp=286s. Used on Von Braun launch vehicle.

Von Braun-2.

  • Notional Nitric acid/UDMH rocket engine. 461.5 kN. A11, Von Braun studies 1943-1952. Isp=286s.

Von Braun-3.

  • Notional Nitric acid/UDMH rocket engine. 392.3 kN. Study 1952. Isp=286s. Used on Von Braun launch vehicle.

Vulcain.

  • SEP, Ottobrunn lox/lh2 rocket engine. 1075 kN. In production. Isp=431s. Powered the cryogenic core stage of Ariane 5. First flight 1996.

Vulcain 2.

  • SEP, Ottobrunn lox/lh2 rocket engine. 1350 kN. In development. Isp=434s. New generator cycle rocket engine for an Ariane 5 core stage upgrade. Thrust increased more than 30% from Vulcain 1. First flight 2002.

WAC.

  • JPL/Douglas Nitric acid/aniline rocket engine. 6.7 kN.

Wasserfall.

  • Wehrmacht Nitric acid/Tonka rocket engine. 80 kN.

X-1.

  • Rocketdyne Lox/Kerosene rocket engine. 880.440 kN. Booster applications. Gas generator, pump-fed. Thrust from 165,000 to 198,000 lbs.

X-220.

  • Hercules solid rocket engine. 26 kN.

X-241.

  • Hercules solid rocket engine. 12.1 kN.

X-248.

  • Thiokol solid rocket engine. 12.4 kN. Isp=256s. Used on Atlas Able, Blue Scout 2, Caleb, Delta, Delta A, Delta B, Delta C. First flight 1959.

X-248A.

  • Thiokol solid rocket engine. 13.8 kN. Isp=255s. Used on Scout X-1, Scout X-2, Scout X-3. First flight 1960.

X-250.

  • Hercules solid rocket engine.

X-254.

  • Thiokol solid rocket engine. 60.5 kN. Isp=256s. Used on Blue Scout 1, Blue Scout 2, Blue Scout Junior, Scout X-1. First flight 1960.

X-256.

  • Hercules solid rocket engine. 257.5 kN.

X-258.

  • Thiokol solid rocket engine. 22.2 kN. Isp=266s. Kick stage motor for Delta D, Scout A, Scout X-4. First flight 1963.

X-259.

  • Thiokol solid rocket engine. 93.1 kN. Isp=293s. Used on Scout A, Scout B, Scout D, Scout F, Scout X-2, Scout X-3, Scout X-4. First flight 1962.

X-259A.

  • Thiokol solid rocket engine. 80.8 kN. Out of production. Isp=295s. Used on Scout G launch vehicle. First flight 1979.

X-260.

  • Hercules solid rocket engine.

X-265.

  • Hercules solid rocket engine.

X-271.

  • Hercules solid rocket engine.

X35AL-6000.

  • Aerojet rocket engine. PB2Y-3 ATO. Launch thrust 26.77 kN. Development begun November 1942.

X-405.

  • GE Lox/Kerosene rocket engine. 134.8 kN. Vanguard 1st stage. Isp=270s. First flight 1957.

X-430.

  • GE exoticLF2/LH2 rocket engine. 334 kN. Developed 1960's. Very high energy engine developed in early 1960's for future large upper stages. Not flown due to toxicity of propellants.

X45ALD-4000.

  • Manufacturer's designation of XLR13-AJ-5 Nitric acid-Amine rocket engine.

X45ALD-4000.

  • Aerojet Nitric acid/Amine rocket engine. B-29 ATO. Launch thrust 17.6 kN. Development begun June 1948. Regenerative cooling, nitrogen pressure-fed, droppable but no recoverable. Early version using XLR-13-AJ-1 thrust chamber assembly.

X4-AL-1000.

  • Aerojet Nitric acid/Amine rocket engine. Brake rocket for G-4A. Launch thrust 4.41 kN. Braking rocket for glider. Single uncooled chamber, pressure fed, 13 kg of propellant.

X60AL-1300.

  • Aerojet Nitric acid/Amine rocket engine. P-51 superperformance. Launch thrust 5.78 kN. Development begun January 1945. Superperformance

X60ALD-4000.

  • Manufacturer's designation of XLR13-AJ-7 Nitric acid-Amine rocket engine.

X60ALD-4000.

  • Aerojet Nitric acid/Amine rocket engine. ATO for XB-45, B-45A. Launch thrust 17.6 kN. Development begun May 1946. Pressurising tank surrounded propellant tanks. Regeneratively cooled. Parachute for dropping and recovery after takeoff.

X-8.

  • Rocketdyne lox/lh2 rocket engine. Launch thrust 400.1 kN. Booster applications. Gas generator, pump-fed. Thrust and specific impulse values are at sea level.

X90ALT-60000.

  • Aerojet Nitric acid/Amine rocket engine. Launch thrust 264 kN. Development begun April 1947. Unspecified Application, 20,000 Ibf subscale tested, new vertical test facility

XASR-1.

  • Aerojet Nitric acid/aniline rocket engine. 11.6 kN.

XCAL-200.

  • Government designation of 300LR-200 Nitric acid-Amine rocket engine.

XCALR-2000A-1.

  • Aerojet Nitric acid/Amine rocket engine for XP-79 Northrop Flying Wing. Thrust 9.12 kN. Aerotojet, a pair of canted 130 kgf thrust chambers mounted longitudinally on a drive shaft, which drove the turbopumps. Developed 1943-1945; blew up on first test.

XCALT-6000.

  • Aerojet Nitric acid/Amine rocket engine. Thrust 26.67 kN. Conservative alternate to Aerotojet for XP-79 flying wing rocket fighter. Successfully tested in August 1945, but project cancelled. Regeneratively cooled, 4 thrust chambers, pump-fed.

XCNLT-1500.

  • Aerojet isopropylnitrate monopropellant rocket engine. Lark. Launch thrust 6.66 kN. Development begun March 1945. Turborocket; turbine-pump fed monopropellant, single uncooled thrust chamber. Development unsuccessful, all work terminated.

XCNLT-600/1000/1500.

  • Manufacturer's designation of XCNLT-1500 Isopropylnitrate rocket engine.

XIPS-13 0.44 kW.

  • Hughes electric/xenon rocket engine. 17.8 mN. In Production. Isp=2585s. HS 702 operational communications satellites each employed four of these 0.44 kW xenon ion thrusters.

XIPS-25 1.3 kW.

  • Hughes electric/xenon rocket engine. 63 mN. Isp=2800s. XIPS-25 program, conducted by Hughes, developed thrusters, BBPPUs, and a feed system pressure regulator for stationkeeping of 2500 kg class communication satellites.

XIPS-25 4.2 kW.

  • Hughes electric/xenon rocket engine. 165 mN. Isp=3800s. 25 cm diameter xenon engine system for orbital circularization, station-keeping, attitude control, and momentum dumping for its HS 702 spacecraft.

XJ40-WE-1.

  • Wright turbojet engine. 48.5 kN. Out of production. Thrust is maximum thrust at cruise altitude. Specific impulse is that at cruise design point. Isp=1800s. Used on Navaho X-10 launch vehicle. First flight 1955.

XLR105-5.

  • Rocketdyne Lox/Kerosene rocket engine. 363.2 kN. Atlas D. Atlas Sustainer. Gas generator, pump-fed. Shared turbopumps for booster engines. Isp=309s. First flight 1958.

XLR11.

  • Reaction Motors, Thiokol Lox/Alcohol rocket engine. Out of Production. Launch thrust 26.67 kN. Rocket engine developed for X-1 in 1940s to break the sound barrier and used twenty years later to power experimental lifting bodies. Four combustion chambers.

XLR11-RM-1.

  • Government designation of XLR11 Lox-Alcohol rocket engine.

XLR132.

  • Rocketdyne N2O4/MMH rocket engine. 16.7 kN. Out of Production. Isp=340s. Pump-fed high performance upper stage engine for perigee/apogee stages. as well as transfer vehicles and lunar and Martian missions. Tested extensively but no production.

XLR13-AJ-1.

XLR13-AJ-3.

XLR13-AJ-5.

  • Aerojet Nitric acid/Amine rocket engine. B-29 ATO. Launch thrust 17.6 kN. Development begun June 1948. Ceramic chamber and nozzle, nitrogen pressure-fed, droppable but no recoverable.

XLR13-AJ-7.

  • Aerojet Nitric acid/Amine rocket engine. Launch thrust 17.6 kN. Modification of -AJ-1. Regeneratively cooled by fuel, droppable.

XLR15-AJ-1.

  • Government designation of XCNLT-1500 Isopropylnitrate rocket engine.

XLR16-AJ-1.

  • Government designation of LR16 rocket engine.

XLR17-CW-1.

  • Government designation of LR17 Lox-Gasoline rocket engine.

XLR19-CW-1.

  • Government designation of LR19 Lox-Gasoline rocket engine.

XLR1-AJ-1.

  • Government designation of 25AL-1000 Nitric acid-Amine rocket engine.

XLR20-AJ-2.

  • Government designation of XLR20AJ-2 Nitric acid-Gasoline rocket engine.

XLR20AJ-2.

  • Aerojet Nitric acid/Gasoline rocket engine. Lark. Launch thrust 6.66 kN. Development begun January 1946. Blast turbine, three levels of thrust (600/1000/7500 lbf). Replaced NM Lark.

XLR21-CW-1.

  • Government designation of LR21 Lox-Gasoline rocket engine.

XLR22-RM-1.

  • Government designation of LR22 rocket engine.

XLR23-AJ-1.

  • Government designation of X90ALT-60000 Nitric acid-Amine rocket engine.

XLR24-AJ-2.

  • Government designation of XLR24AJ-2 Nitric acid-Gasoline rocket engine.

XLR24AJ-2.

  • Aerojet Nitric acid/Gasoline rocket engine. Lark. Launch thrust 10.7 kN. Development begun January 1946. Blast turbine, 2500 Ibf fixed thrust (both were part of overall R&D contract)

XLR25-CW-1.

  • Curtiss-Wright Lox/Alcohol rocket engine. 66.880 kN. Out of Production. First flight 1954. Two chamber engine built for X-2 rocketplane. Engine could be throttled continuously from 1140 kgf to 6820 kgf.

XLR26-RM-1.

  • Government designation of LR26 rocket engine.

XLR27-CW-1.

  • Government designation of LR27 rocket engine.

XLR29-CW-1.

  • Government designation of LR29 rocket engine.

XLR2-RM-1.

  • Government designation of LR2 rocket engine.

XLR30-RM-2.

  • Government designation of LR30 Lox-Ammonia rocket engine.

XLR31-K-1.

  • Government designation of LR31 rocket engine.

XLR32-RM-1.

  • Government designation of LR32 rocket engine.

XLR33-RM-1.

  • Government designation of LR33 rocket engine.

XLR35-RM-1.

  • Government designation of LR35 rocket engine.

XLR37-CW-1.

  • Government designation of LR37 Lox-Gasoline rocket engine.

XLR39-RM-1.

  • Government designation of LR39 Lox-Alcohol rocket engine.

XLR3-AJ-1.

  • Government designation of 25XALD-1000 Nitric acid-Amine rocket engine.

XLR40-RM-1.

  • Government designation of LR40 H2O2-Kerosene rocket engine.

XLR41-NA-1.

  • Government designation of LR41 rocket engine.

XLR42-NA-1.

  • Government designation of LR42 rocket engine.

XLR43-NA-1.

  • Rocketdyne Lox/Alcohol rocket engine. 333 kN. Development completed 1951. Mark III American version of single-chamber V-2 engine tested in WW2, but with half mass and 34% more thrust. Starting point for all later Rocketdyne engines.

XLR48-RM-1.

  • Government designation of LR48 rocket engine.

XLR49-AJ-1.

  • Government designation of LR49 rocket engine.

XLR51-AJ-1.

  • Government designation of LR51 rocket engine.

XLR53-AJ-1.

  • Government designation of XLR53AJ-1 Nitric acid-Amine rocket engine.

XLR53AJ-1.

  • Aerojet Nitric acid/Amine rocket engine. F-80. Out of Production. Launch thrust 4.41 kN. Development begun 1949. Superperformance, wing tip mounted, regenerative cooling, pressure fed, 240 sec duration, 1000 Ibf thrust each.

XLR54-NA-1.

  • Government designation of LR54 H2O2-Kerosene rocket engine.

XLR55-?-1.

  • Government designation of LR55 rocket engine.

XLR5-AJ-1.

  • Government designation of 40ALD-3000 Nitric acid-Amine rocket engine.

XLR65-B-1.

  • Government designation of LR65 rocket engine.

XLR6-RM-1.

  • Government designation of LR6 rocket engine.

XLR71-NA-1.

  • Rocketdyne Lox/Alcohol rocket engine. Development cancelled 1955. Launch thrust 533.7 kN. Planned engine for the booster of the Navaho II test vehicle. Gas generator, pump-fed.

XLR7-AJ-1.

  • Government designation of XCALT-6000 Nitric acid-Amine rocket engine.

XLR81-BA.

  • Government designation of Bell 8081 Nitric acid-UDMH rocket engine.

XLR81-BA-13.

  • Government designation of Bell 8247 Nitric acid-UDMH rocket engine.

XLR83-NA-1.

  • Rocketdyne Lox/Kerosene rocket engine. 602 kN. Out of production. Isp=273s. Experimental version of the engine for the booster of the Navaho G-38 intercontinental cruise missile. Flown in the Navaho G-26 booster prototypes. First flight 1956.

XLR89-1.

  • Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Atlas A, B, C. Out of production. Designed for booster applications. Gas generator, pump-fed. Shared turbopumps for booster engines. Isp=282s. First flight 1957.

XLR89-5.

  • Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Atlas D. Designed for booster applications. Gas generator, pump-fed. Shared turbopumps for booster engines. Isp=282s. First flight 1958.

XLR99.

  • Thiokol Lox/Ammonia rocket engine. 262.4 kN. Out of production. Isp=276s. The first large, man-rated, throttleable, restartable liquid propellant rocket engine, boosted the X-15A. First flight 1959.

XLR9-AJ-1.

  • Government designation of X4-AL-1000 Nitric acid-Amine rocket engine.

XM-42.

  • Hercules solid rocket engine. 772 kN.

XM-45.

  • Rocket solid engine. 200 kN.

XM-51.

  • American turbojet engine.

XR2P1.

  • XCOR Nitrous oxide/Alcohol rocket engine. 0.067 kN. First stages. Hardware. Engine was run on oxygen and nitrous oxide oxidizers, with propane, ethane, kerosene, turpentine, and a variety of alcohols.

XR3A2.

  • XCOR Lox/Alcohol rocket engine. 0.700 kN. First stages. Hardware. The XR3A2 700-newton engine was the first XCOR LOX/alcohol engine, accumulating 61 brief runs in the course of injector concept development, which led to later engines.

XR3B4.

  • XCOR Nitrous oxide/Alcohol rocket engine. 0.220 kN. First stages. Hardware. Regeneratively cooled engine using nitrous oxide and isopropyl alcohol as propellants.

XR3M9.

  • XCOR Lox/CH4 rocket engine. 0.223 kN. First stages. Hardware. Methane-fueled engine allowing long-term on-orbit storage, higher density than hydrogen engines. Intended for use in reaction control systems and satellite maneuvering systems

XR4A3.

  • XCOR Lox/Alcohol rocket engine. 1.780 kN. First stages. Fully operational pressure-fed, regeneratively cooled engine. Flown on the EZ-Rocket, a modified Long-EZ aircraft fitted with two engines. First flight 2001.

XR4K14.

  • XCOR Lox/Kerosene rocket engine. 6.670 kN. First stages. Hardware. Built for the Rocket Racing League's first X-Racer. The rocket engine was sized for the best compromise between acceleration and endurance.

XR4K5.

  • XCOR Lox/Kerosene rocket engine. 8 kN. First stages. Hardware. Pump-fed, regeneratively cooled with fuel. Engine could be used to power the prototype Xerus suborbital manned vehicle for initial flight testing.

XR5M12.

  • XCOR Lox/CH4 rocket engine. 22.3 kN. First stages. Conceptual lox/methane rocket engine developed for a DARPA program through layout design phase, but never built.

XR5M15.

  • XCOR Lox/CH4 rocket engine. 33.360 kN. First stages. Hardware. Prototype LOX/methane rocket engine developed as a stepping stone to NASA's original Orion manned spacecraft and return to the moon and manned mission to Mars plans.

XRJ47-W-5.

  • Wright ramjet engine. 33.4 kN. Out of production. Thrust is maximum thrust at cruise altitude. Specific impulse is that at cruise design point. Isp=1200s. Used on Navaho G-26 launch vehicle. First flight 1956.

XRS-2200.

  • Rocketdyne lox/lh2 rocket engine. 1192 kN. Development ended 1999. Isp=439s. Linear aerospike engine for X-33 SSTO technology demonstrator. Based on J-2S engine developed for improved Saturn launch vehicles in the 1960's.

YaERD-2200.

  • Korolev nuclear/lh2 rocket engine. 81 kN. Developed 1962-69.

YaRD OKB-456.

  • Glushko nuclear/ammonia rocket engine. 1373 kN. Development ended 1960. Isp=470s. Used nuclear reactor in cylindrical housing, operating at 3000 deg K. Propellant heated in the reactor and exhausted through four expansion nozzles

YaRD OKB-670.

  • Bondaryuk nuclear/ammonia+alcohol rocket engine. 1667 kN. Development ended 1960. Isp=470s. Proposed for YaRD nuclear-powered ICBM. Propellant was heated in the reactor and exhausted through four expansion nozzles.

YaRD Type A.

  • Korolev nuclear/lh2 rocket engine. 177 kN. Study 1963. Design considered in N1 nuclear upper stage studies. Outgrowth of work done by Bondaryuk and Glushko on YaRD engines for nuclear ICBM's, but using liquid hydrogen as propellant. Isp=900s.

YaRD Type AF.

  • Korolev nuclear/lh2 rocket engine. 196 kN. Study 1963. Design considered in N1 nuclear upper stage studies. Outgrowth of work done by Bondaryuk and Glushko on YaRD engines for nuclear ICBM's, but using liquid hydrogen as propellant. Isp=950s.

YaRD Type V.

  • Korolev nuclear/lh2 rocket engine. 392 kN. Study 1963. Design considered in N1 nuclear upper stage studies. Outgrowth of work done by Bondaryuk and Glushko on YaRD engines for nuclear ICBM's, but using liquid hydrogen as propellant. Isp=900s.

YaRD Type V-B.

  • Korolev nuclear/lh2 rocket engine. 392 kN. Study 1963. Isp=900s. Design considered in N1 nuclear upper stage studies. This version had 7,000 kg bioshield for manned missions. Used liquid hydrogen as propellant.

Yardbird.

  • Thiokol solid rocket engine. 75 kN.

YF-1.

  • CALT Nitric acid/kerosene rocket engine. 300 kN.

YF-120t.

  • CAALPT Lox/Kerosene rocket engine. 1340.2 kN. In development. Isp=336s. For CZ-5 Next Generation Launch Vehicle series. Engine can be throttled to 65% of rated thrust. Firing tests began in 2005.

YF-20A.

  • Beijing Wan Yuan N2O4/UDMH rocket engine. 750.2 kN. Out of production. Isp=289s. Boosted CZ-2A, CZ-2C, CZ-2E(A), CZ-3, FB-1. First flight 1972.

YF-20B.

  • Beijing Wan Yuan N2O4/UDMH rocket engine. 816.3 kN. In production. Isp=289s. Boosted CZ-2C, CZ-2D, CZ-2E, CZ-2E(A), CZ-3A, CZ-3B, CZ-3C, CZ-4A. First flight 1988.

YF-22.

  • Beijing Wan Yuan N2O4/UDMH rocket engine. 717.8 kN. In Production. Isp=295s.

YF-22/23.

  • Beijing Wan Yuan N2O4/UDMH rocket engine. 762 kN. Out of production. Cluster of YF-22 and 4 x YF-23 verniers. Isp=295s. Boosted CZ-2A, FB-1. First flight 1972.

YF-22A/23A.

  • Beijing Wan Yuan N2O4/UDMH rocket engine. 762 kN. Out of production. Cluster of YF-22A and 4 x YF-23 verniers. Isp=295s. Boosted CZ-2C, CZ-3. First flight 1975.

YF-22B.

  • SAST N2O4/UDMH rocket engine. 742 kN.

YF-23.

  • Beijing Wan Yuan N2O4/UDMH rocket engine. 11 kN. In Production. Used as vernier motor with YF-22 and YF-25. Isp=282s.

YF-25.

  • Beijing Wan Yuan N2O4/UDMH rocket engine. 787.4 kN. In Production. Isp=297s.

YF-25/23.

  • Beijing Wan Yuan N2O4/UDMH rocket engine. 831 kN. In production. Cluster of YF-25 and 4 x YF-23 verniers. Isp=295s. First stage engine for CZ-2D, CZ-2E, CZ-2E(A), CZ-3A, CZ-3B, CZ-3C, CZ-4A. First flight 1988.

YF-2A.

  • Beijing Wan Yuan Nitric acid/UDMH rocket engine. 306.1 kN. Out of production. Isp=268s. Used on CZ-1, CZ-1C, CZ-1D, CZ-1M. First flight 1969.

YF-3.

  • Beijing Wan Yuan N2O4/UDMH rocket engine. 294 kN. Out of production. Isp=287s. Used on CZ-1D launch vehicle. First flight 1995.

YF-40.

  • Beijing Wan Yuan N2O4/UDMH rocket engine. 49 kN. Out of production. Isp=295s. Used on CZ-4A launch vehicle. First flight 1988.

YF-50t.

  • CAALPT lox/lh2 rocket engine. 700 kN. In development. Isp=432s. New Lox/LH2 engine for next generation Chinese launch vehicles. It is an indigenous development based on Chinese experience with the YF-73 and YF-75 upper stage engines.

YF-73.

  • Beijing Wan Yuan lox/lh2 rocket engine. 11 kN. In development. Gas-generator turbopump. Gimballed engine. Isp=425s. Used on CZ-3 launch vehicle. First flight 1984.

YF-75.

  • Beijing Wan Yuan lox/lh2 rocket engine. 78.5 kN. In development. Gas-generator turbopump. Gimballed engine. Isp=440s. First flight 1994.

YLR113-AJ-1.

  • Government designation of AJ10-51 rocket engine.

YLR44-RM-1.

  • Government designation of LR44 rocket engine.

YLR45-AJ-1.

  • Aerojet Nitric acid/Kerosene rocket engine. B-47C ATO. Out of Production. Development begun August 1948. Turbojet engine bleed air drive for turbopump. Fixed internal acid tanks, regenerative cooling.

YLR45-AJ-3.

  • Government designation of YLR45AJ-3 Nitric acid-Kerosene rocket engine.

YLR45AJ-3.

  • Aerojet Nitric acid/Kerosene rocket engine. F-84 ATO. Out of Production. Development begun 1948. Bleed air drive, droppable acid tanks, ceramic chamber with oval throat, 60 second duration, reusable 50 times

YLR47-K-1.

  • Government designation of LR47 rocket engine.

YLR63-AJ-3.

  • Government designation of YLR63AJ-3 Nitric acid-UDMH rocket engine.

YLR63AJ-3.

  • Aerojet Nitric acid/UDMH rocket engine. F-86. Out of Production. Development begun 1953. Superperformance, modification of YLR45AJ-3 with gas generator turbine drive, 6 restarts.

YLR81-BA.

  • Government designation of Bell 8096 Nitric acid-UDMH rocket engine.

Zebra.

  • Alternate designation for Alcor Solid rocket engine.

Zefiro.

  • FiatAvio solid rocket engine. 590 kN.

Zefiro 23.

  • Fiat-Avio solid rocket engine. 1200 kN. In production. Isp=289s. Carbon epoxy filament wound case; low density EPDM insulation; HTPB 1912 composite propellant. Used on Vega launch vehicle.

Zefiro 9.

  • Fiat-Avio solid rocket engine. 313 kN. In production. Isp=294s. Motor derived from the 16-metric-ton Zefiro 16. Carbon epoxy filament wound case; low density EPDM insulation; HTPB 1912 composite propellant.

Zenit.

  • Oerlikon solid rocket engine. 45 kN.

Zeus A.

  • GCR solid rocket engine.

ZN-1.

  • NUDT Changsha solid rocket engine.

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