Category of engines.
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Associated Engines

11D23 Kosberg N2O4/UDMH rocket engine. 230.5 kN. Study 1968. Engine used in Block 1 and Block 11 stages of LK700 manned lunar lander. More...

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 LK700 manned spacecraft. More...

11D423 Izotov N2O4/UDMH rocket engine. 134 kN. LK700S manned lunar lander ascent stage engine. Development ended 1968. Isp=326s. Based UR100 stage 2 engine. Gas generator cycle; 2 large turbine exhaust pipes. More...

11D428 Melnikov N2O4/UDMH rocket engine. 0.110 kN. Yantar2K orbital propulsion. In Production. Orbital propulsion system of the Yantar2K military satellite, including one 11D430, four 11D431, four 11D446, and eight 11D428. Up to 40,000 ignitions. More...

11D43 Glushko N2O4/UDMH rocket engine. 1642 kN. Developed 196064. Isp=316s. Lowexpansion 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. More...

11D430 Melnikov N2O4/UDMH rocket engine. 29.430 kN. Yantar2K orbital propulsion. In Production. Orbital propulsion system of the Yantar2K military satellite, including one 11D430, four 11D431, four 11D446, and eight 11D428. Up to 50 ignitions. Isp=307s. Chamber Pressure: 9.00 bar. More...

11D431 Melnikov N2O4/UDMH rocket engine. 6 N. Yantar2K orbital propulsion. In Production. Orbital propulsion system of the Yantar2K military satellite, including one 11D430, four 11D431, four 11D446, and eight 11D428. Up to 150,000 ignitions. More...

11D445 Melnikov N2O4/UDMH rocket engine. 0.065 kN. Yantar2K descent propulsion. In Production. Propulsion system of the Yantar2K military satellite descent capsule. Up to 10,000 ignitions. Thrust from 0,065  0,012 kN. More...

11D446 Melnikov N2O4/UDMH rocket engine. 0.052 kN. Yantar2K orbital propulsion. In Production. Orbital propulsion system of the Yantar2K military satellite, including one 11D430, four 11D431, four 11D446, and eight 11D428. Up to 40,000 ignitions. More...

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 kgs. Minimum impulse 4 kgs. Specific impulse also reported as 275 sec. More...

11D49 Isayev Nitric acid/UDMH rocket engine. 157.5 kN. Kosmos3M stage 2. Engine has one main and four steering nozzles. Thrust 157.5 + 4 x 25 kN. Precessor was 11D47 in R14 (derivative ?) stage 2. Isp=303s. First flight 1964. More...

11D79 Stepanov N2O4/UDMH rocket engine. 44 kN. Blok D SOZ. In Production. Thrust 1.14.5 tf variable. More...

15D13 Klimov N2O4/UDMH rocket engine. 131.4 kN. Study 1968. Main engine for midcourse Block 1V ascent/transearth injection stage of LK700 manned spacecraft. See also 11D423. More...

17D58E Isayev N2O4/UDMH rocket engine.13 N. In Production. Isp=247s. Small attitude control thruster used in Briz, BrizM upper stage propulsion system S5.98M. More...

17D61 Melnikov N2O4/UDMH rocket engine. 2.943 kN. Ikar stage 4 for SoyuzIkar. 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. More...

21AL2600 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. More...

25AL1000 Aerojet Nitric acid/Amine rocket engine. A20 ATO. Launch thrust 4.41 kN. Development begun May 1942. Production version of GALCIT unit. First flight 1944. More...

25XALD1000 Aerojet Nitric acid/Amine rocket engine. JATO, Droppable for P38, B24, and B25J. Thrust 4.41 kN. Development begun May 1942. Droppable version of XLR1, packaged compactly with parachute. First flight 1944. More...

300LR200 Aerojet Nitric acid/Amine rocket engine. XP79 Launch thrust .882 kN. Development begun January 1943. Planned successor to XCALT6000, developed under 'Project X' for the Northrop XP79 Flying Wing rocket fighter. First flight 1945. More...

30AL1000 Aerojet Nitric acid/Amine rocket engine. GAPA. Launch thrust 4.41 kN. Development begun March 1947. Boeing surfacetoair missile, which would evolve into Bomarc and reach IOC in 1959. More...

38ALDW1500 Aerojet Nitric acid/Amine rocket engine. ATO Seaplanes. Launch thrust 6.66 kN. Development begun July 1943. Regeneratively cooled. Also a few 45ALDW1500 were built. Droppable version. First flight 1945. More...

40ALD3000 Aerojet Nitric acid/Amine rocket engine. B29 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. More...

40XAL4000 Aerojet Nitric acid/Amine rocket engine. PB2Y3 ATO. Launch thrust 17.6 kN. Development begun July 1943. Gasoline engine driven pumps. Also 40ALD6000 and 60ALD8000 versions First flight 1945. More...

45AL2600 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. More...

45LR35000 Aerojet Nitric acid/UDMH rocket engine. Bomarc. Out of Production. Launch thrust 159.583 kN. Development begun 1953. Pressurefed, uncooled, ceramiclined engine. First flight 1959. More...

4D10 Isayev N2O4/UDMH rocket engine. 255 kN. R27 / RSM25 (SSN6). 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. More...

8D423 Izotov N2O4/UDMH rocket engine. 131 kN. Production from 1964. Isp=325s. Single chamber engine for UR100 stage 2. Gas generator cycle with two large turbine exhaust pipes. First flight 1965. More...

8D43 Kosberg N2O4/UDMH rocket engine. 559 kN. UR500 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 RD0208 and RD0210. More...

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. More...

8D725 Glushko N2O4/UDMH rocket engine. 117 kN. Developed 19631970. 10 to 12 tonne thrust engine developed for an unstated military requirement. Isp=325s. More...

A612 Dushkin rocket engine. 39 kN. V600. Developed 195562. Thrust variable 1500  4000 kgf. More...

Aerojet 21 Aerojet N2O4/MMH rocket engine. 0.021 kN. In Production. Mixture Ratio(O/F): 1.60. Isp=285s. More...

Aerojet 62 Aerojet N2O4/MMH rocket engine. 0.062 kN. In Production. Mixture Ratio(O/F): 1.65. Isp=287s. More...

Aerojet 445 Aerojet N2O4/MMH rocket engine. 0.445 kN. In Production. Mixture Ratio(O/F): 1.65. Isp=309s. More...

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

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

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. More...

Aestus2 Rocketdyne / DASA N2O4/MMH rocket engine. 60 kN. Production. Restartable upperstage engine, began test firings at Lampoldshausen in February 2000. More...

AJ10196 Aerojet rocket engine. 40.1 kN. Liquid Throttling Engine. Liquid Throttling Engine More...

AJ10137 Aerojet N2O4/Aerozine50 rocket engine. 97.5 kN. Apollo SPS. Out of Production. Pressurefed engine. Used as Apollo SM engine. Isp=312s. More...

AJ1033 Aerojet Nitric acid/UDMH rocket engine. 509 kN. SMART Sled. Development begun early 1950s. 114,000 Ibf thrust, uncooled, ceramic lined, 3 chamber system More...

AJ10138 Aerojet N2O4/Aerozine50 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 19641980. More...

AJ1040 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. More...

AJ1051 Aerojet rocket engine. 666 kN. Sled. Thrust variable to 33% indicated. More...

AJ1028 Aerojet Nitric acid/JPX rocket engine. 156 kN. SNORT Sled. Development begun early 1950s. 35,000 Ibf thrust, 210 second duration. JPX was a jet fuel / hydrazine mixture. More...

AJ10118 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 19571962. More...

AJ10104 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 21/2 times First flight 1960. More...

AJ10131 Aerojet N2O4/Aerozine50 rocket engine. 9.8 kN. Subscale Apollo SPS. Subscale Apollo SPS More...

AJ10118D Aerojet Nitric acid/UDMH rocket engine. 33.7 kN. Isp=278s. Used on Delta B, Delta C, Delta D upper stages. First flight 1962. More...

AJ10118E 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. More...

AJ10118F Aerojet Nitric acid/UDMH rocket engine. 41.4 kN. Isp=306s. Used on Delta upper stage for Delta 0100, Delta 1000, N2 boosters. First flight 1972. More...

AJ10118G Aerojet Nitric acid/UDMH rocket engine. 43.414 kN. Delta G. Isp=314s. More...

AJ10118H Aerojet Nitric acid/UDMH rocket engine. 43.414 kN. Delta H. Isp=319s. More...

AJ10118K Aerojet N2O4/Aerozine50 rocket engine. 43.4 kN. Isp=321s. Pressurefed 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. More...

AJ10101 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. More...

AJ116 Aerojet Nitric acid/aniline rocket engine. 17.8 kN. Typical ideal dV=3839 m/s; gravity and drag losses = 1012 m/s. More...

AJ6091 Aerojet rocket engine. 72.324 kN. Aerobee 350. Aerobee motor. Four Chambers More...

AR1 Rocketdyne h2o2/kerosene rocket engine. 22.260 kN. Engine for FJ4F naval interceptor. More...

AR23 Rocketdyne h2o2/kerosene rocket engine. 29.341 kN. FutureX Demonstrator Engine. Gas generator, pumpfed. Heritage technology in evaluation for current applications. X37 Reusable Upper Stage Vehicle. Isp=245s. More...

Ares Aerojet N2O4/Aerozine50 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. More...

Astris German N2O4/Aerozine50 rocket engine. 23.3 kN. Isp=310s. Used on Europa launch vehicle. First flight 1964. More...

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

BA3200 Beal H2O2/Kerosene rocket engine. 14,100 kN. Development 1990's. Pressurefed engine with composite ablative chamber and nozzle. Helium pressurant. Thrust declines to 70% of initial value before shutdown. Isp=259s. More...

BA44 Beal H2O2/Kerosene rocket engine. 196 kN. Development 1990's. Pressurefed restartable engine with composite ablative chamber and nozzle. Helium pressurant. Thrust declines to 50% of initial value before shutdown. Isp=300s. More...

BA810 Beal H2O2/Kerosene rocket engine. 3600 kN. Development 1990's. Pressurefed engine with composite ablative chamber and nozzle. Helium pressurant. Thrust declines to 50% of initial value before shutdown. Isp=282s. More...

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. More...

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. More...

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. More...

Bell 8247 Bell Nitric acid/UDMH rocket engine. 71.2 kN. Out of Production. Isp=291s. Version of Agena engine for the GeminiAgena Target Vehicle. Minimum capability of five restarts and a demonstrated capability of fifteen restarts. First flight 1963. More...

Burlak Stage 1 Russian N2O4/UDMH rocket engine. 360 kN. Burlak stage 1. Development ended 1992. Isp=320s. Air launched from Tu160 at 13,500 m, Mach 1.7 release conditions. More...

Burlak Stage 2 N2O4/UDMH rocket engine. 98 kN. Burlak stage 2. Development ended 1992. Isp=330s. Air launched from Tu160 at 13,500 m, Mach 1.7 release conditions. More...

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. More...

Corporal Firestone Nitric acid/AnilineFurfuyrl alcohol rocket engine. 89 kN. More...

Corporal E Douglas/JPL Nitric acid/AnilineFurfuyrl alcohol rocket engine. 89 kN. More...

CZ1C3 Chinese N2O4/UDMH rocket engine. 107.9 kN. Development ended 1988. Isp=287s. Used on CZ1C launch vehicle. More...

DMT600 Isayev N2O4/UDMH rocket engine. 0.600 kN. In Production. Bipropellant hypergolic (selfigniting) engine, pressurefed. 6,000 ignitions Isp=300s. More...

DMT600 MMH Isayev N2O4/MMH rocket engine. 0.600 kN. Hermes. In Production. Version of DMT600 using MMH in place of UDMH, adaptation to western market (was discussed for European Hermes space plane project). 6,000 ignitions Isp=305s. More...

DST200 Isayev N2O4/UDMH rocket engine. 0.200 kN. In Production. Bipropellant hypergolic (selfigniting) engine, pressurefed. 10,000 ignitions Isp=280s. More...

DST200A Isayev N2O4/UDMH rocket engine. 0.20 kN. In Production. Bipropellant hypergolic engine, pressurefed. Larger nozzle and reduced chamber pressure to increase performance and lifetime compared to DST200. 100,0000 ignitions. Isp=300s. More...

DST100 Isayev N2O4/UDMH rocket engine. 0.100 kN. In Production. Bipropellant hypergolic (selfigniting) engine, pressurefed. 10,000 ignitions Isp=276s. More...

DST25 Isayev N2O4/UDMH rocket engine. 0.025 kN. In Production. Bipropellant hypergolic (selfigniting) engine, pressurefed. 300,000 ignitions Isp=285s. More...

DST100A Isayev N2O4/UDMH rocket engine. 0.100 kN. In Production. Bipropellant hypergolic engine, pressurefed. Larger nozzle and reduced chamber pressure to increase performance and lifetime in comparison to DST100. 450,0000 ignitions. Isp=304s. More...

Dual ModeLiquid 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 bipropellant torque motor valve. More...

ExpansionDeflection 10k Rocketdyne N2O4/Aerozine50 rocket engine. Launch thrust 44.463 kN. ExpansionDeflection Booster (10,000 lb thrust). Pressurefed. Thrust and specific impulse values are at sea level. More...

ExpansionDeflection 50k Rocketdyne N2O4/Aerozine50 rocket engine. Launch thrust 222.326 kN. ExpansionDeflection Booster (50,000 Ib thrust). Pressurefed. Thrust and specific impulse values are at sea level. More...

FY25 Beijing Wan Yuan rocket engine. In Production. Chinese liquid apogee insertion motor. 1800 seconds rated firing time. First flight 1994. More...

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. More...

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. More...

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 19631970. Largest thrust chamber ever tested in Russia was Glushko's RD270 of 680 tf. More...

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

Isayev V750V Isayev Nitric acid/Amine rocket engine. 30.4 kN. SAMmissile V750V. Out of Production. Designation unknown. More...

Isayev R17 Isayev Nitric acid/Kerosene rocket engine. 131.2 kN. R17. Out of production. Designation unknown. First flight 1961. More...

Isayev 218 Isayev Nitric acid/Amine rocket engine. 218 (S25 system). Out of Production. Launch thrust 166 kN. More...

Isayev P15 Isayev Nitric acid/Amine rocket engine. 11.9 kN. P15 Termit. Out of Production. Designation unknown. Thrust range 11.8955.43 kN. More...

JP5/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. More...

KDU414 Isayev Nitric acid/UDMH rocket engine. 1.961 kN. Molniya 1, Mars 1, Venera 1, Zond 23 maneuvering engine. Out of Production. Spacecraft maneuvering engine. Isp=272s. More...

KDU426 Isayev N2O4/UDMH rocket engine. 3.089 kN. SoyuzT orbital correction engine. In Production. Pressurefed engine. Used as long duration engine for correction orbits of satellites. Isp=292s. More...

KEW2 Rocketdyne N2O4/MMH rocket engine. 0.215 kN. Kinetic Energy Propulsion (50 Ib thrust). Pressurefed. ASAT Strapdown test, XSS / DICE Microsatellite, GBI GroundBased Interceptor, THAAD Theater High Altitude Area Defense. Isp=275s. More...

KEW3 Rocketdyne N2O4/MMH rocket engine. 0.441 kN. Kinetic Energy Propulsion (100 Ib thrust). Pressurefed. ASAT Strapdown test, XSS / DICE Microsatellite, GBI GroundBased Interceptor, THAAD Theater High Altitude Area Defense. Isp=283s. More...

KEW1 Rocketdyne N2O4/MMH rocket engine. 0.029 kN. Kinetic Energy Propulsion (7 Ib thrust). Pressurefed. ASAT Strapdown test, XSS / DICE Microsatellite, GBI GroundBased Interceptor, THAAD Theater High Altitude Area Defense. Isp=266s. More...

KEW4 Rocketdyne N2O4/MMH rocket engine. 2.216 kN. Kinetic Energy Propulsion (500 Ib thrust). Pressurefed. ASAT Strapdown test, XSS / DICE Microsatellite, GBI GroundBased Interceptor, THAAD Theater High Altitude Area Defense. Isp=235s. More...

KRD442 Isayev N2O4/UDMH rocket engine. 4.38 / 0.17 kN. Orbital propulsion for FGBderived modules for Mir and ISS. In Production. Main and lowthrust mode. Operation of turbopump without chamber used to pump propellants into tanks from Progress tankers. More...

KRD61 Isayev N2O4/UDMH rocket engine. 18.8 kN. Luna Ye8. Out of Production. Spacecraft maneuvering engine for ascent stage of Luna moon sample return missions. Isp=313s. First flight 1969. More...

KRD79 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 KDU426. Pressure fed engine. More...

KRR300 Dushkin rocket engine. 98 kN. G300. Developed 195562. Thrust variable 0.1 / 3.0 / 10 tf. More...

KTDU417B Isayev N2O4/UDMH rocket engine. 3.430 kN. Luna 1524 used this low thrust engine in system KTDU417 for softlanding on the moon. Out of Production. Isp=254s. Pressurefed engine; could be throttled to 2.06 kN. More...

KTDU53 Isayev Nitric acid/UDMH rocket engine. 4.089 kN. Zond 47 maneuvering engine. Out of Production. Spacecraft maneuvering engine, derivative of KTDU35 without backup engine. Isp=280s. More...

KTDU80 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. More...

KTDU66 Isayev Nitric acid/UDMH rocket engine. 4.090 kN. Out of Production. Isp=280s. Maneuvering engine for Salyut 1, derivative of KTDU35. Longer burn time of 1000 s. Comprised singlechamber main engine plus dualchamber backup engine. Thrusts 4.09 + 4.03 kN More...

KTDU5A Isayev Nitric acid/Amine rocket engine. 45.5 kN. Used on Luna E6 probes. Out of Production. Isp=287s. First turbopump engine with surface tension propellant management devices in tanks, allowing reignition in zeroG. More...

KTDU425 Isayev N2O4/UDMH rocket engine. 18.850 kN. Mars 2 and 3 maneuver engine. Out of Production. Pumpfed engine. Could be throttled to 7.05 kN / 9.5 MPa / 2850 m/s. . Chamber pressure 133,2  95 bar. Isp=312s. More...

KTDU35 Isayev Nitric acid/UDMH rocket engine. 4.09 kN. Out of Production. Isp=280s. Soyuz, Salyut 4 maneuvering engine. KTDU53 version in L1 circumlunar spacecraft; KTDU66 in Salyut 1 space station. Thrusts 4.09 kN main + 4.03 kN secondary. First flight 1966. More...

KTDU417 Isayev Nitric acid/UDMH rocket engine. 18.920 kN. Luna 1524 descent stage. Out of Production. Isp=314s. Comprised turbopumpfed highthrust engine with plus KTDU417B lowthrust engine. Eleven ignitions for lunar orbit insertion and orbit corrections. More...

KTDU425A Isayev N2O4/UDMH rocket engine. 18.890 kN. Mars 47, Venera 916, Vega 12, and Phobos 12 maneuvering engine. Out of Production. Could be throttled to 9.86/9.5/2870. Chamber pressure 149  95 bar. Isp=315s. First flight 1973. More...

L7 MBB N2O4/MMH rocket engine. 27.4 kN. In Production. Isp=320s. Used on Ariane 5 launch vehicle. First flight 1996. More...

LE3 Rocketdyne N2O4/Aerozine50 rocket engine. 53.340 kN. MHI(Japan)/Rocketdyne Upper Stage. Pressurefed. Isp=285s. More...

Liberty2 Notional N2O4/MMH rocket engine. 17.8 kN. Development ended 1988. Pressurefed engine. Isp=300s. Used on Liberty launch vehicle. More...

LR101NA7 Rocketdyne N2O4/MMH rocket engine. 5.148 kN. Upper Stage Target Engine Systems. Pressurefed. Derived from Atlas vernier. Isp=251s. More...

LR40 Reaction Motors H2O2/Kerosene rocket engine. 35.690 kN. F8U1 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. More...

LR54 Rocketdyne H2O2/Kerosene rocket engine. 26.4 kN. After the failure of the Reaction Motors XLR40 for use in the F8U1 fighter, Vought elected to continue the project using the XLR54 . Project never reached flight status More...

LR65 Bell rocket engine for the X9 Shrike, an experimental prototype of the Rascal airtoground missile. More...

LR67 Bell rocket engine. Rascal GAM63. 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. More...

LR875 Aerojet N2O4/Aerozine50 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 19741982. More...

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 inspace starts after a period of coasting). More...

LR877 Aerojet N2O4/Aerozine50 rocket engine. 1086.1 kN. Study 1961. Version of LR875 used on Gemini Titan 2 launch vehicle. Isp=296s. Proposed for unflown Titan 3L2, Titan 3L4 boosters. First flight 1962. More...

LR879 Aerojet N2O4/Aerozine50 rocket engine. Launch thrust 956.1 kN. Variant of LR87 used on early versions of Titan III B,C First flight 1966. More...

LR87+ Aerojet N2O4/Aerozine50 rocket engine. 1634.4 kN. Study 1965. Nominal improved LR87 in booster studies. Isp=293s. Used on Martin Astrorocket launch vehicle. More...

LR8711 Aerojet N2O4/Aerozine50 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. More...

LR8711 AJ23138 Aerojet N2O4/Aerozine50 rocket engine. Launch thrust 1008.31 kN. Version of LR8711 tuned for launch pad ignition when used on Titan 3B. First flight 1966. More...

LR9111 Aerojet N2O4/Aerozine50 rocket engine. 467 kN. Out of production. Isp=316s. Second stage engine for Titan 3 and 4. First flight 1968. More...

LR915 Aerojet N2O4/Aerozine50 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. More...

LR917 Aerojet N2O4/Aerozine50 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. More...

LR919 Aerojet N2O4/Aerozine50 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. More...

MR120 Redmond Hydrazine rocket engine. 0.090 kN. Small ICBM. In Production. Developed as an attitude control thruster for the small ICBM. Isp=229s. More...

MR509 Redmond Hydrazine rocket engine. 254 mN. In Production. Lowpower arcjet system. Input power 1800 W at 65 V DC. Isp=502s. More...

MR510 Redmond Hydrazine rocket engine. 254 mN. In Production. Arcjet system. Isp=600s. More...

MR512 Redmond Hydrazine rocket engine. 254 mN. In Production. Lowvoltage bus arcjet system. Input power 1780 W at 35 V DC. Isp=502s. More...

MR501B Redmond Hydrazine rocket engine. 369 mN. BSAT2 communications satellite. In Production. Electrothermal hydrazine thruster (EHT). 493 W input power at 24 V DC. Isp=303s. More...

MRM122 Redmond Hydrazine rocket engine. 0.142 kN. In Production. Steadystate thrust 51 N. Isp=228s. More...

MRM103 Redmond Hydrazine rocket engine. 0.22 N. In Production. Steadystate thrust 0.22 N. Isp=224s. More...

MRM106 Redmond Hydrazine rocket engine. 0.027 kN. In Production. Steadystate thrust 9 N. Isp=231s. More...

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. More...

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. More...

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. More...

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 reentry initiation. First flight 1981. More...

Otrag Otrag N2O4/Kerosene rocket engine. 27.5 kN. First and upper stages of lowcost booster. Out of production. Isp=297s. Pressurefed, using cheapest possible propellants. Injection pressure: 4015 bar; thrust control: 10040 %. First flight 1977. More...

P7 Rocketdyne N2O4/Aerozine50 rocket engine. Launch thrust 222.31 kN. Aspen Booster. Pressurefed. Thrust from 12,000 lb to 50,000 lb at sea level. More...

P8E9 Rocketdyne Nitric acid/UDMH rocket engine. Lance. Launch thrust 205.44 kN. Lance Booster and Sustainer System. Pressurefed. Sustainer 4400 14,400 lbf, 227 sec Isp. Thrust and specific impulse values are at sea level. First flight 1972. More...

PF N204/Alumizine1925k Notional N2O4/Alumizine rocket engine. 18,873 kN. Study 1967. Isp=280s. Used on Saturn LCBAlumizine250 launch vehicle. More...

PF N204/Alumizine2300k Notional N2O4/Alumizine rocket engine. 22,562 kN. Study 1967. Isp=280s. Used on Saturn LCBAlumizine140 launch vehicle. More...

PF N204/UDMH2165k Notional N2O4/UDMH rocket engine. 21,232 kN. Study 1967. Isp=267s. Used on Saturn LCBStorable250 launch vehicle. More...

PF N204/UDMH2912k Notional N2O4/UDMH rocket engine. 28,552 kN. Study 1967. Isp=267s. Used on Saturn LCBStorable140 launch vehicle. More...

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. More...

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. More...

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

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. More...

PSLV4 ISRO N2O4/MMH rocket engine. 7 kN. Isp=308s. Used on PSLV launch vehicle. First flight 1993. More...

R101B.360000 Isayev Nitric acid/Amine rocket engine. R101B/R108 SAM. Developed 195051. Launch thrust 83.3 kN. Single chamber engine designed for use in the R101B and R108 (derivative of German Wasserfall). More...

R1E 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 R40 thrusters. More...

R200 Dushkin rocket engine. 9.8 kN. Out of Production. Thrust variable 0.8 tf 1.0 tf. More...

R40A 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. More...

R40B Redmond N2O4/MMH rocket engine. 4 kN. In Production. Isp=293s. More...

R42 Redmond N2O4/MMH rocket engine. 0.890 kN. In Production. Isp=303s. More...

R4D 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. More...

R56 Blok A Notional Nitric acid/Kerosene rocket engine. 4412 kN. R56 Blok A. Notional engines for polyblock R56, immense booster/ICBM; planned range 16,000 km. payload 35,000 kg. Tsniimash has 1:10 structural simulation model. Isp=320s. More...

R56 Blok B Notional Nitric acid/Kerosene rocket engine. 784 kN. R56 Blok B. Notional engines for polyblock R56, immense booster/ICBM; planned range 16,000 km. payload 35,000 kg. Tsniimash has 1:10 structural simulation model. Isp=330s. More...

R6C 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 HS393 satellites. More...

R6117 Chelomei N2O4/UDMH rocket engine. 132 kN. LK1 Blok A. Developed 196466. Developed in cooperation with OKB117 on the basis of the latter's main engine for the UR100 stage II. More...

RD0245 Kosberg N2O4/UDMH rocket engine. 211 kN. R29RM / RSM54 (SSN23) stage 1 vernier. Out of Production. Fourchamber steering engine in system RD0243 driven by turbine exhaust gas. Isp=300s. First flight 1985. More...

RD0231 Kosberg N2O4/UDMH rocket engine. 29 kN. P700 Granit. Out of Production. Staged combustion cycle. Isp=275s. First flight 1970. More...

RD0232 Kosberg N2O4/UDMH rocket engine. UR100N / Rokot Stage 1. Engine unit (DU  dvigatelnaya ustanovka) consisting of 1 RD0234 for tank pressurization and three RD0233. First flight 1972. More...

RD0233 Kosberg N2O4/UDMH rocket engine. 520 kN. UR100N / RS18 (SS19) stage 1. Out of Production. Staged combustion cycle. Isp=310s. First flight 1974. More...

RD0234 Kosberg N2O4/UDMH rocket engine. 520 kN. UR100N / RS18 (SS19) stage 1. Out of Production. Staged combustion cycle. Modification of RD0233 including tank pressurization system. Isp=310s. First flight 1974. More...

RD0235 Kosberg N2O4/UDMH rocket engine. 240 kN. UR100N / RS18 (SS19) stage 2. Main engine based on RD0217 with larger nozzle for altitude operation. Staged combustion cycle. Isp=320s. First flight 1972. More...

RD0236 Kosberg N2O4/UDMH rocket engine. 15.760 kN. UR100N / RS18 (SS19) stage 2 vernier. Out of Production. Developed in 19691974 / problems not solved until 1978. Vernier engines. Gas generator cycle. Isp=293s. More...

RD0237 Kosberg N2O4/UDMH rocket engine. 4.9 kN. UR100N / RS18 (SS19) stage 3. MIRV service block. Open cycle. Analogous to RD0225, pressure fed. Steering engine for space vehicles gimbaling +/ 45 degree. Isp=200s. First flight 1972. More...

RD0242 Kosberg N2O4/UDMH rocket engine. 123.6 kN. seabased missile booster stage developed 197783. Isp=302s. First concept planned N2O4/kerosene as propellant, but changed to N2O4/UDMH. Single ignition, 297 development tests. 50 engines for sale. More...

RD0242M Kosberg N2O4/MMH rocket engine. 98.1 kN. Design concept 1998. Isp=335s. Proposed variant of RD0242 engine for upper stages using MMH in place of UDMH. Reusable for 6 ignitions total. Throttling to 80%. More...

RD0242M1 Kosberg N2O4/MMH rocket engine. 98.1 kN. Design concept 1998. Proposed variant of RD0242 engine for upper stages using MMH in place of UDMH (adaptation to western market ?). Reusable for 6 ignitions total. Throttling to 80%. Isp=343s. More...

RD0244 Kosberg N2O4/UDMH rocket engine. 682 kN. R29RM / RSM54 (SSN23) stage 1. Out of Production. Main engine in system RD0243. Staged combustion cycle. Submerged in propellant tank. Isp=310s. First flight 1985. More...

RD0246 Kosberg N2O4/UDMH rocket engine. Design concept. Project for further development of RD0243. More...

RD0250 Kosberg N2O4/UDMH rocket engine. Further development of RD0235 main engine for projected modification of stage 2 of classified Chelomei rocket. Development ceased during study phase. Staged combustion cycle. More...

RD0251 Kosberg N2O4/UDMH rocket engine. Further development of RD0236 steering engine for projected modification of stage 2 of classified Chelomei rocket. Development ceased during study phase. Gas generator cycle. More...

RD0255 Kosberg N2O4/UDMH rocket engine. 755 kN. R36M2 / RS20V (SS18 Mod4) stage 2. Comprises of singlechamber main engine RD0256 plus fourchamber steering engines RD0257. Development based on RD0228 with thrust increase by 11%. First flight 1986. More...

RD0256 Kosberg N2O4/UDMH rocket engine. R36M2 / RS20V (SS18 Mod4) stage 2. Out of Production. Main engine of system RD0255. Staged combustion cycle. First flight 1987. More...

RD0257 Kosberg N2O4/UDMH rocket engine. R36M2 / RS20V (SS18 Mod4) stage 2 vernier. Out of Production. Steering engine of system RD0255. Gas generator cycle. First flight 1987. More...

RD0230 Kosberg N2O4/UDMH rocket engine. R36M / RS20A (SS18 mod1) stage 2 vernier. Out of Production. Vernier engine. Gas generator cycle. First flight 1974. More...

RD0225 Kosberg N2O4/UDMH rocket engine. 3.923 kN. Almaz space station orbital maneuvering. Hardware. Originally designed for UR100 followons spaceships. Two engines used on Almaz space station for orbital maneuvering, Pressure fed. Isp=287s. First flight 1974. More...

RD0243 Kosberg N2O4/UDMH rocket engine. 825.8 kN. R29RM stage 1. Out of Production. Isp=300s. Consisted pf singlechamber main engine RD0244 plus fourchamber steering engines RD0245 driven by turbine exhaust gas. Engine submerged in propellant tank. More...

RD0211 Kosberg N2O4/UDMH rocket engine. 582.1 kN. Proton stage 2. Out of Production. Variant of RD0210 providing tank pressurization. Staged combustion cycle. Isp=326s. More...

RD0201 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. More...

RD0202 Kosberg N2O4/UDMH rocket engine. 2236 kN. UR200 stage 1. Engine unit (DU  dvigatelnaya ustanovka) consisting of 1 RD0204 for tank pressurization and three RD0203. Isp=311s. First flight 1963. More...

RD0203 Kosberg N2O4/UDMH rocket engine. 559 kN. UR200 stage 1. Hardware. DU consisting of 4 RD0204 gimballed motors. Staged combustion cycle. Isp=311s. First flight 1964. More...

RD0204 Kosberg N2O4/UDMH rocket engine. 559 kN. UR200 stage 1. Hardware. Diameter is per chamber. Staged combustion cycle. Variant of RD0203 with additional pressure sensor. Isp=311s. First flight 1964. More...

RD0205 Kosberg N2O4/UDMH rocket engine. 606.4 kN. UR200 stage 2. Engine unit consisting of 1 RD0206 maine engine and 4 RD0207 vernier/steering engines. Version of 8D44 and 8D45 with extended nozzle. Developed 1961. Isp=322s. First flight 1963. More...

RD0206 Kosberg N2O4/UDMH rocket engine. 575.5 kN. UR200 stage 2. Developed 196164. Staged combustion cycle. Isp=326s. First flight 1964. More...

RD0207 Kosberg N2O4/UDMH rocket engine. 30.9 kN. UR200 stage 2 vernier. Developed 196164. Gas generator cycle. Four vernier thrusters. Isp=297s. First flight 1964. More...

RD0208 Kosberg N2O4/UDMH rocket engine. UR200 stage 1. Developed 196165. Stage 1 had three RD0208 plus one RD0209. Further developed into RD0210. More...

RD0229 Kosberg N2O4/UDMH rocket engine. R36M / RS20A (SS18 mod1) stage 2. Out of Production. Main engine. Staged combustion cycle. Used on Ikar launch vehicle. First flight 1974. More...

RD0210 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/RD0211) and three (8D411K/RD0210). Staged combustion cycle. First flight 1965. More...

RD0212 Kosberg N2O4/UDMH rocket engine. 613 kN. Proton stage 3. Engine unit consisting of 1 RD0213 maine engine and 4 RD0214 vernier/steering engines. 8D48 essentially similar to 8D411 and 8D412 and has the same combustion chamber. Isp=324s. First flight 1967. More...

RD0213 Kosberg N2O4/UDMH rocket engine. 582.1 kN. Proton stage 3. Design 1962. Version of RD0210. Staged combustion cycle (Oxidizer preburner gas routed to main chamber after driving turbine). Main engine for Proton Stage 3 in system RD0212. Isp=326s. More...

RD0214 Kosberg N2O4/UDMH rocket engine. 30.980 kN. Proton stage 3 vernier. In Production. Based on RD0207. Four used as steering engines for Proton Stage 3 in system RD0212. Isp=293s. First flight 1967. More...

RD0215 Kosberg N2O4/UDMH rocket engine. 2450 kN. Developed 196265 for heavy Chelomei launcher (UR900?) stage 1. Isp=310s. Engine unit consisting of 1 RD0217 for tank pressurization and three RD0216. Hardware not hottested. More...

RD0216 Kosberg N2O4/UDMH rocket engine. 219 kN. UR100 stage 1. Isp=313s. Staged combustion cycle. Includes tank pressurization system (RD0217 without tank press.). First launch November 1963, manufactured until 1974, operational until 1991. First flight 1965. More...

RD0217 Kosberg N2O4/UDMH rocket engine. 219 kN. UR100, UR100K stage 1. Out of Production. Staged combustion cycle. Version of RD0216 without tank pressurization system. Manufacturing until 1974, operational use until 1991. Isp=313s. More...

RD0221 Kosberg N2O4/UDMH rocket engine. 78 kN. upper stage of unnamed missile by Mishin. Developed 196570. Isp=330s. More...

RD0200 Kosberg Nitric acid/Amine rocket engine. 58.8 kN. Lavochkin SAM, flew 1960. Out of Production. First liquid rocket engine by OKB154, evolution of Isayev S2.1200 transferred to Kosberg. Thrust range 59  5.9 kN. Sea level specific impulse 230  166 sec More...

RD0228 Kosberg N2O4/UDMH rocket engine. 755 kN. R36M / RS20A (SS18 mod1) stage 2. Out of Production. Comprises singlechamber main engine RD0229 plus fourchamber steering engine RD0230. Further developed to RD0255. More...

RD0209 Kosberg N2O4/UDMH rocket engine. UR200 stage 1. Developed 196165. Engine unit consisting of 1 RD0211 for tank pressurization and three RD0210. Modification of RD0208 with tank pressurization. Further developed into RD0211. First flight 1965. More...

RD1 Glushko Nitric acid/Kerosene rocket engine. 2.940 kN. Takeoff acelleration of Pe2, La7, Yak3, Su6 airplanes. Developed 194145. First Russian liquid propellant rocket engine. Production 194445. Ignition was by an ethaneair mixture. Isp=200s. More...

RD1KhZ Glushko Nitric acid/Kerosene rocket engine. 2.940 kN. takeoff acelleration of Pe2R, La7R, Yak3, Su6, Su7, La120R airplanes. Developed 194146. The RD1KhZ was a variant of the RD1 engine with chemical ignition. Production 194445. Isp=200s. More...

RD215 Glushko Nitric acid/UDMH rocket engine. 864 kN. R14, Kosmos 11K63 stage 1. Out of Production. Original intended use unknown. Two RD215 clustered to make RD216. Isp=291s. First flight 1966. More...

RD253 Glushko N2O4/UDMH rocket engine. 1745 kN. In Production. Version of RD253 with thrust increased by 7%. Included an additional gas generator for tank pressurization. First flight 1986. More...

RD25311D48 Glushko N2O4/UDMH rocket engine. 1635 kN. Isp=316s. Six gimballed single chamber RD253s provide the first stage power for the UR500 Proton launch vehicle. First flown in 1965. More...

RD25314D14 Glushko N2O4/UDMH rocket engine. 1746 kN. Proton KM1. In production. Developed in 1990s. Isp=317s. First flight 1999. More...

RD253UR700 Glushko N2O4/UDMH rocket engine. 1745 kN. Designed 19641968. UR700 Stage 3. Development of RD253 with increased expansion ratio for upper stage use. More...

RD254 Glushko N2O4/UDMH rocket engine. 1716 kN. N1 upper stage, UR700 stage 3. Study 1961. Proposed for use in N1. High altitude version of RD253 for 2nd stages. First flight 1974. More...

RD261 Glushko N2O4/UDMH rocket engine. 3032 kN. Tsyklon 3 stage 1. In production. Based on RD251 Isp=301s. First flight 1977. More...

RD262 Glushko N2O4/UDMH rocket engine. 941 kN. Tsyklon 3 stage 2. In production. Based on RD252 Isp=317s. First flight 1977. More...

RD263 Glushko N2O4/UDMH rocket engine. 1155 kN. R36M / RS20A (SS18 Mod 1) stage 1. Out of Production. Four RD263 engines combined into RD264 system. Isp=318s. More...

RD2MZVF Dushkin Nitric acid/Kerosene rocket engine. 19.6 kN. Samolet 5. Developed 1946. More...

RD264 Glushko N2O4/UDMH rocket engine. 4521 kN. R36M / RS20A (SS18 Mod 1) stage 1. Consists of four RD263 engines. Isp=318s. Used on Dnepr launch vehicle. First flight 1986. More...

RD268 Glushko N2O4/UDMH rocket engine. 1236 kN. MRUR100 / RS16 (SS17) stage 1. Out of Production. First flight 1976. Modification of RD263 engine. Isp=319s. First flight 1990. More...

RD270 Glushko N2O4/UDMH rocket engine. 6713 kN. UR700, R56 stage 1. Development ended 1968. Isp=322s. Developed 19621971, largest rocket engine ever built in the Soviet Union, answer to F1. Tested but cancelled before combustion instability problems solved. More...

RD273 Glushko N2O4/UDMH rocket engine. 1238 kN. Developed 197582. Upgrade of RD263 in 1982 based on RD263F project. More...

RD274 Glushko N2O4/UDMH rocket engine. 4952 kN. Developed 197585. Upgrade of RD264 engine with increased chamber pressure and thrust. Development stopped due to problems with turbopump shaft balance. More...

RD275 Glushko N2O4/UDMH rocket engine. 1745 kN. Proton stage 1. In Production. Uprated version of RD253, developed in the 1980's. Isp=317s. First flight 1986. More...

RD280 Glushko N2O4/Aerozine50 rocket engine. 117.6 kN. Experimental engine. Study 1961. Experimental engine using Aerozine 50 (50% UDMH + 50% hydrazine) as fuel. Isp=350s. More...

RD293 Yuzhnoye rocket engine. Maneuvering vehicle axial maneuvering. More...

RD2MZV Dushkin Nitric acid/Kerosene rocket engine. 13.7 kN. I270. Developed 194447. Thrust variable 0.10.3 tf / 0.351.4 tf. More...

RD252 Glushko N2O4/UDMH rocket engine. 940.5 kN. R360 stage 2; Tsyklon 2 stage 2. In production. Used modified chamber from RD219, nozzle is conventional, so performance is higher. Isp=317s. First flight 1965. More...

RD263F Glushko N2O4/UDMH rocket engine. Developed 1980. Project to upgrade RD263. Upgrade was realized in RD273 engine. More...

RD200 Glushko Nitric acid/Kerosene rocket engine. 98.508 kN. vertical sounding rocket. Developed 1951. Isp=234s. More...

RD216M Glushko Nitric acid/UDMH rocket engine. Kosmos3M stage I. Out of Production. More...

RD251 Glushko N2O4/UDMH rocket engine. 2643 kN. R360 stage 1, Tsyklon 2 stage 1. In production. Assembly of 3 RD250type units. Isp=301s. First flight 1965. More...

RD2 Glushko Nitric acid/Kerosene rocket engine. 6 kN. experimental. Developed 194547. The RD2 was based on the RD1 engine. Used chemical ignition. Isp=200s. More...

RD210 Glushko Nitric acid/Kerosene rocket engine. 29.850 kN. vertical sounding rocket. Developed 1954. Isp=241s. More...

RD211 Glushko Nitric acid/Kerosene rocket engine. 642.3 kN. longdistance missile. Developed 195255. Original fourchamber engine design planned for use on the R12 IRBM. Abandoned due to limited thrust and the RD214 was developed in its place. Isp=261s. More...

RD212 Glushko Nitric acid/Kerosene rocket engine. 623 kN. Developed 195256. Isp=253s. Original fourchamber engine design planned for the booster stage of the Buran intercontinental ramjet missile. Abandoned due to limited thrust; RD213 was developed instead. More...

RD213 Glushko Nitric acid/Kerosene rocket engine. 755 kN. Winged rocket M40 (2). Development ended 1957. Two thrust levels. Ignition with propellant TG02. Chamber pressure 233,8 / 46,6 bar. Specific impulse 223 / 231 sea level. Isp=254s. More...

RD214 Glushko Nitric acid/Kerosene rocket engine. 730 kN. R12, Kosmos 11K63 stage 1. Isp=264s. Single turbopump driven by H2O2 gas generator feeding four fixed chambers. Ignition with propellant TG02. First flight 1957. More...

RD216 Glushko Nitric acid/UDMH rocket engine. 1728 kN. R14, Kosmos 11K65 stage 1. Isp=291s. RD216 was an assembly of 2 RD215's with 2 combustion chambers and 2 turbines. Two sets of these were in turn used in the first stage of the R14. First flight 1964. More...

RD218 Glushko Nitric acid/UDMH rocket engine. 2592 kN. R16 stage 1. Isp=289s. Consisted of three RD217; had 6 combustion chambers and 3 turbines; powered the R16 ICBM. First flight 1960. More...

RD250 Glushko N2O4/UDMH rocket engine. 881 kN. R360 stage 1, Tsyklon 2 stage 1. Out of Production. Assembly of 3 RD250 units make RD251. Isp=301s. More...

RD219 Glushko Nitric acid/UDMH rocket engine. 883 kN. R16 stage 2. Isp=293s. Derivative of RD217 with a truss and piping changes. Despite higher expansion ratio, engine was shorter than first stage version, with relatively low performance. Flown 19601972. More...

RD220 Glushko Nitric acid/UDMH rocket engine. 1074 kN. missile stage 1 (stage 2 used RD221). Developed 1960. Isp=306s. More...

RD221 Glushko Nitric acid/UDMH rocket engine. 1118 kN. missile stage 2 (stage 1 used RD220). Developed 1960. Isp=318s. More...

RD222 Glushko Nitric acid/UDMH rocket engine. 1634 kN. missile stage 1 (stage 2 used RD223). Developed 196061. Precursor to RD253. Isp=302s. More...

RD223 Glushko Nitric acid/UDMH rocket engine. 1697 kN. missile stage 2 (stage 1 used RD222). Developed 196061. Precursor to RD253. Isp=314s. More...

RD225 Glushko Nitric acid/UDMH rocket engine. 889 kN. R26 stage 1. Out of Production. Two clustered together to make RD224. Isp=294s. First flight 1961. More...

RD224 Glushko Nitric acid/UDMH rocket engine. 1778 kN. R26 stage 1. Out of production. RD224 is a block of 2 RD225s. An upper stage thrust chamber was developed under designation U102000. Isp=294s. First flight 1961. More...

RD217 Glushko Nitric acid/UDMH rocket engine. 865 kN. R16 stage 1. Out of Production. Original intended use unknown. Three RD217 clustered to make RD218. Isp=289s. First flight 1961. More...

RD3 Glushko Nitric acid/Kerosene rocket engine. 9 kN. experimental. Developed 1950's. The RD3 was a cluster of three RD1 engines with a new common turbopump. Ignition was by an ethaneair mixture. Isp=190s. More...

RD510T Glushko H2O2/CxHy rocket engine. Developed 196575. First flight 1975. More...

RD511 Glushko H2O2/CxHy rocket engine. Developed 196575. First flight 1975. More...

RD502 Glushko H2O2/Pentaborane rocket engine. 98.1 kN. Experimental upper stage engine. Developed 196066. Isp=380s. Experimental upper stage engine. Program stopped due to toxicity of propellants. Intended for Proton upper stage. First flight 1966. More...

RD510 Glushko H2O2/CxHy rocket engine. Developed 196575. First flight 1975. More...

RD68M Yuzhnoye N2O4/UDMH rocket engine. 285 kN. R36 stage 1 attitude control engine. Out of Production. 4 nozzles, maximum 42 degree gimbal angle. More...

RD69 Yuzhnoye Nitric acid/UDMH rocket engine. 49.2 kN. R16 stage 2 attitude control engine. Out of Production. More...

RD69M Yuzhnoye N2O4/UDMH rocket engine. 54.3 kN. R36 stage 2 attitude control engine. Out of Production. 4 nozzles, maximum 50 degree gimbal angle. More...

RD68 Yuzhnoye Nitric acid/UDMH rocket engine. 380 kN. R16 stage 1 attitude control engine. Out of Production. More...

RD866 Yuzhnoye N2O4/UDMH rocket engine. 5.2 kN. RT23 MIRVbus. 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. More...

RD861G Yuzhnoye, Fiat Avio N2O4/UDMH rocket engine. 76.453 kN. Vega upper stage. Developed 1996. Isp=325s. Proposed uprate of RD861 engine. Thrust vector control by gimbal, roll control by 4 nozzles (thrust 29 N each). More...

RD861K 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 RD861. More...

RD862 Yuzhnoye N2O4/UDMH rocket engine. 142.630 kN. MRUR100 / RS16 (SS17) stage 2. Out of Production. Based on RD857. Thrust vector control by secondary gas injection into nozzle. Roll control via special small jet nozzles. Isp=331s. More...

RD863 Yuzhnoye N2O4/UDMH rocket engine. 276.840 kN. MRUR100 / RS16 (SS17) stage 1 attitude control engine. Out of Production. Isp=301s. More...

RD869 Yuzhnoye N2O4/UDMH rocket engine. 8.580 kN. R36M2 vehicle bus. Based on RD864. 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. More...

RD853 Yuzhnoye Nitric acid/UDMH rocket engine. 467.6 kN. Stage 2, no application. Developed 196063. Designed for second stage, no application. Two thrust levels. Thrust 467.6 kN + 11.8 kN / 7.65 kN. Isp=300s. More...

RD868 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. More...

RD861 Yuzhnoye N2O4/UDMH rocket engine. 78.710 kN. Tsyklon 2 and 3 stage 3; Ikar. In production. Isp=317s. Based on RD854. Thrust vector control by 4 nozzles (thrust 98 N each) fed from a gas generator. First flight 1965. More...

RD864 Yuzhnoye N2O4/UDMH rocket engine. 20.2 kN. R36M 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. More...

RD859 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 RD858 engine failed. Restart within three seconds after shut down. Flight tests 1970. More...

RD858 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. More...

RD857 Yuzhnoye N2O4/UDMH rocket engine. 137.3 kN. RT20P 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. More...

RD856 Yuzhnoye N2O4/UDMH rocket engine. 54.230 kN. Tsyklon stage 2 attitude control engine. Out of Production. Isp=280s. Autonomous fourchamber pumpfed singlerun engine burned hypergolic propellants in a gas generator scheme. More...

RD854 Yuzhnoye N2O4/UDMH rocket engine. 75.5 kN. R36orb (SSX10) orbital stage. Out of Production. Thrust vector control by 4 nozzles fed from gas generator. Isp=312s. More...

RD852 Yuzhnoye Nitric acid/UDMH rocket engine. 48.250 kN. R16 (SS7) stage 2 attitude control engine. Out of Production. Four thrusters are each gimbaled in one single axis. Isp=255s. More...

RD851 Yuzhnoye Nitric acid/UDMH rocket engine. 32.480 kN. R16 (SS7) stage 1 attitude control engine . Out of Production. Four thrusters are each gimbaled in one single axis. Isp=279s. More...

RD860 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. More...

RD855 Yuzhnoye N2O4/UDMH rocket engine. 328 kN. Tsyklon stage 1 attitude control engine. Out of Production. Isp=292s. Fourchamber pumpfed singlerun engine burned hypergolic propellants in a gas generator scheme. More...

RDKS1 Russian rocket engine. Developed End 40's. Single chamber with turbopump propellant feed. More...

RDMT100 NII Mash N2O4/UDMH rocket engine. 0.100 kN. Salyut, Mir, SoyuzT and TM, Progress, Kosmossatellites. In Production. Lowthrust attitude control thruster. Isp=260s. More...

RDMT8 X NII Mash N2O4/UDMH rocket engine. 8 N. Developed 1980's. Experimental lowthrust thruster. Isp=296s. More...

RDMT50 NII Mash N2O4/UDMH rocket engine. 0.050 kN. Kosmos satellites. In Production. Lowthrust attitude control thruster. Isp=255s. More...

RDMT400A NII Mash N2O4/UDMH rocket engine. 0.400 kN. Developed 1980's. Experimental lowthrust thruster. Niobium combustion chamber with coating. Isp=290s. More...

RDMT400 X NII Mash N2O4/UDMH rocket engine. 0.400 kN. Developed 1980's. Experimental lowthrust thruster. Carbon combustion chamber. Mass may be chamber only. Isp=296s. More...

RDMT400 NII Mash N2O4/UDMH rocket engine. 0.400 kN. Almaz, Kvant, Kristall, Spektr, Priroda. In Production. Lowthrust attitude control thruster. Used in Isayev 11D458 engine. Isp=255s. More...

RDMT200 NII Mash N2O4/UDMH rocket engine. 0.200 kN. Almaz. In Production. Lowthrust attitude control thruster. Isp=255s. More...

RDMT12 NII Mash N2O4/UDMH rocket engine. 12 N. Almaz, Kvant, Kristall, Spektr, Priroda. In Production. Lowthrust attitude control thruster. Predecessor was RDMT400. Used in Isayev 17D58E engine. Isp=279s. More...

RDMT0.4 X NII Mash N2O4/UDMH rocket engine. 400 mN. In Production. Experimental lowthrust thruster. Chamber from niobium alloy. Chamber pressure 41 / 17 bar. Specific impulse 313 / 302,3 sec. Isp=290s. More...

RDMT135 NII Mash N2O4/UDMH rocket engine. 0.135 kN. Salyut, Mir, SoyuzT and TM, Progress, Kosmossatellites. In Production. Lowthrust attitude control thruster. Isp=260s. More...

RESA2 Rocketdyne N2O4/MMH rocket engine. 0.215 kN. Pitch Control Propulsion Module. Pressurefed. More...

RESA5 Rocketdyne N2O4/MMH rocket engine. 7.109 kN. Spacecraft. Pressurefed. Isp=280s. More...

RM05 Rocketdyne N2O4/MMH rocket engine. 0.020 kN. Satellite Reaction Control System. Pressurefed. Isp=238s. More...

RM100B Rocketdyne Nitric acid/UDMH rocket engine. 0.441 kN. Satellite Reaction Control. Pressurefed. Isp=283s. More...

RM12 Rocketdyne N2O4/MMH rocket engine. 4.4 N. Satellite Reaction Control. Pressurefed. Isp=238s. More...

RM11 Rocketdyne N2O4/MMH rocket engine. 4.4 N. Satellite Reaction Control System. Pressurefed. Isp=245s. More...

RM100A Rocketdyne N2O4/MMH rocket engine. 0.441 kN. Spacecraft. Pressurefed. Isp=301s. More...

RM100T Rocketdyne N2O4/Aerozine50 rocket engine. 0.441 kN. Lunar Flyer. Pressurefed. Isp=296s. More...

RM25 Rocketdyne N2O4/MMH rocket engine. 0.107 kN. Spacecraft. Pressurefed. Isp=286s. More...

RM251 Rocketdyne N2O4/MMH rocket engine. 0.107 kN. Spacecraft. Pressurefed. Isp=300s. More...

RM900 Rocketdyne N2O4/MMH rocket engine. 4.001 kN. Shuttle Orbiter Reaction Control. Pressurefed. Isp=309s. More...

RS1403 Rocketdyne N2O4/MMH rocket engine. 0.078 kN. Minuteman Pitch, Yaw & Roll Control. Pressurefed. Technology engine, developed, but not produced. Led to RS14 prodution engines. Isp=230s. More...

RS18 Rocketdyne N2O4/Aerozine50 rocket engine. 15.563 kN. Apollo Lunar Ascent Module Engine. Pressurefed. Isp=310s. More...

RS1402 Rocketdyne N2O4/MMH rocket engine. 0.098 kN. Minuteman Pitch, Yaw & Roll Control. Pressurefed. Technology engine, developed, but not produced. Led to RS14 prodution engines. Isp=259s. More...

RS14 Rocketdyne N2O4/MMH rocket engine. 1.392 kN. Minuteman Postboost Velocity Control. Pressurefed. Isp=315s. First flight 1970. More...

RS2101C Rocketdyne N2O4/MMH rocket engine. 1.333 kN. Viking. Pressurefed. Derivtive of RS14 Minuteman engine. Isp=294s. First flight 1975. More...

RS23 Rocketdyne N2O4/MMH rocket engine. 26.670 kN. Space Shuttle Orbiter Orbit Maneuvering System. Pressurefed. Isp=313s. First flight 1981. More...

RS28 Rocketdyne N2O4/MMH rocket engine. 2.667 kN. Space Shuttle Orbiter Reaction Control. Pressurefed. Isp=220s. More...

RS2101A Rocketdyne N2O4/MMH rocket engine. 1.333 kN. Mars Mariner. Pressurefed. Derivtive of RS14 Minuteman engine. Isp=287s. First flight 1971. More...

RS32 Rocketdyne N2O4/MMH rocket engine. 1.392 kN. Upper Stage Target Engine Systems. Pressurefed. Derived from Minuteman RS14. Isp=288s. More...

RS34 Rocketdyne N2O4/MMH rocket engine. 11.7 kN. Peacekeeper Postboost Axial Thrust. Pressurefed. 1 main axial thruster per postboost propulsion system. Isp=308s. First flight 1983. More...

RS36 Rocketdyne N2O4/MMH rocket engine. 55.6 kN. HOE Homing Overlay Experiment Upper Stage Axial Propulsion System. Pressurefed. Derivative of Lance propulsioon system. Isp=281s. First flight 1983. More...

RS41 Rocketdyne N2O4/MMH rocket engine. 11.960 kN. Axial Spacecraft. Pressurefed. Isp=320s. More...

RS45 Rocketdyne N2O4/MMH rocket engine. 4.4 N. Satellite Attitude Control and Stationkeeping. Pressurefed. Isp=300s. More...

RS42 Rocketdyne N2O4/MMH rocket engine. 0.441 kN. Axial Spacecraft. Pressurefed. Isp=305s. More...

RS43 Rocketdyne N2O4/MMH rocket engine. 0.020 kN. Attitude Control. Pressurefed. Isp=284s. More...

RS51 Rocketdyne N2O4/MMH rocket engine. 11.552 kN. Axial Spacecraft. Pressurefed. Isp=315s. More...

RS72 Rocketdyne, Ottobrunn N2O4/MMH rocket engine. 55.4 kN. Isp=340s. Aestus engine enhanced with the addition of a BoeingRocketdyne XLR 32 turbopump. More...

RS82 Rocketdyne H2O2/kerosene rocket engine. 44.463 kN. Next Generation NonToxic Upper Stage. Gas generator, pumpfed. Isp=320s. More...

S155 Dushkin rocket engine. 39 kN. E50. Developed 195556. Thrust variable 2000  4000 kgf. More...

S320M5A Dushkin Nitric acid/Kerosene rocket engine. U21. Developed 1959. Launch thrust 29.4 kN. More...

S09.502 Isayev Nitric acid/Amine rocket engine. R101 SAM. Developed 194950. Launch thrust 78.4 kN. Four chamber engine designed for use in the R101 (derivative of German Wasserfall). Abandoned by 1950 in favour of singlechamber engine. More...

S09.29 Isayev Nitric acid/Amine rocket engine. 88 kN. V300/V303 (S25 system). Out of Production. More...

S2.1150 Isayev Nitric acid/Amine rocket engine. 671.2 kN. Burya booster. Out of production. Isp=250s. First flight 1957. Engines developed from R11 S2.253 engine. More...

S2.1200 Isayev rocket engine. Developed 1950s middle. OKB2 transferred work on the S2.1200 to OKB154 in 1957. The latter used the designation RO1 for the engine. More...

S2.145 Isayev rocket engine. 88 kN. Developed 1950s early. More...

S2.1100 Isayev rocket engine. V1000. Out of Production. OKB2 transferred work on the S2.1100 to OKB117 in 195859. OKB117 completed development. More...

S2.253 Isayev Nitric acid/Kerosene rocket engine. 93.3 kN. R11 (Scud B) 8A61. Thrust 8300 kgf at sea level. Fuel Kerosene T1, chemical ignition by TG02. Isp=251s. First flight 1953. More...

S2.253A Isayev Nitric acid/Kerosene rocket engine. 93 kN. R11FM. Out of Production. Used in R11FM submarine version of Scud B. Fuel Kerosene T1, chemical ignition by TG02. Mixture ratio derived from tank content. 81 kN sealevel. More...

S2.720 Isayev Nitric acid/Amine rocket engine. 34.3 kN. Engine for SAMmissile V755. Out of Production. Pumpfed engine. Used in engine unit of a special apparatus. Pumpfed engine. 20,4 kN sea level. More...

S2.713 Isayev Nitric acid/Amine rocket engine. 252.2 kN. R13 (SSN4). Out of Production. First engine to employ gas generator on main propellants. One main and four vernier thrusters. (Mixture derived ratio from tank content.) More...

S2.721V Isayev Nitric acid/Amine rocket engine. 11.8 kN. KSR. Developed 1956. More...

S3.42A Sevruk rocket engine. 166 kN. 217. Out of Production. More...

S5.1 Isayev Nitric acid/Amine rocket engine. 167 kN. SAMmissiles 217M and 218. Out of Production. Designation unknown. More...

S5.3 Isayev Nitric acid/Amine rocket engine. 392 kN. R21 (SSN5). Out of Production. First engine to start underwater. 392 kN sealevel. More...

S5.3M Isayev Nitric acid/Amine rocket engine. 396.7 kN. R9 (SS8) missile stage 1. Out of Production. Proposed for R9 missile stage 1. Four engines per stage. 396,7 kN sealevel. More...

S5.44 Isayev Nitric acid/Amine rocket engine. 177 kN. SAMmissile 5Ya24. Out of Production. Could be throttled. 17749 kN sealevel. Area ratio 118  44. More...

S5.45 Isayev Nitric acid/UDMH rocket engine. 1961 kN. correction engine for Zond1, Venera28, and others. Out of Production. Pressurefed engine. Used as correction engine for spacecraft Zond1, Vernera8, and others. Isp=267s. More...

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. More...

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. More...

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 lowthrust thrust levels. More...

S5.98M Isayev N2O4/UDMH rocket engine. 19.62 kN. Used on Briz and BrizM 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. More...

SE1, 11, 2, and 4 Series Rocketdyne N2O4/UDMH rocket engine. SE1, 11, 2, and 4 Series. Spacecraft Reaction Control. Pressurefed. Multiple thrust levels. First flight 1959. More...

SE10 Rocketdyne N2O4/Aerozine50 rocket engine. 46.670 kN. Lunar Module Descent. Pressurefed. Thrust throttleable 105010,500 lbs vac. Isp=305s. First flight 1968. More...

SE52/3 Rocketdyne N2O4/UDMH rocket engine. 0.205 kN. SE52/3. Agena Auxiliary. Pressurefed. SE52 four engines in satellite system. SE53 two engines for Agena auxiliary propuslion. Isp=272s. First flight 1963. More...

SE6 Rocketdyne N2O4/MMH rocket engine. 0.107 kN. Gemini Reentry Control System. Pressurefed. Isp=277s. First flight 1964. More...

SE725 Rocketdyne N2O4/MMH rocket engine. 0.107 kN. Gemini Orbit Attitude and Maneuvering System (25 Ib thrust). Pressurefed. Isp=277s. First flight 1964. More...

SE785 Rocketdyne N2O4/MMH rocket engine. 0.372 kN. Gemini Orbit Attitude and Maneuvering System (85 Ib thrust). Pressurefed. Isp=295s. First flight 1964. More...

SE71 Rocketdyne N2O4/MMH rocket engine. 0.313 kN. SIVB Stage APS Ullage Control Engine (propellant settling). Pressurefed. Isp=274s. First flight 1966. More...

SE7100 Rocketdyne N2O4/MMH rocket engine. 0.441 kN. Gemini Orbit Attitude and Maneuvering System (100 Ib thrust). Pressurefed. Isp=296s. First flight 1964. More...

SE8 Rocketdyne N2O4/MMH rocket engine. 0.411 kN. Apollo Command Module Reaction Control. Pressurefed. Isp=274s. First flight 1966. More...

SE93 Rocketdyne N2O4/Aerozine50 rocket engine. 0.107 kN. Titan III Transtage. Pressurefed. System included two modules of three engines plus two additional SE95 separate engines, tanks, and a pressuirzation system. Isp=295s. First flight 1964. More...

SE95 Rocketdyne N2O4/Aerozine50 rocket engine. 0.196 kN. Titan III Transtage. Pressurefed. System included two modules of three engines plus two additional SE95 separate engines, tanks, and a pressuirzation system. Isp=300s. First flight 1964. More...

SEPR 16 SEPR rocket engine. 200 kN. AA.10 AAM. First flight 1950. More...

SEPR 2 SEPR rocket engine. 1250 kN. SE 4100 SAM. Used turbopumps SEPR 3 and SEPR 4. First flight 1950. More...

SEPR 25 SEPR rocket engine. 4500 kN. Trident/Espadon fighter augmentation. More...

SEPR 43 SEPR rocket engine. 1250 kN. R.04 SAM. First flight 1950. More...

TD2 CMIK Nitric acid/UDMH rocket engine. 1000 kN. More...

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. More...

Topaze SEP N2O4/UDMH rocket engine. 120.1 kN. Out of production. Isp=255s. Used on Diamant launch vehicle. First flight 1965. More...

TR201 TRW N2O4/Aerozine50 rocket engine. 41.9 kN. Apollo lunar module ascent stage engines. Surplus engines used on Delta P stage. Isp=301s. First flight 1972. More...

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 pumpfed for increased chamber pressure and Isp. Tested; no production. More...

U1250 Isayev rocket engine. 12.7 kN. Developed 194546. Isp=208s. More...

U2000 Isayev rocket engine. 19.6 kN. for SAM. Out of Production. More...

U4002 Isayev Nitric acid/Amine rocket engine. Shchuka. Out of Production. More...

U40010 Isayev rocket engine. 3.920 kN. Samolet 5. Developed 194647. More...

U102000 Glushko Nitric acid/UDMH rocket engine. 468 kN. R26 stage 2. Out of production. Isp=307s. More...

Vesta LRBA Nitic acid/Turpentine rocket engine. 140 kN. More...

Vexin A SEP N2O4/UDMH rocket engine. 68.6 kN. Isp=277s. Used on Europa launch vehicle. First flight 1964. More...

Vexin B SEP N2O4/UDMH rocket engine. 75.4 kN. Out of production. Isp=251s. Used on Diamant launch vehicle. First flight 1965. More...

Vexin C SEP N2O4/UDMH rocket engine. 99.1 kN. Out of production. Isp=251s. Used on Diamant B launch vehicle. First flight 1970. More...

Viking 2 SEP N2O4/UDMH rocket engine. 693 kN. In production. Isp=281s. Used on Ariane 1, GSLV space launchers. First flight 1979. More...

Viking 5C SEP N2O4/UDMH rocket engine. 752 kN. Isp=278s. Used on Ariane 42L, Ariane 44L, Ariane 44LP. First flight 1988. More...

Viking 4B SEP N2O4/UDMH rocket engine. 805 kN. Isp=296s. Used on Ariane 4. First flight 1984. More...

Viking 2B SEP N2O4/UDMH rocket engine. 720 kN. Isp=278s. Used on Ariane 2/3. First flight 1984. More...

Viking 4 SEP N2O4/UDMH rocket engine. 721 kN. Isp=296s. Used on Ariane 1, GSLV, PSLV. First flight 1979. More...

Von Braun1 Notional Nitric acid/UDMH rocket engine. 3057.3 kN. Study 1952. Isp=286s. Used on Von Braun launch vehicle. More...

Von Braun2 Notional Nitric acid/UDMH rocket engine. 461.5 kN. A11, Von Braun studies 19431952. Isp=286s. More...

Von Braun3 Notional Nitric acid/UDMH rocket engine. 392.3 kN. Study 1952. Isp=286s. Used on Von Braun launch vehicle. More...

WAC JPL/Douglas Nitric acid/aniline rocket engine. 6.7 kN. More...

X35AL6000 Aerojet rocket engine. PB2Y3 ATO. Launch thrust 26.77 kN. Development begun November 1942. More...

X4AL1000 Aerojet Nitric acid/Amine rocket engine. Brake rocket for G4A. Launch thrust 4.41 kN. Braking rocket for glider. Single uncooled chamber, pressure fed, 13 kg of propellant. More...

X45ALD4000 Aerojet Nitric acid/Amine rocket engine. B29 ATO. Launch thrust 17.6 kN. Development begun June 1948. Regenerative cooling, nitrogen pressurefed, droppable but no recoverable. Early version using XLR13AJ1 thrust chamber assembly. More...

X60AL1300 Aerojet Nitric acid/Amine rocket engine. P51 superperformance. Launch thrust 5.78 kN. Development begun January 1945. Superperformance More...

X60ALD4000 Aerojet Nitric acid/Amine rocket engine. ATO for XB45, B45A. Launch thrust 17.6 kN. Development begun May 1946. Pressurising tank surrounded propellant tanks. Regeneratively cooled. Parachute for dropping and recovery after takeoff. More...

X90ALT60000 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 More...

XASR1 Aerojet Nitric acid/aniline rocket engine. 11.6 kN. More...

XCALR2000A1 Aerojet Nitric acid/Amine rocket engine for XP79 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 19431945; blew up on first test. More...

XCALT6000 Aerojet Nitric acid/Amine rocket engine. Thrust 26.67 kN. Conservative alternate to Aerotojet for XP79 flying wing rocket fighter. Successfully tested in August 1945, but project cancelled. Regeneratively cooled, 4 thrust chambers, pumpfed. More...

XLR13AJ5 Aerojet Nitric acid/Amine rocket engine. B29 ATO. Launch thrust 17.6 kN. Development begun June 1948. Ceramic chamber and nozzle, nitrogen pressurefed, droppable but no recoverable. More...

XLR13AJ7 Aerojet Nitric acid/Amine rocket engine. Launch thrust 17.6 kN. Modification of AJ1. Regeneratively cooled by fuel, droppable. More...

XLR132 Rocketdyne N2O4/MMH rocket engine. 16.7 kN. Out of Production. Isp=340s. Pumpfed high performance upper stage engine for perigee/apogee stages. as well as transfer vehicles and lunar and Martian missions. Tested extensively but no production. More...

XLR24AJ2 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) More...

XLR20AJ2 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. More...

XLR53AJ1 Aerojet Nitric acid/Amine rocket engine. F80. 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. More...

YF1 CALT Nitric acid/kerosene rocket engine. 300 kN. More...

YF22 Beijing Wan Yuan N2O4/UDMH rocket engine. 717.8 kN. In Production. Isp=295s. More...

YF25/23 Beijing Wan Yuan N2O4/UDMH rocket engine. 831 kN. In production. Cluster of YF25 and 4 x YF23 verniers. Isp=295s. First stage engine for CZ2D, CZ2E, CZ2E(A), CZ3A, CZ3B, CZ3C, CZ4A. First flight 1988. More...

YF25 Beijing Wan Yuan N2O4/UDMH rocket engine. 787.4 kN. In Production. Isp=297s. More...

YF2A Beijing Wan Yuan Nitric acid/UDMH rocket engine. 306.1 kN. Out of production. Isp=268s. Used on CZ1, CZ1C, CZ1D, CZ1M. First flight 1969. More...

YF23 Beijing Wan Yuan N2O4/UDMH rocket engine. 11 kN. In Production. Used as vernier motor with YF22 and YF25. Isp=282s. More...

YF22/23 Beijing Wan Yuan N2O4/UDMH rocket engine. 762 kN. Out of production. Cluster of YF22 and 4 x YF23 verniers. Isp=295s. Boosted CZ2A, FB1. First flight 1972. More...

YF20B Beijing Wan Yuan N2O4/UDMH rocket engine. 816.3 kN. In production. Isp=289s. Boosted CZ2C, CZ2D, CZ2E, CZ2E(A), CZ3A, CZ3B, CZ3C, CZ4A. First flight 1988. More...

YF20A Beijing Wan Yuan N2O4/UDMH rocket engine. 750.2 kN. Out of production. Isp=289s. Boosted CZ2A, CZ2C, CZ2E(A), CZ3, FB1. First flight 1972. More...

YF22A/23A Beijing Wan Yuan N2O4/UDMH rocket engine. 762 kN. Out of production. Cluster of YF22A and 4 x YF23 verniers. Isp=295s. Boosted CZ2C, CZ3. First flight 1975. More...

YF3 Beijing Wan Yuan N2O4/UDMH rocket engine. 294 kN. Out of production. Isp=287s. Used on CZ1D launch vehicle. First flight 1995. More...

YF40 Beijing Wan Yuan N2O4/UDMH rocket engine. 49 kN. Out of production. Isp=295s. Used on CZ4A launch vehicle. First flight 1988. More...

YLR45AJ1 Aerojet Nitric acid/Kerosene rocket engine. B47C ATO. Out of Production. Development begun August 1948. Turbojet engine bleed air drive for turbopump. Fixed internal acid tanks, regenerative cooling. More...

YLR45AJ3 Aerojet Nitric acid/Kerosene rocket engine. F84 ATO. Out of Production. Development begun 1948. Bleed air drive, droppable acid tanks, ceramic chamber with oval throat, 60 second duration, reusable 50 times More...

YLR63AJ3 Aerojet Nitric acid/UDMH rocket engine. F86. Out of Production. Development begun 1953. Superperformance, modification of YLR45AJ3 with gas generator turbine drive, 6 restarts. More...
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