Encyclopedia Astronautica
Storable liquid


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 LK-700 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 LK-700 manned spacecraft. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. 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 kg-s. Minimum impulse 4 kg-s. Specific impulse also reported as 275 sec. More...
  • 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. More...
  • 11D79 Stepanov N2O4/UDMH rocket engine. 44 kN. Blok D SOZ. In Production. Thrust 1.1-4.5 tf variable. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. 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 1963-1970. 10 to 12 tonne thrust engine developed for an unstated military requirement. Isp=325s. More...
  • A6-12 Dushkin rocket engine. 39 kN. V-600. Developed 1955-62. 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...
  • Aestus-2 Rocketdyne / DASA N2O4/MMH rocket engine. 60 kN. Production. Restartable upper-stage engine, began test firings at Lampoldshausen in February 2000. More...
  • AJ10-196 Aerojet rocket engine. 40.1 kN. Liquid Throttling Engine. Liquid Throttling Engine More...
  • 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. More...
  • 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 More...
  • 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. More...
  • 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. More...
  • AJ10-51 Aerojet rocket engine. 666 kN. Sled. Thrust variable to 33% indicated. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • AJ10-131 Aerojet N2O4/Aerozine-50 rocket engine. 9.8 kN. Subscale Apollo SPS. Subscale Apollo SPS More...
  • 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. More...
  • 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. More...
  • 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. More...
  • AJ10-118G Aerojet Nitric acid/UDMH rocket engine. 43.414 kN. Delta G. Isp=314s. More...
  • AJ10-118H Aerojet Nitric acid/UDMH rocket engine. 43.414 kN. Delta H. Isp=319s. More...
  • 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. More...
  • 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. More...
  • AJ11-6 Aerojet Nitric acid/aniline rocket engine. 17.8 kN. Typical ideal dV=3839 m/s; gravity and drag losses = 1012 m/s. More...
  • AJ60-91 Aerojet rocket engine. 72.324 kN. Aerobee 350. Aerobee motor. Four Chambers More...
  • AR1 Rocketdyne h2o2/kerosene rocket engine. 22.260 kN. Engine for FJ-4F naval interceptor. More...
  • 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. More...
  • 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. More...
  • Astris German N2O4/Aerozine-50 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...
  • 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. More...
  • 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. More...
  • 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. 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 Gemini-Agena 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 Tu-160 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 Tu-160 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/Aniline-Furfuyrl alcohol rocket engine. 89 kN. More...
  • Corporal E Douglas/JPL Nitric acid/Aniline-Furfuyrl alcohol rocket engine. 89 kN. More...
  • CZ-1C-3 Chinese N2O4/UDMH rocket engine. 107.9 kN. Development ended 1988. Isp=287s. Used on CZ-1C launch vehicle. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • FY-25 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 1963-1970. Largest thrust chamber ever tested in Russia was Glushko's RD-270 of 680 tf. More...
  • HiPAT Redmond N2O4/MMH rocket engine. 0.445 kN. In Production. High performance liquid apogee thruster. Isp=323s. More...
  • Isayev V-750V Isayev Nitric acid/Amine rocket engine. 30.4 kN. SAM-missile V-750V. Out of Production. Designation unknown. More...
  • Isayev R-17 Isayev Nitric acid/Kerosene rocket engine. 131.2 kN. R-17. Out of production. Designation unknown. First flight 1961. More...
  • Isayev 218 Isayev Nitric acid/Amine rocket engine. 218 (S-25 system). Out of Production. Launch thrust 166 kN. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • KRR-300 Dushkin rocket engine. 98 kN. G-300. Developed 1955-62. Thrust variable 0.1 / 3.0 / 10 tf. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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 More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • L7 MBB N2O4/MMH rocket engine. 27.4 kN. In Production. Isp=320s. Used on Ariane 5 launch vehicle. First flight 1996. More...
  • LE-3 Rocketdyne N2O4/Aerozine-50 rocket engine. 53.340 kN. MHI(Japan)/Rocketdyne Upper Stage. Pressure-fed. Isp=285s. More...
  • Liberty-2 Notional N2O4/MMH rocket engine. 17.8 kN. Development ended 1988. Pressure-fed engine. Isp=300s. Used on Liberty launch vehicle. More...
  • LR101-NA-7 Rocketdyne N2O4/MMH rocket engine. 5.148 kN. Upper Stage Target Engine Systems. Pressure-fed. Derived from Atlas vernier. Isp=251s. More...
  • 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. More...
  • 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 More...
  • LR65 Bell rocket engine for the X-9 Shrike, an experimental prototype of the Rascal air-to-ground missile. More...
  • 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. More...
  • 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. 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 in-space starts after a period of coasting). More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • MR-509 Redmond Hydrazine rocket engine. 254 mN. In Production. Low-power arcjet system. Input power 1800 W at 65 V DC. Isp=502s. More...
  • MR-510 Redmond Hydrazine rocket engine. 254 mN. In Production. Arcjet system. Isp=600s. More...
  • 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. More...
  • 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. More...
  • MRM-122 Redmond Hydrazine rocket engine. 0.142 kN. In Production. Steady-state thrust 51 N. Isp=228s. More...
  • MRM-103 Redmond Hydrazine rocket engine. 0.22 N. In Production. Steady-state thrust 0.22 N. Isp=224s. More...
  • MRM-106 Redmond Hydrazine rocket engine. 0.027 kN. In Production. Steady-state 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 re-entry initiation. First flight 1981. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • PF N204/Alumizine-1925k Notional N2O4/Alumizine rocket engine. 18,873 kN. Study 1967. Isp=280s. Used on Saturn LCB-Alumizine-250 launch vehicle. More...
  • PF N204/Alumizine-2300k Notional N2O4/Alumizine rocket engine. 22,562 kN. Study 1967. Isp=280s. Used on Saturn LCB-Alumizine-140 launch vehicle. More...
  • PF N204/UDMH-2165k Notional N2O4/UDMH rocket engine. 21,232 kN. Study 1967. Isp=267s. Used on Saturn LCB-Storable-250 launch vehicle. More...
  • PF N204/UDMH-2912k Notional N2O4/UDMH rocket engine. 28,552 kN. Study 1967. Isp=267s. Used on Saturn LCB-Storable-140 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...
  • PSLV-4 ISRO N2O4/MMH rocket engine. 7 kN. Isp=308s. Used on PSLV launch vehicle. First flight 1993. More...
  • 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). More...
  • 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. More...
  • R-200 Dushkin rocket engine. 9.8 kN. Out of Production. Thrust variable 0.8 tf -1.0 tf. More...
  • 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. More...
  • R-40B Redmond N2O4/MMH rocket engine. 4 kN. In Production. Isp=293s. More...
  • R-42 Redmond N2O4/MMH rocket engine. 0.890 kN. In Production. Isp=303s. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • RD-0231 Kosberg N2O4/UDMH rocket engine. 29 kN. P-700 Granit. Out of Production. Staged combustion cycle. Isp=275s. First flight 1970. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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%. More...
  • 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. More...
  • 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. More...
  • RD-0246 Kosberg N2O4/UDMH rocket engine. Design concept. Project for further development of RD-0243. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • RD-0221 Kosberg N2O4/UDMH rocket engine. 78 kN. upper stage of unnamed missile by Mishin. Developed 1965-70. Isp=330s. More...
  • 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 More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • RD-253-14D14 Glushko N2O4/UDMH rocket engine. 1746 kN. Proton KM-1. In production. Developed in 1990s. Isp=317s. First flight 1999. More...
  • 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. More...
  • 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. More...
  • RD-261 Glushko N2O4/UDMH rocket engine. 3032 kN. Tsyklon 3 stage 1. In production. Based on RD-251 Isp=301s. First flight 1977. More...
  • RD-262 Glushko N2O4/UDMH rocket engine. 941 kN. Tsyklon 3 stage 2. In production. Based on RD-252 Isp=317s. First flight 1977. More...
  • 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. More...
  • RD-2MZV-F Dushkin Nitric acid/Kerosene rocket engine. 19.6 kN. Samolet 5. Developed 1946. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • RD-273 Glushko N2O4/UDMH rocket engine. 1238 kN. Developed 1975-82. Upgrade of RD-263 in 1982 based on RD-263F project. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • RD-293 Yuzhnoye rocket engine. Maneuvering vehicle axial maneuvering. More...
  • 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. More...
  • 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. More...
  • RD-263F Glushko N2O4/UDMH rocket engine. Developed 1980. Project to upgrade RD-263. Upgrade was realized in RD-273 engine. More...
  • RD-200 Glushko Nitric acid/Kerosene rocket engine. 98.508 kN. vertical sounding rocket. Developed -1951. Isp=234s. More...
  • RD-216M Glushko Nitric acid/UDMH rocket engine. Kosmos-3M stage I. Out of Production. More...
  • 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. More...
  • 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. More...
  • RD-210 Glushko Nitric acid/Kerosene rocket engine. 29.850 kN. vertical sounding rocket. Developed -1954. Isp=241s. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • RD-220 Glushko Nitric acid/UDMH rocket engine. 1074 kN. missile stage 1 (stage 2 used RD-221). Developed 1960-. Isp=306s. More...
  • RD-221 Glushko Nitric acid/UDMH rocket engine. 1118 kN. missile stage 2 (stage 1 used RD-220). Developed 1960-. Isp=318s. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • RD-510T Glushko H2O2/CxHy rocket engine. Developed 1965-75. First flight 1975. More...
  • RD-511 Glushko H2O2/CxHy rocket engine. Developed 1965-75. First flight 1975. More...
  • 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. More...
  • RD-510 Glushko H2O2/CxHy rocket engine. Developed 1965-75. First flight 1975. More...
  • 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. More...
  • RD-69 Yuzhnoye Nitric acid/UDMH rocket engine. 49.2 kN. R-16 stage 2 attitude control engine. Out of Production. More...
  • 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. More...
  • RD-68 Yuzhnoye Nitric acid/UDMH rocket engine. 380 kN. R-16 stage 1 attitude control engine. Out of Production. More...
  • 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. More...
  • 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). More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • RDKS-1 Russian rocket engine. Developed End 40's. Single chamber with turbopump propellant feed. More...
  • 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. More...
  • RDMT-8 X NII Mash N2O4/UDMH rocket engine. 8 N. Developed 1980's. Experimental low-thrust thruster. Isp=296s. More...
  • RDMT-50 NII Mash N2O4/UDMH rocket engine. 0.050 kN. Kosmos satellites. In Production. Low-thrust attitude control thruster. Isp=255s. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • RDMT-200 NII Mash N2O4/UDMH rocket engine. 0.200 kN. Almaz. In Production. Low-thrust attitude control thruster. Isp=255s. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • RESA-2 Rocketdyne N2O4/MMH rocket engine. 0.215 kN. Pitch Control Propulsion Module. Pressure-fed. More...
  • RESA-5 Rocketdyne N2O4/MMH rocket engine. 7.109 kN. Spacecraft. Pressure-fed. Isp=280s. More...
  • RM-05 Rocketdyne N2O4/MMH rocket engine. 0.020 kN. Satellite Reaction Control System. Pressure-fed. Isp=238s. More...
  • RM-100B Rocketdyne Nitric acid/UDMH rocket engine. 0.441 kN. Satellite Reaction Control. Pressure-fed. Isp=283s. More...
  • RM-1-2 Rocketdyne N2O4/MMH rocket engine. 4.4 N. Satellite Reaction Control. Pressure-fed. Isp=238s. More...
  • RM-1-1 Rocketdyne N2O4/MMH rocket engine. 4.4 N. Satellite Reaction Control System. Pressure-fed. Isp=245s. More...
  • RM-100A Rocketdyne N2O4/MMH rocket engine. 0.441 kN. Spacecraft. Pressure-fed. Isp=301s. More...
  • RM-100T Rocketdyne N2O4/Aerozine-50 rocket engine. 0.441 kN. Lunar Flyer. Pressure-fed. Isp=296s. More...
  • RM-25 Rocketdyne N2O4/MMH rocket engine. 0.107 kN. Spacecraft. Pressure-fed. Isp=286s. More...
  • RM-25-1 Rocketdyne N2O4/MMH rocket engine. 0.107 kN. Spacecraft. Pressure-fed. Isp=300s. More...
  • RM-900 Rocketdyne N2O4/MMH rocket engine. 4.001 kN. Shuttle Orbiter Reaction Control. Pressure-fed. Isp=309s. More...
  • 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. More...
  • RS-18 Rocketdyne N2O4/Aerozine-50 rocket engine. 15.563 kN. Apollo Lunar Ascent Module Engine. Pressure-fed. Isp=310s. More...
  • 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. More...
  • RS-14 Rocketdyne N2O4/MMH rocket engine. 1.392 kN. Minuteman Postboost Velocity Control. Pressure-fed. Isp=315s. First flight 1970. More...
  • RS-2101C Rocketdyne N2O4/MMH rocket engine. 1.333 kN. Viking. Pressure-fed. Derivtive of RS-14 Minuteman engine. Isp=294s. First flight 1975. More...
  • RS-23 Rocketdyne N2O4/MMH rocket engine. 26.670 kN. Space Shuttle Orbiter Orbit Maneuvering System. Pressure-fed. Isp=313s. First flight 1981. More...
  • RS-28 Rocketdyne N2O4/MMH rocket engine. 2.667 kN. Space Shuttle Orbiter Reaction Control. Pressure-fed. Isp=220s. More...
  • 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. More...
  • RS-32 Rocketdyne N2O4/MMH rocket engine. 1.392 kN. Upper Stage Target Engine Systems. Pressure-fed. Derived from Minuteman RS-14. Isp=288s. More...
  • 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. More...
  • 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. More...
  • RS-41 Rocketdyne N2O4/MMH rocket engine. 11.960 kN. Axial Spacecraft. Pressure-fed. Isp=320s. More...
  • RS-45 Rocketdyne N2O4/MMH rocket engine. 4.4 N. Satellite Attitude Control and Stationkeeping. Pressure-fed. Isp=300s. More...
  • RS-42 Rocketdyne N2O4/MMH rocket engine. 0.441 kN. Axial Spacecraft. Pressure-fed. Isp=305s. More...
  • RS-43 Rocketdyne N2O4/MMH rocket engine. 0.020 kN. Attitude Control. Pressure-fed. Isp=284s. More...
  • RS-51 Rocketdyne N2O4/MMH rocket engine. 11.552 kN. Axial Spacecraft. Pressure-fed. Isp=315s. More...
  • 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. More...
  • RS-82 Rocketdyne H2O2/kerosene rocket engine. 44.463 kN. Next Generation Non-Toxic Upper Stage. Gas generator, pump-fed. Isp=320s. More...
  • S-155 Dushkin rocket engine. 39 kN. E-50. Developed 1955-56. Thrust variable 2000 - 4000 kgf. More...
  • S-3-20M5A Dushkin Nitric acid/Kerosene rocket engine. U-21. Developed -1959. Launch thrust 29.4 kN. More...
  • 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. More...
  • S09.29 Isayev Nitric acid/Amine rocket engine. 88 kN. V-300/V-303 (S-25 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 R-11 S2.253 engine. More...
  • 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. More...
  • S2.145 Isayev rocket engine. 88 kN. Developed 1950s early. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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.) 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. SAM-missiles 217M and 218. Out of Production. Designation unknown. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. 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 low-thrust thrust levels. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • SE-6 Rocketdyne N2O4/MMH rocket engine. 0.107 kN. Gemini Re-entry Control System. Pressure-fed. Isp=277s. First flight 1964. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • SE-8 Rocketdyne N2O4/MMH rocket engine. 0.411 kN. Apollo Command Module Reaction Control. Pressure-fed. Isp=274s. First flight 1966. More...
  • 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. More...
  • 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. 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...
  • TD-2 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...
  • 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. 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 pump-fed for increased chamber pressure and Isp. Tested; no production. More...
  • U-1250 Isayev rocket engine. 12.7 kN. Developed 1945-46. Isp=208s. More...
  • U-2000 Isayev rocket engine. 19.6 kN. for SAM. Out of Production. More...
  • U-400-2 Isayev Nitric acid/Amine rocket engine. Shchuka. Out of Production. More...
  • U-400-10 Isayev rocket engine. 3.920 kN. Samolet 5. Developed 1946-47. More...
  • U102-000 Glushko Nitric acid/UDMH rocket engine. 468 kN. R-26 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 Braun-1 Notional Nitric acid/UDMH rocket engine. 3057.3 kN. Study 1952. Isp=286s. Used on Von Braun launch vehicle. More...
  • Von Braun-2 Notional Nitric acid/UDMH rocket engine. 461.5 kN. A11, Von Braun studies 1943-1952. Isp=286s. More...
  • Von Braun-3 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...
  • X35AL-6000 Aerojet rocket engine. PB2Y-3 ATO. Launch thrust 26.77 kN. Development begun November 1942. More...
  • 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. More...
  • 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. More...
  • X60AL-1300 Aerojet Nitric acid/Amine rocket engine. P-51 superperformance. Launch thrust 5.78 kN. Development begun January 1945. Superperformance More...
  • 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. More...
  • 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 More...
  • XASR-1 Aerojet Nitric acid/aniline rocket engine. 11.6 kN. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • XLR13-AJ-7 Aerojet Nitric acid/Amine rocket engine. Launch thrust 17.6 kN. Modification of -AJ-1. Regeneratively cooled by fuel, droppable. More...
  • 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. More...
  • 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) More...
  • 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. More...
  • 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. More...
  • YF-1 CALT Nitric acid/kerosene rocket engine. 300 kN. More...
  • YF-22 Beijing Wan Yuan N2O4/UDMH rocket engine. 717.8 kN. In Production. Isp=295s. More...
  • 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. More...
  • YF-25 Beijing Wan Yuan N2O4/UDMH rocket engine. 787.4 kN. In Production. Isp=297s. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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. More...
  • 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 More...
  • 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. More...

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