Encyclopedia Astronautica
Upper Stages


Category of engines.

More... - Chronology...


Associated Engines
  • 11B97 Korolev nuclear electric/xenon rocket engine. 450 mN. Engine for Interorbital Tug for launch by Energia. Developed 1978-1986. Isp=3000s. Powered by nuclear reactor providing 50-150 kWt for 3 to 5 years operation. More...
  • 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...
  • 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...
  • 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...
  • 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...
  • 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...
  • 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...
  • 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...
  • 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...
  • 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...
  • 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...
  • 11D53M Kuznetsov Lox/Kerosene rocket engine. 735 kN. N1M 1965 - V. Study 1965. As per N1 improvement study, 1965. Further increase in thrust of Block V engines. Isp=347s. Used on N-IM 1965 launch vehicle. More...
  • 11D53F Kuznetsov Lox/Kerosene rocket engine. 612 kN. N1F 1965 - V. Study 1965. As per N1 improvement study, 1965. Engine thrust increased and stretched propellant tanks resulting in 20% longer burn time. Isp=346s. More...
  • 11D52M Kuznetsov Lox/Kerosene rocket engine. 2745 kN. N1M 1965 - B. Study 1965. As per N1 improvement study, 1965. Thrust increased to 280 tonnes per engine. Isp=330s. More...
  • 11D52F Kuznetsov Lox/Kerosene rocket engine. 1961 kN. N1F 1965 - B. Study 1965. As per N1 improvement study, 1965. Engine thrust increased from 150 t each to 200 t. Isp=347s. 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...
  • 15D24 TsKB-7 solid rocket engine. 431 kN. RT-2 Stage 2. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/aluminium propellant. Chamber pressure 40 kgf/cm2. Average thrust 33 tonnes. More...
  • 15D24P TsKB-7 solid rocket engine. 437.3 kN. RT-2P Stage 2. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/ammonium butyl propellant. Chamber pressure 48 kgf/cm2. More...
  • 15D25 KBMash solid rocket engine. 137 kN. RT-2 Stage 3. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/aluminium propellant. More...
  • 15D339 Yuzhnoye. Tsurilnikov solid rocket engine. RT-23 stage II. Out of Production. The case-bound START composite solid propellant charge had a cylindrical-conical umbrella shape channel. The case was of organic fibre-wound plastic material. More...
  • 15D94 TsKB-7 solid rocket engine. 180.4 kN. RT-2P Stage 3. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/ammonium butyl propellant. Chamber pressure 48 kgf/cm2. More...
  • 17D11 Korolev Lox/Kerosene rocket engine. 86.3 kN. Buran OMS and verniers. Out of Production. Buran orbital propulsion system, including 2 x 17D12, 38 x 17D15, 8 x RDMT-200K Isp=362s. More...
  • 17D12 Korolev Lox/Kerosene rocket engine. 86.3 kN. Out of Production. Isp=362s. Version of RD-58 for Buran orbital propulsion system 17D11. Used synthetic kerosene ('Sintin') for higher specific impulse. More...
  • 17D15 Korolev GOX/Sintin rocket engine. 4 kN. Buran OMS large verniers. Out of Production. Isp=295s. Large verniers for Buran orbital propulsion system 17D11. Uses synthetic kerosene ('Sintin') for high specific impulse. Oxygen is gaseous in system. 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...
  • 200 inch solid segment x 4 Notional solid rocket engine. 11,120 kN. Study 1960. Isp=285s. 4 used as first stage of NASA all-solid Nova design. Extended high-expansion nozzles. 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...
  • 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...
  • 8D726 Korolev Lox/Kerosene rocket engine. 66.7 kN. GR-1 Stage 3, N-11GR - V. Development based on S1.5400. Isp=350s. More...
  • A-9 Thiel Lox/Alcohol rocket engine. 288.7 kN. Single chamber engine for V-2 series C, A9. Tested 1942-45. Isp=255s. Never went into production in Germany, but formed the basis for successful post-war American and French rocket engines. More...
  • Aerojet 445 Aerojet N2O4/MMH rocket engine. 0.445 kN. In Production. Mixture Ratio(O/F): 1.65. Isp=309s. More...
  • Aerojet 62 Aerojet N2O4/MMH rocket engine. 0.062 kN. In Production. Mixture Ratio(O/F): 1.65. Isp=287s. More...
  • Aerojet 21 Aerojet N2O4/MMH rocket engine. 0.021 kN. In Production. Mixture Ratio(O/F): 1.60. Isp=285s. More...
  • Aerojet 2 Aerojet N2O4/MMH rocket engine. 2 N. In Production. Mixture Ratio(O/F): 1.65. Isp=265s. 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...
  • 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...
  • AirLaunch Propane Engine Air Launch Lox/Propane rocket engine. 106.8 kN. Flow calibration, ignition and initial short duration tests completed in 2005 of this upper stage rocket engine with application to future small spacecraft launchers. More...
  • AJ-60C Aerojet lox/lh2 rocket engine. 280 kN. Design 2000. Isp=470s. Design announced on 3 October 2000 for a new cryogenic upper-stage engine aimed at the very large commercial spacecraft market. 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...
  • AJ10-138 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...
  • AJ10-118K 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...
  • AJ10-118D 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...
  • AJ10-118 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...
  • AJ10-101 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...
  • 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...
  • AJ10-118E 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...
  • Alcor Aerojet solid rocket engine. Originally developed for the Air Force as a third Stage for the Athena sounding rocket; in some applications known as Zebra. One of its main attractions was a very high mass fraction First flight 1960. More...
  • Astris German N2O4/Aerozine-50 rocket engine. 23.3 kN. Isp=310s. Used on Europa launch vehicle. First flight 1964. More...
  • ATCRE Notional lox/lh2 rocket engine. 1280 kN. Study 1985. Isp=490s. Used on Sanger II launch vehicle. More...
  • ATE Rocketdyne N2O4/MMH rocket engine. 20 kN. Developed 1990's. Advance technology engine for maneuvering stages. Isp=347s. More...
  • ATS 5 cm EOS electric/cesium rocket engine. 0.089 mN. Flown in 1968-1969. Isp=6700s. Thruster for the ATS-4 and ATS-5 tests; consisted of two contact ionization engines using cesium propellant. More...
  • ATS 8 cm EOS electric/cesium rocket engine. 4.5 mN. Flown in 1974. Isp=6700s.Thruster for the ATS-6 test; consisted of two electron bombardment engines using cesium propellant. The thruster anode diameter was 8 cm, and a cesiated tungsten neutralizer was used. 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...
  • Black Arrow-3 British solid rocket engine. 29.4 kN. Out of production. Isp=278s. Used on Black Arrow launch vehicle. First flight 1969. More...
  • BPT-600k Redmond electric/xenon rocket engine. 0.030 kN. In Development, 2005-2006. Isp=1800s. Began as 1995 contract for 600kWe Hall thruster electric propulsion system designed for future interplanetary manned spacecraft. More...
  • BPT-4000 Redmond electric/xenon rocket engine. 270 mN. In Production. Hall effect thruster. Nominal power input 4500 W at 350 V. Isp=1950s. More...
  • BPT-2000 Redmond electric/xenon rocket engine. 120 mN. In Production. Hall effect thruster. Nominal power input 2200 W at 350 V. Isp=1765s. 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...
  • Castor 4AXL Thiokol solid rocket engine. 599.8 kN. In production. Isp=269s. Strap-on booster version, first tested May 1992. Its 30% performance increase would improve performance of Atlas and other vehicles. First flight 2001. More...
  • Castor 4B Thiokol solid rocket engine. 430.6 kN. Out of production. The Castor 4B, which incorporated thrust vector control in the series for the first time, was developed for ESA's Maxus (first flown in 1991). Isp=281s. First flight 1982. More...
  • Castor 4BXL Thiokol solid rocket engine. 429 kN. In Production. Isp=267s. ORBEX version, combined the 4XL motor with 4B's TVC system (6 degree). More...
  • Chariot Bell exotic LF2/Hydrazine rocket engine. 155.9 kN. Titan 3 upper stage. Developed 1960's. Engine developed for high-energy replacement of Titan 3 transtage in late 1950's / early 1960's. Not flown due to toxicity of propellants. More...
  • Cold Gas Thruster Module Parker Bertea nitrogen cold gas thruster. 0.111 kN. In Production. Isp=68s. Designed to provide triaxial attitude control for small launch vehicles. The module comprised three cold gas thrusters operated by integral independent solenoid valves. More...
  • CZ-1C-3 Chinese N2O4/UDMH rocket engine. 107.9 kN. Development ended 1988. Isp=287s. Used on CZ-1C launch vehicle. More...
  • CZ-1D-3 Fourth Academy solid rocket engine. Out of production. Motor for proposed CZ-1D launch vehicle. Isp=291s. First flight 1995. More...
  • DFH-2 AKM Fourth Academy solid rocket engine. 43.460 kN. DFH series apogee kick motor. Out of Production. Isp=287s. First flight 1984. First use in China of glass fibre wound cases, carbon/carbon nozzle throat insert material, contoured divergent nozzle. 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...
  • DOK-50 Isayev monopropellant rocket engine. 0.050 kN. In Production. Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by an iridium-based catalyst, which heated to increase stability. 40,000 ignitions Isp=229s. More...
  • DOK-10 Isayev monopropellant rocket engine. 10 N. In Production. Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by an iridium-based catalyst, which heated to increase stability. 40,000 ignitions Isp=229s. More...
  • DOT-25 Isayev monopropellant rocket engine. 0.025 kN. In Production. Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by a wire catalyst, which is electrically heated to 620 K. 60,000 ignitions Isp=234s. More...
  • DOT-5 Isayev monopropellant rocket engine. 5 N. In Production. Pressure-fed monopropellant engine. Thermal decomposition of hydrazine by a wire catalyst, which is electrically heated to 620 K. 550,000 ignitions Isp=230s. 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-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...
  • 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-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...
  • 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...
  • EPKM Fourth Academy solid rocket engine. 189.994 kN. Isp=292s. Chinese kick stage for use on CZ-2E for launch of Asiasat-2 and Echostar-1. Diameter increased to 1.7 m in comparison to basic 1.4 m diameter motor. Spin stabilised. First flight 1990. More...
  • ESEX Arcjet Redmond electric/ammonia rocket engine. 2 N. In Production. Isp=800s. Electric Propulsion Space Experiment) program begun 1989 under the then Air Force Astronautics Lab. Flew once in 1999 on board the ARGOS satellite. More...
  • Falcon SLV-2 Michoud hybrid rocket Lox/Solid engine. 133 kN. Upper stages. Study 2005. Part of the USAF FALCON program to assess hybrid propulsion applications for a responsive small launch vehicle. More...
  • FSW Retromotor Fourth Academy solid rocket engine. 40.660 kN. In Production. Isp=280s. Retrorocket designed for deorbit of FSW recoverable satellite. First flight 1975. More...
  • FW-4D Thiokol solid rocket engine. 25 kN. Isp=287s. Kick stage motor for Delta E, Delta L. First flight 1965. More...
  • FW-4S TEM640 Thiokol solid rocket engine. 27.4 kN. Isp=280s. Used on Advanced Scout, Scout B, Scout D, Scout F, Scout G. First flight 1965. More...
  • FY-25 Beijing Wan Yuan rocket engine. In Production. Chinese liquid apogee insertion motor. 1800 seconds rated firing time. First flight 1994. More...
  • G-1 Rocketdyne exotic LF2/Hydrazine rocket engine. 53.5 kN. Atlas upper stage. Developed 1960's. Engine developed for replacement of Agena upper stage in late 1950's. Not flown due to toxicity of propellants. NOMAD Upper Stage System. Pressure-fed. Isp=357s. 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...
  • GCRC GCR solid rocket engine. 11.6 kN. Isp=230s. Used on Vanguard launch vehicle. First flight 1957. More...
  • GF-02 Fourth Academy solid rocket engine. 181 kN. CZ-1 launch vehicle. Out of production. Isp=254s. First upper stage, zero-G, vacuum-start solid rocket motor developed in China. Inserted China's first satellite into orbit on 24 April 1970. More...
  • H-1-3 Nissan solid rocket engine. 77 kN. Isp=291s. Used on H-1 launch vehicle. First flight 1986. More...
  • HG-3 Rocketdyne lox/lh2 rocket engine. 1400.7 kN. Study 1967. Isp=451s. High-performance high-pressure chamber engine developed from J-2. Considered for upgrades to Saturn V launch vehicle upper stages. Technology led to Space Shuttle Main Engines. More...
  • HIMES Mitsubishi lox/lh2 rocket engine. 137.3 kN. Design 1999. Isp=452s. Used on H-2 HIMES launch vehicle. More...
  • HiPAT Redmond N2O4/MMH rocket engine. 0.445 kN. In Production. High performance liquid apogee thruster. Isp=323s. More...
  • HM-10 SEP, Ottobrunn lox/lh2 rocket engine. 61.8 kN. Developed 1990's. Engine for potential Ariane 5 upper stage. Isp=443s. More...
  • HM7-A SEP, Ottobrunn lox/lh2 rocket engine. 61.7 kN. Development begun 1973. Out of production. Isp=443s. Used on Ariane 1 launch vehicle. First flight 1979. More...
  • HM7-B SEP, Ottobrunn lox/lh2 rocket engine. 70 kN. Isp=447s. Increased performance version of the HM-7 engine for the Ariane 2 and 3. Combustion chamber pressure raised from 30 to 35 bar and nozzle extended. First flight 1984. More...
  • Ion Notional electric/mercury rocket engine. 0.275 kN. Study 1981. Conceptual ion engine design of the 1970's for a shuttle-sized upper stage. Isp=5300s. More...
  • IPD Rocketdyne lox/lh2 rocket engine. 1100 kN. Development ended 2006. Integrated Powerhead Demonstrator, end goal was flight-rated, full-flow, hydrogen-fueled, staged combustion rocket engine in the 1.1-million-newton thrust class. More...
  • Iris BPD solid rocket engine. 29.4 kN. Out of production. Isp=291s. Used on CZ-1M launch vehicle. More...
  • J-2 Rocketdyne lox/lh2 rocket engine. 1033.1 kN. Study 1961. Isp=421s. Used in Saturn IVB stage in Saturn IB and Saturn V, and Saturn II stage in Saturn V. Gas generator, pump-fed. First flight 1966. More...
  • J-2S Rocketdyne lox/lh2 rocket engine. 1138.5 kN. Developed 1965-1969. Isp=436s. J-2 version proposed for Saturn follow-on vehicles, using results of the J-2X technology program. The engine was simplified while offering improved performance. More...
  • J-2T-200K Rocketdyne lox/lh2 rocket engine. 889.3 kN. Study 1965. Proposed for later versions of Saturn V. Toroidal aerospike plug nozzle version of J-2. Isp=435s. More...
  • J-2T-250K Rocketdyne lox/lh2 rocket engine. 1111.6 kN. Study 1967. Proposed for later versions of Saturn V. Toroidal aerospike plug nozzle version of J-2. Isp=441s. More...
  • J-2X Rocketdyne lox/lh2 rocket engine. 1310 kN. Ares I launch vehicle second stage. In development 2006-2016. Isp=448s. Began as an update to the J-2 engine of the 1960s, but final design was all-new, 20% more thrust, but double the weight. 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...
  • Kestrel SpaceX Lox/Kerosene rocket engine. 30.7 kN. Upper stages. Hardware. Isp=320s. Pintle architecture, designed to be a high efficiency, low pressure vacuum engine. Fed only by tank pressure, ablatively cooled First flight 2006. 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-604 Dushkin Nitric acid/Solid hybrid rocket engine. Out of Production. The KRD-604 engine was developed in the late 1930s by OKB Dushkin. It was a combined (powder+liquid) engine, characterized by a new technical approach. 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-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...
  • 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-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-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-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-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-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-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-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...
  • L7 MBB N2O4/MMH rocket engine. 27.4 kN. In Production. Isp=320s. Used on Ariane 5 launch vehicle. First flight 1996. More...
  • LE-5 Mitsubishi lox/lh2 rocket engine. 103 kN. Isp=450s. Used on H-1 launch vehicle. First flight 1986. More...
  • LE-5A Mitsubishi lox/lh2 rocket engine. 121.5 kN. Isp=452s. Used on H-2 launch vehicle. First flight 1994. More...
  • LE-5B Mitsubishi lox/lh2 rocket engine. 137 kN. In production. Isp=447s. Improved model of the LE-5A for second stage of the H-II rocket; used hydrogen for the cooling of the thrust chamber, then as the gas to drive the turbine. First flight 2001. More...
  • LH2-80k Notional lox/lh2 rocket engine. 355.7 kN. Study 1959. Isp=425s. Used on Nova 4L launch vehicle. 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...
  • 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 LH2 Aerojet lox/lh2 rocket engine. 667 kN. Development ended 1961. Version of the Titan engine, and first large Lox/LH2 engine fired in the world. 52 static tests. But NASA selected Rocketdyne instead to develop the J-2 engine for Saturn from scratch. 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...
  • LR91-3 Aerojet Lox/Kerosene rocket engine. 355.9 kN. Development begun 1957. Titan 1 Stage 2 major production version. Isp=308s. Proposed for second stage of Juno V-A, Super-Jupiter in 1959. Flown 1959-1965. 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...
  • M-1 Aerojet lox/lh2 rocket engine. 5335.9 kN. Study 1961. Isp=428s. Engine developed 1962-1966 for Uprated Saturn and Nova million-pound payload boosters to support manned Mars missions. Reached component test stage before cancellation. More...
  • M-23-J Nissan solid rocket engine. 524.8 kN. In development. Isp=282s. Used on J-1 launch vehicle. First flight 1996. More...
  • M-23-Mu Nissan solid rocket engine. 524 kN. Isp=285s. Used on Mu-3S launch vehicle. First flight 1969. More...
  • M-3B-Mu Nissan solid rocket engine. 132.1 kN. Isp=294s. Used on Mu-3S launch vehicle. First flight 1969. More...
  • M-3B-J Nissan solid rocket engine. 132.1 kN. In development. Isp=294s. Used on J-1 launch vehicle. First flight 1996. More...
  • M-V-4 Nissan solid rocket engine. 52 kN. Isp=298s. Used on M-V launch vehicle. First flight 1997. More...
  • M24 Nissan solid rocket engine. 1245.3 kN. Isp=288s. Used on M-V launch vehicle. First flight 1997. More...
  • M34 Nissan solid rocket engine. 294.2 kN. Isp=301s. Used on M-V launch vehicle. First flight 1997. More...
  • M56A-1 Aerojet solid rocket engine. 228.5 kN. Out of Production. Used in Aries. Isp=297s. More...
  • Mage 1 SEP solid rocket engine. 19.4 kN. Out of production. Orbital circularization motor. Isp=295s. First flight 1979. More...
  • Mage 2 SEP solid rocket engine. 45.5 kN. Orbital circularization motor for Advanced Scout, Ariane 2/3. Isp=293s. First flight 1984. More...
  • Martlet 4-2 Bull solid rocket engine. 20.6 kN. Development ended 1966. Isp=300s. Used on Martlet 4 launch vehicle. More...
  • Martlet 4-3 Bull solid rocket engine. 5.390 kN. Development ended 1966. Isp=300s. Used on Martlet 4 launch vehicle. More...
  • MB-35 Rocketdyne lox/lh2 rocket engine. 156 kN. Design 2004. Isp=467s. Mitsubishi / Boeing joint project for an engine for Delta IV cryogenic upper stages. Expander bleed, pump-fed. More...
  • MB-45 Rocketdyne lox/lh2 rocket engine. 200 kN. Design 2004. Isp=467s. Mitsubishi / Boeing joint project for an engine for Delta IV cryogenic upper stages, announced February 2000. More...
  • MB-60 Rocketdyne lox/lh2 rocket engine. 266.7 kN. Design 2004. Isp=467s. Mitsubishi / Boeing joint project for an engine for Delta IV cryogenic upper stages. Expander bleed, pump-fed. More...
  • MIHT-2 solid rocket engine. 490.3 kN. Start-2. In production. Used in Start-2. Estimated values. Isp=280s. First flight 1993. More...
  • MIHT-3 MIHT solid rocket engine. 245.2 kN. Start-3. In production. Used in Start-3. Estimated values. Isp=280s. First flight 1993. More...
  • MIHT-4 MIHT solid rocket engine. 9.8 kN. Start-4. In production. Used in Start-4. Estimated values. Isp=295s. First flight 1993. More...
  • MR-103 Redmond hydrazine monopropellant rocket engine. 1.12 N. Attitude control thruster for Voyager, GPS, Intelsat 5, MMAS 3000, 4000,. 5000, and 7000, Mars Observer, ACTS, and Magellan. In Production. Isp=227s. First flight 1974. More...
  • MR-104 Redmond hydrazine monopropellant rocket engine. 0.441 kN. Attitude control and velocity corrections, Voyager, Magellan, DMSP, Tiros N, Landsat. In Production. Isp=239s. First flight 1977. More...
  • MR-106 Redmond hydrazine monopropellant rocket engine. 0.027 kN. Spacecraft and upper stage attitude control and velocity corrections, PAM A/S,. Radarsat, GPS Block 2R, HAS/Peace Courage, Titan Centaur, Atlas Centaur. In Production. Isp=232s. More...
  • MR-107 Redmond hydrazine monopropellant rocket engine. 0.257 kN. Spacecraft and upper stage attitude control and dV corrections, Delta 2, Titan 2, PAM D, SICBM, HAS/Peace Courage, Atlas roll control module, STEP, Pegasus. Isp=236s. First flight 1990. More...
  • MR-111 Redmond hydrazine monopropellant rocket engine. 4.4 N. Attitude control, Intelsat 5, ERBS, ACTS, Radarsat, MMAS 4000, 5000, and. 7000, Wind/Polar Landsat, and Mars Observer. In Production. Isp=229s. First flight 1980. 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-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...
  • MR-510 Redmond Hydrazine rocket engine. 254 mN. In Production. Arcjet system. Isp=600s. More...
  • MR-508 Redmond hydrazine monopropellant rocket engine. 230 mN. Communications satellite N-S stationkeeping, MMAS 7000. In Production. Isp=502s. First flight 1993. More...
  • MR-502 Redmond hydrazine monopropellant rocket engine. 500 mN. Communications satellite N-S stationkeeping, MMAS 5000. In Production. Isp=304s. First flight 1991. More...
  • MR-50 Redmond hydrazine monopropellant rocket engine. 0.022 kN. Attitude control for SMS, Viking, Metosat, GOES, Voyager, GPS, Intelsat 5,. Scatha, MMAS 5000, Delta Star, Magellan, Wind/Polar. In Production. Isp=228s. First flight 1974. 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...
  • MRE-15/OMV TRW hydrazine monopropellant rocket engine. 0.089 kN. In Production. Isp=225s. Mono-propellant Hydrazine Thrusters. 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...
  • MRM-122 Redmond Hydrazine rocket engine. 0.142 kN. In Production. Steady-state thrust 51 N. Isp=228s. More...
  • MTV Motor SpaceDev N2O/Solid hybrid rocket engine. Upper stages. Small hybrid rocket motor designed for use in the Maneuver and Transfer Vehicle, an upper stage orbital transfer motor. Tested 2001. 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...
  • Nerva 12 GW Notional nuclear/lh2 rocket engine. Study 1959. Used on Hyperion launch vehicle. More...
  • NERVA 1mlbf Notional nuclear/lh2 rocket engine. 8963 kN. DAC Helios, DAC Helios ISI studies 1963. Isp=850s. More...
  • Nerva 2 DoE nuclear/lh2 rocket engine. 867.4 kN. Developed 1950-74. Isp=825s. More...
  • Nerva Alpha DoE nuclear/lh2 rocket engine. 71.7 kN. Study 1972. The final Nerva Alpha flight engine reference configuration as documented at the end of its development. Isp=860s. More...
  • Nerva Gamma DoE nuclear/lh2 rocket engine. 81 kN. Study 1972. Isp=975s. The final Nerva Gamma flight engine was an improved version of the Alpha, a small engine that could be launched together with its stage and a payload in a single space shuttle launch. More...
  • Nerva NTR DoE nuclear/lh2 rocket engine. 333.4 kN. Study 1991. Late 1980's update of 1960's Nerva design. Isp=925s. More...
  • Nerva DoE nuclear/lh2 rocket engine. 266 kN. Study 1968. Early version of Nerva engine proposed for use in Saturn and RIFT configurations in 1961. Isp=800s. More...
  • Nihka Bristol Aerospace solid rocket engine. 50.5 kN. Upper stages. Out of production. Isp=284s. Used on Black Brant 10 launch vehicle. First flight 1981. 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...
  • NK-15VM Kuznetsov lox/lh2 rocket engine. 1960 kN. N-1 stage 2 (block B) replacement. Design 1972. Derivative of NK-15 with kerosene replaced by hydrogen. Canceled before hot-tests. More...
  • NK-21 Kuznetsov Lox/Kerosene rocket engine. N-1 stage 3 (block V). Out of production. Based on NK-9 engine. Propellants kerosene T-1 / LOX. 4 engines used in N-1 stage 3 (block V). Isp=318s. Used on N1 launch vehicle. First flight 1969. More...
  • NK-35 Kuznetsov lox/lh2 rocket engine. 1960 kN. Design 1972. Derivative of the NK-15 with kerosene replaced by hydrogen. The engine was canceled before hot-tests. Proposed for the UR-700M Mars booster in 1972, but this was not approved either. More...
  • NK-39 Kuznetsov Lox/Kerosene rocket engine. 402 kN. N-1F stage 3. Development ended 1971. Isp=352s. Modified version of original engine with multiple ignition capability. Never flown and mothballed after the cancellation of the N1. More...
  • NK-43 Kuznetsov Lox/Kerosene rocket engine. 1755 kN. N-1F, Kistler stage 2. Design 1975. Isp=346s. Modified version of original engine with multiple ignition capability. Never flown and mothballed after the cancellation of the N1. Resurrected for Kistler. More...
  • NK-9V Kuznetsov Lox/Kerosene rocket engine. 441.3 kN. N-1 stage 2 / N-1 stage 3 / R-9 Stage 2. Developed for 2nd stage of the R-9 ICBM (alternative to RD-111 engine by OKB-456). NK-9 with increased expansion ratio. Isp=340s. First flight 1965. More...
  • NK-9V-11D53 Kuznetsov Lox/Kerosene rocket engine. 449 kN. N-1 stage 3 (block V). Out of Production. Modification of NK-9 engine for the N-1 lunar rocket. May be identical to NK-21 (stage 3). Isp=340s. More...
  • NK-9V-11D54 Kuznetsov Lox/Kerosene rocket engine. 392 kN. N-1 stage 4 (block G). Out of Production. Modification of NK-9 engine for the N-1 lunar rocket. May be identical to NK-19 (stage 4). Isp=340s. More...
  • NOTS-4 NOTS solid rocket engine. 0.700 kN. Out of production. Isp=250s. Used on Caleb launch vehicle. First flight 1960. More...
  • NOTS 100A NOTS solid rocket engine. Used on Blue Scout Junior launch vehicle. First flight 1960. More...
  • NOTS-3 NOTS solid rocket engine. 2.260 kN. Out of production. Isp=250s. Used on Caleb launch vehicle. First flight 1960. More...
  • Nuclear 12 Gw Notional nuclear/lh2 rocket engine. 2892 kN. Helios A, Helios C study 1960. Nuclear second stage. Isp=830s. More...
  • Nuclear 14 Gw Notional nuclear/lh2 rocket engine. 3334 kN. Study 1960. Nuclear second stage Isp=830s. Used on Helios B launch vehicle. More...
  • OPI Methane Engine Orion Propulsion Lox/LCH4 rocket engine. 0.445 kN. Reaction control thruster for future manned spacecraft. Developed from 2001; tested 2005. More...
  • Orbitec Methane Engine Orbital Technologies Corporation Lox/LCH4 rocket engine. 0.133 kN. Reaction control thruster. Tested 2005. Used vortex-cooled combustion process to eliminate combustion chamber heating. More...
  • Ottobrunn 300N Ottobrunn lox/lh2 rocket engine. 300 N. Upper stages. Developed 2000. Isp=415s - highest value ever achieved in Europe for an engine of such small size. More...
  • P320 Rocketdyne, Friedrichshafen lox/lh2 rocket engine. Development. Launch thrust 129 kN. BORD 1/P320 BOELKOW (Germany)/Rocketdyne Technology. Pressure-fed. More...
  • P4 SNPE solid rocket engine. 176.5 kN. Out of Production. Isp=273s. Used on Diamant B launch vehicle. First flight 1970. More...
  • P6 SNPE solid rocket engine for Diamant launcher. 29.4 kN. Out of production. Isp=211s. First flight 1965. More...
  • P78-2 Hughes electric/xenon rocket engine. 0.14 mN. Flown in 1979. Isp=350s. The thruster for the Scatha experiment consisted of one electron bombardment engines using xenon propellant. More...
  • Pegasus-3 Hercules solid rocket engine. 34.6 kN. Isp=287s. Upper stage engine for Pegasus, Pegasus XL, Taurus. First flight 1989. More...
  • Pegasus XL-2 Hercules solid rocket engine. 153.5 kN. Isp=290s. Used on Pegasus XL launch vehicle. First flight 1994. More...
  • Pegasus-2 Hercules solid rocket engine. 118.2 kN. Isp=290s. Used on Pegasus, Taurus. First flight 1989. More...
  • Perigee Orbit Transfer Motor Fourth Academy solid rocket engine. 222.840 kN. In Production. Isp=280s. Basic perigee kick motor for CZ-2E launch vehicle. Featured glass fibre-wound case, HTPB propellant, 3-D finocyl propellant grain, and carbon/carbon throat insert. First flight 1990. 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 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 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...
  • Program 661 EOS electric/cesium rocket engine. 8.9 mN. Flew 1962-1964. Isp=7400s. Cesium contact ion propulsion system used on three sub-orbital flight tests aboard Blue Scout Junior launch vehicles. More...
  • PRS-101 Redmond electric/teflon rocket engine. 1.24 mN. In Production. Pulsed plasma thruster system. Completely solid state propulsion. Up to 100 W input power at 28 V DC, thrust to power ratio 12.4 microN/W. Isp=1350s. More...
  • PSLV-3 ISRO solid rocket engine. 328.7 kN. Isp=291s. Used on PSLV launch vehicle. First flight 1993. More...
  • PSLV-4 ISRO N2O4/MMH rocket engine. 7 kN. Isp=308s. Used on PSLV launch vehicle. First flight 1993. 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-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 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-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-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-0234-CH Kosberg Lox/LCH4 rocket engine. 442 kN. Developed 1996-. Proposed variant of RD-0234 engine using LOX-liquid methane instead of N2O4/UDMH as propellants. Isp=343s. 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-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-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-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-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-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-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-0210-HC Kosberg Lox/Kerosene rocket engine. 592 kN. Design concept 1990's. Proposed variant of RD-0210 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=342s. 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-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-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-0221 Kosberg N2O4/UDMH rocket engine. 78 kN. upper stage of unnamed missile by Mishin. Developed 1965-70. Isp=330s. 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-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-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-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-0256-Methane Kosberg Lox/LCH4 rocket engine. 836 kN. Design concept 1996-. Proposed variant of RD-0256 engine using LOX-liquid methane instead of N2O4/UDMH as propellants. Isp=353s. More...
  • RD-0146 Kosberg lox/lh2 rocket engine. 98.1 kN. Centaur upper stage (Atlas); high performance upper stages for Onega, Proton, Angara launch vehicles. Design concept 1998-. Isp=463s. More...
  • RD-0410 Kosberg nuclear/lh2 rocket engine. 35.3 kN. Experimental nuclear engine, propellant LH2. Developed 1965-94. Isp=910s. Tested at Semipalatinsk test range in 1980s and was "the only operational nuclear engine in the USSR". First flight 1985. More...
  • RD-0411 Kosberg nuclear/lh2 rocket engine. 392 kN. Full-size nuclear thermal engine. Design concept 1965-94. Planned full-size nuclear thermal engine for Mars expeditions. Never progressed beyond study stage. Isp=900s. More...
  • RD-0600 Kosberg laser rocket engine. Space station "Skif". Developed 1970-85. Gas dynamic laser. Working medium gaseous carbon monoxide + air + nitrogen + ethanol. Flow rate up to 100 kg/s. Tests were performed at NII TP. More...
  • RD-0750 Kosberg lox/lh2/kerosene rocket engine. 1412 kN. Alternative for Angara central stage, MAKS. Developed 1997-. Isp=455s. Tripropellant derivative of RD-0120. Some components tested in RD-0120TD technology demonstration in cooperation with Aerojet. More...
  • RD-0256-HC Kosberg Lox/Kerosene rocket engine. 820 kN. Design concept 1996-. Proposed variant of RD-0256 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=344s. More...
  • RD-0124M Kosberg Lox/Kerosene rocket engine. 294.3 kN. Developed 1998-. Proposed single chamber variant of RD-0124. Obviously same turbopumps, but one single chamber. Isp=348s. More...
  • RD-0105 Kosberg Lox/Kerosene rocket engine. 49.4 kN. Luna 8K72, Vostok 8K72 upper stage. Out of production. Isp=316s. Developed jointly with OKB-1 in nine months on the basis of OKB-1'ssteering chamber from the RD-107 engine. First flight 1958. More...
  • RD-0106 Kosberg Lox/Kerosene rocket engine. 304 kN. R-9 stage 2. Gas generator cycle. Isp=330s. First flight 1961. More...
  • RD-0107 Kosberg Lox/Kerosene rocket engine. 297.9 kN. R-9, Molniya 8K78, Voskhod 11A57 stage 3. Out of Production. Gas generator cycle. Isp=326s. More...
  • RD-0108 Kosberg Lox/Kerosene rocket engine. 297.9 kN. Voskhod 11A57, Molniya 8K78 stage 3. Isp=326s. First flight 1960. More...
  • RD-0109 Kosberg Lox/Kerosene rocket engine. 54.520 kN. 8A92 Vostok stage 3, 8K72K stage 3 (block E-Vostok). Out of production. Developed in 15 months. Isp=323s. First flight 1960. More...
  • RD-0110 Kosberg Lox/Kerosene rocket engine. 297.9 kN. Soyuz 11A511, Molniya-M 8K78M. Precursor RD-0107 used in 11A57 Voskhod stage 2. Modified to increase reliability. Isp=326s. First flight 1964. More...
  • RD-0110MD Kosberg Lox/LNG rocket engine. 245 kN. Developed 1994-on. Prototype engine for tests with propellants LOX/liquified natural gas. Tests performed from 30 April 1998 on, test duration 20s. More...
  • RD-0120TD Kosberg tri-propellant (lox/lh2/kerosene) rocket engine. 1317 kN. Developed 1990's. Isp=419 / 452s. Experimental version of the RD-0120 engine. Tested by supply of high-pressure kerosene from test bench or adapted existing kerosene pump for tests. More...
  • RD-0154 Kosberg Lox/Kerosene rocket engine. 294.3 kN. Design concept 2007. Engine proposed to replace RD-110 in Avrora improved version of Soyuz launch vehicle. The single chamber engine had a deployable nozzle extension for improved vacuum specific impulse. More...
  • RD-0124 Kosberg Lox/Kerosene rocket engine. 294.3 kN. In development. Isp=359s. Engine to succeed RD-0110 in second stage of Soyuz. Used staged combustion; chamber pressure increased from 70 to 160 bar, specific impulse from 326 to 359 seconds First flight 2001. 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-0124M1 Kosberg Lox/Kerosene rocket engine. 294.3 kN. Developed 1998-. Proposed single chamber variant of RD-0124. Obviously same turbopumps, but one single chamber with larger nozzle extension compared to RD-0124M. Isp=359s. More...
  • RD-0126 Kosberg lox/lh2 rocket engine. 39.2 kN. Space tugs or upper stage for Onega or Yastreb versions of Soyuz. Isp=476s. Single annular chamber with expansion-deflection nozzle, separate turbopumps. Design concept 1993. Hot-tests in 1998. More...
  • RD-0126A Kosberg lox/lh2 rocket engine. 98 kN. Upper stages. Design concept 1996-. Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump. Isp=476s. More...
  • RD-0149 Kosberg Lox/LNG rocket engine. 49 kN. upper stage. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Variant of RD-0141 with larger nozzle. Isp=370s. More...
  • RD-0122 Kosberg lox/lh2 rocket engine. 2313 kN. Energia-M core stage. Planned for Angara central stage. Developed 1990-. Isp=460s. Upgrade of RD-0120 engine for Energia-M launcher with increased thrust. Prototype from RD-0120 hardware. 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-0126E Kosberg lox/lh2 rocket engine. 39.2 kN. Upper stages. Design concept 1998-. Concept for a cryogenic engine for upper stages. Single annular chamber with straight expansion nozzle, common turbopump. Isp=472s. More...
  • RD-0145 Kosberg Lox/LNG rocket engine. 147 kN. upper stage. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Four-chamber variant of RD-0144. Isp=374s. More...
  • RD-0144 Kosberg Lox/LNG rocket engine. 147 kN. upper stage. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Radiation cooled nozzle extension. Isp=374s. More...
  • RD-0143 Kosberg Lox/LNG rocket engine. 343 kN. Vozdushnyy Start stage 2. Design concept 1998-. Proposed variant of RD-0124, replacing kerosene by liquid natural gas. Selected for stage 2 of Vozdushnyy Start project by Kompomash. Isp=372s. More...
  • RD-0140 Kosberg Lox/LNG rocket engine. 2086 kN. stage 2. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Gas generator cycle with turbine gas injection into supersonic nozzle. Isp=349s. More...
  • RD-0133 Kosberg lox/lh2 rocket engine. 98 kN. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. Four chambers with bell nozzles, common turbopump. Isp=467s. More...
  • RD-0132M Kosberg Lox/LNG rocket engine. 98 kN. Vozdushnyy Start stage 2. Design concept 1998-. Proposed variant of RD-0132, replacing hydrogen by liquid natural gas. Initially selected for stage 2 of Vozdushnyy Start project by Kompomash. More...
  • RD-0132 Kosberg lox/lh2 rocket engine. 98 kN. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. Derived from RD-0131, but four chambers with bell nozzles, common turbopump. Isp=469s. More...
  • RD-0131 Kosberg lox/lh2 rocket engine. 98 kN. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump. Isp=467s. More...
  • RD-0128 Kosberg lox/lh2 rocket engine. 98 kN. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. One single chamber with bell nozzle, separate turbopumps. Isp=474s. More...
  • RD-0142 Kosberg Lox/LNG rocket engine. 2353 kN. stage 2. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Obviously variant of RD-0141 with larger nozzle. Isp=369s. More...
  • RD-192S Glushko Lox/LCH4 rocket engine. 2128 kN. Developed 1996-on. Isp=371s. Proposed variant of RD-192. Staged combustion cycle with oxidizer-rich gas generator. Gimbaling +/- 8 degree in two planes. More...
  • RD-161-2 Glushko Lox/Kerosene rocket engine. 19.9 kN. Design concept 1990's. Proposed for use on Soyuz M-3. Version with uncooled nozzle extension. Engine Cycle: closed gas generator. Feed Method: turbopump. Isp=365s. More...
  • RD-161P Glushko H2O2/Kerosene rocket engine. 24.5 kN. Soyuz M stage 3 (block LM). Developed 1993-. Two thrust levels. Minimum 1500 kgf. Proposed for use on Soyuz M-3. Version for H2O2 fuel, concentration 96-98%. Isp=319s. More...
  • RD-167 Glushko Lox/LCH4 rocket engine. 353 kN. Upper stage. Design concept 1990's. Isp=379s. Proposed upper stage engine, a methane variant of RD-134. Gimbaling +/- 3 degree in two planes. Four chambers with one common turbopump. More...
  • RD-183 Glushko Lox/LCH4 rocket engine. 9.8 kN. Developed 1996-. Isp=360s. Main engine for apogee stage of Riksha-1 launcher project. Gimbaling +/- 10 degree in two planes. Nozzle expansion ratio is 75/0.055=1364. More...
  • RD-184 Glushko Lox/LCH4 rocket engine. Developed 1996-on. Isp=322s. Attitude correction engine for apogee stage of Riksha-1 launcher project (together with RD-183). Gimbaling +/- 20 degree in two planes. More...
  • RD-185 Glushko Lox/LCH4 rocket engine. 179 kN. Riksha-0 stage 2. Developed 1996-. Isp=378s. Upper stage version of RD-169 with larger nozzle. Gimbaling +/- 4 degree in two planes. More...
  • RD-192 Glushko Lox/LCH4 rocket engine. 2138 kN. Isp=356s. Proposed methane-variant of RD-191. Gimbaling +/- 8 degree in two planes. In 1996 prototype development was estimated to take four years from go-ahead. Nozzle expansion ratio is 262/0.75=349. More...
  • RD-161-1 Glushko Lox/Kerosene rocket engine. 19.6 kN. Development ended 2000. Proposed for use on Soyuz M-3. Basic version. Engine Cycle: closed gas generator. Feed Method: turbopump. Isp=360s. More...
  • RD-192.3 Glushko Lox/LCH4 rocket engine. 2089 kN. Developed 1996-on. Proposed variant of RD-192. Gas generator cycle. Gimbaling +/- 8 degree in two planes. Status 1998 was project based on RD-191 protoype, development estimated for four years. Isp=341s. More...
  • RD-120.03 Glushko Lox/Kerosene rocket engine. 882 kN. Design concept. Isp=353s. More...
  • RD-192.2 Glushko Lox/LCH4 rocket engine. 1942 kN. Developed 1996-on. Isp=354s. Proposed variant of RD-192. Staged combustion cycle with fuel-rich gas generator. Gimbaling +/- 8 degree in two planes. More...
  • RD-120 Glushko Lox/Kerosene rocket engine. 833 kN. Zenit stage 2. In production. Isp=350s. High altitude engine used in the Zenit second stage. First production Russian engine to be test fired in the United States (3 test burns were made). First flight 1985. More...
  • RD-160 Glushko Lox/LCH4 rocket engine. 19.6 kN. Upper stage. Developed 1993-1996. Isp=380s. Methane version of lox / kerosene upper stage engine RD-161. Gimbaling +/- 6 degree in two planes. More...
  • RD-109 Glushko lox/udmh rocket engine. 101.6 kN. Developed 1957-60. Isp=334s. Intended for second stage of Lox/UDMH 8K73 version of R-7. Abandoned because of Korolev's refusal to use such a toxic fuel. Later basis for RD-119 used on the Kosmos space launcher. More...
  • RD-113 Glushko lox/udmh rocket engine. 1138 kN. ICBM stage 2 (stage 1 was RD-112). Developed 1960. Upper stage version of RD-112 with larger nozzle. Isp=360s. More...
  • RD-119 Glushko lox/udmh rocket engine. 105.5 kN. Kosmos 1 stage 2. Out of production. Isp=352s. Derived from RD-109 motor originally intended for the second stage of a Lox/UDMH version of the R-7. First flight 1961. More...
  • RD-120.01 Glushko Lox/Kerosene rocket engine. 784 kN. Design concept. Isp=329s. More...
  • RD-134R Glushko Lox/Kerosene rocket engine. 343 kN. Angara stage 2 vernier. Design concept 1993-on. Proposed in initial study for Angara by RKK Energia in1993. Steering engines for Angara upper stage. Kerosene RG-1. More...
  • RD-134 Glushko Lox/Kerosene rocket engine. 343 kN. upper stage. Design concept. Isp=357s. Proposed upper stage kerosene engine. Gimbaling +/- 3 degree in two planes. Four chamber s with one common turbopump. Nozzle expansion ratio is 170/0.05=3400. More...
  • RD-108-8D727K Glushko Lox/Kerosene rocket engine. 976 kN. Molniya 8K78-3. Out of Production. Isp=316s. More...
  • RD-135 Glushko lox/lh2 rocket engine. upper stage. Developed -1976. Experimental cryogenic engine. (Ref. May be not correct.) More...
  • RD-146 Glushko Lox/Kerosene rocket engine. 883 kN. Angara stage 2. Design concept 1993-on. Sea-level variant of RD-120 engine. Proposed in initial study for Angara by RKK Energia in1993. Kerosene RG-1. More...
  • RD-115 Glushko lox/udmh rocket engine. 1726 kN. ICBM stage 2 (stage 1 was RD-114). Developed 1961-65. Upper stage version of RD-114 with larger nozzle. Isp=357s. 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-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-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-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-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-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-221 Glushko Nitric acid/UDMH rocket engine. 1118 kN. missile stage 2 (stage 1 used RD-220). Developed 1960-. Isp=318s. 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-350 Glushko exotic LF2/LH2 rocket engine. 98 kN. Design concept 1963-. Studied by Glushko as engine concept with high-energy propellants. Isp=464s. More...
  • RD-301 Glushko exotic LF2/Ammonia rocket engine. 96.670 kN. Proton K stage 4. Developed 1965-77. Developed by Glushko beginning in 1965. Planned for use in Proton K-4H high energy upper stage. Motor tested but never flown. Isp=400s. First flight 1977. More...
  • RD-302 Glushko exotic LF2/Ammonia rocket engine. 98 kN. Developed 1960-69. Successor to RD-303 and predecessor to RD-301. Staged combustion cycle. Isp=405s. More...
  • RD-303 Glushko exotic LF2/Ammonia rocket engine. Developed 1960-65. Predecessor to RD-302 and RD-301. More...
  • RD-410 Glushko nuclear/lh2 rocket engine. 68 kN. UR-700M concept. Developed 1960s. More...
  • RD-58MF Korolev Lox/Kerosene rocket engine. 83.4 kN. In Production. Isp=353s. Multi-function variant of RD-58 for uprated upper stages applications (Zenit stage 3, Angara). Block-DM-SL for Sea-Launch may have used RD-58M. More...
  • RD-56M LNG Isayev Lox/LNG rocket engine. 73.5 kN. Vozdushnyy Start stage 2. Developed 1996-. Variant of RD-56M using liquid natural gas in place of hydrogen. First engine tests performed in 1998. More...
  • RD-58M Korolev Lox/Kerosene rocket engine. 83.4 kN. Proton 8K824K / 11S824M; 11S824F; 11S86; 11S861; 17S40 stage 4 (block DM). In production. Isp=353s. First flight 1974. More...
  • RD-58 Korolev Lox/Kerosene rocket engine. 83.4 kN. Isp=349s. High-performance upper-stage engine developed for N1 lunar crasher stage, but saw general use as restartable Block D upper stage of Proton launch vehicle. First flight 1967. More...
  • RD-57M Lyulka lox/lh2 rocket engine. 397 kN. Vulkan Blok V. Development ended 1976. Isp=461s. Version with extendible nozzle. Length 4.06 / 2.61 m. Specific impulse 461 / 448 sec. Area ratio 170 / 87.6. More...
  • RD-57A-1 Lyulka lox/lh2 rocket engine. 395 kN. Developed 1995-98. Isp=460s. New version of RD-57M for SSTO-demonstrator proposed by Aerojet. Optimized nozzle contour for performance increase, new chamber material for weight reduction. More...
  • RD-57 Lyulka lox/lh2 rocket engine. 392 kN. N1 Block S (N-1M). Study 1965. One to have been used in N1 Block S. In fixed chamber version, 3 to 6 to have been used in N1 Block V-III. Engine system includes roll control thruster with 1.29 kN thrust. Isp=456s. More...
  • RD-58S Korolev Lox/Kerosene rocket engine. 86.3 kN. Proton 8K82K / 11S861-01 stage 4 (block DM). Version 17D12 for Buran OMS. Version uses synthetic kerosene ('Sintin') for higher specific impulse. Isp=361s. First flight 1994. More...
  • RD-56 Isayev lox/lh2 rocket engine. 69.6 kN. N1 block R. Development ended 1971. Oxygen-hydrogen engine for cryogenic upper stage. Developed but never flown. Design sold to India in 1990's for GSLV. Isp=462s. More...
  • RD-550 Glushko exotic rocket engine. 98.060 kN. Experimental upper stage engine. Developed 1963-70. Isp=400s. Propellants Lox/30% Beryllium+Pentaborane in 70% Hydrazine. More...
  • RD-54 Lyulka lox/lh2 rocket engine. 392 kN. N1 concept stage III. Developed 1960-75. Isp=440s. More...
  • RD-511 Glushko H2O2/CxHy rocket engine. Developed 1965-75. First flight 1975. More...
  • RD-510T Glushko H2O2/CxHy rocket engine. Developed 1965-75. First flight 1975. More...
  • RD-510 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-56M Isayev lox/lh2 rocket engine. 73.580 kN. Proton and Angara upper stage KVRB, 12KRB upper stage for GSLV (India). In development. Isp=461s. First flight 2001. More...
  • RD-58Z Korolev Lox/Kerosene rocket engine. 71 kN. Zenit stage 3. Developed 1981-1990. Isp=361s. More...
  • RD-600 Glushko nuclear/lh2 rocket engine. 1960 kN. Isp=2000s. Gas core nuclear engine worked developed 1962-1970 for use in second stage of two-stage interplanetary rockets. 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-704 Glushko Lox/Kerosene/LH2 tripropellant engine. 1966 kN. Developed 1990's. Isp=407 / 452 s. Tripropellant engine, single chamber, derived from RD-701 project. Chamber pressure 294 / 124 bar. First flight 1999. 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-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-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-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-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-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-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-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-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-802 Yuzhnoye Lox/Kerosene rocket engine. 19.6 kN. Upper stages. Design concept 2007. Isp=344s. Derivative of the RD-8 Zenit-2 second stage vernier thrust engine combustion chamber for use in launch vehicle upper stages. 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-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-8 Yuzhnoye Lox/Kerosene rocket engine. 78.4 kN. Zenit stage 2 attitude control engine. In Production. Isp=342s. Four-chamber pump-fed single-run engine operated in a staged combustion scheme with afterburning of the generator gas. Development began in 1976. More...
  • RD-809 Yuzhnoye Lox/Kerosene rocket engine. 88 kN. Upper stages. Isp=345s. 2007 design concept for a four-chamber restartable main engine for launch vehicle upper stages. 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-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-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-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-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...
  • 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-2600 NII Mash GOX/Alcohol rocket engine. 2.6 kN. Developed 1980's. Experimental low-thrust thruster. Isp=270s. 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-8 X NII Mash N2O4/UDMH rocket engine. 8 N. Developed 1980's. Experimental low-thrust thruster. Isp=296s. More...
  • RDMT-200K NII Mash GOX/Kerosene rocket engine. 0.200 kN. Buran. Out of Production. Low-thrust attitude control thruster. Mass in ref. NIIMash 95 given as only 2.5 kg. Isp=265s. 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-0.8 NII Mash nitrogen+helium cold gas thruster. 800 mN. Kosmos satellites. In Production. Low-thrust cold-gas thruster. Specific impulse 70 / 160 sec. Isp=70s. 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...
  • REA 22-17 Marquardt hydrazine monopropellant rocket engine. 0.178 kN. In Production. More...
  • REA 39-2 Marquardt hydrazine monopropellant rocket engine. 2.22 N. In Production. More...
  • REA 22-16 Marquardt hydrazine monopropellant rocket engine. 0.130 kN. In Production. More...
  • REA 22-2 Marquardt hydrazine monopropellant rocket engine. 0.090 kN. In Production. More...
  • REA 17-6 Marquardt hydrazine monopropellant rocket engine. 2.22 N. In Production. More...
  • REA 22-5 Marquardt hydrazine monopropellant rocket engine. 0.050 kN. In Production. More...
  • REA 17-12 Marquardt hydrazine monopropellant rocket engine. 4.45 N. In Production. More...
  • REA 16 Marquardt hydrazine monopropellant rocket engine. 0.020 kN. In Production. More...
  • REA 10 Marquardt hydrazine monopropellant rocket engine. 890 mN. In Production. More...
  • REA 20-4 Marquardt hydrazine monopropellant rocket engine. 0.556 kN. In Production. More...
  • RL-10B-X Pratt and Whitney lox/lh2 rocket engine. 93.4 kN. Design concept 1994. Isp=470s. More...
  • RL-10C Pratt and Whitney lox/lh2 rocket engine. 155.7 kN. In Production. Used in Delta 3 - 2. Isp=450s. First flight 1998. More...
  • RL-10B-2 Pratt and Whitney lox/lh2 rocket engine. 110 kN. In production. Isp=462s. Used on Delta 3 , Delta IV launch vehicles. First flight 1998. Extendable exit cone for increased specific impulse; electromechanical actuators replace hydraulic systems. More...
  • RL-10A-4-2 Pratt and Whitney lox/lh2 rocket engine. 99.1 kN. In production. Isp=451s. Used on Atlas IIIB launch vehicle. First flight 2002. Two engines; electro-mechanical thrust vector control actuators replaced earlier hydraulically actuated system. More...
  • RL-10A-4-1 Pratt and Whitney lox/lh2 rocket engine. 99.1 kN. Out of production. Isp=451s. Used on Atlas IIIA launch vehicle. First flight 2000. Version with one of engines removed; remaining engine re-positioned to center-mount; new electro-mechanical gimbals. More...
  • RL-10A-3A Pratt and Whitney lox/lh2 rocket engine. 73.4 kN. Isp=444s. Used on Centaur stage atop Atlas G, Atlas I, Atlas II, Titan 4. First flight 1984. More...
  • RL-10A-3 Pratt and Whitney lox/lh2 rocket engine. 65.6 kN. Study 1968. Isp=444s. First flight 1967. More...
  • RL-10 Pratt and Whitney lox/lh2 rocket engine. 66.7 kN. Isp=410s. Early version as proposed for Nova A, Nova B, Saturn B-1, Saturn C-2, Saturn C-3, Saturn I. First flight 1961. More...
  • RL-10A-1 Pratt and Whitney lox/lh2 rocket engine. 66.7 kN. Isp=425s. Version used on Atlas Centaur LV-3C, and proposed for various early Saturn launch vehicle designs. First flight 1961. More...
  • RL-10C-X Pratt and Whitney lox/lh2 rocket engine. 110.8 kN. Design concept 1994. Isp=450s. More...
  • RL-10A-4 Pratt and Whitney lox/lh2 rocket engine. 92.5 kN. Out of production. Isp=449s. Centaur stage for Atlas IIA, Atlas IIAS. First flight 1992. More...
  • RL-50 Pratt and Whitney lox/lh2 rocket engine. 290 kN. Development. Isp=472s. Advanced, high-performance upper-stage rocket engine proposed by Pratt & Whitney for both domestic and international launch vehicles. More...
  • RL-60 Pratt and Whitney lox/lh2 rocket engine. 289.1 kN. Design. Isp=470s. Upper stage engine to have been developed by Pratt and Whitney with several international partners. Same dimensions as the RL-10, but over twice the thrust. More...
  • RLA-300 Glushko Lox/Kerosene rocket engine. 3187 kN. Design 1974. Proposed for the RLA series launch vehicles and the UR-700M Mars booster. Following rejection of RLA, design 'down-sized' to 200 tonnes thrust for Energia and Zenit. More...
  • RO-31 Kosberg nuclear/lh2 rocket engine. 392 kN. UR-700 Third Stage. Study 1967. Engine proposed for UR-700 third stage to achieve 250 tonne payload to low earth orbit. Probably closely related to RD-0411. More...
  • RS-2200 Rocketdyne lox/lh2 rocket engine. 2201 kN. Development cancelled 1999. Isp=455s. Linear Aerospike Engine developed for use on the Lockheed Reusable Launch Vehicle, the production follow-on to the X-33. More...
  • RSA-3-2 South African solid rocket engine. 519 kN. In production. Built in both Israel and South Africa for RSA-3 and Shavit. Source: Missile exhibit and placards, AF Museum, South Africa. Isp=284s. First flight 1988. More...
  • RSA-3-3 South Africansolid rocket engine. 51 kN. In production. Israeli AUS-51 rocket motor, built in both Israel and South Africa. Isp=292s. Upper stage engine for RSA-3, RSA-4, Shavit, Shavit 1. First flight 1988. More...
  • RSA-4-2 South African solid rocket engine. 676 kN. Development ended 1994. Isp=275s. Used on RSA-4 launch vehicle. More...
  • S-30 IAE solid rocket engine. 20.490 kN. Development ended 1997. Isp=275s. More...
  • S-4 Rocketdyne Lox/Kerosene rocket engine. 412.8 kN. Design ca. 1957. Version of Atlas sustainer tailored to Redstone Arsenal upper-stage requirements. Paper study only. Used on Super Jupiter launch vehicle. More...
  • S-40TM IAE solid rocket engine. 208.4 kN. Isp=272s. Used on VLS launch vehicle. First flight 1985. More...
  • S-43TM IAE solid rocket engine. 321.7 kN. Isp=276s. Used on VLS launch vehicle. First flight 1985. More...
  • S-44 IAE solid rocket engine. 33.2 kN. Isp=282s. Used on VLS launch vehicle. First flight 1985. More...
  • S1.5400 Korolev Lox/Kerosene rocket engine. 66.7 kN for Molniya 8K78 Stage 3. Flew 1960-1965. Isp=340s. Designed by Korolev; passed to Isayev for production. Began a series of engines leading through the 8D726 for GR-1 to the Block D for the N1 and Proton. More...
  • S1.5400A Korolev Lox/Kerosene rocket engine. 67.3 kN. Molniya 8K78M-3. Isp=342s. First flight 1964. 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...
  • S5.45 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...
  • S5.51 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...
  • S5.80.1100-0 Isayev Lox/Kerosene rocket engine. 2.940 kN. Soyuz-2 Blok LM. Developed 1990s. Thrust chamber from KTDU-80 / S5.80 converted to burn Lox/Kerosene. 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...
  • Sea Dragon-2 Aerojet lox/lh2 rocket engine. 62,270 kN. Design, 1962. Truax pressure fed design. Diameter of extended nozzle 30 m. Specific impulse estimated from booster performance figures. Isp=320s. More...
  • Sergeant Multiple-source solid rocket engine. 6.660 kN. Out of Production. Used in Jupiter C, Juno 2. Isp=235s. First flight 1956. More...
  • Sert II NASA Cleveland electric/mercury rocket engine. 28 mN. Flown in 1970. Isp=4200s. The thruster for the Sert-II test consisted of two electron bombardment engines using mercury propellant. More...
  • Sert-I Cesium Hughes electric/cesium rocket engine. 5.6 naN. In Development, 1962-1964. Isp=8050s. 8 cm diameter cesium contact ion engine was designed to operate at 0.6 kW. More...
  • Sert-I Mercury NASA Cleveland electric/mercury rocket engine. 28 mN. Developed 1962-1964. Isp=4900s. 10 cm diameter mercury electron bombardment ion engine used on the first successful flight test of ion propulsion on a Scout X-4 launch vehicle. More...
  • SLV-2 ISRO solid rocket engine. 267 kN. Isp=267s. Used on ASLV, SLV. First flight 1979. More...
  • SLV-3 ISRO solid rocket engine. 90.7 kN. Isp=277s. Used on ASLV, SLV. First flight 1979. More...
  • SLV-4 ISRO solid rocket engine. 26.8 kN. Isp=283s. Used on ASLV, SLV. First flight 1979. More...
  • Snapshot EOS electric/cesium rocket engine. 8.5 mN. In Development, 1962-1964. Isp=5100s. Launched on Blue Scout Junior launch vehicle on Snapshot test; a contact ionization engine; thruster anode diameter was 5 cm. More...
  • SpaceDev Hybrid SpaceDev N2O/Solid hybrid rocket engine. 73.5 kN. Rocketplane boost. Out of production. Isp=250s. Used on Tier One launch vehicle. First flight 2002. More...
  • SPT-100 Stechkin electric rocket engine. 0.196 kN. Meteor, Gals. In Production. 1.35 kW Hall thruster. Thrust variable 2 to 20 kgf. Marketed in USA by Space Systems/Loral and Fakel. Isp=2500s. More...
  • SPT-70 Stechkin solid rocket engine. 0.098 kN. Yamal. In Production. Thrust variable 1 to 10 kgf Isp=2500s. More...
  • SPT-50 Stechkin solid rocket engine. Meteor-Priroda. In Production. More...
  • SPT-200 Stechkin solid rocket engine. 0.780 kN. In Production. Thrust variable 8 to 80 kgf Isp=3000s. More...
  • SPT-100-SEP Stechkin solid rocket engine. In Production. The French company SEP is developing this uprated version of the SPT-100 in cooperation with OKB Fakel. Isp=2200s. More...
  • SPW-2000 SNECMA, Pratt and Whitney lox/lh2 rocket engine. 230.4 kN. Design 2000. New upper-stage cryogenic engine for the upgraded Ariane-5, the Atlas-5, and other new vehicles. More...
  • SR-19 Aerojet solid rocket engine. 267.7 kN. Minuteman 2 2nd stage. In production. Second stage of Minuteman 2. Surplus motors used as second stage of Minotaur launch vehicle and various SDI targets in 1980's. Isp=287s. First flight 2000. More...
  • SRM-1 CSD solid rocket engine. 181.5 kN. Used in TOS; IUS-1 on Shuttle, Titan 34D. Known by manufacturer as Orbus 21. Propellant: 86% solids made up of HTPB UTP-19360A. Shape: cylindrical. Isp=296s. First flight 1982. More...
  • SRM-2 CSD solid rocket engine. 78.4 kN. Used in Shuttle, Titan 34D; IUS-2. Known by manufacturer as Orbus 6. Isp=304s. First flight 1982. More...
  • SSUS-A Motor Thiokol solid rocket engine. In Production. A slightly modified stage 3 Minuteman 3 with TVC and roll control systems removed, provided propulsion for the Douglas Spinning Solid Upper Stage for use with Space Shuttle payloads. More...
  • Star 37FM Thiokol solid rocket engine. 47.9 kN. In Production. Isp=289s. Apogee kick motor for the FLTSTACOM satellite. The motor case contained the same volume as the discontinued STAR 37E. More...
  • Star 37S Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 190,590 kgf-sec. Motor propellant mass fraction 0.925. Isp=287s. More...
  • Star 40 Thiokol solid rocket engine. Out of Production. Total impulse 200,882 kgf-sec. Motor propellant mass fraction 0.925. Isp=207s. More...
  • Star 37XFP Thiokol solid rocket engine. 31.5 kN. In Production. Isp=290s. Orbit insertion motor qualified for Global Positioning Satellite. Used as a replacement for the discontinued STAR 37F. Propellant: 884 kg of AP/HTPB/Al in 6Al-4V titanium case. More...
  • Star 37XF 8 Thiokol solid rocket engine. Out of Production. Total impulse 238,809 kgf-sec. Motor propellant mass fraction 0.924. Isp=291s. More...
  • Star 37XF Thiokol solid rocket engine. 45 kN. Out of Production. Total flown included in total for Star-37XF-8. Total impulse 259,123 kgf-sec. Motor propellant mass fraction 0.929. Isp=290s. More...
  • Star 37X Thiokol solid rocket engine. 51.1 kN. Out of Production. Total impulse 310,668 kgf-sec. Motor propellant mass fraction 0.928. Isp=295s. More...
  • Star 37Y Thiokol solid rocket engine. Out of Production. Total impulse 317,856 kgf-sec. Motor propellant mass fraction 0.93. Isp=297s. More...
  • Star 27B Thiokol solid rocket engine. In Production. Total flown included in total for Star-27E. Total impulse 92,296 kgf-sec. Motor propellant mass fraction 0.921. Isp=288s. More...
  • Star 37N Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 162,102 kgf-sec. Motor propellant mass fraction 0.898. Isp=290s. More...
  • Star 48 Thiokol solid rocket engine. 67.2 kN. Used in Delta 3900; Conesotga; PAM-S; PAM-D. Total flown included in total for Star-48-8. Total impulse 575,682 kgf-sec. Motor propellant mass fraction 0.946. Isp=286s. First flight 1982. More...
  • Star 37G Thiokol solid rocket engine. Out of Production. Total impulse 304,620 kgf-sec. Motor propellant mass fraction 0.925. Isp=289s. More...
  • Star 48B l Thiokol solid rocket engine. In Production. Isp=292s. Lengthened version of Star 48B to provide increased payload capability. The design incorporates a longer cylindrical section in the motor case. More...
  • Star 37F Thiokol solid rocket engine. 55.5 kN. Out of Production. Total impulse 249,177 kgf-sec. Motor propellant mass fraction 0.928. Isp=286s. More...
  • Star 37E Thiokol solid rocket engine. 68 kN. Out of Production. Total impulse 296,635 kgf-sec. Motor propellant mass fraction 0.926. Isp=283s. More...
  • Star 37D Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 189,489 kgf-sec. Motor propellant mass fraction 0.91. Isp=266s. More...
  • Star 37C Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 275,959 kgf-sec. Motor propellant mass fraction 0.921. Isp=285s. More...
  • Star 37B Thiokol solid rocket engine. 45 kN. Out of Production. Total impulse 189,489 kgf-sec. Motor propellant mass fraction 0.91. Isp=291s. More...
  • Star 75 Thiokol solid rocket engine. 242.8 kN. In Production. Isp=288s. A demonstration motor tested as a first step in the development of a perigee kick motor in the 4080-7940 kg propellant range. More...
  • Star 5C/CB Thiokol solid rocket engine. 1.951 kN. In Production. Isp=266s. Titan Retro designed to separate the second stage from the transtage on the Titan II missile and Titan launch vehicle. The motor was also adapted for other uses. More...
  • Star 37 Thiokol solid rocket engine. 43.5 kN. Total impulse 161,512 kgf-sec. Motor propellant mass fraction 0.899. Isp=260s. First flight 1963. More...
  • Star 6B Thiokol solid rocket engine. 2.510 kN. In Production. Isp=273s. Delta-V reentry motor developed as a spin-up and propulsion motor for reentry vehicles. The design incorporated an aluminum case and a plastic nozzle assembly. More...
  • Star 6A Thiokol solid rocket engine. Out of Production. Total impulse 935 kgf-sec. Motor propellant mass fraction 0.723. Isp=285s. More...
  • Star 63F Thiokol solid rocket engine. 104.627 kN. In Production. Isp=297s. Provided perigee kick for the McDonnell PAM-D2 system. Another version was the Star 63D (TU-936). More...
  • Star 63D Thiokol solid rocket engine. 84.739 kN. In Production. Isp=283s. Perigee motor with a range of propellant loads, yielding GTO payloads from 3,080 to 4,588 pounds at a constant velocity of 8,012 feet per second. More...
  • Star 63 Thiokol solid rocket engine. 107.2 kN. Used in Shuttle,Titan 34D. Isp=282s. Used on Delta 7925 launch vehicle. First flight 1990. More...
  • Star 62 Thiokol solid rocket engine. Out of Production. Total impulse 725,491 kgf-sec. Motor propellant mass fraction 0.94. Isp=294s. More...
  • Star 48A s Thiokol solid rocket engine. 77.109 kN. In Production. Isp=283s. Short nozzle upper-stage motor designed to fit within the dimensional envelope of the long nozzle. More...
  • Star 5CB Thiokol solid rocket engine. 2 kN. In Production. Reduced Al HTPB propellant (2.1 kg) minimizes contamination when Used in a Titan 4 stage separation motor. Diameter: 121 mm. Length: 341 mm. Mass: 4.5 kg. Itotal: 5.5 kNs. Burn Time: 2.77 sec. More...
  • Star 48 8 Thiokol solid rocket engine. Out of Production. Total impulse 587,784 kgf-sec. Motor propellant mass fraction 0.945. Isp=292s. More...
  • Star 5C Thiokol solid rocket engine. 2.039 kN. Out of Production. Titan Retro designed to separate the second stage from the upper stage of the Titan IV launch vehicle. More...
  • Star 5A Thiokol solid rocket engine. 0.166 kN. In Production. Isp=249s. Space Gnat was designed to provide a minimum acceleration, extended burn delta-V impulse, for small payload replacement or spin-up applications. More...
  • Star 5 Thiokol solid rocket engine. Out of Production. Total impulse 405 kgf-sec. Motor propellant mass fraction 0.87. Isp=189s. More...
  • Star 48V Thiokol solid rocket engine. In Production. Developed for Conestoga's upper stage, providing some 4 degrees capability at 30 degree/sec using the same loaded casing as the 48B. First Flight: 1994. More...
  • Star 48B s Thiokol solid rocket engine. 77.109 kN. In Production. Isp=286s. Short nozzle upper-stage motor qualified for the McDonnell Douglas Payload Assist Module (PAM) Space Transportation System (STS). More...
  • Star 48B Thiokol solid rocket engine. 66 kN. In Production. Isp=286s. Long nozzle upper-stage motor qualified for the McDonnell Payload Assist Module (PAM) Delta. More...
  • Star 48A l Thiokol solid rocket engine. In Production. Total impulse 709,062 kgf-sec. Motor propellant mass fraction 0.941. Isp=289s. More...
  • Star 6 Thiokol solid rocket engine. Out of Production. Total flown included in total for Star-6A. Total impulse 1,395 kgf-sec. Motor propellant mass fraction 0.795. Isp=287s. More...
  • Star 13C Thiokol solid rocket engine. Out of Production. Total impulse 8,252 kgf-sec. Motor propellant mass fraction 0.795. Isp=218s. More...
  • Star 31 Thiokol solid rocket engine. 80 kN. In Production. Isp=293s. Antares III, third-generation third stage for Scout launch vehicle. Propellant: AP/HTPB/Al propellant in a filament wound Kevlar case. More...
  • Star 20 Spherical Thiokol solid rocket engine. Out of Production. Total impulse 30,198 kgf-sec. Motor propellant mass fraction 0.934. Isp=234s. More...
  • Star 20 Thiokol solid rocket engine. 27.135 kN. In Production. Isp=286s. Altair III was developed as the propulsion unit for the fourth stage of the Scout launch vehicle. A filament-wound, fiberglass-epoxy case contained the CTPB propellant grain. More...
  • Star 17A Thiokol solid rocket engine. 16.014 kN. In Production. Isp=286s. Apogee kick motor, modified with 175 mm straight section added to the Star 17. The 17A was used to circularize orbits for the Skynet 1, NATO 1, and IMP-H & J satellites. More...
  • Star 17 Thiokol solid rocket engine. 10.9 kN. Skynet 1, NATO 1, and IMP-H & J. Out of production. Isp=286s. Used on Atlas LV-3A / Agena D launch vehicle. First flight 1963. More...
  • Star 15 Thiokol solid rocket engine. Out of Production. Total impulse 11,109 kgf-sec. Motor propellant mass fraction 0.926. Isp=228s. More...
  • Star 13F Thiokol solid rocket engine. Out of Production. Total impulse 9,608 kgf-sec. Motor propellant mass fraction 0.83. Isp=240s. More...
  • Star 20B Thiokol solid rocket engine. 24.467 kN. In Production. Isp=289s. Modified version of the STAR 20 with increased case structural capability over the. A filament-wound, fiberglass-epoxy case contained the CTPB propellant grain. More...
  • Star 13D Thiokol solid rocket engine. Out of Production. Total impulse 7,799 kgf-sec. Motor propellant mass fraction 0.81. Isp=223s. More...
  • Star 24 Thiokol solid rocket engine. 20 kN. Skynet 2. In Production. Isp=282s. Apogee boost motor was qualified and flown for the Skynet II, later apogee boost motor for NRL and SAMSO. More...
  • Star 13B Thiokol solid rocket engine. 7.6 kN. Out of Production. Isp=285s. Orbit insertion motor incorporated the lightweight case developed for the STAR 13 with the propellant and nozzle design of the earlier TE-M-516 apogee motor. More...
  • Star 13A Thiokol solid rocket engine. 5.874 kN. In Production. Isp=286s. Orbit insertion motor incorporated the lightweight titanium case developed for the STAR 13 with the propellant and nozzle design of the earlier TE-M-444 apogee motor. More...
  • Star 13 Thiokol solid rocket engine. 3.8 kN. Out of Production. Isp=273s. A braking motor used by NASA for the Anchored Interplanetary Monitoring Platform program. More...
  • Star 12A Thiokol solid rocket engine. 7.247 kN. In Production. Isp=270s. Super SARV Retro was a longer, higher impulse version of the STAR 12, used as a retrograde rocket for an unmanned satellite vehicle. More...
  • Star 12 Thiokol solid rocket engine. 5.560 kN. In Production. Isp=252s. SARV Retro, MK IV and V was a 60-pound motor using 40 pounds of propellant. It was designed for use as a retrograde rocket for an unmanned satellite vehicle. More...
  • Star 10 Thiokol solid rocket engine. 3.353 kN. In Production. Isp=251s. SARV Retro MK I was a small, high-performance motor designed for use as a retrograde rocket for an unmanned satellite vehicle. More...
  • Star 27D Thiokol solid rocket engine. In Production. Total flown included in total for Star-27E. Total impulse 88,668 kgf-sec. Motor propellant mass fraction 0.921. Isp=287s. More...
  • Star 13E Thiokol solid rocket engine. Out of Production. Total impulse 6,438 kgf-sec. Motor propellant mass fraction 0.822. Isp=211s. More...
  • Star 27A Thiokol solid rocket engine. In Production. Total flown included in total for Star-27E. Total impulse 89,684 kgf-sec. Motor propellant mass fraction 0.919. Isp=287s. More...
  • Star 30E Thiokol solid rocket engine. 35.4 kN. Koreasat. In Production. Isp=290s. Apogee motor used for the BAe Skynet 4 satellite, Koreasat and by the ORBEX small orbital launcher. More...
  • Star 30C Thiokol solid rocket engine. 32.6 kN. AS 3000. In Production. Isp=286s. Apogee motor used for the RCA G-STAR and Martin Marietta series 3000 telecom satelllites. More...
  • Star 30BP Thiokol solid rocket engine. 27 kN. In Production. Isp=292s. Apogee motor used for the HS 376 satellite bus. Incorporated an 89-percent-solids HTPB propellant in a 6AI-4V titanium case insulated with silica-filled EPDM rubber. More...
  • Star 30B Thiokol solid rocket engine. Out of Production. Total impulse 148,816 kgf-sec. Motor propellant mass fraction 0.941. Isp=293s. More...
  • Star 30A Thiokol solid rocket engine. Out of Production. Total impulse 137,095 kgf-sec. Motor propellant mass fraction 0.942. Isp=294s. More...
  • Star 30 Thiokol solid rocket engine. Out of Production. Total flown included in total for Star-30A. Total impulse 136,455 kgf-sec. Motor propellant mass fraction 0.943. Isp=293s. More...
  • Star 20A Thiokol solid rocket engine. Out of Production. Total impulse 83,839 kgf-sec. Motor propellant mass fraction 0.91. Isp=291s. More...
  • Star 27C Thiokol solid rocket engine. In Production. Total flown included in total for Star-27E. Total impulse 88,555 kgf-sec. Motor propellant mass fraction 0.918. Isp=287s. More...
  • Star 27 Thiokol solid rocket engine. 27 kN. Apogee motor used on CTS, GMS, BS, GPS, GOES satellites. In Production. Isp=288s. More...
  • Star 26C Thiokol solid rocket engine. 35 kN. In Production. Isp=272s. Upper stage motor used the titanium alloy case and nozzle attachment ring of the STAR 26B design to provide high propellant mass fraction and was insulated for high-spin-rate applications. More...
  • Star 26B Thiokol solid rocket engine. 34.627 kN. In Production. Isp=271s. Upper stage motor flown on the Burner IIA spacecraft for Boeing and the U.S. Air Force. More...
  • Star 26 Thiokol solid rocket engine. 39.1 kN. In Production. Upper stage motor used in the Sandia Strypi IV vehicle. Total flown included in total for Star-26C. Total impulse 62,800 kgf-sec. Motor propellant mass fraction 0.86. Isp=271s. First flight 1965. More...
  • Star 25 Thiokol solid rocket engine. Out of Production. Total impulse 61,086 kgf-sec. Motor propellant mass fraction 0.917. Isp=240s. More...
  • Star 24C Thiokol solid rocket engine. 21.466 kN. In Production. Isp=282s. Apogee motor designed and qualified for the NASA International Ultraviolet Experiment satellite. More...
  • Star 24B Thiokol solid rocket engine. Out of Production. Total flown included in total for Star-24C. Total impulse 57,236 kgf-sec. Motor propellant mass fraction 0.915. Isp=282s. More...
  • Star 24A Thiokol solid rocket engine. Out of Production. Total flown included in total for Star-24C. Total impulse 50,965 kgf-sec. Motor propellant mass fraction 0.903. Isp=282s. More...
  • Star 27E Thiokol solid rocket engine. In Production. Total impulse 88,301 kgf-sec. Motor propellant mass fraction 0.921. Isp=287s. More...
  • Timberwind 250 DoE nuclear/lh2 rocket engine. 2451.6 kN. Development ended 1992. Isp=1000s. Used on Timberwind launch vehicle. More...
  • Timberwind 45 DoE nuclear/lh2 rocket engine. 441.3 kN. Development ended 1992. Isp=1000s. Used on Timberwind Centaur launch vehicle. More...
  • Timberwind 75 DoE nuclear/lh2 rocket engine. 735.5 kN. Development ended 1992. Isp=1000s. Used on Timberwind Titan launch vehicle. More...
  • Topaze SEP N2O4/UDMH rocket engine. 120.1 kN. Out of production. Isp=255s. Used on Diamant launch vehicle. First flight 1965. More...
  • Toroid FD Notional lox/lh2 rocket engine. 20,015 kN. Study 1963. Operational date would have been December 1976. Engines for recoverable stage. Isp=455s. Used on Nova MM T10RR-2 launch vehicle. More...
  • Toroidal 400k Notional lox/lh2 rocket engine. 1778 kN. Study 1967. Isp=447s. Used on Saturn V-3B launch vehicle. 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...
  • Truax LH2 Aerojet lox/lh2 rocket engine. 147.1 kN. Test 1962. Used in Sea Horse-2. Isp=425s. More...
  • U102-000 Glushko Nitric acid/UDMH rocket engine. 468 kN. R-26 stage 2. Out of production. Isp=307s. More...
  • UM-129A Nissan solid rocket engine. 77.5 kN. In Production. Used in H-1-3. Isp=291s. More...
  • Vexin A SEP N2O4/UDMH rocket engine. 68.6 kN. Isp=277s. Used on Europa launch vehicle. First flight 1964. More...
  • Viking 4 SEP N2O4/UDMH rocket engine. 721 kN. Isp=296s. Used on Ariane 1, GSLV, PSLV. First flight 1979. More...
  • Viking 4B SEP N2O4/UDMH rocket engine. 805 kN. Isp=296s. Used on Ariane 4. First flight 1984. More...
  • Vinci Snecma, Ottobrunn lox/lh2 rocket engine. 180 kN. Upper Stages. In development. Isp=467s. Advanced expander cycle cryogenic propellant rocket engine with the capability of five in-space restarts. First hot-fire tests 2005. First flight 2010. More...
  • Von Braun-3 Notional Nitric acid/UDMH rocket engine. 392.3 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...
  • X-248A Thiokol solid rocket engine. 13.8 kN. Isp=255s. Used on Scout X-1, Scout X-2, Scout X-3. First flight 1960. More...
  • X-248 Thiokol solid rocket engine. 12.4 kN. Isp=256s. Used on Atlas Able, Blue Scout 2, Caleb, Delta, Delta A, Delta B, Delta C. First flight 1959. More...
  • X-254 Thiokol solid rocket engine. 60.5 kN. Isp=256s. Used on Blue Scout 1, Blue Scout 2, Blue Scout Junior, Scout X-1. First flight 1960. More...
  • X-258 Thiokol solid rocket engine. 22.2 kN. Isp=266s. Kick stage motor for Delta D, Scout A, Scout X-4. First flight 1963. More...
  • X-259 Thiokol solid rocket engine. 93.1 kN. Isp=293s. Used on Scout A, Scout B, Scout D, Scout F, Scout X-2, Scout X-3, Scout X-4. First flight 1962. More...
  • X-259A Thiokol solid rocket engine. 80.8 kN. Out of production. Isp=295s. Used on Scout G launch vehicle. First flight 1979. More...
  • X-430 GE exoticLF2/LH2 rocket engine. 334 kN. Developed 1960's. Very high energy engine developed in early 1960's for future large upper stages. Not flown due to toxicity of propellants. More...
  • XIPS-13 0.44 kW Hughes electric/xenon rocket engine. 17.8 mN. In Production. Isp=2585s. HS 702 operational communications satellites each employed four of these 0.44 kW xenon ion thrusters. 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...
  • XR2P1 XCOR Nitrous oxide/Alcohol rocket engine. 0.067 kN. First stages. Hardware. Engine was run on oxygen and nitrous oxide oxidizers, with propane, ethane, kerosene, turpentine, and a variety of alcohols. More...
  • XR3B4 XCOR Nitrous oxide/Alcohol rocket engine. 0.220 kN. First stages. Hardware. Regeneratively cooled engine using nitrous oxide and isopropyl alcohol as propellants. More...
  • XR3M9 XCOR Lox/CH4 rocket engine. 0.223 kN. First stages. Hardware. Methane-fueled engine allowing long-term on-orbit storage, higher density than hydrogen engines. Intended for use in reaction control systems and satellite maneuvering systems More...
  • YaRD Type A Korolev nuclear/lh2 rocket engine. 177 kN. Study 1963. Design considered in N1 nuclear upper stage studies. Outgrowth of work done by Bondaryuk and Glushko on YaRD engines for nuclear ICBM's, but using liquid hydrogen as propellant. Isp=900s. More...
  • YaRD Type AF Korolev nuclear/lh2 rocket engine. 196 kN. Study 1963. Design considered in N1 nuclear upper stage studies. Outgrowth of work done by Bondaryuk and Glushko on YaRD engines for nuclear ICBM's, but using liquid hydrogen as propellant. Isp=950s. More...
  • YaRD Type V Korolev nuclear/lh2 rocket engine. 392 kN. Study 1963. Design considered in N1 nuclear upper stage studies. Outgrowth of work done by Bondaryuk and Glushko on YaRD engines for nuclear ICBM's, but using liquid hydrogen as propellant. Isp=900s. More...
  • YaRD Type V-B Korolev nuclear/lh2 rocket engine. 392 kN. Study 1963. Isp=900s. Design considered in N1 nuclear upper stage studies. This version had 7,000 kg bioshield for manned missions. Used liquid hydrogen as propellant. 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-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-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-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-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...
  • YF-73 Beijing Wan Yuan lox/lh2 rocket engine. 11 kN. In development. Gas-generator turbopump. Gimballed engine. Isp=425s. Used on CZ-3 launch vehicle. First flight 1984. More...
  • YF-75 Beijing Wan Yuan lox/lh2 rocket engine. 78.5 kN. In development. Gas-generator turbopump. Gimballed engine. Isp=440s. First flight 1994. More...
  • Zefiro 9 Fiat-Avio solid rocket engine. 313 kN. In production. Isp=294s. Motor derived from the 16-metric-ton Zefiro 16. Carbon epoxy filament wound case; low density EPDM insulation; HTPB 1912 composite propellant. More...
  • Zefiro 23 Fiat-Avio solid rocket engine. 1200 kN. In production. Isp=289s. Carbon epoxy filament wound case; low density EPDM insulation; HTPB 1912 composite propellant. Used on Vega launch vehicle. More...

Home - Browse - Contact
© / Conditions for Use