Encyclopedia Astronautica
First Stages


Category of engines.

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Associated Engines
  • 11D121 Korolev GOX/Kerosene rocket engine. 68.650 kN. N-1 stage 1 (block A) roll control engine. Developed 1969-74. Gimbaling +/- 45 degree. Propellants are fed from main engine (NK-15, NK-33) turbopumps. Isp=313s. Chamber Pressure: 71.60 bar. More...
  • 11D43 Glushko N2O4/UDMH rocket engine. 1642 kN. Developed 1960-64. Isp=316s. Low-expansion ratio gimbaled variant for Proton stage 1 concept. Configuration 4 x 8D43 clustered with 4 x 11D43 abandoned in favor of 6 x Glushko 11D48 in final Proton design. More...
  • 11D51F Kuznetsov Lox/Kerosene rocket engine. 1918 kN. N1F 1965 - A. Study 1965. As described in N1 improvement study, 1965. Block A engine thrust increased. Isp=331s. More...
  • 11D51M Kuznetsov Lox/Kerosene rocket engine. 2843 kN. N1M 1965 - A. Study 1965. As described in N1 improvement study, 1965. Huge modification of Block A engines - sea level thrust increased from 175 tonnes thrust to 250 tonnes. Isp=346s. More...
  • 15D151 NII-125 solid rocket engine. Combined missile (RT-20P) stage 1. Out of production. Launch thrust 588 kN. Designed for first stage of combined missile and SLBM; flight tested, no production. First flight 1967. More...
  • 15D206 Yuzhnoye solid rocket engine. RT-23 early models stage I. Out of Production. The case-bound T9-BK composite solid propellant charge had a star shape channel. The case was of organic fibre-wound plastic material. More...
  • 15D23 KBMash solid rocket engine. 892 kN. RT-2 Stage 1. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/aluminium propellant. Chamber pressure 40 kgf/cm2. More...
  • 15D23P TsKB-7 solid rocket engine. 980 kN. RT-2P Stage 1. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/ammonium butyl propellant. Chamber pressure 56 kgf/cm2. More...
  • 15D305 Yuzhnoye, Tsurilnikov solid rocket engine. RT-23 stage I. Out of Production. Case-bound OPAL composite solid propellant charge with a star shape channel. The case was of organic fibre-wound plastic material. More...
  • 16 in gun US Navy gun for launch of rocket-boosted projectile. 1,470,981 kN. Development ended 1966. The proposed Martlet gun-launched small satellite launcher used a converted 16 inch naval gun to propell the rocket sabot. Isp=43s. More...
  • 280 inch solid Notional solid rocket engine. 46,208 kN. Study 1963. Operational date would have been February 1973 Isp=265s. Used on Nova MM 14B launch vehicle. More...
  • 293-P Kartukov solid rocket engine. P-70 Ametist. Out of Production. More...
  • 300 inch solid Notional solid rocket engine. 63,595 kN. Study 1963. Operational date would have been April 1973 Isp=263s. Used on Nova MM 14A launch vehicle. More...
  • 325 in solid Notional solid rocket engine in GD Nova studies. 69,047 kN. Study 1963. Isp=263s. Recoverable motors; separation at 1,972 m/s at 53,000 m altitude; splashdown using retrorockets under 3 61 m diameter parachutes 610 km downrange. More...
  • 5 mlbf Notional lox/lh2 rocket engine. 41,361 kN. OOST, ROOST studies 1963. Isp=410s. First flight 1977. More...
  • 5 mlbf RP-4 Notional Lox/Kerosene rocket engine. 24,459 kN. Study 1963. Operational date would have been July 1977. Recoverable stage. 10% plug nozzle. Isp=299s. Used on Nova-1 DAC launch vehicle. More...
  • 8D415K Kosberg Lox/Kerosene rocket engine. 1471 kN. Designed for use in N-1. Development canceled in 1960 when Korolev turned to Kuznetsov for R-9 and N-1 engines after continuous rows with Glushko over performance and propellant types. First flight 1966. More...
  • 8D43 Kosberg N2O4/UDMH rocket engine. 559 kN. UR-500 stage 1 original concept. Hardware. Isp=316s. In early Proton design would be clustered with 4 x Glushko 11D43. Abandoned in favor of 6 x Glushko 11D48, but later developed into the RD-0208 and RD-0210. More...
  • 8D43 + 11D43 Kosberg N2O4/UDMH rocket engine. 2247.450 kN. Design 1962. Isp=310s. Originally the first stage of the Proton was designed for 4 x fixed 11D43 and 4 x gimballed Kosberg 8D43; replaced by 6 x 11D48 from Glushko in final Proton design. More...
  • A-10 Thiel Lox/Alcohol rocket engine. 2306.8 kN. Study 1942. Planned for use in A-10. Unique dual-thrust chamber / single nozzle design, which was later shown to be not feasible technically. Isp=247s. More...
  • A-4 Thiel Lox/Alcohol rocket engine. 311.8 kN. Isp=239s. Used on V-2 missile. Work began June 1936. Interim design, but went into production. Used 18 x 1.5 tonne thrust chambers, feeding common mixing chamber. Tested from 1939, mass production 1943-1945. More...
  • A-6 Rocketdyne Lox/Alcohol rocket engine. 414.3 kN. Out of production. Isp=265s. Used on Redstone launch vehicle. First flight 1953. Developed from the XLR43-NA-1, an American version of the V-2 single-chamber engine tested in 1945. More...
  • A-7 Rocketdyne Lox/Hydyne rocket engine. 416.2 kN. Out of Production. Version of Redstone engine for Jupiter-C test vehicle, with Hydyne fuel and 140 seconds burn time. Flew 1956-1959. Gas generator, pump-fed. Thrust 370 kN at sea level. Isp=265s. More...
  • A6-12 Dushkin rocket engine. 39 kN. V-600. Developed 1955-62. Thrust variable 1500 - 4000 kgf. More...
  • Aerojet SRB Aerojet solid rocket engine. 1270 kN. In production. Isp=275s. First flight 2002. More...
  • AJ-260-1/3 Aerojet solid rocket engine. 10,105 kN. Design concept 1960's. Isp=275s. Used on Saturn INT-05B launch vehicle. More...
  • AJ-260-2 Aerojet solid rocket engine. 17,695.3 kN. Study 1965. Isp=263s. 260 inch solid rocket booster half length. The version tested and also proposed for use as a first stage with the Saturn IVB. More...
  • AJ-260X Aerojet solid rocket engine. 35,390.7 kN. Study 1967. Full length version of 260 inch motor tested in 1960's. Proposed for use in various Saturn and Nova configurations. Isp=263s. More...
  • AJ-260X 1/3 Aerojet solid rocket engine. 11,143 kN. Design concept 1960's. Isp=263s. More...
  • Algol 1 Aerojet solid rocket engine. 470.9 kN. Isp=236s. This rocket started as a Polaris test motor with a 40 inch diameter, which at the time was the largest solid motor ever tested. First flight 1960. More...
  • Algol 2 CSD solid rocket engine. 564.2 kN. Isp=255s. Used on Scout A, Scout B, Scout X-3, Scout X-4; proposed as strap-on for Titan 3BAS2. First flight 1962. More...
  • Algol 3 CSD solid rocket engine. 471.9 kN. Isp=284s. Used on Advanced Scout, Scout D, Scout F, Scout G. First flight 1972. More...
  • Algol 3A CSD solid rocket engine. 464.7 kN. In Production. Isp=259s. More...
  • Ares Aerojet N2O4/Aerozine-50 rocket engine. 440 kN. SSTO ICBM. Development 1968. Isp=370s. Advanced Rocket Engine System - single shaft turbopump, integrated single pressure vessel in a staged combustion cycle configuration. More...
  • Atar 9K SNECMA turbojet engine. 48 kN. Out of Production. Isp=2020s. More...
  • BA-3200 Beal H2O2/Kerosene rocket engine. 14,100 kN. Development 1990's. Pressure-fed engine with composite ablative chamber and nozzle. Helium pressurant. Thrust declines to 70% of initial value before shutdown. Isp=259s. More...
  • Burlak Stage 1 Russian N2O4/UDMH rocket engine. 360 kN. Burlak stage 1. Development ended 1992. Isp=320s. Air launched from Tu-160 at 13,500 m, Mach 1.7 release conditions. More...
  • Castor 120 Thiokol solid rocket engine. 1650 kN. Isp=280s. Motor similar in size to the Peacekeeper missile stage 1 motor; filled the gap between Castor 4A and the large segmented motors. First flight 1989. More...
  • Castor 4 Thiokol solid rocket engine. 407.2 kN. Series of motors used as Delta strap-on boosters and as first and upper stages for low-cost all-solid-propellant designs. Isp=261s. First flight 1975. More...
  • Castor 4A Thiokol solid rocket engine. 478.3 kN. Out of production. Isp=266s. Castor 4A improved Delta performance by 11% by replacing the old fuel with HTPB propellant. Used in Delta 6900; Atlas IIAS; Castor 4A. First flight 1982. More...
  • CD Module Notional lox/lh2 rocket engine. 7361 kN. Study 1969. Isp=420s. CD Modules - conceptual engines of various thrusts, according to design - were clustered in Martin Marietta Nova designs More...
  • Chamber/single nozzle Notional lox/lh2 rocket engine. 13,231 kN. Study 1963. Isp=455s. Before moving to favored plug nozzle designs, Bono at Douglas considered having multiple combustion chambers exhaust into a single large nozzle to obtained Improved Specific Impulse. More...
  • Cobra Pratt and Whitney lox/lh2 rocket engine. 4500 kN. Design 2003. Proposed as a long-life, moderate-to high-thrust, reusable booster engine that incorporated a safe, low-cost, low-risk, LH2/LOX single burner, using a fuel-rich, staged combustion cycle. More...
  • D-1 Kosberg isopropylnitrate monopropellant rocket engine. 39 kN. Developed 1955-56. Second thrust level at 50%. Explosion of D-1 on test bench in 1956 forced stop of work with mono-propellant OT-152. Sea level thrust 39 kN. More...
  • D-18T Lotarev turbofan engine. 229.4 kN. Used on An-225 launch aircraft for Interim HOTOL, MAKS concepts. Development ended 1988. Isp=9000s. More...
  • D-2 Polyarniy Lox/Kerosene rocket engine. 1373 kN. R-3. Out of Production. Competing engine for 3000 km range IRBM design to study problems of long-range rockets. Developed from April 1947 until cancellation. Isp=288s. More...
  • D-7 Kosberg isopropylnitrate monopropellant rocket engine. 11.8 kN. Missile by Toropov. Out of Production. Intended for air-air missile by I I Toropov. Uncooled thrust chamber. Sea level thrust 11.8 kN. More...
  • E-1 Rocketdyne Lox/Kerosene rocket engine. 1885 kN. Study 1957. Developed by USAF in late 1950's. Cancelled and decision to go direct to 1,500,000 lbf F-1 as next step. Booster applications. Gas generator, pump-fed. Isp=290s. More...
  • EKR Ramjet Bondaryuk ramjet engine. 6.130 kN. EKR Stage 2. Study 1953. Isp=1580s. Study for an experimental winged cruise missile. Not developed but formed basis for Burya and Buran missiles. More...
  • F-1 Rocketdyne Lox/Kerosene rocket engine. 7740.5 kN. Isp=304s. Largest liquid rocket engine ever developed and flown. Severe combustion stability problems were solved during development and it never failed in flight. First flight 1967. More...
  • F-1A Rocketdyne Lox/Kerosene rocket engine. 9189.6 kN. Study 1968. Designed for booster applications. Gas generator, pump-fed. Isp=310s. More...
  • F100-100 Pratt and Whitney turbofan engine. 63.9 kN. In Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=1552s. More...
  • F101 Pratt and Whitney turbofan engine. 75.6 kN. In Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=1980s. More...
  • Falcon SLV-1 Michoud Lox/Solid hybrid rocket engine. 1400 kN. First stage. Study 2005. Part of the USAF FALCON program to assess hybrid propulsion applications for a responsive small launch vehicle. More...
  • FastTrack Notional Lox/Kerosene rocket engine. 44.1 kN. Design concept. NASA Marshall Space Flight Center prototype experimental engine that led to Fastrac low-cost engine for X-34. Isp=348s. More...
  • Fastrac Huntsville Lox/Kerosene rocket engine. 269 kN. Development ended 1996. Isp=310s. Used on X-34A launch vehicle. Intended to demonstrate lower cost in a reusable simple turbopump rocket engine. More...
  • Gamma 8 Bristol Siddley H2O2/Kerosene rocket engine. 234.8 kN. Out of production. Isp=265s. Used on Black Arrow launch vehicle. First flight 1969. More...
  • Garvey Aerospike Garvey Lox/Alcohol rocket engine. Development ended 2005. Launch thrust .044 kN. Single-chamber, liquid-propellant, annular aerospike engine. More...
  • GEM 40 Hercules solid rocket engine. 499.2 kN. Air-ignited versions have nozzle ratio of 16:1, specific impulse of 283.4 sec. Isp=274s. Used on Delta 7925 launch vehicle. First flight 1990. More...
  • GEM 46 Hercules solid rocket engine. 608.1 kN. Air-ignited versions have nozzle ratio of 24.8:1, specific impulse of 284 sec. Isp=274s. First flight 1998. More...
  • GEM 60 Hercules solid rocket engine. 851.5 kN. In production. Isp=275s. Used as strap-on boosters for Delta 3 , Delta IV Medium. First flight 2002. More...
  • Glushko C Glushko storable lqiuid rocket engine. 29,400 kN. Study 1970. Glushko studied liquid propellant engines of 'several thousand tonnes thrust' in the period 1963-1970. Largest thrust chamber ever tested in Russia was Glushko's RD-270 of 680 tf. More...
  • H-1 Rocketdyne Lox/Kerosene rocket engine. 947.7 kN. Saturn l/lB. Designed for booster applications. Gas generator, pump-fed. Isp=289s. First flight 1961. More...
  • H-1b Rocketdyne Lox/Kerosene rocket engine. 1030.2 kN. Isp=296s. First flight 1966. More...
  • H-1c Rocketdyne Lox/Kerosene rocket engine. 1130 kN. Study Saturn IB-A, Saturn IB-B, 1965. Isp=296s. More...
  • H-2-0 Nissan solid rocket engine. 1540 kN. Isp=273s. Used as strap-on booster on H-2, first stage on J-1. First flight 1994. More...
  • H-2/J-1-1 Nissan solid rocket engine. 1556.6 kN. In Production. Used in J-1-1. Isp=273s. More...
  • H1500 Notional Lox/Solid hybrid rocket engine. 931.3 kN. Design 1988. Isp=284s. Used on Industrial Launch Vehicle launch vehicle. More...
  • Helios Stage 1 Notional lox/lh2 rocket engine. 1667 kN. Study 1960. Engines for booster stage with Lox tanks only to take nuclear second stage to stratosphere. Isp=400s. Helios A, B, C studies. More...
  • Hercules Hercules solid rocket engine. 15,565.8 kN. In development. Isp=286s. Planned replacement for shuttle solid rocket boosters after Challenger disaster. A billion dollars spent in development, but contract terminated. NASA decided to stay with Thiokol RSRM. More...
  • HG-3-SL Rocketdyne lox/lh2 rocket engine. 1387 kN. Study 1966. Isp=450s. High-performance high-pressure chamber engine developed from the J-2, fitted with lower-expansion nozzle for sea level use on Saturn INT-17. Technology led to Space Shuttle Main Engines. More...
  • HP-1 Notional lox/lh2 rocket engine. 6536 kN. Study 1963. Operational date would have been December 1974. Isp=451s. Used in Martin Nova studies MM 24G, MM 33. More...
  • Isayev 218 Isayev Nitric acid/Amine rocket engine. 218 (S-25 system). Out of Production. Launch thrust 166 kN. More...
  • Isayev P-15 Isayev Nitric acid/Amine rocket engine. 11.9 kN. P-15 Termit. Out of Production. Designation unknown. Thrust range 11.895-5.43 kN. More...
  • Isayev R-17 Isayev Nitric acid/Kerosene rocket engine. 131.2 kN. R-17. Out of production. Designation unknown. First flight 1961. More...
  • Isayev V-750V Isayev Nitric acid/Amine rocket engine. 30.4 kN. SAM-missile V-750V. Out of Production. Designation unknown. More...
  • J-2-SL Rocketdyne lox/lh2 rocket engine. 996.7 kN. Study 1966. Sea level version of J-2 with reduced expansion ratio proposed for Saturn II first stage use. Isp=390s. More...
  • J57-8 Pratt and Whitney turbojet engine. 45.4 kN. Out of production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=1414s. Used on Caleb launch vehicle. First flight 1960. More...
  • J57-19 Pratt and Whitney turbojet engine. 53.8 kN. Out of production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=5142s. Used on B-52 launch aircraft for X-15A. First flight 1959. More...
  • J58 Pratt and Whitney turbojet engine. Out of Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=2084s. More...
  • J75-17 Pratt and Whitney turbojet engine. 71.6 kN. Out of Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=1800s. More...
  • J79- 5 GE turbojet engine. 45.8 kN. Out of Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=2020s. More...
  • J79-17 GE turbojet engine. 52.8 kN. Out of Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=2020s. More...
  • J93-3 GE turbojet engine. 86.7 kN. Out of Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=2084s. More...
  • JP-5/H2O2 Notional H2O2/Kerosene rocket engine. 63 kN. Study 1993. Isp=335s. Engine for Black Horse winged, single stage to orbit launch vehicle using aerial refueling. More...
  • JT9D-3A Pratt and Whitney turbofan engine. 208.8 kN. Out of Production. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=10939s. More...
  • Kartukov LL Kartukov solid rocket engine. 14.7 kN. LL-1, LL-2, LL-3. Developed 1946-48. More...
  • Kartukov Soyuz SAS Kartukov solid rocket engine. 785 kN. Soyuz 7K-OK, Soyuz 7KT-OK, Soyuz 7K-T. Out of Production. Thrust 76 tf at cutout - 80.1tf at ignition. More...
  • KSR-3 Korean Lox/Kerosene rocket engine. In development. Launch thrust 122.5 kN. Pressure-fed indigenous design. First flight 2002. More...
  • L-5.00H Notional lox/lh2 rocket engine. 30,684 kN. Study 1963. Isp=428s. Used on Nova GD-H launch vehicle. More...
  • L-5.25H Notional lox/lh2 rocket engine. 27,350 kN. Study 1963. Isp=410s. Engines for recoverable booster engine package 'half stage' of a 1 1/2 stage arrangement. Used on Nova GD-H launch vehicle. More...
  • L-6.55 Notional Lox/Kerosene rocket engine. 31,010 kN. Study 1963. Engines used in recoverable stage of ballistic shape; separation at 3,420 m/s at 93,900 m altitude; splashdown using retrorockets under 7 parachutes 1340 km downrange. Isp=330s. More...
  • L-7.70 Notional Lox/Kerosene rocket engine. 37,007 kN. Study 1963. Engines used in recoverable stage; separation at 3,365 m/s at 89,300 m altitude; splashdown using retrorockets under 8 46 m diameter parachutes 1300 km downrange. Isp=335s. More...
  • L6H Notional lox/lh2 rocket engine. 122,748 kN. Study 1963. Operational date would have been June 1976. Used in booster stage (engines only). Isp=439s. Used on Nova MM 34 launch vehicle. More...
  • LACE/LE-5 Mitsubishi air augmented Liquid Air/LH2 rocket engine. 147.1 kN. Design 1999. Isp=1200s. Used on H-2 HIMES launch vehicle. More...
  • LE-7 Mitsubishi lox/lh2 rocket engine for H-2 upper stage. 1078 kN. Staged combustion turbopump. No throttle capability. Isp=446s. First flight 1994. More...
  • LE-7A Mitsubishi lox/lh2 rocket engine. 1098 kN. In production. Isp=438s. Improved model of the original LE-7 for the first stage of the H-II rocket with a two stage combustion cycle system. First flight 2001. More...
  • Liberty Liberty Lox/Kerosene rocket engine. Development 1994-2006. Pressure-fed engine. Price $ 12,000 in 1995. Used on Scorpius launch vehicle. More...
  • Liberty-1 Notional Lox/Kerosene rocket engine. 245.2 kN. Development ended 1988. Pressure-fed engine. Isp=270s. Used on Liberty launch vehicle. More...
  • LK-1 IAI solid rocket engine. 774 kN. In production. Isp=272s. Lengthened version of Shavit rocket motor. Lower stage used 9:1 nozzle. 23.6:1 nozzle for upper stage use inceased Isp to 279 seconds, First flight 1995. More...
  • LR101-11 Rocketdyne Lox/Kerosene rocket engine. 5.3 kN. In Production. Isp=246s. Verniers for RS-27 powerplant, used on Delta boosters 1974-1992. More...
  • LR105-3 Rocketdyne Lox/Kerosene rocket engine. 375 kN. Out of Production. Early version of Atlas Sustainer. Gas generator, pump-fed. Isp=308s. More...
  • LR105-5 Rocketdyne Lox/Kerosene rocket engine. 386.4 kN. Atlas E, F. Atlas Sustainer. Gas generator, pump-fed. Separate turbopumps for each booster engine. Isp=316s. First flight 1960. More...
  • LR105-7 Rocketdyne Lox/Kerosene rocket engine. 386.4 kN. Atlas space launchers. Out of production. Atlas Sustainer. Gas generator, pump-fed. Evolved from MA-2 ICBM system. Isp=316s. First flight 1963. More...
  • LR79-7 Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Out of production. Designed for booster applications. Gas generator, pump-fed. Isp=282s. First flight 1957. More...
  • LR8-RM-5 Reaction Motors Lox/Alcohol rocket engine for rocketplanes. Out of Production. Launch thrust 26.67 kN. Advanced version of the LR-11, 4 chambers. Engine in the X-1E was modified in 1958 to increase chamber pressure to 20 atm and burn Hydyne fuel. More...
  • LR83-NA-1 Rocketdyne Lox/Kerosene rocket engine. 683 kN. Development ended 1958. Isp=282s. Planned production version of the engine for the booster of the Navaho G-38 intercontinental cruise missile. More...
  • LR87-9 Aerojet N2O4/Aerozine-50 rocket engine. Launch thrust 956.1 kN. Variant of LR-87 used on early versions of Titan III B,C First flight 1966. More...
  • LR87-7 Aerojet N2O4/Aerozine-50 rocket engine. 1086.1 kN. Study 1961. Version of LR-87-5 used on Gemini Titan 2 launch vehicle. Isp=296s. Proposed for unflown Titan 3L2, Titan 3L4 boosters. First flight 1962. More...
  • LR87-5 Aerojet N2O4/Aerozine-50 rocket engine. 1096.8 kN. Out of Production. Isp=297s. Used on Titan 2 launch vehicle. Engines refurbished for space launcher versions from decommissioned missiles between 1974-1982. More...
  • LR87-3 Aerojet Lox/Kerosene rocket engine. 733.9 kN. Study 1957. Titan 1 booster engine. Surplus Flight Engines were available for various uses in the 1960's. Isp=290s. First flight 1959. More...
  • LR87-11 AJ23-138 Aerojet N2O4/Aerozine-50 rocket engine. Launch thrust 1008.31 kN. Version of LR-87-11 tuned for launch pad ignition when used on Titan 3B. First flight 1966. More...
  • LR87+ Aerojet N2O4/Aerozine-50 rocket engine. 1634.4 kN. Study 1965. Nominal improved LR87 in booster studies. Isp=293s. Used on Martin Astrorocket launch vehicle. More...
  • LR87-11 Aerojet N2O4/Aerozine-50 rocket engine. 1218.8 kN. Out of production. Isp=302s. Powered Titan 3 and 4 first stages. Replaced the -9 model, first flown 1968. First flight 1964. More...
  • LR89-5 Rocketdyne Lox/Kerosene rocket engine. 822.5 kN. Atlas E, F. Designed for booster applications. Gas generator, pump-fed. Separate turbopumps for each booster engine. Isp=290s. First flight 1960. More...
  • LR89-7 Rocketdyne Lox/Kerosene rocket engine. 948 kN. Atlas space launchers. Out of production. Designed for booster applications. Gas generator, pump-fed. Shared turbopumps for booster engines. Evolved from MA-2 ICBM system. Isp=294s. First flight 1963. More...
  • M-13 Nissan solid rocket engine. 1262.4 kN. Isp=263s. Used on Mu-3S launch vehicle. First flight 1969. More...
  • M14 Nissan solid rocket engine. 3780.3 kN. Isp=276s. Used on M-V launch vehicle. First flight 1997. More...
  • M33-20-4 Thiokol solid rocket engine. 286 kN. Isp=247s. Used as apogee kick motor on Delta D, LT Thor Agena D, Scout X-1, Scout X-2, Scout X-3, Scout X-4, TA Thor Agena B, TA Thor Agena D. First flight 1960. More...
  • M55/TX-55/Tu-122 Thiokol solid rocket engine. 792 kN. In production. Isp=262s. Proposed as strap-on booster for Saturn IB-C, Saturn INT-14, Saturn INT-15, Saturn INT-19 variants. First flight 2000. More...
  • MA-5A Rocketdyne Lox/Kerosene rocket engine. 2100 kN. Out of Production. Isp=296s. Atlas Engine System, an updated version of the MA-5, included replacments with selected RS-27 components for sea-level Isp increase of 4 secs. First flight 1991. More...
  • Martlet 4-1 Bull solid rocket engine. 67.7 kN. Development ended 1966. Isp=300s. Used on Martlet 4 launch vehicle. More...
  • MB-3 Press Mod Rocketdyne Lox/Kerosene rocket engine. 755.1 kN. Test 1962. Isp=285s. Used on Sea Horse launch vehicle. More...
  • MB-3-1 Rocketdyne Lox/Kerosene rocket engine. 760.6 kN. Out of production. Designed for booster applications. Gas generator, pump-fed. Isp=285s. Boosted Delta A, B, C, Thor Able-Star. First flight 1960. More...
  • MB-3-3 Rocketdyne Lox/Kerosene rocket engine. 866.7 kN. Out of Production. License built in Japan for H-1. Isp=290s. First flight 1964. More...
  • MBB-ATC500 MBB lox/lh2 rocket engine. 441.3 kN. Study 1969. Isp=460s. Used on Beta launch vehicle. More...
  • Merlin 1V SpaceX Lox/Kerosene rocket engine. 411.4 kN. Hardware. Isp=342s. Upper stage version of the Merlin developed for the Falcon 9 second stage. Based on the Merlin 1C and using a regeneratively cooled combustion chamber. First flight 2009. More...
  • Merlin 1A SpaceX Lox/Kerosene rocket engine. 378.040 kN. First stages. Hardware. Isp=300s. Completed development in early 2005. Pintle injector concept. Replaced by Merlin 1C. First flight 2006. More...
  • Merlin 1C SpaceX Lox/Kerosene rocket engine. 614.7 kN. First stages. Hardware. Isp=304s. Regeneratively cooled; turbo-pump also provided high pressure kerosene for the hydraulic actuators. Actuated turbine exhaust nozzle provided roll control. First flight 2008. More...
  • Microcosm 89N Microcosm Lox/Kerosene rocket engine. 89 kN. First stages. Hardware. In 2005 tests were conducted of this low-cost ablative composite rocket engine for responsive launch vehicle applications. More...
  • Microcosm 22N Microcosm Lox/Kerosene rocket engine. 22.250 kN. First stages. Hardware. Pressure-fed, ablatively cooled engine using liquid oxygen and jet fuel as propellants. Flown 1999/2001. More...
  • Microcosm 356N Microcosm Lox/Kerosene rocket engine. 356 kN. First stages. Hardware. Funded under AFRL SBIR Phase 1 contract of 2006. Ablative chamber, LOX/Jet A propellant engines designed for very low-cost, robust design margins. More...
  • MIHT-1 MIHT solid rocket engine. 980.6 kN. Start-1. In production. Used in Start-1. Estimated values. Isp=263s. First flight 1993. More...
  • Mustard Notional lox/lh2 rocket engine. 2157.4 kN. Study 1968. Isp=405s. Used on Mustard launch vehicle. More...
  • NK-15 Kuznetsov Lox/Kerosene rocket engine. 1544 kN. N-1 stage 1 (block A). Development ended 1964. On the basis of NK-9 the NK-15 was developed for the N-1 launcher. 30 were used on the Block A (Stage 1) of the N-1. Isp=318s. First flight 1969. More...
  • NK-15F Kuznetsov Lox/Kerosene rocket engine. 2180 kN. Development 1966-1972. Isp=350s. Engine had only a very short nozzle, the 24 engines around the periphery were to expand along a common central plug on the first stage of a studied N1 variant. More...
  • NK-15V Kuznetsov Lox/Kerosene rocket engine. 1648 kN. Development ended 1964. Isp=325s. Developed from the NK-9. 8 engines, featuring high-expansion nozzles, used on N1 Stage 2. First flight 1969. More...
  • NK-19 Kuznetsov Lox/Kerosene rocket engine. N-1 stage 4. Development ended 1964. Based on NK-9 engine. Originally developed for the modernized second stage of the R-9 (abandoned). Also to have been used on GR-1 / 8K713 Stage 2. First flight 1969. More...
  • NK-231 Kuznetsov turbofan engine. 226.5 kN. Tu-160. Development ended 1992. Turbofan engine used in Tu-160. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=1980s. More...
  • NK-33 LH2 Mod + 4 x LACE Kuznetsov air augmented rocket engine. 980.7 kN. N1-MOK. Study 1974. Isp=430s. Ultimate derivative of NK-9. Propellants changed to LH2/LOX, 16 x modified NK-33 engines + 4 Liquid Air Cycle Engine Liquid Air/LH2 boosters. More...
  • NK-33 Kuznetsov Lox/Kerosene rocket engine. 1638 kN. N-1F, Kistler stage 1, Taurus II stage 1. Isp=331s. Modified version of original engine with multiple ignition capability. Never flown and mothballed in 1975 after the cancellation of the N1. Resurrected for Kistler, then for Taurus. More...
  • NK-31 Kuznetsov Lox/Kerosene rocket engine. 402 kN. Isp=353s. Upgraded version of engines for N-1 stage 4, with multiple ignition capability and increased operational lifetime. Mothballed in 1974. Proposed for Black Colt launch vehicle in 1993. More...
  • NK-9 Kuznetsov Lox/Kerosene rocket engine. 441.3 kN. R-9, GR-1 stage 1. Isp=327s. Reached phase of stand testing in 1965, but then RD-111 selected. Later planned for 1st Stage of GR-1, but that rocket also cancelled. More...
  • Nodong North Korean Nitric acid/UDMH rocket engine. 144 kN. In production. Isp=255s. Used in North Korean missiles and Taepodong 1 satellite launcher. Derived from Isayev designs developed for Scud missiles and SLBM's of the Makeyev bureau. First flight 1998. More...
  • NOTS-1 NOTS solid rocket engine. 53.4 kN. Out of production. Isp=204s. Used on Caleb launch vehicle. First flight 1960. More...
  • OME Aerojet N2O4/MMH rocket engine. 26.7 kN. Study 1972. Isp=316s. Engine used in Shuttle Orbiter Orbital Maneuvering System pods, for orbit insertion, maneuvering, and re-entry initiation. First flight 1981. More...
  • Otrag Otrag N2O4/Kerosene rocket engine. 27.5 kN. First and upper stages of low-cost booster. Out of production. Isp=297s. Pressure-fed, using cheapest possible propellants. Injection pressure: 40-15 bar; thrust control: 100-40 %. First flight 1977. More...
  • P230 SNPE solid rocket engine. 6472.3 kN. In production. Isp=286s. Used on Ariane 5 launch vehicle. First flight 1996. More...
  • P241 SEP solid rocket engine. 6470 kN. In development. Isp=275s. First flight 2002. More...
  • P80 Fiat-Avio solid rocket engine. 3040 kN. In production. Isp=279s. Vega's first stage, introduced advanced low-cost technologies that could be reused for future evolutions of Ariane-5 boosters. More...
  • P9.5 SNPE solid rocket engine. 690 kN. Isp=263s. Strap-on booster engine for Ariane 42P, Ariane 44LP, Ariane 44P. First flight 1988. More...
  • Peacekeeper 1 Thiokol solid rocket engine. 2204.5 kN. In Production. MX Stage 1. Used as first stage of Taurus launch vehicle for initial test. Isp=282s. More...
  • Pegasus-1 Hercules solid rocket engine. 484.9 kN. Isp=285s. Used on Pegasus, Taurus. First flight 1989. More...
  • Pegasus XL-1 Hercules solid rocket engine. 589 kN. Isp=293s. Used on Pegasus XL launch vehicle. First flight 1994. More...
  • PF N204/Alumizine-1925k Notional N2O4/Alumizine rocket engine. 18,873 kN. Study 1967. Isp=280s. Used on Saturn LCB-Alumizine-250 launch vehicle. More...
  • PF N204/Alumizine-2300k Notional N2O4/Alumizine rocket engine. 22,562 kN. Study 1967. Isp=280s. Used on Saturn LCB-Alumizine-140 launch vehicle. More...
  • PF N204/UDMH-2165k Notional N2O4/UDMH rocket engine. 21,232 kN. Study 1967. Isp=267s. Used on Saturn LCB-Storable-250 launch vehicle. More...
  • PF N204/UDMH-2912k Notional N2O4/UDMH rocket engine. 28,552 kN. Study 1967. Isp=267s. Used on Saturn LCB-Storable-140 launch vehicle. More...
  • PF RP-1 Notional Lox/Kerosene rocket engine. 20,306 kN. Study 1967. Isp=275s. Used on Saturn LCB-Lox/RP-1 launch vehicle. More...
  • Plug-Nozzle J-2 Rocketdyne lox/lh2 rocket engine. 6864.6 kN. Study 1993. Plug nozzle version of J-2 proposed for certain Saturn V upgrades in late 1960's. Isp=425s. Used on DC-I launch vehicle. More...
  • Plug-Nozzle SSME Notional lox/lh2 rocket engine. 3728.7 kN. Study 1978. Isp=485s. Used on VTOVL launch vehicle. More...
  • Plug-Nozzle SERV Notional lox/lh2 rocket engine. 31,980.2 kN. Study 1971. Isp=455s. Used on Shuttle SERV launch vehicle. More...
  • Plug-Nozzle Pegasus Notional lox/lh2 rocket engine. 23,928 kN. Study 1966. Isp=459s. Used on Pegasus VTOVL launch vehicle. More...
  • PRD-70 Kartukov solid rocket engine. 400/5V11 stage I. Out of Production. More...
  • PRD-15 Kartukov solid rocket engine. 392 kN. Strela-1 missile. Out of Production. More...
  • PRD-19M Kartukov solid rocket engine. KSShch Shchuka. Out of Production. More...
  • PRD-22 Kartukov solid rocket engine. 3.920 kN. SM-30. Out of Production. More...
  • PRD-36 Kartukov solid rocket engine. V-600. Out of Production. More...
  • PRD-52 Kartukov solid rocket engine. 784 kN. DBR-1 Yastreb. Out of Production. Thrust 80 tf at ignition, 75 tf at cutout. More...
  • PRD-61 Kartukov solid rocket engine. 036 Vikhr. Out of Production. More...
  • Press Fed 25k TRW Lox/Kerosene rocket engine. 245.2 kN. Design concept 1960's. 1960's designs for 'big dumb booster'. Isp=270s. More...
  • Press Fed 5748k TRW N2O4/UDMH rocket engine. 56,368 kN. Study 1968. 1960's designs for 'big dumb booster'. Isp=267s. Used on LCLV launch vehicle. More...
  • PSLV-1 ISRO solid rocket engine. 4860 kN. Isp=264s. Used on GSLV, PSLV. First flight 1993. More...
  • PW 1000000 lb LH2 Pratt and Whitney lox/lh2 rocket engine. 4457 kN. Study 1988. Part of launch vehicle proposed by Martin as alternative to NLS. All figures estimated based on 1,000,000 lb thrust single engine. Isp=425s. More...
  • R-101B.36000-0 Isayev Nitric acid/Amine rocket engine. R-101B/R-108 SAM. Developed 1950-51. Launch thrust 83.3 kN. Single chamber engine designed for use in the R-101B and R-108 (derivative of German Wasserfall). More...
  • R-13 Dushkin Nitric acid/Solid hybrid rocket engine. Out of Production. Developed in the late 1950s by OKB Dushkin. It was a combined (powder+liquid) engine, characterized by a new technical approach conceived by Dushkin in the prewar design of the KRD-604. More...
  • R-200 Dushkin rocket engine. 9.8 kN. Out of Production. Thrust variable 0.8 tf -1.0 tf. More...
  • R-31 Lyulka turbojet engine. 91.2 kN. MiG-25. Out of Production. Used in MiG-25. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=2073s. More...
  • R-56 Blok A Notional Nitric acid/Kerosene rocket engine. 4412 kN. R-56 Blok A. Notional engines for polyblock R-56, immense booster/ICBM; planned range 16,000 km. payload 35,000 kg. Tsniimash has 1:10 structural simulation model. Isp=320s. More...
  • RB-211-22B Rolls Royce turbofan engine. 29.4 kN. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=9900s. Used on L1011 launch aircraft for Pegasus, Pegasus XL. First flight 1990. More...
  • RB545 Rolls Royce air augmented rocket engine. 367.7 kN. Used Liquid Air/Lox/LH2. Development ended 1985. Isp=700s. Used on HOTOL launch vehicle. More...
  • RD-0234 Kosberg N2O4/UDMH rocket engine. 520 kN. UR-100N / RS-18 (SS-19) stage 1. Out of Production. Staged combustion cycle. Modification of RD-0233 including tank pressurization system. Isp=310s. First flight 1974. More...
  • RD-0246 Kosberg N2O4/UDMH rocket engine. Design concept. Project for further development of RD-0243. More...
  • RD-0209 Kosberg N2O4/UDMH rocket engine. UR-200 stage 1. Developed 1961-65. Engine unit consisting of 1 RD-0211 for tank pressurization and three RD-0210. Modification of RD-0208 with tank pressurization. Further developed into RD--0211. First flight 1965. More...
  • RD-0208 Kosberg N2O4/UDMH rocket engine. UR-200 stage 1. Developed 1961-65. Stage 1 had three RD-0208 plus one RD-0209. Further developed into RD-0210. More...
  • RD-0216 Kosberg N2O4/UDMH rocket engine. 219 kN. UR-100 stage 1. Isp=313s. Staged combustion cycle. Includes tank pressurization system (RD-0217 without tank press.). First launch November 1963, manufactured until 1974, operational until 1991. First flight 1965. More...
  • RD-0217 Kosberg N2O4/UDMH rocket engine. 219 kN. UR-100, UR-100K stage 1. Out of Production. Staged combustion cycle. Version of RD-0216 without tank pressurization system. Manufacturing until 1974, operational use until 1991. Isp=313s. More...
  • RD-0229M Kosberg Lox/LNG rocket engine. 883 kN. Vozdushnyy Start stage 1. Developed 1997. Derivative of RD-0229 for the propellants LOX and liquid natural gas (methane). Initial candidate for stage 1 propulsion of Vozdushnyy Start project by Kompomash. More...
  • RD-0231 Kosberg N2O4/UDMH rocket engine. 29 kN. P-700 Granit. Out of Production. Staged combustion cycle. Isp=275s. First flight 1970. More...
  • RD-0245-HC Kosberg Lox/Kerosene rocket engine. 214 kN. Design concept 1990's. Proposed variant of RD-0245 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=320s. More...
  • RD-0233 Kosberg N2O4/UDMH rocket engine. 520 kN. UR-100N / RS-18 (SS-19) stage 1. Out of Production. Staged combustion cycle. Isp=310s. First flight 1974. More...
  • RD-0234-HC Kosberg Lox/Kerosene rocket engine. 516 kN. Developed 1996-. Proposed variant of RD-0234 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=331s. More...
  • RD-0242 Kosberg N2O4/UDMH rocket engine. 123.6 kN. sea-based missile booster stage developed 1977-83. Isp=302s. First concept planned N2O4/kerosene as propellant, but changed to N2O4/UDMH. Single ignition, 297 development tests. 50 engines for sale. More...
  • RD-0242-HC Kosberg Lox/Kerosene rocket engine. 125 kN. Developed 1998-. Proposed variant of RD-0242 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=312s. More...
  • RD-0243 Kosberg N2O4/UDMH rocket engine. 825.8 kN. R-29RM stage 1. Out of Production. Isp=300s. Consisted pf single-chamber main engine RD-0244 plus four-chamber steering engines RD-0245 driven by turbine exhaust gas. Engine submerged in propellant tank. More...
  • RD-0244 Kosberg N2O4/UDMH rocket engine. 682 kN. R-29RM / RSM-54 (SS-N-23) stage 1. Out of Production. Main engine in system RD-0243. Staged combustion cycle. Submerged in propellant tank. Isp=310s. First flight 1985. More...
  • RD-0244-HC Kosberg Lox/Kerosene rocket engine. 690 kN. Design concept 1990's. Proposed variant of RD-0244 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=332s. More...
  • RD-0245 Kosberg N2O4/UDMH rocket engine. 211 kN. R-29RM / RSM-54 (SS-N-23) stage 1 vernier. Out of Production. Four-chamber steering engine in system RD-0243 driven by turbine exhaust gas. Isp=300s. First flight 1985. More...
  • RD-0204 Kosberg N2O4/UDMH rocket engine. 559 kN. UR-200 stage 1. Hardware. Diameter is per chamber. Staged combustion cycle. Variant of RD-0203 with additional pressure sensor. Isp=311s. First flight 1964. More...
  • RD-0232 Kosberg N2O4/UDMH rocket engine. UR-100N / Rokot Stage 1. Engine unit (DU - dvigatelnaya ustanovka) consisting of 1 RD-0234 for tank pressurization and three RD-0233. First flight 1972. More...
  • RD-0120-CH Kosberg Lox/LCH4 rocket engine. 1576 kN. Design concept 1990's. Proposed variant of the RD-0120 engine using liquid methane instead of hydrogen as propellant. Isp=363s. More...
  • RD-0215 Kosberg N2O4/UDMH rocket engine. 2450 kN. Developed 1962-65 for heavy Chelomei launcher (UR-900?) stage 1. Isp=310s. Engine unit consisting of 1 RD-0217 for tank pressurization and three RD-0216. Hardware not hot-tested. More...
  • RD-0203 Kosberg N2O4/UDMH rocket engine. 559 kN. UR-200 stage 1. Hardware. DU consisting of 4 RD-0204 gimballed motors. Staged combustion cycle. Isp=311s. First flight 1964. More...
  • RD-0101 Kosberg Lox/Alcohol rocket engine. 39.2 kN. E-50A aircraft by Mikoyan. Out of Production. Chamber pressure 42,7 - 22,1 bar. Specific impulse 255 - 248,5 sec. Isp=255s. More...
  • RD-0102 Kosberg Lox/Kerosene rocket engine. 39.2 kN. Yak-27V aircraft by Yakovlev. Out of Production. Based on RD-0101. Two ignitions possible. Chamber pressure 41,2 - 16,4 bar. Isp=260s. More...
  • RD-0120 Kosberg lox/lh2 rocket engine. 1961 kN. Energia core stage. Design 1987. Isp=455s. First operational Russian cryogenic engine system, built to the same overall performance specifications as America's SSME, but using superior Russian technology. More...
  • RD-0120M Kosberg lox/lh2 rocket engine. 1961 kN. Energia-M core stage. Development ended 1993. Isp=455s. From 1987 KBKhA worked on upgrading the 11D122 (RD-0120) engine for Energia-M launcher, including the possibility to throttle the engine down to 28% thrust. More...
  • RD-0120M-CH Kosberg Lox/LCH4 rocket engine. 1720 kN. Design concept 1990's. Proposed variant of the RD-0120M engine using liquid methane instead of hydrogen as propellant. Isp=372s. More...
  • RD-0124-14D23 Kosberg Lox/Kerosene rocket engine. 298.640 kN. Propoed in 1993 for Angara stage 2 verniers, Kvant-1 stage 1 vernier. Designed 1986-1990. Isp=331s. Variant of RD-0124 with shortened nozzle for sea-level operation. More...
  • RD-012U Bondaryuk ramjet engine. 76 kN. Burya. Out of production. 1.2 m diameter ramjet to be used in Burya cruise missile. Thrust is maximum thrust at cruise altitude. Specific impulse is that at cruise design point. Isp=1500s. First flight 1957. More...
  • RD-020 Bondaryuk ramjet engine. 103 kN. Buran M-42. Development ended 1957. Isp=1500s. Ramjet for Buran cruise missile. 8,500 km cruise at Mach 3.1 at 18-20 km altitude. More...
  • RD-0202 Kosberg N2O4/UDMH rocket engine. 2236 kN. UR-200 stage 1. Engine unit (DU - dvigatelnaya ustanovka) consisting of 1 RD-0204 for tank pressurization and three RD-0203. Isp=311s. First flight 1963. More...
  • RD-0103 Kosberg Lox/Kerosene rocket engine. 34.6 kN. T-3, P-1 aircraft by Sukhoy. Out of Production. Based on RD-0102. Chamber pressure 37.3 - 15.7 bar. Isp=277s. More...
  • RD-0134 Kosberg Lox/LNG rocket engine. 2038 kN. stage 1. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle variant of RD-0139. Isp=358s. More...
  • RD-0200 Kosberg Nitric acid/Amine rocket engine. 58.8 kN. Lavochkin SAM, flew 1960. Out of Production. First liquid rocket engine by OKB-154, evolution of Isayev S2.1200 transferred to Kosberg. Thrust range 59 - 5.9 kN. Sea level specific impulse 230 - 166 sec More...
  • RD-0201 Kosberg Nitric acid/Amine rocket engine. 58.060 kN. SAM V1100 by Grushin stage 3. Out of Production. Thrust range 59 - 28 kN. Isp=260s. First flight 1960. More...
  • RD-018 Bondaryuk ramjet engine. 98 kN. Buran missile, early version. Out of Production. Isp=1500s. 1.8 m diameter ramjet engine initially considered for Buran M-42. RD-020 adpopted later during development. More...
  • RD-0155 Kosberg Lox/Kerosene rocket engine. Design concept 2007. Launch thrust 902.5 kN. Engine proposed to replace RD-107 in Onega and Avrora versions of the Soyuz launch vehicle. More...
  • RD-0143A Kosberg Lox/LNG rocket engine. 343 kN. Vozdushnyy Start stage 1. Design concept 1998-. Proposed single chamber variant of RD-0143. Selected for stage 1 of Vozdushnyy Start project by Kompomash. Isp=370s. More...
  • RD-0141 Kosberg Lox/LNG rocket engine. 2251 kN. stage 1. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Obviously variant of RD-0141 with larger nozzle. Isp=353s. More...
  • RD-0139 Kosberg Lox/LNG rocket engine. 2038 kN. stage 1. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Gas generator cycle with turbine gas injection into supersonic nozzle. Isp=341s. More...
  • RD-118 Glushko Lox/Kerosene rocket engine. 999.601 kN. In production. Isp=311s. Update of RD-107, used in Soyuz ST launcher. Little performance change from RD-107, changes may mainly relate to use of all-Russian components. First flight 2001. More...
  • RD-1KhZ Glushko Nitric acid/Kerosene rocket engine. 2.940 kN. take-off acelleration of Pe-2R, La-7R, Yak-3, Su-6, Su-7, La-120R airplanes. Developed 1941-46. The RD-1KhZ was a variant of the RD-1 engine with chemical ignition. Production 1944-45. Isp=200s. More...
  • RD-107-8D74PS Glushko Lox/Kerosene rocket engine. 971 kN. Sputnik 8K71PS-0. Out of Production. OKB Glushko. Used on 8K71PS Stage 0. Developed in 1956-1957. Flown 1957-1958. Propellants kerosene (RG-1) / Lox. Diameter is per chamber. Isp=306s. More...
  • RD-117 Glushko Lox/Kerosene rocket engine. 1021.097 kN. Soyuz ST stage 1. In production. Update of RD-107. Little performance change from RD-107, changes may mainly relate to use of all-Russian components. Isp=310s. First flown 2001. More...
  • RD-117PF Glushko Lox/Kerosene rocket engine. manned Soyuz-launcher stage 1. Design concept. Update of RD-107. Probably version using Sintin instead of kerosene. More...
  • RD-114 Glushko lox/udmh rocket engine. 1653 kN. Used in ICBM stage 1 (stage 2 was RD-115). Developed 1961-65. Isp=341s. More...
  • RD-112 Glushko lox/udmh rocket engine. 1089 kN. ICBM stage 1 (stage 2 was RD-113). Developed 1960. Isp=344s. More...
  • RD-111 Glushko Lox/Kerosene rocket engine. 1628 kN. R-9 stage 1. Isp=317s. Developed for R-9 ICBM. It had special flexible pipelines and gimbals, allowing lox loading in 20 minutes. First flight 1961. More...
  • RD-108-8D77 Glushko Lox/Kerosene rocket engine. 804 kN. Sputnik 8A91-1. Out of Production. Diameter is per chamber. Isp=315s. First flight 1958. More...
  • RD-120K Glushko Lox/Kerosene rocket engine. 873 kN. Soyuz M stage 1, 2. Proposed for X-34. Isp=336s. Sea-level variant of RD-120. As of 1996 RD-120 prototype with 1.8 m diameter had been built, development time estimated for three years. More...
  • RD-191 Glushko Lox/Kerosene rocket engine. 2079 kN. Isp=337s. Proposed for stage 1 of Angara. Single chamber from 4-chamber RD-170 would have been cheap and fast to develop. Only reached the draft project stage by 2003. Gimbaling +/- 8 degree in two planes. More...
  • RD-110 Glushko Lox/Kerosene rocket engine. 1374 kN. Development ended 1949. Isp=285s. For R-3 IRBM, 19 ED-140 7 tonne chambers used as preburners to feed a main mixing chamber, a scale-up of the V-2 production motor. Tested, but technical problems too severe. More...
  • RD-120M Glushko Lox/Kerosene rocket engine. 850.4 kN. PacAstro-2 stage 1. Out of Production. Sea-level variant of RD-120 engine, similar to RD-120K. Gimbaling +/- 6 degree in two planes. Isp=330s. More...
  • RD-169 Glushko Lox/LCH4 rocket engine. 167 kN. Riksha-0 stage 1. Design concept 1990's. Isp=351s. LOX/Methane engine derived from RD-120. Gimbaling +/- 8 degree in two planes. In 1996 prototype development was estimated to take four years from go-ahead. More...
  • RD-170 Glushko Lox/Kerosene rocket engine. 7903 kN. Energia strap-on. Developed 1973-1985. Isp=337s. First flight 1987. Used one-plane gimablling versus the two-plane gimablling required on the RD-171 of the Zenit launch vehicle. Designed for 10 reuses. More...
  • RD-171 Glushko Lox/Kerosene rocket engine. 7903 kN. Zenit stage 1. In production. Isp=337s. RD-171 used two-plane gimablling versus one-plane gimablling on RD-170 developed in parallel for Energia. First flight 1985. More...
  • RD-172 Glushko Lox/Kerosene rocket engine. 8354 kN. Zenit-3 stage 1 (?). Developed -1994. Uprated version of RD-171. To have been qualified for flight 1994. Isp=337s. More...
  • RD-173 Glushko Lox/Kerosene rocket engine. 8181 kN. Zenit-3 stage 1 (?). Design concept 1990's. Uprated version of RD-171 with 4 chambers, 1 turbo-pump and 2 gas generators. Intended for uprated Zenit named Zenit 3 Isp=337s. More...
  • RD-174 Glushko Lox/Kerosene rocket engine. 7905 kN. Angara stage I. Developed 1995-. More...
  • RD-180 Glushko Lox/Kerosene rocket engine. 4152 kN. Atlas III, Atlas V stage 1. In production. Isp=337s. First flight 2000. Two-thrust-chamber derivative of the four-chamber RD-170 used on Zenit. More...
  • RD-182 Glushko Lox/LCH4 rocket engine. 902 kN. Riksha (-1, -2) stage 1. Developed 1994-. Isp=353s. Methane variant of RD-120K engine. Thrust range and Isp range due to throat diameter and chamber pressure. Gimbaling +/- 6 degree in two planes. More...
  • RD-190 Glushko Lox/LCH4 rocket engine. 1000 kN. Riksha-0 stage 1. Developed 1996-. The RD-190 consists of 6 RD-169 engines. Each chamber can be gimbaled individually in two planes by +/- 8 degree. Isp=351s. More...
  • RD-191M Glushko Lox/Kerosene rocket engine. 1976 kN. Angara stage I. Developed 1996-. Single chamber version of the RD-170 / RD-171. Isp=337s. More...
  • RD-108-8D75PS Glushko Lox/Kerosene rocket engine. 912 kN. Sputnik 8K71PS-1. Out of Production. Diameter is per chamber. Isp=308s. First flight 1957. More...
  • RD-182M Glushko Lox/LNG rocket engine. 882 kN. Vozdushnyy Start stage 1. Developed 1998-. Variant of RD-182 engine for liquid natural gas (mainly CH4). Proposed initial candidate for project Vozdushnyy Start of Kompomash. More...
  • RD-102 Glushko Lox/Alcohol rocket engine. 428 kN. R-3A. Development ended 1951. Project for R-3A experimental missile. Stopped in favor of RD-103. Isp=235s. More...
  • RD-108-8D75K Glushko Lox/Kerosene rocket engine. 941 kN. Molniya 8K78-1, R-7A 8K74-1, Voskhod 11A57-1, Vostok 8A92-1, Vostok 8A92M-1. Diameter is per chamber. Isp=315s. First flight 1959. More...
  • RD-108-11D512 Glushko Lox/Kerosene rocket engine. 997 kN. Soyuz 11A511-1, Soyuz 11A511U-1. Design 2000. Diameter is per chamber. Isp=315s. First flight 1965. More...
  • RD-1 Glushko Nitric acid/Kerosene rocket engine. 2.940 kN. Take-off acelleration of Pe-2, La-7, Yak-3, Su-6 airplanes. Developed 1941-45. First Russian liquid propellant rocket engine. Production 1944-45. Ignition was by an ethane-air mixture. Isp=200s. More...
  • RD-101 Glushko Lox/Alcohol rocket engine. 404 kN. R-2 and V-2A. Isp=237s. Developed simultaneously with the RD-100 but with no German involvement. More compact, increased thrust, increased chamber pressure and higher alcohol concentration. First flight 1949. More...
  • RD-103 Glushko Lox/Alcohol rocket engine. 500 kN. R-5. Out of Production. Isp=243s. Final extrapolation of the V-2 rocket engine in Russia. First flight 1953. More...
  • RD-103M Glushko Lox/Alcohol rocket engine. 500.1 kN. R-5M 8K51. Isp=248s. First flight 1953. More...
  • RD-103RD Glushko Lox/Alcohol rocket engine. M5RD. Out of Production. More...
  • RD-105 Glushko Lox/Kerosene rocket engine. 627.6 kN. R-7 ICBM stage 1 (strap-on) initial project. Out of Production. Isp=302s. Single chamber engine intended for the R-7 strap-ons in mid-1950s. Subsequently replaced by the 4 chamber RD-107. More...
  • RD-106 Glushko Lox/Kerosene rocket engine. 645.3 kN. R-7 ICBM stage 2 (core) initial project. Out of Production. Isp=310s. Single chamber engine intended for the R-7 sustainer. Version of RD-105 with larger nozzle. Subsequently replaced by the 4 chamber RD-108. More...
  • RD-107-11D511 Glushko Lox/Kerosene rocket engine. 992 kN. Soyuz 11A511-0, Soyuz 11A511U-0. Design 2000. Diameter is per chamber. Isp=314s. First flight 1965. More...
  • RD-107-11D511P Glushko Lox/Kerosene rocket engine. 996.4 kN. Soyuz 11A511U2-0. Out of production. OKB Glushko. Used on 11A511U2 Stage 0. Propellants kerosene (RG-1) / Lox. Diameter is per chamber. Isp=314s. First flight 1982. More...
  • RD-108-8D75 Glushko Lox/Kerosene rocket engine. 912 kN. R-7 8K71-1, Vostok 8K72-1, Vostok 8K72K-1. OKB Glushko. Used on 8K71 R-7 Stage 1. Developed in 1954-1955. Propellants kerosene (RG-1) / Lox. Diameter is per chamber. Isp=308s. First flight 1957. More...
  • RD-100 Glushko Lox/Alcohol rocket engine. 304 kN. R-1, V-1A. Isp=237s. Russian copy of the V-2 engine using Russian materials - which made it very difficult! German rocket scientists assisted in its development. First flight 1948. More...
  • RD-107-8D728 Glushko Lox/Kerosene rocket engine. 996 kN. Molniya 0, Molniya 8K78M-0. OKB Glushko. Used on Molniya 8K78M and 11A57 Stage 0. Propellants kerosene (RG-1 or T-1) / Lox. Diameter is per chamber. Isp=314s. First flight 1964. More...
  • RD-108-8D75-1959 Glushko Lox/Kerosene rocket engine. 941 kN. Out of production. Further development of 8D74-1958, 1958-1959. Diameter is per chamber. Isp=315s. Used on Vostok 8K72K launch vehicle. First flight 1960. More...
  • RD-108-8D75-1958 Glushko Lox/Kerosene rocket engine. 941 kN. Luna 8K72-1. Out of production. Diameter is per chamber. Isp=315s. First flight 1958. More...
  • RD-108-8D727 Glushko Lox/Kerosene rocket engine. 977 kN. Molniya 1, Molniya 8K78M-1. OKB Glushko. Used on Molniya 8K78L, 8K78M and 11A57 Stage 1. Propellants kerosene (RG-1 or T-1) / Lox. Diameter is per chamber. Isp=316s. First flight 1964. More...
  • RD-108-11D512P Glushko Lox/Kerosene rocket engine. 1011 kN. Soyuz 11A511U2-1. Out of production. Isp=319s. A 1-2 second specific impulse increase was made possible by the use of synthetic fuel Sintin and a modified mixing head. First flight 1982. More...
  • RD-107-8D76 Glushko Lox/Kerosene rocket engine. 971 kN. Sputnik 8A91-0. Out of Production. OKB Glushko. Used on 8A91 Stage 0. Developed in 1956-1957. Propellants kerosene (RG-1) / Lox. Diameter is per chamber. Isp=310s. First flight 1958. More...
  • RD-107-8D74K Glushko Lox/Kerosene rocket engine. 996 kN. Developed in 1957-1960. Used in strap-ons for Molniya 8K78, R-7A 8K74, Voskhod 11A57, Vostok 8A92, Vostok 8A92M. Isp=313s. Fuel T-1 or RG-1 kerosene. First flight 1959. More...
  • RD-107-8D74-1959 Glushko Lox/Kerosene rocket engine. 996 kN. Out of production. Diameter is per chamber. Isp=313s. Used on Vostok 8K72K launch vehicle. First flight 1960. More...
  • RD-107-8D74-1958 Glushko Lox/Kerosene rocket engine. 996 kN. Luna 8K72-0. Out of production. Diameter is per chamber. Isp=312s. First flight 1958. More...
  • RD-107-8D74 Glushko Lox/Kerosene rocket engine. 971 kN. R-7 8K71, Vostok 8K72, Vostok 8K72K strap-ons. Isp=306s. First flight 1957. Used four combustion chambers fed by single turbopump to circumvent combustion instability problems with larger chambers 1950's. More...
  • RD-253 Glushko N2O4/UDMH rocket engine. 1745 kN. In Production. Version of RD-253 with thrust increased by 7%. Included an additional gas generator for tank pressurization. First flight 1986. More...
  • RD-2MZV-F Dushkin Nitric acid/Kerosene rocket engine. 19.6 kN. Samolet 5. Developed 1946. More...
  • RD-264 Glushko N2O4/UDMH rocket engine. 4521 kN. R-36M / RS-20A (SS-18 Mod 1) stage 1. Consists of four RD-263 engines. Isp=318s. Used on Dnepr launch vehicle. First flight 1986. More...
  • RD-253-14D14 Glushko N2O4/UDMH rocket engine. 1746 kN. Proton KM-1. In production. Developed in 1990s. Isp=317s. First flight 1999. More...
  • RD-261 Glushko N2O4/UDMH rocket engine. 3032 kN. Tsyklon 3 stage 1. In production. Based on RD-251 Isp=301s. First flight 1977. More...
  • RD-263 Glushko N2O4/UDMH rocket engine. 1155 kN. R-36M / RS-20A (SS-18 Mod 1) stage 1. Out of Production. Four RD-263 engines combined into RD-264 system. Isp=318s. More...
  • RD-263F Glushko N2O4/UDMH rocket engine. Developed 1980. Project to upgrade RD-263. Upgrade was realized in RD-273 engine. More...
  • RD-253-11D48 Glushko N2O4/UDMH rocket engine. 1635 kN. Isp=316s. Six gimballed single chamber RD-253s provide the first stage power for the UR-500 Proton launch vehicle. First flown in 1965. More...
  • RD-268 Glushko N2O4/UDMH rocket engine. 1236 kN. MR-UR-100 / RS-16 (SS-17) stage 1. Out of Production. First flight 1976. Modification of RD-263 engine. Isp=319s. First flight 1990. More...
  • RD-270 Glushko N2O4/UDMH rocket engine. 6713 kN. UR-700, R-56 stage 1. Development ended 1968. Isp=322s. Developed 1962-1971, largest rocket engine ever built in the Soviet Union, answer to F-1. Tested but cancelled before combustion instability problems solved. More...
  • RD-270M Glushko exotic N2O4/Pentaborane rocket engine. 7159 kN. Isp=365s. In 1962-1970 Glushko studied use of Pentaborane 'zip' propellants in his monster RD-270 engine. Created immense toxicity problems but increased specific impulse of the engine by 42 seconds. More...
  • RD-273 Glushko N2O4/UDMH rocket engine. 1238 kN. Developed 1975-82. Upgrade of RD-263 in 1982 based on RD-263F project. More...
  • RD-274 Glushko N2O4/UDMH rocket engine. 4952 kN. Developed 1975-85. Upgrade of RD-264 engine with increased chamber pressure and thrust. Development stopped due to problems with turbopump shaft balance. More...
  • RD-2MZV Dushkin Nitric acid/Kerosene rocket engine. 13.7 kN. I-270. Developed 1944-47. Thrust variable 0.1-0.3 tf / 0.35-1.4 tf. More...
  • RD-251 Glushko N2O4/UDMH rocket engine. 2643 kN. R-36-0 stage 1, Tsyklon 2 stage 1. In production. Assembly of 3 RD-250-type units. Isp=301s. First flight 1965. More...
  • RD-212 Glushko Nitric acid/Kerosene rocket engine. 623 kN. Developed 1952-56. Isp=253s. Original four-chamber engine design planned for the booster stage of the Buran intercontinental ramjet missile. Abandoned due to limited thrust; RD-213 was developed instead. More...
  • RD-275 Glushko N2O4/UDMH rocket engine. 1745 kN. Proton stage 1. In Production. Uprated version of RD-253, developed in the 1980's. Isp=317s. First flight 1986. More...
  • RD-216 Glushko Nitric acid/UDMH rocket engine. 1728 kN. R-14, Kosmos 11K65 stage 1. Isp=291s. RD-216 was an assembly of 2 RD-215's with 2 combustion chambers and 2 turbines. Two sets of these were in turn used in the first stage of the R-14. First flight 1964. More...
  • RD-2 Glushko Nitric acid/Kerosene rocket engine. 6 kN. experimental. Developed 1945-47. The RD-2 was based on the RD-1 engine. Used chemical ignition. Isp=200s. More...
  • RD-200 Glushko Nitric acid/Kerosene rocket engine. 98.508 kN. vertical sounding rocket. Developed -1951. Isp=234s. More...
  • RD-210 Glushko Nitric acid/Kerosene rocket engine. 29.850 kN. vertical sounding rocket. Developed -1954. Isp=241s. More...
  • RD-211 Glushko Nitric acid/Kerosene rocket engine. 642.3 kN. long-distance missile. Developed 1952-55. Original four-chamber engine design planned for use on the R-12 IRBM. Abandoned due to limited thrust and the RD-214 was developed in its place. Isp=261s. More...
  • RD-213 Glushko Nitric acid/Kerosene rocket engine. 755 kN. Winged rocket M-40 (2). Development ended 1957. Two thrust levels. Ignition with propellant TG-02. Chamber pressure 233,8 / 46,6 bar. Specific impulse 223 / 231 sea level. Isp=254s. More...
  • RD-214 Glushko Nitric acid/Kerosene rocket engine. 730 kN. R-12, Kosmos 11K63 stage 1. Isp=264s. Single turbopump driven by H2O2 gas generator feeding four fixed chambers. Ignition with propellant TG-02. First flight 1957. More...
  • RD-215 Glushko Nitric acid/UDMH rocket engine. 864 kN. R-14, Kosmos 11K63 stage 1. Out of Production. Original intended use unknown. Two RD-215 clustered to make RD-216. Isp=291s. First flight 1966. More...
  • RD-250 Glushko N2O4/UDMH rocket engine. 881 kN. R-36-0 stage 1, Tsyklon 2 stage 1. Out of Production. Assembly of 3 RD-250 units make RD-251. Isp=301s. More...
  • RD-216M Glushko Nitric acid/UDMH rocket engine. Kosmos-3M stage I. Out of Production. More...
  • RD-217 Glushko Nitric acid/UDMH rocket engine. 865 kN. R-16 stage 1. Out of Production. Original intended use unknown. Three RD-217 clustered to make RD-218. Isp=289s. First flight 1961. More...
  • RD-218 Glushko Nitric acid/UDMH rocket engine. 2592 kN. R-16 stage 1. Isp=289s. Consisted of three RD-217; had 6 combustion chambers and 3 turbines; powered the R-16 ICBM. First flight 1960. More...
  • RD-220 Glushko Nitric acid/UDMH rocket engine. 1074 kN. missile stage 1 (stage 2 used RD-221). Developed 1960-. Isp=306s. More...
  • RD-222 Glushko Nitric acid/UDMH rocket engine. 1634 kN. missile stage 1 (stage 2 used RD-223). Developed 1960-61. Precursor to RD-253. Isp=302s. More...
  • RD-224 Glushko Nitric acid/UDMH rocket engine. 1778 kN. R-26 stage 1. Out of production. RD-224 is a block of 2 RD-225s. An upper stage thrust chamber was developed under designation U102-000. Isp=294s. First flight 1961. More...
  • RD-225 Glushko Nitric acid/UDMH rocket engine. 889 kN. R-26 stage 1. Out of Production. Two clustered together to make RD-224. Isp=294s. First flight 1961. More...
  • RD-36-41 Lyulka turbojet engine. 158.4 kN. T-4. Out of Production. Used in Sukhoi March 3 aircraft. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=1980s. More...
  • RD-3A Glushko Lox/Alcohol rocket engine. R-3A. Out of Production. Project for R-3A experimental missile. Stopped in favour of RD-103. More...
  • RD-3 Glushko Nitric acid/Kerosene rocket engine. 9 kN. experimental. Developed 1950's. The RD-3 was a cluster of three RD-1 engines with a new common turbopump. Ignition was by an ethane-air mixture. Isp=190s. More...
  • RD-68M Yuzhnoye N2O4/UDMH rocket engine. 285 kN. R-36 stage 1 attitude control engine. Out of Production. 4 nozzles, maximum 42 degree gimbal angle. More...
  • RD-69 Yuzhnoye Nitric acid/UDMH rocket engine. 49.2 kN. R-16 stage 2 attitude control engine. Out of Production. More...
  • RD-68 Yuzhnoye Nitric acid/UDMH rocket engine. 380 kN. R-16 stage 1 attitude control engine. Out of Production. More...
  • RD-701 Glushko lox/lh2/kerosene tripropellant rocket engine for air-launched MAKS spaceplane. 4003 kN. Development ended 1988. Isp=415 / 460s. First flight 2001. More...
  • RD-851 Yuzhnoye Nitric acid/UDMH rocket engine. 32.480 kN. R-16 (SS-7) stage 1 attitude control engine . Out of Production. Four thrusters are each gimbaled in one single axis. Isp=279s. More...
  • RD-855 Yuzhnoye N2O4/UDMH rocket engine. 328 kN. Tsyklon stage 1 attitude control engine. Out of Production. Isp=292s. Four-chamber pump-fed single-run engine burned hypergolic propellants in a gas generator scheme. More...
  • RD-863 Yuzhnoye N2O4/UDMH rocket engine. 276.840 kN. MR-UR-100 / RS-16 (SS-17) stage 1 attitude control engine. Out of Production. Isp=301s. More...
  • RDKS-1 Russian rocket engine. Developed End 40's. Single chamber with turbopump propellant feed. More...
  • RDKS-100 Dushkin Lox/Kerosene rocket engine. 980 kN. Sanger. Developed 1946-51. Isp=285s. More...
  • RDMT-5 NII Mash air cold gas thruster. 5 N. MMK. In Production. Low-thrust cold-gas thruster. Isp=70s. More...
  • Redesigned SRM Thiokol solid rocket engine. 11,520 kN. In Production. Isp=268s. Replacement shuttle solid rocket booster with redesigned field joints to prevent failure that caused the Challenger disaster. More...
  • RJ47 Wright ramjet engine. 44.6 kN. Development ended 1958. Thrust is maximum thrust at cruise altitude. Specific impulse is that at cruise design point. Isp=1200s. Used on Navaho G-38 launch vehicle. More...
  • RKDS-100 Glushko Lox/Kerosene rocket engine. 980 kN. Keldysh Bomber. Design 1946. Nominal design engine for 1946 Keldysh bomber design. The Soviet Union would not produce an engine with these propellants and thrust levels until nearly 20 years later. Isp=285s. More...
  • RL-10A-5 Pratt and Whitney lox/lh2 rocket engine. 64.7 kN. Isp=373s. Throttleable to 30% of thrust, sea level version of RL10. Four engines were built and were used on the DC-X and the upgraded DC-XA VTOVL SSTO launch vehicle demonstrators. First flight 1993. More...
  • RL-10A-5KA Pratt and Whitney lox/lh2 rocket engine. 100.488 kN. Kistler proposal. Design 1992. Isp=398s. Throttleable to 30% of thrust, sea level version of RL10 with extendable nozzle for high altitude operation. More...
  • RLA-1200 Glushko Lox/Kerosene rocket engine. 12,700 kN. Design 1974. Proposed engines for the RLA series launch vehicles. This version would use four chambers. 'Down-sized' to 200 tonnes thrust for Energia. More...
  • RLA-600 Glushko Lox/Kerosene rocket engine. 6370 kN. Design 1972. Two-chamber version of RLA-300. Proposed for the RLA series launch vehicles and the UR-700M Mars booster. More...
  • Rotary Rocket XCOR Lox/Kerosene rocket engine. 22.250 kN. First stages. Developed in 1990's. Developed and tested by Rotary Rocket for their launcher before its cancellation. More...
  • RPD-04 Dushkin Lox/Kerosene rocket engine. Out of Production. More...
  • RS-27 Rocketdyne Lox/Kerosene rocket engine. 1023 kN. Out of production. Isp=295s. Consisted of RS2701A/B main engine, and twin LR101-NA-11 verniers. Introduced in 1974 on the McDonnell Douglas' Delta 2000 series launcher; replaced the MB-3. First flight 1972. More...
  • RS-27A Rocketdyne Lox/Kerosene rocket engine. 1054.2 kN. . Isp=302s. Replaced the RS-27 as the main system for the Delta and in the MA- 5A for the Atlas. RS2701B main engine, and twin LR101-NA-11 verniers. First flight 1989. More...
  • RS-27C Rocketdyne Lox/Kerosene rocket engine for Delta 7000. 1054.2 kN. Isp=302s. First flight 1990. More...
  • RS-56-OBA Rocketdyne Lox/Kerosene rocket engine. 1046.8 kN. Out of production. Designed for booster applications. Gas generator, pump-fed. Isp=299s. Booster engine for Atlas II, IIA, IIAS. First flight 1991. More...
  • RS-56-OSA Rocketdyne Lox/Kerosene rocket engine. 386.4 kN. Out of production. Designed for booster applications. Gas generator, pump-fed. Isp=316s. Sustainer engine for Atlas II, IIA, IIAS. First flight 1991. More...
  • RS-68 Rocketdyne lox/lh2 rocket engine. 3312 kN. In production. Isp=420s. First new large liquid-fueled rocket engine developed in America in more than 25 years. Powered the Delta IV booster. First flight 2002. More...
  • RS-68 Regen Rocketdyne lox/lh2 rocket engine. Design concept -2004. Upgrade to basic RS-68 for Delta IV Heavy growth versions. Would use a regeneratively-cooled expansion nozzle, allowing it to run hotter, with higher thrust and specific impulse. More...
  • RS-68B Rocketdyne lox/lh2 rocket engine. Design concept -2004. Upgrade (details not specificed) to basic RS-68 for Delta IV Heavy growth versions. More...
  • RS-800 Rocketdyne lox/lh2 rocket engine. 4110 kN. Design concept -2004. New high-thrust cryogenic engine for Delta IV Heavy growth versions. More...
  • RS-84 Rocketdyne lox/kerosene rocket engine. 5159 kN. Booster stages. Development ended 2005. Isp=335s. Design for NASA's Space Launch Initiative; borrowed extensively from Russian technology developed in the forty years since the USA abandoned the F-1. More...
  • RS-X Rocketdyne Lox/Kerosene rocket engine. 1890 kN. Design concept -1997. Employed existing Delta and Atlas MA and RS engine hardware with a new thrust chamber assembly to generate a thrust of 1890 kN for ELV applications. More...
  • RS-XXX Rocketdyne lox/lh2 rocket engine. 8230 kN. Design concept -2004. New high-thrust cryogenic engine concept for Next Generation Delta with 7 m diameter modules. More...
  • RSA-4-1 South Africansolid rocket engine. 1520 kN. Development ended 1994. Isp=263s. Used on RSA-4 launch vehicle. More...
  • RSA-3-1 South Africansolid rocket engine. 500 kN. Out of production. Built in both Israel and South Africa for RSA-3 and Shavit. Source: Missile exhibit and placards, AF Museum, South Africa. Isp=273s. First flight 1988. More...
  • RSRM Thiokol solid rocket engine. 11,520 kN. Study 1996. After the Challenger disaster the redesigned solid rocket motors had a slight reduction in performance due to reliability improvements. Isp=267s. More...
  • RZ.2 Rolls Royce Lox/Kerosene rocket engine. 836.3 kN. Isp=282s. Used on Europa launch vehicle. First flight 1964. More...
  • S-155 Dushkin rocket engine. 39 kN. E-50. Developed 1955-56. Thrust variable 2000 - 4000 kgf. More...
  • S-3 Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Juno II, Saturn A-2 studies of 1959. Isp=282s. First flight 1958. More...
  • S-3-20M5A Dushkin Nitric acid/Kerosene rocket engine. U-21. Developed -1959. Launch thrust 29.4 kN. More...
  • S-43 IAE solid rocket engine. 303 kN. Isp=265s. Used on VLS launch vehicle. First flight 1985. More...
  • S09.29 Isayev Nitric acid/Amine rocket engine. 88 kN. V-300/V-303 (S-25 system). Out of Production. More...
  • S09.502 Isayev Nitric acid/Amine rocket engine. R-101 SAM. Developed 1949-50. Launch thrust 78.4 kN. Four chamber engine designed for use in the R-101 (derivative of German Wasserfall). Abandoned by 1950 in favour of single-chamber engine. More...
  • S1.35800 Korolev Lox/Kerosene rocket engine. 30 kN. R-7 verniers. Out of Production. Thrust variable 2.5-3.1 tf More...
  • S2.1200 Isayev rocket engine. Developed 1950s middle. OKB-2 transferred work on the S2.1200 to OKB-154 in 1957. The latter used the designation RO-1 for the engine. More...
  • S2.145 Isayev rocket engine. 88 kN. Developed 1950s early. More...
  • S2.1150 Isayev Nitric acid/Amine rocket engine. 671.2 kN. Burya booster. Out of production. Isp=250s. First flight 1957. Engines developed from R-11 S2.253 engine. More...
  • S2.1100 Isayev rocket engine. V-1000. Out of Production. OKB-2 transferred work on the S2.1100 to OKB-117 in 1958-59. OKB-117 completed development. More...
  • S2.253 derivative Isayev Lox/Kerosene rocket engine. 93.2 kN. EKR (experimental winged missile). Study 1953. Derivative of S2.253 was proposed for use in EKR Stage 1 (project for an experimental winged missile). Isp=250s. More...
  • S2.253A Isayev Nitric acid/Kerosene rocket engine. 93 kN. R-11FM. Out of Production. Used in R-11FM submarine version of Scud B. Fuel Kerosene T-1, chemical ignition by TG-02. Mixture ratio derived from tank content. 81 kN sea-level. More...
  • S2.253 Isayev Nitric acid/Kerosene rocket engine. 93.3 kN. R-11 (Scud B) 8A61. Thrust 8300 kgf at sea level. Fuel Kerosene T-1, chemical ignition by TG-02. Isp=251s. First flight 1953. More...
  • S2.713 Isayev Nitric acid/Amine rocket engine. 252.2 kN. R-13 (SS-N-4). Out of Production. First engine to employ gas generator on main propellants. One main and four vernier thrusters. (Mixture derived ratio from tank content.) More...
  • S2.720 Isayev Nitric acid/Amine rocket engine. 34.3 kN. Engine for SAM-missile V-755. Out of Production. Pump-fed engine. Used in engine unit of a special apparatus. Pump-fed engine. 20,4 kN sea level. More...
  • S2.721V Isayev Nitric acid/Amine rocket engine. 11.8 kN. KSR. Developed 1956-. More...
  • S3.42A Sevruk rocket engine. 166 kN. 217. Out of Production. More...
  • S5.1 Isayev Nitric acid/Amine rocket engine. 167 kN. SAM-missiles 217M and 218. Out of Production. Designation unknown. More...
  • S5.3 Isayev Nitric acid/Amine rocket engine. 392 kN. R-21 (SS-N-5). Out of Production. First engine to start underwater. 392 kN sea-level. More...
  • S5.3M Isayev Nitric acid/Amine rocket engine. 396.7 kN. R-9 (SS-8) missile stage 1. Out of Production. Proposed for R-9 missile stage 1. Four engines per stage. 396,7 kN sea-level. More...
  • S5.44 Isayev Nitric acid/Amine rocket engine. 177 kN. SAM-missile 5Ya24. Out of Production. Could be throttled. 177-49 kN sea-level. Area ratio 118 - 44. More...
  • Sabre Rolls Royce air augmented rocket engine. Used Air/Lox/LH2. Developed -1995. Isp=700s. In development for Skylon launch vehicl; descendent of RB545 developed for abandoned HOTOL space launcher. More...
  • Sanger-Bredt Notional Lox/Kerosene rocket engine. 1428.8 kN. Study 1943. Used in Sanger-Bredt. Isp=306s. More...
  • Sanger-Bredt Sled Saenger Lox/Alcohol rocket engine. 1144.1 kN. Study 1943. Isp=245s. Used on Sanger launch vehicle. More...
  • SB-735 Nissan solid rocket engine. 327.8 kN. Isp=263s. Used on Mu-3S launch vehicle. First flight 1969. More...
  • SBIR Hybrid SpaceDev N2O/Solid hybrid rocket engine. 1100 kN. First stage. Upper-stage hybrid propulsion system, part of 2004 Phase 2 of SBIR contract from AFRL for a hybrid rocket motor-based small launch vehicle project. More...
  • Scramjet Scramjet engine for X-30 SSTO. 1372.9 kN. Development ended 1992. Thrust is maximum sea level thrust; specific impulse is average during ascent. Isp=1550s. Propellant Slush LH2. More...
  • Sea Dragon-1 Aerojet Lox/Kerosene rocket engine. 356,9 kN. Design, 1962. Isp=290s. Truax pressure fed design. Thrust, chamber pressure varied during ascent. More...
  • SLV-1 ISRO solid rocket engine. 502.6 kN. Isp=253s. Used on ASLV, PSLV, SLV. First flight 1979. More...
  • SPB 7.35 SNPE solid rocket engine. 690 kN. Isp=263s. Strap-on booster for Advanced Scout, Ariane 2/3. First flight 1984. More...
  • SPRD-15 Kartukov solid rocket engine. 402 kN. S-2 Strela-2 missile, Sopka. Out of Production. Thrust 27 tf at cutout - 41at ignition. More...
  • SPRD-30 Kartukov solid rocket engine. 294 kN. P-15 Termit. Out of Production. Thrust 28 tf at cutout - 30 tf at ignition. More...
  • SPRD-99 Kartukov solid rocket engine. 24.5 kN. MiG-21PFM. Out of Production. More...
  • SRB Thiokol solid rocket engine. 11,520 kN. Isp=269s. Segmented solid rocket boosters for the compromised space shuttle design. Field joint design led to Challenger shuttle disaster. Production 1981-1985, after which superseded by RSRM's. More...
  • SRB-A Nissan solid rocket engine. 2250 kN. In production. Monolithic motor, shorter than that for H-2, using Thiokol filament wound composite structure. Isp=280s. First flight 2001. More...
  • SSME Rocketdyne lox/lh2 rocket engine. 2278 kN. In production. Isp=453s. Space Shuttle Main Engines; only high-pressure closed-cycle reusable cryogenic rocket engine ever flown. . Three mounted in the base of the American space shuttle. First flight 1981. More...
  • SSME Plus Notional lox/lh2 rocket engine. 3728.7 kN. VTOHL studies, 1978. Isp=467s. More...
  • STME Rocketdyne lox/lh2 rocket engine. 2890 kN. Cancelled 1984. Isp=430s. Space Transportation Main Engine. Rocketdyne was teamed with Aerojet and Pratt & Whitney on the STME, which was to have powered the next generation of large launch vehicles. More...
  • T-7A Booster Fourth Academy solid rocket engine. 46 kN. T-7 sounding rocket. Out of Production. Isp=209s. China's first flight solid rocket. First flight 1965. Polysulfide binder with aluminium binder fuel in case of high strength steel with a graphite throat insert. More...
  • Thiokol 156 Thiokol solid rocket engine. 14,746.1 kN. Developed to 1966. Isp=263s. More...
  • TR-106 TRW lox/lh2 rocket engine. 2892 kN. Development. Innovative TRW 650K Low Cost Pintle Engine, test fired at NASA's test center in October 2000. More...
  • TX-354-3 Thiokol solid rocket engine. 258.9 kN. Used in Scout A; Delta E; H-1-0; Castor 2. License built in Japan for H-1. Isp=262s. First flight 1960. More...
  • U-1250 Isayev rocket engine. 12.7 kN. Developed 1945-46. Isp=208s. More...
  • U-2000 Isayev rocket engine. 19.6 kN. for SAM. Out of Production. More...
  • U-400-2 Isayev Nitric acid/Amine rocket engine. Shchuka. Out of Production. More...
  • U-400-10 Isayev rocket engine. 3.920 kN. Samolet 5. Developed 1946-47. More...
  • UA-156 CSD solid rocket engine. 8924.3 kN. Tested 1968. Isp=263s. Proposed as strap-on booster for Saturn INT-27, Saturn V-25(S)B, Saturn V-25(S)U. More...
  • UA1207 CSD solid rocket engine. 7116.9 kN. Isp=272s. First flight 1989. More...
  • UA1206 CSD solid rocket engine. 6226.9 kN. Isp=265s. Used on Titan 34D launch vehicle. First flight 1982. More...
  • UA1205 CSD solid rocket engine. 5849.3 kN. Out of production. Isp=263s. Strap-on boosters for Titan 3C, 3D, 3E. Proposed for advanced Saturn IB versions. First flight 1965. More...
  • USRM Hercules solid rocket engine. 7560.5 kN. Isp=286s.Strap-on booster for Titan 4B. First flight 1997. More...
  • Vexin B SEP N2O4/UDMH rocket engine. 75.4 kN. Out of production. Isp=251s. Used on Diamant launch vehicle. First flight 1965. More...
  • Vexin C SEP N2O4/UDMH rocket engine. 99.1 kN. Out of production. Isp=251s. Used on Diamant B launch vehicle. First flight 1970. More...
  • Viking 2 SEP N2O4/UDMH rocket engine. 693 kN. In production. Isp=281s. Used on Ariane 1, GSLV space launchers. First flight 1979. More...
  • Viking 2B SEP N2O4/UDMH rocket engine. 720 kN. Isp=278s. Used on Ariane 2/3. First flight 1984. More...
  • Viking 5C SEP N2O4/UDMH rocket engine. 752 kN. Isp=278s. Used on Ariane 42L, Ariane 44L, Ariane 44LP. First flight 1988. More...
  • Von Braun-1 Notional Nitric acid/UDMH rocket engine. 3057.3 kN. Study 1952. Isp=286s. Used on Von Braun launch vehicle. More...
  • Vulcain SEP, Ottobrunn lox/lh2 rocket engine. 1075 kN. In production. Isp=431s. Powered the cryogenic core stage of Ariane 5. First flight 1996. More...
  • Vulcain 2 SEP, Ottobrunn lox/lh2 rocket engine. 1350 kN. In development. Isp=434s. New generator cycle rocket engine for an Ariane 5 core stage upgrade. Thrust increased more than 30% from Vulcain 1. First flight 2002. More...
  • X-405 GE Lox/Kerosene rocket engine. 134.8 kN. Vanguard 1st stage. Isp=270s. First flight 1957. More...
  • XJ40-WE-1 Wright turbojet engine. 48.5 kN. Out of production. Thrust is maximum thrust at cruise altitude. Specific impulse is that at cruise design point. Isp=1800s. Used on Navaho X-10 launch vehicle. First flight 1955. More...
  • XLR11 Reaction Motors, Thiokol Lox/Alcohol rocket engine. Out of Production. Launch thrust 26.67 kN. Rocket engine developed for X-1 in 1940s to break the sound barrier and used twenty years later to power experimental lifting bodies. Four combustion chambers. More...
  • XLR105-5 Rocketdyne Lox/Kerosene rocket engine. 363.2 kN. Atlas D. Atlas Sustainer. Gas generator, pump-fed. Shared turbopumps for booster engines. Isp=309s. First flight 1958. More...
  • XLR25-CW-1 Curtiss-Wright Lox/Alcohol rocket engine. 66.880 kN. Out of Production. First flight 1954. Two chamber engine built for X-2 rocketplane. Engine could be throttled continuously from 1140 kgf to 6820 kgf. More...
  • XLR89-5 Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Atlas D. Designed for booster applications. Gas generator, pump-fed. Shared turbopumps for booster engines. Isp=282s. First flight 1958. More...
  • XLR89-1 Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Atlas A, B, C. Out of production. Designed for booster applications. Gas generator, pump-fed. Shared turbopumps for booster engines. Isp=282s. First flight 1957. More...
  • XLR83-NA-1 Rocketdyne Lox/Kerosene rocket engine. 602 kN. Out of production. Isp=273s. Experimental version of the engine for the booster of the Navaho G-38 intercontinental cruise missile. Flown in the Navaho G-26 booster prototypes. First flight 1956. More...
  • XLR99 Thiokol Lox/Ammonia rocket engine. 262.4 kN. Out of production. Isp=276s. The first large, man-rated, throttleable, restartable liquid propellant rocket engine, boosted the X-15A. First flight 1959. More...
  • XR3A2 XCOR Lox/Alcohol rocket engine. 0.700 kN. First stages. Hardware. The XR3A2 700-newton engine was the first XCOR LOX/alcohol engine, accumulating 61 brief runs in the course of injector concept development, which led to later engines. More...
  • XR4A3 XCOR Lox/Alcohol rocket engine. 1.780 kN. First stages. Fully operational pressure-fed, regeneratively cooled engine. Flown on the EZ-Rocket, a modified Long-EZ aircraft fitted with two engines. First flight 2001. More...
  • XR4K14 XCOR Lox/Kerosene rocket engine. 6.670 kN. First stages. Hardware. Built for the Rocket Racing League's first X-Racer. The rocket engine was sized for the best compromise between acceleration and endurance. More...
  • XR4K5 XCOR Lox/Kerosene rocket engine. 8 kN. First stages. Hardware. Pump-fed, regeneratively cooled with fuel. Engine could be used to power the prototype Xerus suborbital manned vehicle for initial flight testing. More...
  • XR5M12 XCOR Lox/CH4 rocket engine. 22.3 kN. First stages. Conceptual lox/methane rocket engine developed for a DARPA program through layout design phase, but never built. More...
  • XR5M15 XCOR Lox/CH4 rocket engine. 33.360 kN. First stages. Hardware. Prototype LOX/methane rocket engine developed as a stepping stone to NASA's original Orion manned spacecraft and return to the moon and manned mission to Mars plans. More...
  • XRJ47-W-5 Wright ramjet engine. 33.4 kN. Out of production. Thrust is maximum thrust at cruise altitude. Specific impulse is that at cruise design point. Isp=1200s. Used on Navaho G-26 launch vehicle. First flight 1956. More...
  • XRS-2200 Rocketdyne lox/lh2 rocket engine. 1192 kN. Development ended 1999. Isp=439s. Linear aerospike engine for X-33 SSTO technology demonstrator. Based on J-2S engine developed for improved Saturn launch vehicles in the 1960's. More...
  • YaRD OKB-456 Glushko nuclear/ammonia rocket engine. 1373 kN. Development ended 1960. Isp=470s. Used nuclear reactor in cylindrical housing, operating at 3000 deg K. Propellant heated in the reactor and exhausted through four expansion nozzles More...
  • YaRD OKB-670 Bondaryuk nuclear/ammonia+alcohol rocket engine. 1667 kN. Development ended 1960. Isp=470s. Proposed for YaRD nuclear-powered ICBM. Propellant was heated in the reactor and exhausted through four expansion nozzles. More...
  • YF-120t CAALPT Lox/Kerosene rocket engine. 1340.2 kN. In development. Isp=336s. For CZ-5 Next Generation Launch Vehicle series. Engine can be throttled to 65% of rated thrust. Firing tests began in 2005. More...
  • YF-2A Beijing Wan Yuan Nitric acid/UDMH rocket engine. 306.1 kN. Out of production. Isp=268s. Used on CZ-1, CZ-1C, CZ-1D, CZ-1M. First flight 1969. More...
  • YF-20B Beijing Wan Yuan N2O4/UDMH rocket engine. 816.3 kN. In production. Isp=289s. Boosted CZ-2C, CZ-2D, CZ-2E, CZ-2E(A), CZ-3A, CZ-3B, CZ-3C, CZ-4A. First flight 1988. More...
  • YF-20A Beijing Wan Yuan N2O4/UDMH rocket engine. 750.2 kN. Out of production. Isp=289s. Boosted CZ-2A, CZ-2C, CZ-2E(A), CZ-3, FB-1. First flight 1972. More...
  • YF-50t CAALPT lox/lh2 rocket engine. 700 kN. In development. Isp=432s. New Lox/LH2 engine for next generation Chinese launch vehicles. It is an indigenous development based on Chinese experience with the YF-73 and YF-75 upper stage engines. More...

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