Category of engines.
More...  Chronology...
Associated Engines

11D121 Korolev GOX/Kerosene rocket engine. 68.650 kN. N1 stage 1 (block A) roll control engine. Developed 196974. Gimbaling +/ 45 degree. Propellants are fed from main engine (NK15, NK33) turbopumps. Isp=313s. Chamber Pressure: 71.60 bar. More...

11D43 Glushko N2O4/UDMH rocket engine. 1642 kN. Developed 196064. Isp=316s. Lowexpansion ratio gimbaled variant for Proton stage 1 concept. Configuration 4 x 8D43 clustered with 4 x 11D43 abandoned in favor of 6 x Glushko 11D48 in final Proton design. More...

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 NII125 solid rocket engine. Combined missile (RT20P) 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. RT23 early models stage I. Out of Production. The casebound T9BK composite solid propellant charge had a star shape channel. The case was of organic fibrewound plastic material. More...

15D23 KBMash solid rocket engine. 892 kN. RT2 Stage 1. Out of Production. Three gimballed nozzles for steering. Ammonium perchlorate/aluminium propellant. Chamber pressure 40 kgf/cm2. More...

15D23P TsKB7 solid rocket engine. 980 kN. RT2P 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. RT23 stage I. Out of Production. Casebound OPAL composite solid propellant charge with a star shape channel. The case was of organic fibrewound plastic material. More...

16 in gun US Navy gun for launch of rocketboosted projectile. 1,470,981 kN. Development ended 1966. The proposed Martlet gunlaunched 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...

293P Kartukov solid rocket engine. P70 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 RP4 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 Nova1 DAC launch vehicle. More...

8D415K Kosberg Lox/Kerosene rocket engine. 1471 kN. Designed for use in N1. Development canceled in 1960 when Korolev turned to Kuznetsov for R9 and N1 engines after continuous rows with Glushko over performance and propellant types. First flight 1966. More...

8D43 Kosberg N2O4/UDMH rocket engine. 559 kN. UR500 stage 1 original concept. Hardware. Isp=316s. In early Proton design would be clustered with 4 x Glushko 11D43. Abandoned in favor of 6 x Glushko 11D48, but later developed into the RD0208 and RD0210. More...

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

A10 Thiel Lox/Alcohol rocket engine. 2306.8 kN. Study 1942. Planned for use in A10. Unique dualthrust chamber / single nozzle design, which was later shown to be not feasible technically. Isp=247s. More...

A4 Thiel Lox/Alcohol rocket engine. 311.8 kN. Isp=239s. Used on V2 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 19431945. More...

A6 Rocketdyne Lox/Alcohol rocket engine. 414.3 kN. Out of production. Isp=265s. Used on Redstone launch vehicle. First flight 1953. Developed from the XLR43NA1, an American version of the V2 singlechamber engine tested in 1945. More...

A7 Rocketdyne Lox/Hydyne rocket engine. 416.2 kN. Out of Production. Version of Redstone engine for JupiterC test vehicle, with Hydyne fuel and 140 seconds burn time. Flew 19561959. Gas generator, pumpfed. Thrust 370 kN at sea level. Isp=265s. More...

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

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

AJ2601/3 Aerojet solid rocket engine. 10,105 kN. Design concept 1960's. Isp=275s. Used on Saturn INT05B launch vehicle. More...

AJ2602 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...

AJ260X 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...

AJ260X 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 X3, Scout X4; proposed as strapon 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/Aerozine50 rocket engine. 440 kN. SSTO ICBM. Development 1968. Isp=370s. Advanced Rocket Engine System  single shaft turbopump, integrated single pressure vessel in a staged combustion cycle configuration. More...

Atar 9K SNECMA turbojet engine. 48 kN. Out of Production. Isp=2020s. More...

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

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

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 strapon boosters and as first and upper stages for lowcost allsolidpropellant 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 longlife, moderateto highthrust, reusable booster engine that incorporated a safe, lowcost, lowrisk, LH2/LOX single burner, using a fuelrich, staged combustion cycle. More...

D1 Kosberg isopropylnitrate monopropellant rocket engine. 39 kN. Developed 195556. Second thrust level at 50%. Explosion of D1 on test bench in 1956 forced stop of work with monopropellant OT152. Sea level thrust 39 kN. More...

D18T Lotarev turbofan engine. 229.4 kN. Used on An225 launch aircraft for Interim HOTOL, MAKS concepts. Development ended 1988. Isp=9000s. More...

D2 Polyarniy Lox/Kerosene rocket engine. 1373 kN. R3. Out of Production. Competing engine for 3000 km range IRBM design to study problems of longrange rockets. Developed from April 1947 until cancellation. Isp=288s. More...

D7 Kosberg isopropylnitrate monopropellant rocket engine. 11.8 kN. Missile by Toropov. Out of Production. Intended for airair missile by I I Toropov. Uncooled thrust chamber. Sea level thrust 11.8 kN. More...

E1 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 F1 as next step. Booster applications. Gas generator, pumpfed. 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...

F1 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...

F1A Rocketdyne Lox/Kerosene rocket engine. 9189.6 kN. Study 1968. Designed for booster applications. Gas generator, pumpfed. Isp=310s. More...

F100100 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 SLV1 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 lowcost engine for X34. Isp=348s. More...

Fastrac Huntsville Lox/Kerosene rocket engine. 269 kN. Development ended 1996. Isp=310s. Used on X34A 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. Singlechamber, liquidpropellant, annular aerospike engine. More...

GEM 40 Hercules solid rocket engine. 499.2 kN. Airignited 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. Airignited 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 strapon 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 19631970. Largest thrust chamber ever tested in Russia was Glushko's RD270 of 680 tf. More...

H1 Rocketdyne Lox/Kerosene rocket engine. 947.7 kN. Saturn l/lB. Designed for booster applications. Gas generator, pumpfed. Isp=289s. First flight 1961. More...

H1b Rocketdyne Lox/Kerosene rocket engine. 1030.2 kN. Isp=296s. First flight 1966. More...

H1c Rocketdyne Lox/Kerosene rocket engine. 1130 kN. Study Saturn IBA, Saturn IBB, 1965. Isp=296s. More...

H20 Nissan solid rocket engine. 1540 kN. Isp=273s. Used as strapon booster on H2, first stage on J1. First flight 1994. More...

H2/J11 Nissan solid rocket engine. 1556.6 kN. In Production. Used in J11. 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...

HG3SL Rocketdyne lox/lh2 rocket engine. 1387 kN. Study 1966. Isp=450s. Highperformance highpressure chamber engine developed from the J2, fitted with lowerexpansion nozzle for sea level use on Saturn INT17. Technology led to Space Shuttle Main Engines. More...

HP1 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 (S25 system). Out of Production. Launch thrust 166 kN. More...

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

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

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

J2SL Rocketdyne lox/lh2 rocket engine. 996.7 kN. Study 1966. Sea level version of J2 with reduced expansion ratio proposed for Saturn II first stage use. Isp=390s. More...

J578 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...

J5719 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 B52 launch aircraft for X15A. 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...

J7517 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...

J7917 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...

J933 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...

JP5/H2O2 Notional H2O2/Kerosene rocket engine. 63 kN. Study 1993. Isp=335s. Engine for Black Horse winged, single stage to orbit launch vehicle using aerial refueling. More...

JT9D3A 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. LL1, LL2, LL3. Developed 194648. More...

Kartukov Soyuz SAS Kartukov solid rocket engine. 785 kN. Soyuz 7KOK, Soyuz 7KTOK, Soyuz 7KT. Out of Production. Thrust 76 tf at cutout  80.1tf at ignition. More...

KSR3 Korean Lox/Kerosene rocket engine. In development. Launch thrust 122.5 kN. Pressurefed indigenous design. First flight 2002. More...

L5.00H Notional lox/lh2 rocket engine. 30,684 kN. Study 1963. Isp=428s. Used on Nova GDH launch vehicle. More...

L5.25H 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 GDH launch vehicle. More...

L6.55 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...

L7.70 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/LE5 Mitsubishi air augmented Liquid Air/LH2 rocket engine. 147.1 kN. Design 1999. Isp=1200s. Used on H2 HIMES launch vehicle. More...

LE7 Mitsubishi lox/lh2 rocket engine for H2 upper stage. 1078 kN. Staged combustion turbopump. No throttle capability. Isp=446s. First flight 1994. More...

LE7A Mitsubishi lox/lh2 rocket engine. 1098 kN. In production. Isp=438s. Improved model of the original LE7 for the first stage of the HII rocket with a two stage combustion cycle system. First flight 2001. More...

Liberty Liberty Lox/Kerosene rocket engine. Development 19942006. Pressurefed engine. Price $ 12,000 in 1995. Used on Scorpius launch vehicle. More...

Liberty1 Notional Lox/Kerosene rocket engine. 245.2 kN. Development ended 1988. Pressurefed engine. Isp=270s. Used on Liberty launch vehicle. More...

LK1 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...

LR10111 Rocketdyne Lox/Kerosene rocket engine. 5.3 kN. In Production. Isp=246s. Verniers for RS27 powerplant, used on Delta boosters 19741992. More...

LR1053 Rocketdyne Lox/Kerosene rocket engine. 375 kN. Out of Production. Early version of Atlas Sustainer. Gas generator, pumpfed. Isp=308s. More...

LR1055 Rocketdyne Lox/Kerosene rocket engine. 386.4 kN. Atlas E, F. Atlas Sustainer. Gas generator, pumpfed. Separate turbopumps for each booster engine. Isp=316s. First flight 1960. More...

LR1057 Rocketdyne Lox/Kerosene rocket engine. 386.4 kN. Atlas space launchers. Out of production. Atlas Sustainer. Gas generator, pumpfed. Evolved from MA2 ICBM system. Isp=316s. First flight 1963. More...

LR797 Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Out of production. Designed for booster applications. Gas generator, pumpfed. Isp=282s. First flight 1957. More...

LR8RM5 Reaction Motors Lox/Alcohol rocket engine for rocketplanes. Out of Production. Launch thrust 26.67 kN. Advanced version of the LR11, 4 chambers. Engine in the X1E was modified in 1958 to increase chamber pressure to 20 atm and burn Hydyne fuel. More...

LR83NA1 Rocketdyne Lox/Kerosene rocket engine. 683 kN. Development ended 1958. Isp=282s. Planned production version of the engine for the booster of the Navaho G38 intercontinental cruise missile. More...

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

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

LR875 Aerojet N2O4/Aerozine50 rocket engine. 1096.8 kN. Out of Production. Isp=297s. Used on Titan 2 launch vehicle. Engines refurbished for space launcher versions from decommissioned missiles between 19741982. More...

LR873 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...

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

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

LR8711 Aerojet N2O4/Aerozine50 rocket engine. 1218.8 kN. Out of production. Isp=302s. Powered Titan 3 and 4 first stages. Replaced the 9 model, first flown 1968. First flight 1964. More...

LR895 Rocketdyne Lox/Kerosene rocket engine. 822.5 kN. Atlas E, F. Designed for booster applications. Gas generator, pumpfed. Separate turbopumps for each booster engine. Isp=290s. First flight 1960. More...

LR897 Rocketdyne Lox/Kerosene rocket engine. 948 kN. Atlas space launchers. Out of production. Designed for booster applications. Gas generator, pumpfed. Shared turbopumps for booster engines. Evolved from MA2 ICBM system. Isp=294s. First flight 1963. More...

M13 Nissan solid rocket engine. 1262.4 kN. Isp=263s. Used on Mu3S launch vehicle. First flight 1969. More...

M14 Nissan solid rocket engine. 3780.3 kN. Isp=276s. Used on MV launch vehicle. First flight 1997. More...

M33204 Thiokol solid rocket engine. 286 kN. Isp=247s. Used as apogee kick motor on Delta D, LT Thor Agena D, Scout X1, Scout X2, Scout X3, Scout X4, TA Thor Agena B, TA Thor Agena D. First flight 1960. More...

M55/TX55/Tu122 Thiokol solid rocket engine. 792 kN. In production. Isp=262s. Proposed as strapon booster for Saturn IBC, Saturn INT14, Saturn INT15, Saturn INT19 variants. First flight 2000. More...

MA5A Rocketdyne Lox/Kerosene rocket engine. 2100 kN. Out of Production. Isp=296s. Atlas Engine System, an updated version of the MA5, included replacments with selected RS27 components for sealevel Isp increase of 4 secs. First flight 1991. More...

Martlet 41 Bull solid rocket engine. 67.7 kN. Development ended 1966. Isp=300s. Used on Martlet 4 launch vehicle. More...

MB3 Press Mod Rocketdyne Lox/Kerosene rocket engine. 755.1 kN. Test 1962. Isp=285s. Used on Sea Horse launch vehicle. More...

MB31 Rocketdyne Lox/Kerosene rocket engine. 760.6 kN. Out of production. Designed for booster applications. Gas generator, pumpfed. Isp=285s. Boosted Delta A, B, C, Thor AbleStar. First flight 1960. More...

MB33 Rocketdyne Lox/Kerosene rocket engine. 866.7 kN. Out of Production. License built in Japan for H1. Isp=290s. First flight 1964. More...

MBBATC500 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; turbopump 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 lowcost ablative composite rocket engine for responsive launch vehicle applications. More...

Microcosm 22N Microcosm Lox/Kerosene rocket engine. 22.250 kN. First stages. Hardware. Pressurefed, 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 lowcost, robust design margins. More...

MIHT1 MIHT solid rocket engine. 980.6 kN. Start1. In production. Used in Start1. 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...

NK15 Kuznetsov Lox/Kerosene rocket engine. 1544 kN. N1 stage 1 (block A). Development ended 1964. On the basis of NK9 the NK15 was developed for the N1 launcher. 30 were used on the Block A (Stage 1) of the N1. Isp=318s. First flight 1969. More...

NK15F Kuznetsov Lox/Kerosene rocket engine. 2180 kN. Development 19661972. 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...

NK15V Kuznetsov Lox/Kerosene rocket engine. 1648 kN. Development ended 1964. Isp=325s. Developed from the NK9. 8 engines, featuring highexpansion nozzles, used on N1 Stage 2. First flight 1969. More...

NK19 Kuznetsov Lox/Kerosene rocket engine. N1 stage 4. Development ended 1964. Based on NK9 engine. Originally developed for the modernized second stage of the R9 (abandoned). Also to have been used on GR1 / 8K713 Stage 2. First flight 1969. More...

NK231 Kuznetsov turbofan engine. 226.5 kN. Tu160. Development ended 1992. Turbofan engine used in Tu160. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=1980s. More...

NK33 LH2 Mod + 4 x LACE Kuznetsov air augmented rocket engine. 980.7 kN. N1MOK. Study 1974. Isp=430s. Ultimate derivative of NK9. Propellants changed to LH2/LOX, 16 x modified NK33 engines + 4 Liquid Air Cycle Engine Liquid Air/LH2 boosters. More...

NK33 Kuznetsov Lox/Kerosene rocket engine. 1638 kN. N1F, 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...

NK31 Kuznetsov Lox/Kerosene rocket engine. 402 kN. Isp=353s. Upgraded version of engines for N1 stage 4, with multiple ignition capability and increased operational lifetime. Mothballed in 1974. Proposed for Black Colt launch vehicle in 1993. More...

NK9 Kuznetsov Lox/Kerosene rocket engine. 441.3 kN. R9, GR1 stage 1. Isp=327s. Reached phase of stand testing in 1965, but then RD111 selected. Later planned for 1st Stage of GR1, 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...

NOTS1 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 reentry initiation. First flight 1981. More...

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

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 FiatAvio solid rocket engine. 3040 kN. In production. Isp=279s. Vega's first stage, introduced advanced lowcost technologies that could be reused for future evolutions of Ariane5 boosters. More...

P9.5 SNPE solid rocket engine. 690 kN. Isp=263s. Strapon 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...

Pegasus1 Hercules solid rocket engine. 484.9 kN. Isp=285s. Used on Pegasus, Taurus. First flight 1989. More...

Pegasus XL1 Hercules solid rocket engine. 589 kN. Isp=293s. Used on Pegasus XL launch vehicle. First flight 1994. More...

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

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

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

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

PF RP1 Notional Lox/Kerosene rocket engine. 20,306 kN. Study 1967. Isp=275s. Used on Saturn LCBLox/RP1 launch vehicle. More...

PlugNozzle J2 Rocketdyne lox/lh2 rocket engine. 6864.6 kN. Study 1993. Plug nozzle version of J2 proposed for certain Saturn V upgrades in late 1960's. Isp=425s. Used on DCI launch vehicle. More...

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

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

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

PRD70 Kartukov solid rocket engine. 400/5V11 stage I. Out of Production. More...

PRD15 Kartukov solid rocket engine. 392 kN. Strela1 missile. Out of Production. More...

PRD19M Kartukov solid rocket engine. KSShch Shchuka. Out of Production. More...

PRD22 Kartukov solid rocket engine. 3.920 kN. SM30. Out of Production. More...

PRD36 Kartukov solid rocket engine. V600. Out of Production. More...

PRD52 Kartukov solid rocket engine. 784 kN. DBR1 Yastreb. Out of Production. Thrust 80 tf at ignition, 75 tf at cutout. More...

PRD61 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...

PSLV1 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...

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

R13 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 KRD604. More...

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

R31 Lyulka turbojet engine. 91.2 kN. MiG25. Out of Production. Used in MiG25. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=2073s. More...

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

RB21122B 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...

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

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

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

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

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

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

RD0229M Kosberg Lox/LNG rocket engine. 883 kN. Vozdushnyy Start stage 1. Developed 1997. Derivative of RD0229 for the propellants LOX and liquid natural gas (methane). Initial candidate for stage 1 propulsion of Vozdushnyy Start project by Kompomash. More...

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

RD0245HC Kosberg Lox/Kerosene rocket engine. 214 kN. Design concept 1990's. Proposed variant of RD0245 engine using LOXkerosene instead of N2O4/UDMH as propellants. Isp=320s. More...

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

RD0234HC Kosberg Lox/Kerosene rocket engine. 516 kN. Developed 1996. Proposed variant of RD0234 engine using LOXkerosene instead of N2O4/UDMH as propellants. Isp=331s. More...

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

RD0242HC Kosberg Lox/Kerosene rocket engine. 125 kN. Developed 1998. Proposed variant of RD0242 engine using LOXkerosene instead of N2O4/UDMH as propellants. Isp=312s. More...

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

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

RD0244HC Kosberg Lox/Kerosene rocket engine. 690 kN. Design concept 1990's. Proposed variant of RD0244 engine using LOXkerosene instead of N2O4/UDMH as propellants. Isp=332s. More...

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

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

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

RD0120CH Kosberg Lox/LCH4 rocket engine. 1576 kN. Design concept 1990's. Proposed variant of the RD0120 engine using liquid methane instead of hydrogen as propellant. Isp=363s. More...

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

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

RD0101 Kosberg Lox/Alcohol rocket engine. 39.2 kN. E50A aircraft by Mikoyan. Out of Production. Chamber pressure 42,7  22,1 bar. Specific impulse 255  248,5 sec. Isp=255s. More...

RD0102 Kosberg Lox/Kerosene rocket engine. 39.2 kN. Yak27V aircraft by Yakovlev. Out of Production. Based on RD0101. Two ignitions possible. Chamber pressure 41,2  16,4 bar. Isp=260s. More...

RD0120 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...

RD0120M Kosberg lox/lh2 rocket engine. 1961 kN. EnergiaM core stage. Development ended 1993. Isp=455s. From 1987 KBKhA worked on upgrading the 11D122 (RD0120) engine for EnergiaM launcher, including the possibility to throttle the engine down to 28% thrust. More...

RD0120MCH Kosberg Lox/LCH4 rocket engine. 1720 kN. Design concept 1990's. Proposed variant of the RD0120M engine using liquid methane instead of hydrogen as propellant. Isp=372s. More...

RD012414D23 Kosberg Lox/Kerosene rocket engine. 298.640 kN. Propoed in 1993 for Angara stage 2 verniers, Kvant1 stage 1 vernier. Designed 19861990. Isp=331s. Variant of RD0124 with shortened nozzle for sealevel operation. More...

RD012U 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...

RD020 Bondaryuk ramjet engine. 103 kN. Buran M42. Development ended 1957. Isp=1500s. Ramjet for Buran cruise missile. 8,500 km cruise at Mach 3.1 at 1820 km altitude. More...

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

RD0103 Kosberg Lox/Kerosene rocket engine. 34.6 kN. T3, P1 aircraft by Sukhoy. Out of Production. Based on RD0102. Chamber pressure 37.3  15.7 bar. Isp=277s. More...

RD0134 Kosberg Lox/LNG rocket engine. 2038 kN. stage 1. Developed 1998on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle variant of RD0139. Isp=358s. More...

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

RD0201 Kosberg Nitric acid/Amine rocket engine. 58.060 kN. SAM V1100 by Grushin stage 3. Out of Production. Thrust range 59  28 kN. Isp=260s. First flight 1960. More...

RD018 Bondaryuk ramjet engine. 98 kN. Buran missile, early version. Out of Production. Isp=1500s. 1.8 m diameter ramjet engine initially considered for Buran M42. RD020 adpopted later during development. More...

RD0155 Kosberg Lox/Kerosene rocket engine. Design concept 2007. Launch thrust 902.5 kN. Engine proposed to replace RD107 in Onega and Avrora versions of the Soyuz launch vehicle. More...

RD0143A Kosberg Lox/LNG rocket engine. 343 kN. Vozdushnyy Start stage 1. Design concept 1998. Proposed single chamber variant of RD0143. Selected for stage 1 of Vozdushnyy Start project by Kompomash. Isp=370s. More...

RD0141 Kosberg Lox/LNG rocket engine. 2251 kN. stage 1. Developed 1998on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Obviously variant of RD0141 with larger nozzle. Isp=353s. More...

RD0139 Kosberg Lox/LNG rocket engine. 2038 kN. stage 1. Developed 1998on. Proposed engine for LOX/liquid natural gas. Gas generator cycle with turbine gas injection into supersonic nozzle. Isp=341s. More...

RD118 Glushko Lox/Kerosene rocket engine. 999.601 kN. In production. Isp=311s. Update of RD107, used in Soyuz ST launcher. Little performance change from RD107, changes may mainly relate to use of allRussian components. First flight 2001. More...

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

RD1078D74PS Glushko Lox/Kerosene rocket engine. 971 kN. Sputnik 8K71PS0. Out of Production. OKB Glushko. Used on 8K71PS Stage 0. Developed in 19561957. Flown 19571958. Propellants kerosene (RG1) / Lox. Diameter is per chamber. Isp=306s. More...

RD117 Glushko Lox/Kerosene rocket engine. 1021.097 kN. Soyuz ST stage 1. In production. Update of RD107. Little performance change from RD107, changes may mainly relate to use of allRussian components. Isp=310s. First flown 2001. More...

RD117PF Glushko Lox/Kerosene rocket engine. manned Soyuzlauncher stage 1. Design concept. Update of RD107. Probably version using Sintin instead of kerosene. More...

RD114 Glushko lox/udmh rocket engine. 1653 kN. Used in ICBM stage 1 (stage 2 was RD115). Developed 196165. Isp=341s. More...

RD112 Glushko lox/udmh rocket engine. 1089 kN. ICBM stage 1 (stage 2 was RD113). Developed 1960. Isp=344s. More...

RD111 Glushko Lox/Kerosene rocket engine. 1628 kN. R9 stage 1. Isp=317s. Developed for R9 ICBM. It had special flexible pipelines and gimbals, allowing lox loading in 20 minutes. First flight 1961. More...

RD1088D77 Glushko Lox/Kerosene rocket engine. 804 kN. Sputnik 8A911. Out of Production. Diameter is per chamber. Isp=315s. First flight 1958. More...

RD120K Glushko Lox/Kerosene rocket engine. 873 kN. Soyuz M stage 1, 2. Proposed for X34. Isp=336s. Sealevel variant of RD120. As of 1996 RD120 prototype with 1.8 m diameter had been built, development time estimated for three years. More...

RD191 Glushko Lox/Kerosene rocket engine. 2079 kN. Isp=337s. Proposed for stage 1 of Angara. Single chamber from 4chamber RD170 would have been cheap and fast to develop. Only reached the draft project stage by 2003. Gimbaling +/ 8 degree in two planes. More...

RD110 Glushko Lox/Kerosene rocket engine. 1374 kN. Development ended 1949. Isp=285s. For R3 IRBM, 19 ED140 7 tonne chambers used as preburners to feed a main mixing chamber, a scaleup of the V2 production motor. Tested, but technical problems too severe. More...

RD120M Glushko Lox/Kerosene rocket engine. 850.4 kN. PacAstro2 stage 1. Out of Production. Sealevel variant of RD120 engine, similar to RD120K. Gimbaling +/ 6 degree in two planes. Isp=330s. More...

RD169 Glushko Lox/LCH4 rocket engine. 167 kN. Riksha0 stage 1. Design concept 1990's. Isp=351s. LOX/Methane engine derived from RD120. Gimbaling +/ 8 degree in two planes. In 1996 prototype development was estimated to take four years from goahead. More...

RD170 Glushko Lox/Kerosene rocket engine. 7903 kN. Energia strapon. Developed 19731985. Isp=337s. First flight 1987. Used oneplane gimablling versus the twoplane gimablling required on the RD171 of the Zenit launch vehicle. Designed for 10 reuses. More...

RD171 Glushko Lox/Kerosene rocket engine. 7903 kN. Zenit stage 1. In production. Isp=337s. RD171 used twoplane gimablling versus oneplane gimablling on RD170 developed in parallel for Energia. First flight 1985. More...

RD172 Glushko Lox/Kerosene rocket engine. 8354 kN. Zenit3 stage 1 (?). Developed 1994. Uprated version of RD171. To have been qualified for flight 1994. Isp=337s. More...

RD173 Glushko Lox/Kerosene rocket engine. 8181 kN. Zenit3 stage 1 (?). Design concept 1990's. Uprated version of RD171 with 4 chambers, 1 turbopump and 2 gas generators. Intended for uprated Zenit named Zenit 3 Isp=337s. More...

RD174 Glushko Lox/Kerosene rocket engine. 7905 kN. Angara stage I. Developed 1995. More...

RD180 Glushko Lox/Kerosene rocket engine. 4152 kN. Atlas III, Atlas V stage 1. In production. Isp=337s. First flight 2000. Twothrustchamber derivative of the fourchamber RD170 used on Zenit. More...

RD182 Glushko Lox/LCH4 rocket engine. 902 kN. Riksha (1, 2) stage 1. Developed 1994. Isp=353s. Methane variant of RD120K engine. Thrust range and Isp range due to throat diameter and chamber pressure. Gimbaling +/ 6 degree in two planes. More...

RD190 Glushko Lox/LCH4 rocket engine. 1000 kN. Riksha0 stage 1. Developed 1996. The RD190 consists of 6 RD169 engines. Each chamber can be gimbaled individually in two planes by +/ 8 degree. Isp=351s. More...

RD191M Glushko Lox/Kerosene rocket engine. 1976 kN. Angara stage I. Developed 1996. Single chamber version of the RD170 / RD171. Isp=337s. More...

RD1088D75PS Glushko Lox/Kerosene rocket engine. 912 kN. Sputnik 8K71PS1. Out of Production. Diameter is per chamber. Isp=308s. First flight 1957. More...

RD182M Glushko Lox/LNG rocket engine. 882 kN. Vozdushnyy Start stage 1. Developed 1998. Variant of RD182 engine for liquid natural gas (mainly CH4). Proposed initial candidate for project Vozdushnyy Start of Kompomash. More...

RD102 Glushko Lox/Alcohol rocket engine. 428 kN. R3A. Development ended 1951. Project for R3A experimental missile. Stopped in favor of RD103. Isp=235s. More...

RD1088D75K Glushko Lox/Kerosene rocket engine. 941 kN. Molniya 8K781, R7A 8K741, Voskhod 11A571, Vostok 8A921, Vostok 8A92M1. Diameter is per chamber. Isp=315s. First flight 1959. More...

RD10811D512 Glushko Lox/Kerosene rocket engine. 997 kN. Soyuz 11A5111, Soyuz 11A511U1. Design 2000. Diameter is per chamber. Isp=315s. First flight 1965. More...

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

RD101 Glushko Lox/Alcohol rocket engine. 404 kN. R2 and V2A. Isp=237s. Developed simultaneously with the RD100 but with no German involvement. More compact, increased thrust, increased chamber pressure and higher alcohol concentration. First flight 1949. More...

RD103 Glushko Lox/Alcohol rocket engine. 500 kN. R5. Out of Production. Isp=243s. Final extrapolation of the V2 rocket engine in Russia. First flight 1953. More...

RD103M Glushko Lox/Alcohol rocket engine. 500.1 kN. R5M 8K51. Isp=248s. First flight 1953. More...

RD103RD Glushko Lox/Alcohol rocket engine. M5RD. Out of Production. More...

RD105 Glushko Lox/Kerosene rocket engine. 627.6 kN. R7 ICBM stage 1 (strapon) initial project. Out of Production. Isp=302s. Single chamber engine intended for the R7 strapons in mid1950s. Subsequently replaced by the 4 chamber RD107. More...

RD106 Glushko Lox/Kerosene rocket engine. 645.3 kN. R7 ICBM stage 2 (core) initial project. Out of Production. Isp=310s. Single chamber engine intended for the R7 sustainer. Version of RD105 with larger nozzle. Subsequently replaced by the 4 chamber RD108. More...

RD10711D511 Glushko Lox/Kerosene rocket engine. 992 kN. Soyuz 11A5110, Soyuz 11A511U0. Design 2000. Diameter is per chamber. Isp=314s. First flight 1965. More...

RD10711D511P Glushko Lox/Kerosene rocket engine. 996.4 kN. Soyuz 11A511U20. Out of production. OKB Glushko. Used on 11A511U2 Stage 0. Propellants kerosene (RG1) / Lox. Diameter is per chamber. Isp=314s. First flight 1982. More...

RD1088D75 Glushko Lox/Kerosene rocket engine. 912 kN. R7 8K711, Vostok 8K721, Vostok 8K72K1. OKB Glushko. Used on 8K71 R7 Stage 1. Developed in 19541955. Propellants kerosene (RG1) / Lox. Diameter is per chamber. Isp=308s. First flight 1957. More...

RD100 Glushko Lox/Alcohol rocket engine. 304 kN. R1, V1A. Isp=237s. Russian copy of the V2 engine using Russian materials  which made it very difficult! German rocket scientists assisted in its development. First flight 1948. More...

RD1078D728 Glushko Lox/Kerosene rocket engine. 996 kN. Molniya 0, Molniya 8K78M0. OKB Glushko. Used on Molniya 8K78M and 11A57 Stage 0. Propellants kerosene (RG1 or T1) / Lox. Diameter is per chamber. Isp=314s. First flight 1964. More...

RD1088D751959 Glushko Lox/Kerosene rocket engine. 941 kN. Out of production. Further development of 8D741958, 19581959. Diameter is per chamber. Isp=315s. Used on Vostok 8K72K launch vehicle. First flight 1960. More...

RD1088D751958 Glushko Lox/Kerosene rocket engine. 941 kN. Luna 8K721. Out of production. Diameter is per chamber. Isp=315s. First flight 1958. More...

RD1088D727 Glushko Lox/Kerosene rocket engine. 977 kN. Molniya 1, Molniya 8K78M1. OKB Glushko. Used on Molniya 8K78L, 8K78M and 11A57 Stage 1. Propellants kerosene (RG1 or T1) / Lox. Diameter is per chamber. Isp=316s. First flight 1964. More...

RD10811D512P Glushko Lox/Kerosene rocket engine. 1011 kN. Soyuz 11A511U21. Out of production. Isp=319s. A 12 second specific impulse increase was made possible by the use of synthetic fuel Sintin and a modified mixing head. First flight 1982. More...

RD1078D76 Glushko Lox/Kerosene rocket engine. 971 kN. Sputnik 8A910. Out of Production. OKB Glushko. Used on 8A91 Stage 0. Developed in 19561957. Propellants kerosene (RG1) / Lox. Diameter is per chamber. Isp=310s. First flight 1958. More...

RD1078D74K Glushko Lox/Kerosene rocket engine. 996 kN. Developed in 19571960. Used in strapons for Molniya 8K78, R7A 8K74, Voskhod 11A57, Vostok 8A92, Vostok 8A92M. Isp=313s. Fuel T1 or RG1 kerosene. First flight 1959. More...

RD1078D741959 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...

RD1078D741958 Glushko Lox/Kerosene rocket engine. 996 kN. Luna 8K720. Out of production. Diameter is per chamber. Isp=312s. First flight 1958. More...

RD1078D74 Glushko Lox/Kerosene rocket engine. 971 kN. R7 8K71, Vostok 8K72, Vostok 8K72K strapons. Isp=306s. First flight 1957. Used four combustion chambers fed by single turbopump to circumvent combustion instability problems with larger chambers 1950's. More...

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

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

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

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

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

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

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

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

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

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

RD270M Glushko exotic N2O4/Pentaborane rocket engine. 7159 kN. Isp=365s. In 19621970 Glushko studied use of Pentaborane 'zip' propellants in his monster RD270 engine. Created immense toxicity problems but increased specific impulse of the engine by 42 seconds. More...

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

RD3641 Lyulka turbojet engine. 158.4 kN. T4. 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...

RD3A Glushko Lox/Alcohol rocket engine. R3A. Out of Production. Project for R3A experimental missile. Stopped in favour of RD103. More...

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

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

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

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

RD701 Glushko lox/lh2/kerosene tripropellant rocket engine for airlaunched MAKS spaceplane. 4003 kN. Development ended 1988. Isp=415 / 460s. First flight 2001. More...

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

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

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

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

RDKS100 Dushkin Lox/Kerosene rocket engine. 980 kN. Sanger. Developed 194651. Isp=285s. More...

RDMT5 NII Mash air cold gas thruster. 5 N. MMK. In Production. Lowthrust coldgas 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 G38 launch vehicle. More...

RKDS100 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...

RL10A5 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 DCX and the upgraded DCXA VTOVL SSTO launch vehicle demonstrators. First flight 1993. More...

RL10A5KA 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...

RLA1200 Glushko Lox/Kerosene rocket engine. 12,700 kN. Design 1974. Proposed engines for the RLA series launch vehicles. This version would use four chambers. 'Downsized' to 200 tonnes thrust for Energia. More...

RLA600 Glushko Lox/Kerosene rocket engine. 6370 kN. Design 1972. Twochamber version of RLA300. Proposed for the RLA series launch vehicles and the UR700M 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...

RPD04 Dushkin Lox/Kerosene rocket engine. Out of Production. More...

RS27 Rocketdyne Lox/Kerosene rocket engine. 1023 kN. Out of production. Isp=295s. Consisted of RS2701A/B main engine, and twin LR101NA11 verniers. Introduced in 1974 on the McDonnell Douglas' Delta 2000 series launcher; replaced the MB3. First flight 1972. More...

RS27A Rocketdyne Lox/Kerosene rocket engine. 1054.2 kN. . Isp=302s. Replaced the RS27 as the main system for the Delta and in the MA 5A for the Atlas. RS2701B main engine, and twin LR101NA11 verniers. First flight 1989. More...

RS27C Rocketdyne Lox/Kerosene rocket engine for Delta 7000. 1054.2 kN. Isp=302s. First flight 1990. More...

RS56OBA Rocketdyne Lox/Kerosene rocket engine. 1046.8 kN. Out of production. Designed for booster applications. Gas generator, pumpfed. Isp=299s. Booster engine for Atlas II, IIA, IIAS. First flight 1991. More...

RS56OSA Rocketdyne Lox/Kerosene rocket engine. 386.4 kN. Out of production. Designed for booster applications. Gas generator, pumpfed. Isp=316s. Sustainer engine for Atlas II, IIA, IIAS. First flight 1991. More...

RS68 Rocketdyne lox/lh2 rocket engine. 3312 kN. In production. Isp=420s. First new large liquidfueled rocket engine developed in America in more than 25 years. Powered the Delta IV booster. First flight 2002. More...

RS68 Regen Rocketdyne lox/lh2 rocket engine. Design concept 2004. Upgrade to basic RS68 for Delta IV Heavy growth versions. Would use a regenerativelycooled expansion nozzle, allowing it to run hotter, with higher thrust and specific impulse. More...

RS68B Rocketdyne lox/lh2 rocket engine. Design concept 2004. Upgrade (details not specificed) to basic RS68 for Delta IV Heavy growth versions. More...

RS800 Rocketdyne lox/lh2 rocket engine. 4110 kN. Design concept 2004. New highthrust cryogenic engine for Delta IV Heavy growth versions. More...

RS84 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 F1. More...

RSX 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...

RSXXX Rocketdyne lox/lh2 rocket engine. 8230 kN. Design concept 2004. New highthrust cryogenic engine concept for Next Generation Delta with 7 m diameter modules. More...

RSA41 South Africansolid rocket engine. 1520 kN. Development ended 1994. Isp=263s. Used on RSA4 launch vehicle. More...

RSA31 South Africansolid rocket engine. 500 kN. Out of production. Built in both Israel and South Africa for RSA3 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...

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

S3 Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Juno II, Saturn A2 studies of 1959. Isp=282s. First flight 1958. More...

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

S43 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. V300/V303 (S25 system). Out of Production. More...

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

S1.35800 Korolev Lox/Kerosene rocket engine. 30 kN. R7 verniers. Out of Production. Thrust variable 2.53.1 tf More...

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

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

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

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

S2.253 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. R11FM. Out of Production. Used in R11FM submarine version of Scud B. Fuel Kerosene T1, chemical ignition by TG02. Mixture ratio derived from tank content. 81 kN sealevel. More...

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

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

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

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

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

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

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

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

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

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...

SangerBredt Notional Lox/Kerosene rocket engine. 1428.8 kN. Study 1943. Used in SangerBredt. Isp=306s. More...

SangerBredt Sled Saenger Lox/Alcohol rocket engine. 1144.1 kN. Study 1943. Isp=245s. Used on Sanger launch vehicle. More...

SB735 Nissan solid rocket engine. 327.8 kN. Isp=263s. Used on Mu3S launch vehicle. First flight 1969. More...

SBIR Hybrid SpaceDev N2O/Solid hybrid rocket engine. 1100 kN. First stage. Upperstage hybrid propulsion system, part of 2004 Phase 2 of SBIR contract from AFRL for a hybrid rocket motorbased small launch vehicle project. More...

Scramjet Scramjet engine for X30 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 Dragon1 Aerojet Lox/Kerosene rocket engine. 356,9 kN. Design, 1962. Isp=290s. Truax pressure fed design. Thrust, chamber pressure varied during ascent. More...

SLV1 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. Strapon booster for Advanced Scout, Ariane 2/3. First flight 1984. More...

SPRD15 Kartukov solid rocket engine. 402 kN. S2 Strela2 missile, Sopka. Out of Production. Thrust 27 tf at cutout  41at ignition. More...

SPRD30 Kartukov solid rocket engine. 294 kN. P15 Termit. Out of Production. Thrust 28 tf at cutout  30 tf at ignition. More...

SPRD99 Kartukov solid rocket engine. 24.5 kN. MiG21PFM. 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 19811985, after which superseded by RSRM's. More...

SRBA Nissan solid rocket engine. 2250 kN. In production. Monolithic motor, shorter than that for H2, 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 highpressure closedcycle 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...

T7A Booster Fourth Academy solid rocket engine. 46 kN. T7 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...

TR106 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...

TX3543 Thiokol solid rocket engine. 258.9 kN. Used in Scout A; Delta E; H10; Castor 2. License built in Japan for H1. Isp=262s. First flight 1960. More...

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

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

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

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

UA156 CSD solid rocket engine. 8924.3 kN. Tested 1968. Isp=263s. Proposed as strapon booster for Saturn INT27, Saturn V25(S)B, Saturn V25(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. Strapon 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.Strapon 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 Braun1 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...

X405 GE Lox/Kerosene rocket engine. 134.8 kN. Vanguard 1st stage. Isp=270s. First flight 1957. More...

XJ40WE1 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 X10 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 X1 in 1940s to break the sound barrier and used twenty years later to power experimental lifting bodies. Four combustion chambers. More...

XLR1055 Rocketdyne Lox/Kerosene rocket engine. 363.2 kN. Atlas D. Atlas Sustainer. Gas generator, pumpfed. Shared turbopumps for booster engines. Isp=309s. First flight 1958. More...

XLR25CW1 CurtissWright Lox/Alcohol rocket engine. 66.880 kN. Out of Production. First flight 1954. Two chamber engine built for X2 rocketplane. Engine could be throttled continuously from 1140 kgf to 6820 kgf. More...

XLR895 Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Atlas D. Designed for booster applications. Gas generator, pumpfed. Shared turbopumps for booster engines. Isp=282s. First flight 1958. More...

XLR891 Rocketdyne Lox/Kerosene rocket engine. 758.7 kN. Atlas A, B, C. Out of production. Designed for booster applications. Gas generator, pumpfed. Shared turbopumps for booster engines. Isp=282s. First flight 1957. More...

XLR83NA1 Rocketdyne Lox/Kerosene rocket engine. 602 kN. Out of production. Isp=273s. Experimental version of the engine for the booster of the Navaho G38 intercontinental cruise missile. Flown in the Navaho G26 booster prototypes. First flight 1956. More...

XLR99 Thiokol Lox/Ammonia rocket engine. 262.4 kN. Out of production. Isp=276s. The first large, manrated, throttleable, restartable liquid propellant rocket engine, boosted the X15A. First flight 1959. More...

XR3A2 XCOR Lox/Alcohol rocket engine. 0.700 kN. First stages. Hardware. The XR3A2 700newton 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 pressurefed, regeneratively cooled engine. Flown on the EZRocket, a modified LongEZ 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 XRacer. 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. Pumpfed, 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...

XRJ47W5 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 G26 launch vehicle. First flight 1956. More...

XRS2200 Rocketdyne lox/lh2 rocket engine. 1192 kN. Development ended 1999. Isp=439s. Linear aerospike engine for X33 SSTO technology demonstrator. Based on J2S engine developed for improved Saturn launch vehicles in the 1960's. More...

YaRD OKB456 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 OKB670 Bondaryuk nuclear/ammonia+alcohol rocket engine. 1667 kN. Development ended 1960. Isp=470s. Proposed for YaRD nuclearpowered ICBM. Propellant was heated in the reactor and exhausted through four expansion nozzles. More...

YF120t CAALPT Lox/Kerosene rocket engine. 1340.2 kN. In development. Isp=336s. For CZ5 Next Generation Launch Vehicle series. Engine can be throttled to 65% of rated thrust. Firing tests began in 2005. More...

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

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

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

YF50t 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 YF73 and YF75 upper stage engines. More...
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