Encyclopedia Astronautica
Rocketdyne


Rocketdyne, USA.

AKA: North American Aviation (1944); Rocketdyne Division of North American (1955); Rockwell Rocketdyne (1966?); Boeing Rocketdyne (1996); Boeing Canoga Park.

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Associated People
  • Dixon Dixon, Thomas F (1926-) American engineer, analyzed a recovered V-2 rocket engine in 1944. Important role at Rocketdyne 1948-1961 in development of rocket engines from the V-2 through to the prototype for the F-1. NASA Deputy Associate Administrator 1961-1963. More...

Associated Countries
Associated Spacecraft
  • KE ASAT American military anti-satellite system. Study 1989. In 1989 the US Army began a demonstration/validation program to develop a direct ascent kinetic energy ASAT for US forces. More...

Associated Engines
  • 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...
  • AABS Rocketdyne Lox/Kerosene rocket engine. 17.779 kN. Aerospike Annular Booster and Sustainer. Pressure-fed. Booster thrust 3000 to 4000 lb vac; sustainer 1500-2000 lb vac, 257 sec specific impulse. Isp=285s. More...
  • AEC Rocketdyne lox/lh2 rocket engine. 66.695 kN. Advanced Expander Cycle Engine. Expander regenerator, pump-fed. Isp=481s. More...
  • Aerospike Annular Booster Rocketdyne lox/lh2 rocket engine. 1111.662 kN. Aerospike Typical Annular Booster . Pressure-fed. Thrust from 50,000 to 250,000 lbs at altitude. Isp=450s. More...
  • Aestus DASA/Rocketdyne Rocketdyne rocket engine. Dasa (Germany)/Rocketdyne Non-Toxic Shuttle OMS. Gas generator, pump-fed. Name later reapplied to storable propellant engine for Ariane 5. More...
  • Aestus-2 Rocketdyne / DASA N2O4/MMH rocket engine. 60 kN. Production. Restartable upper-stage engine, began test firings at Lampoldshausen in February 2000. More...
  • AMPS-1 Rocketdyne lox/lh2 rocket engine. 80.032 kN. Advanced Maneuvering Propulsion System Booster. Pressure-fed. Isp=468s. More...
  • AR1 Rocketdyne h2o2/kerosene rocket engine. 22.260 kN. Engine for FJ-4F naval interceptor. More...
  • AR2-3 Rocketdyne h2o2/kerosene rocket engine. 29.341 kN. Future-X Demonstrator Engine. Gas generator, pump-fed. Heritage technology in evaluation for current applications. X-37 Reusable Upper Stage Vehicle. Isp=245s. More...
  • ASE Rocketdyne lox/lh2 rocket engine. 88.926 kN. Advanced Space Engine. Staged combusion, pump-fed. Isp=473s. More...
  • ATE Rocketdyne N2O4/MMH rocket engine. 20 kN. Developed 1990's. Advance technology engine for maneuvering stages. Isp=347s. More...
  • B-2C Rocketdyne Lox/Kerosene rocket engine. Atlas A. Launch thrust 1374 kN. Atlas Booster. Gas generator, pump-fed. Thrust and specific impulse values are at sea level. First flight 1958. 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...
  • Expansion-Deflection 10k Rocketdyne N2O4/Aerozine-50 rocket engine. Launch thrust 44.463 kN. Expansion-Deflection Booster (10,000 lb thrust). Pressure-fed. Thrust and specific impulse values are at sea level. More...
  • Expansion-Deflection 50k Rocketdyne N2O4/Aerozine-50 rocket engine. Launch thrust 222.326 kN. Expansion-Deflection Booster (50,000 Ib thrust). Pressure-fed. Thrust and specific impulse values are at sea level. More...
  • 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...
  • FLEXEM Rocketdyne exotic ClF3/Hydrazine rocket engine. 48.905 kN. Flexible Energy Management. Pressure-fed. Sustainer 267-4000 lb thrust vacuum, specific impulse 260 seconds. Isp=275s. More...
  • G-1 Rocketdyne exotic LF2/Hydrazine rocket engine. 53.5 kN. Atlas upper stage. Developed 1960's. Engine developed for replacement of Agena upper stage in late 1950's. Not flown due to toxicity of propellants. NOMAD Upper Stage System. Pressure-fed. Isp=357s. More...
  • 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...
  • Hall Electric Thruster TsNIIMASH / Rocketdyne electric/xenon rocket engine. 3 N. Development. Isp=1600s. Satellite orbit raising and station-keeping applications. Electric, pressure-fed. Variable 80 mN - 3.0 N thrust, specific impulse 1600 to 3500 seconds. More...
  • HG-3 Rocketdyne lox/lh2 rocket engine. 1400.7 kN. Study 1967. Isp=451s. High-performance high-pressure chamber engine developed from J-2. Considered for upgrades to Saturn V launch vehicle upper stages. Technology led to Space Shuttle Main Engines. More...
  • IPD Rocketdyne lox/lh2 rocket engine. 1100 kN. Development ended 2006. Integrated Powerhead Demonstrator, end goal was flight-rated, full-flow, hydrogen-fueled, staged combustion rocket engine in the 1.1-million-newton thrust class. More...
  • J-2 Rocketdyne lox/lh2 rocket engine. 1033.1 kN. Study 1961. Isp=421s. Used in Saturn IVB stage in Saturn IB and Saturn V, and Saturn II stage in Saturn V. Gas generator, pump-fed. First flight 1966. More...
  • J-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...
  • J-2S Rocketdyne lox/lh2 rocket engine. 1138.5 kN. Developed 1965-1969. Isp=436s. J-2 version proposed for Saturn follow-on vehicles, using results of the J-2X technology program. The engine was simplified while offering improved performance. More...
  • J-2T-200K Rocketdyne lox/lh2 rocket engine. 889.3 kN. Study 1965. Proposed for later versions of Saturn V. Toroidal aerospike plug nozzle version of J-2. Isp=435s. More...
  • J-2T-250K Rocketdyne lox/lh2 rocket engine. 1111.6 kN. Study 1967. Proposed for later versions of Saturn V. Toroidal aerospike plug nozzle version of J-2. Isp=441s. More...
  • J-2X Rocketdyne lox/lh2 rocket engine. 1310 kN. Ares I launch vehicle second stage. In development 2006-2016. Isp=448s. Began as an update to the J-2 engine of the 1960s, but final design was all-new, 20% more thrust, but double the weight. More...
  • KEW-3 Rocketdyne N2O4/MMH rocket engine. 0.441 kN. Kinetic Energy Propulsion (100 Ib thrust). Pressure-fed. ASAT Strap-down test, XSS / DICE Microsatellite, GBI Ground-Based Interceptor, THAAD Theater High Altitude Area Defense. Isp=283s. More...
  • KEW-2 Rocketdyne N2O4/MMH rocket engine. 0.215 kN. Kinetic Energy Propulsion (50 Ib thrust). Pressure-fed. ASAT Strap-down test, XSS / DICE Microsatellite, GBI Ground-Based Interceptor, THAAD Theater High Altitude Area Defense. Isp=275s. More...
  • KEW-1 Rocketdyne N2O4/MMH rocket engine. 0.029 kN. Kinetic Energy Propulsion (7 Ib thrust). Pressure-fed. ASAT Strap-down test, XSS / DICE Microsatellite, GBI Ground-Based Interceptor, THAAD Theater High Altitude Area Defense. Isp=266s. More...
  • KEW-4 Rocketdyne N2O4/MMH rocket engine. 2.216 kN. Kinetic Energy Propulsion (500 Ib thrust). Pressure-fed. ASAT Strap-down test, XSS / DICE Microsatellite, GBI Ground-Based Interceptor, THAAD Theater High Altitude Area Defense. Isp=235s. More...
  • L-1 Linear Aerospike Booster Rocketdyne Lox/Kerosene rocket engine. Launch thrust 889.36 kN. Gas generator, pump-fed. Thrust and specific impulse values are at sea level. More...
  • L-2 Linear Aerospike Booster Rocketdyne Lox/Kerosene rocket engine. Launch thrust 444.63 kN. Gas generator, pump-fed. Thrust and specific impulse values are at sea level. More...
  • LE-3 Rocketdyne N2O4/Aerozine-50 rocket engine. 53.340 kN. MHI(Japan)/Rocketdyne Upper Stage. Pressure-fed. Isp=285s. 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...
  • LR101-NA-7 Rocketdyne N2O4/MMH rocket engine. 5.148 kN. Upper Stage Target Engine Systems. Pressure-fed. Derived from Atlas vernier. Isp=251s. More...
  • 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...
  • LR54 Rocketdyne H2O2/Kerosene rocket engine. 26.4 kN. After the failure of the Reaction Motors XLR-40 for use in the F8U-1 fighter, Vought elected to continue the project using the XLR-54 . Project never reached flight status More...
  • 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...
  • 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...
  • 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...
  • 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...
  • MB-3-J Rocketdyne Lox/Kerosene rocket engine. Out of production. Launch thrust 755.89 kN. N Booster . Gas generator, pump-fed. Joint MHI (Japan) / Rocketdyne project, evolved from MB-3. Thrust and specific impulse values are at sea level. First flight 1975. 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...
  • MB-35 Rocketdyne lox/lh2 rocket engine. 156 kN. Design 2004. Isp=467s. Mitsubishi / Boeing joint project for an engine for Delta IV cryogenic upper stages. Expander bleed, pump-fed. More...
  • MB-45 Rocketdyne lox/lh2 rocket engine. 200 kN. Design 2004. Isp=467s. Mitsubishi / Boeing joint project for an engine for Delta IV cryogenic upper stages, announced February 2000. More...
  • MB-60 Rocketdyne lox/lh2 rocket engine. 266.7 kN. Design 2004. Isp=467s. Mitsubishi / Boeing joint project for an engine for Delta IV cryogenic upper stages. Expander bleed, pump-fed. More...
  • MUT Rocketdyne MON/UDMH rocket engine. 5.635 kN. Satellite maneuvering motor. Developed 2005. Isp=292s. New technology motor with improved thrust/weight ratio and use of mixed oxides of nitrogen oxidiser with a much lower freezing point than N2O4. More...
  • NPS-2 Rocketdyne nuclear/lh2 rocket engine. Nuclear Deep Space. Nuclear. Liquid hydrogen turbopumps, feed systems, and nozzles developed for KIWI-A, KIWI-B, Nerva, Pheobus IA, MFS-1, MFS-2, MFS-3, and Rover nuclear development systems. More...
  • P-7 Rocketdyne N2O4/Aerozine-50 rocket engine. Launch thrust 222.31 kN. Aspen Booster. Pressure-fed. Thrust from 12,000 lb to 50,000 lb at sea level. More...
  • P320 Rocketdyne, Friedrichshafen lox/lh2 rocket engine. Development. Launch thrust 129 kN. BORD 1/P320 BOELKOW (Germany)/Rocketdyne Technology. Pressure-fed. More...
  • P4-1 Booster Rocketdyne Lox/Kerosene rocket engine. 2.441 kN. AQM-37. Target System Booster. Pressure-fed. Isp=232s. First flight 1963. More...
  • P4-1 Sustainer Rocketdyne Lox/Kerosene rocket engine. 0.470 kN. AQM-37. Target System Sustainer. Pressure-fed. Isp=262s. First flight 1963. More...
  • P8E-9 Rocketdyne Nitric acid/UDMH rocket engine. Lance. Launch thrust 205.44 kN. Lance Booster and Sustainer System. Pressure-fed. Sustainer 4400 -14,400 lbf, 227 sec Isp. Thrust and specific impulse values are at sea level. First flight 1972. More...
  • 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...
  • RBCC Rocketdyne lox/lh2 rocket engine. Launch thrust 111.158 kN. Isp>400s. Rocket Based Combined-Cycle A5 Development Engine; integrated rocket, air-augmented rocket, ramjet, and sramjet propulsion elements into a single flowpath. More...
  • RESA-2 Rocketdyne N2O4/MMH rocket engine. 0.215 kN. Pitch Control Propulsion Module. Pressure-fed. More...
  • RESA-5 Rocketdyne N2O4/MMH rocket engine. 7.109 kN. Spacecraft. Pressure-fed. Isp=280s. More...
  • RM-01 Rocketdyne hydrazine monopropellant rocket engine. 44 mN. Spacecraft. Pressure-fed. Isp=91s. More...
  • RM-05 Rocketdyne N2O4/MMH rocket engine. 0.020 kN. Satellite Reaction Control System. Pressure-fed. Isp=238s. More...
  • RM-100A Rocketdyne N2O4/MMH rocket engine. 0.441 kN. Spacecraft. Pressure-fed. Isp=301s. More...
  • RM-100B Rocketdyne Nitric acid/UDMH rocket engine. 0.441 kN. Satellite Reaction Control. Pressure-fed. Isp=283s. More...
  • RM-100T Rocketdyne N2O4/Aerozine-50 rocket engine. 0.441 kN. Lunar Flyer. Pressure-fed. Isp=296s. More...
  • RM-1-1 Rocketdyne N2O4/MMH rocket engine. 4.4 N. Satellite Reaction Control System. Pressure-fed. Isp=245s. More...
  • RM-1-2 Rocketdyne N2O4/MMH rocket engine. 4.4 N. Satellite Reaction Control. Pressure-fed. Isp=238s. More...
  • RM-1500H Rocketdyne lox/lh2 rocket engine. 6.660 kN. Space Shuttle Orbiter Auxiliary Propulsion. Pressure-fed. Isp=400s. More...
  • RM-25 Rocketdyne N2O4/MMH rocket engine. 0.107 kN. Spacecraft. Pressure-fed. Isp=286s. More...
  • RM-25-1 Rocketdyne N2O4/MMH rocket engine. 0.107 kN. Spacecraft. Pressure-fed. Isp=300s. More...
  • RM-900 Rocketdyne N2O4/MMH rocket engine. 4.001 kN. Shuttle Orbiter Reaction Control. Pressure-fed. Isp=309s. More...
  • RN-6 Rocketdyne nuclear/lh2 rocket engine. Nuclear Deep Space. Nuclear. More...
  • RS-14 Rocketdyne N2O4/MMH rocket engine. 1.392 kN. Minuteman Postboost Velocity Control. Pressure-fed. Isp=315s. First flight 1970. More...
  • RS-1402 Rocketdyne N2O4/MMH rocket engine. 0.098 kN. Minuteman Pitch, Yaw & Roll Control. Pressure-fed. Technology engine, developed, but not produced. Led to RS-14 prodution engines. Isp=259s. More...
  • RS-1403 Rocketdyne N2O4/MMH rocket engine. 0.078 kN. Minuteman Pitch, Yaw & Roll Control. Pressure-fed. Technology engine, developed, but not produced. Led to RS-14 prodution engines. Isp=230s. More...
  • RS-18 Rocketdyne N2O4/Aerozine-50 rocket engine. 15.563 kN. Apollo Lunar Ascent Module Engine. Pressure-fed. Isp=310s. More...
  • RS-19 Rocketdyne exotic ClF3/Hydrazine rocket engine. Launch thrust 3.108 kN. Condor Development Booster Air-to-Ground Missile. Pressure-fed. Thrust and specific impulse values are at sea level. More...
  • RS-2200 Rocketdyne lox/lh2 rocket engine. 2201 kN. Development cancelled 1999. Isp=455s. Linear Aerospike Engine developed for use on the Lockheed Reusable Launch Vehicle, the production follow-on to the X-33. More...
  • RS-28 Rocketdyne N2O4/MMH rocket engine. 2.667 kN. Space Shuttle Orbiter Reaction Control. Pressure-fed. Isp=220s. More...
  • RS-27C Rocketdyne Lox/Kerosene rocket engine for Delta 7000. 1054.2 kN. Isp=302s. First flight 1990. 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-23 Rocketdyne N2O4/MMH rocket engine. 26.670 kN. Space Shuttle Orbiter Orbit Maneuvering System. Pressure-fed. Isp=313s. First flight 1981. More...
  • RS-2101C Rocketdyne N2O4/MMH rocket engine. 1.333 kN. Viking. Pressure-fed. Derivtive of RS-14 Minuteman engine. Isp=294s. First flight 1975. More...
  • RS-2101A Rocketdyne N2O4/MMH rocket engine. 1.333 kN. Mars Mariner. Pressure-fed. Derivtive of RS-14 Minuteman engine. Isp=287s. First flight 1971. More...
  • RS-2100 Rocketdyne lox/lh2 rocket engine. Launch thrust 2047.6 kN. Next Generation Launch Vehicle Booster. Full flow staged combustion, pump-fed. Thrust and specific impulse values are at sea level. 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-36 Sustainer Rocketdyne Lox/Kerosene rocket engine. 9.210 kN. HOE Homing Overlay Experiment Upper Stage Axial Propulsion System. Pressure-fed. Derivative of Lance propulsioon system. Isp=262s. First flight 1983. More...
  • RS-32 Rocketdyne N2O4/MMH rocket engine. 1.392 kN. Upper Stage Target Engine Systems. Pressure-fed. Derived from Minuteman RS-14. Isp=288s. More...
  • RS-34 Rocketdyne N2O4/MMH rocket engine. 11.7 kN. Peacekeeper Postboost Axial Thrust. Pressure-fed. 1 main axial thruster per postboost propulsion system. Isp=308s. First flight 1983. More...
  • RS-34 Attitude Control Rocketdyne Lox/Kerosene rocket engine. 0.304 kN. Peacekeeper Postboost Attitude Control. Pressure-fed. 8 attitude thrusters in each postboost propulsion system. Isp=255s. First flight 1983. More...
  • RS-36 Rocketdyne N2O4/MMH rocket engine. 55.6 kN. HOE Homing Overlay Experiment Upper Stage Axial Propulsion System. Pressure-fed. Derivative of Lance propulsioon system. Isp=281s. First flight 1983. More...
  • RS-45 Rocketdyne N2O4/MMH rocket engine. 4.4 N. Satellite Attitude Control and Stationkeeping. Pressure-fed. Isp=300s. More...
  • RS-43 Rocketdyne N2O4/MMH rocket engine. 0.020 kN. Attitude Control. Pressure-fed. Isp=284s. More...
  • RS-41 Rocketdyne N2O4/MMH rocket engine. 11.960 kN. Axial Spacecraft. Pressure-fed. Isp=320s. More...
  • RS-42 Rocketdyne N2O4/MMH rocket engine. 0.441 kN. Axial Spacecraft. Pressure-fed. Isp=305s. More...
  • RS-51 Rocketdyne N2O4/MMH rocket engine. 11.552 kN. Axial Spacecraft. Pressure-fed. Isp=315s. More...
  • RS-52 Rocketdyne lox/lh2 rocket engine. 0.107 kN. Oxygen/Hydrogen Space Station Thruster. Pressure-fed. Technology was developed with 0.1 lb thrust resistojet by using electrically heated waste for space station propulsion. Isp=405s. 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-71 Rocketdyne lox/lh2 rocket engine. 31.126 kN. Development ended 1999. Linear Aerospike SR-71 Experiment. Pressure-fed. Isp=430s. More...
  • RS-77 Rocketdyne solar/lh2 rocket engine. 0.176 kN. Solar Thermal Engine. Pressure-fed. SOTV Solar Orbit Transver Vehicle. Isp=870s. More...
  • RS-76 Rocketdyne Lox/Kerosene rocket engine. Launch thrust 4002 kN. Space Shuttle Reusable First Stage. Ox-Rich staged combustion, pump-fed. Thrust and specific impulse values are at sea level. More...
  • RS-72 Rocketdyne, Ottobrunn N2O4/MMH rocket engine. 55.4 kN. Isp=340s. Aestus engine enhanced with the addition of a Boeing-Rocketdyne XLR 32 turbo-pump. More...
  • RS-74 Rocketdyne lox/lh2 rocket engine. Launch thrust 1112 kN. Next Generation Launch Vehicle Booster. Full flow staged combustion, pump-fed. Thrust and specific impulse values are at sea level. 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-82 Rocketdyne H2O2/kerosene rocket engine. 44.463 kN. Next Generation Non-Toxic Upper Stage. Gas generator, pump-fed. Isp=320s. 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-88 Rocketdyne rocket engine designed and built by Rocketdyne for use on Lockheed's Pad Abort Demonstration vehicle. In 2003, NASA tested the RS-88 in a series of 14 hot-fire tests, resulting in 55 seconds of successful engine operation. 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...
  • 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...
  • 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-3D Rocketdyne Lox/Kerosene rocket engine. Launch thrust 600.1 kN. Jupiter Booster. Gas generator, pump-fed. Thrust later 150,000 lbs. Thrust and specific impulse values are at sea level. First flight 1957. More...
  • S-4 Rocketdyne Lox/Kerosene rocket engine. 412.8 kN. Design ca. 1957. Version of Atlas sustainer tailored to Redstone Arsenal upper-stage requirements. Paper study only. Used on Super Jupiter launch vehicle. More...
  • SE-1, 1-1, -2, and -4 Series Rocketdyne N2O4/UDMH rocket engine. SE-1, 1-1, -2, and -4 Series. Spacecraft Reaction Control. Pressure-fed. Multiple thrust levels. First flight 1959. More...
  • SE-10 Rocketdyne N2O4/Aerozine-50 rocket engine. 46.670 kN. Lunar Module Descent. Pressure-fed. Thrust throttleable 1050-10,500 lbs vac. Isp=305s. First flight 1968. More...
  • SE-5-2/-3 Rocketdyne N2O4/UDMH rocket engine. 0.205 kN. SE-5-2/-3. Agena Auxiliary. Pressure-fed. SE-5-2 four engines in satellite system. SE-5-3 two engines for Agena auxiliary propuslion. Isp=272s. First flight 1963. More...
  • SE-6 Rocketdyne N2O4/MMH rocket engine. 0.107 kN. Gemini Re-entry Control System. Pressure-fed. Isp=277s. First flight 1964. More...
  • SE-7-85 Rocketdyne N2O4/MMH rocket engine. 0.372 kN. Gemini Orbit Attitude and Maneuvering System (85 Ib thrust). Pressure-fed. Isp=295s. First flight 1964. More...
  • SE-7-1 Rocketdyne N2O4/MMH rocket engine. 0.313 kN. S-IVB Stage APS Ullage Control Engine (propellant settling). Pressure-fed. Isp=274s. First flight 1966. More...
  • SE-7-100 Rocketdyne N2O4/MMH rocket engine. 0.441 kN. Gemini Orbit Attitude and Maneuvering System (100 Ib thrust). Pressure-fed. Isp=296s. First flight 1964. More...
  • SE-7-25 Rocketdyne N2O4/MMH rocket engine. 0.107 kN. Gemini Orbit Attitude and Maneuvering System (25 Ib thrust). Pressure-fed. Isp=277s. First flight 1964. More...
  • SE-8 Rocketdyne N2O4/MMH rocket engine. 0.411 kN. Apollo Command Module Reaction Control. Pressure-fed. Isp=274s. First flight 1966. More...
  • SE-9-5 Rocketdyne N2O4/Aerozine-50 rocket engine. 0.196 kN. Titan III Transtage. Pressure-fed. System included two modules of three engines plus two additional SE-9-5 separate engines, tanks, and a pressuirzation system. Isp=300s. First flight 1964. More...
  • SE-9-3 Rocketdyne N2O4/Aerozine-50 rocket engine. 0.107 kN. Titan III Transtage. Pressure-fed. System included two modules of three engines plus two additional SE-9-5 separate engines, tanks, and a pressuirzation system. Isp=295s. First flight 1964. More...
  • Sled Technology Rocketdyne Lox/Alcohol rocket engine. 666 kN. Pressure-fed. From 35,000 to 150,000 lbf. Cook Sled, Air Force Sleds 1 and 2, RS-2 Sled, operated at Edwards and Holloman Air Force Bases. More...
  • SR122 Rocketdyne solid rocket engine. Also designated WPU-9/B1 (AGM-130). 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...
  • 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...
  • X-1 Rocketdyne Lox/Kerosene rocket engine. 880.440 kN. Booster applications. Gas generator, pump-fed. Thrust from 165,000 to 198,000 lbs. More...
  • X-8 Rocketdyne lox/lh2 rocket engine. Launch thrust 400.1 kN. Booster applications. Gas generator, pump-fed. Thrust and specific impulse values are at sea level. 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...
  • XLR132 Rocketdyne N2O4/MMH rocket engine. 16.7 kN. Out of Production. Isp=340s. Pump-fed high performance upper stage engine for perigee/apogee stages. as well as transfer vehicles and lunar and Martian missions. Tested extensively but no production. More...
  • XLR43-NA-1 Rocketdyne Lox/Alcohol rocket engine. 333 kN. Development completed 1951. Mark III American version of single-chamber V-2 engine tested in WW2, but with half mass and 34% more thrust. Starting point for all later Rocketdyne engines. More...
  • XLR71-NA-1 Rocketdyne Lox/Alcohol rocket engine. Development cancelled 1955. Launch thrust 533.7 kN. Planned engine for the booster of the Navaho II test vehicle. Gas generator, pump-fed. 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...
  • 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...
  • 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...
  • 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...

See also
Associated Stages
  • PBS N2O4/MMH propellant rocket stage. Loaded mass 1,000 kg. Thrust 1.40 kN. More...

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