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Lox/LH2

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J-2 Credit: © Mark Wade

Specific impulse: 451 s. Specific impulse sea level: 391 s. Location: 2435.

Temperature of Combustion: 2,985 deg K. Ratio of Specific Heats: 1.26. Characteristic velocity c: 2,435 m/s (7,988 ft/sec). Isp Shifting: 391 sec. Isp Frozen: 388 sec. Mol: 10.00 M (32.00 ft).Oxidizer Density: 1.140 g/cc. Oxidizer Freezing Point: -219 deg C.Oxidizer Boiling Point: -183 deg C.Fuel Density: 0.071 g/cc. Fuel Freezing Point: -259 deg C. Fuel Boiling Point: -253 deg C.

Propellant Formulation: LOX/LH2. Optimum Oxidizer to Fuel Ratio: 6. Density: 0.28 g/cc.

Propellant Formulation: LOX/Slush LH2. Optimum Oxidizer to Fuel Ratio: 4. Density: 0.33 g/cc,

AEC engine Rocketdyne LOx/LH2 rocket engine. Advanced Expander Cycle Engine. Expander regenerator, pump-fed.

Aerospike Annular Booster Rocketdyne LOx/LH2 rocket engine. Aerospike Typical Annular Booster . Pressure-fed. Thrust from 50,000 to 250,000 lbs at altitude.

AMPS-1 Rocketdyne LOx/LH2 rocket engine. Advanced Maneuvering Propulsion System Booster. Pressure-fed.

ASE Rocketdyne LOx/LH2 rocket engine. Advanced Space Engine. Staged combustion, pump-fed.

Bono Saucer American manned spaceplane. Study 1963. In 1963 Phil Bono of Douglas Aircraft considered a lenticular configuration for a single-stage-to-orbit reusable booster. This was the largest application found to date for the lenticular concept.

Centaur C LOx/LH2 propellant rocket stage. Initial flight version of the Centaur series.

CEV SAIC American manned spacecraft. Study 2012. SAIC's notional CEV was a Soyuz-shaped aeroshell, enclosing a common pressurized module, and accommodating a crew of four.

CEV Schafer American manned spacecraft. Study 2012. Schafer proposed a lightweight 11 metric ton integral CEV, staged from L1.

Cobra Pratt and Whitney LOx/LH2 rocket engine. Design 2003. Proposed as a long-life, moderate-to high-thrust, reusable booster engine that incorporated a safe, low-cost, low-risk, LH2/LOX single burner, using a fuel-rich, staged combustion cycle.

HG-3 Rocketdyne LOx/LH2 rocket engine. Study 1967. 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.

J-2 Rocketdyne LOx/LH2 rocket engine. Used in the Saturn IVB stage in Saturn IB and Saturn V, and the Saturn II stage in the Saturn V. First flight 1966. Sea level versions with reduced expansion ratio were proposed for Saturn II first stage use. Upgraded toroidal aerospike versions (J-2T-200K and J-2T-250K) were developed for upgrades to Saturn upper stages. The modestly improved J-2S was tested and provided basis for X-33 linear aerospike engine thirty years later. After 30 years the J-2 was resurrected again for use in boosting NASA's new Orion manned capsule to orbit. In the event, NASA was unable to resist 'improving' the J-2S, and by early 2007 the engine for the second stage of the Ares 1 Crew Launch Vehicle was the redesignated and substantially different J-2X.

J-2S Rocketdyne LOx/LH2 rocket engine. Developed 1965-1969. 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.

J-2T-200K Rocketdyne LOx/LH2 rocket engine. Study 1965. Proposed for later versions of Saturn V. Toroidal aerospike plug nozzle version of J-2.

J-2T-250K Rocketdyne LOx/LH2 rocket engine. Study 1967. Proposed for later versions of Saturn V. Toroidal aerospike plug nozzle version of J-2.

J-2X Rocketdyne LOx/LH2 rocket engine. Ares I launch vehicle second stage. In development 2006-2016. 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.

KVRB Russian space tug. Study 1992. Upper stage / space tug - design 1992. High energy upper stage for Proton, never put into production.

LE-5B engine Mitsubishi LOx/LH2 rocket engine. In production. Improved model of the LE-5A for second stage of the H-II rocket; used hydrogen for the cooling of the thrust chamber, then as the gas to drive the turbine. First flight 2001.

LE-7 Mitsubishi LOx/LH2 rocket engine for H-2 upper stages. Staged combustion turbopump. No throttle capability. First flight 1994.

LEV American manned lunar lander. Study 1989. The Lunar Excursion Vehicle (LEV) figured in numerous NASA studies of the 1980's and 1990's.

LLV American lunar logistics spacecraft. Study 1966. Many versions of new Lunar Logistic Vehicles (LLV's) using several possible candidate propellants were studied by NASA and its contractors in the mid-1960's for post-Apollo lunar base support.

LM Langley Lighter American manned lunar lander. Study 1961. This early open-cab Langley design used cryogenic propellants. The cryogenic design was estimated to gross 3,284 kg - to be compared with the 15,000 kg / 2 man LM design that eventually was selected.

LM Langley Lightest American manned lunar lander. Study 1961. Extremely light-weight open-cab lunar module design considered in early Langley studies.

LR87 LH2 Aerojet LOx/LH2 rocket engine. Development ended 1961. Version of the Titan engine, and first large LOx/LH2 engine fired in the world. 52 static tests. But NASA selected Rocketdyne instead to develop the J-2 engine for Saturn from scratch.

M-1 Aerojet LOx/LH2 rocket engine. Study 1961. Engine developed 1962-1966 for Uprated Saturn and Nova million-pound payload boosters to support manned Mars missions. Reached component test stage before cancellation.

Mars Oz Australian manned Mars expedition. Study 2006. 2001 design study by the Mars Society Australia that incorporated many innovative elements to produce a minimum-mass non-nuclear Mars expedition concept.

MB-60 Rocketdyne LOx/LH2 rocket engine. Design 2004. Mitsubishi / Boeing joint project for an engine for Delta IV cryogenic upper stages. Expander bleed, pump-fed.

N1 Block R LOx/LH2 propellant rocket stage. Designed 1965-1971 as replacement for N-1 Blok D. Cancelled 1971 in favor of Blok Sr; revived and developed in 1974-1976. First static test Oct 12 1976. Two stages tested 1976-1977. Strangely never replaced Blok D on Proton.

N1 Block Sr LOx/LH2 propellant rocket stage. Upper stage developed 1971-1974 to support manned lunar expedition. Replaced Blok R/Blok S previously under development. Capable of five restarts and 11 days of flight. Could insert 24 metric tons into lunar orbit or 20 metric tons into geosynchronous orbit.

NASA Mars Expedition 1971 American manned Mars expedition. Study 1971. Final NASA Mars expedition before the 1980's. The spacecraft would use shuttle hardware, including SSME engines in the rocket stages.

Nova 60-8-2 LOx/LH2 propellant rocket stage. Mass estimated based on total LV weight. J-2-powered version of this stage also proposed.

OOST stage Bono's earliest design for an expendable single-stage-to-orbit LH2/LOx booster. The baseline version used conventional engines.

OTV American space tug. Studied 1985-1989. The Orbital Transfer Vehicle was reusable space tug, powered by LOx/LH2 engines and equipped with an aerobrake allowing it to be returned for refueling and reuse at an orbiting space station.

P320 Rocketdyne, Friedrichshafen LOx/LH2 rocket engine. BORD 1/P320 BOELKOW (Germany)/Rocketdyne Technology. Pressure-fed.

RBCC Rocketdyne LOx/LH2 rocket engine. Isp>400s. Rocket Based Combined-Cycle A5 Development Engine; integrated rocket, air-augmented rocket, ramjet, and scramjet propulsion elements into a single flow path.

RD-0120 Kosberg engine used in the Energia core stage. In 1987 it became the first operational Russian LOx/LH2 engine system, built to the same overall performance specifications as America's SSME, but using Russian technology.

RD-0120M Kosberg LOx/LH2 rocket engine. Energia-M core stage. Development ended 1993. From 1987 KBKhA worked on upgrading the 11D122 (RD-0120) engine for Energia-M launcher, including the possibility to throttle the engine down to 28% thrust.

RD-0126 Kosberg LOx/LH2 rocket engine. Space tugs or upper stage for Onega or Yastreb versions of Soyuz. Single annular chamber with expansion-deflection nozzle, separate turbopumps. Design concept 1993. Hot-tests in 1998.

RD-0126A Kosberg LOx/LH2 rocket engine. Upper stages. Design concept 1996-. Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump.

RD-0146 Kosberg LOx/LH2 rocket engine. Centaur upper stage (Atlas); high performance upper stages for Onega, Proton, Angara launch vehicles. Design concept 1998-.

RL-10 Pratt and Whitney LOx/LH2 rocket engine family. First flight 1961. Originally planned for use in Centaur upper stage for Atlas, but earliest successful flights in Saturn IV stage for Saturn I. Throttleable version designed for direct-landing Apollo mission, but cancelled. Sea-level version used in DC-X SSTO test vehicle. Numerous developed versions used in Atlas, Atlas V, Delta IV upper stages. Only production American upper-stage LOx/LH2 engine. Specifications are for early version as proposed for Nova A, Nova B, Saturn B-1, Saturn C-2, Saturn C-3, Saturn I. First flight 1961.

RL-10A-1 Pratt and Whitney LOx/LH2 rocket engine. Version used on Atlas Centaur LV-3C, and proposed for various early Saturn launch vehicle designs. First flight 1961.

RL-10A-3 Pratt and Whitney LOx/LH2 rocket engine. First flight 1967.

RL-10A-3A Pratt and Whitney LOx/LH2 rocket engine. Used on Centaur stage atop Atlas G, Atlas I, Atlas II, Titan 4. First flight 1984.

RL-10A-4 Pratt and Whitney LOx/LH2 rocket engine. Out of production. Centaur stage for Atlas IIA, Atlas IIAS. First flight 1992.

RL-10A-4-1 Pratt and Whitney LOx/LH2 rocket engine. Out of production. Used on Atlas IIIA launch vehicle. First flight 2000. Version with one of engines removed; remaining engine re-positioned to center-mount; new electro-mechanical gimbals.

RL-10A-4-2 Pratt and Whitney LOx/LH2 rocket engine. In production. Used on Atlas IIIB launch vehicle. First flight 2002. Two engines; electro-mechanical thrust vector control actuators replaced earlier hydraulically actuated system.

RL-10B-2 Pratt and Whitney LOx/LH2 rocket engine. In production. Used on Delta 3 , Delta IV launch vehicles. First flight 1998. Extendable exit cone for increased specific impulse; electromechanical actuators replace hydraulic systems.

RL-50 Pratt and Whitney LOx/LH2 rocket engine. Development. Advanced, high-performance upper-stage rocket engine proposed by Pratt & Whitney for both domestic and international launch vehicles.

RL-60 Pratt and Whitney LOx/LH2 rocket engine. Design. Upper stage engine to have been developed by Pratt and Whitney with several international partners. Same dimensions as the RL-10, but over twice the thrust.

RM-1500H Rocketdyne LOx/LH2 rocket engine. Space Shuttle Orbiter Auxiliary Propulsion. Pressure-fed.

RS-2100 Rocketdyne LOx/LH2 rocket engine. Next Generation Launch Vehicle Booster. Full flow staged combustion, pump-fed. Thrust and specific impulse values are at sea level.

RS-2200 Rocketdyne LOx/LH2 rocket engine. Development cancelled 1999. Linear Aerospike Engine developed for use on the Lockheed Reusable Launch Vehicle, the production follow-on to the X-33.

RS-52 Rocketdyne LOx/LH2 rocket engine. 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.

RS-68 Rocketdyne LOx/LH2 rocket engine. In production. First new large liquid-fueled rocket engine developed in America in more than 25 years. Powered the Delta IV booster. First flight 2002.

RS-71 Rocketdyne LOx/LH2 rocket engine. Development ended 1999. Linear Aerospike SR-71 Experiment. Pressure-fed.

RS-74 Rocketdyne LOx/LH2 rocket engine. Next Generation Launch Vehicle Booster. Full flow staged combustion, pump-fed. Thrust and specific impulse values are at sea level.

Saturn II LOx/LH2 propellant rocket stage. Configuration as flown.

Saturn IV LOx/LH2 propellant rocket stage. Configuration as flown.

Saturn MS-IVB-2 LOx/LH2 propellant rocket stage. Douglas Studies, 1965: S-IVB with 315 k high pressure 3000 psia engine, 350,000 pounds propellant.

Space Tug The original Boeing Space Tug design of the early 1970's was sized to be flown either in a single shuttle mission or as a Saturn V payload. Optimum mass was found to be 20.6 metric tons regardless.

SSME Rocketdyne LOx/LH2 rocket engine. In production. 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.

SSME Demonstrator Booster Rocketdyne LOx/LH2 rocket engine. Pressure-fed.

STCAEM Cryogenic Aerobrake American manned Mars expedition. Study 1991. The STCAEM cryogenic / aerobrake (CAB) concept was used as the NASA reference vehicle.

TRW Mars American manned Mars expedition. Study 1963. In 1963 TRW designed a Mars expedition using aerobraking at both Mars and Earth, and a swing-by of Venus on return.

VTOHL 45t American SSTO winged orbital launch vehicle. Vertical Takeoff Horizontal Landing (winged).

Vulcain 2 SEP, Ottobrunn LOx/LH2 rocket engine. In development. New generator cycle rocket engine for an Ariane 5 core stage upgrade. Thrust increased more than 30% from Vulcain 1. First flight 2002.

X-8 Rocketdyne LOx/LH2 rocket engine. Booster applications. Gas generator, pump-fed. Thrust and specific impulse values are at sea level.

XRS-2200 Rocketdyne LOx/LH2 rocket engine. Development ended 1999. Linear aerospike engine for X-33 SSTO technology demonstrator. Based on J-2S engine developed for improved Saturn launch vehicles in the 1960's.

YF-73 Beijing Wan Yuan LOx/LH2 rocket engine. In development. Gas-generator turbopump. Gimbaled engine. Used on CZ-3 launch vehicle. First flight 1984.

YF-77 CAALPT LOx/LH2 rocket engine for next generation Chinese launch vehicle series. It was an indigenous development based on Chinese experience with the YF-73 and YF-75 upper stage engines.