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N2O4/Aerozine-50

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Oxidizer Density: 1.450 g/cc. Oxidizer Freezing Point: -11 deg C. Oxidizer Boiling Point: 21 deg C. Fuel Density: 0.903 g/cc. Fuel Freezing Point: -7 deg C. Fuel Boiling Point: 70 deg C.

Apollo LM American manned lunar lander.

Apollo LM Shelter American manned lunar habitat. Cancelled 1968. The LM Shelter was essentially an Apollo LM lunar module with ascent stage engine and fuel tanks removed and replaced with consumables and scientific equipment for 14 days extended lunar exploration.

Apollo LM Taxi American manned lunar lander. Cancelled 1968. The LM Taxi was essentially the basic Apollo LM modified for extended lunar surface stays.

Apollo LM Truck American lunar logistics spacecraft. Cancelled 1968. The LM Truck was an LM Descent stage adapted for unmanned delivery of payloads of up to 5,000 kg to the lunar surface in support of a lunar base using Apollo technology.

Expansion-Deflection 10k Rocketdyne N2O4/Aerozine-50 rocket engine. Expansion-Deflection Booster (10,000 lb thrust). Pressure-fed. Thrust and specific impulse values are at sea level.

Expansion-Deflection 50k Rocketdyne N2O4/Aerozine-50 rocket engine. Expansion-Deflection Booster (50,000 lb thrust). Pressure-fed. Thrust and specific impulse values are at sea level.

LE-3 Rocketdyne N2O4/Aerozine-50 rocket engine. MHI(Japan)/Rocketdyne Upper Stage. Pressure-fed.

P-7 Rocketdyne N2O4/Aerozine-50 rocket engine. Aspen Booster. Pressure-fed. Thrust from 12,000 lb to 50,000 lb at sea level.

R-56 Block K N2O4/Aerozine-50 propellant rocket stage. Empty mass estimated (rounded figures given in source material indicates impossible 9 metric tons gross with 8.7 metric tons propellant).

RM-100T Rocketdyne N2O4/Aerozine-50 rocket engine. Lunar Flyer. Pressure-fed.

RS-18 Rocketdyne N2O4/Aerozine-50 rocket engine. Apollo Lunar Ascent Module Engine. Pressure-fed.

SE-10 Rocketdyne N2O4/Aerozine-50 rocket engine. Lunar Module Descent. Pressure-fed. Thrust throttleable 1050-10,500 lbs vac. First flight 1968.

SE-9-3 Rocketdyne N2O4/Aerozine-50 rocket engine. Titan III Transtage. Pressure-fed. System included two modules of three engines plus two additional SE-9-5 separate engines, tanks, and a pressurization system. First flight 1964.

SE-9-5 Rocketdyne N2O4/Aerozine-50 rocket engine. Titan III Transtage. Pressure-fed. System included two modules of three engines plus two additional SE-9-5 separate engines, tanks, and a pressurization system. First flight 1964.