American manned spacecraft module. 12 launches, 1964.04.08 (Gemini 1) to 1966.11.11 (Gemini 12).
Structure: 250 kg (550 lb). Reaction Control System: 60 kg (132 lb). Telemetry Equipment: 40 kg (88 lb). Electrical Equipment: 294 kg (648 lb). Miscellaneous Contingency: 75 kg (165 lb). Environmental Control System: 117 kg (257 lb). RCS Fine No x Thrust: 8 x 98 N. RCS specific imulse: 288 sec. RCS total impulse: 1,078 kgf-sec. Spacecraft delta v: 222 m/s (728 ft/sec). Electric System: 151.00 kWh. Electric System: 2.16 average kW.
AKA: Equipment Module.
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Gross mass: 1,277 kg (2,815 lb).
Unfuelled mass: 955 kg (2,105 lb).
Height: 1.40 m (4.50 ft).
Diameter: 3.05 m (10.00 ft).
Specific impulse: 273 s.
Gemini American manned spacecraft. 12 launches, 1964.04.08 (Gemini 1) to 1966.11.11 (Gemini 12). It was obvious to NASA that there was a big gap of three to four years between the last Mercury flight and the first scheduled Apollo flight. More...
N2O4/MMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Monomethylhydrazine (CH3NHNH2) is a storable liquid fuel that found favour in the United States for use in orbital spacecraft engines. Its advantages in comparison to UDMH are higher density and slightly higher performance. More...
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