User:JustinTime55/sandbox/Gemini spacecraft
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The Gemini spacecraft was a two-man spacecraft used for the United States Project Gemini, which followed the one-man Project Mercury and supported the Apollo program goal of landing men on the Moon by the end of the 1960's. It was built for NASA by McDonnell Aircraft. It was launched into low Earth orbit by the Titan II launch vehicle, a derivative of the US Air Force Titan II missile. Two unmanned test flights were made, followed by 10 manned missions, in 1965 and 1966. Gemini demonstrated the capability of keeping two astronauts in orbit for up to 14 days, and was the world's first manned spacecraft capable of changing its orbit in space, and rendezvous and dock with another craft. Its hatches were designed to be opened and closed in space, allowing astronauts to perform extravehicular activity.
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Manufacturer | McDonnell Aircraft | ||
---|---|---|---|
Country of origin | United States | ||
Operator | NASA | ||
Applications | Manned orbital flight | ||
Specifications | |||
Launch mass | 7,100 to 8,350 pounds (3,220 to 3,790 kg) | ||
Crew capacity | 2 | ||
Dimensions | 18 feet 5 inches (5.61 m) long 10 feet (3.0 m) diameter | ||
Volume | 90 cubic feet (2.5 m3) | ||
Power | 2 General Electric fuel cells | ||
Batteries | 5 silver-zinc batteries for re-entry | ||
Regime | Low Earth orbit | ||
Design life | 14 days | ||
Production | |||
Status | Retired | ||
Built | 12 | ||
Launched | 12 | ||
Failed | 0 | ||
Lost | 0 | ||
Maiden launch | April 8, 1964 | ||
Last launch | November 11, 1966 | ||
Last retirement | November 15, 1966 | ||
Related spacecraft | |||
Flown with | Agena Docking Target | ||
Configuration | |||
Gemini spacecraft diagram
|
Mass | ||
---|---|---|
Crew compartment: | 5,910 pounds (2,680 kg) | |
Retro module: | 1,303 pounds (591 kg) | |
Equipment module: | 1,277 pounds (579 kg) | |
Total: | 8,490 pounds (3,850 kg) | |
Rocket engines | ||
Reentry Control System (MMH/N2O4): | 16 x 25 pounds-force (110 N) | |
OAMS (attitude) (MMH/N2O4): | 8 x 25 pounds-force (110 N) | |
OAMS (maneuvering) (MMH/N2O4): | 6 x100 pounds-force (440 N) transverse/fwd 2 x85 pounds-force (380 N) aft | |
Performance | ||
Max delta-v: | 8,490 feet per second (2,590 m/s) |
The Gemini consisted of three segments: the crew compartment (capsule) with seats for two and equipment needed for re-entry and splashdown; a retro module which housed four rockets used to take the craft out of orbit; and an equipment module that provided propulsion, electrical power and storage for various consumables required during a mission. The equipment and retro modules were cast off and allowed to burn up in the atmosphere before the crew compartment re-entered and brought the crew home.
The Gemini program used an Agena Target Vehicle, a modified version of the Agena D rocket stage, to practice docking techniques and for propulsion to raise its orbit to as high as 739.2 nautical miles (1,369.0 km).
The United States Air Force chose a modified Gemini (Gemini B) as the crew launch and re-entry vehicle for its Manned Orbiting Laboratory (MOL). An Air Force astronaut corps was selected, and MOL made one unmanned test flight in 1966 reusing one of the unmanned Gemini capsules. But MOL was cancelled in 1969 by the administration of President Richard M. Nixon.
In August 1969, McDonnell (then McDonnell Douglas) proposed a Big Gemini derivative of the spacecraft as a reusable 9-12 person shuttle vehicle for a space station. This proposal was never adopted.