American manned spacecraft module. Study 1961. Conventional spacecraft structures were employed, following the proven materials and concepts demonstrated in the Mercury and Gemini designs.
Primary structure consisted of a semimonocoque shell with reinforcements around cut-outs and fittings to distribute localized loads. Titanium was used as the basic shell material. Re-entry heat protection was conservatively designed for a controlled 17,000 km range, polar re-entry. The ablative material was M.A.C. Thermorad Shield S-3 elastomeric composite, which was being used for the Gemini blunt face heat shield. A 1.15 factor was applied to the predicted heating rates. Nominal material physical properties were used, determined from Project Gemini testing. Total ablative material design weight was 259 kg.
Crew Size: 2.
Gross mass: 2,337 kg (5,152 lb).
Height: 2.67 m (8.75 ft).
Diameter: 3.18 m (10.43 ft).
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Associated Countries
Associated Spacecraft
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Apollo Direct 2-Man American manned lunar lander. Study 1961. A direct lunar lander design of 1961, capable of being launched to the moon in a single Saturn V launch through use of a 75% scale 2-man Apollo command module. More...
See also
Associated Manufacturers and Agencies
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NASA American agency overseeing development of rockets and spacecraft. National Aeronautics and Space Administration, USA, USA. More...
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McDonnell American manufacturer of spacecraft. McDonnell, St Louis, USA. More...
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