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Manufacturer's Designation: McDonnell. Class: Manned. Type: Spacecraft Module. Nation: USA. Agency: NASA. Manufacturer: McDonnell. 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. Length: 2.67 m (8.75 ft). Basic Diameter: 3.18 m (10.43 ft). Mass: 2,337 kg (5,152 lb). L/D Hypersonic: 0.45. Electrical System: Batteries. Contact us with any corrections, additions, or comments. Conditions for use of drawings, pictures, or other materials from this site.. To contact astronauts or cosmonauts. © Mark Wade, 1997 - 2008 except where otherwise noted. |