Langley 4,372 kg LM - Langley 4,372 kg lunar lander Credit: © Mark Wade. 993 bytes. 162 x 120 pixels.

Earliest lunar orbit rendezvous schemes involved use of one or more extremely lightweight, unpressurized lunar landers to take a single astronaut to the lunar service. This Langley design used cryogenic propellants. An even more marginal cryogenic design was estimated to gross 1,460 kg - to be compared with the 15,000 kg / 2 man design that eventually was selected. Propellant load estimated.

Craft.Crew Size: 1. Design Life: 1 days. Total Length: 2.6 m. Maximum Diameter: 3.5 m. Total Mass: 3,284 kg. Total Payload: 150 kg. Total Propellants: 2,200 kg. Main Engine Propellants: Lox/LH2. Main Engine Isp: 444 sec.

• 26 - Baker, David, The History of Manned Spaceflight, Crown, New York, 1981.
• 27 - Brooks, Courtney G, Grimwood, Hames M, Swenson, Lloyd S, Chariots for Apollo, Government Printing Office, 1989. HTML when accessed: http://www.hq.nasa.gov/office/pao/History/SP-4205/cover.html

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LM Langley Credit: © Mark Wade. 7,279 bytes. 344 x 576 pixels.

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