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Apollo CSM

Apollo Command/Service Module
Apollo CSM lunar orbit.jpg
Apollo 15 Command and Service Module in lunar orbit
Manufacturer

North American Aviation

North American Rockwell
Designer Maxime Faget
Country of origin United States
Operator NASA
Applications Manned cislunar flight and lunar orbit
Skylab crew shuttle
Apollo-Soyuz Test Project
Specifications
Design life 14 days
Launch mass 32,390 pounds (14,690 kg) Earth orbit
63,500 pounds (28,800 kg) Lunar
Dry mass 26,300 pounds (11,900 kg)
Payload capacity 2,320 pounds (1,050 kg)
Crew capacity 3
Dimensions 36.2 feet (11.0 m) high
12.8 feet (3.9 m) diameter
Volume 218 cubic feet (6.2 m3)
Power Fuel cells
Regime Low Earth orbit
Cislunar space
Lunar orbit
Production
Status Retired
Built 35
Launched 19
Operational 19
Failed 2
Lost 1
First launch February 26, 1966
Last launch July 15, 1975
Last retirement July 24, 1975
Related spacecraft
Flown with Apollo Lunar Module

Apollo program insignia.pngApollo-linedrawing.png
Apollo Block II CSM diagram

← Gemini spacecraft Orion (spacecraft)

North American Aviation

Apollo program insignia.pngApollo-linedrawing.png
Apollo Block II CSM diagram

The Command/Service Module (CSM) was one of two spacecraft, along with the Lunar Module, used for the United States Apollo program which landed astronauts on the Moon. It was built for NASA by North American Aviation. It was launched by itself on three suborbital and low Earth orbit Apollo test missions using the Saturn IB launch vehicle. It was also launched twelve times on the larger Saturn V launch vehicle, both by itself and with the Lunar Module. It made a total of nine manned flights to the Moon aboard the Saturn V.

After the Apollo lunar program, the CSM saw manned service as a crew shuttle for the Skylab program, and the Apollo-Soyuz Test Project in which an American crew rendezvoused and docked with a Soviet Soyuz spacecraft in Earth orbit.


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