Apollo spacecraft

The Apollo spacecraft was designed as part of the Apollo Program, by the United States in the early 1960s to land people on the moon before 1970 and return them safely to earth. It was made up of multiple units or modules that worked together to perform the mission of landing on the moon and returning to earth. The main parts of the Apollo spacecraft were (going from top to bottom) the launch escape system, the Command Module, the Service Module, the Lunar Module and the lunar module adapter.

Command Module (CM)

The Command Module was the control center for the Apollo spacecraft and living quarters for the crew. It contained the pressurized main crew cabin, crew couches, control and instrument panel, optical and electronic guidance systems, communications systems, environmental control system, batteries, heat shield, reaction control system, forward docking hatch, side hatch, five windows and the parachute recovery system.

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• Specifications:
• Crew: 3
• Crew cabin volume: 6.17 m³
• Length: 3.47 m
• Diameter: 3.90 m
• Mass: 5,806 kg
• Structure Mass: 1,567 kg
• Heat Shield Mass: 848 kg
• RCS Mass: 400 kg
• Recovery Equipment Mass: 245 kg
• Navigation Equipment Mass: 505 kg
• Telemetry Equipment Mass: 200 kg
• Electrical Equipment Mass: 700 kg
• Communications Systems Mass: 100 kg
• Crew Couches and Provisions Mass: 550 kg
• Environmental Control System Mass: 200 kg
• Mis. Contingency Mass: 200 kg
• RCS Thrust: 12 x 420 N
• RCS Propellants: N₂O₄/UDMH
• RCS Engine Propellants: 75 kg
• RCS Specific Impulse I_sp: 290 lbf·s/lb (2.84 kN·s/kg)
• RCS Impulse: 257 kN·s
• Electric System Batteries: 20.0 kW·h, 1000 A·h