This, plus other required design changes, led to the decision to design two versions of the CSM: Block I was to be used for uncrewed missions and a single crewed Earth orbit flight ( Apollo 1), while the more advanced Block II was designed for use with the lunar module. It was initially designed to land on the Moon atop a landing rocket stage and return all three astronauts on a direct-ascent mission, which would not use a separate lunar module, and thus had no provisions for docking with another spacecraft. The CSM was developed and built for NASA by North American Aviation starting in November 1961.

Just before reentry of the command module on the return home, the umbilical connection was severed and the service module was cast off and allowed to burn up in the atmosphere. An umbilical connection transferred power and consumables between the two modules. It consisted of two parts: the conical command module, a cabin that housed the crew and carried equipment needed for atmospheric reentry and splashdown and the cylindrical service module which provided propulsion, electrical power and storage for various consumables required during a mission. The CSM functioned as a mother ship, which carried a crew of three astronauts and the second Apollo spacecraft, the Apollo Lunar Module, to lunar orbit, and brought the astronauts back to Earth.

The Apollo command and service module ( CSM) was one of two principal components of the United States Apollo spacecraft, used for the Apollo program, which landed astronauts on the Moon between 19. Service Propulsion System (Lunar descent assist) Apollo CSM Endeavour in lunar orbit during Apollo 15

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