Editing AS-201 (section)

==Objectives==
The objectives of the mission were to:
* Demonstrate the Saturn IB launch vehicle propulsion, guidance and electrical systems
* Demonstrate structural compatibility between the launch vehicle and CSM, ensuring the spacecraft's design loads weren't exceeded
* Demonstrate appropriate separation of all vehicle elements
* Demonstrate the CSM's heat shield, service propulsion system (including in-space restart), CM and SM reaction control systems, environmental control of cabin pressure and temperature, partial communications, stability and control, Earth landing system, and electrical power subsystem.
* Evaluate the Emergency Detection System in an [[Open-loop controller|open-loop]] configuration
* Demonstrate the CM heat shield [[Ablation|ablator]] at a 200 BTU/ft<sup>2</sup>/sec heat transfer rate
* Demonstrate support facilities for launch, mission control, and recovery

The mission profile called for the Saturn IB to launch the spacecraft on an east-by-southeast heading into a high ballistic trajectory; then the CSM would separate from the SLA. The service module engine would be fired twice, then the command module would re-enter and land in the south Atlantic Ocean.