Automatic and Manual Checkout of the Atlas Space Launch Vehicle Pneumatic System

The monocoque structure and the flight mission requirements of the Atlas space launch vehicle (SLV) has resulted in very stringent pressure and flow control conditions for its pneumatic system. The system characteristics of the Atlas ground and airborne pneumatic system are discussed, with special emphasis on the functional testing of the vehicle and the associated ground support equipment at the launch site. Description of the automatic and manual check-out of the Atlas space launch vehicle pneumatic system is presented, including basic test philosophy and hardware description. Results of system tests and the experience gathered in over five years of operational use are reviewed.