Design of the Apollo Service Module Rocket Engine for Manned Operation

Abstract

The Apollo spacecraft service module engine utilizes a liquid rocket engine generating 20000 lb of thrust. Presented is a summary of the techniques employed to ensure maximum pilot safety. Man-rating techniques described include extensive use of redundancy on critical moving parts and the use of unusual design margins on other parts. Particular emphasis is placed on the redundancy developed for the bi-propellant valve and the gimbal actuators.