Development of the Apollo launch escape system.

This paper outlines the development of the Apollo launch escape system (LES) from the formulation of the basic system requirements through tests. A brief review of previous escape systems is presented to provide a frame of reference for the Apollo effort. The LES requirements are divided into those associated with pad abort, abort in the high dynamic pressure region, and abort at high altitudes where the absence of aerodynamic stability causes escape vehicle tumbling. A description of the major launch escape system elements is given together with a review of system operation. Dynamic analysis of the system characteristics necessitated the development of sophisticated digital computer programs, and an extensive wind-tunnel program was necessary to define the aerodynamic characteristics of the launch escape vehicle over a wide range of Mach numbers.