MIL-P-83126A

Abstract

This specification establishes the minimum requirements for the design, development/adaptation, design verification, and service release criteria for Aircrew Escape Propulsion Systems (AEPS) and testing of units manufactured for Aircrew Escape System (AES) system and subsystem tests. <b><u>Intended Use:</u></b> The AEPS is composed of a variety of propellant actuated devices that when sequentially activated provides for aircrew safety during an emergency egress. Units such as catapults or the catapult phase of a rocket catapult will propel the ejection seat and its occupant out of the aircraft. Units such as under seat or seat back rocket motors or the rocket phase of a rocket catapult will propel the ejection seat and occupant safely away from the aircraft. Other rocket motors provide reactive impulse for seat subsystems such as man seat separation, seat rotational control, or parachute deployment. The system will propel the occupant of the seat at a sufficient velocity to ensure that he will clear a fast moving aircraft by a safe margin and attain a height required to permit parachute deployment and a normal descent. <br>