Abstract: A pitch stabilization system for an ejection seat includes a gyroscope rotor assembly having a pinion gear attached to two rotor wheels. The rotor assembly is mounted with a geometry to precess in response to change in the pitch rate of the seat. Precession of the gyro rotor rotates a vernier rocket with the resulting thrust applying a correcting moment to counter the adverse moment causing the ejection seat to pitch. When the seat is at rest in the cockpit of the aircraft, the rotor pinion gear teeth engage the teeth of a rack mounted stationarily to a fixed attach point on the aircraft. When an ejection force is applied to the seat, by a catapult or the like, the rotor wheel is rotated by virtue of the interengaging relationship between the rotor pinion gear teeth and the rack teeth so that by the time the ejection seat exits the cockpit the rotor disengages from the upper end of the rack, and is fully spun to operating revolution so that it can precess gyroscopically.

Abstract: A parachute ring release mechanism with a spring incorporated to insure disengagement of the parachute risers. The ring release is structured such that the parachute risers may be released by either one of two rip cords.