Pitch stabilization system for an ejection seat

Details Pitch stabilization system for an ejection seat Pitch stabilization system for an ejection seat

1991-01-22

1992-07-28

Peters, Jr., Joseph F.

Aeronautics and astronautics

Aircraft structure

Fuselage and body construction

244122A, B64D 25112

Patent

active

051335158

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. Thus, the pitch stabilization system is actuated merely by the seat ejection force rather than by some additional actuation force. The vernier rocket is ignited during ejection as part of the ejection seat sequencing system.

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