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 powered canopy breaker attached to an ejection seat, that fractures a canopy when the seat is ejected. The breaker has a piston that is operatively connected to an explosive cartridge. When the seat is ejected, the piston engages the canopy, pushing the piston a predetermined distance until the cartridge is detonated. The detonated cartridge ignites a detonating cord that fractures the canopy.

Abstract: A powered canopy breaker attached to an ejection seat, that fractures a canopy when the seat is ejected. The breaker has a piston that is operatively connected to an explosive cartridge. When the seat is ejected, the piston engages the canopy, pushing the piston a predetermined distance until the cartridge is detonated. The detonated cartridge thrusts the piston back, fracturing the canopy.

Abstract: A powered articulated headrest system for use with a seat structure having a backrest, such as the ejection seat of a high performance aircraft, e.g., a combat aircraft. The headrest system includes: a headrest assembly which is movably connected to the backrest; and, an electro-hydraulic actuator assembly for moving the headrest from an original (and normal) position above the backrest to any one of an infinite variety of positions which are rearward and downward of the headrest, and for moving the headrest from these other positions to the original position. The actuator assembly is controlled by the occupant of the seat, e.g., the pilot of the aircraft.