Abstract: A capsule and rocket extraction system for providing an inflight escape system for the pilot of a damaged aircraft. The system comprises a capsule that is separable from the main fuselage of the aircraft and a rocket for extracting the pilot from the capsule. A control system is carried by the capsule for sensing the capsule's speed, altitude and attitude, and for actuating only the rocket to extract the pilot directly from the capsule when the speed, altitude and attitude are at predetermined conditions, and for sequentially actuating a capsule separation device to separate the capsule from the main fuselage and then actuating the rocket to extract the pilot from the separated capsule when the speed, altitude and attitude are at different predetermined conditions.

Abstract: A hinged container with a releasable closure for receiving a compressed down sleeping bag therein. The container comprises a pair of mating top and bottom members coupled at one end by a hinge; and the closure comprises a pair of bars which are rigidly coupled, respectively, to the top and bottom members and a pair of torsional shear bolts releasably coupling the bars together. These bolts are sheared by pivotal movement of two levers coupled thereto. The apparatus for compressing the sleeping bag into the container comprises an elongated, open-ended sleeve; a hydraulically-actuated compressing ram movable into and out of the sleeve; and an assembly at an end of the sleeve for releasably securing the container to the sleeve with an open end of the container aligned with the open end of the sleeve.

Abstract: An ejection seat is provided with fins on opposite sides which are normally stored along the seat side rails and are deployed immediately after ejection to yaw-stabilize the seat as it is slowed by a drogue. The fins are mounted for rotation and are deployed such that they extend rearwardly and out to the sides.

Abstract: A parachute deployment sequencer includes two sequencer systems in electromagnetic shielding housings. Each housing contains two bellows connected to pitot tubes, a third bellows for measuring ambient pressure and three switch contact sets connected in series, each contact set being operated by one of the bellows. Each housing also contains a battery actuated by seat ejection and a deployment firing circuit with a series switch circuit in between. After ejection, deployment is initiated when all three switches are closed.

Abstract: A pilot limb retention system for an aircraft ejection seat comprising two main straps, two secondary straps and two nets coupled to the seat. The system includes a stowage assembly and a deployment system for the straps and nets. The stowage assembly comprises two compartments in the seat back and two compartments in the seat pan. The deployment system comprises four inflatable bladders, two adjacent the knees of the pilot on opposite sides of the seat pan and two adjacent the shoulders of the pilot on opposite sides of the seat back. These bladders are also stowed in the compartments and are releasably connected to the main straps.

Abstract: An ejection sequencing system used particularly in an ejection seat operation includes continuous sensing of both airspeed and altitude. The continuous airspeed sensing is accomplished by continuously measuring the airstream temperature and then determining the optimum instant for parachute deployment from the measured temperature, thus making the deployment event temperature-responsive. When the sensed airspeed is within a predetermined acceptable limits, a first signal is generated. Continuous altitude sensing is accomplished by an aneroid barometer and when the sensed altitude is within predetermined acceptable limits, a second signal is generated. When these first and second signals are transmitted to the parachute container, they initiate parachute deployment. Redundant, failsafe system operation can be provided through the use of two or more interconnected airspeed sensing devices having fixed time delays for backup.