Abstract: The ejection seat on a high performance aircraft is provided with a plurality of inflatable air bags on the back of the seat. The air bags are generally elliptical in cross-section and arranged one above the other in two parallel vertical rows on a supporting pallet attached to the seat back. Suitable gas generators cause the air bags to inflate in sequence top-to-bottom as the seat ejects from the aircraft to produce a rearwardly extending generally streamline afterbody thereby reducing aerodynamic drag and stabilizing the seat with its occupant after emergency ejection.

Abstract: A collision avoidance system having a seat parachute deployment system secured to the pilot's seat. The seat parachute deployment system has a flap member secured to the survival kit on the side remote from the pilot. The flap member drops down to prevent entanglement of the seat parachute or suspension lines with the pilot's legs. The seat parachute is stowed in an elongated sleeve on the flap and is drawn from the sleeve during seat separation. The suspension lines are stowed in a conventional manner. A connecting line, connected between the suspension lines and seat attachment lines, is stowed in elongated sleeves on the flap.

Abstract: A seat mounted arm restraint net system for restraining a crewman's arms during an ejection sequence wherein a pair of nets, mounted with one on each side of the seat, are deployable by separate static lines passing through snubber boxes to frangible anchorages on the vehicle floor. Each static line is releasably attached to a separate swinging arm rotatably secured to its seat side such that the swinging arms throw the free net sides laterally outwards and then release the nets to close over the crewman's arms.

Abstract: A deployable stowed rotor having a rotor hub to which a pair of telescoping otor blades are connected is foldable into a package suitable for stowage prior to use. When the rotor is deployed, for example, as a lifting device for an ejection seat, positive preconing of the blades is provided by a spreading link arrangement connected to a drogue chute. Further coning during rotor spin-up is synchronized by intermeshed gears provided at respective one ends of the blades attached to the hub by teeter link hinges. Rotor speed is automatically regulated by a governing spring formed in conjunction with a helical spline arrangement between each of the blades and the hub and which varies the pitch of the spinning blades according to rotational velocity.

Abstract: A system for ejection of a crew member from an aircraft is disclosed. In one embodiment a mass is fired from a mortar or similar ejection device and the mass has attached to it a pendant which is resilient. As the pendant reaches the limit of its length as a result of the motion of the mass, the stretch force therein pulls down the seat pan upon which the crew member is resting and a divestment device is actuated. The crew member is then accelerated upward and out of the aircraft. Once the crew member is clear of the aircraft, the pendant's weak link separates just before the peak loading is reached and the action of the pendant initiates deployment of the parachute. The mass and pendant then separate and carry on out of the area of the pilot in a ballistic trajectory. In a second embodiment of the invention, a slipping clutch mechanism is utilized such that as the pendant runs off the clutch spool, and tightens, the pendant spool begins to rotate against the clutch torque feeding out more line.

Abstract: A release mechanism is provided for separating a pendant from a load that operable by an electrical pyrotechnic squib activated by an electrical signal from a remote control station. The pyrotechnic squib is mounted within the yoke connector of a harness fitted to the load. The load is an aircrewman who is to be propelled from a cockpit by a rocket.

Abstract: An improved tow line and attachment apparatus for use with a rocket motor ilized in carrying a line, towing a load or extracting an aircrew member from a disabled aircraft. The tow or pendant line is attached to the rear end of a rocket motor adjacent its nozzles and sustains the load to be carried during powered flight. Flame and heat exiting from the nozzles during powered flight from the burning propellant can impinge a pendant line attached adjacent the nozzles. To prevent weakening or destruction of this portion of the tow line a silicone rubber envelope is fabricated around the line.