Abstract: A first rack is maintained in spatial relationship from a pinion so that the rack may be moved vertically with a pilot's seat, thereby accommodating height adjustments. An actuating handle is connected, via a cable, to a linkage which displaces the rack toward engagement with a pinion gear. A second rack is normally maintained in engagement with the same pinion gear and is driven by it. When the pinion gear is driven by the first rack, the second rack follows and it pulls upon a cable connected at an opposite end to a seat firing head.

Abstract: A pilot's ejection seat is propelled in an upward direction after ejection by employing a high gain signal from a radio altimeter on board an aircraft. The vertically downward high gain vector is inverted by adding 180.degree. to its phase component and providing the resultant signal to an inexpensive gyro or assembly of gyros installed in the seat. The gyros are constantly updated with information concerning the upward vertical direction and upon ejection, the gyros maintain this information for a sufficient period of time to control the ejection seat propulsion system in a manner achieving a vertically upward trajectory that will enable the pilot to clear a disabled aircraft and achieve the orientation necessary to deploy a parachute.

Abstract: A method of effecting the in-flight departure of an astronaut from a shuttle craft, and apparatus therefor. A plurality of rocket assemblies with a lanyard for each are provided, although only one rocket assembly is used for one escape. The astronaut is carried in a parachute harness which is selectively connectible by the astronaut to one of the lanyards. A safety lever is moved when the astronaut pulls the lanyard. An ignition system is subsequently actuated when the lanyard is pulled further by the astronaut. Two rods push their corresponding rocket out through the side hatch of the shuttle craft. When the lanyard grows taut, one means fires the rocket. Subsequently, other means pull the parachute ripcord.

Abstract: A substantially one piece molded shell ejection seat (10) having a rocket motor propulsion system (74), the propulsion system (74) being adapted to be integrated into the molded seat (10) during the molding process. The seat body (12) has upper and lower side walls (14, 16, 20, 22), front wall (60) between the lower side walls (20, 22) and back wall portions (30, 32, 34, 36, 38, 40, 42, 44). A molded backrest panel (50) is removably secured to the body (12) to extend generally between the upper side walls (14, 16). The rocket motor propulsion system (74) is incorporated within the body (12) below the upper side walls (14, 16), within the lower side walls (20, 22), generally rearwardly of and below the backrest panel (50), and generally rearwardly of the occupant sitting area (66). A rocket nozzle (78) is connected to the motor (86) by a manifold (82) and is fitted generally within the lower back seat periphery and seat envelope.

Abstract: Each of two aircraft ejection seats, initially mounted in a side-by-side arrangement in an aircraft, has a primary rocket motor for accelerating the seat/airman combination on ejection, by producing a thrust vector substantially through the center of gravity of the combination, and having a substantial component along that axis of the seat/airman combination about which the combination is rotationally balanced, which lies closest to parallelism with the vertical center line of the airman. To ensure separation, upon ejection, between the two ejection seats, each has, in addition to its primary rocket motor, a lateral thrust rocket motor arranged to produce a transverse thrust vector which passes through said axis at a position spaced from said center of gravity, so as to produce a rotational moment acting on the combination, whereby the two seats are caused to move in respective arcs diverging from one another, but without spinning about said axis.

Abstract: The acceleration applied to an ejection seat during the catapult phase of emergency escape from an aircraft is limited to a maximum value which can be tolerated by the ejectee by incrementally venting exhaust gas from the high pressure chamber of the ejection catapult. Such venting may be accomplished mechanically by a mass which acts in response to acceleration to open venting orifices, the mass being preloaded to prevent its movement until a desired acceleration is experienced. Alternatively, venting may be accomplished electromechanically.

Abstract: An aircraft ejection seat which seeks the upward vertical direction to ene safe ejection from inverted aircraft at low altitude. An attitude control processor processes signals from three-axis attitude sensors and controls servo valves which regulate the flow of hydraulic fluid to hydraulic actuators connected to a spherical rocket motor mounted on a two axis gimbal system.

Abstract: An aircraft ejection seat having pitch, roll, and yaw control. Two gimbal rocket motors are attached to an aircraft ejection seat. A servo control circuit rotates the rocket motors in response to command signals.

Abstract: An attitude reference system which uses microwave radiometry to sense the orientation of a vehicle. A fundamental fact of microwave radiometry is that more natural energy emanates from the earth than from the sky. The difference in energy, which is directly proportional to temperature, can be used to estimate attitudinal position. Microwave antennas mounted on an escape vehicle, such as an aircraft ejection seat, receive energy from different directions in a base plane and from a direction perpendicular to the base plane. Vehicle orientation relative to the earth is discerned by comparing the sensed radiometric temperature received from each antenna direction, and seat guidance equipment is programmed to steer the seat in a predefined direction based upon the radiometrically sensed orientation.

Abstract: An improved rocket catapult is disclosed for use in aircraft ejection systems permitting direct ignition of the rocket motor by a mechanically-actuated igniter situated in proximity to the rocket motor grain and which is actuated when the rocket motor has traveled a predetermined distance during the catapult phase of its operation.

Abstract: A steerable rocket motor for towing a load or extracting an aircrew member rom a disabled aircraft, regardless of aircarft attitude or altitude. The rocket motor is formed from a hollow cylindrical thin walled casing containing a high burn rate propellant and having a plurality of rocket nozzles at one end. The rocket nozzles are positioned around the circumference of the rocket body and are angled to thrust outward and toward the load or aircrew member being towed. A thrust control proportions thrust among the plurality of nozzles for controlling the pitch and yaw of the rocket. Position and rate sensing apparatus informs the thrust control regarding rocket attitude to enable the rocket to steer a predefined desirable flight trafectory. One or more lines are attached to the rocket and are adapted to be fastened to the load or aircrew member being towed.

Abstract: A rocket catapult ejection system for a seat-occupant mass of a disabled craft in which the rocket motor has an annular nozzle throat defined by a spherical pintle and an adjustable nozzle housing. Axial adjustment of the nozzle housing will displace the centroid of the nozzle throat and adjust the rocket thrust vector to compensate for deviations in the occupant-seat mass center of gravity.

Abstract: A rocket powered escape vehicle is equipped with an electrostatic attitude ensing system which commands a rocket motor mounted in gimbals on the bottom of the vehicle to provide a vertically upward seeking escape from an aircraft independent of aircraft attitude.

Abstract: A rocket catapult arrangement having an erector mechanism to move the roc catapult from an out-of-the-way prone position to an upright firing position immediately before launch. When employed as emergency escape means for a seat-occupant mass of a disabled aircraft, the arrangement prior to need for ejection, enables use of available space other than its upright firing position which usually is a sight obstacle for a pilot or an occupant of a rearwardly adjacent seat.

Abstract: A rocket motor assembly for a rocket motor utilized for towing a load or racting an aircrew member from an aircraft. The rocket motor is formed in two separate sections, a casing portion and a unitary nozzle igniter housing portion. The nozzle and igniter housing portion has a circumferential portion that mates with the internal surface wall of the casing portion. A seal and fastener holds the housing in place whenever the rocket motor is assembled. A shackle secured to the igniter mechanism is fastened to a tow line extending to a load to be towed.

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.