Abstract: A device for protection of a spinal column of a pilot during an ejection shock comprises an ejectable seat with a seat back having tensioners integrated therein, a rigid framework and a buttock support. To prevent concentration of the weight of the upper portion of the body on the lumbar/abdominal region, the buttock support is lowered through use of an electromagnetic arrangement retracting connection elements between the seat back and the rigid framework.

Abstract: An automatic vehicle warning and control program is provided for determining if safety enhancing actions are appropriate. The on-line determination of an action that results in a preferred outcome (e.g., aircraft ejection) is made using a neural network controller. The neural network controller is trained off-line using appropriate preferred outcome data obtained via computer simulation or experimentation. Appropriate actions are established for all conceivable sets of vehicle conditions. On-line, the neural network controller uses actual sensed vehicle conditions to determine the appropriate action. Various actions can be performed based on the preferred outcome determination. Appropriate actions can include commanding audible and visual warnings, guidance cues, automatic vehicle control, and aircraft automatic ejection.

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: Seat structure is provided for supporting a person. An inflatable cushion is coupled to the seat structure in a position for bearing at least a part of the force exerted by the person when supported by the seat structure. A source of gas under pressure is provided for inflating the cushion. A control arrangement including a pressure sensor and a valve is coupled to the cushion and to the source for maintaining the pressure of the gas in the cushion at a given level. Also provided is a pressure release mechanism including an outlet and an outlet valve independent of the control arrangement for deflating the cushion to allow the force exerted by the person supported by the seat structure, when high acceleration forces are encountered, to be born primarily by the seat structure. In one embodiment, the pressure release mechanism is a flexible strap for compressing the cushion when the outlet valve is opened for increasing the rate of deflation.

Abstract: An ejection seat firing mechanism has a primary cartridge and a firing pin within a housing. A firing head is outside the housing coaxial with the primary cartridge and the firing pin, and a nut affixes the firing head to the firing pin thereby enclosing the housing. A first bore is formed through the flange of the housing and a second bore is formed in the nut spaced from the housing and aligned with the first bore in spaced parallel relation with the axis. A torquing shaft with an internally threaded axial coupling bore formed therein extends a determined distance into the torquing shaft. A spring is coaxially positioned around the torquing shaft and has a top end abutting the nut and a spaced opposite bottom end biasing the torquing shaft toward the flange. A bolt member extends through the first bore and is threadedly coupled with the torquing shaft via the coupling bore. The bolt provides a visual and sensory indication that the primary cartridge is installed and the firing head is torqued.

Abstract: Threaded shafts engage threaded fittings at the top and bottom of a pilot's ejection seat. A motorized gear train selectively rotates the threaded shafts so as to adjust the fore-aft position of a seat while maintaining it behind a pre-designed emergency ejection path from a cockpit.

Abstract: An improved cockpit area for manned atmospheric or space vehicles includes a generally spherical, multi-axis G-compensating cockpit capsule which houses the crewmen, together with the appropriate operational and navigational instruments and the mechanisms necessary for controlling the vehicle and which is rotatably mounted in the vehicle and is controllable by the crewman to permit the crewman direct visual observation throughout virtually a full circle about the vehicle, without altering the course of the vehicle, together with a device for automatically rotating the capsule to minimize the effect of high G-forces on the crewmen, and an emergency mechanism for ejecting the capsule, with the crewmen therein, and for protecting the crewmen during and after descent and landing of the capsule.

Abstract: A head equipment comprises a component such as a helmet connectable to the head of a wearer and movable by the wearer in a limited field, with at least five degrees of freedom. It comprises an arm constituted by articulated segments giving the component at least five degrees of freedom with respect to the fixed structure and linking the component to a fixed structure.

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: An ejection seat (1), supported on ejection gun guide rails (2) and moveable between an upright position to a reclining position thus affords the pilot greater protection from the effects of high "g" forces. Movement of the seat (1) is effected by hydraulic acutators (3), (4), guided by an arcuate track (15). The invention has the further advantage of allowing ejection from an upright or a reclining position or any intermediate transitional position.

Abstract: A high-performance aircraft seat is disclosed that automatically reacts to ecline the pilot as the aircraft experience higher G's in the vertical direction, or along the pilot's Z-axis. The seat, consisting of a seat pan joined to a seat back, is hingedly fixed, at a point forward of the pilot/seat combination center of gravity, to the surface. An hydraulic cylinder is fixed between the surface, aft of the hinge point, and the seat back and will react to return the seat to its initial position, from a "G-force" induced reclining position, whenever the "G" forces subside.

Abstract: A yaw fin deployment apparatus provides a continuous depolyment force to fin during the entire range of deployment. A shaft, a movable sleeve bearing for riding along the shaft, a strut connected between the sleeve bearing and the fin, and a lanyard for continuously pulling the sleeve bearing along the shaft are provided. The momentum created when the ejection seat separates from the aircraft is transmitted to the lanyard, to the sleeve bearing, and to the strut for deploying the fin. A pulley is attached to the seat and is located near the aft end of the shaft and guides the lanyard to assure that the actuation force exerted on the sleeve bearing is in a direction parallel to the axis of the shaft. When the fin is fully deployed, the lanyard separates from the sleeve bearing through a split ring at the bottom of the sleeve bearing. A primary spring-loaded latch located at the aft end of the shaft locks the fin in a fully deployed position.

Abstract: An improved aircraft ejection seat system is described which embodies a forward leaning position for an occupant of the aircraft providing enhanced acceleration tolerance for an occupant during ejection from the cockpit, comprising a platform supporting at a rearward end thereof a seat having a seat back and seat pan sized and configured for accommodating the occupant, a forwardly disposed cowling integral with and faired to the platform for providing windblast protection to the occupant, a solid or cushioned upright wall member disposed centrally of the platform and extending between the seat and cowling and supporting an inclined chest plate for supporting the chest of the occupant in the forward leaning position, a head rest and a shield disposed near the upper end of the plate for shielding the occupant's head upon ejection from the aircraft, and a restraint harness for holding the occupant in the forward leaning position against the plate upon ejection from the aircraft.

Abstract: A flying emergency ejection seat for endangered airman to escape from distressed aircraft and to fly cross country in the seat to sanctuary of a more favorable environment for recovery having the following existing state-of-the-art non-flying seat survival features of an airman's ejection seat including: a parachute, a rocket/catapult propelled escape seat for ejection, a survival kit for air, land, and water survival equipment, guidance controls on the escape seat and mating guides in the aircraft to direct the path of the seat ejection from the aircraft, seat/man separation device, and added on design features of this invention to make it a flying seat:shall include add-on folding wings for extension in flight to sustain the seat in flight, add-on extendable empennage for extension during ejection to stabilize and guide the direction of flight of the seat in a prone attitude, add-on actuators on the seat bucket to stretch out the airman into a physical prone head down, face forward configuration for minimum

Abstract: A self contained, self powered microprocessor controlled aircraft ejection seat escape parachute deployment sequencer which can handle problems caused by high altitudes into the stratosphere and by high speeds above Mach 1, and which will deploy the parachute, based on seat mounted pitot tube and ambient pressure readings plus stored data, when speed and altitude are at human physiologically acceptable levels. Many failsafes to cope with unusual conditions, and additional features are also included.

Abstract: A G-protective ejection seat assembly for an occupant of the cockpit of an aircraft. The assembly includes a cradle having a rigid, non-articulated upper portion and a rigid lower portion pivotally attached to the upper portion. The upper portion is pivotally attached to the aircraft for selected angular movement within the cockpit between an upright position and a reclined position. The cradle upper portion includes arm rests movable therewith for supporting hand flight controls. Foot flight controls are mounted to the cradle lower portion which is formed by a pair of leg rests. The assembly includes a separable, non-articulated ejection seat removably carried by and stationary with respect to the cradle upper portion during non-ejection use. The seal is moved with the cradle upper portion as the cradle upper portion pivots between the upright and reclined positions.

Abstract: Inner catapult tubes (8) of aircraft (2) are pivotably mounted on the upper rear portion of ejection seat (12). When they separate from outer catapult tubes (4), tubes (8) pivot upwardly and rearwardly to form stabilizing booms (8). A drag device (30,30',30") is stowed inside the outer end of each boom (8) and extends axially outwardly therefrom upon deployment to apply a small drag load to the upper portion of seat (12) and counteract a tendency of seat (12) to pitch forward during operation of stabilization control rockets (18,20). The drag surfaces of devices (30,30',30") are folded around a center shaft (32,32',32") when stowed and extend radially outwardly from shaft (32,32',32") when deployed. The drag device may be a ram air inflatable device (30), a split tube/daisy petal device (30"), or a device having spring steel ribbons (40) forming a tuft-like appendage (30'). Ribbons (40) are wound around shaft (32' ) when stowed and spring radially outwardly from shaft (32') upon deployment.

Abstract: An apparatus for ejecting an aircrewmans helmet-mounted electro-optical equipment from an aircraft cockpit comprising an arm having a first end pivotally mounted at a position behind an aircrewmans ejection seat, a second end of the arm having on it a line reel-in apparatus and a flexible line depending therefrom, the flexible line attachable to helmet mounted electro-optical equipment, a guide and damper connecting the arm to the ejection seat, upon operation of the ejection seat the electro-optical equipment being detached from the helmet, the ejection seat rising in the cockpit and causing rotation of the arm about the pivot point, the line reel-in apparatus locking to prevent the line extending and the electro-optical equipemnt being ejected from the cockpit into the airstream by rotation of the arm prior to the ejection seat leaving the cockpit.

Abstract: A programmable crewmember emergency ejection system is disclosed which will eject the crewmember expeditiously from a disabled aircraft, while at the same time assuring that the crewmember will not be subjected to forces that are beyond crewmember tolerance. This is accomplished by a control system involving sensors having signals that are processed and used to vary ejection thrust and acceleration onset rate. The system involves a two phase ejection: A catapult phase followed by a rocket phase, both phases cooperating to provide a substantially constant maximum thrust that is well within human tolerances such that a second jolt to the crewmember is substantially minimized.

Abstract: An ejection seat (10) having roll thrusters (38, 40, 112, 114) and propellant chambers in the inner catapult tubes (44, 46, 124, 126). The roll thrusters (38, 40, 112, 114) are adapted to roll the seat (10), when ejected from an inverted or unsatisfactory attitude to an upright proper attitude. Solid propellants (44, 46, 128, 130) within the inner catapult tubes are to be ignited after the seat is being ejected. There is a roll thruster valve housing (36, 110) connected to both roll thruster nozzles (38, 40, 112, 114) and to both inner catapult tubes (24, 26, 124, 126) so that propellant gas may flow from both catapult tubes to both nozzles. The check valve (52) in each inner catapult is operable to open during ejection by ejection gas and is operable to close by the roll thruster gas when the roll thruster propellants are ignited. The check valve system modulates the catapult gas pressure during ejection, prior to roll thruster propellant ignition.

Abstract: Apparatus for adjustably mounting an ejection seat (16) in an aircraft in which outer catapult cylinders (58, 60) support inner catapult cylinders (62, 64) and supply force to the inner cylinders to eject the inner cylinders and the seat from the aircraft, the inner cylinders being connected to an upper rear end of the seat (66, 68). The seat (16) is supported in the aircraft by the inner and outer catapult cylinders (62, 64, 58, 60), by adjusting actuators (40) to raise and lower and to tilt the seat forwardly and rearwardly, by lower anchor links (30) pivotally connected to the aircraft and to lower end (26, 28) of the outer catapult cylinders and to the actuators (40), and by upper links (50). The seat is connected to the catapult cylinders (58, 60) by slipper blocks 82. The slipper blocks (82) are pivotally connected to the seat by pins (84) and are slidably engaged with the outer catapult cylinders.

Abstract: A pilot arm retention system for an aircraft ejection seat which includes ertia reels and a parachute is comprised of a pair of nets connected between respective sides of the seat and a pair of deployment straps which are releasably coupled to the inertia reel straps and parachute risers and routed down over the front of the seat through a pair of snubbers to fixed points on the cockpit floor.

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: The invention is a system for ingressing and egressing a crew member from the flight station of an aircraft. A passageway is provided having a first end coupled to the flight station and a second end terminating at the underside of the aircraft. A crew seat assembly is movably mounted in the aircraft, movable from a first position within the flight station, for example, at the pilot's controls in a single-seater fighter aircraft, to a second position located such that the crew member can gain access to the crew seat assembly from the ground. This second position is typically at least partially out of the aircraft and, preferably, completely out. A positioning mechanism is mounted within the aircraft for moving the crew seat assembly from the first position to the second position. A door is provided at the second end of the passageway for sealing off the passageway from the exterior of the aircraft.

Abstract: An emergency oxygen system for use on aircraft in conjunction with an on-board primary oxygen supply system is designed to supply oxygen to aircraft personnel in the event that the on-board oxygen supply system fails. Additionally, if the aircraft personnel is forced to eject from the aircraft, the emergency oxygen system automatically activates to provide oxygen and simultaneously disengages all electrical connections from the aircraft frame. The system includes an emergency oxygen supply which is coupled to a differential pressure activated valve through an oxygen release valve, the oxygen release valve having the capability of being manually or automatically triggered.

Abstract: Apparatus and method for repositioning an aircraft ejection seat (10) during an ejection sequence from a semi-reclined position (FIG. 1) to a more upright position (FIG. 2) for safer ejection. The seat (10) is supported in the aircraft by inner catapult cylinders (18, 20) slidably engaged in outer catapult cylinders (14, 16), collapsible truss links (54, 56), connected to the seat at one end and having their other ends connected to slipper blocks (68) slidably engaged on the outer catapults (14, 16). The collapsible truss links hold the seat away from the lower ends of the catapults and firmly in a semi-reclined position during normal operation. There are triangular trusses comprised of seat structure (10), the catapults (14, 16, 18, 20), stops (70) on lower ends of the outer catapult cylinders (14, 16) and the compression links (56). The slipper block (68) are restrained by the down stops (70) and the compression links (56).

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: An aircraft ejection seat is provided with deployable fins for stabilizing aw rotation. The fins are normally stowed along the sides of the ejection seat. During ejection, the fins are deployed aft of the seat by means of rotational actuators. Anti-entanglement sheets are collapsibly disposed between the fins and the sides of the seat in order to prevent fouling of the parachute.

Abstract: A self-deploying afterbody apparatus for an ejection seat of an aircraft includes a cover plate, a plurality of arcuate-shaped stiffeners and a fabric skin of material. The cover plate is pivotally mounted at one end to the back side of the ejection seat and the stiffeners are pivotally mounted at their bases to the back side of the seat and share a common pivotal axis with the cover plate. The stiffeners are located between the cover plate and seat, and the fabric skin extends between the cover plate and seat and covers the stiffeners so as to form an expandible and collapsible bellows-like afterbody structure. In the collapsed position, the afterbody structure is folded up and locked against the back of the seat. When the seat ejects, a lanyard attached between the cover plate and aircraft floor pulls the afterbody structure into an expended, operative position. When the afterbody structure is fully extended, the continued ejection of the seat causes the lanyard to detach from the floor or cover plate.

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 yaw stabilization system for an aircraft ejection seat having a vane for sensing the angular offset of the yaw air flow velocity vector and for extending paddles into the air stream in response to the velocity vector offset. The extended paddle is acted upon by the air stream to provide a restoring moment around the center of gravity of the seat and occupant to return the seat to the desired attitude with respect to the air flow velocity vector.

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: The device retains the ejection seat arm/dearm lever in safe position to allow the seat to be tilted safely for required maintenance and repair work. A bolt positioned through a clearance hole in an inverted U-shaped base member engages threads in the ejection seat structure. An upstanding brace extends upward from one end of the base member at an angle to abut the seat ejection arming lever to physically block and prevent its movement into the armed position. The bolt is retained in the base member by a cotter pin through the body of the bolt under the head to allow turning while preventing separation from the base.

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 reclining or semi-supine aircrew ejection seat is provided with an ejection gun that is in the usual upwardly extending and rearwardly inclined attitude, and the seat is attached to the portion of the gun assembly that leaves the aircraft by a pivotal connection between the back of the seat and the upper part of the gun assembly portion. This allows the part of the seat that supports the user's back to extend forward away from the pivotal connection and the gun assembly. During the initial phase of ejection, the seat turns angularly, bringing the part of the seat that supports the user's back against the gun assembly.

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: 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 dual-motion firing device having both its firing and its arming mechani internal to its tubular housing. A tubular sear is enclosed by the housing and, in turn, encloses an arming rod, both sear and rod extending out of the housing. A tubular firing pin capped and nippled on its forward end encloses the front end of the sear. Pushing the arming rod forward releases a ball which restrains the sear from rearward movement. Then, pulling the sear backward releases another ball which prevents forward motion of the firing pin and a spring propels the latter forward sharply.

Abstract: A supinating seat for aircraft cockpit which is articulated to improve pilot physiological and cognitive capability in high acceleration maneuvers of the aircraft, and which seat does not interfere with rapid ejection or displacement of the controls from pilot convenience of operation, or interfere with a full view of the instrument display.

Abstract: A high acceleration cockpit-ejection seat having an air bladder-liner element acting as a cushion/pad and inflatable to effectively provide a significant backward tilt to, and thus greatly increase the pilot's tolerance to the high g-loads associated with fighter aircraft maneuvering at high speeds.

Abstract: A harness mounted arm restraint system for the occupant of an aircraft ejion seat to prevent the arms from flailing and being injured during ejection. Harness-mounted ribbons with slidable rings on them are hooked to snubber lines. The snubber lines are secured to the airframe of the aircraft so that when the seat ejects, the snubber lines pull the ribbons tightly around the upper arms and forearms of the seated occupant. The snubber lines then break away from the frame but the lines and ribbons are kept taut by a snubber block on the seat. The snubber lines are cut when seat and occupant separate.