Abstract: A portable, temporarily installable and removable safety seat for the carriage of an infant or small child aboard an aircraft includes securing anchors which cooperate with the standard seat or cargo tiedown tracks of most passenger aircraft. The anchors permit the safety seat to be secured directly to the floor of the aircraft in the same manner as other standard seats or other articles. The safety seat may be made foldable or so the back may be removed from the bottom for more compact storage, and may be constructed of relatively sturdy but lightweight materials such as aircraft grade steel tubing or aluminum tubing. Preferably, all of the materials used in the safety seat will meet or exceed the appropriate standards for fire resistance.

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 quick setting and releasing system for installing and removing fixtures in a longitudinal track comprises a bottom track having an inverted, T-shaped, longitudinal channel and a fixture track having a T-shaped, longitudinal channel. The actuating and locking mechanisms comprise a pair of wing shaped lugs which float on and pivot around a longitudinal pin to lock the lugs in the fixture channel when upward pressure is applied to the pin and in the bottom track when downward pressure is applied to the pin.

Abstract: A seat belt for a pilot seat or flight attendant seat in an aircraft includes a belt tightener with a reversible energy storage member in the form of a helical compression spring and a rod-shaped energy converter coupled to the energy storage member. The energy converter is at least indirectly connected to a belt member of the seat belt. After the belt member has been tightened and the energy converter has been displaced as a result with an at least partial regeneration of the energy storage member, a cutting chisel penetrates the surface of the energy converter and dampens the movement of the belt member. A renewed activation of the energy storage member after the deceleration phase is prevented by the penetration of a clamping edge of a clamping member in the surface of the energy converter.

Abstract: A main seat support frame includes slidable seat sections to allow the overall length of the seat and the number of sitting positions to be varied as required. The frame is provided with fixing positions for arm dividers which allow delimitation of a predetermined number of sitting positions when the seat is fully expanded corresponding to an economy class configuration and a fewer number of sitting positions of greater sitting width when the seat is contracted corresponding to a business class configuration. Since the width of the seat backs remains constant, bolsters may be attached to them when the seat is contracted for business class usage allowing for rapid conversion of the seating arrangement as between economy and business class usage.

Abstract: An aircraft seat assembly (14) is convertible between three seats (LA, LM, LW) with a first seat width and two seats (LA, W) with a second wider seat width. The seat assembly includes a tube-in-tube support frame for the seats which allows the conversion to be accomplished by a simple sliding movement of the aisle and middle seat frames towards and away from the window seat frame which is fixed in position. Movement of the aisle and middle seat frames automatically changes the position of the two inside armrests (22, 24). The middle seat back frame (66) is vertically split into parts (66A, 66B). Movement of the seat frames from the three-seat configuration to the two-seat configuration disconnects seat back parts (66A, 66B) from each other and locks one part (66A) to the window seat back frame (64) and the other part (66B) to the aisle seat back frame (68).

Abstract: A track fastener apparatus for use with a locking track of the type used to secure a seat or cargo apparatus to the floor of an aircraft. The track includes a slot, and the upper walls of the slot have regularly spaced-apart enlarged openings separated by relatively narrower track slot segments defining locking segments. The track also includes a channel for carrying wiring along the length of the aircraft. The track fastener apparatus includes a housing. A screw member cooperates with the track fastener housing and the locking wedge to perform first and second functions in distinct first and second locking wedge positions. In the case of the first position the locking wedge is not completely positioned in alignment with and into the one enlarged opening, preventing the locking wedge from being tightened into the track. In the case of the second position the locking wedge is positioned in alignment with and into the enlarged opening, permitting the locking wedge to be tightened into the track.

Abstract: Presentation of an adjustable lumbar support mechanism for use in the airline aircraft seats. A new method of lumbar adjustment is introduced utilizing a push button (10) and control cable (12) to unlock the positioning rod (42). Rod holds any selected curvature of the lumbar support panel (46). The lumbar panel is formed and preloaded to a convex shape (50) and assumes the most forward adjustment position when control button is depressed and while pressure on the seat back is removed. The lumbar panel is flexible to assume any intermediate curvature when control button is depressed and when the passenger lightly pushes back against the seat back in the lumbar region. The new lumbar system is a fast acting device compared to traditional knob driven units and permits a frequent, quick and easy readjustment of lumbar position whenever said push button is depressed.

Abstract: A track fastener apparatus for use with a locking track of the type used to secure a seat or cargo apparatus to the floor of a vehicle. The track includes a slot, and the upper walls of the slot have regularly spaced-apart enlarged openings separated by relatively narrower track slot segments defining locking segments. The track fastener apparatus includes a housing. The track fastener housing has a top side and a bottom side with first and second spaced-apart locking studs on the bottom side, the spacing of the locking studs being the same as the spacing of the spaced-apart enlarged openings in the track for being positioned into the enlarged openings. A locking wedge is extended through one enlarged opening in the slot when the locking studs are shifted along the length of the track to adjacent, relatively narrow locking segments, and tightened into the slot to prevent movement of the track fastener apparatus in the track.

Abstract: The seat comprises panels made of ceramic matrix composite and assembled to one another by shape and by adhesion, either by interposition of an adhesive or else by condensification using the ceramic matrix material. The invention is particularly suitable for armored seats for helicopters.

Abstract: A front leg (1) is formed by an upright support rod extending vertically above a fixing stud (8), a rear leg (2) is formed by both a lower support rod (2a) extending on a diagonal line joining the upper end of the front leg and the lower end of the rear leg and an upper support rod (2b) contiguous to the lower support rod (2a) in an upper position relative to the lower support rod, the upper support rod (2b) being curved arcuately and inclined rearwardly upwards, and an energy absorber (12) is mounted bridgewise as a diagonal member between the upper end portion of the front leg and the lower end portion of the rear leg, to constitute a leg structure. Accordingly to this leg structure, a striking energy is absorbed by an anti-plastic deformation force induced when the rear leg (2) and the energy absorber (12) is deformed plastically under an impact larger than a predetermined value, and the seat is held at its supported posture in normal use.

Abstract: A reclining ejection seat (1) for an aircraft which includes an arm support (7) composed of two parts (8,10) which are moveable fore and aft. A first part (8) carries flying controls (9) and is adjustable for reach. A second part (10) which is adjustable for comfort, locates the elbow of a pilot (11) and supports his forearm. The arm support (7) permits the pilot (11) to maintain adequate control over his arm movements even when the aircraft is carrying out very high speed maneuvers.

Abstract: An aircraft seat assembly (12) is convertible between a first, narrower configuration of three seats (RA, RN, RW) and a second, widened seat configuration which adds an even increase in space between armrests (18, 22, 24). A seat assembly (12) includes a tube-in-tube support frame for the seats which allows the conversion to be accomplished by a simple sliding movement of the aisle and middle seat frames (RA, RM) toward and away from the window seat frame (RW) which is fixed in position. Movement of the aisle and middle seat frames (RA, RM) automatically centers the middle seat frame (RM) between the aisle and window seat frames (RA, RW) and automatically changes the position of the two inside armrests (22, 24) to provide even spacing therebetween. A lock mechanism (124, 130) locks the seat frame parts together, both in the first, narrower configuration and in the second, widened configuration.

Abstract: An energy attenuating seat for a vehicle includes a seat member having a seat back and a seat pan. The seat pan includes a front and rear portion. The seat back is rigidly attached to a rigid seat structure or directly to the vehicle. Support structure is provided which is rigidly attached to the vehicle and which is disposed adjacent to the front portion of the seat pan for supporting the seat pan front portion. Structure is provided for hingedly interconnecting the seat pan front portion and the support structure, such that the seat pan rotates about this interconnection. An energy attenuator is interconnected between the seat back and the rear portion of the seat pan, such that vertical load forces experienced by an occupant of the vehicle during a crash causes the seat pan to pivot downwardly whereby the rear portion of the seat pan is disposed closer to the vehicle floor than the seat pan front portion. A vertical height adjustment is provided by allowing the seat to pivot upward and downward.

Abstract: Two seat assemblies are provided side-by-side, in a row, on opposite sides of an aisle (16). A first seat assembly comprises window, middle and aisle seats (RW, RM, RA) which are movable between a first narrow seat spacing and a second wider seat spacing (FIGS. 7 and 8). The second seat assembly is convertible between three seats (LA, LM, LW) with the first spacing and two seats with the larger spacing (FIGS. 7 and 8). Each seat assembly includes a tube-in-tube support frame for the seats which allows the conversion and seat size to be accomplished by a simple sliding of movement of the aisle and middle seat frames towards and away from the window seat frame which is fixed in position (FIGS. 9 and 10).

Abstract: Disclosed is a track fitting for an airplane seat leg which has a unitary bearing section and wall element that carries the pin holding the seat leg in position. The bearing section comprises an opening defined by two truncated conical walls with the abutting truncated sections providing a bearing site. The open ends of the opening are surrounded by segmented spherical bearing surfaces which carry caps having conforming internal, spherical bearing surfaces. The pin passes through the assembly of caps and bearing section to secure the leg in position. A plastic, box-like anti-rattle device to prevent rattling is mounted to the rear of the track fitting and bears against the top of a track receiving the fitting.

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: An improved anchor fitting assembly that provides a connecting seat leg member with a degree of freedom of movement thereby allowing for greater load carrying capability. The anchor fitting includes a substantially spherically shaped housing with a bolt-receiving channel therethrough that rotatably engages a bolting member. Also, the anchor fitting is cast as a single-body which makes it relatively simple and economical to construct.

Abstract: A restraint system is provided for restraining a pilot in a safe position during high-acceleration conditions. A stationary harness portion is attached to the pilot's body and haulback straps are connected in a slidable manner to the stationary harness. Under normal conditions, the pilot has some freedom of movement to lean forward or move from side to side. In the event of high acceleration or other emergency conditions, a pair of haulback straps that are slidably attached at the mid-torso position of the pilot are retracted to bring the entire back of the pilot against the back support of his seat. Lateral support pads positioned at the back and side of the pilot are moved to provide support to the sides, ribs and lumbar regions of the mid-torso and to restrain side-to-side movement of the pilot. The position of the lateral support pads is automatically adjusted according to the size of the pilot.

Abstract: An apparatus for supporting the head of a crew member sitting in a forward posture in a vehicle during high "G" accelerations is disclosed. The invention comprises an upper torso assembly secured to the crew member's upper torso and a head support member. The head support member is hingedly connected to the upper torso assembly for preventing the crew member's head from rotating forward when sitting in a forward lean posture during high G accelerations. The apparatus thereby maintains the proper head position for viewing aircraft displays and viewing the vehicle's external environment. The head support member further allows for free head mobility when the crew member is in the normal upright sitting position.

Abstract: A modular work station particularly suited for aircraft slidably mounts computer work station seats. The seats and work stations may be oriented in a modular manner with the seat orientation being directed toward the fore or aft ends of an aircraft to enhance operator comfort during long periods of flight. The seats are provided with a swivel capability of at least 180.degree. to enable ingress into a walkway. During landing and take-off, the operator seat has the capability of being latched in a forward- or rearward-facing position to enhance operator safety during these conditions. The seat is slidably mounted along a track that has rear curved portions that allow a seat to slide back to an angular orientation to facilitate an operator's ingress or egress.

Abstract: Safety enclosures for use in high speed vehicles such as aircraft and high speed trains. The safety enclosures include an enclosure shell which preferably has two shell walls separated by a crash resistant intermediate material which also provides thermal insulation against fires and acoustic attenuation. The enclosures also advantageously include cooling systems which utilize a refrigerant which is expanded through tubes connected along the inner wall of the enclosure shell. A compressed air supply is provided which supplies breathing air to passengers and is used to expand a crash bag. Air is supplied through both the crash bag at passenger contacting panels and through supply lines which exhaust near the passengers' heads. A motor driven door assembly is controlled to close as the crash bag is being deployed. Exhaust ports having check valves allow positive pressure to be maintained in the cabin of the enclosures to exclude smoke and fire.

Abstract: A lightweight energy attenuating seat for a vehicle comprising apparatus for seating and integral impact energy dissipation and stroke guide apparatus including support apparatus for the apparatus for seating for absorbing impact energy that would otherwise be transferred thereto by permitting a regulated stroke thereof in a direction determined by the dissipation and stroke guide apparatus substantially parallel to a component of a force experienced by the integral apparatus.

Abstract: In a pivotable seat especially for a flight attendant in an aircraft, the backrest and the seat part are constructed to be pivotable together about an approximately vertical axis when the seat part is pivoted about an approximately horizontal axis into an upright position. The seat is secured to a carrying structure of the aircraft. The seat plate (25) and the backrest carrier plate (27) are milled parts. A spring is activated by tilting the seat part (2) into an upright position, whereby the seat 1 is biased into a recess (15) for storage. For pivoting the seat out of the use position into the recess (15) during non-use, only the locking of the seat part must be released and the seat part tilts itself into the vertical position, whereby the mentioned spring is activated for pivoting the seat into the recess (15) and locking it automatically in the recess.

Abstract: A harness and belt assembly for a crewmember of an aircraft including left and right slings, a first belt assembly having first end second ends, a survival kit strap assembly attachment fitting which slidably engages the belt assembly, and a mechanism for releasably attaching the fitting to a seat of an aircraft. The slings are designed to extend from the chest of the crewmember, over the crewmember's shoulders, to the back of the crewmember. The first end of the belt assembly is attached to one of the slings at the portion designed to be adjacent the crewmember's chest. The second end of the belt assembly is attached to the other of the slings. A survival kit belt can be affixed to the fitting so that the survival kit ejects with the crewmember during an ejection.

Abstract: A seat insert insertable within the existing seat of a vehicle for maintaining a crew member of the vehicle in a forward posture during high G acceleration. An elongated head support member is provided for supporting the crew member's head during a forward leaning posture. A back plate assembly including at least one back plate is connected to the head support member for supporting the spine in its natural curvature. Means being connected to the back plate assembly are provided for pivoting the back plate assembly forward relative to the seat of the vehicle. Means are provided for transfering any G-induced weight from the spine to the back plate assembly and ultimately to the existing seat of the vehicle. The head support member is restrained in such a manner so as to maintain the crew member's head in an "eyes up" attitude during a forward lean.

Abstract: A leg assembly with special floor attachment fittings for mounting passenger seats in transport aircraft is disclosed as being especially configured to absorb energy resulting from a survivable crash or other cause of sudden deceleration, for increased passenger safety. The leg assembly includes a special base member having improved load distribution characteristics and legs which are attached to the base member and the seat in a way which allows the seat and legs to move to a forwardly stroked position in the event of inertial loading in excess of the value required to operate an energy absorbing mechanism that is provided on the leg assembly. The special floor attachment fittings are configured to absorb forces applied in various directions to minimize fitting failures and the changes of the seat being torn loose from the floor.

Abstract: An electro ballistic escape sequencing system is actuated only by the seat initiators. Current entering the system by any other means will see only open circuits. A pressure sensitive switch is provided in each circuit subject to outside interference and is normally in the open position. When ejection is required, pressure from one of the seat initiators activates the thermal battery and closes all circuits required for ejection.

Abstract: Fire-resistant seating, in particular aircraft seats, which consist of at least a soft, supporting material and a cover, between which there is a fire-resistant intermediate layer, which is a combustion of a layer of fiberglass fabric, which is firmly attached to the soft supporting material, and a layer of polyurethane foam, which has been rendered fire-resistant and is firmly attached both to the layer of fiberglass fabric and to the cover.

Abstract: An ejection seat includes a rigid shell adapted to closely surround the head of a pilot during ejection to restrain lateral movement of the pilot's head. The pilot's head is supported within the shell during ejection at a position that causes it to be aligned with the pilot's spinal column. During normal flight conditions, the pilot's head is supported in a forwardly pivoted position by a front panel. In this forwardly pivoted position, the pilot's head is free to move about to check for other aircraft. In one embodiment, the front panel slides rearwardly into the shell during ejection. In another embodiment, the front panel is divided into two sections, each of which pivots inwardly into the shell during ejection.

Abstract: A structure which resists dynamic forces, forming a mounting for a seat of an air transport craft and a seat having such a structure comprising front and rear feet, a front anchorage, an energy absorption device, and a stop mechanism. The front and rear feet are articulated at their upper ends on the seat framework, so that each can pivot about a horizontal and transverse pivot axle. The front anchorage comprises a joint having a traverse horizontal pivot axle, which allows the front foot to pivot forwards from its normal position about the joint pivot axle. The energy absorption device extends between the lower front anchorage and the upper part of the rear foot, but at a distance from the upper rear joint. The energy absorption device includes a stop mechanism for preventing the forward pivoting of the rear foot about its lower rear anchorage on the fixed structure of the craft.

Abstract: An adjustable seating system for a vehicle, particularly an aircraft, providing means for readily adapting the seating layout in an aircraft cabin to vary passenger density where a plurality of seating units are mounted upon a pair of longitudinal seat rails. Each seating unit incorporates a seat adjustment and locking system comprising a pair of interconnected sprocket wheels arranged to be in driving engagement with a related one of the seat rails so that the seating units can be moved to selected locations without physical separation from the track. Sprocket locking means, when engaged, restrains the seat against horizontal movement and reacts induced fore and aft flight loads obviating the need for separate seat rail engaging restraint means.

Abstract: A vehicle seat, especially for attendants in an aircraft is constructed as a double seat. The seat is equipped with seat cushions on opposite sides of a frame made of two posts interconnected by a cross-member. The seats are preferably hinged to opposite frame sides so that one or the other or both seats can be used.

Abstract: Disclosed is a leg seat track fitting used to removably secure the leg of an airplane seat to the floor of the fuselage. The fitting has a body member, including a wall element from which a series of pairs of tabs project outwardly. These tabs engage the track in which the fitting is carried. A pivotable detent element attached to one end of the wall element secures the fitting in position when depressed. A yoke element mounted at another end of the wall is moved towards and away from the body member by a spring loaded screw. This yoke includes a pair of plungers which straddle the wall and engage the floor of the track when the yoke is moved toward the body member. The detent element and plungers resist sliding movement of the fitting in its track. To absorb energy when torque is exerted on the seat, a spherical bearing carries a pin which passes through this bearing member and attaches to the leg of the seat.

Abstract: In a backrest cushion of polyurethane foam in flame-retardant finish for air passenger seats, the protection against the risk of fire spreading is increased and at the same time the weight is reduced and the comfort increased according to the invention by making the whole volume of the backrest cushion of a flame-retardant foam and providing it, at least in the region which is put under pressure in use, with recesses extending parallel to the direction of pressure and all ending equidistant from the surface of the cushion.

Abstract: An improved aircraft seat is equipped with a special flexible lumbar panel to better and more comfortably support the back of the passenger seated in the aircraft seat. The flexible lumbar panel can be used with different type of reclining chairs but is especially useful with high hinge point aircraft seats. The lumbar panel has a moveable lower end which can be guided by guide members. The upper end of the lumbar panel can be secured to a torque bar.

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: The specification discloses a passive restraint system for high speed vehicles utilizing inflatable bags placed in the backs of the seats of the vehicle. The bags are connected by headers to a manifold which communicates with the exterior of the vehicle and, when open, allows air at high speed to enter and inflate the bags. A relief valve is provided in the cabin to open moments before the bags inflate to remove any danger of pressure shock from the rapid inflation of the bags and to, in some cases, aid in the inflation thereof. In some applications, an optional compressed air and/or compressed gas supply is also disclosed.

Abstract: This invention relates to a cockpit comprising a seat with armrest, as well as a mechanical control member of the control stick type adapted to be actuated by one hand and mounted at a fixed location in said cockpit at least substantially in forward extension of an armrest of said seat, the position of said seat being adjustable with respect to said mechanical control member. According to the invention, at least a part of said armrest is articulated about a transverse pin connected to said seat, in order to be able to occupy a plurality of fixed positions of different inclinations about said pin, converging towards said mechanical control member and adjustable thanks to control means. The invention is more particularly applicable to the piloting of aircraft.

Abstract: A textile fabric suitable for use as a fire-blocking sheet in aircraft seat cushion comprises three to seven, fastened together nonwoven layers of hydarulically needled batts of aramid staple fibers.

Abstract: Seat with protecting shell, fastened to a floor contained inside two hinged hollow hemispheres, suitable to close onto each other, provided with a back constituted by articulated segments. The seat is furthermore equipped with safety devices housed within special hollows provided inside the same shell.

Abstract: An airline passenger seat with flame-retarding properties with seat and back-rest upholstery consisting of polyurethane foam which is provided with a flame-retarding surface and is covered by a covering material with flame-retarding properties. A polyurethane foam film is arranged between the seat and back-rest upholstery and the covering material, at least on the surface not covered by the seat frame parts, and the surface of the film is connected to the upholstery.

Abstract: Improved energy absorbing seat frame structure for an aircraft seat has leg structures which comprise a pair of generally U-shaped front and rear legs which are joined back to back in a generally X-shaped configuration. A curved die member is held in contact with the forward facing concave portion of the front leg by a strap member which surrounds the rear leg. In a crash situation, the front leg can bend about the die member to lower the center of gravity. In a preferred embodiment, strap type clamps on the upper ends of each leg permit the legs to rotate relative to the tubular stretcher members of the seat. The ability of the front legs to be deformed downwardly permits a portion of the excess loading on one front leg to be transferred through the front stretcher member to the other leg which is less heavily loaded.

Abstract: A bottom cushion for use in a seat of the type used in situations where an occupant could be subjected to spine damaging injury resulting from rapid vertical acceleration or deceleration. The seat cushion includes a frame mounted above the rigid seat pan of the seat with an air-permeable, flexible membrane suspendingly carried in the frame. The seat cushion is provided with a membrane adjusting mechanism by which an occupant applies tension to the membrane to lift his or her posterior above the seat pan for comfort reasons, and has a vertical displacement limiting mechanism which for safety reasons prevents the occupant from lifting the membrane and his or her posterior an excessive distance above the set pan.

Abstract: There is disclosed auxiliary airplane seats which include a containment unit or housing having located therein a vertically movable seat back member provided on each side with a linkage including a guide pin which is guided in a guide located on the back panel of the containment unit. A seat bottom member provided on each side with a member having a slot which forms a track and which is movable vertically and horizontally is also disposed in the containment unit. The seat bottom member is guided on pins located on the side panels of the containment unit or housing and which pins are disposed in the slots of the members provided on the sides of the seat bottom of the track is also disposed in the containment unit. The vertical movement of the back member and vertical and horizontal movement of the seat bottom member may be assisted by a ring reel provided with a cable attached to the back member and to the ring reel.

Abstract: There is disclosed double airplane seats disposed in a side-by-side, inboard and outboard relationship with respect to their disposition in an airplane fuselage. The seats have a common base member provided with a pair of tracks on the bottom thereof which cooperate with a pair of tracks located on the floor of an airplane fuselage and which moves in a fore and aft direction. Fore and aft tracking is located on the top of the outboard portion of the base member and an opening is located in the top inboard portion thereof with a clutch located therein adapted to move universally in fore, aft and lateral directions.

Abstract: In the operation of modern tactical aircraft, crew members are subjected to periodic high acceleration loads that cause fatigue and a decrease in operating capacity. Restraining the torso of a crew member and pulling the crew member back against the ejection seat (2) of the aircraft would help prevent such fatigue. Known restraint and haul back apparatus for use during ejection are not adapted for repeated in flight use. The invention provides a single mechanism that retracts torso restraint straps (6) any number of times during in flight maneuvering and also retracts straps (6) for ejection. A loop (7) of each strap (6) extends around an inflatable member (28). When in flight acceleration loads exceed a preset limit, engine bleed air inflates member (28) to expand loops (7). This retracts straps (6) and positions the crew member. Member (28) is allowed to deflate when the acceleration subsides. When the ejection procedure is initiated, a gas generator (44) inflates member (28).

Abstract: A crashworthy helicopter cockpit having a pyrotechnic system actuated by a stroking pilot seat for repositioning the upper portion of the cyclic control stick upon a severe or crash landing that is independent of aircraft electric and hydraulic systems.

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.