Abstract: An actuator/sensor responsive to concentration of a substance in a liquid comprising a case containing in a rigid chamber a liquid of lesser concentration of that substance, and an exit opening at least in part occluded by a membrane possessing osmotic properties, whereby when a sufficiently concentrated solution contacts the membrane outside the chamber, liquid in the chamber leaves in an attempt to dilute the more concentrated solution, creating a lesser pressure which can be utilized as a signal or actuating power. Actuating means such as a retention pin can be moved from a ready to an actuated position as a function of the lowering of pressure in the compartment.

Abstract: A system for counteracting the effect of helicopter vibrations on a seat in the helicopter which seat includes a plurality of controllable air cells includes a means for varying the pressure of the cells and transducer means for sensing cell pressure and vibrations and for providing electrical signals representative thereof. Control means provide signals for controlling the means for varying and processing means process the electrical signals and provide driving signals for driving the control means. A processing means converts the electrical signals to provide driving signals which drive the control means to control the means for varying so as to counteract the changes in pressure in the air cells due to vibrations to eliminate or reduce the changes in pressure with this system, the pilot is isolated from the helicopter compared with prior art systems where the seat is isolated from the helicopter.

Abstract: An improved cushion of buoyant material for an airplane seat in which the cushion is removably attached to the seat, such as by Velcro strips. The cushion has straps to receive the arms of the passenger sitting on the cushion whereby the passenger can become coupled to the cushion and cause the cushion to be separated from the seat by pulling the cushion away from the seat. The cushion is formed from a number of hinged sections which pivot forwardly and partially around the passenger to stabilize the passenger when the passenger is in the water and coupled to the cushion by the straps. Actuating devices cause the forward pivoting of the hinged sections when the cushion is pulled away from the seat.

Abstract: There is disclosed an airplane seat having a base member provided with a pair of tracks located 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. Located above the base member is an adjustable seat base and adjustable back member pivotally joined thereto. The seat base is connected through a shaft which cooperates with a clutch located in an opening in the top of the base and which permits universal movement of the seat base in fore, aft and lateral directions independently of the movement of the base member in a fore and aft direction.

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: 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: A dual redundant pitot-static sensing system for use in a system for deplng a parachute during ejection of an occupant from a disabled aircraft includes a pair of pressure-sensitive check valves to store peak dynamic airstream pressure for obviating difficulties experienced when the pitots are blocked by airborne debris.

Abstract: A tandem seat assembly for ultra light aircraft is disclosed which is interchangeable with a single seat configuration. The assembly, which is primarily used for pilot training, is fitted with dual aircraft controls. The single seat must be removable from an ultra light aircraft in order for the tandem seat assembly as described by this invention to be utilized. The tandem seat assembly is thereby placed in the aircraft such that the center of gravity of the seat assembly is near the nominal center of gravity of the aircraft. Universal attachments of the seat assembly to the aircraft frame allow the seat assembly to be used with a number of different manufacturers of ultra light aircraft models.

Abstract: Multipassenger aircraft seat has at least one seating position which can be converted from a seat to a cocktail table to increase the comfort of adjacent seat passengers. The headrest pivots about 180.degree. relative to the back cushion frame so that it becomes hidden under the back cushion frame and in compressed contact with the lower seat cushion when a cocktail table on the back cushion frame is deployed in a horizontal plane. Concealed locks inside the headrest permit the headrest and back cushion frame to be firmly locked to the reclinable main seat back frame.

Abstract: An aircraft seat (11) particularly adapted as a pilot seat for a helicopter includes a seat bucket (12) having a back-rest portion (13) supported by an articulated support structure (14) adapted to react vertical, longitudinal and lateral loads and to permit normal vertical stroking of the seat by extension of any energy absorber (32) in the event that the support structure becomes mis-aligned in a hard landing. The structure comprises two parallel generally vertical guide tubes (15a, 15b). The lower ends of both guide tubes are attached to a cabin floor (17) by universally pivoted joints (18), the upper end of a first one of the guide tubes (15a) is pivotally attached to one end of a generally horizontal straight link (20) to react longitudinal loads only and the upper end of the second guide tube (15b) is pivotally attached at the apex of a generally horizontal triangular link (21) so as to react both lateral and longitudinal loads.

Abstract: An energy absorbing seat arrangement, particularly for a helicopter, in which a seat pan is carried by a frame slidably mounted on parallel upwardly extending pillars secured to the helicopter. In normal conditions, downward sliding of the frame on the pillars is prevented, in one embodiment, by metal rods fixed with respect to the pillars, and extending through drawing dies fixed with respect to the seat frame. In a variant the rods and dies are replaced by a deformable metal tube and a mandrel extending through the tube. In the event of a crash in which rapid downward movement of the helicopter and the pillars is halted suddenly, the seat and seat frame continue to move downwardly, sliding along the pillars, while drawing of the rods through the dies, or drawing of the mandrel through the deformable tube, to dissipate the kinetic energy of the seat and its occupant relatively gradually.

Abstract: Track fastener apparatus for use with a vehicle locking track located within a vehicle such as an aircraft or the like, that includes a bracket member having portions thereof locatable around a portion of the locking track for restraining portions of the locking track from bulging outward when the track fastener is subjected to large loads such as would occur when the vehicle is subjected to a crash. The track fastener has a body portion and the bracket member is connected to the body portion by a bolt so that the bolt can be tightened to clamp the lower portion of the bracket member against the locking track, and hence, reduce or eliminate rattle between the locking track and the track fastener. By loosening the bolt, it is also possible to readily slide the track fastener along the locking track or remove the track fastener from the locking track.

Abstract: A rear-facing crashworthy set for fixed wing aircraft comprises a seat facing in the opposite direction to the direction of flight of the aircraft and energy absorbers attached between the seat and the floor of the aircraft. The energy absorbers include forward energy absorbers attached to a forward section of the seat, intermediate energy absorbers attached rearwardly of the forward energy absorbers, and rearward energy absorbers attached rearwardly of the intermediate energy absorbers, all energy absorbers having the capability of operating in both tension and compression. Stabilizing members are attached between the seat and the floor of the aircraft. Energy attendant upon a crash is absorbed, and the seat is enabled to flex with crash-induced distortions of the floor to prevent separation of the seat therefrom, thus preventing severe injury or death as a result of a second impact of the detached seat with a structural member of the aircraft, such as a bulkhead, under crash conditions.

Abstract: A translating rudder pedal system which includes a rudder pedal assembly and a reclinable, translationally movable, seat operably connected to the pedal assembly, with both the pedal assembly and the seat mounted in a vehicle, such as an aircraft. The system ensures that, irrespective of the movement and positioning of the seat, the feet of the user seated in the seat always remain in contact with the control pedals of the rudder pedal assembly.

Abstract: The invention relates to an improved ejection seat restraint system for protecting the head and neck and spinal cord from injuries resulting from rapid forward deceleration and ejection from aircraft. The neck of human beings is at risk from lethal spinal cord injury with rupture of the atlanto-occipital membrane which holds the base of the skull to first cervical vertebra. Such lethal injuries according to the invention are prevented by a single inertial reel connection to the helmet of the user, at a point, aligned with or slightly above the superior nuchal line of the skull of the user. The helmet includes forehead padding, a wrap around cup shaped chin strap and an adjustable nape strap. The webbing for the inertial reel connection is preferably medium to soft.

Abstract: A crashworthy vehicle seat comprises a seat bucket member suspended by supporting webs engaged with rotary energy absorbers attached to the overhead of the vehicle. Beneath the seat bucket member, pairs of extensible and compressible energy absorbers are attached between the seat bucket member and the floor of the vehicle. Upon impact, the rotary energy absorbers and the extensible and compressible energy absorbers are arrayed to permit controlled and energy absorbing movement to reduce the probability of injury to the occupant of the seat. In the one form of the seat it accommodates itself to fore and aft forces acting upon it. In a modified form of the seat the design is optimized to accommodate these forces. In further forms of the seat the design is arranged for a sideward or lateral facing seat and the design is optimized to accommodate lateral forces.

Abstract: A powered articulated headrest system for use with a seat structure having a backrest, such as the ejection seat of a high performance aircraft, e.g., a combat aircraft. The headrest system includes: a headrest assembly which is movably connected to the backrest; and, an electro-hydraulic actuator assembly for moving the headrest from an original (and normal) position above the backrest to any one of an infinite variety of positions which are rearward and downward of the headrest, and for moving the headrest from these other positions to the original position. The actuator assembly is controlled by the occupant of the seat, e.g., the pilot of the aircraft.

Abstract: A seat structure includes a flexible canvas seat bottom portion (14) and a flexible canvas seat back portion (12). A horizontally disposed, transversely extending beam member (58) is rotatably disposed above the seat bottom portion (14) and is operatively connected to the lower end of the seat back portion (12). The beam member (58) is movable between two positions 90.degree. apart such that when the beam member (58) is disposed in its first position, the beam member (58) effectively defines a support shelf or platform projecting forwardly of the seat back portion (12) and is therefore capable of supporting parachute packs borne by parachuting personnel seated within the seat structure. The seat back portion (12) is also disposed in a slackened state at such time so as to accommodate the depth of the parachute packs.

Abstract: An improved helicopter seat primarily for combat aircraft includes at least upper, intermediate, and lower pairs of energy absorbers attached between the seat bucket and the frame of the helicopter and operable in both tension and compression. An upper pair and lower pair of steel tension rods attached between the frame and the seat bucket provide attentuation in a lateral direction. The energy absorbers comprise a plurality of telescoped tubes interfitted into one another and having coils of wire frictionally engaged between adjoining tubes such that energy is dissipated by motion of the tubes relative to one another through the plastic deformation of the coils of wire. The energy absorbers are adjusted to optimize the safety parameters of occupants of the seat under a range of potential crash conditions including the most probable crash condition, and for occupants having a substantial range of weight.

Abstract: An improved crashworthy helicopter seat primarily for combat aircraft includes at least upper, intermediate and lower pairs of energy absorbers attached between the seat bucket and the frame of the aircraft and operable in both tension and compression. The energy absorbers comprise a plurality of telescoped tubes interfitted into one another and having coils of wire frictionally engaged between adjoining tubes such that energy is dissipated by motion of the tubes relative to one another through the plastic deformation of the coils of wire. The energy absorbers are adjustable to optimize safety parameters of occupants of the seat under a range of potential crash conditions including the most probable crash condition, for occupants having a substantial range of weight and size.

Abstract: Mounting system for the back rest of a vehicle seat permits normal reclining action as well as two modes of forward movement. In a first mode, a slight forward force applied near the top of the seat back, such as about 10 lbs. or less, will pivot the top of the seat back forwardly several inches to facilitate access to the space behind the seat. The slight rearward force produced by an occupant leaning back against the seat back as he occupies the seat will then return the back to its normal upright position. A substantially larger forward force, such as one of about 25-35 lbs., can also be applied to the top of the seat back in a second mode to cause the back to "break-over" about 90.degree. and lie flat. The various movements are achieved by means of a channel-shaped quadrant member which overlies the back rest frame on one side of a seat, pivots on the back rest support shaft, and includes a long curved slot and a short curved slot.

Abstract: Improved framing system for a multi-passenger seat incorporates a generally inverted L-shaped rear leg whose shorter leg portion is joined to the rear stretcher tube at its free end and to a compression member at its point of intersection with its longer leg portion. The compression member and short leg portion form one side of a triangle which includes the front leg and a support member connecting the front and rear stretcher tubes. The longer leg portion forms one leg of a triangle which includes the compression member and a seat track covering member. The design provides greatly improved passenger leg room for close pitch seating arrangements.

Abstract: A light-weight aircraft passenger seat, which includes a plurality of integrally mounted wire-bending energy attenuators, and which can be floor mounted to face either forward or backward. Four seat legs, pivotally connected between the seat and floor, extend upward at the same angle from the floor, which is determined by two energy attenuators also pivotally connected between the seat and the floor, and extending upward from the floor in an opposite direction from the seat legs. When facing forward, the seat is stroked forward and downward. When facing backward, the seat is stroked backward and downward. In either a forward or backward facing disposition, the free ends of the energy attenuations extend into the back of the seat. Also the seat is flexibly connected to the seat legs and energy attenuators, which, in turn are connected by swivels to the floor to provide seat articulation as the floor distorts during a crash.

Abstract: A G-protective seat is disclosed for disposing an occupant within a vehicle n a supine tucked posture during high acceleration loading substantially along the Z-axis of the vehicle. At the onset of high Z-axis acceleration, a pair of pivotal leg support members are actuated to fold the legs of the occupant upwardly thereby drawing the knees up to the chest of the occupant in an intermediate tucked position. With the occupant in the tucked position, the seat rotates upward about an axis substantially defined by the occupant's eyes into a supine position for the duration of the high acceleration loading.

Abstract: An aircraft seat having a pivotal seat back which has an upright position for occupancy and an advanced position for affording additional living space to the passenger occupying the next rearward seat including a detent mechanism to maintain the seat back in either of its positions and to allow passenger adjustment of the seat back between these two positions.

Abstract: Life and weight saving aircraft seat structure employs frame supported interconnected pneumatic seat and seatback cushions with automatic compensation for pressure and temperature changes primarily by provision of predetermined pneumatic overflow envelope elastic force variables; in preferred embodiment self-extinguishing inflating gas is provided, a vented sleeve or sheath limits amount of expansion of the overflow envelope and an overflow relief valve limits system pressure.

Abstract: An operating station having an operator's seat and one or more observer's seats movable along a U-shaped track so as to be positioned either behind or on either side of the operator's seat. The track comprises four individual rails to which is mounted a set of four swivel rollers which support a base member of the observer's seat. The rails each have a substantially identical U-shaped configuration, with the center of symmetry of each U-shaped rail being offset from one another in a manner that the base member of the observer's seat is able to move along the entire U-shaped track assembly without changing its orientation with respect to the aircraft. In another configuration, the two halves of the U-shaped rail are made as mirror images of one another.

Abstract: A man-carrying vehicle modified with a device for alleviating accelerative forces particularly useful for space travel is provided with a personnel carrier which automatically orients its occupant, with an imaginary Z-axis parallel to the spinal column and through the centers of mass of cross sections of the body and of the head perpendicular to the Z-axis such that the Z-axis is in a position normal to the resultant of the forces of acceleration, and which rotates the occupant about the Z-axis to alleviate or counteract the effects of the forces of acceleration in the X and Y directions normal to the Z-axis.

Abstract: An aircraft seating arrangement for an aircraft in which the seats for the pilot and passengers are disposed on first and second pairs of longitudinally extending rails in a fashion that permits the seated occupant to position his seat at a desired location along the fuselage of the aircraft. The rails or tracks are disposed in the floor of the fuselage and roller members cooperate with the parallel tracks and with the seat frames to facilitate sliding the seats back and forth along the rails or tracks. A suitable detent is provided for locking the seat with respect to the rails at the desired location. Also, provision is made for rotating the seat cushion assembly from a normal, horizontal orientation to a substantially vertical orientation when a latching device is released.

Abstract: A tri-axis crash survivable seat, utilizing a plurality of energy absorbers, which are swivel mounted to the seat bucket and also to a frame where the frame is securely fastened to the structure of a rotary wing or fixed wing aircraft. The energy absorbers are utilized in upper, intermediate and lower pairs, each having different energy absorbing characteristics, stroking distances, and force-displacement relationships from the other pairs. The energy absorbing devices attach to the bucketseat and supporting frame so as to permit tri-axial energy absorption during impact for various vertical or combined vertical impact angles. Each of the intermediate pair of energy absorbing devices is a two stage device designed to minimize the dynamic overshoot associated with the elasticity of the human body, such that a reduced probability of injury is obtained. Energy is dissipated in a controlled manner through the process of the displacement of the seat relative to the craft under arbitrary crash conditions.

Abstract: A support system for an object such as a crashworthy aircraft crew seat which is floor mounted will isolate the seat from floor distortions as well as floor vibrations which would otherwise be introduced into the seat. The floor distortions occur only during a severe crash or impact. The floor vibrations occur continuously during normal flight as well as during maneuvers which could increase or decrease from a nominal level of relatively high G forces as they are transmitted from the floor. The invention provides a plurality of vibration and distortion isolating units from which the chair is supported at a plurality of points. The isolation units are circular holding members made of resilient material with crushable metal inserts in the resilient material. Supporting pins or members pass through the metal inserts in the isolation units. The isolation units are carried by rail guides constructed to translate along rails. The isolation units provide the capability of plus or minus 10.degree.

Abstract: An aircraft letdown system is deployable in the event of power failure or mechanical failure over inhospitable terrain or in the event of environmental conditions which preclude VFR or IFR landings. A parachute system, which is attached to the aircraft at a point in approximate vertical alignment with the aircraft center of gravity, is selectively energized by the pilot when it becomes apparent that a safe normal landing cannot be made. On energization, the parachute canopy and the shroud lines are repositioned from the place of storage to a location external to the aircraft and deployed in the conventional manner. To alleviate the shock of landing to the passengers and cargo, a specially constructed impact absorbing landing gear is extended and the occupants are further protected from the landing shock through impact absorbing seats.

Abstract: Triangular net-like arm restraining members, one for each side of an aircraft ejection seat, extend during the first phase of ejection so that each has an upper corner near the top of the back portion of the seat, a front corner near the front of the horizontal seat portion, and a lower corner near the junction of the back and seat portions. The upper corner of each restraining member is anchored near the top of the back portion, at its side thereof. The restraining members are normally furled and extend laterally outwardly from the back portion to the cabin wall, thence forwardly along the cabin wall, to be spaced, embracing relation to the seat occupant's shoulders. Upon ejection, one tension element for each restraining member draws its front corner forwardly, downwardly and laterally inwardly; another draws its lower corner downwardly.

Abstract: An articulated high "G" force aircraft seat which is movable between a conventional upright position and a reclined position. As described, the head and eyes remain in a relatively stationary position without affecting instrument monitoring or external vision. The aircraft controls remain within easy reach, yet the pilot is able to sustain high acceleration maneuvers in excess of eight "G's".

Abstract: An adjustable crashworthy pilot seat adapted to be used in aircraft such as helicopters is supported from the floor thereof within a support frame such that the normal lateral vibrations of the aircraft are not imparted to the pilot and so that the seat retains its crashworthy and adjustment capabilities.

Abstract: To enable a single pilot to make a safe and beautiful SOLO flight of a side-by-side dual-control airplane, the pilot is provided with a seat and seatbelts which seat him in the centerplane of the airplane, his right hand being placed on the right grip of the right control wheel, his left hand being placed on the left grip of the left control wheel, and his feet being placed on the two outboard rudder pedals, thereby permitting him to control the airplane with conventional motions. He leans sideward and/or diagonally forward to the right or left windows and/or elbow rests, banking and/or pitching the airplane while scanning the view, traffic and weather. Thus from the vantage point of the centerplane seat, the SOLO pilot can execute in less than a minute a prescribed routine of 0 percent BLIND maneuvers characteristic of his airplane type, whether it has the pilot seated ahead of, under, or over, the wing.

Abstract: A special form of adjustable height seat, such as would be used for a pilot or crew member in a plane or helicopter, provides a generally vertical mounting arrangement for positioning of a seat height adjuster between a fixed height seat base and a slidable unitary seating section. In addition, the height adjuster means is provided with an energy absorption connection for at least one end portion thereof by having a movable portion in alignment with and available to be forced through a restricted section in the event of a crash landing situation.

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: In an electronic version of the present invention, the potentiometer is cected to an aircraft control stick for sensing the position thereof. The output is coupled to logic circuits that detect the position of the control stick, associated with a severe maneuver about the pitch axis. Such detection actuates a valve for preinflation of a G-suit. Additional logic circuits are provided for detecting when the rate of control stick movement exceeds a preselected threshold. This, also corresponds with a severe maneuver about the pitch axis of the aircraft and also serves to actuate the G-suit valve. Analogous fluidic components may be utilized to effectuate equivalent operation of the G-suit.