Abstract: A flexible airframe flying wing, such as used for hang gliding, includes a central rib to which is perpendicularly connected two flexible spars. In turn, a plurality of floating ribs are releasably connected to the flexible spars, and extend generally parallel to the central rib. A flexible membrane envelops the central rib, the floating ribs, and the flexible spars in such manner as to bias the flexible spars in an arcuate configuration to define the leading edge of the flying wing. By virtue of the components thereof, and the flexible interconnection therebetween, the resulting flexible airframe flying wing is autostable and will adapt itself a various flight attitudes and conditions.

Abstract: A unitary frame having a central, annular-shaped fuselage section and a pair of outwardly opposed wing spars is fabricated from fiber-reinforced, resin matrix composites, and constitutes one of a number of similar such frames that are assembled together to form a framework of an aircraft body. Each wing spar has the general configuration of an I-beam incorporating a sine wave shear web reinforced along the upper and lower edges by flanges and lengthwise extending, tension/compression chords formed by bundles of lengthwise oriented fibers. The fuselage section has a circumferentially oriented sine wave shear web that is otherwise similar to the web of the wing spars, and has inner and outer circumferentially extending flanges that are similar to the upper and lower flanges along the wing spars.

Abstract: An improved vehicle skid control braking system is provided of the type that selectively controls the engagement and disengagement of the brake system of the vehicle in accordance with selective braking conditions, such as vehicle, speed, wheel speed, road surface conditions, wheel speed "slip" conditions, etc.

Abstract: An ejector release unit comprising a pair of hooks for supporting a store and an ejection device for ejecting a store supported by the hooks also includes, adjacent each hook, a sway brace assembly comprising a pair of pads for engagement with the upper surface of a store supported by the hooks, the pads being so mounted that during loading of a store they are free to yield, but at the completion of loading are locked firmly in position in contact with the surface of the store by way of irreversible mechanical connections exerting a thrust on the pads and resisting reverse movement. Each irreversible connection includes a slideable member having an end surface co-operating with a wedge-shaped surface on a vertically slideable member.

Abstract: A banner towing adapter for use in the towing of a banner or target by an rcraft of the type having an arresting tail hook assembly. The towing adapter is installable in the hollow tail hook attachment pin of the aircraft by means of an expanding sleeve. The sleeve is fixed to a first upwardly extending immovable arm which secures the sleeve to the tail hook support structure located on the aircraft. A second arm, rotatably attached to the sleeve and coupled to the tail hook, is provided at its distal end with a hook suitable for securing a towline from the banner to be towed. The towline securing hook is disposable between two hook retainers which act as a constraint when the towline is on the hook. One of the retainers is disposed at the far end of the first arm while the other hook retainer is rotatable about a point fixed on the first arm. The second retainer is lockable in a retaining position by a ball lock pin.

Abstract: A lift and propulsion system for partial piloting of a pendular effect piloted aircraft having a gliding structure. The system comprises a frame having a frame axis which is parallel to the pitch axis of the aircraft, the frame being rotatable about the frame axis. A pair of engines are supported by the frame and are each provided with throttle valves for controlling the power or speed of such engines. A rotation control lever arm having one end connected to the frame and the other end movably connected to the gliding structure is provided for controlling the rotation of the frame about the frame axis to control the orientation of the thrust of the engines, and a throttle control mechanism is provided for simultaneously and differentially controlling the power of the engines. The throttle control mechanism comprises a handle having a longitudinal axis and a support member for supporting the handle for rotation about such longitudinal axis.

Abstract: System for braking a vehicle comprising an anti-skid device receiving speed data from a detector coupled to a non-braked wheel, wherein the system comprises a correction device comprising on the one hand first apparatus adapted to tramsmit to the anti-skid device the speed data each time that the variations of these data in time are lower than a deceleration threshold representative of the aquaplaning of the non-braked wheel, and, on the other hand, second apparatus adapted, each time that the variations of the velocity data are greater than the threshold, to transmit to the anti-skid device an estimated decreasing speed datum. The invention is more particularly applied to the braking of aircraft.

Abstract: A recoverable remotely piloted vehicle (RPV) having: a deflectable canard/elevator placed very close to the nose tip; a constant (cross) section fuselage; wings mounted low and well aft on the fuselage; elevons; a centrally positioned weapons/payload bay, with doors, located internal of the upper portion of the fuselage; and, inflatable landing skids. The weapon/payload is dropped from the RVP, while the RVP is in flight in an inverted position.

Abstract: Process of landing an airplane on a solid landing surface covered with a layer of water comprising the steps of forming and maintaining a curtain of gas from a point forward and outboard of each of the landing wheels of an airplane on each side of the fuselage thereof to a point forward and central of the wheels and thereby displacing the water of the layer of water from the path of those landing wheels on that solid surface and later releasing the water from the curtain of gas at points lateral of each of the landing wheels while moving the gas curtain and airplane forward at a sufficiently high rate of speed to maintain the landing wheels in contact with the dry surface. Structural modifications of conventional cascade type thrust reversers and target type thrust reversers are provided to accomplish the steps of such process.

Abstract: A quick-release mooring apparatus for a floating vessel comprising a substantially stationary structure anchored to the sea floor and projecting above sea level, a vessel mooring member attached at a first end above sea level to the stationary structure in a manner which permits the mooring member to rotate about vertical and horizontal axes passing through the point of attachment to the stationary structure, the second end of the mooring member comprising a vessel mooring yoke having a pair of spaced arms, one end of each of which is adapted to be releasably attached, by lifting the vessel mooring yoke, to opposite sides of the bow of a vessel for rotation about a horizontal axis, and the mooring member having sufficient buoyancy for the second end to float on the sea when unconnected to a vessel. The stationary structure can be a buoy anchored to the sea floor by lines, or it can be a tower supported by the sea floor.

Abstract: An apparatus for controlling nutation motion in a spinning body, comprising an angular accelerometer having its input axis perpendicular to the spin axis of the body, a flywheel having an axis of rotation perpendicular to the axis of the accelerometer and to the spin axis of the body, and a motor for driving the flywheel to attenuate or build nutation. The motor is controlled by circuitry that monitors the output of the angular accelerometer and drives the motor clockwise or counterclockwise during predetermined nutation angles synchronized to the zero crossover points of the accelerometer signal and centered about the nutation peaks. In one embodiment, the motor drive is phased to damp nutation motion to zero for stabilization.

Abstract: A lifejacket is provided comprising a one piece body member of moulded, flexible, plastic foam. The lifejacket is divided into three distinct portions; that is a headrest portion, a shoulder portion and a chest portion, the shoulder portion incorporating a neck aperture. A longitudinal slit is provided which extends through the chest portion from the neck aperture thereby dividing the chest portion into two similar parts. The longitudinal slit facilitates the fitting of the life jacket to a wearer. A one piece tape is provided which passes through two longitudinally spaced transverse bores, one extending through the headrest portion and the other through the chest portion.

Abstract: The multi-cell canopy of the gliding wing type comprises an upper wall and a lower wall interconnected by ribs forming partition wall defining parallel cells open on the leading edge of the wing. Parachute control lines are secured to the trailing edge for deforming a part of the latter which forms a plain flap. The canopy comprises in its upper wall at least one air outlet passage which has the shape of a rearwardly facing slot so as to direct a laminar current of air tangentially of the upper wall.

Abstract: A ball joint is affixed to the harness of a kite and a kite string is tied at its first end to the ball joint. A kite tethering device is affixed to the frame of a bicycle for affixing the second end of the string to the bicycle. The kite tethering device comprises an elastic cord affixed at its first end to the second end of the kite string. A tubular member has a ball joint seat formed in a first end thereof for accommodating the ball joint. The elastic cord passes through the tubular member and out of such member at the second end thereof. A clamp affixed to the second end of the elastic cord is clamped to the frame of the bicycle between the seat and the rear wheel thereof whereby when the kite is not borne aloft, the elastic cord maintains the ball joint seated in the ball joint seat of the tubular member.

Abstract: Tailoring the contour and chord length of a variable camber leading edge flap for the tapered wing of an aircraft is aimed at improving the aircraft's low speed performance particularly for takeoff and landing. Each segment of a spanwise series of leading edge flap segments has a constant chord flexible panel and a spanwise tapered leading edge or bullnose member. By using different chord flexible panels in adjacent flap segments, together with a tapered bullnose, the effective chord length and contour of the variable camber leading edge flap can be varied smoothly in the spanwise direction without resorting to different flap linkage mechanisms at each spanwise station. Further, through the change in cross-sectional shape of the bullnose member along the semi-span of the wing, a change in the effective flap angle (angle-of-incidence of the flap-chord relative to the wing-chord plane) is also produced.

Abstract: A leading edge flap system for the tapered wing of an aircraft and more particularly, the spanwise flap segments and their linkage mechanism allow a relatively large leading edge bullnose member to be extended and unfolded out from a wing cavity. Each of the spanwise flap segments is supported from the leading edge of the wing by a pair of linkage mechanisms which are spaced apart spanwise and attached towards each spanwise end portion of the flap segment. The spanwise spaced apart linkage mechanisms are interconnected by a torque tube which is rotated through a fixed number of degrees by an actuator. By altering the geometry of the linkage mechanism, a differential motion is applied between the spanwise ends of the flap segment to torsionally twist the panel in a spanwise direction thereby varying the flap deflection angle spanwise.

Abstract: A disintegratable aerodynamic brake is disclosed for use on a re-entry vehicle for retarding vehicle speed upon re-entry. The brake is connected to the travelling vehicle and is fabricated from a refractory material and is configured to progressively fuse and disintegrate as it becomes heated by friction as the vehicle encounters increasing atmospheric resistance upon reentry thereinto, so as to retard vehicle speed.

Abstract: A crew station module that retracts or lowers itself during supersonic cruise flight to provide a small protuberance with adequate pilot vision over the nose and side which module extends or raises itself at takeoff and landing to provide increased downward vision over the nose and sides which module is adaptable for high acceleration cockpit seating i.e. seating that will be adjustable for accommodating variable G-loading upon the occupant such as during combat maneuvers and so forth.

Abstract: The present variable airfoil assembly has an adjustable airfoil member pivotally mounted in the top of a fixed airfoil member for adjustment between a fully lowered position (for minimum wind resistance) and different raised positions in which it projects up above the top surface of the fixed airfoil member to control the lift and drag. A minimum clearance between the fixed and adjustable airfoil members is provided at the front end of the adjustable airfoil member over a range of its pivotal adjustments. The variable airfoil assembly is capable of increasing the lift of the airfoil, then lowering stalling speed, and it may either replace flaps or be used in conjunction with flaps. Higher cruise speeds can be achieved as well as good low speed performance.

Abstract: The invention relates to a thrust reverser comprising two symmetrical doors, approximately hemi-truncated in shape, pivotally mounted about an axis which is transverse and substantially diametrical to the jet of a jet engine and which is disposed downstream of the jet exhaust pipe thereof, the doors occupying a folded, or stowed, position in which they determine a sleeve forming part of the fairing of the engine and fuselage of the aircraft, or an unfolded, or opened out, position in which they are disposed transversely with respect to the jet, wherein the structure of each of the doors is such that, in stowed position, the inner volume of the sleeve forms a useful extension of the jet pipe of the engine. The invention finds particular application in the braking of aircraft.