Abstract: The invention discloses an ejector release unit having a bell crank lever to positively lock the store retaining hooks in their retracted positions following release of a store. One arm of the lever is operatively associated with a surface on an adjustment hook when the hook is in its retracted position and the other arm of the lever is contacted by one end of a plunger. The other end of the plunger contacts a surface of the store so that, as the store is lifted into position, the lever is automatically moved out of engagement with the hook to permit the hook to be moved to its engaged position.

Abstract: Fore mounted aft swept and aft mounted forward swept wings extend from either side of a lifting body fuselage. Each lateral pair of the wings is joined at the tops by a wing tip vortex translating device to induce translation of the tip generated vortices along the trailing edge of the aft wings. End plates extend rearwardly from the maximum chord thickness of the fuselage to increase the effective lift of the fuselage. An elevator, mounted intermediate the rear top of the end plates, provides pitch control and structurally augments the wing root and fuselage junction of the aft mounted wings. A power plant disposed at the rear of the fuselage provides thrust and also dissipates, as useful thrust, the wing tip vortices translated from the tips to the power plant along the trailing edges of the aft wings.

Abstract: An aircraft which includes a lower main support structure to which there is attached wings, empennage, and a cabin section. The cabin section is positioned forwardly of the empennage and is supported in overlying relationship respective to the lower main support structure and to the wings attached thereto. The cabin section has a deck attached to an upper platform of the main support structure in such a manner that the cabin section can be moved horizontally and forwardly respective to the platform. A plurality of fasteners are arranged to affix the cabin section to the main support structure. Some of the fasteners are in the form of releasable bolts and other of the fasteners are in the form of shear bolts which attach the platform and deck together. Accordingly, should the aircraft impact against an object with sufficient force, some of the fasteners are released to enable the cabin section to separate from the remainder of the aircraft and to continue to travel away therefrom.

Abstract: This aircraft arrester net gear comprises at least one flexible frame having each at least one elementary net slidably mounted therein, in such a manner that when a forwardly projecting element of the aircraft engages the net the elementary nets can slide in relation to the frame and the horizontal width of the net mesh normally engaged by the aircraft wings is reduced; for this purpose, open-loop slack portions of the horizontal straps of the elementary nets are provided at each end thereof.

Abstract: Apparatus including a spoiler quadrant coupled to the aileron cable control system of the aircraft, rotation of which spoiler quadrant in either direction causes a bell crank to rotate about its pivot point in one direction only from its inactive position. A plurality of links transfer this motion to operate inboard spoilers simultaneously on both sides of the aircraft in response to and proportional to the degree of aileron deflection.

Abstract: A passive aircraft landing gear system in which the spring rate and damping for aircraft rolling motions about a longitudinal axis are independent of the spring rate and damping for aircraft vertical motions, thereby permitting the landing gear system to optimally accomplish both landing impact attenuation and ground resonance instability abatement.

Abstract: A vehicle bumper formed by a rearwardly opening U-shaped profile member having arranged therein reinforcements fashioned as vertically arranged ribs extending in the longitudinal direction of the vehicle. The ribs are formed of a metallic material and are individually secured with the bumper which is fashioned from sheet steel.

Abstract: A tracked vehicle system comprises a track having a downwardly facing surface of magnetic material, and a vehicle movable along the track, the vehicle comprising a magnetic suspension system including a permanent magnet, the suspension system being arranged to be magnetically attracted upwardly towards the surface of the track by the flux of the magnet whereby the weight of the vehicle is at least partially balanced by the magnetic force between the magnet and the track, and a magnetic circuit for controlling the magnetic flux, without permanently reducing the magnetic strength of the magnet, whereby to control the lifting force.

Abstract: A locking mechanism for a swingably mounted flight control surface member of an airplane, such as a rudder, which is embodied in a unitized frame structure that can be applied to either new or existing airplanes, which includes a bracket mounted assembly arranged for mounting within an enclosed portion such as the tail cone, in a position wherein a reciprocable locking bolt may be manually selectively moved by an outside ground attendant to a projecting position in locking engagement with a keeper carried by an adjacent part of the flight control member, and to a released retracted position. The bolt is connected to one end of a rocker arm carried by a rotatable shaft having an end extending to the exterior of the enclosed portion, and being arranged for releasably receiving an actuating tool.

Abstract: A novel kite parachute toy, consisting of a plastic parachute toy and a plastic releasing device. The parachute toy having a hook and the releasing device having a forward and rear eyelet for attaching to a kite string. A parachute is attached to the parachute toy and when the hook of the parachute toy is placed over the string of a flying kite, wind will fill the bag of the attached parachute and propel the parachute toy up the string to a releasing device. When the parachute toy meets the releasing device it is released from the kite string and slowly descends to earth with the attached parachute.

Abstract: The roll control of V/STOL aircraft is augmented by deriving a controlled, transverse thrust component from the lift producing engine. This is accomplished by redirecting a jet to introduce such a component not compensated by a counteracting jet or jet component of the craft. Jets can be redirected through pivoting of bent pipe sections of gimbal-hung nozzles.

Abstract: An electromagnetic suspension and guide system for a magnetically suspended vehicle comprises an armature rail of three-legged shape in cross section fixedly mounted on a rail support laid on the ground, and an electromagnet core of three-legged shape in cross section fixedly mounted on a magnetically suspended vehicle and disposed so that the three legs thereof are in an opposing relationship to the three legs of the armature rail with a gap therebetween, respectively. The three-legged electromagnet core has a different width from that of the three-legged armature rail, and the two side legs of the core are provided with windings wound thereon, respectively. The suspending and guiding operations of the vehicle are controlled by controlling the energizing currents supplied to the electromagnet.

Abstract: An apparatus for attaching a load bearing line to a helicopter is disclosed that utilizes a curvilinear track mounted on the underside of the helicopter with a carriage having a cargo hook freely movable thereon. The curvilinear track has a radius of curvature that extends from the center of gravity of the helicopter to maintain forces imposed on the helicopter from a swinging load directed through a point near the center of gravity of the helicopter.

Abstract: A pair of semi-rigid solar cell panels are curved under stress and latched in arcuate edge abutting fashion about the exterior of a spacecraft body, and upon release of the latched ends flatten into tangency at opposite sides of the spacecraft body. Spring hinges at the ends of a deployment arm cause each panel to automatically move radially outward of the spacecraft body, and a motor mounted to the spacecraft body and to one end of the deployment arm rotates the panel to orient the solar cells relative to the source of solar energy.

Abstract: A plurality of arrays of solar cells are symmetrically stored about a spacecraft during launch to provide symmetrical loading. When the spacecraft is in operational configuration, the solar arrays are deployed adjacent each other on one side of the spacecraft to effectively form a single array and the single array may be oriented to face the sun by a common drive mechanism.

Abstract: A slide-articulation bearing for supporting a shaft, in particular for tiltable converters, has a circular-cylindrical sliding face forming a unit with the shaft, sliding elements held by a cage contacting the sliding face, and an outer race with a spherical inner face for accommodating wobbling movements of the shaft. The cage is provided with radially directed recesses that are open towards the cage inner and outer sides, the sliding elements being inserted therein so as to project out of the recesses. The sliding elements have outwardly projecting ends provided with spherical outer faces that contact and cooperate with the spherical inner face of the outer race.

Abstract: An ejector release unit for carrying aircraft stores is provided having single-pronged or double-pronged hooks adapted to be pivotably mounted on the unit. The hooks are utilized with wedges, spigots, and crutch arm adaptors in arrangements that enable interchangeable selective fitment to the unit. This arrangement provides for sway bracing of a store to be carried by the unit by a crutched or crutchless system as is required. Two alternative crutched arrangements are disclosed.

Abstract: A ball joint connection for the torque scissors of aircraft landing gear provides realignment of the scissors during stroking of the piston to avoid the usual distortion and wearing of parts in the conventional straight pin hinge. Quick disconnect of the scissors for aircraft towing is accomplished through the simple expediency of rotating the ball portion of the scissors design, upon which two diametrically opposed flats have been machined. The scissors can thereby be easily and quickly disconnected prior to towing and then reconnected for the torque transfer operation. As an added feature a ball rotating and locking device is provided as an integral part of the scissors assembly.

Abstract: A device for starting an aircraft engine which is capable of being started by rotating a propeller connected to the crankshaft of the engine. The device comprises an anchor for fixedly positioning on the landing surface below the propeller; this anchor can be held in place by a portion of the aircraft itself; in one case, the nose wheel and in another case, a separate extension arrangement. A holding device is provided for holding the propeller and crankshaft of the engine against rotation in a proper starting position while a rotative device is provided for placing a biasing force on the propeller for rotating it. When desired, the holding device is remotely released and the propeller is pulled through the compression stroke by the rotative device and rotated in a manner to start the engine by the rotation of the crankshaft. Each of the holding device and rotative device has a propeller tip cap for connection to the propeller, while the other ends are fixed to the anchor.

Abstract: A portable and adjustable aircraft cargo handling system designed to facilitate substantially simultaneous aerial delivery of cargo from a cargo ramp and paratroops from side doors from a conventional troop carrying aircraft of the Hercules C130 type which is provided with an inwardly and upwardly-opening rear cargo door and an outwardly and downwardly opening rear cargo ramp. The cargo device includes a base, which can be secured to the conventional aircraft cargo ramp; a load carrying platform, having friction reducing rollers or the like, superimposed on the base and pivotally connected thereto along one of its marginal edges; and a lifting device which is located between the base and the platform to raise and lower one end of the platform relative to the base between a first, lowered position in which cargo is loaded thereon and loaded into the aircraft and a second, raised position in which cargo is carried in flight and is discharged from the aircraft when the rear cargo door is raised.