Abstract: This invention relates to methods and apparatus for forming composite material components that have relatively complex surfaces. Currently such components are very expensive to manufacture because forming them requires a good deal of time and hand working of the material. In the system of the invention, a flexible membrane (38) is heated to a forming temperature. Composite material (70) is laid on membrane (38) and heated evenly by contact with membrane (38). Fluid pressure is applied to membrane (38) to force membrane (38) and material (70) upwardly against a mold surface. While it is urged against the mold surface, material (70) flow forms to the shape of the mold surface. Preferably, the mold surface and membrane (38) are rotated about a horizontal axis approximately 180.degree. to position the mold surface below membrane (38) before the fluid pressure is removed to allow membrane (38) to move out of contact with material (70).

Abstract: An end seal (36) for a variable camber flap in which the seal is formed of an upper portion (52) including closely spaced fingers (56). The fingers extend generally vertically downwardly from adjacent a flexible surface (40) of a flap (20). There are lower sealing walls (94, 96) extending generally vertically upwardly from adjacent the bottom of the flap (106). The lower sealing walls are adapted to remain in sealing engagement with the fingers as the camber of the flap is varied by increasing the curvature as it is lowered from a normally upper position.

Abstract: A container delivery system by which cargo containers are dropped from an airplane in which release gates are generally centrally positioned and longitudinally spaced in the cargo space of the airplane. The containers are secured forwardly and rearwardly by straps extending thereacross from one athwartship aircraft portion to another, generally from one outer side to the center. Release gates are generally positioned in central longitudinal rows so that the containers may be dropped out of a rear door when the door is opened, and the containers are released by opening the release gates which secure the straps to the central portion of the aircraft. A release gate secures one end of a rearwardly holding strap so that the one end of the strap is freed to allow respective containers to move rearwardly on rollers in the aircraft deck when the respective gate is opened.

Abstract: A support clamp for wire or hydraulic bundles has a flexible strap for binding the bundles. The strap has lateral teeth along one side, one end of the strap is integral with a head and the other end of the strap goes around the bundle and enters an opening that extends through the head. A member integral with the head is resiliently pivotable, extends into the head opening, and has lateral teeth. The member is pivoted as the strap is inserted, the teeth engage, and hold the strap tight against the bundles to prevent loosening of the strap unless a handle on the member is actuated.

Abstract: An intermodal cargo container capable of being quickly and easily converted between a solid storage mode and a fluent storage mode is disclosed. Shell sections adapted to be either removed from, or pivoted within, an outer container are provided to support an impermeable liner in the fluent storage mode. Elements of both the inner and outer container may be of conventional construction for surface transport or of lightweight construction suitable for air as well as surface transport.

Abstract: A filler of polyisobutylene dissolved in a solvent is combined with boron nitride to form a stop-off compound used as a parting agent when diffusion bonding metals. A uniform coating of the compound is applied with screen printing methods prior to bonding.

Abstract: An elongate hollow structure with a plurality of reinforcements arranged in a pattern and acting as spacers between a pair of skins. The skins are of resin impregnated wound filaments with reinforcing strips of facing preimpregnated wound filaments that crisscross at the spacing reinforcements, abutting panels extend between adjacent reinforcing spacers to fill the space between the skins, and the structure is bonded with resin into a composite structure.

Abstract: A pivotably mounted door stop linkage has a resilient member acting on the linkage to maintain the door stop in position for conventional door operation while allowing rotation of the stop to release the door in reaction to a pressure differential acting across the door.

Abstract: A rivet for joining fiber reinforced plastic laminates has an alloy of titanium columbium. The rivet is semi-tubular in shape. The tubular portion is shaped with an outwardly tapered inner wall to provide for expansion of the tubular section without expanding the balance of the shank.

Abstract: Apparatus for internally mixing fan exhaust with primary exhaust forward of the nozzle exit plane of a turbofan engine having an outer engine cowling, a splitter wall structure and a tail plug disposed in mid engine upstream of the nozzle exit plane is provided by a plurality of struts disposed radially between the engine tail plug and the outer engine cowling upstream of the nozzle exit plane and a plurality of vortex generating means disposed on the struts for generating vorticies across the entire engine exhaust area.

Abstract: An aircraft thrust reverser having a plurality of doors rotatably secured to linkage members at each door's center, and rotatably secured to a carriage ring at one end. As the carriage ring moves toward the direction of travel of the aircraft, the linkage members cause the doors to extend in a forward slope, intercepting fan air and directing it outward and forward.

Abstract: A composite structure is prepared in a mold using a vacuum bag with an edge breather separated from a layup to be formed into a composite. A means of communication between the edge breather and the layup provides a path for air being drawn from the layup and to provide a path that closes off and prevents excess resin flow from the layup as it cures.

Abstract: An apparatus and method for modifying a jet engine to be carried externally in an inoperative condition on an aircraft to minimize aerodynamic drag and oscillation of the engine. The apparatus includes an annular inlet extension adapted to be mounted to the operating air inlet which slightly extends and contracts the inlet to reduce air spillage. The disclosed method includes the removal of the fan blades from the fan section of the inlet, attaching an ice deflector dome to the engine core inlet, and attaching the inlet extension to the nacelle air inlet.

Abstract: An air launched cruise missile carrier airplane having a floor mounted track system for moving missile racks into a launch position adjacent to a side opening in the fuselage and ejecting missiles therethrough, then moving the empty missile racks from the launch location and repositioning a full rack of missiles thereat. A continuous missile launching sequence is provided by the floor track system which guides the movement of the missile racks within a cargo compartment of the fuselage for a continuous carousel movement.

Abstract: A cylindrical shaped tube freely rotatable within a housing provides the pressure chamber for an eccentrically mounted rotary seal vane type pneumatic motor with the drive actuating air moving axially through the pressure chamber.

Abstract: A single impact rivet gun has a piston freely movable within a cylinder that is surrounded by an air accumulator. A valve to control flow of the air from the accumulator to the inside of the cylinder is located at one end of the cylinder and the valve has an opening leading from outside the gun to the inside of the cylinder. The gun includes means for introducing a vacuum at the opening to pull the piston to a starting position.

Abstract: A resilient seal material is compressibly held against the side of a lined bearing at the juncture between the inner and outer race of the bearing with a formed ring fastened to the side of the outer race. The formed ring extends outward with the inner diameter of the ring contacting the outer surface of the inner race.

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.