Abstract: A flow control system selectively operable to either invert the relative position of first and second coaxially flowing fluid streams or to combine the two fluid streams for discharge as a single annular fluid stream is disclosed. The system includes a longitudinally extending input transition section which is partitioned into separate flow passages that receive sectorial regions of the first and second annular fluid streams and redirect the fluid streams into a segmented annular flow pattern in which portions of the first and second fluid streams form circumferentially extending annular sectors that are interspersed in circumferential alternation. Fluid exiting the input transition section flows into a longitudinally extending valve section having entrance and exit openings of geometry substantially identical to the segmented annular exit opening of the input transition section.

Abstract: A variable geometry gas turbine engine exhaust nozzle is disclosed wherein the inner surface of the nozzle housing and the surface of the tail plug are defined by two sets of hinged together axially extending elements and the nozzle housing outer surface is defined by a single set of axially extending elements. Viewed in the transverse direction, the elements are of an annular geometry with adjacent elements circumferentially overlapping one another to define an annular exhaust duct. A set of hydraulically operated drive units, connected for radial displacement of the juncture between the two sets of elements that define the nozzle housing inner surface, provides rapid control over the nozzle throat diameter. A set of gear driven drive units controls axial displacement of the forward end of the elements defining the nozzle housing outer surface and drives hinged together annular extending support beams into abutment with the overlapping regions of the nozzle housing inner wall.

Abstract: An aircraft engine installation is disclosed wherein a gas turbine engine is supported within the interior of a tubular cowling that is affixed to the aircraft and all other components of the engine installation such as an air inlet and exhaust system structurally depend from the cowling rather than being mounted to the gas turbine engine. To permit access to the engine for inspection, repair or removal. the lower portion of the cowling is linked to a stationary upper portion of the cowling by a set of jackscrew assemblies spaced apart along each axial boundary of the upper and lower cowling units. The jackscrew assemblies are operable to lower the lower cowling unit to a position at which integral locks, included in one set of the jackscrews, can be released to permit the lower cowling unit to be swung open about integral hinges that are included in the second set of jackscrews.

Abstract: A cargo pallet incorporates a plurality of pneumatically extendable and retractable roller means disposed in a lower, deck or floor contacting portion thereof. The roller means are arranged in a pattern to provide equitable load distribution such that, when the roller means are extended, the pallet and any cargo thereon may be easily moved in any horizontal direction; and, when the roller means are retracted, the pallet is immobilized with its lower surface resting substantially flush with a cargo-supporting floor, deck or platform. Inherent load-levelling is accomplished since one or more roller means may be partially retracted to accommodate bumps and uneven portions of the floor, deck or platform over which the pallet is to be moved. The conjoint operation of one or more roller means in the foregoing manner also provides a cushioning or load-distributing action for the pallet and its cargo.

Abstract: A three-dimensional composite structure with integral reinforcing ribs. The ribs have a core to include spaced metal inserts that are positioned to accept load bearing fasteners. A lightweight reinforcing material fills the remainder of the core. An adhesive tape with continuous filament composite fibers encircle the rib. The ribs are positioned between an inner and outer shell of structurally reinforced plastic and wound circumferentially and laterally with continuous filament composite tape.

Abstract: A thrust reverser cascade section comprising a plurality of cascade windows mounted in an engine nacelle rearwardly of the fan air compressor, each cascade window including a plurality of cascade elements, is disclosed. The cascade elements are rotatable through an arc of 90.degree., more or less, between closed and open positions, along axes lying generally parallel to the longitudinal axis of the nacelle. The cascade elements include deflecting vanes and are generally S-shaped when viewed in cross-section. Adjacent cascade elements abut one another in both their open and closed positions. Seals are located in the regions of abutment. The vanes direct fan air flow from the fan air duct toward the front of the nacelle when the cascade elements are in their open position. Each cascade window also includes sealing end plates adapted to move into and out of sealing relationship with the cascade elements to seal the ends when the cascade elements are closed.

Abstract: A three-dimensional composite structure with integral reinforcing ribs. The ribs have a core to include spaced metal inserts that are positioned to accept load bearing fasteners. A lightweight reinforcing material fills the remainder of the core. An adhesive tape with continuous filament composite fibers encircle the rib. The ribs are positioned between an inner and outer shell of structurally reinforced plastic and wound circumferentially and laterally with continuous filament composite tape.

Abstract: A projectile energy absorbing protective barrier comprising a blanket formed of multiple layers of woven cloth and a rigid supporting layer is disclosed. Each cloth layer comprises a plurality of tapes, each tape formed of high tensile strength, continuous filaments having a low modulus of elasticity. The cloth layers are each woven in a manner such that relative sliding movement between the tapes is permitted. The rigid backing layer supports the multiple cloth layers in a corrugated configuration such that the longitudinal axes defined by the corrugation nodes lie at an angle relative to the direction of the weave pattern. The corrugations, and the weave pattern, allow the cloth layers to instantly move without resistance upon impact by a projectile, in the direction of projectile travel. Subsequent to impact and achieving the speed of the projectile, the filaments wrap partially around the projectile and contain it by reacting in tension.

Abstract: A lightweight engine mounting assembly for attaching an engine to the wing of an airplane includes an outboard beam, an inboard beam, a forward annular stabilizing member and upper and lower, rear stabilizing members. Rearward extensions of the inboard and outboard beams have upper portions that extend rearwardly over the upper airfoil surface of a wing and lower portions that extend rearwardly and under the lower surface of the wing. The rearward extensions of the inboard and outboard beams are attached to the front main spar and to the upper and lower skins of the wing at the location of the wing ribs. The engine mount has a lower opening, bounded by the lower portion of the forward stabilizing member, the lower edges of the beams, and the lower, rear stabilizing member, and an upper opening bounded by the upper portion of the forward stabilizing member, the upper edges of the beams, and the upper, rear stabilizing member. Suitably shaped, removable cowl sections are located in the upper and lower openings.