Abstract: An attitude reference system which uses microwave radiometry to sense the orientation of a vehicle. A fundamental fact of microwave radiometry is that more natural energy emanates from the earth than from the sky. The difference in energy, which is directly proportional to temperature, can be used to estimate attitudinal position. Microwave antennas mounted on an escape vehicle, such as an aircraft ejection seat, receive energy from different directions in a base plane and from a direction perpendicular to the base plane. Vehicle orientation relative to the earth is discerned by comparing the sensed radiometric temperature received from each antenna direction, and seat guidance equipment is programmed to steer the seat in a predefined direction based upon the radiometrically sensed orientation.

Abstract: An apparatus for handling and storing baggage or cargo within an aircraft fuselage including a fuselage door and a plurality of storage platforms with each platform consisting of a flat rectangular base and two upwardly extending side walls closely juxataposed to the shape of the fuselage. The platforms are capable of stacking one atop another when not in use adjacent the fuselage door. Each platform can move longitudinally relative to the aircraft fuselage away from and back towards the fuselage door in a telescoping sequence such that the uppermost platform will move away from said stack first and such that the lowermost platform will always return to said stack first.

Abstract: A seat mounted arm restraint net system for restraining a crewman's arms during an ejection sequence wherein a pair of nets, mounted with one on each side of the seat, are deployable by separate static lines passing through snubber boxes to frangible anchorages on the vehicle floor. Each static line is releasably attached to a separate swinging arm rotatably secured to its seat side such that the swinging arms throw the free net sides laterally outwards and then release the nets to close over the crewman's arms.

Abstract: An aircraft is disclosed which includes a body having the shape of an inverted cone with a downwardly extending rim formed about the edge thereof and a triangularly shaped tail section. The aircraft can be constructed as a glider or a powered device and several alternative tail sections are shown such as square, radii, circle and tangent.

Abstract: A collapsible fuel tank for aircraft, the tank having rigid top and bottom elements and foldable rigid side walls containing therein a non-vented fluid-impervious elastomeric bladder. When fluid is pumped into the bladder, it distends to deploy the top, bottom, and side walls whereby a box-like structure whose rigid walls protect the bladder is erected. The withdrawal of fluid from the bladder causes it to contract such that the walls are folded and the tank thereby collapsed into a space-saving volume. The tank can be mounted on the outside surface of an aircraft and the contraction of the tank as fuel is expended effects a reduction of the aircraft frontal area to reduce drag.

Abstract: A main engine support structure having a rear portion hinge-mounted at two laterally spaced locations to a leading edge of a wing in a manner to permit limited up and down swing movement of the engine relative to the wing. A generally vertically aligned forward support link connects a forward inboard side portion of the engine support structure to the airplane fuselage, thus providing vertical support for the engine at its forward end. At the rear of the support structure there is a laterally extending link, connecting the support structure to the wing and resisting lateral loads exerted on the engine. This mounting system reliably mounts the engine to the wing, does not interfere with the wing's ability to flex upwardly and downwardly, and properly transmits the loads from the engine into the aircraft structure.

Abstract: The pitch and roll channels of the stability augmentation system (inner loop) of a helicopter automatic flight control system are utilized to provide positional and attitude stability at low speeds and hover, and to reduce the attitude effects of wind gusts during essentially level, forward flight at cruise speeds. In the longitudinal or pitch channel, true longitudinal acceleration is summed with washed-out vertical gyro pitch in level flight below 60 knots, and washed-out vertical gyro pitch is used alone above 60 knots; in the lateral or roll channel, true lateral acceleration is summed with vertical gyro roll at speeds below 60 knots in essentially level flight, and vertical gyro roll is inputted alone above 60 knots whenever the heading hold logic has not been disengaged (indicating a roll has not been commanded to perfect a turn); thereby to provide positional and attitude stability at low speeds, and to provide attitude stability at cruise speeds.

Abstract: A wing pivot assembly for variable sweep wing aircraft for movably securing a wing of the aircraft to the fuselage. The wing pivot assembly has a pivot pin supported by a pair of inboard lugs secured to the fuselage of the aircraft. The wing is, in turn, movably secured to the pivot pin by bearings interposed between the pivot pin and a pair of outboard lugs. In addition an outboard shear fitting located between the wing and the pivot pin movably supports the wing and transfers shear loads to the pivot pin. An inboard shear fitting and anti-rotation device secures and transfers shear loads between the pivot pin and the fuselage. As a result of the above arrangement a multi-load path structure provides for a fail-safe pivot assembly.

Abstract: A gondola-type railway car has a bottom which comprises at least one and preferably at least two transversely parabolic surfaces which extend below the side sills of the car, giving increased capacity, a lower center of gravity, and increased resistance to bottom damage.

Abstract: A banner in the form of an elongated sheet of flexible material is attached to an air dropped sonobuoy for stabilization of the sonobuoy during descent as well as for descent speed control, entry angle control, and wave action damping once the sonobuoy is floating at the surface of the ocean. The banner is roller furled and stored on top of the sonobuoy. When the sonobuoy is dropped, the banner unrolls and streams out behind the sonobuoy during descent. It is a feature of this drogue apparatus that it is deployed by the time that the sonobuoy has descended a distance corresponding approximately to the length of the banner. The banner is not released when the sonobuoy hits the water in order to enable it to stream out over the surface of the water to provide wave damping action.

Abstract: An anti-skid brake control system has a brake pressure control unit for producing a release signal to trigger the release of brake pressure and a subsequent re-apply signal to trigger the re-application of brake pressure in successive brake pressure release/re-apply cycles; and a change-over control unit for producing a change-over signal to trigger a change from a first, rapid re-apply stage, in which brake pressure is re-applied rapidly, to a second, slow re-apply stage in which brake pressure is re-applied slowly, during the re-apply period of each cycle; the change-over control unit including a storing device responsive to the duration of the re-apply period in successive cycles so that the change-over point in each cycle is controlled in a manner dependent on the duration of the re-apply period in the preceding cycle, whereby the duration of the re-apply period is dynamically adjusted to assume a preset value.

Abstract: A slot seal closure apparatus for use in an aircraft engine mounting strut comprises at least one door which covers a slot formed in the strut to accommodate fore/aft movement of a portion of the engine cowl. When the engine is in a cruise mode, the movable portion of the cowl is in its forwardmost position disengaged from the slot and the door is in a first position covering the slot so as to prevent airflow through the slot. When the engine is placed in a reverse mode, the movable portion of the cowl moves aft and the door swings to a second position spaced from the slot in reaction to the aft movement of the cowl portion so as to expose the slot thereby enabling the movable portion of the cowl to engage the slot.

Abstract: An efficient aircraft utilizes a stabilizer spaced from a fixed wing, and supported for controlled rolling about an axis extending generally in a forward direction, to control aircraft yaw. The stabilizer extends generally horizontally in straight forward flight. Pitch of the stabilizer is also controlled.

Abstract: Cascades and associated blocker doors are provided in the lower section of a turbofan engine nacelle such that when the blocker doors are closed the bypass flow is diverted through the open cascades to produce vertical thrust. Vanes are provided in the cascades to assist in directing the diverted airflow in the downward direction. The upper section of the bypass duct is isolated from the lower cascade section by way of horizontal struts extending across the bypass duct. A pair of outer doors may be provided over the cascades such that, when opened, they act to provide side skirts to guide the downward flow of air.

Abstract: An inflatable landing bag having a valve for release of the inflating fluid from the landing bag as the pressure of the inflating fluid of the landing bag rises above a given level, such valve including a sleeve comprised at least in part of a woven stretch fabric having interstitially variable inflating fluid porosity such as to control release of inflating fluid from the landing bag.

Abstract: An aircraft landing wheel rotating device including a body portion eccentrically secured to the outer face of the landing wheel hub. A series of like air-receiving portions extend outwardly from the body member in spaced relation for catching the wind and effecting rotation of the wheel prior to landing.

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 air inlet control inset in the skin or outer wall surface of an aircraft or the like. The control device has an open position in which it is able to capture ram air flowing over the wall surface and which at the same time defines an open flow area through which lower pressure ambient air can be inducted when ram air is unavailable. The air inlet control includes a shutter opening into ram air flow, and an actuating mechanism therefor. In one disclosed form of the invention, the shutter is aerodynamically biased to reduce actuating forces required to close the shutter against ram air pressure.

Abstract: A box-type kite constructed of unitary polygonal end frames having interior corners and with passages in the interior corners subtending more than 180.degree.. Struts carrying sails thereon and equal in number to the corners, having a cross-sectional dimension greater than the openings to the passages are received in the passages to provide a polygonal box-type kite which requires no cross bracing for rigidity.

Abstract: A drooping leading edge device is provided in which the leading edge structure that droops is pivotally mounted, by a single pivot inside the wing, upon the front spar structure of the wing and is of substantially constant shape. A gap which would otherwise open up between the upper skin of the main part of the wing and the upper skin of the leading edge structure, when the leading edge droops, is filled by an upper flexible skin section secured to the main part of the wing and extending forward first into contiguity with the rear edge of the upper skin of the leading edge structure and then inside said leading edge structure. At the underneath of the wing, a rear flexible portion of the lower skin of the leading edge device extends back to meet the forward edge of the lower skin of the main part of the wing.