Abstract: A method and system for supporting an airborne vehicle in space over a predetermined location and for an extensive period, comprises coupling the airborne vehicle by cables to a plurality of unmanned aircraft each having its own propulsion system; controlling the unmanned aircraft to fly in circular orbits at equally-spaced angles around the airborne vehicle while coupled to the airborne vehicle, to tension the cables and thereby to support the airborne vehicle in space over the predetermined location; and supplying the unmanned aircraft with energy from an external source to maintain the unmanned aircraft in flight over an extended or indefinite period of time.

Abstract: A high altitude reconnaissance platform is implemented by an ultralight aircraft powered solely by long wave infrared cells mounted on the lower surfaces of the wings and the fuselage. The aircraft may be of the pusher, slow speed propeller style, with a larger rear wing and a small, canard-type front wing. The bottom of the fuselage may be flat. The two wings may be vertically offset from one-another, and the cross-section of the wings may be relatively thick, with the ratio of the width of the wings to their thickness being in the order of about 6 to 8.

Abstract: A deployment system for a deployable truss structure particularly adapted to space applications which has high structural efficiency and can be remotely operated in a controlled, sequential manner. The truss in its deployed configuration exhibits a "diamond" cross section. Each of the four sides of the structure is essentially a "Warren" truss. Diagonals on the opposite sides of each diamond incorporate a mid-span hinge and the other two diagonals are rigid tubes. When packaged, all elements of the truss are folded so that they are parallel to one another and contained between two guide rails. The guide rails are located on either side of the diamond truss. The horizontal strut connection points or nodes are fitted with rollers that are locked in the guide rails for movement therealong. The deployment initially lifts upright truss members to the vertical position, forming the basic diamond shape of the truss.

Abstract: A cabin pressure control system has two independent controllers, one of which is used as primary controller while the other serves as standby. On alternate flights the identity of primary and standby controller are switched so that both controllers will be regularly utilized.

Abstract: This invention relates to a method and apparatus whereby functioning airborne conventional aircraft and engine combinations may be assisted during flight in attaining above normal airspeeds and/or altitudes; for the purpose of improving their performance during flight. In the method steps, well known apparatus elements, and/or new and useful combinations thereof, are utilized to enable such aircraft to achieve flight advantages, and improved flight performance, not believed to be possible prior to this invention. According to the method, booster apparatus is used initially in acquiring altitude, forward momentum of the aircraft, rotational momentum of its rotor airfoils, and the like. Apparatus used includes oxygen booster systems. Such systems can include forward thrust rockets, rotational boosters, and apparatus for injecting a supplemental oxidizer into a gas turbine engine afterburner.

Abstract: An integrated thermal anti-icing and environmental control system for a gas turbine powered aircraft uses hot high pressure bleed air from the turbine compressor to de-ice the wings and the engine air inlet, and supplies conditioned air for the aircraft cabin. In order to minimize total bleed air requirements and maximize heat recovery, bleed air exhausted from the inlet anti-icing system is passed sequentially through other systems. In this invention, the usual pre-cooler unit and the associated heat sink are eliminated and the pre-cooling function is performed within the inlet anti-icing system, preferably through the use of a double skin heat exchanger contained within the lip of the inlet. One embodiment of this system includes a closed-loop liquid anti-icing system for acoustic rings mounted in the inlet wherein the liquid is heated by passing the bleed air through a heat exchanger mounted immediately downstream of the inlet anti-icing system.