Abstract: The invention is a short/vertical takeoff and landing aircraft. In detail, it comprises an airframe having aerodynamic lift and flight control surfaces. An engine is mounted in the airframe in a reversed position having the inlet facing toward the rear of the aircraft and the exhaust nozzle assembly, having a pair of exhaust nozzles, facing toward the front. The exhaust nozzles extend outward from the sides of the aircraft and are rotatable from a vertically downward position to provide upward thrust to a horizontally rearward direction to provide forward thrust. The thrust axis when in the vertical position is approximately through the center of gravity. A generally U-shaped engine inlet duct is mounted in the airframe having an inlet opening facing forward and an outlet coupled to the inlet of the engine.

Abstract: The invention is a split-point twist drill for use in drilling holes in sandwich structures composed of a combination of organic matrix composite, titanium and steel. The drill (20) preferably has a web thickness (50) prior to splitting of between 23 and 27 percent of the drill diameter, a point angle (60) between 132 and 138 degrees, a web taper from the point to flute run out between 0.015 to 0.020 inch per inch, a chisel-edge angle (44) between 115 and 121 degrees and a splitting angle (70) between 127 and 137 degrees. Further important dimensions are a helix angle (24) of between 28 and 32 degrees and a lip relief angle (62) of between 10 and 14 degrees. Additional important splitting dimensions are a positive notch rake angle (74) of between 5 and 10 degrees, and an angle of the notch (72) to the drill axis between 32 and 38 degrees.

Abstract: The invention is a propulsion system for a buoyant aircraft. The invention comprises a gas storage container filled with a lighter-than-air gas and having outer walls of which at least a portion thereof are flexible. A system is provided to move the flexible portions of the walls alternately inward and outward varying the internal volume of the container, thus, varying the buoyancy of the aircraft and providing a propulsive force. Air foils mounted on the aircraft are adapted to provide trimming forces as the aircraft descends and ascends.

Abstract: The invention is a system for removing volatile hydrocarbon contaminates from both water and moisture-ladened air. In detail the invention comprises a steam stripping system for mixing the contaminated water with steam, at below atmospheric pressure, providing clean water for reuse and contaminated steam and vaporized hydrocarbon contaminates. A first condenser receives the contaminated steam and vaporized hydrocarbon contaminates and condenses, at below atmospheric pressure, a portion of the vaporized contaminates and a portion of the contaminated steam into contaminate water. A second condenser thereafter further condenses the steam and hydrocarbon vapor.

Abstract: The invention is a compact wave antenna system for use on an aircraft. The antenna is mounted on a boom made of a dielectric material extending from the rear of the aircraft. The antenna comprises a thin, flat conductor wrapped around the boom. A large, "capacitive hat" is mounted to the extreme rear end of the conductor. The main contributors to the performance is the use of thin, wide conductor design and its relatively long length. The width causes high shunt capacity and high RF current flow to the airframe from all sections of the compact wave conductor topped off the capacitive hat at the end. The thin conductor cross-section minimizes series inductance and improves the flow of RF current. Additional current flows due to the spiral section coupling to sympathetic polarities of the airframe and due to additional radiation from the directional discontinuities.

Abstract: An improvement to a Flight Management System (FMS) for an aircraft is described. The improvement comprises: a system coupled to the flight management system for accepting flight data information, including a required time of arrival, and for generating therefrom an estimated arrival time and deriving from the estimated arrival time a signal representative of the required airspeed needed to allow the aircraft to reach a particular point at the required arrival time; and a system for receiving the signal and for generating an output signal for modifying the actual airspeed of the aircraft to correspond to the required airspeed. The signal is derived by applying to the actual airspeed a correctional factor which is a function of the estimated arrival time and the required arrival time. The correctional factor is generated from the ratio of the difference of the estimated arrival time and the required arrival time to the required arrival time.

Abstract: The invention is an aircraft jet engine variable shape, fluid flow nozzle (10) which is adjustable to sound-suppression (take-off) and nozzle open (cruise) modes. In the take-off or sound-suppression mode a plurality of movable flaps (24) are positioned inwardly by actuators (36) so as to form a fluted arrangement with a plurality of webs (13) that define the periphery of the nozzle (10) exit. A plurality of transverse fins (32) on the flaps (24) maintain a seal via a plurality of seals (34) with the web side walls (22). In the nozzle open or cruise mode of operation the guide vanes (26) of the flaps (24) are maintained in alignment with the outer walls of the webs (13) to form a maximum area-circular cross-section nozzle exit.

Abstract: The invention is an energy recovery system (20) which uses excess air emanating from an aircraft cabin (16) to drive a turbo-compressor unit (30). The outlet air from the compressor (26) of turbo-compressor unit (30) is optionally fed, either around or through heat exchanger (24), back into the aircraft cabin (16) inlet line, reducing the amount of bleed air required to power the aircraft ECS. Mass flow sensors (34) and (38) are used, via flow control valve (36) and flow control valve control unit (40), to monitor and control the amount of engine bleed air required at any point in time to satisfy overall ECS requirements. The energy recovery system (20") may be utilized in conjunction with a motor driven cabin compressor (42) to reduce the output air requirements of the compressor and thus the weight and horsepower requirements of the compressor motor.