Abstract: An improved satellite cellular telephone and data communication system facilitates dual satellite coverage over at least eighty-five percent of the earth. This improved system permits communication with hand held and mobile mounted cellular telephones (120). The system permits two-way communications anywhere on or above the earth up to a particular height above the earth of several hundred nautical miles. The system employs a number of low-earth orbiting satellites (12) moving about the earth in orbit. The satellites (12) are inclined at an angle between 30 and 90 degrees. Links (102) are provided from the satellites directly to the users (120) and via the public switched telephone network (20) to other users. The satellites (12) are interconnected via links in a ring structure surrounding the earth. Switching is performed by each of the satellites (12).

Abstract: A three axis stabilized geostationary satellite comprises a structure having walls that face North and South when the satellite is on station and carrying at a storage battery of large capacity. The storage battery is constituted by cells mounted on a chassis having a base plate oriented North-South and mechanically secured to sides that face North and South when the satellite is on station. The sides carry thermal radiators that are thermally connected to each other and to the cells. Typically sides are in alignment with North and South faces of the structure and extend away from the Earth.

Abstract: Methods for using tip generated vortices to improve performance of foils. These methods include generating a substantially streamwise beneficial vortex (74) near the outboard end (60) of a foil (82). This beneficial vortex (74) spins in the opposite direction of an induced drag vortex (62), and is used to create an upwash field (76) which neutralizes induced drag by deflecting the flow behind the trailing edge (56) at an upward angle. Upwash field (76) causes the lift vector (118) on the foil (82) to tilt forward, thereby creating a forward directed force of induced thrust upon the foil (82). Beneficial vortex (74) is also used to contain and compress the high pressure field existing along the attacking surface of the foil (82), and displace the induced drag vortex (62) inboard from the tip of the foil (82). Numerous performance parameters are improved dramatically by using beneficial vortex (74), as well as by using a double vortex pattern (124).

Abstract: An actuation system for controlling the steerable nozzle of a missile or like vehicle is combined with an aerofin control system, both of which are driven in unison by associated drive motors and gear assemblies, one set for each aerofin. The nozzle steering system comprises two essentially identical yoke plates mounted along a plane generally transverse to the missile axis and oriented orthogonally relative to each other about the missile axis for pivoting the nozzle through mutually orthogonal axes, thereby achieving omni-directional steering. The yoke plates are coupled at opposite ends to pinion gears which are driven by the same gear assemblies which drive the associated aerofins. The arrangement permits common directional control of the steerable nozzle and the aerofins while maintaining the nozzle in a neutral direction when the aerofins are rotated to a missile roll control mode.

Abstract: Apparatus for detecting and signaling a skewing or misalignment of adjacent aircraft leading edge slats is disclosed. A cable is attached to an actuator having a compression spring system and located in an outboard slat. The cable passes through cable guides in several adjacent slats before being attached to an inboard slat. The compression spring system utilizes a dual concentric pair of compression springs for maintaining a tight cable. When a misaligned condition is detected by a proximity switch, the increased cable load will cause the actuator to lock itself in a position out of the range of the proximity sensor.

Abstract: A submarine launched unmanned aerial vehicle comprises an elongated genery cylindrically-shaped body. Tail fins are stored in the body and are self-deployable to extend outwardly from the body. A booster motor is fixed to an aft end of the body and is self-releasable from the body. A propeller is disposed at the aft end of the body and is self-deployable to an exposed position at the aft end of the body after release of the booster motor. A propulsion motor is mounted in the body and is operative to drive the propeller. Rotors are stored in the body and are self-deployable to an exposed position wherein the rotors provide lift to the vehicle.

Abstract: Acoustic noise resulting from the interaction of a periodic pressure and velocity fluctuation induced by a periodically passing blade wake interacting with a downstream airfoil (10)is attenuated by locating an antisymmetric pressure wave generator (30) adjacent the leading edge (18) of the vane (10).

Abstract: A process for arranging seats within an airplane to provide optimal combinations of passenger comfort and space utilization. The process involves calculating the average passenger comfort level in each possible row configuration using the comfort levels enjoyed by passengers seated in different seating environments created by adjacent occupied seats, empty seats, sidewalls and aisles, each such comfort level being weighted by the portion of passengers who would be seated in the seating environments at each possible load factor and the frequency of occurrence of that load factor. The row configuration with the highest passenger comfort level may be installed in the airplane.

Abstract: An adjustable sprinkler head positioning assembly is disclosed that includes a first conduit member and a second conduit member that are selectively positionable relative to each other and to a drop line fitting so as to position a sprinkler head at a desired location. The first and second conduit members each have an inlet portion and an outlet portion that are offset relative to each other by a predetermined distance. The sprinkler head is positionable anywhere within a circle having a radius equal to the sum of the offsetting distances between the inlet and outlet portions of each conduit member. Elbow couplings further increase versatility. The elbow couplings may have an inlet positioned at a 45.degree. angle or a 90.degree. angle relative to an outlet.A drop line fitting is weldable to a sprinkler drop line and includes a socket for receiving sprinkler system plumbing such as the first and second conduit members.

Abstract: A mechanical regulation system for controlling tow line payout between the aerobody and a towing vehicle. The system comprises a housing, a nonrotating spool, and a tow line wound around the spool that is coupled between the aerobody and the vehicle. The regulation portion of the present system comprises a rotatable wedge-shaped tube, having the tow line wrapped around it. A rotatable mechanical regulator is slidably coupled to the wedge-shaped tube. The regulator is adapted to rotate with the tube and move transversely along the length of the tube as the tow line is removed from the spool. A brake mechanism is provided as part of the regulator, and a brake drum is disposed adjacent the periphery of the regulator that is contacted by the brake mechanism.

Abstract: A flush mounted panel fastener is provided for use in aircraft or the like of the so-called stealth type designed to avoid detection by radar. The panel fastener comprises a fastener element such as a threaded bolt having a head and shank for fastening a panel onto a substrate or frame. The head is sized for recessed seating within a counterbore formed in the panel, and a fastener cap is mounted and magnetically retained on the head of the fastener element. The fastener cap has a surface coating or finish thereon disposed substantially coplanar with an outer surface of the panel, wherein the surface coating is formed from a suitable nonreflective radar material and cooperates with the panel to present a substantially uninterrupted surface of low radar signature.

Abstract: A launching and regulation system that incorporates an expendable towing and deployment mechanism for use with a towed aerobody that provides for launching and controlled tow line payout between the towed aerobody and a towing vehicle. The system comprises a housing, a nonrotating spool disposed in the housing, and a tow line wound around the spool that is coupled between the aerobody and the vehicle. The tow line preferably comprises a photonic, fiber optic, link. The launching mechanism comprises a plurality of impulse cartridges for deploying the aerobody and severing the tow line at a predetermined time. A spring piston is disposed inside a wedge-shaped tube that confines expanding gasses within the tube that are generated by an impulse cartridge and moves the spring piston to launch the aerobody. The regulation mechanism may comprise a mechanical system or adhesive resin system. The mechanical system comprises a rotatable wedge-shaped tube, and the tow line is wrapped around it.

Abstract: An apparatus for deicing an aircraft is defined by an insulated shelter being a size capable of enclosing an aircraft. The shelter is positioned on a deicing surface that absorbs heat from means such as electrical filaments or heated pipes within the deicing surface or through the application of infrared radiation onto the deicing surface. In turn, the deicing surface radiates heat into the air within the shelter. Once an aircraft is enclosed within the shelter, infrared radiation is applied to a portion of the exterior surface of the aircraft. The combination of the infrared radiation and the heat radiating from the deicing surface rapidly deices and substantially dries the exterior surface of the aircraft. The exterior of the aircraft is subsequently heated to a sufficiently high temperature that ice will not reform on the aircraft prior to take off.

Abstract: The present invention relates in general to aeronautical engineering and concerns specifically transport vehicles for transportation of liquid and loose cargoes. The invention provides an airborne vehicle capable of carrying a multiton cargo from a limited ground area. The object of the invention is accomplished due to the fact that in the airborne vehicle of the present invention the lifting aerodynamic airfoil system is made of two parts, that is, a stationary part in the form of a ring-shaped fuselage 1, consisting of aerodynamic members 2 and 3 curved spanwise, and a movable part in the form of lifting rotor units 6 arranged along the ring perimeter. A power unit of the vehicle comprises a gas-generator, propulsive units, ramjet ducts, and flywheel members interconnected through a reversible rotary-reciprocating engine-supercharger 22 and a fluid converter.

Abstract: Methods and apparatus for reducing the velocity of a rider in or on an open cockpit vehicle when the rider is thrown from the vehicle are disclosed. The present invention provides a drag-reducing device such as a parachute or parawing that is affixed to the rider so that when a crash occurs, the rider is slowed down after ejection and therefore more likely to survive the crash without severe injuries. The present invention is preferably used in conjunction with a motorcycle and includes a sensor system for sensing the imminence or occurrence of a crash an/or the ejection of the rider from the vehicle. A transmitter receiver system is used to relay a signal to a deployment system that is attached to the rider as part of a system containing the drag inducing device, which rapidly deployed, thereby causing the velocity of the ejected rider to be reduced and providing the further benefit of lifting the rider away from the crash site.

Abstract: Arcs of segmented spoilers generate a ring on intake airfoil surface of cantilever-suspended jet engines. Strain and temperature sensors on sides of a cantilever connecting structure feed data to a stress-limiting computer whose output communicates with actuator motors of spoiler segments. This stress-feedback network selects and actuates segmented spoiler surfaces to release radial forces that normally are balanced within the engine intake zone. The stress-limiting computer also takes autopilot data of anticipated attitude change patterns and forecasts anticipated strain patterns of an aircraft. An output communication is integrated with an electric power conditioning that actuates motors to position the segmented spoiler barriers.

Abstract: The air intake includes two main flaps (1, 2) facing each other and each pivoting about a pin (4, 5) adjacent to a wall (6, 7) extending the flap in question (1, 2) rearwards, and in which a first boundary layer bleed (8a, 8b) is arranged, the pins (4, 5) being substantially parallel to the plane of the wings or of the fuselage so that the flaps (1, 2) move perpendicularly to this plane, and a ramp (11) pivoting about a pin (12) adjacent to its leading edge (11a) by which it is adjacent to the wings and to the fuselage and substantially parallel to the pins (4, 5) is upstream of the flap (1) which is closest to the wings and with which it delimits another boundary layer bleed (13) of variable cross section.

Abstract: A linear ballscrew type actuator including a bi-directional no-back device having both primary and secondary no-back features is provided. The secondary no-back features only become active following a failure of the primary no-back features, thereby ensuring maximum reliability by precluding wear or fatigue of the secondary no-back components during normal operation of the actuator. The secondary no-back features are provided by secondary pawl mechanisms mounted at the distal end of an articulated eccentric arm. The angular position of the eccentric arm is utilized to annunciate the operational condition of the no-back device. Angular motion of the eccentric arm is utilized to trigger engagement of a secondary locking device, upon failure of the primary no-back features.

Abstract: A self-contained fueling module (10) provides the exact amount of hydrazine necessary to fuel a satellite (50) prior to launch. The fueling module (10) includes a propellant tank (14), a vacuum tank (12) and a pressurant tank (16). The propellant tank, filled with hydrazine, is shipped to the launch site where it is installed in the fueling module. Prior to launch, the fueling module is connected to the satellite and the hydrazine is driven with Helium pressurant into the satellite fuel tank. The Helium also pressurizes the satellite fuel tank to flight pressure. Any remaining fuel is evacuated from the connections (45) and fuel transfer lines (42) with the vacuum tank. Personnel do not have to wear self-contained atmospheric pressurized environment (SCAPE) suits because there is no risk of hydrazine exposure.

Abstract: A special set of elliptical satellite orbits are described which allow preferential coverage of one parameter over another. According to a first modification, the orbits are retrograde, and preferentially cover one geographical location or time of day as compared with another. A second modification uses prograde orbits and allows the apogee of the orbit to be offset a constant amount with respect to the sun, to thereby cover a different time of day relative to the others. According to a special preferred mode of the invention, the apogee is always pointing towards the sun.