Abstract: A hinge arm for a thrust reverser door may be mounted to an exhaust nozzle using an aft mount. The mount includes a frame for attachment to the nozzle. A swing link has a first pin pivotally joined to the frame, and a second pin for pivotally joining the hinge arm to the link to permit both swinging and pivoting of the hinge arm from the frame. The aft mount thusly permits the reverser doors to be reliably stowed around the nozzle.

Abstract: The Oya glider is a modified hang-glider that incorporates many advanced aerospace technologies, such as, glues, for binding Shape Memory Alloy materials to Piezoelectric Ceramic Strips, and synthetic feathers. Lightweight composite plastic materials treated with the MuCell Process, both for framing and chassis construction. Piezoelectric Sensors and Actuators. Nano wires, and nano cables, for electrical connections and manual control levers. Computer firmware and software, designed to mimic, in real time, the aerodynamic flight reactions to external wind conditions, of a gliding bird. The Oya computerized glider will come as close as technologically possible to imitating a bird's mastery of the wind.

Abstract: A spacecraft includes a spacecraft base structure having an externally facing, electrically conducting spacecraft surface, with the spacecraft structure including a solar cell array. A grounding structure has an externally facing, electrically conducting plasma grounding surface, and an electrical ground extends between the plasma grounding surface and the spacecraft base structure. In space, the spacecraft is oriented with the plasma grounding surface facing the sun. Electron photoemission from the plasma grounding surface balances electron charging of that portion of the spacecraft surface that does not face the sun, preventing electrical charging of the spacecraft relative to the plasma environment.

Abstract: The disclosure relates to a low cost and highly accurate precision guided system suitable for use in conventional aircraft launched bombs. The system includes a kit mounted upon the nose of the conventional bomb which replaces the conventional fuse disposed in a fuse well, the kit including guidance electronics controlling a self-contained jet reaction device and GPS P-code receiver electronics. The bombs are readied for discharge by signals broadcast from the aircraft into the bomb bay which transfer initial GPS data and commence operation of a gas generator which powers the jet reaction device.

Abstract: A synchronized target subsystem for use in an automated docking system for docking a chase vehicle with a target vehicle wherein the chase vehicle is provided with a video camera for feeding digitized frames to an image processing unit which feeds signals to a control circuit. The control circuit turns on the video camera to digitize a background frame which will include the target vehicle. After the camera grabs the background frame the control circuit turns on a light, which is carried by carried on the chase vehicle and aimed at the target vehicle, and signals the video camera to digitize a foreground frame. A light sensing circuit on the target vehicle receives the light from the chase vehicle and connects a power supply to lights on the target vehicle such that when the foreground frame is digitized the Lights on the target vehicle will show in the foreground frame. The image processing unit subtracts the background frame from the foreground frame and provides a docking signal.

Abstract: The aircraft comprises a central cabin, which is located in the center of a circular wing. Several pivotal electric drive units are arranged in a gap between the central cabin and the circular ring. In hover flight, the drive units are pivoted to generate a lift. When the aircraft goes into cruise flight, the drive units are pivoted to generate a forward thrust. Attitude and movements of the aircraft can be controlled by individual or common adjustment of the thrust and pivot angle of the drive units. Due to its simple design, the aircraft is economic and safe in operation. Still it has a high payload for its size.

Abstract: A forced air aircraft de-icing system is described, which in a preferred embodiment includes a vehicle having a articulable aerial boom mounted thereon with an operator platform disposed on the distal end of the boom, a compressed air source including a compressor and power source operatively attached to the distal end of the boom at or below the operator platform, and a high speed air jet nozzle operatively attached to the outlet of the compressor for directing a high speed air jet against the surface of an aircraft in the removal of snow and ice therefrom.

Abstract: A vehicle with improved maneuverability includes: a vehicle body; a first bladelike element; a first tuned compliant transmission shaft attached to the bladelike element; and a reciprocating unit for reciprocally driving the bladelike element within a fluid medium in a first travel path such that interaction between the bladelike element and a fluid medium produces propulsive forces that propel the vehicle body in a desired direction. Preferably, the pitch and heave natural frequencies of the natural transmission shaft are approximately equal to each other and to the natural bending frequency and torsional frequency of the bladelike element, and the natural thrust frequency of the transmission shaft is often approximately twice that of the pitch frequency. In this configuration, the vehicle can be directed in virtually any direction, the directing force is be generated far more quickly than is the case for prior art vehicles, and energy typically lost as shaking or vibration instead provides thrust.

Abstract: A pylon conversion system (100) for operating a pylon (12) on a tiltrotor aircraft (10) between an aircraft mode and a helicopter mode is disclosed. The system (100) comprises first and second pylon conversion actuators (102,104) each having a retracted position and an extended position which corresponding to the aircraft mode and the helicopter mode. A first gearing system (156) is operably coupled to the first pylon conversion actuator (102) and to a first primary power unit (110), a first backup power unit (112) and a first clutch (138). A second gearing system (158) is operably coupled to the second pylon conversion actuator (104) and to a second primary power unit (114), a second backup power unit (116) and a second clutch (142). An interconnect drive train (126) is operably coupled to the first and second clutches (138, 142) such that the first and second pylon conversion actuators (102, 104) are operable between the extended position and the retracted position.

Abstract: An improvement to an aircraft is provided in the form of an aircraft auxiliary power and thrust unit located in the tail cone of the aircraft. The unit includes a turbofan engine, an air intake opening, an inlet duct extending between the air intake opening and the turbofan engine, a transmission assembly, and various auxiliary equipment. The engine includes a forward-facing main turbine shaft. The air intake opening is located in the tail cone at a body station location forward of the engine. The transmission assembly includes a drive shaft mounted axially to the main turbine shaft and extends forward through the inlet duct through a sealed opening in the inlet duct. The auxiliary equipment is also located in the tail cone, forward of the turbofan engine. The transmission assembly is releasably connected to the auxiliary equipment. In a first operating mode, the engine is operated at a low setting to power the auxiliary equipment.

Abstract: A device for the suspension of a payload in a space launch including annular chambers of fluid with variable geometry installed between the launch and the payload and first and second rigid members fixed, on either side of the chambers, to the payload and to the launch respectively so as to transmit the stresses between the latter through the chambers. The fluid chambers and the first and second rigid coupling members are coextensive, ring-shaped and coaxial with a longitudinal axis common to the launch and to the payload. The first and second annular rigid coupling members each include external and internal ribs respectively, axially separated by one of the annular fluid chambers.

Abstract: A skid landing gear for a helicopter, in which the directional stiffnesses of the cross members of the skid landing gear have been de-coupled from one another, such that optimization of the longitudinal stiffness of the cross members may be performed independently of the optimization of the vertical stiffness and fatigue life of the cross members. In order to de-couple the stiffnesses in the skid type landing gear, two approaches are employed. In the first approach, the skid landing gear has non-symmetric-section cross members and/or distribution of different materials within the cross-section for de-coupling the vertical stiffness of the cross members from the longitudinal stiffness, such that placement of the ground resonance frequency may be optimized, while retaining the vertical stiffness properties essential for optimizing vertical energy attenuation and fatigue life.

Abstract: A vehicle control system is disclosed utilizing a reaction wheel assembly for producing small scanning motions and, in combination, a scissored pair of low-cost control moment gyros is used to produce larger slewing motions.

Abstract: A retractable airfoil assembly (20) augments the wing surface area (28) of an aircraft (22) enabling it to fly without stalling at reduced speeds during takeoff and landing. The airfoil assembly includes flexible sails (42, 44) and a furling mast (24) for extending and retracting the sails. The furling mast includes a furling drum mounted for clockwise and counterclockwise rotation on a static tube (50). The flexible sail assembly also includes guide tracks (80) located along a leading edge (101) or tailing edge (40) of the wings. The tracks guide the flexible sails during extension and retraction. A drive cable (26) extends and retracts the sails (42, 44) along the guide tracks and maintains tension in the sails while they are extended.

Abstract: System for controlling an aerodynamic surface (1) (flap, aileron, control surface, etc.) of an aircraft. According to the invention, this system comprises: an electric machine (8) which can operate either as a motor or as a generator, the output of which is connected mechanically to said aerodynamic surface (1); and a logic device (17) receiving information about the operating status of the electrical power supply (11) of the machine (8) and of the hydraulic servocontrol (2, 5) and controlling the actuation of said surface (1) either by said machine (8) or by said servocontrol (2, 5).

Abstract: An airbag configuration for braking the landing impact of flying payloads has a central airbag (17) and at least one torus ring (11, 12, 13) surrounding the central airbag. A payload (L) is attachable on the central airbag (17). A stabilizing device (19) is provided which extends from the lowermost portion of the at least one torus ring (11, 12, 13) to the central airbag (17). The central airbag provides primarily vertical braking of the landing impact while the torus ring provides primarily horizontal braking of the landing impact.

Abstract: A box-structure airfoil is constructed of a composite material upper skin, a composite material lower skin 12 and a spar. Ribs and an elongate projection are formed integrally on the inner surface of each of the two skins. The upper and lower skins and the spar are simultaneously bonded by an adhesive to form a single structure. Since the ribs and the elongate projection are one-piece formed with each skin, it is possible to reduce the number of principal constituent components. Furthermore, since assembly operation is made by using the adhesive, there is no need for fasteners or the like for assembling. Moreover, the spar is bonded not only to Moreover, because not only a web but also flanges on both sides of the spar are bonded to the respective skins, it is possible to obtain a large strength. According to the invention, it is possible to reduce the number of principal constituent components and that of assembling components of an airfoil, thereby achieving its cost reduction.

Abstract: The invention is related to air flight vehicles, such as vertical take-off and landing (VTOL) airplanes, helicopters and covercraft. The goal of this invention is to create an air rotor designed so that while after vertical take off or cover regime, one can be stopped, fixed in a specific position and hidden into the fuselage (gondola) thus eliminating of air resistance when the rotor is not in working state. On landing this rotor can be extended out, brought into rotation and used for creation of lift force and vertical landing. The indicated goal is achieved by means of the rotor made as single blade (uniblade). The author solved the problem of force and moment balance of single blade. The center of gravity of the counterweight is located below the horizontal plane, and the blade has the horizontal sway axle, that crosses the vertical rotor rotation axis. The author offer this rotor on single axis, on co-axis, and on different exiles.

Abstract: An airfoil member, especially a rotor blade for a helicopter, includes an airfoil body and a servo-actuated flap tiltably connected to the airfoil body so as to form at least a portion of the trailing edge of the airfoil member. At least one piezoelectric actuator is arranged inside the airfoil member, and connected to the servo-flap via a transmission mechanism and a connecting rod linkage so as to tiltingly deflect the servo-flap as needed. Preferably, two counter-acting piezoelectric actuators are connected to the flap via respective transmission mechanisms and connecting rod linkages. An elongation of the piezoelectric actuators in the span width direction of the airfoil member is converted or redirected into an actuating motion in the chord length direction of the airfoil member by the transmission mechanisms.

Abstract: A variable volume fluid storage tank or reservoir and related fluid transfer system are provided for storing and transferring volatile or hazardous fluids, particularly such as fuel in an aircraft fuel supply system. Each fluid storage tank comprises a tank body in combination with a movable base wall defining a variable volume internal chamber for receiving and storing fluid. Each storage tank further includes a dispense port for dispensing the fluid, e.g., to a manifold or the like for supply to one or more aircraft engines, with the base wall moving relative to the tank body during fluid dispensing to substantially preclude any residual air or vapor space within the storage tank. A fluid level sensor unit mounted outside the tank chamber tracks displacement of the base wall to provide an indication of the fluid volume remaining within the storage tank.