Abstract: A wing positioner apparatus for installing and removing an aircraft wing includes a wheeled base having a pair of vertically extending telescoping posts attached thereto. A wing support arm is hinged to each vertically extending telescoping post. A winch couples one wing support arm to one of the vertically extending posts for raising and lowering the wing support arm. A telescoping post winch is attached to the wheeled base for raising both vertically extending telescoping posts simultaneously. This allows an aircraft wing to be supported between the pair of wing support arms and the pair of vertically extending telescoping posts while being moved on the wheeled base and positioned for installation or removal from an aircraft fuselage.

Abstract: A power supply system operable to supply power and/or data to aircraft passenger seats that eliminates the need to extend individual cables to each seat and eliminates the need to rewire the passenger cabin when the seats are moved. The system includes a first connector housing secured to a first seat leg and a second connector housing secured to at least one of the first seat leg and the second leg. A first connector of a seat electronic subsystem is mounted to the first housing. A second connector of the seat electronic subsystem is mounted to the second housing. A conductor is operable to mate with at least one of the first connector and the second connector for conducting at least one of data and electricity to or from the seat.

Abstract: The invention provides a catch device of a cockpit door of an aircraft with improved safety. A cockpit door 1 disposed between a cockpit 2 and a passenger cabin 3 in an aircraft comprises a door body 10 that opens toward the cockpit via a hinge 12. A latch device 100 for opening and closing the door is provided on the cockpit side, and a bolt 120 thereof engages with a catch device 200 provided on a wall adjacent to the door. The catch device 200 has a solenoid device which restrains the rotatably disposed catch device by electromagnetic force. When trouble occurs to the solenoid, the restrained status of the catch member is released and the cockpit door may be opened. In such case, a pit pin 300 is inserted to the catch device to restrict rotation of the catch member.

Abstract: The present invention provides a device for controlling the movement of a vehicle closure element, the device comprising, interposed between a vehicle structure and a closure element, firstly a driver element that can be activated on command, constituted by a pyrotechnic actuator, and secondly mechanical connection means suitable for allowing a driving connection between the pyrotechnic actuator and the closure element when the pyrotechnic actuator is activated, while also allowing the closure element to move freely relative to the pyrotechnic actuator when the closure element is moved over a stroke greater than that enabling said driving connection.

Abstract: The device (1) for guiding an aircraft at least over an intermediate trajectory between a first flight trajectory for a low-altitude flight and a second flight trajectory which starts at an initial point, and from which trajectory a parachute drop is carried out, comprises means (9) for determining a point of transition which lies on the first flight trajectory which represents the start of the intermediate trajectory, and which corresponds to the point where the aircraft must exit the first flight trajectory so as to reach the initial point under predetermined flight conditions, and means (13A, 13B) which use the point of transition to aid the guidance of the aircraft between the first and second flight trajectories.

Abstract: An airship ballast system includes an engine driven propeller and a cooling tube that is positioned coplanar with the propeller and outside its tip path. One end of the cooling tube is connected to receive exhaust gases from the engine while the other end is connected to a ballast tank. In operation, exhaust gases from the engine are cooled as they transit the cooling tube, and water condensed from the cooled exhaust gases is pumped to the ballast tank to maintain a ballast for the airship.

Abstract: A process and device for optimization of deflection of spoiler flaps of an aircraft in flight may, in real time, compute an incidence potential available to be consumed by the spoiler flaps without endangering the aircraft and deflect the spoiler flaps toward the instructed deployed position as a function of the incidence potential.

Abstract: A multi-spectral shield and associated inlet structure is provided for reducing the signature of an air inlet port defined within an exterior wall of an aircraft, ship, or land-based vehicle across radar and infrared wavelengths. The multi-spectral inlet shield includes a plate disposed in front of the air inlet port. The plate is sized to visibly eclipse the air inlet port, when viewed from a direction perpendicular to the plate. The plate is supported in this position by a plate mount or splitter that extends from within the air inlet port and attaches to the plate. A support may optionally combine with the splitter to support the plate in this position. Air passes behind the plate and into the air inlet port via a channel defined around at least a portion of the plate.

Abstract: Various embodiments of the invention relate generally to systems for providing active vertical control of an airship. More particularly, at least one embodiment of the invention relates to a system for actively controlling the aerostatic lift of an airship by manipulating the ratio of air to lifting gas contained within the airship, and thus the overall mass of the airship. This manipulation is accomplished by actively compressing and/or decompressing the lifting gas or internal air, with the resulting pressure differential borne primarily by the hull and/or an internal pressure tank depending upon the configuration.

Abstract: A system for the hookup of either a manned or unmanned vehicle with a second vehicle which may be refueling. These vehicles may be both airborne, one airborne and the other on the ground or both on the ground. A probe extending from a first vehicle which may be refueled is joined to a paradrogue or “flycatcher” at the end of a boom on a second vehicle which may be a refueling vehicle. In bringing the probe into the paradrogue an optical sensor on one of the vehicles is employed in conjunction with optical beacons on the other vehicle with the sensor measuring the relative motion between the probe and the paradrogue and generating a control signal for controlling motion of the probe relative to the paradrogue. The positioning of the probe relative to the paradrogue is accurately controlled during the fueling operation by a reeled cable mechanism utilizing a reel which is driven to wind one end of the cable there around to retain the cable in a tensioned state.

Abstract: The present invention relates to a new type aircraft. The aircraft includes the airframe and wing, characterized in that the transverse section of airframe has an oblate (oval) profile with corrugated area on the ventral of airframe; the aircraft has uneven friction areas on the underside surface of wing; there are fireproof & anti-wear layers on the envelopes of airframe ventral and friction areas; the said fireproof & anti-wear layers have tire rubber material. When the aircraft is in motion with high velocity, the friction with air is increased, which produces bigger lift with more aircraft load and shortened takeoff & landing distance of aircraft, meanwhile the safe peril to aircraft caused by the shear transformation of wind in flight is prevented effectively; the fireproof & anti-wear layers on the envelopes of airframe ventral and friction areas have an effect on higher anti-wear proof and longer aircraft life.

Abstract: Wake vortices are made less detectable or reduced in their effect on nearby vehicles by re-orientation of vorticity about an axis in the direction of vehicle motion to transverse vorticity interacting with the longitudinal vorticity. The re-orientation may be by a flapping foil, and arrangements of a plurality of foils moving toward or from each other may be used. Alternatively, fluid may be injected longitudinally between opposite surfaces each having a port so that selective suction through the ports alternately attaches the fluid to the surfaces to deflect the fluid from the longitudinal direction and generate transverse vortices. Oppositely rotating vortices may be formed by separators extendable from each surface to engage the deflected fluid, and extension of the separators may be varied to control vortex trajectory. The transverse vortices may be intermittent, selected for speed, or made asymmetric for maneuvering.

Abstract: The present invention provides an improved lift system for an aerial crane incorporating a wing, coanda and curved surface. The arrangement of the wing, coanda and curved surface use and induce airflow to create additional lift through an increase in airflow mass, density and velocity. A different configuration of the wing, coanda and curved surface can be used to propel a vehicle.

Abstract: A throttle lever that for being pivoted by a pilot of an aircraft may include a guidance device that is integral with the lever and capable of interacting with first and second guide tracks. The first guide track allows the lever to be moved to continuously control the reverse thrust speed. The second guide track has a plurality of detents for receiving the guidance device so that the lever may take different positions, each of which controls a particular forward engine speed. An auxiliary guide track allows the lever to be moved to continuously control the forward speed of the engine.

Abstract: A wing for an aircraft has a passive jet spoiler for providing yaw control by increasing drag on the wing. The spoiler comprises an inlet located near the leading edge of a lower surface of the wing and at least one outlet formed on the lower surface or on an upper surface of the wing. An internal passage connects the inlet and each outlet for allowing air to pass from the inlet to the outlet. The air exits the outlets generally normal to the respective surface of the wing, causing a laminar flow to separate from the surfaces downstream of each outlet. The separated flow increases the drag on the wing, producing a yawing moment on the aircraft. Selective placement of the outlets on the upper and lower surfaces limits undesirable roll and pitch moments. Valves are provided for selectively controlling the amount of air passing through the spoiler.

Abstract: The invention relates to a force assistance module (10) for providing a load-dependent assistance force, in particular for a lowerable overhead luggage compartment in an aircraft, comprising a housing (18), a spring system for generating the assistance force, of which spring system one end is coupled pivotally about an axis (Z) in the housing (18) and the other, opposite end defines a force application point (P), a force-transmitting device fastened to or in the vicinity of the force application point (P) for transmitting assistance force to a location remote from the force assistance module, a support (36), which is mounted rotatably in the housing (18) and on which a path (40) is provided, along which the force application point (P) is displaceable back and forth between a first end point (A) and a second end point (B), and an adjusting device (52), which interacts with the support (36) and a load sensor and which as a function of the load detected by the load sensor rotates the support (36) in order to var

Abstract: Methods and apparatuses for cable launching airborne devices (e.g., unmanned aircraft) are disclosed. In one embodiment, an apparatus includes an elongated structure, e.g., a tower, boom or derrick. At least one flexible elongated member (e.g., a cable or rope) can be attached toward one end to the structure and toward another end to the ground or another structure to form an elongated launch path. A cradle, which can carry the airborne device, can also be movably attached to the flexible elongated member and can be accelerated along the launch path. As the cradle decelerates, the aircraft can be released into flight.

Abstract: An injection molded windshield is provided for a vehicle. The injection molded acrylic or polycarbonate windshield enables vehicle shape design flexibility while achieving lower aerodynamic drag. The injection molded windshields offer additional benefits for the crew by increasing visibility area with larger windshields while reducing aero noise. The vehicle includes a body and an injection molded window attached to the body. The injection molded windshield is shaped to conform to the fuselage. The injection molded windshield is formed of at least one of an injection molded acrylic or polycarbonate material. The injection molded windshield is impact and ballistic tolerant.

Abstract: Methods and apparatuses for launching unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can belaunched from an apparatus that includes a launch carriage that moves along a launch axis. A gripper carried by the launch carriage can have at least one grip portion in contact with the aircraft while the launch carriage accelerates along the launch axis. The at least one grip portion can move out of contact with the fuselage of the aircraft as the launch carriage decelerates, releasing the aircraft for takeoff.

Abstract: The invention is a helicopter that includes a fuselage with a longitudinal axis, a main rotor and tail rotor; and right and left wings mounted to said fuselage. The right and left wings having at least a portion of which are rotatable from a horizontal position wherein they produce lift in forward flight, to an at least partially downward position wherein they act as landing struts.