Abstract: A platform including two winged aircraft are tethered during flight by a single tether near their respective centers of gravity. The tether is windable about a reel, so that a distance between the aircraft can be changed during flight. The aircraft contain avionics configured to enable autonomous flight using natural wind gradients. One aircraft imposes aerodynamic forces on the other, through the tether, while flying at an altitude where wind speed is significantly different than wind speed at an altitude of the other aircraft. The two aircraft cruise back and forth within a maximum distance from a station on the ground. Cruise conditions are established using an iterative computer algorithm which utilizes flight measurements. The aircraft communicate information between each other, and the ground, and contain a payload which performs a useful function at high altitudes.

Abstract: The present invention is a ram air rigid structure glider, which uses both ram air inflation and a rigid structure in order to produce the necessary aerodynamic lift to glide through the air. The frame uses two main structural beams, the spar and the keel, to form the general shape of the wings and the tail. The hubs and the network of lines expand the structure laid out by the spur and the keel. The hubs are evenly placed along the spur, and the network of lines are connected and crisscrossed in between the hubs. The sail is a piece fabric wrapped around the frame and has a plurality of cells, which are evenly spaces throughout the sail. The plurality of cells allows the sails to be inflated by ram air pressure. The pilot pod carries the user in the supine position and is attached to the frame.

Abstract: A multi-celled ram-air parachute possessing one or more internal one-way valved air passages between at least two parachute cells to maintain positive air pressure within the parachute for the purpose of maintaining shape and rigidity when less than optimal airspeed is present thereby increasing a user's control and safety.

Abstract: A sail wing for a lightweight aircraft comprising a membrane; a front spar; and a tensioned rear wire attached to a trailing edge of the membrane, such that when the front spar is bent to match a curve of the tensioned trailing edge of the sail wing membrane, the sail wing membrane has substantially little or no twist, and results in substantially little or no induced drag.

Abstract: An apparatus for removing harmful gas components out of the earth's atmosphere is a free-flying autonomous lightweight aircraft with an onboard gas processing system including gas separation or extraction devices, and inlets and outlets connected to the devices. Solar cells and/or thermoelectric generators provided on the craft produce electrical energy to operate the individual devices. The system may include a cryogenic closed-loop circulation system that participates in liquefying the extracted gas components. The apparatus is preferably a lighter-than-air craft like a dirigible. A method of extracting harmful gas components from the atmosphere involves flying the apparatus at a prescribed altitude level and operating the gas processing system to remove the harmful gas component from the atmosphere, then returning the apparatus to earth to offload the liquefied stored harmful gas component.

Abstract: In one aspect, a hybrid airship including an outer shell, a plurality of helium filled gas envelopes, and an all-electric propulsion system can have a high-aspect ratio wing shape. In some embodiments, the hybrid airship may be launched using buoyancy lift alone and aerodynamic lift may be provided by the all-electric propulsion system. In one aspect, a photovoltaic array and a high energy density power storage system may be combined to power the propulsion system making the propulsion system regenerative. The high-aspect ratio wing shape provides low drag, and can allow the hybrid airship to fly at an altitude of at least about 100,000 ft. By continuously recharging the power storage system, the hybrid airship in accordance with some embodiments can stay aloft for months or even years. The hybrid airship may function as a military intelligence, surveillance, and reconnaissance and communications relay platform.

Abstract: An airborne enhancement device comprises a harness adapted to secure to a body of a user. A collar is coupled to the harness. A wing is coupled to the collar by at least one structural member. The wing is adjustably deployable. The wing is configured to adjust between an extended position and a folded position. A pack is coupled to the collar and is configured to store the wing in the folded position.

Abstract: A personal aircraft device (“PAD”) and a powered personal aircraft device (“PPAD”) configured to be ridden and/or releasably connected to a person or user. The personal aircraft device can be configured to provide a large array of maneuvers during sky diving or free fall, and perform somewhat as a lifting device requiring a parachute landing and/or alternatively can be configured to glide to a safe landing. The personal aircraft device and powered personal aircraft device according to the present invention provide for high performance, speed and/or maneuvering of a person or user during free fall, and can provide increased or significantly increased gliding capability versus free falling or deployment of a high performance parachute.

Abstract: A wing for a traction kite, etc comprises a plurality of cells formed by chordwise-extending ribs (3), valved openings (6) to the cells allowing ram air to inflate the wing. By changing the initial cut-out of the material forming the cells near wing tips (7, 8), compared with that of the cells central to the wing, it is possible to alter the aerodynamic forces at wing tips (7, 8). This allows attachment of flying lines (9, 10) to wing tips (7, 8) only, despite the wing having no framing to maintain its spanwise shape under the loading of flying lines (9, 10). The increased aerodynamic forces at wing tips (7, 8) are achieved by making the aerofoil profiles of the cells progressively more reflexive towards wing tips (7, 8), by giving wing tips (7, 8) a residual twist increasing their angle of incidence, by placing the centres of pressure of the cells near wing tips (7, 8) somewhat forward of the pivot line of the wing, etc.

Abstract: A personal aircraft device (“PAD”) and a powered personal aircraft device (“PPAD”) configured to be ridden and/or releasably connected to a person or user. The personal aircraft device can be configured to provide a large array of maneuvers during sky diving or free fall, and perform somewhat as a lifting device requiring a parachute landing and/or alternatively can be configured to glide to a safe landing. The personal aircraft device and powered personal aircraft device according to the present invention provide for high performance, speed and/or maneuvering of a person or user during free fall, and can provide increased or significantly increased gliding capability versus free falling or deployment of a high performance parachute.

Abstract: An unmanned flying vehicle comprises an autonomous flying wing having at least two wing portions arranged substantially symmetrically about a center portion. Each wing portion is pivotally attached to each adjoining portion such that the wing portions are foldable for storage and openable for deployment. A preferred form is the so-called seagull wing having four wing portions. The vehicles may be programmable from a mother aircraft whilst being borne to a deployment zone using a data link which may be wireless.

Abstract: A flapping wing flying device comprises wings that pivot about a pivot axis extending generally perpendicularly to an elongate body of the flying device, and wings that move relative to said elongate body of the flying device, so that the entire leading edge of each of the wings is moved away from and toward to the body of the flying device during flight.

Abstract: The airwing structure according to the present invention comprises of an airfoil structure, a main frame, and a means for providing a downward and a forward tension on the airfoil structure. The airfoil structure further comprises of a leading edge, a trailing edge, a left edge, a right edge, a central wing root, and a plurality of chord lines. Moreover, the airfoil structure comprises of a substantially flexible surface skin and the airfoil structure also has a downward arc for producing lift by aerodynamic forces exerted thereon. The main frame attached to the airfoil structure comprises of a leading bar and a supporting bar. The leading bar is fixedly attached to the leading edge supporting and maintaining the leading edge from collapsing. The supporting bar is attached to the leading bar and attached to the trailing edge supporting and maintaining the airfoil structure from collapsing.

Abstract: Aircraft, in particular a hang-glider, with a flexible wing and a pilot's position preferably arranged beneath it, from which space the aircraft can be controlled, wherein the trailing edge of the flexible wing can be locally raised and/or lowered by means of a transmission means leading from said trailing edge to the pilot's space.

Abstract: An aircraft is composed of two elongated inflated, flexible tubes diverging from each other from a nose of the aircraft toward a trailing edge. First and second membranes span the upper and lower surfaces of the tubes respectively to provide upper and lower airfoil surfaces. One of the two membranes is connected to a length of cable extending from the tip end of one tube to the tip end of the other at the trailing edge. Trim is provided by a fixed flap composed of flexible membrane stretched between the cable and another, parallel cable. The nose ends of the tubes are secured to a propulsion motor-mounting plate assembly at the nose end of the aircraft, and the opposite ends of the tubes are secured to plates at the ends of the trailing edge. The cables are secured to the plates at the ends of the trailing edge, and these plates are also used to support horizontal stabilizers.

Abstract: Distress signal kits comprise a parafoil for carrying aloft various emergency or distress signals such as radar reflective materials, lights, flares, distress flags or smoke signals. Preferably the parafoil itself is colored International orange and contains a U.S. Coast Guard-approved distress signal (BLACK SQUARE AND CIRCLE) on both top and bottom surfaces. The parafoil can be used to raise a spinnaker sail attached to a vessel or swimmer. The spinnaker can also carry radar reflective components and/or distress flags, and can be fitted for other survival uses.

Abstract: An aircraft structure, such as a glider including a wing having a substantially flat, upper, first surface and a convex, lower, second surface. The wing first and second surfaces converge to a leading edge and a trailing edge. A weighted member is used to determine the center of gravity of the wing as being 15 to 25% of the length of the chord from the leading edge. The weight structure is fixed to the wing and may also serve as a structural member.

Abstract: An ultralight helicopter has a pair of counter-rotating rotor assemblies which in combination yield zero net angular momentum when rotating at equal speeds. A single motor drives both rotors through a counter-rotating bevel gear set coupled to a pair of concentrically nested output shafts. In an alternative embodiment, the motor is coupled to the rotors through a hydraulic drive system which includes a hydraulic pump and at least one hydraulic motor driving each of the rotor assemblies. The pilot is advantageously suspended in a "hang-glider" type harness from a single hang point positioned proximate the center of lift of the helicopter. A control bar is fixedly mounted to the frame and is grasped by the pilot suspended in the harness. The pilot maneuvers the helicopter in both the pitch and roll directions by manipulating the control bar. The pilot shifts his own center of gravity relative to the center of gravity of the helicopter while grasping the control bar to thereby maneuver the helicopter.

Abstract: A self-inflatable parawing comprises an airfoil made of a flexible sheet erial and having a plurality of apertures located in the lower, aft surface thereof for admitting inflating air created by the positive air pressure of the air stream flowing over the airfoil. An inflatable support frame is located in the airfoil for providing spanwise stiffness to the airfoil. The support frame is inflated by means of a compressed gas cannister connected through a controllable valve to the support frame.

Abstract: A canopy for a paraglider or a parachute. The canopy including upper and lower sides and a plurality of ribs extending between the sides and made of a mesh cloth. The upper and lower sides and the ribs define a plurality of cells which are arranged adjacent one another. Each of the cells has an opening at a front end thereof for introducing air into the canopy. The mesh cloth of the ribs includes large and small apertures disposed therein. According to one embodiment, either the large or the small apertures are arranged in matrix-like groups which are separated from one another by the other of the large and small apertures. According to another embodiment, the large and small apertures are disposed in groups which are arranged parallel to one another in the vertical direction.

Abstract: The weight-shift movements of a suspended pilot are transformed into electrical signals representative of the movements. The signals may be used as the pitch and roll input information in an interactive computerized flight simulation system. The signals may also be generated by an actual pilot of a hang glider or ultralight aircraft and used on board to control ailerons, elevators, rudders, or the like, so as to enhance the performance potentials of these types of aircraft.

Abstract: A flight control apparatus for use in an aircraft includes support structure for suspending a pilot beneath a pair of wings while permitting movement of the pilot relative to the aircraft in the forward, rearward and both lateral directions. A control system is connected between the support structure and the wings for altering the geometries of the wings during flight to vary the drag and lift characteristics of the wings and alter the direction of flight and the speed/performance range of the aircraft in response to movement of the pilot relative to the aircraft in any of the forward, rearward, and lateral directions. The geometries of the wings are altered during flight by moving the leading edges between extended and retracted positions relative to the central longitudinal axis of the aircraft in response to movement of the pilot in the forward, rearward and both lateral directions relative to the aircraft.

Abstract: A human powered hang glider has a right main wing and a left main wing, both of which are swingably attached to a post by a universal joint. A rope is stretched in a loop shape between a pedal provided at a lower part of the post and the main wing, and is fixed to the pedal and the main wing. By operation of the pedals, the main wings are flapped like a bird flaps its wing. By this flapping action of the main wings, the hand glider can take wing, whether or not an upcurrent is present.

Abstract: The device comprises an arch-like structure (3), shaped similar to a cage, which can be fixed to the motorcycle (1), essentially to its frame and sides; a parafoil sail (5), which can be mounted at the top of the cage, the sail ends being lowerable by a pedal or handle control; a propeller propulsion system (8) mounted at the rear of the motorcycle on the arch-like structure; and a clutching and declutching mechanism which, on control, drives either the driving wheel or the propeller.

Abstract: A vertical takeoff ultralight aircraft having an operator controlled high volume vane axial fan in communication with a conduit configured to direct an air stream produced by the fan to a spanwise air duct disposed forwardly of a wing including an air foil. High velocity air is discharged from the air duct and directed over the upper surface of the air foil. An induced air stream flows upwardly and rearwardly through an air flow path defined by the spanwise air duct and the air foil. The wing and air duct are configured such that the induced air stream joins the air stream discharged from the air duct to create reduced static pressure zone on the upper surface of the wing of sufficient magnitude to effect vertical lift. Fan discharge may be partially deflected rearwardly to provide horizontal thrust.

Abstract: A built-in control flap for a ram air, multi-cell, wing type canopy having a ram air inlet is located in each side of the canopy at the rear portion thereof. Each built-in control flap is separated from the adjacent center portion of the canopy between the control flaps. A seal and guide of a sheet of flexible material connects the top of each control flap to the bottom of the adjacent center portion of the canopy across the separation for directing air flow thereby when a control flap is down. Each control flap receives air flow from the ram air inlet.

Abstract: The invention provides an aerodynamically profiled structural pipe (1) comprising a supporting pipe (2) and a rear tapered part (3) of soft material. The tapered part (3) has on both sides beads (15) forced into and captively held by rearwardly open chambers (12) of the supporting pipe (2).

Abstract: An aircraft includes a nonrigid dynamically inflated airfoil wing which carries an operator. The operator is suspended by a plurality of shrouds which interconnect the wing to a control stick. The control stick position is varied to change the angle of attack of the wing. A transverse control bar is connected to the wing tips for direction control. The center of gravity of the total aircraft is rearward of the center of lift. The wing includes air intake orifices at its leading edge and at least one trailing edge exhaust aperture for inflation by airspeed relative to the wing. A spanwise tubular plenum may be employed for air flow control through the wing.

Abstract: An improved wing structure is provided having a self-induced camber. The wing comprises an aerodynamic dihedral sail structure having a fabric sail tensioned on a supporting frame comprised of lateral brace members and a longitudinal member intermediate the ends of the lateral braces. The tensioning of the sail and the configuration of the supporting frame is such that the sail assumes a dihedral shape, with the sail being caused to assume a tensioned or stressed condition along a portion of the leading edge of the sail intermediate the respective lateral ends of the sail resulting in the formation of a self-induced camber at that location.

Abstract: A very light wing, configured like a spherical segment, is intended to be used in the traction and lift of various loads. The wing includes a leading edge and a trailing edge and an inflatable armature covered by a flexible envelope. The surfaces of the wing are configured in the shape of an aircraft wing profile and the edges of the wing curve in two planes. The leading and trailing edges of the wing are oriented to intersect near the tips of the wing, and each of the tips of the wing receives a control rope via an adjusting plate. The control rope is passed through a pulley mounted on a craft to be displaced by a person through a harness. The wing can be used in sliding sports, yachting and gliding.