Abstract: A system for controlling an aircraft in response to deployment of an ejection seat may comprise a seat controller located on the ejection seat and configured to output a signal in response to initiation of an ejection sequence. An aircraft controller may be configured to receive the signal from the seat controller. A tangible, non-transitory memory may be configured to communicate with the aircraft controller. The tangible, non-transitory memory may have instructions stored thereon that, in response to execution by the aircraft controller, cause the aircraft controller to perform operations, which may comprise receiving the signal from the seat controller, receiving data signals from an operational data source, and sending command signals configured to control a component of the aircraft.

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: The invention relates to a steering unit for a wind propulsion system, the steering unit comprising a first fixed attachment means for securing a first end of a tractive cable the second end of which is secured to a device or a vehicle to which a tractive force shall be transferred, a second attachment means for attaching a number of tractive lines, the second end of which being secured to an aerodynamic wing element, a mechanical support frame connecting the first attachment means to the second attachment means for transferring a tractive force. The invention aims at providing such a steering unit with improved design for better maneuverability and stability.

Abstract: An aircraft has an emergency landing system which includes a paraglider for the emergency landing phase of the aircraft and an attitude positioning parachute for decelerating and subsequently swiveling the aircraft with respect to the flight direction. The vertical axis essentially corresponds to the direction of pull from the attitude positioning parachute.

Abstract: An aerodynamic wing formed by a flexible canopy with an internally routed canopy line for controlling the canopy profile. Preferably, the canopy line is routed through a gatherable tube secured to the trailing edge of the canopy. Tensioning the canopy line alters the canopy profile to facilitate launching the kite.

Abstract: Aerodynamic wing to propel a broad range of transport means, principally sail craft. The wing provides a single layer kite structure capable of flying without surface discontinuity, bridles, or rigid or semi-rigid structure. All stresses within the wing are converted into pure tension and transferred through the wing surface outward to attachment lines. The wing shape defines a large diameter self-supporting rolled over leading edge of an airfoil and the wing profile approaching the trailing edge exhibits increasing convexity. The wing is useful to propel, or supplement propulsion to, transportation means.

Abstract: A kite safety, control, and depowering device for a kite having an airfoil with leading and trailing edges, at least two control lines attached to the airfoil and a control flying bar attached to at least two of the control lines. The device features a continuous trim and safety flying line disposed at their lower ends over a rapid depowering apparatus. The depowering apparatus includes means for capturing and rapidly releasing an expansion disposed on the trim line, such that when rapid depowering is required, a simply release mechanism may be actuated to change the angle of attack of the airfoil rapidly.

Abstract: An arch style traction kite which includes a wing or wing envelope which has a leading edge which, when viewed in plan with the wing or envelope laid in a horizontal plane, is concave in a centre section of the wing or envelope and straight or convex in plan near the tips of the wing. The concave leading edge feature can be incorporated in any arch style traction kite such as ram air inflated kites, single skin pneumatic tube framed kites and bridleless ram air inflated kites with flexible leading edge rods or in kites incorporating a combination of the features of such kites.

Abstract: A kite safety device for a kite having an airfoil with leading and trailing edges, at least two control lines attached to the airfoil and a control flying bar attached to at least two of the control lines. The device features a trim line having a hollow central passageway, sized and shaped to fit slidably through a central opening in the control flying bar. A safety flying line is attached at its first end to a first point adjacent a midpoint along a centerline extending from the leading edge to the trailing edge and attached through said passageway at its second end to a fixture providing a point for attachment of the flying line to a harness. When the control flying bar is released a user may rotate beneath the kite and when the safety flying line is tensioned, the kite will begin to stall and the kite will descend.

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: An aircraft is provided having an inflatable parafoil canopy wing and a suspended fuselage. The wing is constructed such that, when inflated, it has an airfoil configuration having leading and trailing edges, thereby producing lift by interaction with air encountered by the leading edge. A central compartment confines a buoyant gas which causes the total volume of the wing to be varied in response to the degree of inflation with the buoyant gas. With sufficient inflation, the aircraft is capable of vertical take-off and landing (VTOL).

Abstract: A small radio controlled flying device propelled by a thermal engine (20) with pusher type airscrew (19) for remote sensing, the device being capable of short take-off and landing and flying at maximum speed of 35 Km/h. The device includes a pod and wings, the pod (1) being a rigid tricycle carriage dismountable by disengagement of substantially pyramidal jig with rear base (2) and front apex (7), lower plane (3), two lateral planes (4, 5) and an upper plane (6). The base is a welded one-piece element that includes the engine, the airscrew, a tank and the radio control. The apex is a welded one-piece element. The lower plane and the two lateral planes include spars (11, 12) assembled at the base and as the apex. The lower plane includes at its three end angles two rear wheels (8) and a front wheel (9), the front wheel being provided to protrude towards the front in the apex and the wheels being low pressure tires.

Abstract: A rescue system for rescuing persons by air, particularly from tall buildings or airplanes, has a receptacle with at least one parachute or paraglider. A harness for the parachute or paraglider is connected to the receptacle. The receptacle is constructed as a closable package with a substantially cuboid or suitcase-like shape and also has an opening mechanism. The harness for the parachute or paraglider is disposed inside the closed receptacle.

Abstract: A deployable wing that is folded so as to fit into a carrier such as an airplane that is released and automatically with the aid of parachutes to deploy and fly a given distance without assistance other than steering to reach a given destination and a propeller driven by a gas powered engine is actuated to propel the wing an extended distance. A guard is disposed adjacent to the propeller to assure that the lines of the parachutes do not get tangled into the propeller blades.

Abstract: A parachute has its suspension lines divided into groups, each group connected to the load through a linear actuator. During descent of the parachute, foreshortening of an actuator or of any group of adjacent actuators causes the parachute trajectory to move in the direction of the foreshortened actuator. Multiple parachutes connected to a single load, with each parachute being connected to the load through an actuator, can similarly have their trajectory controlled. The trajectory of the parachute can also be changed by a system of normally foreshortened actuators which lengthen by actuation. Simultaneous, rapid shortening of all actuators just before ground impact can be used to reduce the descent velocity at ground impact.

Abstract: A para-plane (parachute or parafoil airplane), ultralight, or the like is provided with a ducted propeller or fan to increase efficiency of the powerplant, thus reducing the size of the powerplant required. In addition, the duct may reduce propeller and/or engine noise and enhance safety for pilot, passengers and bystanders. Axial vanes may be provided upstream or downstream of the propeller within the duct to counteract the torque effect of the propeller. In another embodiment, a novel inflatable parafoil may be provided to reduce the effort required to initially inflate a prior art parafoil and reduce the incidence of ground strikes of the parafoil. The inflatable parafoil may be inflated with a buoyant gas such as helium or hot air to further reduce ground contacts and provide limited buoyancy to the aircraft.

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 object of the invention is to provide an escape apparatus which enables persons to promptly escape from an elevated place such as a building and an aircraft, and is easy to handle. An aerial floating flier such as airfoil or a parachute is folded and contained in a case, and by throwing out such a case or an aerial floating flier in folded state into the air, the aerial floating flier is spread in the air, thereby allowing to escape from a site of an accident by hanging from the aerial floating flier and descend slowly on the ground.

Abstract: A ram air wind power device. Parallel chambers of a sail fabricated from flexible material provide structure to the sail when filled with ram air. The chambers have openings at each end and each opening contains a valve. The openings to the parallel chambers provide two leading-trailing edges of the sail. One of the leading-trailing edges will function as a leading edge if the openings on that edge is facing into the wind, in which case the valves of the chambers at that edge will be open and the valves in the chambers at the other edge will be closed. When the other leading-trailing edge faces into the wind that edge becomes the leading edge. Preferred embodiments include kites, parachutes and gliders.

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: An improved ram air, multi-cell wing type canopy with suspension flares has its lower surface shortened to provide an enlarged inlet; one flare is directly attached to its upper surface. A modification has a channel provided to direct air flow over the upper surface. Scoops under the lower surface at the rear end provide protection against the canopy uncontrollably folding under.

Abstract: An aircraft comprises a vehicle (1) suspended in flight by a steering control rod (68) pivotally mounted to the body of the vehicle and having outer ends (12, 14) connected to the lower ends of load suspension lines (3, 5, 6) connected at their upper ends to a flexible wing portion (2) of a ram air inflatable type of airfoil canopy. Steering of the aircraft is by pivotal movement of control rod (68) to manipulate the load suspension lines and thereby the canopy surfaces. The aircraft may be radio controlled by a radio receiver (112) in the vehicle body for operating the speed of a drive motor (36) for driving a propeller (38) and a steering drive motor (98) coupled to the control rod (68) by a suitable linkage system. Battery pack (104) is removably mounted in the vehicle body for providing power to the receiver and motors therein. The radio controlled aircraft is controlled by a remote transmitter which controls the steering and speed of the aircraft.

Abstract: A vehicle, especially an air vehicle or water vehicle, is described which has at least one wing. This wing includes an upper and/or a lower wing covering as well as an area provided at the wing which is movable between a first position in which the air or water resistance of the wing is small and a second position in which the air or water resistance is increased. Furthermore, an actuation mechanism in engagement with the area for carrying out the movement is provided. The area is formed as deformable area and defines a portion of the upper and/or lower wing covering.

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: Disclosed is a parawing with an automatic canopy withdrawing mechanism having a canopy, a frame to which the canopy is fastened and on which a pilot can be carried, a propeller mounted on the frame, and a plurality rows of suspension lines interconnecting the canopy and the frame. Also mounted on the frame is an automatic canopy withdrawing mechanism including a reel which may be operated to pull back the suspension lines for withdrawing the canopy. Further, a front pulling rope interconnecting the reel and two rows of suspension lines near the leading edge of the canopy, a rear pulling rope interconnecting the reel and the trailing edge of the canopy, and a plurality of guide rollers for guiding the movement of the front pulling rope and the rear pulling rope are provided so that the suspension lines and the canopy may be withdrawn by the automatic canopy withdrawing mechanism. With the canopy and the suspension lines being withdrawn.

Abstract: The curve profile of the front edge of an air-filled wing or sports kite of a type which is guided from the ground is maintained without the use of any bracing system. This curve profile, which is very important in determining the flight characteristic of the wing, is controlled exclusively by adjusting the various lengths of balance lines. Two symmetrical line bundles or connecting balances radiate from end points of at least two steering lines and are fastened to various points on the wing base. If so desired, central balance lines can be connected to the wing base without intermediate fastenings. The fastening points on the wing base are located chiefly at the front portion of the wing base. The lengths of the various balance lines preferably increase from the side edges to the middle. However, the rate at which the balance line length becomes greater can increase, decrease, or remain constant, at least in certain areas.

Abstract: Retention apparatus for a parachutist to a parachute of the type having a flexible wing having casings. The apparatus includes a retention assembly adapted to retain the parachutist, and a device for piloting permitting the parachutist to modify the shape of the aerodynamic surface plane by displacement of his center of gravity G.

Abstract: Load lines connect chordwise spaced portions of a ram air inflated, airfoil canopy to spaced anchors connected to a pilot supporting vehicle frame on which a forward thrust producing unit is removably mounted. The geometry of the assembled aircraft enhances take-off inflation of the canopy, establishes a stable flight frame when airborne, and enables simple engine throttle control of the thrust producing unit to regulate climb, descent and level flight. Common control is applied for both ground steering of the vehicle frame and air-borne steering of the canopy.

Abstract: Load lines connect chordwise spaced portions of a ram air inflated, airfoil canopy to spaced anchors connected to a pilot supporting vehicle frame on which a forward thrust producing unit is removably mounted. The geometry of the assembled aircraft enhances take-off inflation of the canopy, establishes a stable flight frame when airborne, and enables simple engine throttle control of the thrust producing unit to regulate climb, descent and level flight. Common control is applied for both ground steering of the vehicle frame and airborne steering of the canopy.

Abstract: An improved parachute utilizing a ram air design and having an upper surface connected to a lower surface by a plurality of rib members and forming a plurality of chambers therebetween. The end chambers are smaller than the center chambers and this increases the lift-to-drag ratio of the parachute. The parachute has a substantially elliptical planform so as to increase the aspect and glide ratios of the parachute.

Abstract: A hybrid wing assembly is made up of a load supporting center frame with laterally outwardly extending, articulated, wing sections. A parafoil is attached to the wing sections by flexible lines in flight, and rigid rods hold the parafoil in spaced relation to the wing at rest. Control lines extend from the parafoil to the user for controlling the assembly.

Abstract: A light aircraft having a parachute-wing, a single propeller, and means for controlling the direction and speed of the aircraft by simple control lines to the canopy. The carriage is supported by at least two support lines which are secured at attachment points spaced apart laterally with respect to the fore and aft direction of the craft. By ensuring that the support lines are of different lengths a side-to-side suspension bias is created which compensates for the propeller torque reaction. This is a permanent adjustment which allows the aircraft to be balanced so that control of flight may be effected without difficulty. Preferably, the carriage is constructed to use a longitudinal base strut on which a foldable tricycle under carriage is mounted. An upright strut is pivotally mounted to the base strut. The frame of the pilot's seat is used as an integral structural member which rigidly links the base strut to the upright strut in the running condition. The two struts and the sear frame form a triangle.

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: A load carrying aerial device having an inflatable component which is inflatable from a collapsed configuration to an inflated aerofoil configuration and which is maintained inflated in flight by air introduced into the component through an air intake as a result of relative motion of the component and the surrounding air. The leading edge of the component throughout its length or substantially throughout its length is closed or maintained closed in flight and is inclined at such an angle to the longitudinal axis of the component that the internal stagnation pressure of the air within the component at the leading edge produced by the relative motion of the component and the air always exceeds the external static pressure of the air on the leading edge, thereby ensuring maintenance of the profile of the leading edge in flight.