Abstract: An aerial vehicle safety apparatus includes a safety mechanism, a drive mechanism, an ejection mechanism, and a control mechanism. The safety mechanism is used for securing safety of at least one of an aerial vehicle and an object outside the aerial vehicle. The drive mechanism includes at least one drive unit serving as a drive source of the safety mechanism. The ejection mechanism ejects the drive mechanism together with the safety mechanism. The control mechanism controls operations of the drive mechanism for the drive mechanism to drive the safety mechanism after the ejection mechanism starts ejection of the safety mechanism.

Abstract: A supply drop assembly for delivering one or more payloads via an aerial vehicle, the assembly comprising a payload body configured to receive a payload; and one or more wings attached to the payload with a connector or integral to the one or more wings; wherein when the supply drop assembly is dropped from the aerial vehicle, the one or more wings start rotating thereby generating lift and slowing the rate of descent of the payload as it falls downwards to a recipient.

Abstract: A traction kite anchor device has a base provided at an end of at least one kite line and a release member able to move relative the base by a hand of a user of the kite. A trip arm is pivotally connected to the base to move between a first rotational position relative the base and a second rotational position relative to the base. The trip arm carries a latch that can lock and release a catch of a chicken loop upon moving the release member relative the base.

Abstract: An aerial vehicle safety apparatus includes an expandable object, an ejection apparatus, a bag-shaped member, and a gas generator. The expandable object is wound or folded in a non-expanded state and generates at least any of lift and buoyancy in an expanded state. The ejection apparatus is coupled to the expandable object by a coupling member and ejects the non-expanded expandable object into air. The bag-shaped member is provided in the expandable object and wound or folded together with or separately from the non-expanded expandable object, and expands the non-expanded expandable object by at least partially being inflated like a tube. The gas generator is provided in the expandable object and inflates the bag-shaped member by causing gas generated at the time of activation to flow into the bag-shaped member.

Abstract: An emergency landing apparatus for an aircraft and a method of operating the emergency landing apparatus is provided. The emergency landing apparatus comprises: one or more rocket motors arranged to eject efflux in order to provide upwards thrust to control descent of the aircraft during emergency landing of the aircraft; and control circuitry configured to: cause the one or more rocket motors to eject efflux and provide upwards thrust to control descent of the aircraft during emergency landing of the aircraft; and cause redirection of the efflux ejected by the one or more rocket motors, during the emergency landing of the aircraft, in order to reduce the upwards thrust provided by the one or more rocket motors.

Abstract: A conventional parachute requires a velocity pressure during descent in order to open the parachute. As a result, a minimum descent distance and time are required from the beginning to the end of the parachute opening operation and use at low altitude has to be restricted. In order to remedy this issue, an airtight tube and a compressed gas device are provided together in a section of the parachute having the largest annular shape when the parachute has been opened. The tube is annularly expanded by the pressure of the gas, and the parachute is forcibly deployed and opened.

Abstract: A parachute deployment apparatus for use with an aircraft, including a deployment body with an internal cavity, the deployment body configured to house a parachute to be deployed through an upper opening of the internal cavity, a firing mechanism configured to release a pressurized gas into the internal cavity of the deployment body, wherein the apparatus includes a cap that engages with the upper opening to close it prior to deployment and is configured to be projected from the upper opening upon release of the pressurized gas into the internal cavity of the deployment body, and wherein the cap is connected to the parachute.

Abstract: A system and method for resisting an uncontrolled descent or uncontrolled flight condition of an aerial vehicle, the system including a parachute having shroud lines attached to a canopy, a housing to store the parachute, an inflatable tube that attaches to and is stored in the housing, the tube having a distal end with a connector that connects to the shroud lines, and a source of fluid that couples to the tube and selectively introduces fluid into the enclosed interior of the inflatable tube to inflate the tube and force the distal end of the tube and the attached parachute out of the housing and away from the aerial vehicle, wherein the tube tethers the parachute to the aerial vehicle.

Abstract: Devices and methods for rescuing people from high-rise facilities, for example, upper floors of multi-storey buildings. A rescue device from a high-rise building includes several flexible spokes interconnected on one end to form a pyramidal figure, wherein the spokes are located on the edges, an aerodynamic deceleration element fastened to the spokes, connectors located between the adjacent flexible spokes, in so doing the connectors are located at some distance from the ends of the flexible spokes, a buffer element fastened in a point of connection of the flexible spokes and a means of fastening an object to be rescued fastened in the point of connection of the flexible spokes on the other side with respect to the buffer element, in so doing each of the flexible spokes is embodied as curved sideways from a central axis of the device.

Abstract: The rotorcraft escape system is deployed from a helicopter or gyroplane to provide clearance from the overhead rotor blades for occupants escaping from the aircraft in an emergency. Each occupant of the rotorcraft is provided with an escape container having a parachute and ejection device (rocket, spring, or combination of the two) therein. When escape from the rotorcraft occurs, each seat of the rotorcraft rotates to face laterally outward, and the ejection mechanism of the escape container is actuated to eject the container and the person wearing the container laterally from the rotorcraft. An inflatable stem extends from the escape container to a plurality of inflatable ribs in the canopy. A compressed air tank provided with the container rapidly inflates the pneumatic stem and ribs in the parachute canopy, thereby providing extremely rapid deployment of the parachute canopy with minimal loss of altitude for the escaping occupant.

Abstract: A reefing slider for providing improved line management and canopy deployment characteristics of a ram air inflated airfoil type canopy. During initial descent of the parachute the slider, secured by retaining elements, is held against the canopy in the upper reefing position where it mechanically restricts canopy deployment while giving the canopy time to achieve proper orientation following the drop from the launching aircraft. Upon sufficient air flow into the canopy cells, the retaining elements separate, releasing the slider and enabling full opening of the canopy.

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 reefing slider for providing improved line management and canopy deployment characteristics of a ram air inflated airfoil type canopy. During initial descent of the parachute the slider, secured by retaining elements, is held against the canopy in the upper reefing position where it mechanically restricts canopy deployment while giving the canopy time to achieve proper orientation following the drop from the launching aircraft. Upon sufficient air flow into the canopy cells, the retaining elements separate, releasing the slider and enabling full opening of the canopy.

Abstract: The invention is an aircraft having an inflatable wing connected to a base unit, with the inflatable wing inflated with a lifting gas such as helium. The inflatable wing has a series of cell structures, and may be configured with ballonets to selectively introduce and expel outside air within the inflatable wing to vary the buoyancy and/or airfoil properties of the inflatable wing. The aircraft is particularly useful at low speeds and in thin atmospheres (such as at high Earth altitudes and on Mars), and can be used for interplanetary missions to explore planetary bodies, such as moons and planets, having atmospheres.

Abstract: A reefing slider for providing improved line management and canopy deployment characteristics of a ram air inflated airfoil type canopy. During initial descent of the parachute the slider, secured by retaining elements, is held against the canopy in the upper reefing position where it mechanically restricts canopy deployment while giving the canopy time to achieve proper orientation following the drop from the launching aircraft. Upon sufficient air flow into the canopy cells, the retaining elements separate, releasing the slider and enabling full opening of the canopy.

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 reefing slider for providing improved line management and canopy deployment characteristics of a ram air inflated airfoil type canopy. During initial descent of the parachute the slider, secured by fastening elements, is held against the canopy in the upper reefing position where it mechanically restricts canopy deployment while giving the canopy time to achieve proper orientation following the drop from the launching aircraft. Upon sufficient air flow into the canopy cells, the fastening elements retaining the slider are broken, releasing the slider and enabling full opening of the canopy.

Abstract: A personal flying apparatus has a substantially horizontal element having a lower surface adapted to acted on by a wind upwardly so as to produce a wind-generated lifting force, and an inflatable element connected with the substantially horizontal element and filled with gas which is lighter than air so as to produce a gas-generated lifting force, so that both the wind-generating lifting force and the gas-generating lifting force jointly lift the flying apparatus to allow it to fly.

Abstract: An aerodynamic wing with a leading edge inflatable strut and at least one inflatable rib strut, wherein the struts are provided with a connection air pathway that allows the leading edge strut to act as a manifold for the inflation of the connected rib struts. Preferably, the connection air pathway is provided with a valve mechanism for selectively isolating the connected rib strut from the leading edge strut.

Abstract: An aerodynamic wing formed by a flexible canopy with integrated inflatable, elastically deformable members integrated into the lifting surface. Preferably, the elastically deformable member extends and contracts the lifting surface depending on forces experienced by the wing. In one embodiment, the wing comprises an inflatable leading edge kite.

Abstract: An improved ram air canopy is disclosed having a top skin formed of a plurality of substantially rectangular top skin pieces. Each top skin piece has areas of reduced width at predetermined locations. The areas of reduced width result in a specific tension pattern of the top skin so as to reduce distortion. The increased tension pattern of the top skin better maintains the modeled desired airfoil shape of the canopy.

Abstract: A ram air parachute of the present invention includes specific cross porting of the ribs between certain cells to create a two-stage or multi-stage deployment. Cross ports between certain sets of cells have reduced or no conductance. In this manner, the center cells of the canopy open first, slowing decent, before the outer cells. The staged deployment reduces the opening forces on the pilot particularly in high speed flights.

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 parafoil recovery system capable of autonomously controlling the descent profile of a payload to a recovery area and maneuvering the parafoil to execute a soft landing in the recovery area is disclosed. A descent profile management system determines wind speed and direction, altitude, heading, and position of the payload based on sensor input. The descent profile management system also determines a gliding flight path profile from the launch point to the desired recovery area. A flare and stall maneuver is executed at the end of the landing sequence by braking the parafoil to slow the vertical descent speed and groundspeed for a soft landing. The pitch attitude of the payload can be adjusted by the descent profile management system to prevent nose-first impact with the ground. The parafoil canopy is released from the payload upon touchdown to prevent the canopy from dragging the payload on the ground after landing.

Abstract: An aerodynamic wing with a leading edge inflatable strut and at least one inflatable rib strut, wherein the struts are provided with a connection air pathway that allows the leading edge strut to act as a manifold for the inflation of the connected rib struts. Preferably, the connection air pathway is provided with a valve mechanism for selectively isolating the connected rib strut from the leading edge strut.

Abstract: An improved ram air canopy is disclosed having a top skin formed of a plurality of substantially rectangular top skin pieces. Each top skin piece has areas of reduced width at predetermined locations. The areas of reduced width result in a specific tension pattern of the top skin so as to reduce distortion. The increased tension pattern of the top skin better maintains the modeled desired airfoil shape of the canopy.

Abstract: A ram air parachute of the present invention includes specific cross porting of the ribs between certain cells to create a two-stage or multi-stage deployments. Cross ports between certain sets of cells have reduced or no conductance. In this manner, the center cells of the canopy open first, slowing decent, before the outer cells. The staged deployment reduces the opening forces on the pilot particularly in high speed flights.

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 emergency parachute 1 comprises an umbrellalike body 10 which has an outer cloth 11 and an inner cloth 12 and is formed in bag shape, an inflator 15 which is inserted in an opening part 121 of the inner cloth 12 and fills a gas into the umbrellalike body 10, a suspension band 16 which holds a person, and a rope set 17 which couples the umbrellalike body 10 and the suspension band 16. The outer cloth 11 and the inner cloth 12 of the umbrellalike body 10 are coupled by a plurality of coupling cords 14, and when the gas is filled, the outer cloth 11 and the inner cloth 12 generate curved surfaces toward the same direction. Also the inflator 15 ignites an ignition device by pulling a tractive cord 30, and a gas producing agent within a gas producing chamber is exploded and the gas is jetted from a jet.

Abstract: A canopy-type parachute is provided which includes improved stability features and lends itself to relatively easy assembly. Integral valves promote stability of the airfoil by not allowing rapid deflation of the airfoil, and their location and orientation within the airfoil promote structural rigidly of the overall airfoil, even out to the front top edge of the airfoil. The valves in one configuration bias against a vertical, loaded rib which tends to provide a consistent taut and planar surface for the valves to bias and act against.

Abstract: An inflatable kite (150) that includes a plurality of longitudinal inflatable tubes (54). The kite includes transverse inflatable tube (53) at the rear end of the kite. When the kite is inflated, the front end has a larger cross-sectional area than the rear end. When inflated the rear edge and the side edges are coplanar. Air vents (57, 157) are provided. The kite may be inflated and launched manually or by an automatic launcher.

Abstract: The balloon support apparatus for a hot air balloon ride comprises a doughnut shaped sleeve engaged within a crown area of an envelope of the hot air balloon. The sleeve contains a lighter than air substance, such as helium, in an amount sufficient to elevate the balloon envelope, the sleeve having a volume which will accommodate expansion of the lighter than air substance when heated to approximately 350.degree. F.

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 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 paraglider having ram-air inflated left and right wings and supported above a pilot by suspension lines, the wings consisting of foldable and flexible sheet material and defining front openings to receive ram-air to inflate the wings in flight, the combination comprising; fluid inflated spar tube means extending spanwise in stiffening relation to the wings, to assist in supporting and shaping the wings in flight; spar tube means extending in such proximity to the front openings as to resist tuck under and collapse of the wings, at low angles of attack; spar tube means consisting of material which is flexible and foldable when the spar tube means is not inflated.

Abstract: Airfoil canopy for paragliders made of non-porous cloth and comprised of a number of parallel primary air chambers (12) having upper surfaces (14), lower surfaces (16), open front ends (18), tail ends (20) and ribs (22). Secondary chambers (30) are provided within each primary chamber together with an opening (36) to the secondary chamber and a flap or curtain member (40) for blocking the back flow of air out of the secondary chamber in the event of air pressure loss in the primary chamber.

Abstract: A life parachute including a canopy formed of pieces of fabric sewed together, sheaths extending from the center of the canopy in a spoke-wise manner, and an inflatable envelope connected to a compressed gas container by way of a conduit. The inflatable envelope has a main body in the center thereof and legs extending spoke-wisely from the periphery of the main body; the legs and the main body are interconnected and inflatable. The number of legs is equal to that of the sheaths. The free ends of the legs are inserted into the corresponding sheaths and then secured onto the canopy so that the main body of the inflatable envelope can be maintained at the central portion of the canopy.

Abstract: A balloon parachute is described that inflates at a controllable rate to gradually slow the descent of an attached instrument package. This balloon parachute is in the form of a pyramid that is closed on all sides in all three dimensions. The balloon parachute is tethered to an instrument package by means of a fabric loop attached to the peak of the parachute pyramid. The inflation of the balloon parachute is effectuated by the use of a set of openings in the peak, just above the loop attachment. As the balloon parachute and instrument package descend, air enters the balloon parachute through the openings in the peak thereof and gradually inflates the balloon parachute to its full pyramidal shape. A burble fence is attached to the base of the pyramid on all sides in order to provide additional drag and rotational stability, and to avoid a penduluming motion of the parachute upon its descent.

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: Device for accelerating the opening and/or the extension of aviation devices, such as canopy, square or gliding parachutes, among others, has an air space (4) at the base (7) and along the circumference of the canopy (2). The air space (4) has for example the form of a hose or of an air-impervious hem which is under high air pressure in operative conditions, so that when the wrapper is opened this air space stretches out in a very short time and the aviation device opens after a fall of only 20-30 m.

Abstract: An improved, cross braced airfoil for a wing-type parachute which is composed of an upper panel having a front edge and a rear edge and angularly oriented rib panels secured to the top panel and extending downwardly away from the top panel to a generally fore and aft row of suspension line attachments.

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: 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.

Abstract: The invention provides a pressure flow control device of the type used primarily to maintain both vertical and horizontal stability and manueverability in a predetermined fluid environment. The device includes the first skin of predetermined configuration, a second skin of predetermined configuration disposed in substantially spaced apart configuration relation from the first skin and a plurality of third skin disposed in interconnecting relation between the first and second skins. One or more spors are defined by the first, second and third skins. One end of the spors at least partially defines a leading edge of the device and the opposite end of the spors at least partially defines the trailing edge of the device. One or more holonomic ports are formed in at least one of the third skins and a jet port is defined by at least a portion of one or more of the spors being open at its aft end.

Abstract: A warning and signaling system includes a kite attached to a flexible tether rope wherein one end of the rope is secured to a person or a lifeboat. The kite is made from a material having high visibility and includes radar reflective material. The tether rope may carry an antenna for a radio transmitter and receiver. An optional inflatable chamber provides rigidity to the kite. The kite may be provided with a tail having radar reflective swatches attached thereon.

Abstract: Upper and lower rectangular canopies are connected by a plurality of transversely spaced vertical airfoil shaped ribs to define a plurality of longitudinal air flow chambers. Suspension lines are connected to selected ones of the ribs and are arranged in longitudinally spaced and transversely extending rows. Cells are defined which consist of a plurality of adjacent chambers between any two transversely adjacent suspension lines. Some of the cells have three chambers while others have two chambers. The suspension line dimensions and trim angles are used to impart multiple pressure centers and different arc anhedral shapes to improve various characteristics of the parachute including opening, stability and accuracy.

Abstract: A parachute assembly includes a canopy, a harness connected to the canopy by lines, the canopy having an apex and a basal perimeter. Envelopes in the canopy defined by a plurality of generally triangular inflatable gussets extend from adjacent the apex to adjacent the basal perimeter and taper outwardly towards the basal perimeter. The assembly includes a source of pressurized gas and flexible conduits connecting the gas source to the gussets. One or more valves for releasing the gas from the source through the conduits to the inflatable envelopes and manually operable valves to release the pressurized gas into the conduits and envelopes to inflate the gussets.

Abstract: The air scoop opening at the leading edge of a flexible, ram-air inflated airfoil canopy, is framed between curved lip sections extending tangentially from the upper and lower surface members of the canopy to prevent airflow separation adjacent the leading edge and the drag producing effect thereof. A baffling curtain extends across the air scoop opening.

Abstract: A system for transferring cargo at sea by helicopter includes an automatily activated self inflatable apparatus for reducing the velocity of the cargo if jettisoned or inadvertently dropped into the sea and for keeping the cargo afloat until retrieval may be accomplished. The cargo is lifted by a support sling attachable to a helicopter suspension cargo hook and simultaneously connected to a second sling in parallel to the helicopter through the rapidly deployable retardation and floatation device. Release of the support sling causes the cargo to drop and initiate deployment and inflation of the ribs of the parachute thereby retarding the cargo's descend and providing buoyancy for its floatation.