Abstract: A flight assembly and glider possessing bilateral, flexible, and collapsible wings and associated method of flight are provided. The flight assembly may include a central frame that may encapsulate a human operator. A wing frame may include at least a pair of wings that couple to the central frame, wherein each wing may include one or more pivotal connections. To control the extension and retraction of the pair of wings, a control lever network may be incorporated within the central frame and the wing frame. The control lever network may include wing sail deployment, flight deceleration and parachute wing conversion features.

Abstract: An unmanned aerial vehicle (UAV) is provided, which includes a main body; a plurality of frames each extending from the main body; and a plurality of thrust generating devices respectively mounted on the plurality of frames, each of the thrust generating devices including a propeller. The propeller includes a hub that provides a rotation axis of the propeller, and rotates according to an operation of the thrust generating device, and a pair of blades, each of which is pivotably mounted on the hub, and generates a thrust or lift while rotating around the rotation axis as the hub is rotated. The blades are pivotably interlocked with each other such that the blades are aligned to a folded position in which the blades are parallel with each other on the hub in a first arrangement or aligned to an expanded position in a diametric direction of a rotating region of the propeller in a second arrangement.

Abstract: The airborne vehicle recovery method and apparatus enables radiosonde users to reliably recover launched radiosondes and provides new and unique opportunities for research and data acquisition with balloon launched radiosondes. Airborne vehicles such as radiosondes are disposed in a flight body adapted for propulsionless, gliding navigation for returning to one of several designated landing sites for recovery. Onboard electronics including a navigation computer, flight computer, and lightweight battery are employed for selecting a landing site, computing a heading and direction, and actuating flaps for pursuing a propulsionless, gliding path to the landing site.

Abstract: One example includes a dual-aircraft system. The system includes a glider aircraft configured to perform at least one mission objective in a gliding-flight mode during a mission objective stage. The system also includes an unmanned singlecopter configured to couple to the glider aircraft via a mechanical linkage to provide propulsion for the glider aircraft during a takeoff and delivery stage. The unmanned singlecopter can be further configured to decouple from the glider aircraft during a detach stage in response to achieving at least one of a predetermined altitude and a predetermined geographic location to provide the gliding-flight mode associated with the glider aircraft, such that the glider aircraft subsequently enters the mission objective stage.

Abstract: A fuzzy logic controller for controlling towed objects includes comprises a winch controller to control extension or retraction of a tow cable based on a control signal. A fuzzy logic controller controls a speed at which the tow cable is extended or retracted. The fuzzy logic controller includes an altitude controller storing a membership function defining ranges for a delta altitude variable and determines an altitude control signal based on the range for the measured delta altitude variable. A gain controller stores respective membership functions defining ranges for speed, heading rate, and cable length variables and determines a gain control signal based on the ranges for the determined speed, heading rate, and cable length variables. A command controller determines the control signal based on the gain control signal and the altitude control signal.

Abstract: The present disclosure relates to an unmanned aerial vehicle (UAV) able to harvest energy from updrafts and a method of enhancing operation of an unmanned aerial vehicle. The unmanned aerial vehicle with a gliding capability comprises a generator arranged to be driven by a rotor, and a battery, wherein the unmanned aerial vehicle can operate in an energy harvesting mode in which the motion of the unmanned aerial vehicle drives the rotor to rotate, the rotor drives the generator, and the generator charges the battery. In the energy harvesting mode regenerative braking of the generator reduces the forward speed of the unmanned aerial vehicle to generate electricity and prevent the unmanned aerial vehicle from flying above a predetermined altitude.

Abstract: Sail deflection, from large resultant moments, creates excess aerodynamic twist and limits hang glider performance. Incorporating a rear spar and sail attachment system, as a design feature, allows control and definition of this critical performance component. Hang gliders with this design feature will produce more total lift which in turn will produce lower stall speeds and less drag.

Abstract: A partially-inflated rigid-structure glider is a portable or collapsible gliding apparatus that a user can transport in a carrying case. The gliding apparatus includes a rigid yet collapsible frame, tension membranes over both on the wings and tail, and inflatable bladder, a pair of drogue brakes, and a left and right steering mechanism. The pair of drogue brakes is located on opposing sides of the gliding apparatus and create drag on its respective side in order to turn the gliding apparatus either left or right. The user can activate either drogue brake with the left and right steering mechanism, which are control lines attached to each drogue brake. The tension membranes are fitted over the frame so that the gliding apparatus has an airfoil shape in order to create lift with the wings and tail while the gliding apparatus is in flight.

Abstract: The system includes a keel fitting that can be rigidly attached directly to the keel of the hang glider. It also includes two elongated frame members symmetrically mounted on opposite sides of the keel fitting. At least one electrical motor is mounted on each frame member and there are at least two propellers, each in driving engagement with a corresponding one of the electrical motors. The system further includes an electrical power unit mounted on the back of the pilot. The electrical power unit includes at least one battery and a pilot-actuated control circuit to vary the electrical power supplied to the electrical motors. The system gives the pilot the capability of taking off from a flat terrain. Once airborne, the system is not operated and the hang glider can then be used as an unpowered one.

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 flying apparatus having a frame configured to couple to a high voltage tether system, and at least one motor module mounted to the frame, the module including a holding structure attached to the frame, a rotating structure, including a rotor shaft, configured to rotate relative to the holding structure, a rotor attached to the rotor shaft and a plurality of motors attached to the holding structure, each including a drive shaft configured to engage with the rotor shaft, wherein the motors are configured to receive electrical energy from the tether system and drive the drive shafts to create a torque on the rotor shaft to thereby rotate the rotor and create lift to fly the apparatus from the ground to a desired position aloft while remaining coupled to the tether system.

Abstract: A projectile and a compact carrying and launching case in combination. The projectile includes foldable wings which when unfolded resemble a plane. The compact carrying and launching case includes a two piece housing that is pivotally attached to each other about a hinge/launching mechanism. When closed, the two piece housing encloses the plane in its folded position. When opened, the hinge/launching mechanism can be pulled to a cocked position and then released forcibly moves the projectile such that it releases from the launching mechanism and is capable of flying.

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: Ejection seats have been on the road towards perfection ever since they were first made. But there are still too many situations that can't be avoided with just one function, ejecting and parachuting down. We have attempted to take it a few steps further: adding a small jet pack and glider wings. This way, pilots and astronauts can apply it in their emergency escape routines. Using the small jet pack, astronauts can push themselves on their way back to the blue planet and pilots can get themselves out of a danger zone quickly. This can also be a wonderful outdoor sport or activity.

Abstract: A multi-use recreational product fully assembled constitutes a toy that can be towed on water and on snow and in the air, and when airborne, the rider can detach the tow rope and use the product as a glider. The toy disassembled, separates a wing section from a fuselage or tail section. The wing section is independently usable as a wakeboard; longitudinally extending fins which provide stability in movement of the assembled product in water and air and easier lift-off into the latter, also aid in control of the wakeboard in water and on snow. The fuselage or tail section is independently usable as a surfboard or water ski, wakeboard, snowboard or kneeboard. As a surfboard, it would be inverted so that thin vertical fins on the wider tail end of its upper surface when used as the fuselage, would extend into the water. Control elements exist on the appropriate surfaces of the sections to enable rider steerage of the sections and/or assembled product.

Abstract: Characterized in that in a first stage are loaded or produced on board in a mother aircraft at least a product or mixed of products to act on forest fires, pests or atmospheric phenomena; in a second stage the said product is stored in a glider container with gliding flight ability and equipped with a precision guidance system; in a third stage the glider container is dropped from the mother aircraft and guided towards the release point of the load; in a fourth stage the glider container releases of its interior the load of product on the release point, and in a fifth stage the glider container is recovered for a following reusing.

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 aircraft has a flight termination system that allows flight of an unmanned aircraft to be quickly and efficiently terminated. The flight termination system separates one of the control surfaces of the aircraft, such as a wing, from a fuselage of the aircraft, while one or more other control surfaces connected to the fuselage. The separation may be accomplished by firing one or more explosive bolts to release a clamp that connects the control surface to the fuselage. The separation causes an asymmetry in configuration that results in a rapid crash of the aircraft. The flight termination system causes termination to be effected in small flight footprint, without use of powerful explosives, and without a large cost in weight or volume. The flight termination system may be used in unpowered or powered aircraft.

Abstract: The present invention provides a practical method for UAVs to take advantage of thermals in a manner similar to piloted aircrafts and soaring birds. In general, the invention is a method for a UAV to autonomously locate a thermal and be guided to the thermal to greatly improve range and endurance of the aircraft.

Abstract: This invention is a “bubble glider” which is a modified hybrid of the hot-air balloon and the glider. It has a distinct undulating forward motion. A simple bubble glider has a soft air-bubble, a hard air-bubble and a thin body and is made of 0.25 mm PVC sheets. It is used inside a completely sealed water tank with an external control unit. An operator uses the control unit to vary the buoyancy of the soft air-bubble and completely control the motion of the bubble glider. Specifically, the glider can glide forward and backward, change direction, take off and land vertically, float motionless and so on. In generalization, bubble gliders can be of many shapes and sizes, and made of, practically, any material. They can be designed to operate in totally closed containers or in open environments such as open water tanks, reservoirs, lakes, oceans and skies.

Abstract: A glider including a center section configured to receive and support an operator thereon, and a pair of air-foil shaped wings extending generally outwardly from the center section. The glider is configured such that when the glider supports the operator thereon the glider is glidable down an incline in the ground effect zone of the incline, and is configured such that the glider cannot sustainably glide above the ground effect zone.

Abstract: A The set of conjugated components to build a ultralight type airplane, in particular a constructive concept that has as end product a ultralight type airplane with a general configuration visually similar to the DEMOISELLE. In summary, the inventive concept has as purpose to enable that a handcrafted and ancient concept airplane is mass-produced, using modern resources, which characterizes by a better aerodynamical sustentation, in particular as a result of parts which are specially designed to carry out the known functions with extraordinarily improved results. In a general concept, without detailing the components in their specific constructions, we define the airplane obtained based on the conjugated components such as the fuselage (1); wings (2); empennages (3); landing gear (4); systems (5) which include the control (6) with rotular ends and fuel systems consisting of a metallic tank (7) fixed on the same level of the engine, with a vent, cover and a system cutting valve and propelling unit (8).

Abstract: A tricycle-type wind-propelled toy land vehicle includes a sail with reliable tangle-free boom control. Both the disposition of the boom and the front wheel steering is actuated by a radio frequency remote control system. The vehicle further includes a skid plate surrounding the front wheel to prevent tip-over. The front wheel is steered by a worm gear drive which is self-locking. Boom control is provided by a guided cable system or, in an alternate embodiment, a direct gear drive to rotate the mast. In yet another embodiment, boom control is provided by a sliding leaf spring which passes underneath the boom and attaches to a track on the underside of the boom.

Abstract: An airfoil for use in kites, movable wing aircraft and fixed wing aircraft has a straight spar inserted into a sleeve in the arcuate leading edge of a flexible wing panel. The resultant forces on the spar dynamically shape the airfoil. The airfoil is reinforced by battens between the leading edge and the trailing edge of the wing panel. Flight control is maintained through control lines warping the airfoil.

Abstract: A wind propelled vehicle. The wind propelled vehicle has a frame. A plurality of wheels is connected to the frame. A mast is connected to the frame and a boom is connected to the mast. A sail is connected to the mast. A motor is operably connected to the boom via a string. The string has a boom end and a motor end. The string is connected to the boom at the boom end and the string is connected to the motor at the motor end. The motor is remotely controlled via a remote control unit. To propel the wind propelled vehicle the motor manipulates the boom in response to control signals generated by the remote control unit to adjust the sail relative to wind. In a preferred embodiment the sail is a rigid wing sail.

Abstract: A lift system is described for free-falling persons including a lift body with a belt system which can be detachably attached to a person. The lift body is designed so that it defines a direction of flight in the longitudinal axis of the person, and a device for detaching the lift system in a free-fall phase, a flight phase or a landing phase from the person. The lift body has an overall delta-wing shaped design.

Abstract: A wind propelled vehicle defining a center of gravity. The wind propelled vehicle has a frame. A rear axle is connected to the frame at its rear portion and two rear wheels are rotatably connected to the rear axle. The center of gravity of the wind propelled vehicle is forward of the rear axle. A front wheel is rotatably connected to the frame at its forward portion. A mast is connected to the frame and a boom is connected to the mast. A sail is connected to the mast and boom. A motor is operably connected to the boom and to the front wheel. The motor is also physically connected to the boom. The motor is remotely controlled via a remote control unit. To propel the wind propelled vehicle the position of the sail is adjusted relative to the wind. Sail position adjustment is achieved by the motor turning the front wheel and manipulating the position of the boom in response to control signals generated by the remote control unit.

Abstract: In order to provide a compact, high-performance drive device for aircraft, in particular for power gliders, which comprise a propeller which is driven by a motor, preferably by an electric motor, and the blades (6) of which can be tilted towards the propeller shaft (15) by way of a joint and in the tilted-out position pass through a running gap (5) for the propeller formed between the nose, in which the generally minimal conditions of space are utilized in an optimum manner and which ensures the necessary aerodynamic properties of the aircraft, the invention proposes that the motor (10) should be arranged in front of the propeller in the space bounded by the nose (4). In this way, the interior of the aircraft as far as the running gap (5) for the propeller is made available for the pilot or the aircraft passengers, so as to ensure optimum use of the said interior and the length of the aircraft can be kept short.

Abstract: It is difficult for free-falling persons to modify substantially their flight trajectory by performing body movements. The lift system of the present invention allows the user of said system to determine himself and in a large amount the direction of his flight. The lift system allows the person to modify substantially her trajectory with her limbs and using lift bodies as well as lift surfaces This lift system is particularly well suited for use as sport equipment for parachutists.

Abstract: A flier structure including a fuselage extending from front side to rear side and a weight body connected with front end of the fuselage. A port wing and a starboard wing respectively leftward and rightward extend from the fuselage. A left tailfin and a right tailfin respectively extend from rear sides of the port wing and starboard wing. The bottoms of front edges of the port wing and starboard wing are respectively connected with a left and a right flow deflecting wings. The rear sides of the left and right flow deflecting wings are respectively spaced from the port wing and starboard wing by a predetermined distance. The left and right flow deflecting wings are respectively connected with the left and right sides of the fuselage. The disconnected portions between the left flow deflecting wing and port wing and the right flow deflecting wing and starboard wing respectively form two flow deflecting spaces.

Abstract: A flier structure including a fuselage extending from front side to rear side and a weight body connected with front end of the fuselage. A port wing and a starboard wing respectively leftward and rightward extend from the fuselage. A left tailfin and a right tailfin respectively extend from rear sides of the port wing and starboard wing. The bottoms of front edges of the port wing and starboard wing are respectively connected with a left and a right flow deflecting wings. The rear sides of the left and right flow deflecting wings are respectively spaced from the port wing and starboard wing by a predetermined distance. The left and right flow deflecting wings are respectively connected with the left and right sides of the fuselage. The disconnected portions between the left flow deflecting wing and port wing and the right flow deflecting wing and starboard wing respectively form two flow deflecting spaces.

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: 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 system and method for wind-powered flight, comprising a low-speed, high-drag leading aircraft such as a kite, tethered to a low-speed, low-drag trailing aircraft, such as a glider. The leading aircraft is launched, and when the leading aircraft ascends into winds which are significantly greater than winds at the ground level and the takeoff velocity of the trailing aircraft, the leading aircraft begins to tow the trailing aircraft. The trailing aircraft becomes airborne and can be flown at a low air speed to maintain a constant drag on the leading aircraft, which in turn provides thrust to maintain the trailing aircraft aloft at the lower altitude.

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: A remotely controllable toy surface vehicle has the capability of deploying wings on command and to attain flight in the absence of any air interactive propulsion mechanism. In an alternate embodiment of the invention, the fixed wings are first pitched to keep the vehicle on the ground or water until a takeoff velocity is reached; after which the pitch of the wings is remotely adjusted for takeoff and flight.

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 bearing and control system to execute flaring and curved flight manoeuvres of a load-bearing paraglider (1) with a parachute (2) with trailing edges (9, 9a, 9b) to execute the manoeuvre, whereby control lines (10) connected to trailing edges are rolled onto an unrolling device (16, 172), with a load unit (3) and with an unrolling device (12a, 173) to unroll lift webs (174) wound on it to lower the load unit (3), whereby the trailing edges (9, 9a, 9b) are moved to execute a manoeuvre by the weight of the load unit (3), and a gear unit (171) and a brake (178, 179) are between the control lines (10) and the load unit (3).

Abstract: The safe and secure mass commercial air transportation to eliminate or, at least, mitigate dramatically the impact of a baggage-born explosion or fire in a cargo hold of a passenger airplane, menacing technical malfunction or failure of the airplane, or a human error, and to accommodate concurrently additional passengers aboard, owing to separating the cargo hold far sufficiently beyond the airplane and further placing the cargo hold into, at least one, cargo airtrailer in the form of an immense glider(s) driven by the airplane so that baggage and cargo are carried in the airtrailer, or accommodating the passengers aboard a passenger airtrailer (glider) driven by the airplane.

Abstract: This invention is an aircraft orientation system that locates the earth's horizon, in order to determine the aircraft's attitude in the pitch and roll axes. The invention uses infrared sensors on the aircraft aimed to the sides, front and rear of the aircraft. These sensors are grouped in pairs, and detect the differences in heat levels between the left and right of the aircraft, and forward and behind the aircraft. The invention utilizes the physical condition that the earth's surface is typically measurably warmer than the sky. This difference is used to provide a reference for an aircraft regarding the attitude of the aircraft. In an alternative embodiment, a third pair of sensors detects the aircraft's vertical orientation (inverted/non-inverted) to the ground. The aircraft's attitude is determined by comparing the electrical outputs of infrared sensors, which can be used to provide a feedback to the aircraft control system to keep the aircraft in a neutral attitude.

Abstract: An aircraft system intended for gliders and low power-to-weight aircraft, to aid the pilot in locating updrafts associated with the buoyancy of humid air in the convective layer of the atmosphere, namely moist thermals. The system comprises a pair of laterally spaced hygrometers, generally at the wingtips. Four types of hygrometer units are described; resistive, piezoelectric, spectrometric, and capacitive. Humidity data is transmitted to the cockpit by telemetry links, of which four types are also described; by dedicated wiring, by carrier current using wingtip position lights wiring, by modulated infrared beams, and by low-power radio waves. The system monitors the difference of humidity between left and right sensors, and also the rate of change of humidity of one or both sensors as a function of time.

Abstract: The deployable wing of the present invention comprises an internal structure having diverging leading edge spars attached to a keel spar and cross spars to form a delta wing configuration. This internal structure is enclosed within a volume defined by a fabric sail having an upper section, a lower section, and fabric ribs disposed therebetween. This fabric sail volume is internally pressurized through a ram air intake at the nose stagnation point. This deployable wing can be folded, extracted from an aircraft and deployed in the air.

Abstract: The present invention relates to an improved model airplane for purposes of scientific education and competition. Model airplanes in the prior art are either bad at flying, or do not look like real airplanes; and all are short of a collision prevention device. By means of some special positioning adapters for fixing the wing section firmly to the body and by adding a collision buffer piece to the nose, the model airplane according to the present invention is not only good at flying, but also safe and durable to use. The model airplane according to this invention is, therefore, best suitable for the above-mentioned purposes.

Abstract: An air-launchable gliding sonobuoy store includes a canister enclosing an flatable membranous wing folded in a collapsed state with an electroacoustic system. After launching, the wing inflates and a steering mechanism controls the wing glide path by skewing the trailing edge thereof. Upon reaching the sea, the wing serves as a buoy with the electroacoustic system transducer depending therefrom.

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: 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 wind driven craft comprising a body and a pair of wings extending therefrom. The wings are pivotally connected to the body of the craft. The wings provide lift and thrust to the craft such that it is able to move under influence of the wind.

Abstract: An air launched, air-to-surface missile which has extended range and reduced radar cross section for low observability is disclosed. The design uses a triangular cross section fuselage, for low profile drag and reduced weight, a very high aspect ratio, such as 22.5, folding wing for low induced drag and three folding tail fins for less profile drag. The wing is a composite structure of graphite/epoxy sparcaps and 2024 aluminum alloy core with glass/epoxy skins and full depth Nomex.

Abstract: An aircraft comprises a body portion and a pair of wings extending from either side of the body portion. An upward step is formed in the underside of the body portion in the center of the aircraft, and defines a rearwardly facing riser surface. The riser surface extends outwardly toward the wing tips, terminating substantially inwardly of the wing tips so that a majority of the length of the underside of each wing is uninterrupted by the riser surface. The step is located at the front-to-rear center of gravity of the aircraft, and provides an area of low pressure adjacent the riser surface to maintain the rear portion of the aircraft down. The aircraft can be constructed either as a full-scale or a small-scale aircraft.

Abstract: An off weight lift wing for a skier and the like is provided and consists of a pair of airfoils each supported on an opposite end of a crossbar which extends across the top of a frame with a harness that secures the frame to the back of the skier. The lift wing will create a balanced lift to the upper body of the skier and allow more agile body movement when skiing, as well as extending the length of a ski jump.