180results about "Hang glider aircrafts" patented technology

A vertical takeoff and landing aircraft, using for vertical lift and lateral thrust a redundant plurality of essentially similar electrically-powered and electronically-controlled thrust units mounted in a mechanically static or fixed fashion relative to one another in a substantially horizontal plane. The thrust units are situated in this planar array in aerodynamically approximate pairs, such that a complete failure of a single thrust unit would not substantially compromise the ability of the aircraft to maintain flight.

An ultralight coaxial dual rotor helicopter having a substantially L shaped frame. Attached to the back of the frame is a vertical shaft engine, and a pair of yaw paddles for controlling yaw of the craft. The drive shaft connects to a belt drive at the top of the frame, which transmits the engine power to a transmission and coaxial drive gear for driving the rotors. Crank actuators are provided for tilting the rotor axis to control the pitch and roll of the craft. A pilot seat and ballast tank are attached to the front of the frame. The ballast tank may be filled with a volume of water to balance the craft for the weight of the pilot. The fuel tank is located behind the pilot seat on the centerline of the helicopter, such that as fuel is used and the weight of fuel in the tank changes, the balance of the craft will not be affected.

A method and apparatus are provided for constructing, operating, and marketing a vehicle that is alternatively adaptable for controlled, powered operation on the ground as an all-terrain vehicle (ATV), or in the air as a powered parachute, or for controlled, powered operation on both the ground and in the air as a flying ATV. On the ground, the vehicle is configured for controlled, powered operation over both smooth and rough terrain, as a true all-terrain vehicle.

An ultralight coaxial dual rotor helicopter having a substantially L shaped frame. Attached to the back of the frame is a vertical shaft engine, and a pair of yaw paddles for controlling yaw of the craft. The drive shaft connects to a belt drive at the top of the frame, which transmits the engine power to a transmission and coaxial drive gear for driving the rotors. Crank actuators are provided for tilting the rotor axis to control the pitch and roll of the craft. A pilot seat and ballast tank are attached to the front of the frame. The ballast tank may be filled with a volume of water to balance the craft for the weight of the pilot. The fuel tank is located behind the pilot seat on the centerline of the helicopter, such that as fuel is used and the weight of fuel in the tank changes, the balance of the craft will not be affected.

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.

Conception introduced for performing powered flight of aircraft by performing work against gravity force, using gliding wing as steady support, namely “flying elevator” conception, and aircraft developed, based on cyclorotor scheme with elaborated steering solution, continuing in flexible handling and control. Said aircraft correctly and optimally implements said conception after presented detailed modeling, simulation and analyzing, having ability for flight with exceptionally high propulsion efficiency, moderate lift to drag ratio and short takeoff and landing. Additionally, it has ability for recuperative descent and deceleration, utilizing direct driving from high torque electrical engines, which can optionally hybridized with combustion engine, and covers speed range up to limits of subsonic flight.

A combination powered parachute and motorcycle modifies an initially conventional motorcycle with the addition of various flight components to provide sustained flight for the machine. A peripheral and overhead safety structure is installed upon the motorcycle, with a second flight engine, propeller, folding propeller guard, and fuel system also installed. The flight engine and all of its systems are completely independent of the conventional motorcycle engine used for surface propulsion. A set of laterally disposed stabilizer wheels is also provided for transition from ground to flight and from flight to ground operation. Lift is provided by a folding parafoil device of either the ram air inflated or partially pneumatically inflated type. For flight operations, the lateral wheels are lowered and extended, the folding propeller guard is extended, and the parafoil is deployed behind the motorcycle, with the parafoil lifting conventionally upon attaining flight speed.

A land, water and air vehicle comprising a kayak body, two power driven mountain bike wheels and two mounting bike steering wheels. A large propeller powers the vehicle on water and in the air and a parachute is employed for air travel. The parachute is adapted to fold for storage and a tent and air mattress can also be mounted on the body of the vehicle.

A backlight unit for use in a liquid crystal display comprises a light guiding plate comprising a light exiting surface, a light reflective surface, and a light incident surface, a light source unit comprising a substrate and a light source disposed on the substrate, wherein the light source unit is disposed to face the light incident surface of the light guiding plate, and a reflecting sheet comprising a first portion facing the light reflective surface of the light guiding plate, a second portion facing the light exiting surface of the light guiding plate, and a third portion connecting the first and the second portions, wherein the third portion comprises light source exposing parts.

One embodiment of a Vertical Take-off and Landing (VToL) air-vehicle (FIG. 1.) having a horizontal rotor, a. providing lift and propulsion, and communicating at or near its centre to structural elements, or fuselage, b. Upon or within the fuselage structure is attached a platform, to which a payload, or occupant or pilot, d. is secured in such a manner as to permit a movement, or range-of-motion, of the payload, as a means of weight-shifting, or mass-balancing, of the vehicle for stability and control in flight. At least two planar elements, or descent-vanes, c.i & c.ii are connected to a structural element of the fuselage at a location which provides vertical and horizontal separation between the rotor and the descent-vanes, thus creating a tandem, biplane arrangement of two aerodynamically active elements which are aerodynamically balanced to provide stability and controllability in hovering flight, in forward flight, and in un-powered gliding and vertical descents. Other embodiments are described and shown.

Disclosed is a soaring platform that is based on biomimicry of soaring bird species and provides bird-like steering modalities and includes an air foil made of feather-like battens, articulating wings, a rudder, and modalities to manipulate the leading edge of the platform's wing spars as well as change in the wings shape in-flight.

The invention relates to a multi-purpose aircraft including at least one cockpit equipped with at least one motor-driven propeller capable of ensuring the displacement of this aircraft through the air and at least one flexible wing having an upper cloth or a flexible wall of the upper wing surface and a lower cloth or a flexible wall of the underwing defining an inflatable volume. When deployed, a leading edge and a trailing edge are defined for two different inflating systems. The aircraft includes a device or an arrangement enabling the insufflation of pressurized gas into the inflatable volume of the wing and air inlet openings distributed along the leading edge of the wing. The opening lead into the inflatable volume thereof for enabling the admission of air into the inflatable volume when in flight.

The invention provides a multifunctional unmanned aerial vehicle provided with a flexible stamping parafoil, which mainly comprises the flexible stamping parafoil (1), a cabin body (2), a propeller (12) and a skid type landing gear (15); the lower part of the flexible stamping parafoil (1) is connected with the cabin cabin (2) through parafoil ropes (10); a control mechanism (13), a modularized mission cabin (14) and an engine (11) are mounted inside the cabin body (2); the propeller (12) is mounted at the tail part of the cabin body (2); the skid type landing gear (15) is mounted at the lower part of the cabin body (2); and equipment required for different purposes is carried in the modularized mission cabin. The multifunctional unmanned aerial vehicle provided with the flexible stamping parafoil has the benefits of safety, reliability, multiple launching manners, long cruise time, wide flying range, small size, light weight, convenience in use, and wide field of use, and is an ideal unmanned aircraft.

The present invention provides a foldable wing which comprises a wing supporting skeleton, a sliding rail, a skin supporting rib, a skin and a wing movement unit. The wing supporting skeleton comprises a horizontal beam, a longitudinal beam, a wing front edge beam, a wing trailing edge beam, a fixture connector and a sliding block, The wing supporting skeleton is a triangular girder for maintaining planar and sectional shapes of the foldable wing, supporting the skin supporting rib and the skin, and sustaining an aerodynamic load from the skin and a load of a fuselage. After the triangular girder is subjected to a force of the wing movement unit, a shape and an area of the triangular girder are changed so as to achieve folding and unfolding of the foldable wing. A rotocraft and a glider using the foldable wing are also provided.

The present invention relates to a lightweight helicopter with features of coaxial, contra-rotating rotors and weight shift control. It has a rotary wing unit attached to a tricycle assembly through a hang bolt. The rotary wing unit has an engine mounted below a keel post, which drives a pair of contra-rotating coaxial rotors through a primary gearbox and a secondary gear box. The keel post is attached to a triangular control frame, the base of which forms the control bar. The keel post also supports a fuel tank connected to the engine and a tail plane having one or more articulated vertical flaps actuated by cables. The secondary gearbox is provided with a free-wheeling clutch, a pinion gear and bevel gears for transmitting the rotary movement of the engine to the counter rotating coaxial vertical shafts each carrying two rotor blades of airfoil cross section fixed by pitch bearing on teetering plates and teetering hinges to form horizontal rotors. The tricycle assembly has a pilot seat and landing gear as well as controls for operation of the engine, rotors, tail plane and landing gear. The directional control of the helicopter is achieved through the weight shift principle by manipulating the control bar, thereby causing a tilt of the contra-rotating rotors, which cause a corresponding tilt in the aerodynamic thrust of the rotors, propelling the helicopter in the required direction.

The invention discloses an unmanned power delta wing aircraft which comprises a body, a delta wing, a power system, a flight control system, an operating system and an undercarriage system, wherein the flight control system comprises a flight actuating mechanism, an onboard control unit and a ground remote control unit; the flight actuating mechanism comprises a pitch controller for controlling the delta wing to make a pitching motion and a roll controller used for controlling the delta wing to make a roll motion; the onboard control unit is connected with the pitch controller and is used for controlling the pitching motion of the delta wing; the onboard control unit is connected with the roll controller and is used for controlling the roll motion of the delta wing; the onboard control unit is connected with the power system and is used for controlling navigational speed of the aircraft; the onboard control unit is connected with the ground remote control unit in a wireless remote control mode and is used for receiving a remote control signal of the ground remote control unit. The aircraft has the advantages that a special airport is not needed, a professional pilot is not needed, the operating safety is high, the maintenance cost is low, the effective load capacity is high, the hang time is long, and the like.

The present invention relates to a lightweight helicopter, comprising of a rotary wing (1) unit and a frame assembly (2), the rotary wing consists of an engine (3) with a primary gear box (7), mounted below a keel post (8) and the keel post attached to a triangular control frame (28), the base of which forms the control bar (29), and is also provided with a tail plane (12) having one or more vertical articulable flaps (34). A secondary gearbox is provided with means capable of transmitting the rotary movement of the said engine to two horizontal rotors (9, 10) capable of pitch change. The rotary wing unit is suspended by means to a frame assembly having means (47) for pilot seating, landing gear (46) and provided with means for control of the engine, rotors, tailplane and landing gear.

The invention discloses a parafoil aircraft applicable to cylindrical space loading. The parafoil aircraft applicable to the cylindrical space loading comprises a parafoil body and a nacelle; the nacelle is entirely cylindrical, and comprises a control cabinet, a power cabinet and a load cabinet which are fixedly arranged in a laminated manner; two rope winding plates are arranged inside the control cabinet; an operation rope in the parafoil body is coiled on each rope winding plate; a main parachute cord is fixed with the both ends of a supporting rod which can be unfolded in the left-right direction and be mounted on the control cabinet; the parafoil body is unfolded by unfolding the supporting rod; and a steering engine controls the rope winding plates to rotate, so that the steering posture of the parafoil aircraft can be controlled. A motor for driving propellers arranged outside the power cabinet to rotate is mounted in the power cabinet, so that the parafoil aircraft climbs out and falls down. The load cabinet can be configured with various types of mission loads aiming at the parafoil aircraft. The parafoil aircraft applicable to the cylindrical space loading, provided by the invention, has the advantages that the high use ratio of the cylindrical space loading the aircraft can be realized; the large-area flexible punching parafoil is used as a lifting surface, so that the lower flight speed can be obtained, and the parafoil aircraft applicable to the cylindrical space loading is applicable to a long-term fixed-point reconnaissance mission; and meanwhile, the parafoil aircraft applicable to the cylindrical space loading has good vertical and transverse stability.

The invention discloses a new type one-man flight vehicle capable of vertically taking off and landing and with fixed wings. The new type one-man flight vehicle comprises wings, a support frame, engines, a rotating bearing, braces, a flight control unit, a fuselage, batteries, holding arms, a solar cell panel, an escape parachute and a lifesaving air bag. The vertical taking off and landing, low-speed flight and transition towards horizontal flight can be realized by rotating the directions of the two engines, low-speed and flexible flight can be realized without the utilization of fixed wings, and also high-speed and remote flight can be realized by utilizing the fixed wings.

The present invention relates to a lightweight helicopter with features of coaxial, contra-rotating rotors and weight shift control. It has a rotary wing unit attached to a tricycle assembly through a hang bolt. The rotary wing unit has an engine mounted below a keel post, which drives a pair of contra-rotating coaxial rotors through a primary gearbox and a secondary gear box. The keel post is attached to a triangular control frame, the base of which forms the control bar. The keel post also supports a fuel tank connected to the engine and a tail plane having one or more articulated vertical flaps actuated by cables. The secondary gearbox is provided with a free-wheeling clutch, a pinion gear and bevel gears for transmitting the rotary movement of the engine to the counter rotating coaxial vertical shafts each carrying two rotor blades of airfoil cross section fixed by pitch bearing on teetering plates and teetering hinges to form horizontal rotors. The tricycle assembly has a pilot seat and landing gear as well as controls for operation of the engine, rotors, tail plane and landing gear. The directional control of the helicopter is achieved through the weight shift principle by manipulating the control bar, thereby causing a tilt of the contra-rotating rotors, which cause a corresponding tilt in the aerodynamic thrust of the rotors, propelling the helicopter in the required direction.