180results about "Microlight aircrafts" patented technology

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.

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.

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 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 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.