52 results about "Wing membrane" patented technology

The invention relates to an inclined rotating wing aircraft with telescopic wing membranes. The inclined rotating wing aircraft comprises an aircraft body, a center shaft, a main transmission mechanism, first to third power units, an outer side rod, a support rod, a main wing membrane, a flight controller, and first to third undercarriages. The inclined rotating wing aircraft disclosed by the invention is improved on the basis of the structure of the traditional four-wing aircraft, and an inclined rotating structure of an inclined rotating four-rotary wing aircraft and a wing membrane structure of a flapping wing aircraft are added. According to the inclined rotating wing aircraft, the structural state of the inclined rotating wing aircraft includes a ground sliding state, a four-rotary wing flying state and a high-altitude cruising state; when the inclined rotating wing aircraft is in a ground movement state, the undercarriages contact with the ground, the main wing membrane is open, and the forward movement, backward movement, left rotation movement, right rotation movement, climbing movement and downgrade movement of the aircraft are realized by regulating the speed of four rotary wings; the movement state of the aircraft on the ground is realized under the action of the undercarriages, and the movement state is impossible to realize by the inclined rotating four-rotary wing aircraft and the flapping wing aircraft; and the climbing movement and the downgrade movement can be realized without changing the state of the aircraft, so that the energy consumption is reduced, and the complexity of a control program is prevented.

An aircraft comprising a fuselage, a sail wing appended to the fuselage, the sail wing having a sail wing root chord length, and wherein the sail wing includes a sail wing leading edge spar, a sail wing membrane attached to the sail wing leading edge spar, and a sail wing trailing edge wire located at a trailing edge of the sail wing membrane, the aircraft further comprising a wing surface extension, located aft and at an inboard area of the sail wing trailing edge wire, the wing surface extension having a wing surface extension root chord length, and wherein the wing surface extension includes a wing surface extension membrane attached to the sail wing trailing edge wire, and a wing surface extension trailing edge, and wherein the wing surface extension trailing edge is reflexed such that the wing surface extension trailing edge is positioned upwards at a first angle with respect to a plane formed along a centerline of the aircraft and along the lower surfaces of the sail wing. The wing surface extension is further configured to affect a reduced nose-up pitching moment, and to produce a more even coefficient of lift along the wing of the aircraft.

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.

The invention discloses a flapping rotor with an angle of attack control device, which belongs to the technical field of micro-aircraft. Including flapping rotor, angle of attack control device and limit device; flapping rotor includes main beam, short beam, inclined beam and wing membrane; Stopper and angle of attack controller; a groove is made on the angle of attack controller, and the baffle moves up and down in the groove; the stopper is used to control the range of motion of the baffle. The other includes deformation sheets and limit beams. By changing the thickness of the deformation sheets or adjusting the distance between the connection point of the short beam and the inclined beam and the main beam, the angle of attack of the airfoil when the flapping rotor is shot up is controlled. The limit beam is used to Limit the deformation of the flapping rotor when the flapping rotor is down; by controlling the angle of attack of the flapping rotor during the flapping process, on the basis of maintaining the positive lift, the negative lift is effectively reduced, and the average lift of the micro flapping rotor aircraft is improved. The energy utilization rate of the aircraft is improved.

The invention discloses an IPMC (Ionic Polymer Metal Composite) driven simulated dragonfly wing flapping robot and relates to a simulated wing flapping robot. The IPMC driven simulated dragonfly wing flapping robot is provided with wing veins, wing membranes, wing IPMC driving parts, wings, a robot body, circuit controllers, copper sheet electrodes, robot body IPMC driving parts and fixing shafts; the wing veins are arranged on the wings; the two wing IPMC driving parts are arranged on the wings; deformation of the wings is achieved due to change of the wing shapes; the two robot body IPMC driving parts are arranged at the bottom of the robot body; one ends of the robot body IPMC driving parts are fixed on the robot body and the other ends are arranged on wing root portions of the wings; the wings are hinged to the robot body which drives flapping of the wings; the copper sheet electrodes enable the circuit controllers and the wing IPMC driving parts or the circuit controllers and the robot body IPMC driving parts to be connected through leads; the circuit controllers, the robot body IPMC driving parts and the fixing shafts are arranged on a robot frame; fixing shaft holes in the wings are hinged to the fixing shafts to achieve rotation between the wings and the robot body.

The invention discloses an externally pressed six-wing tubular membrane and a method for manufacturing the membrane. The externally pressed six-wing tubular membrane comprises a six-wing tubular membrane body, a six-wing lined pipe, a composite filter membrane, a depression bar, a core tube, an electrode lead, an external layer carbon net, an organic filter membrane, an internal layer carbon net, and a prefabricated membrane tube. The composite filter membrane is composed of the internal layer carbon net, the organic filter membrane, the external layer carbon net and the electrode lead. The six-wing membrane is composed of the six-wing lined pipe, the composite filter membrane, the depression bar, the core tube and an end cover; flow guide circular holes are arranged between adjacent wing boards outside the core tube; the composite filter membrane is fixed between two adjacent wing boards by the depression bar and distributed on the outer surface of the six-wing lined pipe in a rising and falling way; both ends of the six-wing tubular membrane are sealed and fixed by the end cover and an epoxy resin; the electrode lead is led out from the sealed position of the epoxy resin. According to the externally pressed six-wing tubular membrane, the high-efficiency filtration, and pollution-preventing and self-cleaning functions are realized, and the manufacturing process is simple, thus the externally pressed six-wing tubular membrane is applied to the large polluted water or waste water treatment engineering.