tilt-wing aircraft with retractable membrane

Abstract

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.

Description

technical field [0001] The invention belongs to the technical field of aerospace power machinery, and in particular relates to a tilting-wing aircraft with a retractable wing membrane. technical background [0002] The current research direction of quadrotor aircraft is mainly to achieve attitude stability control, multi-unit group control, etc., but these controls cannot avoid some shortcomings of quadrotor aircraft, especially slow flight speed, limited energy storage and not suitable for long-distance flight. Because the traditional four-rotor aircraft produces a lift difference by controlling the different speeds of the front and rear rotors, but this will inevitably cause the fuselage to produce a pitching motion, and then achieve a horizontal forward flight action. This forward method will make the traditional quadrotor aircraft horizontal Forward flight and vertical lift affect each other. On the other hand, the traditional four-rotor aircraft is limited by the desig...

AI Technical Summary

Problems solved by technology

[0004] The mechanical efficiency of flapping-wing aircraft is higher than that of fixed-wing aircraft. It generates lift and thrust by flapping up and down. The flapping process of the wing aircraft consumes a lot of energy, and the flapping wing aircraft cannot carry a large amount of energy, so there is a big obstacle to long-distance flight

Images