Bionic flapping-wing micro air vehicle capable of realizing high control moment generation based on double-wing differential motion and steering engine gravity center change

A micro-aircraft and torque control technology, which is applied in the field of bionic flapping-wing micro-aircraft, can solve the problems of small control torque, single rectangular form of control force, and limited change range of angle of attack, so as to improve control torque, increase displacement range, and improve effective The effect of control torque

Active Publication Date: 2020-12-01
BEIHANG UNIV
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  • Claims
  • Application Information

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Problems solved by technology

[0006] The present invention aims at the present situation that the existing bionic flapping-wing micro-aircraft obtains the control moment only by controlling the deformation of the flapping membrane, and in order to solve the problem that the change range of the angle of attack is limited, the generated control moment is ...

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  • Bionic flapping-wing micro air vehicle capable of realizing high control moment generation based on double-wing differential motion and steering engine gravity center change
  • Bionic flapping-wing micro air vehicle capable of realizing high control moment generation based on double-wing differential motion and steering engine gravity center change
  • Bionic flapping-wing micro air vehicle capable of realizing high control moment generation based on double-wing differential motion and steering engine gravity center change

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Embodiment Construction

[0041] The specific implementation method of the present invention will be described in detail below in conjunction with the accompanying drawings.

[0042] The bionic flapping-wing micro-aircraft that realizes the generation of high control moment based on the differential of the two wings and the change of the center of gravity of the steering gear includes a lift system 1 , a transmission system 2 , a control system 3 and a power system 4 .

[0043] The lift system 1 is composed of left and right flapping wings, and each flapping wing is composed of a main beam 101 , a flexible beam 102 , a tension beam 103 and a membrane 104 . The wing membrane 104 is a flexible membrane made of polyimide material, and the front edge and the side edge of the wing membrane 104 are respectively wrapped into tubes and then fixed with an adhesive. The main beam 101 and the tension beam 103 pass through the tubular space formed by the front edge and the side edge of the wing membrane 104 respec...

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Abstract

The invention discloses a bionic flapping-wing micro air vehicle capable of realizing high control moment generation based on double-wing differential motion and steering engine gravity center changeand a control moment generation method thereof. The aircraft comprises a lift system, a transmission system, a control system and a power system. The transmission system achieves reciprocating flapping of the wings in a small space through a distributed gear reduction set gear and a crank-connecting rod combination. The control system drives the flapping wing tensioning beam to move forwards, backwards, leftwards and rightwards through the two independent steering engines to achieve effective adjustment of the flapping wing attack angle. The flapping wing tensioning beam is connected with thespherical hinge device on the base and is controlled by the rolling steering engine and pitching so that the change range of the attack angle of the flapping wing is effectively widened, and the control moment generated by the flapping wing is increased. Besides, when the bionic flapping-wing micro air vehicle performs attitude control, the steering effect is further enhanced by controlling the deflection of the gravity center of the steering engine, and the control moment generated by flapping wings is effectively improved.

Description

technical field [0001] The invention relates to the field of micro-aircraft, in particular to a bionic flapping-wing micro-aircraft that realizes high control torque generation based on biplane differential and center of gravity changes of steering gears. Background technique [0002] With the rapid development of MEMS processing, information remote sensing, computer science and other technologies, micro air vehicles have begun to change from concept to reality. MAVs have broad application prospects in military fields such as reconnaissance and surveillance, low-altitude patrols, and anti-terrorist blasting, as well as civilian fields such as mimic observation and fire disaster relief. At present, according to the principle of flight, MAVs can be roughly divided into three categories: fixed-wing MAVs, rotary-wing MAVs, and bionic flapping-wing MAVs. [0003] Micro air vehicles are small in size and low in flight speed, and their wings are in low Reynolds number flow during ...

Claims

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Application Information

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IPC IPC(8): B64C33/02B64D27/24G05D1/08
CPCB64C33/02B64D27/24G05D1/0808
Inventor 吴江浩程诚
Owner BEIHANG UNIV
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