Bionic flapping wing micro aircraft with adjustable flapping angle average position and flight control method of bionic flapping wing micro aircraft

Abstract

The invention discloses a bionic flapping wing micro aircraft with an adjustable flapping angle average position and a flight control method of the bionic flapping wing micro aircraft. The device comprises a base, a power device, a transmission mechanism, a control mechanism and flapping wings. The power device, the transmission mechanism and the control mechanism are fixed to the base, and vibration of the base is reduced through a reinforcing beam. The transmission mechanism comprises a gear reduction set and a connecting rod mechanism, the connecting rod is connected with the gear, the leftrocker arm and the right rocker arm to form a slider-crank mechanism, a sliding groove is formed between the left rocker arm and the right rocker arm and connected with a base sliding groove and a linear stepping steering engine output arm through rivets, and reciprocating flapping can be achieved around the connecting rivets. The control mechanism drives the connecting rivet through the output arm to achieve adjustment of the average position of the flapping angle. By means of the simple connecting rod set, bionic flapping motion is achieved, the complexity of the mechanism is reduced, and machining is facilitated; meanwhile, by adjusting the average position of the flapping angle, the generation of the control moment is decoupled from the lift force of the aircraft, and maneuvering suchas pitching and circling can be realized.

Description

technical field [0001] The invention relates to the field of micro-aircraft, in particular to a bionic flapping-wing micro-aircraft with adjustable flap angle and average position and a flight control method thereof. Background technique [0002] The rapid development of micro-electromechanical technology has made it possible to miniaturize traditional aircraft. In this context, the concept of micro air vehicle was proposed in the 1990s. This type of aircraft has a wide range of military and civilian uses, and has become a research hotspot in this field. [0003] According to the principle of lift generation, MAVs can be roughly divided into fixed-wing MAVs, rotary-wing MAVs, and bionic flapping-wing MAVs. Compared with traditional aircraft, MAVs are small in size and low in flight speed, so their flying Reynolds number is also small during operation, and the aircraft faces strong viscous effects during flight. Efficiency is generally low. Insects and hummingbirds are nat...

AI Technical Summary

Problems solved by technology

This type of scheme can only roughly increase or decrease the angle of attack, and it is difficult to realize the change of the angle of attack accurately and in real time, which is not conducive to the evaluation of control rudder efficiency and precise control design

In addition, the scheme of changing the average position of the flapping angle needs to adjust and control the wing flapping motion mechanism. On the one hand, it is more difficult to realize this scheme under the requirements of miniaturization and integration design; The change is extremely sensitive, and the adjustment of the flapping motion mechanism will also cause aerodynamic changes at the same time. This solution is difficult to ensure high lift while adjusting the average position of the flapping angle.

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