Bionic flapping wing micro aircraft capable of realizing controllable flapping amplitude based on wing root elastic energy storage

Abstract

The invention discloses a bionic flapping wing micro aircraft capable of realizing controllable flapping amplitude based on wing root elastic energy storage. A wing root elastic stop structure is introduced into the aircraft, inertia work of flapping of a wing rod is stored as elastic potential energy in the flapping ending stage and the flapping starting stage, the elastic potential energy is released in the next flapping initial stage of a flapping wing, on one hand, the transmission efficiency of the aircraft is improved, and energy dissipation of the aircraft is reduced; on the other hand, the motion of the flapping wings in the upward flapping and downward flapping motion conversion process is accelerated, the overturning time of the flapping wings is shortened, and therefore the aerodynamic efficiency of the flapping wings is improved; meanwhile, through three rotary steering engines, pulleys and cams, differential adjustment of flapping amplitude of the flapping wings can be achieved under the condition that operation of a transmission mechanism is not changed, bionic flapping control motion is achieved, and three-axis controllable flight of the bionic flapping wing micro aircraft is achieved.

Description

technical field [0001] The invention relates to the field of micro-aircraft, in particular to a bionic flapping-wing micro-aircraft with controllable flapping amplitude based on wing root elastic energy storage. Background technique [0002] The concept of micro-aircraft was proposed by the US Defense Advanced Research Projects Agency in the 1990s. With the rapid development of MEMS processing and computer technologies, the concept of micro-aircraft has gradually become a reality. Micro air vehicles have broad application prospects in military and civilian fields such as reconnaissance and surveillance, post-disaster search and rescue, and pipeline inspection. The size of insects in nature is comparable to that of micro-aircraft, and they are extremely maneuverable and aerodynamically efficient. Therefore, based on the flight principle of insects, scientists have proposed the concept of bionic flapping-wing micro-aircraft. The flapping motion of bionic flapping-wing micro-...

AI Technical Summary

Problems solved by technology

The mechanism of the angle of attack control scheme is relatively simple, but it changes the angle of attack of the flapping wing within a flapping cycle, making it unable to maintain the best efficiency of the flapping angle of attack, so the aerodynamic efficiency of the flapping wing will be affected during the control process. In addition, because the membrane is mostly made of flexible materials, it is difficult to achieve precise control of the angle of attack of the membrane, which also puts forward higher requirements for the control system.

In the scheme of controlling the flapping motion, the generation of control torque can be realized by changing the flapping amplitude and the average flapping position of the left and right wings, and the angle of attack of the flapping wing can be kept at a high-efficiency angle of attack. However, due to the bionic flapping The transmission structure of the Wing MAV is usually in a state of high-speed rotation, so it is often difficult to control the transmission structure to change the flapping motion

[0004] On the other hand, most of the currently public bionic flapping-wing micro-aircraft use a connecting rod structure to realize the bionic flapping movement. Driven by the inertial load of the flapping wing, it will often continue to move with the flapping wing, causing the transmission link structure to enter a state of poor transmission force or a dead point position, resulting in a decrease in transmission efficiency and affecting the flight time of the aircraft.

At the same time, this part of the inertial load is often dissipated through structural deformation, rivet collisions, and motor stalls, which often lead to problems such as flapping motion deformation and reduced motor efficiency, which further lead to a decrease in the lift of the aircraft and a reduction in battery life. question

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