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Flight control method and system of flapping wing air vehicle

A flapping aircraft and a control method technology, applied in the field of aircraft control, can solve the problems of inability to actively control the balance of pitching moment, inability to actively control the balance of yaw moment, incapable of active control of wingtip torsion, etc., so as to reduce weight and reduce energy consumption. , the effect of large lift and thrust

Inactive Publication Date: 2017-09-26
SHANGHAI JIAO TONG UNIV
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AI Technical Summary

Problems solved by technology

[0003] The present invention aims at the defect that the prior art cannot actively control the twisting of the wingtip, or cannot actively control and balance the yaw moment, or cannot actively control and balance the pitch moment, and proposes a flight control method and system for a flapping-wing aircraft , using new sensors and hybrid control of multiple control surfaces, can achieve extremely high stability and maneuverability; compared with flapping wing aircraft without wingtip twist, the lift and flight efficiency have been greatly improved

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  • Flight control method and system of flapping wing air vehicle
  • Flight control method and system of flapping wing air vehicle
  • Flight control method and system of flapping wing air vehicle

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Embodiment Construction

[0026] like Figure 4 As shown, the flapping wing aircraft flight control system involved in this embodiment includes: an angle acquisition module, a remote control signal receiving module, a twist calculation module and an execution module arranged in the aircraft, wherein the angle acquisition module is connected with the twist calculation module and transmitted For angle information, the twist calculation module integrates the data of the remote control receiving module and the angle acquisition module for calculation, and transmits the target angle to the execution module.

[0027] The angle acquisition module is realized by using, but not limited to, a Hall angle sensor.

[0028] The torsion calculation module in this embodiment is implemented by an Arduino single-chip microcomputer, and its signal input includes two forms, one is an analog signal, and the other is a digital signal. The signal of the angle sensor is an analog signal, which is read directly and scaled fro...

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Abstract

The invention discloses a flight control method of a flapping wing air vehicle. The wing tip torsion angle and the pithing adjusting angle under corresponding flapping angel of a bird are calculated by detecting the flapping angle of a flapping wing of a bionic air vehicle in real time, namely, the relative angle of a wing root connecting rod relative to the horizontal datum of a vehicle body, and a steering engine is set through a torsion angle of a wing tip for torsion of the wing top of the bionic air vehicle and adjustment of pitch attitude, so that the flight efficiency is improved. High stability and maneuverability can be realized; compared with flapping wing air vehicles without wing tip torsion, the flapping wing air vehicle has greatly improved lift force and flight efficiency.

Description

technical field [0001] The invention relates to a technology in the field of aircraft control, in particular to a flight control method and system for a flapping-wing aircraft with greatly improved flight stability and hybrid control. Background technique [0002] In recent years, bionic flapping-wing aircraft has gradually entered people's field of vision. Due to its bird shape and flight mode, and the almost no mechanical noise generated during its flight, the bionic flapping wing aircraft has a high degree of concealment, and has unique advantages in military detection and strikes. In terms of civilian use, fixed-wing aircraft imitating raptors such as eagles have been used to drive birds at airports. The bionic flapping-wing aircraft is not only a change in shape, but also has a great improvement in lift, endurance and flight efficiency compared with fixed-wing aircraft due to its high degree of bionics. However, the controllable degrees of freedom of the previous flap...

Claims

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Application Information

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IPC IPC(8): G05D1/10B64C33/00
Inventor 徐文浩王煜凯张泽天褚雨薇袁家信王福新刘洪
Owner SHANGHAI JIAO TONG UNIV
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