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Steering gear control system and method for a flapping-wing aircraft

A flapping-wing aircraft and control system technology, applied in the field of flapping-wing aircraft, can solve problems such as adverse effects of aircraft operation and large negative lift, and achieve the effects of reducing negative lift, increasing propulsion, and reducing projection area

Active Publication Date: 2020-12-15
MIANYANG KONGTIAN TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] For now, the flapping wing of the flapping wing aircraft will give a large negative lift during the upward flapping process, which will adversely affect the operation of the entire aircraft

Method used

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  • Steering gear control system and method for a flapping-wing aircraft
  • Steering gear control system and method for a flapping-wing aircraft
  • Steering gear control system and method for a flapping-wing aircraft

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Embodiment Construction

[0028] The technical solution of the present invention will be further described in detail below in conjunction with the accompanying drawings, but the protection scope of the present invention is not limited to the following description.

[0029] Such as figure 1 As shown, a steering gear control system of a flapping wing aircraft includes a flapping wing reversing detection module, a central processing unit and a steering gear control module;

[0030] The flapping wing reversing detection module is used to detect the flapping wing reversing information of the flapping wing aircraft, and when it is detected that the flapping wing is in the lowest position and the highest position, different reversing signals are sent to the central processing unit;

[0031] The central processing unit, according to the reversing signal from the flapping wing reversing detection module, generates the steering gear rotation control instruction and transmits it to the steering gear control modul...

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Abstract

The invention discloses a steering gear control system and method of a flapping wing aircraft vehicle. The steering gear control system includes a flapping wing reversing detecting module, a central processing unit and a steering gear control module, wherein the flapping wing reversing detecting module is used for detecting flapping wing reversing information of the flapping wing aircraft vehicle,and when a flapping wing is detected to locate in the lowest position and the highest position, and different reversing signals are sent to the central processing unit; according to the reversing signals from the flapping wing reversing detecting module, a steering gear rotating control instruction is generated by the central processing unit and transmitted to the steering gear control module; and the steering gear control module is used for controlling steering gear rotating of the flapping wing air craft vehicle according to the steering gear rotating control instruction of the central processing unit. According to the steering gear control system and method of the flapping wing aircraft vehicle, during flight of the flapping wing aircraft vehicle, negative lift force brought by upwardflapping the flapping wing is effectively lowered, and forward pushing force can be significantly increased.

Description

technical field [0001] The invention relates to a flapping-wing aircraft, in particular to a steering gear control system and method for the flapping-wing aircraft. Background technique [0002] An orthopter is a heavier-than-air aircraft whose wings flap up and down like the wings of birds and insects. Compared with common fixed-wing and rotary-wing aircraft, flapping-wing aircraft has significant advantages such as high efficiency, light weight, and low energy consumption. Moreover, flapping-wing aircraft has natural advantages in terms of safety and concealment, and is an important direction for the development of aircraft . [0003] For now, when the flapping wings of the flapping-wing aircraft are flapping upwards, there will be a relatively large negative lift force, which will adversely affect the operation of the entire aircraft. Contents of the invention [0004] The purpose of the present invention is to overcome the deficiencies of the prior art, and provide a...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C33/02
CPCB64C33/02
Inventor 汪庭军范中雨刘义春
Owner MIANYANG KONGTIAN TECH CO LTD
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