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Micromechanical controllable flapping rotary wing aircraft and manufacturing method as well as control method thereof

A technology for micro-machines and aircraft, applied in the field of aircraft, can solve the problems of inability to achieve steering and forward flight, and achieve the effects of low cost and simple device structure

Inactive Publication Date: 2012-03-28
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the design scheme and device proposed in this patent can only realize vertical take-off and landing and hovering, and cannot realize steering and forward flight.

Method used

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  • Micromechanical controllable flapping rotary wing aircraft and manufacturing method as well as control method thereof
  • Micromechanical controllable flapping rotary wing aircraft and manufacturing method as well as control method thereof
  • Micromechanical controllable flapping rotary wing aircraft and manufacturing method as well as control method thereof

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Embodiment Construction

[0050] The present invention will be further described in detail with reference to the accompanying drawings and embodiments.

[0051] The present invention is a micro-mechanical controllable flapping rotor aircraft, such as figure 1 As shown, it includes a wing 1, a fuselage 2, a power plant 3, a transmission mechanism 4, a steering control system 5 and a forward flight control system 6.

[0052] The wing 1 is as figure 2 As shown, the wing 1 is two identical membrane wings, and each wing 1 is composed of a main beam 101 , two auxiliary beams (short auxiliary beam 102 , long auxiliary beam 103 ) and a membrane 104 . The main beam 101, the short auxiliary beam 102 and the long auxiliary beam 103 are made of carbon fiber rods, and the wing film 104 is made of polyethylene film. The main beam 101 is coplanar with the short auxiliary beam 102 and the long auxiliary beam 103, the short auxiliary beam 102 is perpendicular to the main beam 101, the long auxiliary beam 103 is betw...

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Abstract

The invention discloses a micromechanical controllable flapping rotary wing aircraft and a manufacturing method as well as a control method thereof. Flight principle of the invention is that: wing oscillation is realized through motor driving; thrust force couple is produced to rotate; and then lift force is produced to realize flight. The control method provided by the invention comprises the following steps of: producing variable lift force by wings by adjusting motor power to realize control over vertical takeoff and landing and hovering; by using downwash produced by rotation of the wings, producing couple around a vertical oscillation shaft in a horizontal plane by controlling a steering control plane outside a body; driving the body to rotate to realize steering control; and forming resultant force in a certain direction in the horizontal plane by controlling a forward flight control plane outside the body to drive the aircraft to fly forward so as to realize forward flight control. The device has a simple and reliable structure and is low in cost. A steering and forward flight control system provided by the invention can realize the functions of vertical takeoff and landing, hovering, steering control and free forward flight of the aircraft.

Description

technical field [0001] The invention relates to the field of aircraft, and more specifically, the invention relates to a micromechanical controllable flapping rotor aircraft and a manufacturing method and a control method thereof. Background technique [0002] Micro air vehicle is a new type of aircraft developed in the mid-1990s. In the past two decades, with the continuous improvement of traditional aircraft design technology, the rapid development of microelectronics technology and people's continuous exploration and in-depth understanding of the mechanism of animal flight and swimming, these principles and technologies are being applied to rapidly developing micro aircraft (Micro-air-vehicle, referred to as MAV) design field. Micro air vehicle generally refers to a wingspan and length of about 15 cm, a weight of tens of grams to hundreds of grams, a payload of 20 grams, a speed of 64-80 km / h, a flight time of 20-60 minutes, and a range of 10 kilometers. Micro flying ma...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C33/00B64C33/02
Inventor 吴江浩周超张艳来
Owner BEIHANG UNIV
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