A micro-drone using chute bleed air wings

Abstract

The invention proposes a novel miniature unmanned aerial vehicle using chute bleed air wings, which belongs to the field of miniature unmanned aerial vehicles. The invention comprises: a chute, a wing, a power system and a steering surface; wherein, the wing is a traditional rectangular wing, and chutes are processed at the wingtips on both sides of the wing; the width D of the chute is between 3 mm and 10 mm, The azimuth angle β of the chute changes from 30° to 150°; the power system is a pair of propeller engines, including two symmetrically installed propellers and motor drives, which are directly installed at the leading edge of the wing; the control surface includes a pair of Ailerons mounted symmetrically at the trailing edge of the wing. A new type of micro UAV using a chute bleed air wing proposed by the present invention can effectively suppress the self-induced roll oscillation phenomenon at a high angle of attack by using the chute bleed air wing as a new type of wing plane. And the structure is simple, and the design and processing are convenient.

Description

technical field [0001] The invention belongs to the field of miniature unmanned aerial vehicles, in particular to a miniature unmanned aerial vehicle using chute bleed air wings. Background technique [0002] MAVs are a category of drones. The definition of a micro air vehicle is that the flight speed is up to 5-20m / s, and the maximum design length of its fuselage is 10-15cm [1] . Because of its small size, light weight, good concealment, strong functionality, low cost, easy to carry, easy to operate, etc., it is more and more used in military, civilian, scientific research and other fields. [2] . MAVs are mainly divided into three categories, namely fixed-wing MAVs, rotary-wing MAVs and flapping-wing MAVs, among which fixed-wing research is currently the most developed and most widely used type of MAVs. [0003] The aerodynamic characteristics of the small-aspect-ratio wing need to be considered in the design of the fixed-wing micro-aircraft. The small-aspect-ratio wing...

AI Technical Summary

Problems solved by technology

[0004] Traditional fixed-wing moment micro-UAVs generally adopt traditional shapes such as ordinary rectangular wings and Zimmerman-shaped wings. They are easily affected by self-induced lateral instability during flight, and self-induced roll oscillations occur. It may even cause the aircraft to lose control or even crash

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