Centroid-variable airbag buffer landing method for small flying-wing unmanned aerial vehicle

An unmanned aerial vehicle (UAV) and centroid-changing technology, applied in aircraft parts, aircraft control, full-wing aircraft, etc., can solve the problems of complex parachuting process, weak structural bearing capacity, large landing position error, etc. Effects of drift, small resistance characteristics, and moderate falling speed

Inactive Publication Date: 2020-06-02
GENERAL ENG RES INST CHINA ACAD OF ENG PHYSICS
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  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Compared with traditional layout UAVs, flying-wing UAVs also have disadvantages such as poor take-off and landing performance and weak structural bearing capacity. Generally, parachuting methods are mainly used to land, and there are still large errors in landing positions, damage to the residual speed of landing, and parachute installation. The umbrella process is more complicated, etc.

Method used

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  • Centroid-variable airbag buffer landing method for small flying-wing unmanned aerial vehicle
  • Centroid-variable airbag buffer landing method for small flying-wing unmanned aerial vehicle
  • Centroid-variable airbag buffer landing method for small flying-wing unmanned aerial vehicle

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Embodiment Construction

[0021] The present invention will be further described below in conjunction with accompanying drawing:

[0022] like figure 1 Shown, a kind of small-sized flying-wing unmanned aerial vehicle metamorphic core airbag buffer landing method, comprises the following steps:

[0023] S1. Slow down in deep stall action; fly the UAV to the sky above the landing position and maintain a level flight state; then use the UAV control system to pull the elevator surface to control the UAV to raise its head at a large angle and turn off the UAV power system, so that no During the deep stall, the horizontal speed of the man-machine decreases rapidly to zero under the action of aerodynamic resistance, and then falls freely;

[0024] S2, vertically descending wing surface resistance deceleration; in the free fall stage of the UAV, the UAV control system controls the variable center of mass structure action, and transfers the position of the UAV center of mass from the center of the UAV fuselage...

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Abstract

The invention discloses a centroid-variable airbag buffer landing method for a small flying-wing unmanned aerial vehicle, the advantage of large wing area of the flying-wing unmanned aerial vehicle isfully utilized, and in the free falling process, a wing surface forms a resistance surface, so that the vertical falling speed of the unmanned aerial vehicle can be effectively reduced; compared witha parachute, the resistance characteristic is small, the falling speed is moderate, and the problem that the falling speed is low and drifts along with wind is solved; through gradual deceleration inthree stages of deep stall deceleration, vertical descending airfoil resistance deceleration and grounding airbag deceleration, the deceleration load is reduced, and the integrity of the unmanned aerial vehicle body and the load is effectively ensured.

Description

technical field [0001] The invention belongs to the technical field of unmanned aerial vehicle landing, and in particular relates to a method for cushioning landing of a small-sized flying-wing unmanned aerial vehicle with a metamorphic core airbag. Background technique [0002] Small fixed-wing UAVs have the advantages of fast flight speed and long time in the air, and have been widely used in various civil aerial surveys and military reconnaissance. In the design of small UAVs, the way of landing and recovery is the key link in the design of UAVs. At present, small fixed-wing UAVs generally use the methods of hitting the ground, sliding, hitting the net, hitting ropes, parachuting, and "parachuting + airbag cushioning". "And other ways to recycle, but each way has its own limitations. For small unmanned aerial vehicles, sliding, hitting the net, and hitting the rope require certain venues and equipment support, which limits its application scenarios; the parachute landing...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C39/10B64C17/02B64D45/04B64C9/00
CPCB64C9/00B64C17/02B64C39/10B64D45/04
Inventor 甄文强关晓辉李潘丁志伟董严龚志斌李波邓坤曾飞陈强洪唐其琴赵平周欢
Owner GENERAL ENG RES INST CHINA ACAD OF ENG PHYSICS
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