A multi-rotor UAV emergency crash ejection protection device

A multi-rotor unmanned aerial vehicle and protection device technology, applied in aircraft parts, emergency equipment, aircraft landers, etc., can solve problems such as large economic losses of unmanned aerial vehicles, and achieve the effect of reducing damage

Active Publication Date: 2020-12-25
JILIN UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] The purpose of the present invention is to propose a multi-rotor UAV emergency crash ejection protection device to solve the problem of large economic losses after the UAV crashes due to the lack of crash protection devices in the prior art

Method used

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  • A multi-rotor UAV emergency crash ejection protection device
  • A multi-rotor UAV emergency crash ejection protection device
  • A multi-rotor UAV emergency crash ejection protection device

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Embodiment Construction

[0046] Embodiments of the present invention will be further described below in conjunction with the accompanying drawings.

[0047]The present invention uses an ejection device to eject a parachute or other high-altitude deceleration airbags to greatly reduce the falling speed of the UAV in the air, and combines the recoil device 22 with a small recoil speed reduction method near the ground to reduce the occurrence of multi-rotor UAVs. Injuries that may occur in an emergency crash, safe to use. Considering the expansion of the ejection device and the recoil device, and the replacement of the recoil gas, a higher drop height can be achieved and a better fall protection effect can be achieved. The parts of the ejection device and the recoil device can be made of light metal such as aluminum alloy, which is simple in machining and good in economy. The large damping spring 143 of general parts that adopts, high-elastic rubber band 145 etc. can be selected flexibly to determine th...

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Abstract

The invention discloses an ejection type protection device for emergency crash of a multi-rotor unmanned aerial vehicle, belongs to the technical field of unmanned aerial vehicle protection, and aimsto solve the problem of high economic loss after crash of the unmanned aerial vehicle due to the fact that a crash-free protection device exists in the prior art. The ejection type protection device comprises an ejection part and n groups of recoil parts, wherein the ejection part comprises an ejection sliding cylinder, a steering engine set, an ejector and a speed reduction device; one end of theejection sliding cylinder is fixed on the multi-rotor unmanned aerial vehicle through a fixed ring seat; the steering engine set is fixed on the fixed ring seat; the ejector is arranged in the ejection sliding cylinder, and is controlled and limited at one end, close to the fixed ring seat, in the ejection sliding cylinder or is ejected towards the other end through the steering engine set; the speed reduction device is arranged on the ejector, and is driven by the ejector to retract or eject the ejection sliding cylinder; each group of recoil parts comprises two pairs of recoil structures which are symmetrically arranged on two rotors of the multi-rotor unmanned aerial vehicle; each pair of recoil structures comprises two traction legs which are arranged on one rotor and are oppositely arranged; and each traction leg is provided with a recoil device.

Description

technical field [0001] The invention belongs to the technical field of UAV protection, and in particular relates to an emergency crash ejection protection device for a multi-rotor UAV. Background technique [0002] A multi-rotor UAV is a special unmanned rotorcraft with three or more rotor shafts. The controller controls the rotation of the motor on each shaft to drive the rotor to generate lift. The collective pitch of the rotors is fixed, not variable like normal helicopters. By changing the relative speed between different rotors, the size of the single-axis propulsion can be changed, thereby controlling the trajectory of the aircraft; the electronic equipment compartment of the multi-rotor UAV is equipped with a GPS altitude locator, an air pressure altimeter auxiliary board, and a gyroscope. The instrument and the acoustic rangefinder module can collect corresponding data, and sense the flight attitude and the distance from the ground through the controller of the mult...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D45/04B64D17/80B64D17/70
CPCB64D17/70B64D17/80B64D45/04
Inventor 陈延礼彭淦李继财程延耕秦靖淳商艺琢施宇罗松松
Owner JILIN UNIV
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