A multi-rotor UAV emergency crash ejection protection device

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...

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

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