Buffer protection adjustable swing arm position device for single-rotor UAV (unmanned aerial vehicle) servo control system

A servo control system and servo control technology, applied in the field of drones, can solve the problem that the servo control system is vulnerable to impact damage, etc., and achieve the effects of proper damping, convenient installation, and precise control

Pending Publication Date: 2019-06-18
广西南宁一键智农科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The purpose of the present invention is to provide a buffer protection adjustable swing arm position device for the servo control system of a single-rotor UAV, which solves the problem that the servo control system for controlling the rotor pitch is easy to solve when the single-rotor unmanned helicopter is hit by an external force such as falling. Problems with impact damage

Method used

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  • Buffer protection adjustable swing arm position device for single-rotor UAV (unmanned aerial vehicle) servo control system
  • Buffer protection adjustable swing arm position device for single-rotor UAV (unmanned aerial vehicle) servo control system
  • Buffer protection adjustable swing arm position device for single-rotor UAV (unmanned aerial vehicle) servo control system

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Embodiment Construction

[0017] The present invention will be described below in conjunction with the accompanying drawings. The specific embodiments described here are only used to illustrate and explain the present invention, and are not intended to limit the present invention. Various modifications and improvements made in the technical solution should fall within the protection scope of the present invention.

[0018] Such as figure 1 Shown, this is the first embodiment of the present invention. The buffer protection adjustable swing arm position device of the single-rotor unmanned helicopter servo control system of this embodiment includes an active swing arm 1 , a buffer link 2 and an actuating swing arm 3 .

[0019] The active swing arm 1 is fixedly connected to the output shaft of the servo control actuator, and driven to rotate by the output shaft of the servo control actuator. The servo control actuator is generally fixed on the frame 4 of the single-rotor UAV by screws, and the target ang...

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Abstract

The invention discloses a buffer protection adjustable swing arm position device for a single-rotor UAV (unmanned aerial vehicle) servo control system. The buffer protection adjustable swing arm position device for the single-rotor UAV servo control system is characterized in that the device comprises an active swing arm, a buffer connecting rod and an executive swing arm; the active swing arm isconnected with an output shaft of a servo control actuator of a servo control system, and the active swing arm is driven to rotate by the output shaft; the executive swing arm is fixed on a frame of asingle-rotor UAV through a hinge, and the executive swing arm can rotate round the hinge; the buffer connecting rod is connected between the active swing arm and the executive swing arm and used fortransferring the rotation of the active swing arm to the executive swing arm; the buffer connecting rod is used for absorbing impact energy by self deformation or destruction when the single-rotor UAVis subjected to an impact that can damage a servo control actuator. The buffer protection adjustable swing arm position device for the single-rotor UAV servo control system has the advantage of effectively solving the problem that the servo control system that controls rotor pitch is vulnerable to impact damage when a single-rotor unmanned helicopter falls.

Description

technical field [0001] The invention belongs to the technical field of unmanned aerial vehicles, and in particular relates to a buffer protection adjustable swing arm position device of a single-rotor unmanned aerial vehicle servo control system. Background technique [0002] At present, single-rotor unmanned helicopters generally adopt a method of controlling the pitch of the main rotor through a servo control system to control the attitude of the aircraft. The internal structure of the servo control system is complex and precise, and the cost is expensive. Most of them are equipped with control boards, brushless motors, reduction gears, output shafts, miniature bearings, magnetic encoder disks and other components. During normal operation, the control board receives the angular position signal from the external controller in real time, controls the rotation of the brushless motor, drives the output shaft to rotate through a series of reduction gears to output angular displ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/68
Inventor 赵刚李兆林陆高鸿梁桂华刘克勤
Owner 广西南宁一键智农科技有限公司
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