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A locking mechanism for an aircraft arm

A locking mechanism and aircraft technology, applied in the field of unmanned aerial vehicles, can solve the problems of easy breakage, large arm span, etc., and achieve the effect of ensuring integrity, simple locking structure, and saving accommodation space

Active Publication Date: 2021-06-29
POWERVISION ROBOT INC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, in the existing aircraft, the stretched arms and tripods are all fixedly connected to the fuselage. After use, the large arm span makes the aircraft have higher requirements for storage space. The weight of the aircraft itself needs to be considered, and the structure of each part of the aircraft is relatively simple. Therefore, the large arm span also leads to the danger of easy damage caused by improper storage

Method used

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  • A locking mechanism for an aircraft arm
  • A locking mechanism for an aircraft arm
  • A locking mechanism for an aircraft arm

Examples

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Effect test

Embodiment 1

[0031] Such as Figure 1 to Figure 3 As shown, a locking mechanism for an aircraft arm of the present invention includes an aircraft arm 1 and an arm mounting seat for connecting the aircraft arm 1 and the aircraft main body. The inner and outer guide holes on the connecting end are arranged on the body of the aircraft arm 1 and the lock head 2 that is slidably matched with the guide hole, and the pull pin 11 that is connected with the lock end 2 and is arranged on the aircraft arm 1. The lock head 2 moves linearly with the pull pin 11 in the guide hole, and the front end of the lock head 2 is in close contact with or away from the surface of the clamping plate 5 arranged on the mounting seat of the machine arm.

[0032] Alternatively, the locking mechanism described in this embodiment includes an aircraft arm 1 and an arm mount for connecting the aircraft arm 1 and the main body of the aircraft, and the aircraft arm 1 is rotatably arranged on the arm mount , the arm mounting...

Embodiment 2

[0053] In this embodiment, the locking mechanism also includes a movable slot arranged on the aircraft arm to limit the linear movement of the pull pin 11, and a connecting portion 14 arranged at the rear end of the lock head 2, and one end of the pulling pin 11 is connected to the connecting portion. 14 are fixedly connected, and the other end runs through the movable groove;

[0054] Wherein, the lock head 2 moves linearly with the pull pin 11 in the guide hole, forming a telescopic fit between the front end of the lock head 2 and the clamping plate 5 .

[0055] Further, the pull pin 11 includes a connecting shaft and a reset structure, the pull pin 11 is connected to the connecting portion 14 of the lock head 2 through the connecting shaft, and a reset structure is arranged between the pulling pin 11 and the connecting portion 14, and the control There is an angle between the pull pin 11 and the movable groove and the pull pin 11 and the movable groove are basically close t...

Embodiment 3

[0059] Such as Figure 4 As shown, the arm mounting seat in this embodiment is used to connect the aircraft arm and the aircraft main body. The arm mounting seat includes a base plate 101, and the two sides of the base plate 101 are respectively provided with two connecting plates extending upwards to form two connections. Arm 106, the aircraft arm 1 is rotatably connected between the two connecting arms 106, the rotatable connection end of the aircraft arm 1 has a lock head 2, and the part of the base plate 101 located between the two connecting arms 106 has The clamping plate 5 that extends upward and contacts and abuts against the lock head 2, the height of the clamping plate 5 is greater than the distance between the top of the lock head 2 of the aircraft arm 1 and the base plate 101, and is smaller than the rotation axis of the aircraft arm 1 and the base plate 101 The clamping plate 5 has a cavity 103 inside.

[0060] Specifically, the arm mounting seat includes a base ...

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Abstract

The invention discloses a locking mechanism for an aircraft arm, which comprises an aircraft arm and an arm mounting seat for connecting the aircraft arm and the aircraft main body. The guide hole is provided with a slidably fitted lock head and a pull pin connected with the lock head and arranged on the aircraft arm. The lock head moves linearly with the pull pin in the guide hole, and the The front end of the lock head is in contact with or away from the surface of the clamping plate arranged on the mounting base of the machine arm. The present invention solves the problem that the aircraft arm can be freely extended / recovered. In the present invention, the pull pin connected with the lock head and arranged on the aircraft arm is mainly used, and the lock head moves linearly in the guide hole along with the pull pin. , and the front end of the locking head is in contact with or away from the surface of the clamping plate arranged on the mounting seat of the aircraft arm, and realizes the locking / unlocking of the aircraft arm.

Description

technical field [0001] The invention relates to the field of unmanned aerial vehicles, in particular to a locking mechanism for an aircraft arm. Background technique [0002] At present, aircraft or unmanned aerial vehicles have been more and more widely used in social life, for close-range observation of places that are difficult for people to reach, or for high-altitude aerial photography, which provides convenience for observation and shooting. [0003] Existing aircraft often consists of an aircraft fuselage and a machine arm extending from the aircraft fuselage to the outside. Motors and propellers are installed at the outer ends of the machine arms to drive the flight of the aircraft. A tripod is also provided at the bottom of the aircraft. to facilitate the landing of the aircraft. [0004] However, in the existing aircraft, the stretched arms and tripods are all fixedly connected to the fuselage. After use, the large arm span makes the aircraft have higher requireme...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C1/30B64C39/00
CPCB64C1/30B64C39/00
Inventor 郑卫锋其他发明人请求不公开姓名
Owner POWERVISION ROBOT INC
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