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A locking mechanism for an aircraft arm

A locking mechanism and aircraft technology, applied to aircraft, affecting the air flow flowing through the surface of the aircraft, aircraft parts, etc., can solve the problems of easy breakage, large arm span, etc.

Active Publication Date: 2021-09-14
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 aircraft 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. Due to the weight reduction of the aircraft itself, 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

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0038] like Figure 1 to Figure 4 As shown, a locking mechanism for an aircraft arm of the present invention includes an aircraft arm 1 and an arm mounting seat 4 for connecting the aircraft arm 1 and the aircraft main body. On the connecting end, there is a guide hole through which the inside and outside are connected, and the lock head 2 which can slide and fit is arranged in the guide hole, and the eccentric wheel drive mechanism 3 which is connected with the lock head 2 and is arranged on the aircraft arm 1, and the eccentric wheel drive mechanism 3 It includes an eccentric wheel 6 movably connected with the lock head 2 and a rotating shaft 8 connected with the eccentric wheel 6. The eccentric wheel 6 moves axially around the rotating shaft 8 and drives the lock head 2 to move linearly in the guide hole. And the front end of the lock head 2 is in contact with or away from the surface of the clamping plate 5 arranged on the machine arm mounting base 4 .

[0039] Alternativ...

Embodiment 2

[0063] The locking mechanism of a kind of aircraft arm 1 described in the present embodiment comprises the guide hole that is arranged on the connecting end of the aircraft arm 1 and penetrates inside and outside, and the lock head 2 that can slide and fit is arranged in the guide hole, and the lock head 2 is connected with the lock end 2 is connected and arranged on the eccentric wheel drive mechanism 3 on the aircraft arm 1, the eccentric wheel drive mechanism 3 includes the eccentric wheel 6 that is movably connected with the lock head 2, and the rotating shaft 8 connected with the eccentric wheel 6, the eccentric wheel The wheel 6 moves axially around the rotating shaft 8, and drives the lock head 2 to move linearly in the guide hole, and the front end of the lock head 2 is in contact with the surface of the clamping plate 5 arranged on the machine arm mounting seat 4 or keep away.

[0064] Specifically, the locking mechanism of the aircraft arm 1 controls that there is an...

Embodiment 3

[0086] like Figure 5 As shown, the arm mount 4 in this embodiment is used to connect the aircraft arm and the main body of the aircraft. The arm mount 4 includes a base plate 101, and the two sides of the base plate 101 are respectively provided with two sides extending upward to form two A connecting arm 106, the aircraft arm 1 is rotatably connected between the two connecting arms 106, the rotatable connecting end of the aircraft arm 1 has a lock head 2, and the base plate 101 is located at the part between the two connecting arms 106 There is a clamping plate 5 that extends upwards 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 distance between the rotation axis of the aircraft arm 1 and the distance between the base plate 101. The distance between the substrates 101 , there is a cavity 103 inside the clam...

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PUM

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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 through guide hole is arranged on the body of the aircraft arm and is slidably fitted with the lock end of the guide hole, and is connected with the lock end and is arranged on the eccentric wheel drive mechanism on the aircraft arm. The eccentric wheel movably connected with the eccentric wheel and the rotating shaft connected with the eccentric wheel, the eccentric wheel moves axially around the rotating shaft, and drives the lock head to make a linear motion in the guide hole, and the front end of the lock head is set in the machine The clamping plate surface on the arm mount comes in snug contact or away. The present invention mainly utilizes the driving structure of the eccentric wheel to drive the locking head to perform linear motion on the guide hole through the connecting end of the main body of the aircraft arm to realize 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 aircraft arms. 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 an aircraft arm extending from the aircraft fuselage to the outside. Motors and propellers are installed on the outer ends of the aircraft arms to drive the flight of the aircraft. The lower part of the aircraft is also provided with feet. frame to facilitate the landing of the aircraft. [0004] However, in the existing aircraft, the stretched aircraft arms and tripods are all fixedly connected to the fuselage. After use, the large arm span makes the aircraft hav...

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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