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UAV hatch cover quick lock device

A technology of lock device and canopy, which is applied in the direction of fuselage, aircraft accessories, aircraft parts, etc., can solve the problems that operability performance hinders the scope and prospect of UAV application, inconvenient disassembly and assembly, and affects the rapidity of the system, etc.

Active Publication Date: 2017-05-10
HIWING AVIATION GENERAL EQUIP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] At present, the installation method of the hatch cover of small civilian drones is usually mainly screw fastening. The fastening method of this hatch cover requires the use of tools, which directly affects the rapidity of the system and makes the removal of the hatch cover longer.
In the process of debugging and field operations of UAVs, it is necessary to open the hatch cover frequently to replace and maintain batteries, check avionics equipment, and download flight data. The embedded thread of the body needs to be repaired; at the same time, this bolt connection method is inconvenient to disassemble and install, and special tools are required to fasten and disassemble the bolts. 3-5 minutes
[0003] The application advantage of UAV is that it is convenient, quick, safe and reliable compared with manned aircraft, but the existing connection method between the hatch cover and the fuselage is cumbersome to assemble and has insufficient reliability. The scope and prospect of man-machine application

Method used

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  • UAV hatch cover quick lock device
  • UAV hatch cover quick lock device
  • UAV hatch cover quick lock device

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0030] see Figure 1-4 , the present invention provides a kind of unmanned aerial vehicle canopy fast locking device, comprising:

[0031] The hatch cover mounting seat 1 is installed on the hatch cover and is cylindrical; one end is open, the other end has an end cover 11, and the center of the end cover 11 has a hole for the pin shaft 21 to pass through. Between the end cover 11 and the pin shaft 21 For tight fit, it can prevent dust and short-term rainproof function;

[0032] The lock cylinder 2 includes a pin shaft 21 pierced in the hatch mounting seat 1, a spring 22 pierced on the pin shaft 21 and a lock pin 23 detachably mounted on the pin shaft 21, and the pin shaft 21 has a spring seat 24. The spring 22 is installed between the spring seat 24 and the lock pin 23; one end of the pin shaft 21 has a rotating head 21a for easy rotation, and the rotating head 21a extends outward from the hatch cover mounting seat 1, and the rotating head 21a is in the shape of a positive p...

Embodiment 2

[0039] see Figure 5-10 , on the basis of Embodiment 1, a limit groove 33 for limiting the rotation angle of the lock pin 23 is also provided on the end extending along the lock groove 32 on the fuselage mounting seat 3, and the cross section of the limit groove 33 includes a pin shaft 21 is fitted with a central hole 33a and two sectors 33b symmetrically distributed with respect to the center of the central hole, and the diameter of the sectors 33b is the same as the length of the lock pin 23 . The central angle of the sector 33b is between 60° and 120°, preferably 90°. A groove 3c for limiting the rotation of the lock pin 23 is provided on the end surface 3b extending along the lock groove on the body mount 3 , and the angle between the groove 3c and the lock groove 32 is 90 degrees.

[0040]Press down the pin shaft 21 and rotate it 90° clockwise, the quick lock is locked, and the pin shaft 21 is turned 90° counterclockwise to pop up, and the quick lock is opened.

[0041]...

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Abstract

The invention discloses a quick-locking device for a hatch cover of an unmanned aerial vehicle. The quick-locking device comprises a hatch cover installation seat, a lock cylinder, and a body installation seat, wherein the lock cylinder comprises a pin shaft arranged in the hatch cover installation seat in a penetrating manner, springs arranged on the pin shaft in a penetrating manner, and lock pins detachably installed on the pin shaft, a spring seat is arranged on the pin shaft, and the springs are installed between the spring seat and the lock pins; a seat hole, and lock grooves for penetration of the pin shaft and the lock pins are sequentially formed in the inner wall of the body installation seat from one end to the other end; a return step is formed between the seat hole and the lock grooves; and one end close to the lock pins, of the hatch cover installation seat, is inserted in the seat hole, the lock pins are clockwise rotated 90 degrees, the springs are abutted between the spring seat and the return step, and the lock pins are abutted in concave grooves of the lock grooves under actions of restoring forces of the springs. According to the invention, locking and unlocking steps are simplified, time is saved, and the operation is more convenient and rapid.

Description

technical field [0001] The invention relates to unmanned aerial vehicle technology, in particular to a quick-locking device for a hatch cover of an unmanned aerial vehicle. Background technique [0002] At present, the installation method of the hatch cover of small civilian drones is usually screw fastening. The fastening method of this hatch cover requires the use of tools, which directly affects the rapidity of the system and makes the removal of the hatch cover longer. . During the debugging and field operations of UAVs, it is necessary to open the hatch cover frequently to replace and maintain batteries, check avionics equipment, and download flight data. The embedded thread of the body needs to be repaired; at the same time, this bolt connection method is inconvenient to disassemble and install, and special tools are required to fasten and disassemble the bolts. 3-5 minutes. [0003] The application advantage of UAV is that it is convenient, quick, safe and reliable...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): E05C19/00B64C1/14
CPCB64C1/1446E05C19/007
Inventor 李想郭凯旋周晓东陈永帅高文坤刘彦飞刘铁军崔秀敏王乐辉关雅雯
Owner HIWING AVIATION GENERAL EQUIP
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