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A UAV landing gear shaft installation structure and installation method

An installation structure and landing gear technology, applied in the field of aircraft landing gear, can solve the problems of weakening the strength of the landing gear shaft, limited installation and operation space of the landing gear, and large operating space, and achieve simple structure, small space required for installation, and easy installation steps simple effect

Active Publication Date: 2022-01-25
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For small UAVs, the diameter of the shaft is small and the space for installing and operating the landing gear is very limited. The method of fixing the shaft with pin bolts requires drilling holes on the shaft, which greatly weakens the strength of the shaft of the landing gear. Large operating space required

Method used

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  • A UAV landing gear shaft installation structure and installation method
  • A UAV landing gear shaft installation structure and installation method
  • A UAV landing gear shaft installation structure and installation method

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0032] A UAV landing gear shaft installation structure, such as Figure 1-Figure 3 , the installation structure includes the landing gear shaft 1, the installation lug 2, the installation bushing 3 and the screw fixing structure 4, the installation bushing 3 is arranged inside the installation ear piece 2, and the shaft body 101 of the landing gear shaft 1 passes through The mounting hole 201 of the mounting lug 2 and the sleeve hole 301 of the mounting bush 3, the end cap 102 of the landing gear shaft 1 is provided with a shaft limit surface 5, and the outer end of the mounting hole 201 of the mounting lug 2 is adapted to the shaft. There is a lug limiting surface 6 at the position of the limiting surface 5 , and the screw fixing structure 4 is installed on the end cap 102 of the landing gear rotating shaft 1 .

[0033] Working principle: In order to overcome the deficiencies of the existing technology, without changing the function and performance of the landing gear shaft, th...

Embodiment 2

[0035] In the present invention, on the basis of the above-mentioned embodiment 1, the screw fixing structure 4 includes a bolt 401 and a nut 402, and the screw rod 403 of the bolt 401 passes through the end cap 102 of the landing gear shaft 1 and the outer end surface of the mounting lug 2 or The lug limiting surface 6 , the nut 402 is fixed on the screw rod 403 .

[0036] The screw fixing structure 4 also includes a cotter pin 404 , and the end of the screw 403 of the bolt 401 has a through hole 405 adapted to the cotter pin 404 . The screw fixing structure further includes a washer 406 .

[0037] A gap adjusting washer 7 is arranged between the mounting lug 2 and the mounting bush 3 . The sleeve hole 301 of the installation bush 3 is provided with a joint bearing 8, the outer ring of the joint bearing 8 is fixed on the sleeve hole 301 of the installation bush 3, and the shaft body 101 of the landing gear rotating shaft is connected from the inside of the joint bearing 8. ...

Embodiment 3

[0042] A method for installing a UAV landing gear shaft, based on a UAV landing gear shaft installation structure as described in Embodiment 1 or Embodiment 2 above, the landing gear shaft 1 passes through the mounting lugs 2 sequentially from the outside The mounting hole 201 and the sleeve hole 301 of the bushing 3 are installed, and the shaft limit surface 5 of the end cap 102 of the landing gear shaft 1 and the ear piece limit surface 6 of the installation lug 2 are placed correspondingly, and the screw fixing structure 4 is installed to the lifting gear. The end cap 102 of the landing gear rotating shaft 1 fixes the landing gear rotating shaft 1 so that the landing gear rotating shaft 1 cannot move axially or rotate in the circumferential direction.

[0043] The working principle of this embodiment is the same as that of Embodiment 1 or 2 above, so it will not be repeated here.

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PUM

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Abstract

A UAV landing gear shaft installation structure and installation method, relating to the field of aircraft landing gear, installation lugs are set between the landing gear shaft and the body, and corresponding positions are set on the outside of the installation lugs and the corresponding positions of the landing gear shaft The limit surface, and a screw fixing structure is installed on the end cap outside the landing gear shaft to further limit the landing gear shaft, limiting the axial movement and circumferential rotation of the landing gear shaft. The structure of this scheme is simple, and the installation required operations The space is small, there is no need to drill holes on the rotating shaft, and it will not affect the strength of the landing gear rotating shaft, so it can be well applied to small aircraft, drones or other aircraft.

Description

technical field [0001] The invention relates to the field of aircraft landing gear, in particular to an installation structure and an installation method for a rotating shaft of an unmanned aerial vehicle landing gear. Background technique [0002] Landing gear (Undercarriage) is an accessory device that supports the aircraft and moves on the ground (or water surface) when the lower part of the aircraft is used for takeoff, landing or ground (or water) taxiing. The landing gear is the only part that supports the entire aircraft, so it is an integral part of the aircraft; without it, the aircraft cannot move on the ground. After the aircraft takes off, you can choose to retract the landing gear depending on the performance of the aircraft. In order to meet the needs of aircraft takeoff, landing roll and ground taxiing, the lowermost end of the landing gear is equipped with wheels with pneumatic tires. In order to shorten the landing roll distance, brakes or automatic brakes...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C25/10
CPCB64C25/10B64U10/00
Inventor 田佳杰冯熙任杰郑华
Owner CHENGDU AIRCRAFT INDUSTRY GROUP