CN204297067U - A kind of anti-loose structure of aircraft pull bar - Google Patents
A kind of anti-loose structure of aircraft pull bar Download PDFInfo
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- CN204297067U CN204297067U CN201420684553.9U CN201420684553U CN204297067U CN 204297067 U CN204297067 U CN 204297067U CN 201420684553 U CN201420684553 U CN 201420684553U CN 204297067 U CN204297067 U CN 204297067U
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- pull bar
- lock washer
- locking
- fuse hole
- rod head
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Abstract
A kind of anti-loose structure of aircraft pull bar, connected to form successively by drag link body, lock washer, stop nut and rod head, drag link body there is internal thread, rod head there is the externally threaded threaded rod of band, the threaded rod of rod head has the locking groove of an axis, lock washer has one with the locking tooth bar of locking matching grooves, lock washer also has first fuse hole, stop nut has the second corresponding fuse hole, connects between the first fuse hole and the second fuse hole with fuse.
Description
Technical field
The present invention relates to the design field technology of aircraft, particularly aircraft pull bar is locking.
Background technology
Pull bar is applied very extensive in flight control system, hatch door motion, for carrying certain pulling force, the structure of pull bar is made up of drag link body and the rod head being screwed onto drag link body termination usually, rotating rod joint, can the length of adjusting yoke, whether the locking patten's design of pull bar and rod head is correct and reasonable, and playing a very important role the security reliability of flight control system, hatch door, is an important step of can not ignore in airplane design.
The anti-loose method of pull bar has a variety of form, and fastening nut can be locking, but the screw thread of this nut does not close up, and easily loosens, and anti-loosing effect is bad.The anti-loose method of another kind of pull bar adds a toothed lock washer, after pull bar length adjustment puts in place, the space of teeth of lock washer is bent, a tooth and nut are fitted, the cylinder of another tooth and pull bar is fitted, and reaches anti-loosing effect, the bad laminating of cylinder of the tooth after this mode lock washer bends and pull bar, have rotation among a small circle, affect the precision of pull bar.Therefore, therefore design is a kind of connects reliable pull bar anti-loose method, just seems very necessary.
Summary of the invention
In order to solve prior art Problems existing, the application proposes a kind of anti-loose structure of aircraft pull bar, to solve the locking problem of aircraft pull bar existed at present.
A kind of anti-loose structure of aircraft pull bar, connected to form successively by drag link body, lock washer, stop nut and rod head, drag link body there is internal thread, rod head there is the externally threaded threaded rod of band, it is characterized in that, the threaded rod of rod head has the locking groove of an axis, lock washer has one with the locking tooth bar of locking matching grooves, lock washer also has first fuse hole, stop nut has the second corresponding fuse hole, connects between the first fuse hole and the second fuse hole with fuse.
Nut is screwed on rod head, rod head is through the macropore of lock washer, the locking tooth bar of lock washer is embedded in the groove of rod head, again by rod head with pull bar with being threaded, rotating rod joint, the length of adjusting yoke, after meeting the demands, again by nut screwing clamping, finally with fuse the first fuse hole of lock washer is connected with the second fuse hole of nut and namely completes the locking of pull bar.
The application has the following advantages:
1) structure is simple, connection is reliable, anti-loosing effect is good.
2) overcome conventional whip locking time the shortcoming that easily loosens.
Below in conjunction with embodiment accompanying drawing, the application is described in further detail:
Accompanying drawing explanation
Fig. 1 pull bar anti-loose structure schematic diagram
The locking assembling decomposing schematic representation of Fig. 2 pull bar
Fig. 3 anti-loosening gasket structure schematic diagram
Fig. 4 nut structure schematic diagram
Fig. 5 fuse scheme of installation
Number description: 1 pull bar, 2 lock washers, 3 stop nuts, 4 rod heads, 5 locking grooves, 6 locking tooth bars, 7 first fuse hole, 8 second fuse hole, 9, fuse
Detailed description of the invention
See accompanying drawing, pull bar 1 is hollow circular-tube, and the endoporus of pipe termination is shaped with internal thread.The termination of rod head 4 is auricle, auricle is shaped with circular hole, for installing load bearing, drag link body is pole shape, drag link body is provided with external screw thread, and locking groove 5 is located at the axis of drag link body, lock washer 2 has a locking tooth bar 6 mated with locking groove 5, lock washer also has first fuse hole 7, and stop nut 3 has the second corresponding fuse hole.
Be screwed in by stop nut 3 on rod head 4, rod head 4 is through the macropore of lock washer 2, and the locking tooth bar 5 of lock washer is embedded in the locking groove 5 of rod head, then by rod head 4 with pull bar 1 with being threaded.Rotating rod joint 4, the length of adjusting yoke 1, after meeting the demands, then tightens stop nut 3, to be connected by the first fuse hole 7 of lock washer can to complete the locking of pull bar with fuse 9 with the second fuse hole 8 of stop nut 3.
Claims (1)
1. the anti-loose structure of an aircraft pull bar, connected to form successively by drag link body, lock washer, stop nut and rod head, drag link body there is internal thread, rod head there is the externally threaded threaded rod of band, it is characterized in that, the threaded rod of rod head has the locking groove of an axis, lock washer has one with the locking tooth bar of locking matching grooves, lock washer also has first fuse hole, stop nut has the second corresponding fuse hole, connects between the first fuse hole and the second fuse hole with fuse.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420684553.9U CN204297067U (en) | 2014-11-14 | 2014-11-14 | A kind of anti-loose structure of aircraft pull bar |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420684553.9U CN204297067U (en) | 2014-11-14 | 2014-11-14 | A kind of anti-loose structure of aircraft pull bar |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204297067U true CN204297067U (en) | 2015-04-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420684553.9U Active CN204297067U (en) | 2014-11-14 | 2014-11-14 | A kind of anti-loose structure of aircraft pull bar |
Country Status (1)
| Country | Link |
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| CN (1) | CN204297067U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828950A (en) * | 2016-12-09 | 2017-06-13 | 上海航空电器有限公司 | A kind of mounting structure of control board bracket |
| CN109538829A (en) * | 2018-11-29 | 2019-03-29 | 北京宇航***工程研究所 | A kind of accumulator anti-shake support construction |
| CN110932029A (en) * | 2019-12-09 | 2020-03-27 | 中航光电科技股份有限公司 | Locking structure that takes off of cabin socket is worn in fastening nut installation |
| CN113418073A (en) * | 2021-06-29 | 2021-09-21 | 济南顾邦信息科技有限公司 | New energy automobile cooling pipeline interval adjustable anti-loosening joint |
-
2014
- 2014-11-14 CN CN201420684553.9U patent/CN204297067U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828950A (en) * | 2016-12-09 | 2017-06-13 | 上海航空电器有限公司 | A kind of mounting structure of control board bracket |
| CN109538829A (en) * | 2018-11-29 | 2019-03-29 | 北京宇航***工程研究所 | A kind of accumulator anti-shake support construction |
| CN110932029A (en) * | 2019-12-09 | 2020-03-27 | 中航光电科技股份有限公司 | Locking structure that takes off of cabin socket is worn in fastening nut installation |
| CN113418073A (en) * | 2021-06-29 | 2021-09-21 | 济南顾邦信息科技有限公司 | New energy automobile cooling pipeline interval adjustable anti-loosening joint |
| CN113418073B (en) * | 2021-06-29 | 2023-02-07 | 济南顾邦信息科技有限公司 | New energy automobile cooling pipeline interval adjustable anti-loosening joint |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: No. 710089 in Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC Xi'an Aircraft Industry Group Co.,Ltd. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: AVIC AIRCRAFT Corp. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20210616 Address after: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee after: AVIC AIRCRAFT Corp. Address before: 1 No. 710089 Shaanxi province Xi'an city Yanliang District West Avenue Patentee before: XI'AN AIRCRAFT BRANCH OF XI'AN AIRCRAFT INTERNATIONAL Corp. |