CN204489197U - A kind of driving engine main thrust pin fixing device with the company's of helping function - Google Patents
A kind of driving engine main thrust pin fixing device with the company's of helping function Download PDFInfo
- Publication number
- CN204489197U CN204489197U CN201520133022.5U CN201520133022U CN204489197U CN 204489197 U CN204489197 U CN 204489197U CN 201520133022 U CN201520133022 U CN 201520133022U CN 204489197 U CN204489197 U CN 204489197U
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- China
- Prior art keywords
- clip
- thrust pin
- main thrust
- eyelet bolt
- pin
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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- Snaps, Bayonet Connections, Set Pins, And Snap Rings (AREA)
- Pivots And Pivotal Connections (AREA)
- Connection Of Plates (AREA)
Abstract
The utility model provides a kind of driving engine main thrust pin fixing device with the company's of helping function, relates to engine parts field engineering, can solve the problem that driving engine main thrust pin and thrust pin clip align difficulty.Driving engine main thrust pin fixing device of the present utility model, comprise aircraft main thrust beam, thrust pin clip, clip locating dowel pin and the hinged eyelet bolt be arranged on aircraft main thrust beam, eyelet bolt is provided with nut; In addition, the U-shaped opening that can hold eyelet bolt is also offered in thrust pin clip one end.Driving engine main thrust pin fixing device of the present utility model, carries out screw thread loading by the nut tightened on eyelet bolt, thrust pin clip is closed and puts in place, thus realizes the closed of thrust pin clip, thrust pin Fast Installation is put in place, improves driving engine installation effectiveness.
Description
Technical field
The utility model relates to engine parts field engineering, is specifically related to a kind of driving engine main thrust pin fixing device with the company's of helping function.
Background technology
Main thrust pin be driving engine to the important point of connection of aircraft transmitting thrust, load-bearing frame has thrust pin clip inside aircraft, for stationary engine main thrust pin.When mounted, due to main thrust pin and thrust pin clip quality of fit high, adjustment degree of freedom is more, causes main thrust pin to be in place difficulty, causes the driving engine set-up time longer, inefficiency.
Summary of the invention
The utility model provides a kind of driving engine main thrust pin fixing device with the company's of helping function, can solve the problem that driving engine main thrust pin and thrust pin clip align difficulty.
In order to achieve the above object, embodiment of the present utility model adopts following technical scheme:
A kind of driving engine main thrust pin fixing device with the company's of helping function, comprise aircraft main thrust beam and be hinged on the thrust pin clip for stationary engine main thrust pin on aircraft main thrust beam, at described thrust pin clip, the one end with described aircraft main thrust beam hinge-point is provided with clip locating dowel pin for fixing thrust pin clip, also comprises:
Eyelet bolt, is hingedly arranged on one end that described aircraft main thrust beam is provided with clip locating dowel pin, and eyelet bolt rotates in perpendicular around its hinge-point;
Nut, matches with described eyelet bolt;
Described thrust pin clip also offer U-shaped opening away from the end, one end with described aircraft main thrust beam hinge-point, the width of described U-shaped opening is not less than the diameter of described eyelet bolt, in addition, the axis of described U-shaped opening, the axis of described clip locating dowel pin and the axis of described eyelet bolt are all positioned at same perpendicular.
Alternatively, the end, one end that described aircraft main thrust beam is provided with clip locating dowel pin vertically offers a groove, one end away from nut of described eyelet bolt has sleeve, is hinged in described groove by described eyelet bolt through described sleeve by a flat-headed pin.
Alternatively, described nut is band shoulder nut.
The beneficial effects of the utility model: the driving engine main thrust pin fixing device with the company's of helping function of the present utility model, screw thread loading is carried out by the nut tightened on eyelet bolt, thrust pin clip is closed put in place, thus realize the closed of thrust pin clip, thrust pin Fast Installation is put in place, improves driving engine installation effectiveness.
Accompanying drawing explanation
Accompanying drawing to be herein merged in specification sheets and to form the part of this specification sheets, shows and meets embodiment of the present utility model, and is used from specification sheets one and explains principle of the present utility model.
Fig. 1 is the structural representation of the driving engine main thrust pin fixing device according to the utility model embodiment with the company's of helping function;
Fig. 2 is eyelet bolt according to the utility model embodiment and nut structure schematic diagram.
Detailed description of the invention
Here will be described exemplary embodiment in detail, its sample table shows in the accompanying drawings.When description below relates to accompanying drawing, unless otherwise indicated, the same numbers in different accompanying drawing represents same or analogous key element.
As depicted in figs. 1 and 2, the driving engine main thrust pin fixing device with the company's of helping function of the present utility model, the thrust pin clip 3 comprising aircraft main thrust beam 1 and be hinged on for stationary engine main thrust pin 2 on aircraft main thrust beam 1.In addition, at thrust pin clip 3 away from the one end with aircraft main thrust beam 1 hinge-point, be vertically provided with the clip locating dowel pin 4 for fixing thrust pin clip 3.
The nut 6 that anchor fitting of the present utility model also comprises eyelet bolt 5 and matches.Eyelet bolt 5 is hingedly arranged on one end that aircraft main thrust beam 1 is provided with clip locating dowel pin 4, and eyelet bolt 5 can rotate in perpendicular around its hinge-point.Further, the axis of eyelet bolt 5 and the axis of clip locating dowel pin 4 are all positioned at same perpendicular.Nut 6 can be multiple applicable structure, selects band shoulder nut, with enlarged contact areas in the present embodiment.
Eyelet bolt 5 can be hinged on aircraft main thrust beam 1 with multiple applicable version, such as, by bearing or bearing pin etc.In the present embodiment, as shown in Figure 1, be the end, one end being provided with clip locating dowel pin 4 on aircraft main thrust beam 1, vertically offer a groove 11, the size of groove 11 can be chosen according to eyelet bolt 5, to ensure that eyelet bolt 5 can rotate around hinge therein.Further, groove 11 on the horizontal surface of aircraft main thrust beam 1 He on vertical plane, all there is opening, the installation of eyelet bolt 5 can be facilitated.In addition, have sleeve in one end away from nut 6 of eyelet bolt 5, sleeve adopts and the integrated structure of eyelet bolt 5, then is passed sleeve by a flat-headed pin 7 thus be hinged in above-mentioned groove 11 by eyelet bolt 5.
At thrust pin clip 3 away from the end, one end with aircraft main thrust beam 1 hinge-point, also offer U-shaped opening 31.The width of U-shaped opening 31 is not less than the diameter of eyelet bolt 5, and the axis of the axis of U-shaped opening 31 and eyelet bolt 5 is positioned at same perpendicular, that is to say, when eyelet bolt 5 turns to a certain position around its hinge (position as shown in Figure 1), a part for eyelet bolt 5 can be positioned at U-shaped opening 31.
During work, after eyelet bolt 5 is fixing with tack axle 7 and aircraft main thrust beam 1, put into from the side direction indentation, there of engine thrust pin card hoop 3, the nut 6 on eyelet bolt 5 is tightened by socket wrench, carry out screw thread loading, thrust pin clip 3 is closed and puts in place, after fixing hoop locating dowel pin 4, unload tack axle 7 and eyelet bolt 5, complete the erection work of driving engine main thrust pin 2.
The above; be only detailed description of the invention of the present utility model; but protection domain of the present utility model is not limited thereto; anyly be familiar with those skilled in the art in the technical scope that the utility model discloses; the change that can expect easily or replacement, all should be encompassed within protection domain of the present utility model.Therefore, protection domain of the present utility model should be as the criterion with the protection domain of described claim.
Claims (3)
1. one kind has the driving engine main thrust pin fixing device of the company's of helping function, comprise aircraft main thrust beam (1) and be hinged on the thrust pin clip (3) for stationary engine main thrust pin (2) on aircraft main thrust beam (1), described thrust pin clip (3), the one end with described aircraft main thrust beam (1) hinge-point is provided with clip locating dowel pin (4) for fixing thrust pin clip (3), it is characterized in that, also comprise:
Eyelet bolt (5), is hingedly arranged on one end that described aircraft main thrust beam (1) is provided with clip locating dowel pin (4), and eyelet bolt (5) rotates in perpendicular around its hinge-point;
Nut (6), matches with described eyelet bolt (5);
Described thrust pin clip (3) also offer U-shaped opening (31) away from the end, one end with described aircraft main thrust beam (1) hinge-point, the width of described U-shaped opening (31) is not less than the diameter of described eyelet bolt (5), in addition, the axis of the axis of described U-shaped opening (31), the axis of described clip locating dowel pin (4) and described eyelet bolt (5) is all positioned at same perpendicular.
2. anchor fitting according to claim 1, it is characterized in that, the end, one end that described aircraft main thrust beam (1) is provided with clip locating dowel pin (4) vertically offers a groove (11), one end away from nut (6) of described eyelet bolt (5) has sleeve, is hinged in described groove (11) by described eyelet bolt (5) through described sleeve by a flat-headed pin (7).
3. anchor fitting according to claim 1, is characterized in that, described nut (6) is band shoulder nut.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520133022.5U CN204489197U (en) | 2015-03-09 | 2015-03-09 | A kind of driving engine main thrust pin fixing device with the company's of helping function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520133022.5U CN204489197U (en) | 2015-03-09 | 2015-03-09 | A kind of driving engine main thrust pin fixing device with the company's of helping function |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204489197U true CN204489197U (en) | 2015-07-22 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520133022.5U Active CN204489197U (en) | 2015-03-09 | 2015-03-09 | A kind of driving engine main thrust pin fixing device with the company's of helping function |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204489197U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105173093A (en) * | 2015-09-24 | 2015-12-23 | 江西洪都航空工业集团有限责任公司 | Hanging and quick-disassembly type mounting node |
| CN105270638A (en) * | 2015-11-17 | 2016-01-27 | 江西洪都航空工业集团有限责任公司 | Aeroengine mounting device |
| CN108361247A (en) * | 2018-04-27 | 2018-08-03 | 安维车件(厦门)有限公司 | A kind of fast disassembly type armful clamp device |
-
2015
- 2015-03-09 CN CN201520133022.5U patent/CN204489197U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105173093A (en) * | 2015-09-24 | 2015-12-23 | 江西洪都航空工业集团有限责任公司 | Hanging and quick-disassembly type mounting node |
| CN105173093B (en) * | 2015-09-24 | 2018-01-30 | 江西洪都航空工业集团有限责任公司 | One kind suspension quick-release type installation section |
| CN105270638A (en) * | 2015-11-17 | 2016-01-27 | 江西洪都航空工业集团有限责任公司 | Aeroengine mounting device |
| CN108361247A (en) * | 2018-04-27 | 2018-08-03 | 安维车件(厦门)有限公司 | A kind of fast disassembly type armful clamp device |
| CN108361247B (en) * | 2018-04-27 | 2023-08-08 | 安维车件(厦门)有限公司 | Quick detach formula embraces and presss from both sides device |
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|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |