CN215491385U - Detection tool for aircraft engine and wing fixing support - Google Patents
Detection tool for aircraft engine and wing fixing support Download PDFInfo
- Publication number
- CN215491385U CN215491385U CN202121052590.4U CN202121052590U CN215491385U CN 215491385 U CN215491385 U CN 215491385U CN 202121052590 U CN202121052590 U CN 202121052590U CN 215491385 U CN215491385 U CN 215491385U
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- China
- Prior art keywords
- wing
- aircraft engine
- connecting point
- detection tool
- fixing sleeve
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- Expired - Fee Related
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- 238000001514 detection method Methods 0.000 title claims abstract description 21
- 238000003780 insertion Methods 0.000 claims description 6
- 230000037431 insertion Effects 0.000 claims description 6
- 230000005389 magnetism Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 210000001503 joint Anatomy 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000011895 specific detection Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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Abstract
The utility model relates to a detection tool for an aircraft engine and a wing fixing bracket, wherein two upright posts are vertically arranged at the rear part of a workbench, an upper inserting post is arranged above each upright post, a lower fixing sleeve is arranged below each upright post, the upper inserting post and the lower fixing sleeve are horizontally arranged forwards, the upper inserting post corresponds to an upper wing connecting point, the lower fixing sleeve corresponds to a lower wing connecting point, four positioning tables are arranged at the front part of the workbench, a stud is arranged above each positioning table, and each positioning table corresponds to an engine connecting point. The utility model can rapidly detect the aircraft engine and the wing fixing bracket, and the detection operation is simple, convenient and rapid.
Description
Technical Field
The utility model belongs to a tool device, relates to a detection tool, and particularly relates to a detection tool for an aircraft engine and a wing fixing bracket.
Background
The aircraft engine is located the wing front side, and for the stability of installation, wing, aircraft engine need be through the support connection an organic whole. The aircraft engine is located and fixed at the front part of the bracket, and the wings are fixed and connected at the rear part of the bracket. The assembly standards of the aircraft are very high, and the brackets for fixedly connecting the engine and the wings must meet certain standards. Because the support is formed by welding a plurality of branch pipes, whether the support meets the standard or not needs to be strictly detected, and the detection of the support needs to be completed by a detection tool.
Disclosure of Invention
The utility model aims to solve the problems and provides a detection tool for an aircraft engine and a wing fixing bracket, which can be used for quickly detecting the fixing bracket.
In order to solve the problems, the technical scheme adopted by the utility model is as follows:
the detection tool for the aircraft engine and the wing fixing support is characterized in that two upright columns are perpendicularly arranged at the rear portion of a workbench, an upper insertion column is arranged above each upright column, a lower fixing sleeve is arranged below each upright column, the upper insertion column and the lower fixing sleeve are horizontally arranged forwards, an upper insertion column corresponds to a connecting point on a wing, a lower fixing sleeve corresponds to a connecting point under the wing, four positioning tables are arranged on the front portion of the workbench, a stud is arranged above each positioning table, and each positioning table corresponds to a connecting point of the engine.
Furthermore, an upper nut and a lower nut are arranged on the stud.
Furthermore, the upper inserting column is provided with a front nut and a rear nut.
Further, the lower fixing sleeve is provided with magnetism.
The utility model has the beneficial effects that:
(1) the engine connecting point is correspondingly fixed on the stud of the positioning table, the wing upper connecting point is fixed on the upper inserting column, at the moment, the aircraft engine and the wing fixing bracket are in a natural state, and if the wing lower connecting point is correspondingly and abutted against the upper fixing sleeve and the lower fixing sleeve, the aircraft engine and the wing fixing bracket meet the standard; if the lower connecting point of the wing is not up or can not abut against the upper and lower fixed sleeves, the aircraft engine and the wing fixing bracket do not meet the standard.
(2) The utility model can realize the rapid detection of the aircraft engine and the wing fixing bracket, and the detection operation is simple, convenient and rapid.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic view of an aircraft engine and wing mounting bracket according to the present invention;
FIG. 2 is a schematic structural diagram of a detection tool for an aircraft engine and a wing fixing bracket according to the utility model;
FIG. 3 is a side view of the upper stake of the present invention;
FIG. 4 is a schematic view of a detection tool for an aircraft engine and a wing fixing bracket according to the utility model during detection;
reference numerals: a support platform-01, an engine connection point-02, an upper wing connection point-03 and a lower wing connection point-04; the device comprises a workbench-11, a vertical column-12, an upper inserting column-13, a front nut-131, a rear nut-132, a lower fixing sleeve-14, a positioning table-15, a stud-16, an upper nut-161 and a lower nut-162.
Detailed Description
The following detailed description of the preferred embodiments of the present invention is provided to enable those skilled in the art to more readily understand the advantages and features of the present invention and to clearly and unequivocally define the scope of the present invention.
In the description of the present invention, it is to be understood that the terms "length," "width," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the present invention and for simplicity in description, and are not intended to indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be construed as limiting the present invention. Furthermore, in the description of the present invention, moreover, "first", "second", "third", and "fourth" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be further noted that, unless otherwise specifically stated or limited, the terms "disposed," "mounted," "connected," and "connected" are used broadly and can be, for example, fixedly connected, detachably connected, or integrally connected, mechanically connected, electrically connected, directly connected, or connected through an intermediate medium, and can be used to connect two elements. It will be understood by those of ordinary skill in the art that the above terms in the present invention have the meaning of "a plurality" of two or more in each particular case unless specifically defined otherwise.
The detection tool for the aircraft engine and the wing fixing support is characterized in that two upright columns 12 are vertically arranged at the rear part of a workbench 11. An upper inserting column 13 is arranged above the upright column 12, and a lower fixing sleeve 14 is arranged below the upright column 12. The upper inserted column 13 and the lower fixed sleeve 14 are horizontally arranged forwards. The upper inserting column 13 corresponds to an upper wing connecting point 03, the lower fixing sleeve 14 corresponds to a lower wing connecting point 04, four positioning platforms 15 are arranged at the front part of the workbench 11, a stud 16 is arranged above the positioning platforms 15, and the positioning platforms 15 correspond to an engine connecting point 02.
In order to adjust the height of the positioning table, the stud 16 is provided with an upper nut 161 and a lower nut 162.
In order to adjust the position of the connection point on the wing in the fore-and-aft direction, the upper post 13 is provided with a front nut 131 and a rear nut 132.
In order to quickly butt joint the lower wing connecting point 04 and eliminate the influence caused by the shaking of the branch pipe connected with the lower wing connecting point 04, the lower fixing sleeve 14 is provided with magnetism.
The functions of the structures of the embodiment are described in detail in the following description with reference to the drawings:
the specific structure of the aircraft engine and the wing fixing bracket is shown in the attached figure 1 of the specification, and comprises a bracket platform 01 for fixing the engine, an engine connecting point 02 is arranged on the bracket platform 01, and an upper wing connecting point 03 and a lower wing connecting point 04 are arranged at the rear part of the bracket platform 01.
The detection tool for the aircraft engine and the wing fixing support is shown in the attached figure 2 of the specification, two upright columns 12 are vertically arranged at the rear part of a workbench 11, the two upright columns 12 are square pipes, the two upright columns 12 are oppositely arranged, and the bottoms of the two upright columns 12 are welded and fixed on the workbench. An upper inserting column 13 is arranged above the upright column 12, an upper fixing plate is arranged at the front part above the upright column 23, and the upper inserting column 13 is arranged on the upper fixing plate. A lower fixing sleeve 14 is arranged below the upright post 12, a lower fixing plate is arranged at the rear part below the upright post 23, and the lower fixing sleeve 14 is arranged on the lower fixing plate. The upper inserted column 13 and the lower fixed sleeve 14 are horizontally arranged forwards. The upper inserting column 13 corresponds to an upper wing connecting point 03, and the lower fixing sleeve 14 corresponds to a lower wing connecting point 04. Four positioning platforms 15 are arranged at the front part of the workbench 11, studs 16 are arranged above the positioning platforms 15, and the positioning platforms 15 correspond to the engine connection points 02. The engine connection point 02 is correspondingly fixed on a stud 16 of the positioning table 15, the upper inserting column 13 is used for fixing the upper wing connection point 03, and the lower fixing sleeve 14 is used for comparing the lower wing connection point 02.
For the specific detection operation process of the present embodiment, referring to fig. 4 in the specification, the engine connection point 02 is correspondingly fixed on the stud 16 of the positioning table 15, and the wing upper connection point 03 is fixed on the upper plug column 13. At the moment, the aircraft engine and the wing fixing bracket are in a natural state, and if the lower wing connecting point 04 corresponds to and abuts against the upper and lower fixing sleeves 14, the aircraft engine and the wing fixing bracket meet the standard; if the lower wing connecting point 04 is not up correspondingly or can not abut against the upper and lower fixing sleeves 14, the aircraft engine and the wing fixing bracket do not meet the standard.
In order to adjust the height of the positioning table or adjust the levelness, referring to the description and the attached fig. 2, the stud 16 is provided with an upper nut 161 and a lower nut 162. The bracket platform 01 for fixing the engine is in a horizontal position by adjusting the height of the lower nut 162, or the bracket platform 01 for fixing the engine is adjusted in height, and the upper nut 161 is used for fixing the bracket platform 01.
In order to adjust the position of the connection point on the wing in the front-rear direction, as shown in fig. 3 in the specification, the upper post 13 is provided with a front nut 131 and a rear nut 132. By adjusting the front and rear positions of the rear nut 132, the wing upper connection point 03 abuts against the rear nut 132, and the front nut 131 is used for fixing the wing upper connection point 03.
In order to quickly butt joint the lower wing connecting point 04 and eliminate the influence caused by the shaking of the branch pipe connected with the lower wing connecting point 04, the lower fixing sleeve 14 is provided with magnetism.
The foregoing shows and describes the general principles, essential features, and advantages of the utility model. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, that the preferred embodiments of the present invention are described above and the present invention is not limited to the preferred embodiments, and that various changes and modifications may be made without departing from the spirit and scope of the present invention and these changes and modifications are within the scope of the utility model as claimed.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.
Claims (4)
1. The detection tool for the aircraft engine and the wing fixing support is characterized in that two upright columns are perpendicularly arranged at the rear portion of a workbench, an upper insertion column is arranged above each upright column, a lower fixing sleeve is arranged below each upright column, the upper insertion column and the lower fixing sleeve are horizontally arranged forwards, an upper insertion column corresponds to a connecting point on a wing, a lower fixing sleeve corresponds to a connecting point under the wing, four positioning tables are arranged on the front portion of the workbench, a stud is arranged above each positioning table, and each positioning table corresponds to a connecting point of the engine.
2. The detection tool for the aircraft engine and the wing fixing bracket according to claim 1, wherein an upper nut and a lower nut are arranged on the stud.
3. The detection tool for the aircraft engine and the wing fixing bracket according to claim 1, wherein the upper inserting column is provided with a front nut and a rear nut.
4. The detection tool for the aircraft engine and the wing fixing bracket according to claim 1, wherein the lower fixing sleeve is magnetic.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121052590.4U CN215491385U (en) | 2021-05-17 | 2021-05-17 | Detection tool for aircraft engine and wing fixing support |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121052590.4U CN215491385U (en) | 2021-05-17 | 2021-05-17 | Detection tool for aircraft engine and wing fixing support |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215491385U true CN215491385U (en) | 2022-01-11 |
Family
ID=79778492
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121052590.4U Expired - Fee Related CN215491385U (en) | 2021-05-17 | 2021-05-17 | Detection tool for aircraft engine and wing fixing support |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215491385U (en) |
-
2021
- 2021-05-17 CN CN202121052590.4U patent/CN215491385U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20220111 |