CN220865671U - Aircraft skin valve universal joint installation frock - Google Patents
Aircraft skin valve universal joint installation frock Download PDFInfo
- Publication number
- CN220865671U CN220865671U CN202322636874.3U CN202322636874U CN220865671U CN 220865671 U CN220865671 U CN 220865671U CN 202322636874 U CN202322636874 U CN 202322636874U CN 220865671 U CN220865671 U CN 220865671U
- Authority
- CN
- China
- Prior art keywords
- base
- universal joint
- aircraft skin
- mounting
- utility
- Prior art date
- 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.)
- Active
Links
- 238000009434 installation Methods 0.000 title claims abstract description 20
- 239000000463 material Substances 0.000 claims abstract description 7
- -1 polytetrafluoroethylene Polymers 0.000 claims description 3
- 229920001343 polytetrafluoroethylene Polymers 0.000 claims description 3
- 239000004810 polytetrafluoroethylene Substances 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 abstract description 12
- 238000000034 method Methods 0.000 abstract description 6
- 239000002699 waste material Substances 0.000 abstract description 5
- 238000012360 testing method Methods 0.000 abstract description 4
- 238000013461 design Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000009423 ventilation Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Self-Closing Valves And Venting Or Aerating Valves (AREA)
Abstract
The utility model discloses an aircraft skin valve universal joint installation tool which comprises a base, a supporting component and an installation component. The top of the base is provided with a first bolt hole; the support component is arranged at the top end of the base and is fixedly connected with the base; and the installation assembly is arranged on one side of the support assembly, is connected with the base and is used for installing the universal joint and the gear output shaft. The utility model is based on ensuring safe and reliable product quality, reducing material waste and improving working efficiency. The utility model effectively improves the maintenance work efficiency, reduces the maintenance period, the cost and the occurrence probability of human errors, and improves the safety and the reliability of the test process.
Description
Technical Field
The utility model relates to the field of aircraft skin valve universal joints, in particular to an aircraft skin valve universal joint installation tool.
Background
The skin valve is arranged on the surface of the A320 skin and is an inlet valve and an outlet valve for ventilation of the electronic cabin. The covering valve mainly comprises an actuator cylinder, a shell, a universal joint and the like. The actuating cylinder is fixed on the shell by bolts, and the inner gear output shaft is connected with the universal joint. The aircraft maintenance personnel can manually rotate on the surface of the aircraft skin to change the telescopic length of the actuator cylinder. Thereby opening and closing the skin flap.
At present, no special tool for installing the universal joint exists in China, so that the working steps are complicated, the working is extremely easy to cause an improper navigation factor due to human errors, and meanwhile, the traditional installation method is complex in operation, low in working efficiency and poor in safety, and the internal gear of the actuator cylinder and the universal joint are damaged.
Therefore, how to solve the problem that the universal joint is convenient to install without damaging the components is a urgent need for those skilled in the art.
Disclosure of utility model
The utility model aims to provide an aircraft skin valve universal joint mounting tool, so that the problems in the prior art are solved.
In order to achieve the above purpose, the technical scheme adopted by the utility model is as follows:
The utility model provides an aircraft skin valve universal joint installation frock which characterized in that includes
The top of the base is provided with a first bolt hole;
the support component is arranged at the top end of the base and is fixedly connected with the base;
And the installation assembly is arranged on one side of the support assembly, is connected with the base and is used for installing the universal joint and the gear output shaft.
In some of the embodiments of the present invention,
The support assembly includes:
The first supporting block is L-shaped and is arranged at one end of the base far away from the first bolt hole;
And the bottom of the second supporting block is provided with a second bolt hole, and the second supporting block is arranged at the top of the first bolt hole.
In some embodiments, the mounting assembly is removably coupled to the base.
In some embodiments, the mounting assembly comprises:
the mounting seat is arranged at the bottom of the base, and one end of the mounting seat, which is far away from the base, is provided with a first groove;
and the pressing block is arranged at the top of the mounting seat, and a second groove is formed in one end, close to the mounting seat, of the pressing block.
In some embodiments, the first recess of the mount and the second recess of the press block form a universal joint channel.
In some embodiments, the pressing block is provided with a positioning pin for fixing the pressing block and the mounting seat.
In some embodiments, the mounting assembly is made of polytetrafluoroethylene material.
The beneficial effects of the utility model are as follows:
The utility model discloses an aircraft skin valve universal joint installation tool which comprises a base, a supporting component and an installation component. The top of the base is provided with a first bolt hole; the support component is arranged at the top end of the base and is fixedly connected with the base; and the installation assembly is arranged on one side of the support assembly, is connected with the base and is used for installing the universal joint and the gear output shaft. The utility model is based on ensuring safe and reliable product quality, reducing material waste and improving working efficiency. The utility model effectively improves the maintenance work efficiency, reduces the maintenance period, the cost and the occurrence probability of human errors, and improves the safety and the reliability of the test process.
Drawings
FIG. 1 is a schematic structural view of an aircraft skin flap universal joint mounting tooling of the present utility model;
FIG. 2 is a side view of an aircraft skin flap universal joint mounting tooling of the present utility model;
Fig. 3 is a top view of an aircraft skin flap universal joint mounting fixture of the present utility model.
In the accompanying drawings: 100. a base; 110. a first support block; 120. a second support block; 130. a mounting base; 140. briquetting; 150. a positioning pin; 160. and (5) a bolt.
Detailed Description
The present utility model will be described in further detail with reference to the accompanying drawings, in order to make the objects, technical solutions and advantages of the present utility model more apparent. It should be understood that the detailed description is presented by way of example only and is not intended to limit the utility model.
The utility model provides a quick installation scheme of a skin valve universal joint of an electronic cabin ventilation system, which aims to solve the technical problems that in the installation process of the skin valve universal joint of an electronic cabin air circulation system, due to the fact that special tools are lacking, the working steps are complicated and the operation is complex, the maintenance efficiency is low, the safety and the stability are poor, and meanwhile, the generation of an navigable factor is easy to cause in the prior art.
Referring to fig. 1, 2 and 3, an aircraft skin flap universal joint mounting fixture is shown, comprising a base 100, a support assembly and a mounting assembly.
The base 100, the top is provided with a first bolt hole. The support component is arranged at the top end of the base 100 and is fixedly connected with the base 100. And the installation assembly is arranged on one side of the support assembly, is connected with the base 100 and is used for installing the universal joint and the gear output shaft. In this embodiment, the base 100 is provided to hold the tooling parts and to distribute the pressure from the press during operation. The utility model is based on ensuring safe and reliable product quality, reducing material waste and improving working efficiency. The utility model effectively improves the maintenance work efficiency, reduces the maintenance period, the cost and the occurrence probability of human errors, and improves the safety and the reliability of the test process.
In some embodiments, the support assembly includes a first support block 110 having an "L" shape disposed at an end of the base remote from the first bolt hole. And a second bolt hole is formed in the bottom of the second support block 120, and the second support block 120 is arranged at the top of the first bolt hole. In this embodiment, the first supporting block 110 is fixed on the base 100. Acting on the support rams and the limit, the dimensions are based on the part lay flat design, avoiding the rams from moving away from the mounting area during operation. The second supporting block 120 is fixed on the tool base 100. Acting on the support universal joint and the spline nut. According to the horizontal lying design of the universal joint and the spline nut, the phenomenon that the pin holes are not aligned due to shaking of the universal joint in the operation process is avoided. The installation pin is not in place, damages the universal joint pin hole, produces human error, leads to maintenance time and cost waste.
In some embodiments, the mounting assembly is removably coupled to the base 100.
In some embodiments, the mounting assembly includes a mounting base 130 disposed at the bottom of the base 100, and a first recess is formed at an end of the mounting base 130 away from the base 100. The pressing block 140 is arranged at the top of the mounting seat 130, and a second groove is formed in one end, close to the mounting seat 130, of the pressing block 140.
In some embodiments, the first recess of the mount 130 and the second recess of the press block 140 form a universal joint channel.
In some embodiments, the pressing block 140 is provided with a positioning pin 150 for fixing the pressing block 140 to the mounting base 130.
In some embodiments, the mounting assembly is made of polytetrafluoroethylene material.
In this embodiment, the mounting base 130, the pressing block 140, the positioning pin 150 are used cooperatively. Acting on the universal joint and the gear output shaft. The mounting seat 130 is supported at the joint of the universal joint and the gear output shaft, and the mounting seat 130 adopts an unfixed form, so that the position of the mounting seat 130 can be finely adjusted according to the actual mounting condition. The L-shaped design of the first support block 110 prevents the mount 130 from moving too far to function. The pin mates the press block 140 with the tight fit when the universal joint is mounted on the gear output shaft. After the position is adjusted, the universal joint and the gear output shaft can be directly connected together by using a punch tool through pins. This saves maintenance time and reduces the occurrence of human errors. Realizing rapid assembly.
By adopting the technical scheme disclosed by the utility model, the following beneficial effects are obtained:
The utility model discloses an aircraft skin valve universal joint installation tool which comprises a base 130, a supporting component and an installation component. The base 100, the top is provided with a first bolt hole. The support assembly is disposed at the top end of the base 100 and fixedly connected with the base 130. And the installation component is arranged on one side of the support component, is connected with the base 130 and is used for installing the universal joint and the gear output shaft. The utility model is based on ensuring safe and reliable product quality, reducing material waste and improving working efficiency. The utility model effectively improves the maintenance work efficiency, reduces the maintenance period, the cost and the occurrence probability of human errors, and improves the safety and the reliability of the test process.
The foregoing is merely a preferred embodiment of the present utility model and it should be noted that modifications and adaptations to those skilled in the art may be made without departing from the principles of the present utility model, which is also intended to be covered by the present utility model.
Claims (7)
1. Aircraft skin valve universal joint installation frock, its characterized in that includes:
the top of the base is provided with a first bolt hole;
The support component is arranged at the top end of the base and is fixedly connected with the base;
And the installation assembly is arranged on one side of the support assembly, is connected with the base and is used for installing the universal joint and the gear output shaft.
2. The aircraft skin flap universal joint mounting fixture of claim 1, wherein,
The support assembly includes:
the first support block is L-shaped and is arranged at one end of the base far away from the first bolt hole;
The second supporting block is provided with a second bolt hole at the bottom, and the second supporting block is arranged at the top of the first bolt hole.
3. The aircraft skin flap universal joint mounting fixture of claim 2, wherein,
The mounting assembly is detachably connected with the base.
4. The aircraft skin flap universal joint mounting fixture of claim 3, wherein,
The mounting assembly includes:
The mounting seat is arranged at the bottom of the base, and one end of the mounting seat, which is far away from the base, is provided with a first groove;
the briquetting is in the top of mount pad, the briquetting is close to the one end of mount pad is equipped with the second recess.
5. The aircraft skin flap universal joint mounting fixture of claim 4, wherein,
The first groove of the mounting seat and the second groove of the pressing block form a universal joint channel.
6. The aircraft skin flap universal joint mounting fixture of claim 4, wherein,
The pressing block is provided with a locating pin for fixing the pressing block and the mounting seat.
7. The aircraft skin flap universal joint mounting fixture of claim 6, wherein,
The mounting component is made of polytetrafluoroethylene materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322636874.3U CN220865671U (en) | 2023-09-27 | 2023-09-27 | Aircraft skin valve universal joint installation frock |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322636874.3U CN220865671U (en) | 2023-09-27 | 2023-09-27 | Aircraft skin valve universal joint installation frock |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220865671U true CN220865671U (en) | 2024-04-30 |
Family
ID=90821053
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322636874.3U Active CN220865671U (en) | 2023-09-27 | 2023-09-27 | Aircraft skin valve universal joint installation frock |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220865671U (en) |
-
2023
- 2023-09-27 CN CN202322636874.3U patent/CN220865671U/en active Active
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| GR01 | Patent grant |