CN215639928U - Balance test tool for airplane control surface - Google Patents
Balance test tool for airplane control surface Download PDFInfo
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- CN215639928U CN215639928U CN202121715196.4U CN202121715196U CN215639928U CN 215639928 U CN215639928 U CN 215639928U CN 202121715196 U CN202121715196 U CN 202121715196U CN 215639928 U CN215639928 U CN 215639928U
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- end plate
- cross beam
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- profile
- clamping plate
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Abstract
The utility model discloses an aircraft rudder surface balance test tool which comprises a support column fixed on the bottom surface of a workbench, wherein a cross beam is installed on the workbench, an arc-shaped clamping plate, a profile clamping plate and two end plates are installed on the side surface of the cross beam, and the arc-shaped clamping plate and the profile clamping plate are arranged between the two end plates.
Description
Technical Field
The utility model relates to the technical field of aircraft production, in particular to an aircraft control surface test tool.
Background
In order to prevent the airplane control surface from shaking caused by unbalance during flight, a balance test must be carried out after the assembly of the control surface is finished. The balance test tool is an important link for carrying out balance test on the control surface of the airplane. The conventional control surface balancing tool is single in design function, complex in installation, long in production period and high in cost.
SUMMERY OF THE UTILITY MODEL
Aiming at the defects in the prior art, the utility model provides the aircraft control surface balance test tool which can realize the assembly and debugging of the aircraft control surfaces with different specifications, is convenient to install and has lower cost.
The purpose of the utility model is realized as follows: the utility model provides an aircraft control surface balance test frock, is including fixing the support column in the workstation bottom surface, install the crossbeam on the workstation, the side-mounting of crossbeam has arc cardboard, profile cardboard and first end plate, second end plate, and arc cardboard and profile cardboard setting are between first end plate, second end plate.
When the test platform is used, the workbench is supported on the ground, the cross beam is arranged on the workbench, the arc-shaped clamping plate, the profile clamping plate, the first end plate and the second end plate are arranged on the cross beam, and finally the control surface of the airplane to be tested is arranged on the arc-shaped clamping plate and the profile clamping plate, and the first end plate and the second end plate at two ends can easily realize clamping at two ends.
Compared with the prior art, the utility model has the beneficial effects that:
the utility model realizes the assembly of the whole work in an installation mode, is more convenient and faster compared with the traditional welding work, and can adjust the specification in the installation process, thereby realizing the test of the control surfaces of airplanes with different specifications.
In order to enable the workbench to be in a horizontal plane, the supporting columns are lifting supporting columns.
In order to make the installation and the adjustment of the cross beam more convenient, a plurality of first through holes are formed in the workbench, second through holes are correspondingly formed in the bottom of the cross beam, and the cross beam and the workbench are installed together through the second through holes in the bottom of the cross beam and the first through holes in the workbench by the quick locking pins.
In order to make the installation and adjustment of arc cardboard, profile cardboard more convenient, the second through-hole has also been seted up to the side of crossbeam, correspond on arc cardboard, profile cardboard and first end plate, the second end plate and seted up the through-hole, quick fitting pin passes through the through-hole and installs arc cardboard, profile cardboard and first end plate, second end plate on the crossbeam.
In order to further make the installation and adjustment of the arc-shaped clamping plate and the profile clamping plate more convenient, the beam is of a square hollow structure, and the top of the beam is provided with a plurality of operation holes corresponding to the arc-shaped clamping plate and the profile clamping plate.
In order to ensure that the installation of the arc-shaped clamping plate and the profile clamping plate is more reliable, the arc-shaped clamping plate, the profile clamping plate, the first end plate and the second end plate are installed on the cross beam through the base plate.
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 embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
Fig. 1 is a schematic structural diagram of embodiment 1 of the present invention.
Fig. 2 is a schematic structural view of the cross beam in embodiment 1.
Wherein, 1 workstation, 1a through-hole, 2 support columns, 3 crossbeams, 3a through-holes, 3b handle hole, 4 arc cardboard, 5 profile cardboards, the first end plate of 6a, 6b second end plate, 7 backing plates.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example 1
As shown in fig. 1-2, the aircraft control surface balance test tool comprises a liftable support column 2 fixed on the bottom surface of a workbench 1 (in this embodiment, adjustment can be realized by adopting a threaded structure), a cross beam 3 is installed on the workbench 1, an arc-shaped clamping plate 4, a profile clamping plate 5, a first end plate 6a and a second end plate 6b are installed on the side surface of the cross beam 3, and the arc-shaped clamping plate 4 and the profile clamping plate 5 are arranged between the first end plate 6a and the second end plate 6 b.
In this embodiment, the workbench 1 is provided with a plurality of first through holes 1a, the bottom of the cross beam 3 is also correspondingly provided with a second through hole 3a, and the quick locking pin is used for installing the cross beam 3 and the workbench 1 together through the second through hole 3a at the bottom of the cross beam 3 and the first through hole 1a on the workbench 1.
In this embodiment, second through-hole 3a has been seted up to crossbeam 3's side, arc cardboard 4, profile cardboard 5 and first end plate 6a, correspond on the second end plate 6b and seted up the through-hole (arc cardboard 4 in this embodiment, profile cardboard 5 can set up two sets ofly, and more have need carry out the adaptability and adjust), quick fitting pin passes through second through-hole 3a with arc cardboard 4, profile cardboard 5 and first end plate 6a, second end plate 6b installs on crossbeam 3, crossbeam 3 is square hollow structure, and crossbeam 3's top has seted up a plurality ofly and arc cardboard 4, the handle hole 3b that profile cardboard 5 corresponds, hand and instrument stretch into when handle hole 3b is convenient for install, arc cardboard 4, profile cardboard 5 and first end plate 6a, second end plate 6b installs on crossbeam 3 through the backing plate.
When the test platform is used, the workbench 1 is supported on the ground, the level is adjusted through the support columns 2, the crossbeam 3 is installed on the workbench 1 through the quick locking pins after the position is adjusted, the arc-shaped clamping plate 4, the profile clamping plate 5, the first end plate 6a and the second end plate 6b are installed on the crossbeam 3 in a matched and quick locking manner, finally, the airplane rudder surface to be tested is installed on the arc-shaped clamping plate 4 and the profile clamping plate 5, and the first end plate 6a and the second end plate 6b at two ends can be clamped at two ends easily; the cambered surface cardboard is used for detecting the aileron and rotates in-process and obturating the board clearance, and profile cardboard 5 is used for adjusting balance test's neutral position and detects the aileron profile.
The balance test tool is suitable for airplane control surface balance tests, the aileron support and the clamping plate are designed by taking the three-dimensional flexible platform as a reference, and the support is efficiently connected with the workbench 1 by utilizing the quick locking pin. The molded surface of cardboard only needs to be adjusted to the aircraft control surface of different models can. The dynamic balance test tool can not only carry out balance test, but also be used for checking the difference of the molded surface and the scissors, thereby improving the application range of the fixture, shortening the design and manufacturing period of the fixture and saving the manufacturing cost of the fixture.
The above description of the embodiments is only intended to facilitate the understanding of the method of the utility model and its core idea. It should be noted that, for those skilled in the art, it is possible to make various improvements and modifications to the present invention without departing from the principle of the present invention, and those improvements and modifications also fall within the scope of the claims of the present invention.
Claims (6)
1. The utility model provides an aircraft control surface balance test frock, its characterized in that, is including fixing support column (2) in workstation (1) bottom surface, install crossbeam (3) on workstation (1), the side-mounting of crossbeam (3) has arc cardboard (4), profile cardboard (5) and first end plate (6a) and second end plate (6b), and arc cardboard (4) and profile cardboard (5) set up between first end plate (6a) and second end plate (6 b).
2. The aircraft control surface balance test tool according to claim 1, characterized in that the support column (2) is a liftable support column (2).
3. The aircraft control surface balance test tool according to claim 1 or 2, wherein the workbench (1) is provided with a plurality of first through holes (1a), the bottom of the cross beam (3) is correspondingly provided with second through holes (3a), and the cross beam (3) and the workbench (1) are installed together by the quick locking pin through the second through holes (3a) at the bottom of the cross beam (3) and the first through holes (1a) on the workbench (1).
4. The aircraft control surface balance test tool according to claim 1 or 2, wherein a second through hole (3a) is formed in the side surface of the cross beam (3), through holes are correspondingly formed in the arc-shaped clamping plate (4), the profile clamping plate (5), the first end plate (6a) and the second end plate (6b), and the arc-shaped clamping plate (4), the profile clamping plate (5), the first end plate (6a) and the second end plate (6b) are installed on the cross beam (3) through the through holes by the quick locking pin.
5. The aircraft control surface balance test tool according to claim 4, wherein the cross beam (3) is of a square hollow structure, and a plurality of operation holes (3b) corresponding to the arc-shaped clamping plates (4) and the profile clamping plates (5) are formed in the top of the cross beam (3).
6. The aircraft control surface balance test tool according to claim 4, characterized in that the arc-shaped clamping plate (4), the profile clamping plate (5) and the first end plate (6a) and the second end plate (6b) are mounted on the cross beam (3) through backing plates.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121715196.4U CN215639928U (en) | 2021-07-27 | 2021-07-27 | Balance test tool for airplane control surface |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121715196.4U CN215639928U (en) | 2021-07-27 | 2021-07-27 | Balance test tool for airplane control surface |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215639928U true CN215639928U (en) | 2022-01-25 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202121715196.4U Active CN215639928U (en) | 2021-07-27 | 2021-07-27 | Balance test tool for airplane control surface |
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| CN (1) | CN215639928U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116986015A (en) * | 2023-09-28 | 2023-11-03 | 航天江南集团有限公司 | Steering engine detection device |
-
2021
- 2021-07-27 CN CN202121715196.4U patent/CN215639928U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116986015A (en) * | 2023-09-28 | 2023-11-03 | 航天江南集团有限公司 | Steering engine detection device |
| CN116986015B (en) * | 2023-09-28 | 2023-12-12 | 航天江南集团有限公司 | Steering engine detection device |
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