CN113602524B - Test platform for flexible skin performance of trailing edge camber wing - Google Patents
Test platform for flexible skin performance of trailing edge camber wing Download PDFInfo
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- CN113602524B CN113602524B CN202110922819.3A CN202110922819A CN113602524B CN 113602524 B CN113602524 B CN 113602524B CN 202110922819 A CN202110922819 A CN 202110922819A CN 113602524 B CN113602524 B CN 113602524B
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- edge bending
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- 238000012360 testing method Methods 0.000 title claims abstract description 53
- 238000005452 bending Methods 0.000 claims abstract description 57
- 238000011056 performance test Methods 0.000 claims abstract description 21
- 239000000463 material Substances 0.000 claims abstract description 11
- 238000009434 installation Methods 0.000 claims description 22
- 238000011900 installation process Methods 0.000 claims description 6
- 238000000034 method Methods 0.000 claims description 4
- 238000010998 test method Methods 0.000 claims 1
- 238000013461 design Methods 0.000 description 6
- 238000011160 research Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000012372 quality testing Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
A platform for trailing edge camber wing flexible skin performance testing, comprising: the device comprises a platform bracket (1) for installing the flexible skin of the trailing edge bending wing, a flexible skin (2) of the trailing edge bending wing to be tested, a connecting support (3) for fixing the platform bracket (1), a driving unit (5) for driving the flexible skin of the trailing edge bending wing to deform, a mounting corner piece (6) for fixing the flexible skin of the trailing edge bending wing, and a mounting panel (4) for fixing the driving unit (5) and the mounting corner piece (6) of the flexible skin of the trailing edge bending wing. The test platform for the related test of the performance of the flexible skin of the trailing edge camber wing has the advantages of simple structure, high reliability, low cost and rapid assembly, and is suitable for the performance test of the flexible skin of the trailing edge camber wing with various materials, various sizes and various driving modes.
Description
Technical Field
The invention relates to a test platform for the performance of a flexible skin of a trailing edge camber wing.
Background
The self-adaptive wing is a wing which can automatically change the geometrical parameters of the wing according to the flight condition in flight so as to obtain the optimal aerodynamic performance, and the wing does not have a conventional rigidly deflected aileron, a flap, a slat and a spoiler, and can achieve the optimal target appearance by deformation according to the task condition. The deformation mode of the self-adaptive wing is mainly divided into two modes of out-of-plane deformation and in-plane deformation, wherein one main mode of in-plane deformation is trailing edge deflection, and the mode mainly changes the pressure distribution of the surface of the trailing edge of the wing by changing the deflection of the trailing edge of the wing, so that the optimal target appearance required by a task is achieved.
The trailing edge camber wing is continuously researched and developed in recent years because of the unique aerodynamic performance advantages and wide flight envelope adaptability, but the existing research on the flexible skin of the trailing edge camber wing mainly focuses on the individual performance of the flexible skin or the selection and the dimensional design of the flexible skin material according to the corresponding trailing edge camber wing structure, however, the research and the design method can only simply test the performance of the flexible skin or need to design and manufacture the complete trailing edge camber wing structure, thus the test is insufficient or consumes a great deal of time and cost, and the method is not suitable for testing the performance of the flexible skin of the trailing edge camber wing with different types, different sizes and different driving modes.
In addition, a new type of trailing edge camber airfoil flexible skin often requires corresponding deformation quality testing and deformability testing in combination with a specific trailing edge camber airfoil structure to determine its performance and applicability. Therefore, a complete trailing edge camber wing structure is required to be designed independently for testing the performance of the flexible skin of the trailing edge camber wing, and when the size of the flexible skin of the trailing edge camber wing changes, the corresponding trailing edge camber wing structure is required to be redesigned for testing, so that the testing period of the flexible skin of the trailing edge camber wing is longer, and the testing cost is higher.
Therefore, a platform suitable for testing the flexible skin performance of the trailing edge bending wing with different driving modes, different materials and different sizes, which is simple to use, convenient to replace and low in cost, needs to be developed so as to realize the test of the flexible skin performance of the trailing edge bending wing with a wider application range.
Disclosure of Invention
The main design ideas of the invention include:
the test of the flexible skin performance of the trailing edge camber wing with different driving modes, different materials and different sizes can be realized through the test platform of the flexible skin performance of the trailing edge camber wing;
the drive unit of the flexible skin of the trailing edge bending wing can be replaced;
the number and the positions of the connecting pieces can be adjusted according to the size of the flexible skin of the trailing edge camber wing;
low cost, simple connection mode, strong adjustable capability and wider application range.
Aiming at the problems of multiple types of flexible skins of the trailing edge camber wing, wide size change range, multiple driving modes and higher test cost, the invention provides a platform for testing the performance of the flexible skins of the trailing edge camber wing, which has simple installation, low cost, stronger adjustability and wider application range, and is characterized in that the platform for testing the performance of the flexible skins of the trailing edge camber wing comprises:
a platform bracket for fixing the trailing edge bending wing flexible skin testing device;
a fixed trailing edge camber wing flexible skin driving unit and a mounting panel connected with the corner piece;
the connecting support is connected with the external ground or the table top;
a driving unit for driving the trailing edge camber wing flexible skin;
and fixing the mounting corner piece of the trailing edge camber wing flexible skin.
According to one embodiment of the invention, there is provided a platform for trailing edge camber airfoil flexible skin performance testing, comprising:
the platform bracket is used for installing and fixing a device for testing the flexible skin of the trailing edge bending wing;
a mounting panel is arranged at the upper part of the platform bracket and is used for connecting the driving unit of the flexible skin of the trailing edge camber wing and a mounting corner piece of the flexible skin of the trailing edge camber wing;
connecting supports are arranged on the left side and the right side of the lower part of the platform support and used for fixing the flexible skin test platform of the trailing edge camber wing;
the two ends of the front surface of the mounting panel are provided with a trailing edge bending wing flexible skin driving unit for driving the deformation of the trailing edge bending wing flexible skin to be tested;
and a plurality of mounting corner pieces of the flexible skin of the trailing edge camber wing are arranged in the middle of the front of the mounting panel and are used for mounting and fixing the flexible skin of the trailing edge camber wing to be tested.
The advantages of the invention include:
1) The flexible skin driving unit is applicable to different deformation modes, and can be replaced with different trailing edge bending wing flexible skin driving units according to test requirements;
2) The method is applicable to various flexible skins, and the flexible skins of the trailing edge bending wing with different materials and different sizes can be replaced according to test requirements;
3) The application test range is wide, and the requirements of different test sites can be met;
4) The practicability is strong, the cost is low, the assembly and the disassembly are convenient, and the reliability is high.
Drawings
FIG. 1 shows a schematic composition of a trailing edge camber airfoil flexible skin performance test platform according to one embodiment of the invention.
FIG. 2 shows a schematic structural diagram of a trailing edge camber airfoil flexible skin performance test platform according to one embodiment of the invention.
Detailed Description
The following describes a specific embodiment of the present invention with reference to the drawings.
The invention adopts a modularized design, and the driving unit 5 of the flexible skin of the trailing edge bending wing and the flexible skin 2 of the trailing edge bending wing to be tested are connected through the mounting panel 4 to form a flexible skin testing module of the trailing edge bending wing, and then the flexible skin testing module is connected with the outside through the platform bracket 1 for relevant testing of the performance of the flexible skin of the trailing edge bending wing. The test platform has the advantages of simple structure, high reliability, low cost and rapid assembly, and is suitable for performance test of the trailing edge bending wing flexible skin of various materials, various sizes and various driving modes.
A platform for trailing edge camber airfoil flexible skin performance testing according to one embodiment of the invention is shown in fig. 1 and 2.
The platform for testing the performance of the flexible skin of the trailing edge bending wing according to one embodiment of the invention is designed by adopting a metal material and comprises the following components:
a platform bracket 1 of the trailing edge bending wing flexible skin testing device is arranged,
the trailing edge camber airfoil flexible skin 2 to be tested,
a connecting support 3 for fixing the platform bracket 1,
a driving unit 5 for driving the deformation of the flexible skin of the trailing edge camber airfoil,
and fixing the mounting corner pieces 6 of the flexible skin of the trailing edge camber wing, and fixing the mounting panel 4 of the flexible skin mounting corner pieces 6 of the trailing edge camber wing and the driving unit 5 of the flexible skin of the trailing edge camber wing.
The invention adopts a modularized design, and the driving unit 5 of the flexible skin of the trailing edge bending wing and the flexible skin 2 of the trailing edge bending wing to be tested are connected through the mounting panel 4 to form a flexible skin testing module of the trailing edge bending wing, and then the flexible skin testing module is connected with the outside through the platform bracket 1 for relevant testing of the performance of the flexible skin of the trailing edge bending wing. The test platform has the advantages of simple structure, high reliability, low cost and rapid assembly, and is suitable for performance test of the trailing edge bending wing flexible skin of various materials, various sizes and various driving modes.
According to one embodiment of the invention, a mounting panel 4 is arranged on the upper side of the platform bracket 1 and is used as a fixed support end of a rear edge camber wing flexible skin driving unit 5 and a mounting corner piece 6 of the rear edge camber wing flexible skin; the left side and the right side of the lower part of the platform bracket 1 are provided with connecting supports 3 which are used as connecting devices of the flexible skin test platform of the trailing edge camber wing and an external supporting surface; the two ends of the front surface of the mounting panel 4 are provided with a rear edge bending wing flexible skin driving unit 5 which is used as a driver for deformation of the rear edge bending wing flexible skin 2 to be tested; a plurality of mounting corner pieces 6 of the flexible skin of the trailing edge camber wing are arranged in the middle of the front of the mounting panel 4 and serve as fixed supporting ends of the flexible skin 2 of the trailing edge camber wing to be tested; the number and the positions of the connectors are adjusted according to the test content, so that the performance test of the trailing edge bending wing flexible skin aiming at different driving modes, different materials and different sizes can be realized.
The mounting panel 4 comprises an upper mounting panel 10 and a lower mounting panel 9, the left and right ends of the mounting panel 4 are respectively connected with the platform bracket 1 by connecting corner fittings,
the distance between the upper mounting panel 10 and the lower mounting panel 9 can be adjusted according to the thickness of the trailing edge camber airfoil, so that the performance test of the trailing edge camber airfoil flexible skin with various different airfoils and different chord lengths can be adapted.
The installation corner pieces 6 of the trailing edge camber wing flexible skin are respectively provided with a chute 7 and a threaded hole 8 for connecting the installation panel 4 and the trailing edge camber wing flexible skin 2 to be tested,
the number and the distance between the mounting corner pieces 6 of the trailing edge camber wing flexible skin can be determined according to the requirements of test contents, so that the performance test of the trailing edge camber wing flexible skin 2 to be tested with different sizes and different materials is realized,
the relative position of the trailing edge camber wing flexible skin 2 to be tested can be ensured by adjusting the position of the bolt in the chute 7 during the installation process.
The connecting support 3 is a right-angle support, holes on two sides of the support are through holes, the platform support 1 is fixed on the ground or a table top through bolts,
the number and mounting position of the connection holders 3 can be selected according to the requirements of the actual test contents.
The trailing edge camber wing flexible skin driving unit is provided with a fixed mechanical interface, and can be connected with the mounting panel 4 through bolts.
The driving unit 5 of the flexible skin of the trailing edge bending wing with different sizes and driving modes can be replaced according to the test requirements, so that the performance test of the flexible skin of the trailing edge bending wing with different wing types and different driving modes is realized.
In the installation process, the installation distance between the flexible skin driving units 5 of the trailing edge camber wing can be adjusted according to different flexible skin sizes, so that the performance test of the flexible skin of the trailing edge camber wing with different sizes is realized.
Claims (2)
1. A performance test platform for a trailing edge camber wing flexible skin, comprising:
a) A platform bracket (1);
b) A mounting panel (4) arranged at the upper part of the platform bracket (1);
c) The mounting corner piece (6) is used for connecting the trailing edge camber wing flexible skin driving unit (5) and the trailing edge camber wing flexible skin;
d) The connecting supports (3) are arranged at the left side and the right side of the lower part of the platform bracket (1) and are used for fixing the flexible skin test platform of the trailing edge bending wing;
e) The rear edge bending wing flexible skin driving units (5) are arranged at the two ends of the front surface of the mounting panel (4) and are used for driving the deformation of the rear edge bending wing flexible skin (2) to be tested;
f) A plurality of mounting corner pieces (6) for connecting the mounting panel (4) and fixing the trailing edge camber wing flexible skin (2) to be tested,
wherein:
the mounting panel (4) comprises an upper mounting panel (10) and a lower mounting panel (9),
the distance between the upper mounting panel (10) and the lower mounting panel (9) is adjusted according to the thickness of the trailing edge camber wing, so as to adapt to the performance test of various kinds of wing profiles and trailing edge camber wing flexible skins with different chord lengths,
the left end and the right end of the installation panel (4) are respectively connected with the platform bracket (1) by connecting corner fittings,
the connecting support (3) is a right-angle support, holes on two sides of the support are through holes, the platform support (1) is fixed on the ground or the table top through bolts,
the number and the installation position of the connecting supports (3) can be selected according to the requirements of the actual test content,
the rear edge bending wing flexible skin driving unit is provided with a fixed mechanical interface which is connected with the mounting panel (4) through bolts,
the flexible skin driving unit (5) of the trailing edge bending wing with different sizes and driving modes is replaced according to the test requirement, thereby realizing the performance test of the flexible skin of the trailing edge bending wing with different wing shapes and different driving modes,
in the installation process, the installation distance between the flexible skin driving units (5) of the trailing edge variable camber wing is adjusted according to different flexible skin sizes, so that the performance test of the flexible skin of the trailing edge variable camber wing with different sizes is realized,
the installation corner piece (6) of the trailing edge bending wing flexible skin is respectively provided with a chute (7) and a threaded hole (8) for connecting the installation panel (4) and the trailing edge bending wing flexible skin (2) to be tested,
the number of the installation corner pieces (6) of the trailing edge bending wing flexible skin and the distance between the installation corner pieces are determined according to the requirements of test contents, so that the performance test of the trailing edge bending wing flexible skin (2) to be tested with different sizes and different materials is realized,
the relative position of the trailing edge bending wing flexible skin (2) to be measured is ensured by adjusting the position of the bolt in the chute in the installation process.
2. A test method based on a performance test platform for a trailing edge camber wing flexible skin, wherein the performance test platform comprises:
a platform bracket (1);
the mounting panel (4) is arranged at the upper part of the platform bracket (1), and the mounting panel (4) comprises an upper mounting panel (10) and a lower mounting panel (9);
connecting supports (3) arranged at the left and right sides of the lower part of the platform bracket (1) are used for fixing the flexible skin test platform of the trailing edge bending wing,
the method is characterized by comprising the following steps of:
the two ends of the front surface of the installation panel (4) are provided with a trailing edge bending wing flexible skin driving unit (5),
the installation corner piece (6) is used for connecting the trailing edge bending wing flexible skin driving unit (5) and the trailing edge bending wing flexible skin,
the flexible skin driving unit (5) of the trailing edge bending wing is used for driving the deformation of the flexible skin (2) of the trailing edge bending wing to be tested,
a plurality of installation corner pieces (6) are used for connecting the installation panel (4) and fixing the trailing edge bending wing flexible skin (2) to be tested,
the distance between the upper mounting panel (10) and the lower mounting panel (9) is adjusted according to the thickness of the trailing edge camber wing, so that the performance test of the flexible skin of the trailing edge camber wing with various different wing profiles and different chord lengths is adapted,
the mechanical interface on the flexible skin driving unit of the trailing edge bending wing is connected with the mounting panel (4) through bolts,
according to the test requirement, the drive unit (5) of the flexible skin of the trailing edge bending wing with different sizes and drive modes is replaced, thereby realizing the performance test of the flexible skin of the trailing edge bending wing with different wing shapes and different drive modes,
in the installation process, the installation distance between the flexible skin driving units (5) of the trailing edge variable camber wing is adjusted according to different flexible skin sizes, so that the performance test of the flexible skin of the trailing edge variable camber wing with different sizes is realized,
wherein:
the left end and the right end of the installation panel (4) are respectively connected with the platform bracket (1) by connecting corner pieces,
the connecting support (3) is a right-angle support, holes on two sides of the support are through holes, the platform support (1) is fixed on the ground or the table top through bolts,
the number and the installation position of the connecting supports (3) are selected according to the test requirement,
the installation panel (4) is connected with the flexible skin (2) of the trailing edge bending wing to be tested through a chute (7) and a threaded hole (8) which are arranged on the installation corner piece (6) of the flexible skin of the trailing edge bending wing,
according to the requirement of the test content, the number of the installation corner pieces (6) of the flexible skin of the trailing edge bending wing and the distance between the installation corner pieces are selected, so that the performance test of the flexible skin (2) of the trailing edge bending wing to be tested with different sizes and different materials is realized,
in the installation process, the relative position of the trailing edge bending wing flexible skin (2) to be tested is kept by adjusting the position of the bolt in the chute.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110922819.3A CN113602524B (en) | 2021-08-11 | 2021-08-11 | Test platform for flexible skin performance of trailing edge camber wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110922819.3A CN113602524B (en) | 2021-08-11 | 2021-08-11 | Test platform for flexible skin performance of trailing edge camber wing |
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| Publication Number | Publication Date |
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| CN113602524A CN113602524A (en) | 2021-11-05 |
| CN113602524B true CN113602524B (en) | 2024-01-30 |
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| CN110666714A (en) * | 2019-09-27 | 2020-01-10 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Wing anchor clamps and wing test system |
| CN111661312A (en) * | 2020-05-20 | 2020-09-15 | 北京航空航天大学 | Flexible trailing edge module for trailing edge camber wing |
| CN111717412A (en) * | 2020-06-17 | 2020-09-29 | 江西洪都航空工业集团有限责任公司 | Flexible missile wing skin deformation load testing device |
| CN112046729A (en) * | 2020-08-11 | 2020-12-08 | 南京航空航天大学 | Support connection structure of variable camber trailing edge sectional type wing rib and flexible skin |
-
2021
- 2021-08-11 CN CN202110922819.3A patent/CN113602524B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105253323A (en) * | 2015-10-08 | 2016-01-20 | 北京航空航天大学 | Transverse-support-equipped compression test tool for composite material reinforcement plate |
| CN110666714A (en) * | 2019-09-27 | 2020-01-10 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Wing anchor clamps and wing test system |
| CN111661312A (en) * | 2020-05-20 | 2020-09-15 | 北京航空航天大学 | Flexible trailing edge module for trailing edge camber wing |
| CN111717412A (en) * | 2020-06-17 | 2020-09-29 | 江西洪都航空工业集团有限责任公司 | Flexible missile wing skin deformation load testing device |
| CN112046729A (en) * | 2020-08-11 | 2020-12-08 | 南京航空航天大学 | Support connection structure of variable camber trailing edge sectional type wing rib and flexible skin |
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| Publication number | Publication date |
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| CN113602524A (en) | 2021-11-05 |
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