Wing test system

Abstract

The invention provides a test system of a wing, and relates to the technical field of wing test, the test system comprises a plurality of fan sets, each fan set can be placed independently, the plurality of fan sets can be arranged mutually and can form a plurality of wind field areas by adjusting positions, and the plurality of wind field areas are used for simulating a plurality of flight loaded environments of the wing; the supporting mechanism is arranged in the wind field area; the wing adapter is arranged on the supporting structure, and an interface of the wing adapter is used for being connected with an interface of a to-be-tested wing; according to the test system, aerodynamic load distribution in the spanwise direction under the real flight working condition can be applied to the wings by adjusting the arrangement mode of the multiple fan sets, meanwhile, due to the fact that the multiple fan sets are arranged and can be combined and arranged at will, the size of a wind field area formed by the multiple fan sets can be adjusted according to the size of the wings, and the test efficiency is improved. And the test can be carried out when the extension telescopic wing with the length of more than 6 meters executes the unfolding action.

Description

Technical Field

[0001] The invention belongs to the technical field of telescopic wing testing, and more specifically, relates to a wing testing system. Background Art

[0002] Variant aircraft is one of the important development directions of future advanced aircraft, and is also the forefront of innovative research in the aerospace field. It is mainly reflected in the obvious overall performance advantages across speed ranges and media, especially transonic intelligent variant combat aircraft, which have better take-off and landing, acceleration performance and supersonic flight capability; it can better perform economic cruise, surveillance, rapid arrival and penetration tasks.

[0003] The wing is the main source of lift and control force for aircraft, so most of the research related to deformation is focused on the deformation of the wing. According to the deformation scale, it can be divided into: micro-scale, medium-scale deformation and overall large deformation. Among them, the most widely studied large-scale deformation are variable-sweep wings and retractable wings.

[0004] For telescopic wings, most variable span concepts are to overlap the outer section of the wing on the inner section to achieve changes in span and area. The telescopic deployment during flight will face a complex aerodynamic load environment. The wing will be subject to typical nonlinear aerodynamic load changes and wing deflection deformation. The wing deflection deformation will cause friction between the skins of the nested telescopic wing during the extension process. In order to verify the telescopic deployment performance of the telescopic wing in different postures and working conditions under high-altitude flight conditions, sufficient tests need to be carried out on the ground. Traditional test methods include:

[0005] Aerodynamics is simulated by applying steady-state loads at single or multiple points on the wing surface. The test is mainly conducted by applying loads by hooking the wing surface. When testing in this way, the loads are concentrated at multiple points, which cannot simulate a more realistic flight load environment.

[0006] Through wind tunnel tests to simulate the flight environment, the wing extension and deployment tests are carried out during the blowing process. When testing in this way, the existing wind tunnel conditions are difficult to meet the requirements for the expansion action of the telescopic wing with a super-large display ratio of more than 6 meters. The test is greatly restricted by the existing wind tunnels, and the wind tunnel test is difficult to implement. At the same time, it is limited by the wind tunnel test angle of attack mechanism and the direction of the incoming flow, and it is difficult to achieve the extension and deployment simulation of the telescopic wing under large pitch angle and small angle of attack conditions (dive posture, the direction of gravity is close to the chord direction of the wing). Summary of the invention

[0007] The purpose of the present invention is to provide a wing test system in view of the deficiencies in existing technology, so as to solve the problem mentioned in the above background technology that the existing test of directly applying loads to the wing surface cannot simulate a more realistic flight load environment, and at the same time solve the problem that it is difficult to test telescopic wings with ultra-large display ratio due to the size limitations of existing wind tunnel tests.

[0008] In order to achieve the above object, the present invention provides a wing test system, the test system comprising:

[0009] A supporting mechanism, wherein the supporting mechanism is provided with a wing adapter, and the wing adapter is used to connect with the wing to be tested;

[0010] A plurality of fan groups are distributed on one side of the support mechanism. When one end of the wing to be tested is connected to the wing adapter, the air outlet ends of the plurality of fan groups face different positions of the wing to be tested.

[0011] Preferably, the fan unit comprises:

[0012] A fan bracket, wherein at least two supporting positions are distributed on the fan bracket;

[0013] At least two fans, each of which is detachably connected to one of the support positions.

[0014] Preferably, the fan support comprises at least two frames, at least two of the frames are stacked and connected together, and the interior of each of the frames is one of the support positions.

[0015] Preferably, a rectifying section is installed at the air outlet end of each fan group, and the rectifying section rectify the outflow and inflow of the fan.

[0016] Preferably, the fan unit further comprises:

[0017] A base frame connected to the bottom of the fan bracket;

[0018] At least four universal wheels are connected to the peripheral side of the base frame.

[0019] Preferably, the wing test system further comprises a fan control unit, wherein the fan control unit is electrically connected to the plurality of fans, and the fan control unit is used to individually control the switch and wind speed of each fan.

[0020] Preferably, the supporting mechanism comprises:

[0021] Base;

[0022] A torque sensor, wherein the torque sensor is arranged on the top of the base;

[0023] A rotating shaft, one end of which is connected to the output end of the torque sensor, and the wing adapter is connected to the rotating shaft.

[0024] Preferably, the supporting mechanism further comprises:

[0025] A support, the bottom of which is connected to the top of the base;

[0026] At least two bearing seats are provided at intervals on one side of the support, and each bearing seat is connected to the rotating shaft through a bearing.

[0027] Preferably, the supporting mechanism further comprises a coupling, and two ends of the coupling are respectively connected to one end of the rotating shaft and an output end of the torque sensor.

[0028] Preferably, the wing test system further comprises:

[0029] A transfer platform, the transfer platform is connected to the rotating shaft, and the transfer platform is provided with a transfer interface;

[0030] An adapter shaft is connected to the wing adapter, a locking boss is provided on the adapter shaft according to the attitude angle of the wing to be tested, a limiting groove is provided on the inner side of the adapter, and the locking boss can be embedded in the limiting groove.

[0031] The present invention provides a wing test system, which has the beneficial effects that: a plurality of wind turbine groups of the test system can be arranged with each other and can form a variety of wind field areas by adjusting their positions, and the various wind field areas will simulate a variety of flight load environments of the wing to test the wing on a supporting mechanism. The test system can impose aerodynamic load distribution along the span direction under real flight conditions on the wing by adjusting the arrangement of the plurality of wind turbine groups, and can meet the use of a variety of postures, a variety of working conditions and a variety of aerodynamic load conditions. At the same time, since a plurality of wind turbine groups are provided and can be arranged in any combination, the size of the wind field area formed by the plurality of wind turbine groups can be adjusted according to the size of the wing, and can meet the test of a telescopic wing with a span of more than 6 meters performing an unfolding action.

[0032] Other features and advantages of the present invention will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] The above and other objects, features and advantages of the present invention will become more apparent through a more detailed description of exemplary embodiments of the present invention in conjunction with the accompanying drawings, wherein like reference numerals generally represent like components throughout the exemplary embodiments of the present invention.

[0034] Figure 1A schematic structural diagram of a wing test system according to an embodiment of the present invention is shown;

[0035] Figure 2 A schematic structural diagram of a fan unit of a wing test system according to an embodiment of the present invention is shown;

[0036] Figure 3 A schematic structural diagram of a support mechanism of a wing test system according to an embodiment of the present invention is shown;

[0037] Figure 4 A schematic diagram of wind distribution of a wing test system according to an embodiment of the present invention is shown.

[0038] Description of reference numerals:

[0039] 1. Fan assembly; 11. Fan bracket; 12. Fan; 13. Rectifier section; 14. Base frame; 15. Universal wheel; 2. Wing; 3. Support mechanism; 31. Base; 32. Torque sensor; 33. Rotating shaft; 34. Support; 35. Bearing seat; 36. Adapter shaft; 37. Locking boss; 38. Coupling; 4. Wing adapter. DETAILED DESCRIPTION

[0040] The preferred embodiments of the present invention will be described in more detail below. Although the preferred embodiments of the present invention are described below, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to make the present invention more thorough and complete, and to fully convey the scope of the present invention to those skilled in the art.

[0041] like Figure 1-Figure 4 As shown, the present invention provides a wing test system, the test system comprising:

[0042] A support mechanism 3, the support mechanism 3 is provided with a wing adapter 4, and the wing adapter 4 is used to connect with the wing 2 to be tested;

[0043] Multiple fan groups 1 are distributed on one side of the support mechanism 3. When one end of the wing 2 to be tested is connected to the wing adapter 4, the air outlet ends of the multiple fan groups 1 face different positions of the wing 2 to be tested.

[0044] Specifically, in order to solve the problem that the existing test of directly applying loads to the wing surface cannot simulate a more realistic flight load environment, and at the same time solve the problem that it is difficult to test a telescopic wing with a larger span due to the size limitation of the existing wind tunnel test, the present invention provides a wing test system, wherein multiple wind turbine groups 1 of the test system can be arranged with each other and can form a variety of wind field areas by adjusting their positions. The various wind field areas will simulate a variety of flight load environments of the wing 2 to test the wing 1 on the support mechanism 2. The test system can impose aerodynamic load distribution along the span direction under real flight conditions on the wing 1 by adjusting the arrangement of the multiple wind turbine groups, and can meet the use of multiple postures, multiple working conditions and multiple aerodynamic load conditions. At the same time, since multiple wind turbine groups 1 are provided and can be arranged in any combination, the size of the wind field area formed by the multiple wind turbine groups 1 can be adjusted according to the size of the wing 2, and can meet the test of a telescopic wing with a span of more than 6 meters performing a deployment action.

[0045] Preferably, the fan unit 1 comprises:

[0046] A fan bracket 11, wherein at least two supporting positions are distributed on the fan bracket 11;

[0047] At least two fans 12 are provided, and each fan 12 is detachably connected to a support position.

[0048] Specifically, the fan 12 can be connected to the support position by bolts, has convenient disassembly capability, and improves the arrangement efficiency of multiple fan groups 1.

[0049] Preferably, each fan unit 1 can be placed individually by means of a fan bracket 11, and the longitudinal arrangement, transverse arrangement and arrangement size of the plurality of fan units 1 can be freely arranged according to usage requirements.

[0050] Specifically, it can meet the use of various postures, various working conditions and various load conditions.

[0051] Preferably, two adjacent fan units 1 are arranged in a staggered manner front to back.

[0052] Specifically, it is used to ensure that the air inlet of the fan 12 is unobstructed.

[0053] Preferably, the fan support 11 includes at least two frames, and the at least two frames are stacked and connected together, and the interior of each frame is a supporting position.

[0054] Preferably, a rectifying section 13 is installed at the outlet of the fan 12 along the airflow direction, and the cross-sectional area of ​​the rectifying section 13 gradually decreases along the flow direction of the airflow.

[0055] Specifically, a rectifying section 13 is installed at the air outlet of each fan unit 1 for controlling the quality of the flow field at the outlet. The outlet airflow area and pressure can be adjusted by adjusting the cross-sectional area of ​​the rectifying section 13 at the outlet.

[0056] Preferably, the fan unit 1 further includes:

[0057] A base frame 14, the base frame 14 is connected to the bottom of the fan bracket 11;

[0058] At least four universal wheels 15 are connected to the circumference of the base frame 14 .

[0059] Specifically, the universal wheel 15 can realize the movement of the fan bracket 11, has convenient movement capability, and improves the arrangement efficiency of multiple fan units 1.

[0060] Preferably, the wing test system further includes a fan control unit, which is electrically connected to the plurality of fans 12 , and is used to individually control the switch and wind speed of each fan 12 .

[0061] Specifically, the fan control unit can adjust the output wind speed / outlet pressure of a single fan / fan group, and adjust the outlet flow rate / pressure of the fan 12 at different spanwise positions, respectively, so as to simulate the aerodynamic load distribution of the wing along the spanwise direction under various real flight environments.

[0062] Preferably, the supporting mechanism 3 comprises:

[0063] Base 31;

[0064] A torque sensor 32, wherein the torque sensor 32 is disposed on the top of the base 31;

[0065] The rotating shaft 33 has one end connected to the output end of the torque sensor 32 , and the wing adapter 4 is connected to the rotating shaft 33 .

[0066] Specifically, the base 31 is used for the entire wing connection system and can be fixed to the ground by anchor bolts.

[0067] The torque sensor 32 is used to measure the root torque of the wing 2. The center of the torque sensor 32 is concentric with the rotating shaft 33 of the twisted wing 2. The torque sensor 32 can be replaced according to the use requirements and load form.

[0068] During the test of this test system, the fan group 1 is turned on to apply a force to the lower surface of the wing 2. The root torque is obtained through the torque sensor 32 at the root of the wing 2, and the corresponding force of the fan 12 on the wing 2 is obtained. The torque measurement can verify whether the aerodynamic load of the fan 12 on the wing 2 meets the requirements.

[0069] Preferably, the supporting mechanism 3 further comprises:

[0070] A support 34, the bottom of the support 34 is connected to the top of the base 31;

[0071] At least two bearing seats 35 are arranged in sequence and spaced apart on one side of the support 34 , and each bearing seat 35 is connected to the rotating shaft 33 through a bearing.

[0072] Specifically, the two bearing seats 35 are used to support the rotating shaft 33 and improve the stability of the rotating shaft 33 .

[0073] Preferably, the supporting mechanism further includes a coupling 38 , and two ends of the coupling 38 are respectively connected to one end of the rotating shaft 33 and an output end of the torque sensor 32 .

[0074] Specifically, the coupling 38 is used to connect one end of the rotating shaft 33 and the output end of the torque sensor 32 .

[0075] Preferably, the wing test system further comprises:

[0076] A transfer platform, the transfer platform is connected to the rotating shaft 33, and the transfer platform is provided with a transfer interface;

[0077] The adapter shaft 36 is connected to the wing adapter 4. A locking boss 37 is provided on the adapter shaft 36 according to the attitude angle of the wing 2 to be tested. A limiting groove is provided on the inner side of the adapter, and the locking boss 37 can be embedded in the limiting groove.

[0078] Specifically, an elongated locking boss 37 is provided on the adapter shaft 36 along the axial direction of the adapter shaft 36. The position of the locking boss 37 can be set according to the attitude angle to be tested. When the locking boss 37 is embedded in the limit groove, the wing 2 can maintain the attitude angle to be tested.

[0079] In summary, when the wing test system of the present invention is implemented, the test system can apply a load distribution along the span direction under actual flight conditions to the wing through the fan control unit and by adjusting the arrangement of the multiple fan groups 1.

[0080] For wings with ultra-large aspect ratio, the telescopic deployment test will be strictly limited by the test site and deployment size constraints. The test system can be easily disassembled and moved, and the test location can be adjusted according to the test requirements, and the number and arrangement of wind turbine groups 1 can be changed.

[0081] When wing 2 is extended and unfolded in flight conditions, wing 2 will be affected by both aerodynamic load and its own gravity. The aerodynamic load and the gravity direction of wing 2 under large pitch angle and small angle of attack conditions present an obvious angle, which makes wind tunnel tests difficult to implement. This test system can decouple the mutual influence of aerodynamic load direction, flight direction and gravity direction under large pitch angle and small angle of attack conditions, and realize unfolding simulation under various flight attitudes and conditions.

[0082] The embodiments of the present invention have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A wing test system, characterized in that: The test system includes: A supporting mechanism, wherein the supporting mechanism is provided with a wing adapter, and the wing adapter is used to connect with the wing to be tested; A plurality of fan groups are distributed on one side of the support mechanism. When one end of the wing to be tested is connected to the wing adapter, the air outlet ends of the plurality of fan groups face different positions of the wing to be tested.

2. A wing test system according to claim 1, characterized in that: The fan unit comprises: A fan bracket, wherein at least two supporting positions are distributed on the fan bracket; At least two fans, each of which is detachably connected to one of the support positions.

3. A wing test system according to claim 2, characterized in that: The fan support comprises at least two frames, at least two of the frames are stacked and connected together, and the interior of each of the frames is a supporting position.

4. A wing test system according to claim 2, characterized in that: A rectifying section is installed at the air outlet end of each fan group, and the rectifying section rectify the airflow at the fan outlet.

5. A wing test system according to claim 2, characterized in that: The fan unit also includes: A base frame connected to the bottom of the fan bracket; At least four universal wheels are connected to the peripheral side of the base frame.

6. A wing test system according to claim 2, characterized in that: The wing test system also includes a fan control unit, which is electrically connected to the plurality of fans and is used to individually control the switch and wind speed of each fan.

7. A wing test system according to claim 1, characterized in that: The supporting mechanism comprises: Base; A torque sensor, wherein the torque sensor is arranged on the top of the base; A rotating shaft, one end of which is connected to the output end of the torque sensor, and the wing adapter is connected to the rotating shaft.

8. A wing test system according to claim 7, characterized in that: The support mechanism also includes: A support, the bottom of which is connected to the top of the base; At least two bearing seats are provided at intervals on one side of the support, and each bearing seat is connected to the rotating shaft through a bearing.

9. A wing test system according to claim 7, characterized in that: The supporting mechanism further comprises a coupling, and two ends of the coupling are respectively connected to one end of the rotating shaft and an output end of the torque sensor.

10. A wing test system according to claim 7, characterized in that: The test system of the wing also includes: A transfer platform, the transfer platform is connected to the rotating shaft, and the transfer platform is provided with a transfer interface; An adapter shaft is connected to the wing adapter, a locking boss is provided on the adapter shaft according to the attitude angle of the wing to be tested, a limiting groove is provided on the inner side of the adapter, and the locking boss can be embedded in the limiting groove.

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