Wing test system

Abstract

The utility model provides a test system for 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 through position adjustment, 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 utility model belongs to retractable wing test technical field, more specifically, it relates to a wing test system. BACKGROUND

[0002] Variable aircraft is one of the important development directions of future advanced aircraft, and is also the innovation research frontier in the field of aerospace; It is mainly embodied in the obvious overall performance advantages in cross-speed domain, cross-medium, etc., especially the cross-supersonic intelligent variable combat aircraft, which has good take-off, acceleration performance and supersonic flight capability; It can better perform economic cruise, monitoring, rapid arrival and penetration tasks.

[0003] Wing is the main source of aircraft lift and control force, so most of the deformation-related researches are concentrated in the deformation of the wing, which can be divided into micro-scale, medium-scale deformation and overall large deformation according to the deformation scale, wherein the most widely used in large-scale deformation research is variable sweep wing and telescopic wing.

[0004] For telescopic wings, most of the variable span concepts are to stack the outer section of the wing on the inner section to realize the change of the span and area. The telescopic expansion in flight will face complex aerodynamic load environment, the wing will be subjected to typical nonlinear aerodynamic load change and wing deflection deformation, and the wing deflection deformation will bring friction between the skins of the nested telescopic wing during the expansion process. In order to verify the telescopic expansion performance of the telescopic wing in different attitudes and working conditions under high-altitude flight conditions, sufficient tests need to be carried out on the ground, and the traditional test methods include:

[0005] The aerodynamic force is simulated by applying steady-state load at a single point / multiple points on the wing surface, mainly by hanging the load on the wing surface through hooks, and the load is concentrated at multiple points during the test, which cannot simulate a more realistic flight load environment;

[0006] Through wind tunnel test, the flight environment is simulated, and the wing telescopic expansion test is carried out during the blowing process. When the test is carried out by this method, the existing wind tunnel conditions are difficult to meet the expansion action of the telescopic wing with an expansion ratio of more than 6 meters, the test is limited by the existing wind tunnel, the wind tunnel test is difficult to realize, and at the same time, the wind tunnel test attack angle mechanism and incoming flow direction are limited, it is difficult to realize the telescopic simulation of the telescopic wing under the condition of large pitch angle and small angle of attack (nose-down attitude, the gravity direction is close to the chord direction of the wing). UTILITY MODEL CONTENTS

[0007] The utility model discloses a test system of wing, which is used to solve the problem that the existing test system cannot simulate a more real flight load environment by directly applying load on the wing surface of the wing.

[0008] To achieve the above object, the utility model provides a test system of wing, which comprises:

[0009] A support mechanism is provided with a wing adapter, which is used to be connected with a wing to be tested;

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

[0011] Preferably, the fan group comprises:

[0012] A fan support is provided with at least two support positions;

[0013] At least two fans are detachably connected to the support positions.

[0014] Preferably, the fan support comprises at least two frames, and the frames are stacked and connected together, and each frame has a support position inside.

[0015] Preferably, the air outlet end of each fan group is provided with a flow straightening section, which is used to straighten the flow of the fan outlet.

[0016] Preferably, the fan group further comprises:

[0017] A base frame is connected with the bottom of the fan support;

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

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

[0020] Preferably, the support mechanism comprises:

[0021] A base;

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

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

[0024] Preferably, the support mechanism further comprises:

[0025] A support base, a bottom of the support base is connected with the top of the base;

[0026] At least two bearing housings, the at least two bearing housings are sequentially and spacedly arranged on one side of the support base, and each bearing housing is connected with the rotating shaft through a bearing.

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

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

[0029] An adapter platform, the adapter platform is connected with the rotating shaft, and the adapter platform is provided with an adapter port;

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

[0031] The test system of the wing has the beneficial effects that: the plurality of fan groups of the test system can be arranged mutually and can form a plurality of wind field regions by adjusting positions, the plurality of wind field regions simulate a plurality of flight load environments of the wing, and the wing on the support mechanism is tested, the test system can exert the aerodynamic load distribution along the span direction of the wing under the real flight working condition by adjusting the arrangement mode of the plurality of fan groups, can meet the use of a plurality of attitudes, a plurality of working conditions and a plurality of aerodynamic load conditions, and simultaneously, since the plurality of fan groups are arranged, and can be arranged arbitrarily, the size of the wind field region formed by the plurality of fan groups can be adjusted according to the size of the wing, and the test when the telescopic wing with an extension length of more than 6 meters performs an unfolding action can be met.

[0032] Other features and advantages of the present application will be described in detail in the following specific embodiment part. BRIEF DESCRIPTION OF DRAWINGS

[0033] The above and other objects, features and advantages of the present application will become more apparent from the following detailed description when taken in conjunction with the accompanying drawings in which similar reference characters refer to similar features throughout the several views, and in which:

[0034] Figure 1A structural schematic view of a test system of a wing is shown according to an embodiment of the utility model;

[0035] Figure 2 A structural schematic view of a fan group of a test system of a wing is shown according to an embodiment of the utility model;

[0036] Figure 3 A structural schematic view of a support mechanism of a test system of a wing is shown according to an embodiment of the utility model;

[0037] Figure 4 A wind distribution schematic view of a test system of a wing is shown according to an embodiment of the utility model.

[0038] Marked legend:

[0039] 1, fan group; 11, fan support; 12, fan; 13, rectifier section; 14, underframe; 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, shaft coupling; 4, wing adapter. Specific implementation

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

[0041] As Figures 1-4 shown, the utility model provides a test system of a wing, which comprises:

[0042] Support mechanism 3, support mechanism 3 is provided with wing adapter 4, wing adapter 4 is used for connecting with the wing to be tested 2;

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

[0044] Specifically, to solve the problem that the existing test of directly applying load on the airfoil of the wing cannot simulate a more realistic flight load environment, and to solve the problem that it is difficult to test a large-span stretchable wing due to the size limitation of the existing wind tunnel test, the utility model provides a test system of a wing, a plurality of fan groups 1 of the test system can be arranged with each other and can form a plurality of wind field areas by adjusting the positions, the plurality of wind field areas will simulate a plurality of flight load environments of the wing 2 to test the wing 1 on the support mechanism 2, the test system can apply the aerodynamic load distribution along the span direction under the real flight working condition to the wing 1 by adjusting the arrangement mode of the plurality of fan groups, can meet the use of a plurality of attitudes, a plurality of working conditions and a plurality of aerodynamic load conditions, and since the plurality of fan groups 1 can be arranged at will, the size of the wind field area formed by the plurality of fan groups 1 can be adjusted according to the size of the wing 2, and the test when the wing with a span length of more than 6 meters performs the unfolding action can be met.

[0045] Preferably, the fan group 1 comprises:

[0046] The fan support 11 is provided with at least two support positions;

[0047] The at least two fans 12 are detachably connected to the support positions.

[0048] Specifically, the fan 12 can be connected to the support position through a bolt, has convenient dismounting capacity, and improves the arrangement efficiency of the plurality of fan groups 1.

[0049] Preferably, each fan group 1 can be placed separately through the fan support 11, and the longitudinal arrangement mode, the transverse arrangement mode and the arrangement size of the plurality of fan groups 1 can be arranged freely according to the use demand.

[0050] Specifically, the use of a plurality of attitudes, a plurality of working conditions and a plurality of load conditions can be met.

[0051] Preferably, the adjacent two fan groups 1 are staggered and arranged.

[0052] Specifically, the fan 12 is used for ensuring the smoothness of the air inlet.

[0053] Preferably, the fan support 11 comprises at least two frames, the at least two frames are stacked and connected together, and each frame is internally provided with a support position.

[0054] Preferably, the outlet of the fan 12 is provided with a flow straightening section 13 along the airflow direction, and the cross-sectional area of the flow straightening section 13 gradually decreases along the flow direction of the airflow.

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

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

[0057] A bottom frame 14 connected to the bottom of the fan support 11;

[0058] At least four universal wheels 15 connected to the circumferential side of the bottom frame 14.

[0059] Specifically, the universal wheels 15 can realize the movement of the fan support 11, have convenient movement ability, and improve the arrangement efficiency of multiple fan units 1.

[0060] Preferably, the wing test system further comprises a fan control unit electrically connected to the multiple fans 12, the fan control unit being 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 unit, respectively, and adjust the outlet flow rate / pressure of the fan 12 at different spanwise positions, so as to simulate the aerodynamic load distribution of the wing along the spanwise direction under multiple real flight environments.

[0062] Preferably, the support mechanism 3 comprises:

[0063] A base 31;

[0064] A torque sensor 32 arranged at the top of the base 31;

[0065] A rotating shaft 33, one end of the rotating shaft 33 being connected to the output end of the torque sensor 32, and the wing adapter 4 being 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 through 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 wing 2 torsion. The torque sensor 32 can be replaced according to the use requirement and load form.

[0068] When the test system is tested, the fan unit 1 is turned on to apply 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, the force of the corresponding fan 12 on the wing 2 is obtained, and the size of the aerodynamic load of the fan 12 on the wing 2 can be verified through the measurement of the torque whether it meets the requirements.

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

[0070] a support 34, a bottom of the support 34 is connected with a top of the base 31;

[0071] at least two bearing seats 35, the at least two bearing seats 35 are sequentially and spacedly arranged on one side of the support 34, and each bearing seat 35 is connected with the rotating shaft 33 through a bearing.

[0072] Specifically, the two bearing seats 35 are used for supporting the rotating shaft 33 and improving the stability of the rotating shaft 33.

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

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

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

[0076] a switching platform, the switching platform is connected with the rotating shaft 33, and the switching platform is provided with a switching port;

[0077] a switching shaft 36, the switching shaft 36 is connected with the wing switching piece 4, the switching shaft 36 is provided with a locking boss 37 according to an attitude angle to be tested of the wing 2, an inner side of the switching port is provided with a limiting groove, and the locking boss 37 can be embedded into the limiting groove.

[0078] Specifically, the switching shaft 36 is provided with an elongated locking boss 37 along an axial direction of the switching shaft 36, and 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 into the limiting groove, the wing 2 can be kept at the attitude angle to be tested.

[0079] In summary, when the test system of the wing is implemented, the test system can exert the load distribution along the span direction of the wing under the real flight working condition by the fan control unit and the arrangement mode of the plurality of fan groups 1.

[0080] For the wing with a large aspect ratio, the telescopic expansion test is strictly limited by the test site and the expansion size constraint, the test system can be conveniently disassembled and moved, the test site can be adjusted according to the test requirement, and the number and arrangement mode of the fan groups 1 can be changed.

[0081] In the flight condition, the wing 2 is extended and retracted, the wing 2 is affected by aerodynamic load and gravity, the aerodynamic load and the gravity direction of the wing 2 under the condition of large pitch angle and small angle of attack are obviously intersected, and the wind tunnel test is relatively difficult to realize, the test system can decouple the mutual influence of the aerodynamic load direction, the flight direction and the gravity direction under the condition of large pitch angle and small angle of attack, and realizes the extension simulation under various flight attitudes and working conditions.

[0082] The above has described various embodiments of the present application, the above description is exemplary, is not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes are obvious to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A test system for a wing, characterized by, The test system comprises: A support mechanism, which is provided with a wing adapter for connecting with a wing to be tested; A plurality of fan groups, which are distributed on one side of the support mechanism, and 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 are directed towards different positions of the wing to be tested.

2. A system for testing a wing according to claim 1, wherein The fan group comprises: A fan support, which is provided with at least two support positions; At least two fans, each of which is detachably connected to one of the support positions.

3. A system for testing a wing according to claim 2, wherein The fan support comprises at least two frames, which are stacked and connected together, and each of the frames has one of the support positions inside.

4. A system for testing a wing according to claim 2, wherein The air outlet end of each of the fan groups is provided with a flow straightening section for straightening the airflow at the outlet of the fan.

5. A system for testing a wing according to claim 2, wherein The fan group further comprises: A base frame, which is connected to the bottom of the fan support; At least four universal wheels, which are connected to the peripheral side of the base frame.

6. A system for testing a wing according to claim 2, wherein The test system for the wing further comprises a fan control unit, which is electrically connected to the plurality of fans, and the fan control unit is used for individually controlling the switch and the wind speed of each of the fans.

7. The system for testing a wing of claim 1, wherein, The support mechanism comprises: A base; A torque sensor, which 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 system for testing a wing according to claim 7, wherein The support mechanism further comprises: A support base, the bottom of which is connected to the top of the base; At least two bearing seats, which are sequentially and spacedly arranged on one side of the support base, and each of the bearing seats is connected to the rotating shaft through one of the bearings.

9. A system for testing a wing according to claim 7, wherein The support mechanism further comprises a coupling, two ends of which are respectively connected to one end of the rotating shaft and the output end of the torque sensor.

10. A system for testing a wing according to claim 7, wherein The test system for the wing further comprises: An adapter platform, which is connected to the rotating shaft and is provided with an adapter opening; An adapter shaft, which is connected to the wing adapter and is provided with a locking boss according to the attitude angle of the wing to be tested, and the inner side of the adapter opening is provided with a limiting groove, and the locking boss can be embedded in the limiting groove.

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