Vibration superposition static load test device for movable airfoil structure

Abstract

The invention belongs to the field of airplane structure strength test, and particularly relates to a movable airfoil structure vibration superposition static load test device which comprises an integral frame, a static load system, a movable excitation platform, an excitation device and a movable airfoil test piece. The integral frame is used for supporting the static load system, the movable excitation platform, the excitation device and the movable airfoil test piece; the movable airfoil test piece is horizontally arranged, the static load system is connected with the movable airfoil test piece, and the static load system can perform distributed static load low-rigidity loading on the movable airfoil test piece through an air bag; the two groups of excitation devices are arranged on the movable excitation platform side by side; through collaborative innovation of the movable excitation platform, the distributed static load system and the high-rigidity frame, remarkable advantages are formed in the aspects of test efficiency, working condition simulation authenticity, data precision, universality and the like, and efficient and reliable test equipment is provided for ground dynamic strength verification of the movable airfoil of the civil aircraft.

Description

Technical Field

[0001] This application belongs to the field of aircraft structural strength testing, and specifically relates to a static load test device for vibration superposition of movable wing structure. Background Technology

[0002] During flight operations, the control surfaces of civil aircraft (such as flaps, ailerons, and rudder surfaces) are subjected to both static aerodynamic loads from steady airflow and vibration loads from airflow disturbances. If these loads exceed certain limits, cracks or even fractures may occur, seriously affecting flight safety. Therefore, it is essential to conduct ground-based vibration-superimposed static load tests on these structures. Currently, there is little research in the field on the dynamic strength of such movable airfoil structures under real-world operating conditions, primarily due to the lack of suitable testing equipment. Therefore, it is necessary to design a vibration-superimposed static load testing device suitable for movable airfoil structures.

[0003] Currently, some research has been conducted on vibration fatigue tests of wing structures under complex loads. These studies primarily focus on fixed wings, emphasizing the implementation of static or fatigue loads, mainly through the design of basic elastic elements such as airbags or rubber ropes to meet loading requirements. However, a significant characteristic of movable wings is that their wing position can be adjusted within a certain range, and the dynamic response of the entire wing is completely different depending on the excitation position.

[0004] Disadvantages of existing technical solutions:

[0005] 1. Technical aspects

[0006] Existing technologies primarily target fixed airfoils, and static load tests involving vibration superposition on movable airfoils (whose positions can be adjusted within a certain range) are rarely conducted. This is because existing technologies use fixed vibration loading positions and are mostly single-point or base-based excitations, which cannot meet the testing requirements of movable airfoils. Vibration excitation devices are heavy and difficult to manually adjust once positioned. Furthermore, the large size of movable airfoil test pieces can hinder the hoisting of the excitation after installation, making it difficult to adjust the vibration excitation position during the test.

[0007] 2. Cost and efficiency aspects

[0008] The existing technical solution requires disassembling the test specimen and then using a crane to adjust the excitation position after each change in the attitude of the movable wing surface. This process is quite cumbersome. Furthermore, if the excitation position is not ideal during the test and needs adjustment, the movable wing surface test specimen must be disassembled and reassembled again, severely impacting test efficiency.

[0009] At this time, traditional wing structure vibration fatigue testing devices cannot meet the testing requirements because the vibration loading points are fixed or difficult to move. There is an urgent need for a testing device that can flexibly apply multi-point vibration excitation and can combine static loads. Summary of the Invention

[0010] To address the aforementioned issues, this application provides a static load test device for vibration superposition of movable wing structure, thereby resolving the problem that the fixed vibration loading points in the prior art cannot meet the requirements of current static load test devices.

[0011] The technical solution of this application is: a static load test device for vibration superposition of movable wing structure, including an integral frame, a static load system, a movable excitation platform, an excitation device and a movable wing test piece;

[0012] The overall frame is used to support the static load system, the movable excitation platform, the excitation device, and the movable wing test specimen; the movable wing test specimen is set horizontally, the static load system is connected to the movable wing test specimen, and the static load system can perform distributed static low-stiffness loading on the movable wing test specimen through airbags; there are two sets of excitation devices arranged side by side on the movable excitation platform.

[0013] The movable excitation platform can control the operation of the excitation device. The movable excitation platform is connected to the excitation device and can drive the excitation device to move. The movable excitation platform can cooperate with the excitation device to apply multi-point surface excitation at arbitrary positions to the movable wing test piece.

[0014] Preferably, the overall frame includes movable wing surface supports, columns, reinforcing beams, a base plate, and airbag support columns;

[0015] The support column consists of multiple columns connected side by side to the base plate. The movable wing support is located at the top of the support column, and the reinforcing beam and airbag support column are located on both sides of the middle part of the support column.

[0016] The movable wing support is detachably connected to the movable wing test piece. A support mounting plate is provided between the movable wing support and the support column, and the support mounting plate is welded to the support column.

[0017] The reinforcing beam is provided with outer and inner diagonal bracing columns. There are multiple sets of the reinforcing beam, outer and inner diagonal bracing columns, which are arranged parallel and equidistantly in the spanwise direction of the movable wing test piece.

[0018] The airbag support column is fixedly connected to the pillar by means of diagonal bracing.

[0019] Preferably, the loading assembly further includes a flexible polyurethane plate, a first support, an air servo valve, and a connecting air path;

[0020] Multiple sets of the adjusting pad, sensing component, and loading component are arranged at intervals on the horizontal fixed plate;

[0021] The adjusting shim is connected to the horizontal fixed plate and can be adjusted in position.

[0022] The sensing component includes a static sensor and a sensor mounting base. The sensor mounting base is connected to an adjustment pad and can be adjusted for heading distance on the adjustment pad. The static sensor is mounted on the sensor mounting base.

[0023] The loading assembly includes a flexible polyurethane plate, an airbag, a first support, an air servo valve, and a connecting air path; the upper part of the flexible polyurethane plate is connected to the movable wing test piece, and the lower part is connected to the airbag; the first support is located below the airbag and supports the airbag; the connecting air path is connected to the airbag, and the air servo valve is located on the connecting air path.

[0024] The air circuit connects the air source and the controller, which can adjust the opening and closing of the air circuit servo valve based on feedback from the static sensor.

[0025] Preferably, the excitation device comprises two sets, and the movable excitation platform includes a first yaw slide, a second yaw slide, a third yaw slide, a fourth yaw slide, a first spanwise slide, a second spanwise slide, a third spanwise slide, and a fourth spanwise slide.

[0026] The first heading slide, the second heading slide, the third heading slide and the fourth heading slide are arranged in parallel, and the first spanning slide, the second spanning slide, the third spanning slide and the fourth spanning slide are arranged in parallel.

[0027] The first and second directional slides slide vertically in conjunction with the first and second spanwise slides; the third and fourth directional slides slide vertically in conjunction with the third and fourth spanwise slides.

[0028] The first spanwise slide and the second spanwise slide are connected to one of the sets of excitation devices; the third spanwise slide and the fourth spanwise slide are connected to another set of excitation devices.

[0029] Preferably, the first heading slide includes a front ball bearing slide, a rear ball bearing slide, a lead screw, a linear guide rail, and a stepper motor;

[0030] One end of the lead screw is connected to the stepper motor, and the other end is connected to the front bearing baffle of the base plate; the front ball slide and the rear ball slide are threadedly connected to the lead screw, and the front ball slide and the linear guide rail are slidably fitted with a front slider assembly; the rear ball slide and the linear guide rail are slidably fitted with a rear slider assembly, and the base plate is also provided with a rear bearing baffle at the end of the lead screw near the stepper motor.

[0031] Preferably, the first directional slide, the second directional slide, the first spanwise slide, and the second spanwise slide form a left-end slide group, which can apply vibration excitation to any position on the left half of the movable wing test piece; the third directional slide, the fourth directional slide, the third spanwise slide, and the fourth spanwise slide form a right-end slide group, and the first directional slide and the second directional slide can rotate synchronously, as can the first spanwise slide and the second spanwise slide.

[0032] The dynamic wing structure vibration superposition static load test device of this application has the following advantages:

[0033] It allows simultaneous application of vibration excitation to two different positions on the movable wing surface, or time-sharing adjustment of the positions of two sets of excitation devices. Combined with the three-dimensional mobility of the movable excitation platform, it can simulate the complex working conditions of "multi-position, multi-frequency" superimposed static loads on the movable wing surface in actual flight (such as flutter and buffeting combined loading), providing more comprehensive experimental data support for the fatigue life assessment and dynamic strength verification of the movable wing surface;

[0034] Through the collaborative innovation of a mobile excitation platform, a distributed static load system, and a high-rigidity frame, significant advantages have been achieved in terms of test efficiency, realism of operating condition simulation, data accuracy, and versatility, providing efficient and reliable test equipment for ground dynamic strength verification of movable wing surfaces of civil aircraft. Attached Figure Description

[0035] Figure 1 This is a schematic diagram of the overall structure of this application;

[0036] Figure 2 This is a schematic diagram of the overall framework structure of this application;

[0037] Figure 3 This is a schematic diagram of the static load system structure of this application;

[0038] Figure 4 This is a schematic diagram of the threaded hole structure of the adjusting pad in this application;

[0039] Figure 5 This is a schematic diagram of the elongated hole structure on the horizontal fixing plate of this application;

[0040] Figure 6 This is a schematic diagram of the movable vibration platform structure of this application;

[0041] Figure 7 This is a schematic diagram of the first heading slide structure of this application;

[0042] Figure 8 This is a schematic diagram of the connection structure between the excitation device and the movable excitation platform of this application.

[0043] 1. Overall frame; 11. Movable wing support; 12. Support mounting plate; 13. Column; 14. External diagonal brace; 15. Internal diagonal brace; 16. Reinforcing beam; 17. Base plate; 18. Airbag support column; 2. Static load system; 21. Flexible polyurethane board; 22. Airbag; 23. First support; 24. Static sensor; 25. Sensor mounting base; 26. Adjusting pad; 261. Threaded hole; 27. Horizontal fixing plate; 271. Long strip hole; 28. Air servo valve; 29. ​​Connecting air path; 3. Movable vibration platform 31. First directional slide; 311. Front bearing baffle; 312. Front slider assembly; 313. Front ball bearing slide; 314. Lead screw; 315. Linear guide rail; 316. Rear slider assembly; 317. Rear ball bearing slide; 318. Rear bearing baffle; 319. Stepper motor; 32. Second directional slide; 33. Third directional slide; 34. Fourth directional slide; 35. First spanwise slide; 36. Second spanwise slide; 37. Third spanwise slide; 38. Fourth spanwise slide; 4. Vibration excitation device; 5. Movable wing test piece. Detailed Implementation

[0044] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0045] The first aspect of this application provides a static load test device for vibration superposition of active wing structure, such as... Figure 1 It includes an overall frame 1, a static load system 2, a movable excitation platform 3, an excitation device 4, and a movable wing test piece 5.

[0046] The overall frame 1 is used to support the static load system 2, the movable excitation platform 3, the excitation device 4, and the movable wing test piece 5. The movable wing test piece 5 is set horizontally, and the static load system 2 is connected to the movable wing test piece 5. The static load system 2 can perform distributed static low-stiffness loading on the movable wing test piece 5 through the airbag 22. There are two sets of excitation devices 4, which are arranged side by side on the movable excitation platform 3.

[0047] The movable excitation platform 3 can control the operation of the excitation device 4. The movable excitation platform 3 is connected to the excitation device 4 and can drive the excitation device 4 to move. The movable excitation platform 3 can cooperate with the excitation device 4 to apply multi-point surface arbitrary position excitation to the movable wing test piece 5.

[0048] The excitation device 4 is a pre-made component.

[0049] Before loading the movable wing test piece 5, first install the movable wing test piece 5 onto the overall frame 1, and then bring the airbag 22 of the static load system 2 into contact with the movable wing test piece 5.

[0050] Then, the excitation rod of the excitation device 4 is adjusted to the designated position and connected to the movable wing test piece 5. The airbag 22 of the static load system 2 is controlled by the controller in the background to load the movable wing test piece 5 to the set static load value.

[0051] Then, the excitation device 4 is controlled to apply sinusoidal or random vibration, and the vibration response of the active wing test piece 5 at the point of interest is monitored. If the vibration response does not meet the requirements, the position of the excitation device 4 is adjusted by the movable excitation platform 3 to re-excite until the vibration response requirements are met.

[0052] It solves the problem of applying vibration loads to large-size variable structures, and can arbitrarily change the position of multiple excitation points without disassembling the test specimen. The movable wing surface of the device is horizontally installed, which conforms to the actual attitude under its flight operation environment, and can complete static load and vibration load tests individually or in combination on a single device without the need for reassembly.

[0053] like Figure 2 Preferably, the overall frame 1 includes a movable wing support 11, a column 13, a reinforcing beam 16, a base plate 17, and an airbag support column 18;

[0054] There are multiple support columns connected side by side to the base plate 17. The movable wing support 11 is located at the top of the support column, and the reinforcing beam 16 and the airbag support column 18 are located on both sides of the middle part of the support column.

[0055] The movable wing support 11 is detachably connected to the movable wing test piece 5. A support mounting plate 12 is provided between the movable wing support 11 and the support column, and the support mounting plate 12 is welded to the support column.

[0056] The reinforcing beam 16 is equipped with an outer inclined brace 14 and an inner inclined brace 15. There are multiple sets of the reinforcing beam 16, the outer inclined brace 14 and the inner inclined brace 15, which are arranged in parallel and equidistantly in the spanwise direction of the movable wing test piece 5.

[0057] The airbag support column 18 is fixedly connected to the support column by means of diagonal bracing. Its position corresponds to the inner diagonal bracing column 15 and the reinforcing beam 16, providing support on both sides of the support column.

[0058] The airbag 22 of the static load system 2 is supported by the airbag support column 18. The reinforcing beam 16, the outer diagonal support column 14 and the inner diagonal support column 15 can strengthen the strength of the column 13. The movable wing support 11 is used to support the movable wing test piece 5, thereby achieving overall support for the entire system.

[0059] All parts inside the frame are connected by full welding to ensure connection strength.

[0060] like Figures 3-5 Preferably, the static load system 2 comprises multiple units distributed at intervals to achieve multi-point distributed loading. The static load system 2 includes a horizontal fixing plate 27, an adjusting pad 26, a sensing component, and a loading component;

[0061] Multiple sets of adjusting pads 26, sensing components and loading components are arranged at intervals on the horizontal fixed plate 27;

[0062] The adjusting shim 26 is connected to the horizontal fixing plate 27 and its position can be adjusted.

[0063] The sensing assembly includes a static sensor 24 and a sensor mounting base 25. The sensor mounting base 25 is connected to an adjustment pad 26 and can be adjusted for heading and distance on the adjustment pad 26. The static sensor 24 is mounted on the sensor mounting base 25. The static sensor 24 can sense the magnitude of the static load borne by the movable wing test piece 5 and transmit it to the controller. The static sensor 24 has a chamfered rectangular structure that connects to the adjustment pad 26, and all connections are made using screws.

[0064] The loading assembly also includes a flexible polyurethane plate 21, a first support 23, an air servo valve 28, and a connecting air passage 29; the upper part of the flexible polyurethane plate 21 is connected to the movable wing test piece 5, and the lower part is connected to the airbag 22; the first support 23 is located below the airbag 22 and supports the airbag 22, the connecting air passage 29 is connected to the airbag 22, and the air servo valve 28 is located on the connecting air passage 29; when the air servo valve 28 is open, it can inflate the airbag 22; when it is closed, it seals the airbag 22.

[0065] The air circuit connects the air source and the controller, which can adjust the opening and closing of the air circuit servo valve 28 based on the feedback from the static sensor 24.

[0066] The flexible polyurethane plate 21 is directly connected to the movable wing test piece 5 to reduce rigid contact. The controller changes the inflation state and degree of the airbag 22 by adjusting the opening and closing of the air servo valve 28, which is sufficient to meet the accuracy requirements for the static load of the movable wing test piece 5.

[0067] The adjusting shim 26 has an additional threaded hole 261 on both the front and rear of the projection face of the static sensor 24 mounting base, allowing the static sensor 24 mounting base to be adjusted forward and backward a certain distance in the test specimen's heading direction. The individual airbag 22 module can be adjusted left and right a certain distance. This design enables simple adjustment of the static load application position in the test specimen's heading and spanwise directions under different static load conditions.

[0068] Preferably, there are two sets of excitation devices 4, which can apply loads to different positions of the movable wing test piece 5 respectively.

[0069] like Figure 6 The movable excitation platform 3 includes a first directional slide 31, a second directional slide 32, a third directional slide 33, a fourth directional slide 34, a first spanwise slide 35, a second spanwise slide 36, a third spanwise slide 37, and a fourth spanwise slide 38.

[0070] The first heading slide 31, the second heading slide 32, the third heading slide 33 and the fourth heading slide 34 are arranged in parallel, and the first spanning slide 35, the second spanning slide 36, the third spanning slide 37 and the fourth spanning slide 38 are arranged in parallel.

[0071] The first heading slide 31 and the second heading slide 32 slide vertically in conjunction with the first spanning slide 35 and the second spanning slide 36; the third heading slide 33 and the fourth heading slide 34 slide vertically in conjunction with the third spanning slide 37 and the fourth spanning slide 38.

[0072] The first spanwise slide 35 and the second spanwise slide 36 are connected to one of the sets of excitation devices 4; the third spanwise slide 37 and the fourth spanwise slide 38 are connected to another set of excitation devices 4.

[0073] The movable vibration platform 3 is equipped with a DC power supply, driver and controller to control the motion of the slide of the heading and war elephant.

[0074] The first azimuth slide 31 to the fourth azimuth slide 34 are fixed to the base plate 17 with screws, and the first spanning slide 35 to the fourth spanning slide 38 are connected to the corresponding azimuth slides with screws to form a three-dimensional overlapping structure.

[0075] Both the yaw and spanwise slides achieve yaw and spanwise movement through the cooperation of sliders and rails. The structures of each yaw and spanwise slide are basically the same. The first yaw slide 31 will be described below:

[0076] like Figure 7 The first heading slide 31 includes a front ball slide 313, a rear ball slide 317, a lead screw 314, a linear guide rail 315, and a stepper motor 319.

[0077] One end of the lead screw 314 is connected to the stepper motor 319, and the other end is connected to the front bearing baffle 311 on the base plate 17. The front ball slide 313 and the rear ball slide 317 are threadedly connected to the lead screw 314. The front ball slide 313 and the linear guide rail 315 are slidably fitted with a front slider assembly 312. The rear ball slide 317 and the linear guide rail 315 are slidably fitted with a rear slider assembly 316. The base plate 17 is also provided with a rear bearing baffle 318 at the end of the lead screw 314 near the stepper motor 319.

[0078] The front bearing baffle 311, the linear guide rail 315, the rear bearing baffle 318, and the stepper motor 319 are fixed to the base plate 17 with screws. When the stepper motor 319 rotates a certain angle under the action of the driver, the front ball slide 313 and the rear ball slide 317 will move forward or backward a certain distance at the same time, and the distance between them remains unchanged, thereby realizing the adjustment of the position of the ball slide load.

[0079] Once the position of the slide support is determined, the stepper motor 319 is locked. The ball slide connected to the support by screws can provide good support rigidity to meet the requirements of vibration testing.

[0080] Changing the excitation position through electromechanical control can significantly improve test efficiency and reduce human error during the test process.

[0081] like Figure 8 Preferably, the first directional slide 31, the second directional slide 32, the first spanwise slide 35, and the second spanwise slide 36 form the left end slide group, and the third directional slide 33, the fourth directional slide 34, the third spanwise slide 37, and the fourth spanwise slide 38 form the right end slide group, which can apply vibration excitation to any position of the left half of the movable wing test piece 5. The spacing between the front ball bearing slide 313 and the rear ball bearing slide 317 inside each slide needs to be determined according to the width of the base of the matching excitation device 4; the first directional slide 31 and the second directional slide 32 can rotate synchronously, and the first spanwise slide 35 and the second spanwise slide 36 can rotate synchronously.

[0082] Figure 8 In this configuration, the excitation device 4 has a yaw width of L1 and a spanwise width of L2. The spacing between the ball bearing slides inside the first yaw slide 31 and the second yaw slide 32 is determined based on L1, and the spacing between the ball bearing slides inside the first spanwise slide 35 and the second spanwise slide 36 is determined based on L2. The controller commands the first yaw slide 31 and the second yaw slide 32 to rotate synchronously, adjusting the yaw position of the excitation device 4, and commands the first spanwise slide 35 and the second spanwise slide 36 to rotate synchronously, adjusting the spanwise position of the excitation device 4.

[0083] In summary, static load loading and vibration loading are modular designs that can be repeatedly expanded and have broad application prospects.

[0084] The specific loading process is as follows:

[0085] 1. Install the movable wing test piece 5 onto the movable wing support 11, and adjust the static load system 2 to make it contact the movable wing test piece 5;

[0086] 2. Adjust the left and right slide groups so that the excitation rods of the two sets of excitation devices 4 are in the designated positions;

[0087] 3. The excitation device 4 connects the excitation rod and the movable wing structure via a vacuum chuck or screw connection;

[0088] 4. The controller inflates each airbag 22 to achieve the set static load value;

[0089] 5. Apply sinusoidal or random vibration to the excitation device 4 via the controller, and monitor the vibration response of the points of interest on the movable wing test piece 5;

[0090] 6. If the response is not ideal, further change the position of the excitation device 4 by using the left and right end slide groups to re-excite it.

[0091] In summary, this application has the following advantages:

[0092] It allows simultaneous application of vibration excitation to two different positions on the movable wing surface, or time-sharing adjustment of the positions of two sets of excitation devices. Combined with the three-dimensional mobility of the movable excitation platform, it can simulate the complex working conditions of "multi-position, multi-frequency" superimposed static loads on the movable wing surface in actual flight (such as flutter and buffeting combined loading), providing more comprehensive experimental data support for the fatigue life assessment and dynamic strength verification of the movable wing surface;

[0093] Through the collaborative innovation of a mobile excitation platform, a distributed static load system, and a high-rigidity frame, significant advantages have been achieved in terms of test efficiency, realism of operating condition simulation, data accuracy, and versatility, providing efficient and reliable test equipment for ground dynamic strength verification of movable wing surfaces of civil aircraft.

[0094] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A static load test device for vibration superposition of movable airfoil structure, characterized in that, It includes an overall frame (1), a static load system (2), a movable excitation platform (3), an excitation device (4), and a movable wing test piece (5); The overall frame (1) is used to support the static load system (2), the movable excitation platform (3), the excitation device (4), and the movable wing test piece (5); the movable wing test piece (5) is set horizontally, the static load system (2) is connected to the movable wing test piece (5), and the static load system (2) can perform distributed static low stiffness loading on the movable wing test piece (5) through the airbag (22); there are two sets of the excitation device (4) arranged side by side on the movable excitation platform (3); The movable excitation platform (3) can control the operation of the excitation device (4). The movable excitation platform (3) is connected to the excitation device (4) and can drive the excitation device (4) to move. The movable excitation platform (3) can cooperate with the excitation device (4) to apply multi-point surface arbitrary position excitation to the movable wing test piece (5).

2. The vibration superposition static load test device for movable wing structure as described in claim 1, characterized in that, The overall frame (1) includes movable wing support (11), column (13), reinforcing beam (16), base plate (17) and airbag support column (18); The support column consists of multiple columns connected side by side to the base plate (17). The movable wing support (11) is located at the top of the support column. The reinforcing beam (16) and the airbag support column (18) are located on both sides of the middle part of the support column. The movable wing support (11) is detachably connected to the movable wing test piece (5). A support mounting plate (12) is provided between the movable wing support (11) and the support column. The support mounting plate (12) is welded to the support column. The reinforcing beam (16) is provided with an outer diagonal brace (14) and an inner diagonal brace (15). There are multiple sets of the reinforcing beam (16), the outer diagonal brace (14) and the inner diagonal brace (15), which are arranged in parallel and equidistantly in the spanwise direction of the movable wing test piece (5). The airbag support column (18) is fixedly connected to the support column by means of diagonal bracing.

3. The vibration superposition static load test device for movable wing structure as described in claim 1, characterized in that, The loading assembly also includes a flexible polyurethane plate (21), a first support (23), an air servo valve (28), and a connecting air passage (29); The adjusting pad (26), sensing component and loading component are all in multiple sets and are spaced apart on the horizontal fixing plate (27); The adjusting pad (26) is connected to the horizontal fixing plate (27) and can be adjusted in position; The sensing component includes a static sensor (24) and a sensor mounting base (25). The sensor mounting base (25) is connected to an adjustment pad (26) and the sensor mounting base (25) is capable of adjusting the heading distance on the adjustment pad (26). The static sensor (24) is mounted on the sensor mounting base (25). The loading assembly includes a flexible polyurethane plate (21), an airbag (22), a first support (23), an air path servo valve (28), and a connecting air path (29); the upper part of the flexible polyurethane plate (21) is connected to the movable wing test piece (5), and the lower part is connected to the airbag (22); the first support (23) is located below the airbag (22) and supports the airbag (22); the connecting air path (29) is connected to the airbag (22), and the air path servo valve (28) is located on the connecting air path (29); The air circuit connects the air source and the controller, which can adjust the opening and closing of the air circuit servo valve (28) based on the feedback from the static sensor (24).

4. The vibration superposition static load test device for movable wing structure as described in claim 2, characterized in that, The excitation device (4) has two sets, and the movable excitation platform (3) includes a first directional slide (31), a second directional slide (32), a third directional slide (33), a fourth directional slide (34), a first spanwise slide (35), a second spanwise slide (36), a third spanwise slide (37), and a fourth spanwise slide (38). The first heading slide (31), the second heading slide (32), the third heading slide (33) and the fourth heading slide (34) are arranged in parallel, and the first spanning slide (35), the second spanning slide (36), the third spanning slide (37) and the fourth spanning slide (38) are arranged in parallel; The first heading slide (31) and the second heading slide (32) slide vertically in conjunction with the first spanning slide (35) and the second spanning slide (36); the third heading slide (33) and the fourth heading slide (34) slide vertically in conjunction with the third spanning slide (37) and the fourth spanning slide (38). The first spanwise slide (35) and the second spanwise slide (36) are connected to one of the sets of excitation devices (4); the third spanwise slide (37) and the fourth spanwise slide (38) are connected to another set of excitation devices (4).

5. The vibration superposition static load test device for movable wing structure as described in claim 4, characterized in that, The first navigating slide (31) includes a front ball slide (313), a rear ball slide (317), a lead screw (314), a linear guide (315), and a stepper motor (319); One end of the lead screw (314) is connected to the stepper motor (319), and the other end is connected to the front bearing baffle (311) on the base plate (17). The front ball slide (313) and the rear ball slide (317) are threadedly connected to the lead screw (314). The front ball slide (313) and the linear guide (315) are slidably fitted with a front slider assembly (312). The rear ball slide (317) and the linear guide (315) are slidably fitted with a rear slider assembly (316). The base plate (17) is also provided with a rear bearing baffle (318) at the end of the lead screw (314) near the stepper motor (319).

6. The vibration superposition static load test device for movable wing structure as described in claim 5, characterized in that, The first directional slide (31), the second directional slide (32), the first spanwise slide (35), and the second spanwise slide (36) form the left end slide group, which can apply vibration excitation to any position of the left half of the movable wing test piece (5); the third directional slide (33), the fourth directional slide (34), the third spanwise slide (37), and the fourth spanwise slide (38) form the right end slide group, the first directional slide (31) and the second directional slide (32) can rotate synchronously, and the first spanwise slide (35) and the second spanwise slide (36) can rotate synchronously.

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