A flexible straight wing rigidity test loading device

Abstract

The present application belongs to the technical field of flexible body aircraft performance testing, and particularly relates to a flexible flat wing stiffness test loading device. The loading device comprises a wing test piece tooling table, a top suspension cable beam, a counterweight loading device and a data monitoring and storage system; the counterweight loading device can realize higher precision equivalent loading of rigid wings and flexible wings under different working conditions through a pump liquid controller and a loading infusion bag, can greatly improve the loading weight through the loading infusion bag, and realizes stepless loading of the wings, improving the flexibility of the loading scheme design; a soft loading force transmission mode is realized through a loading clamping frame, a sliding clamp, a clamp sliding groove and a loading plate, and the loading weight of the loading infusion bag can be more gently and accurately loaded to the surface of the wing; the 3D printing structure of the loading plate can improve the precision and reliability of the bearing test.

Description

Technical Field

[0001] This invention belongs to the field of flexible body aircraft performance testing technology, specifically relating to a flexible straight wing stiffness testing loading device. Background Technology

[0002] Static strength and stiffness tests are crucial for verifying an airfoil's ability to withstand extreme loads under harsh conditions, ensuring flight safety. Traditional static strength and stiffness testing methods primarily employ methods such as laying sandbags flat or single-point suspension to apply the equivalent load of the mission. These loading methods are crude and cannot simulate the actual load distribution on the surface of a high-aspect-ratio airfoil under typical operating conditions. The test results are only instructive and cannot reproduce failure scenarios that may occur due to excessive local loads. Especially for flexible lightweight airfoil structures, single-point suspension can only measure the bending and torsional instability boundary of the airfoil, but under heavy loads, stress concentration near the suspension point may cause damage to the wing test piece. For many years, accurate equivalent loading for load-bearing performance testing of flexible lightweight airfoils has been a challenge in this field, restricting the design and large-scale application of flexible lightweight airfoils.

[0003] Therefore, it is urgent to develop a more reasonable test device for load-bearing tests of high aspect ratio wings, solve the problems of load equivalence and loading methods in load-bearing performance testing, obtain the actual strength, stiffness and other core indicators of high aspect ratio flexible wings, and guide engineering design. Summary of the Invention

[0004] To address the aforementioned problems in the existing technology, the present invention provides a flexible straight wing stiffness testing loading device.

[0005] To achieve the above objectives, the present invention adopts the following specific technical solution:

[0006] A flexible straight wing stiffness test loading device includes a wing test piece fixture, a top suspension beam, a counterweight loading device, and a data monitoring and storage system.

[0007] The wing test piece fixture is used to tightly clamp the wing root of the wing test piece;

[0008] The top suspension beam extends horizontally and can be slidably mounted on the top of the wing test piece fixture along the spanwise direction of the wing test piece to form a rigid cantilever beam, and is located above the wing test piece.

[0009] The counterweight loading device is used to apply equivalent aerodynamic loads to wing test pieces simulating different working conditions, and includes multiple loading clamping frames, a force gauge, a loading infusion bag, an infusion tubing, a pump controller, an infusion bag suspension rope, a loading suspension rope, and a winding motor; the force gauge, the loading infusion bag, the infusion tubing, the infusion bag suspension rope, the loading suspension rope, and the winding motor each correspond one-to-one with the loading clamping frame; the winding motor is fixedly installed on the top suspension beam and located directly above the corresponding loading clamping frame; the multiple loading clamps The holding frame is distributed at intervals along the spanwise direction of the wing test piece and fitted onto the loading positions of the wing test piece, and is connected to the winding motor via the loading suspension rope; the winding motor is used to adjust the loading height at each loading position of the wing test piece in real time by winding the loading suspension rope; the force gauge is suspended from the bottom end of the loading clamping frame via the infusion bag suspension rope; the loading infusion bag is suspended from the bottom end of the force gauge and is connected to the pump controller via the infusion hose; the pump controller can individually control the liquid weight of each loading infusion bag;

[0010] The data monitoring and storage system is connected to the force gauge and is used to monitor the loading weight of each of the loaded infusion bags in real time to ensure high-precision loading.

[0011] Furthermore, the counterweight loading device also includes a sliding clamp, a clamp sliding groove, and a loading plate;

[0012] The loading clamping frame is a hollow airfoil clamping frame structure, and a clamping device sliding groove extending along the chord direction of the wing test piece is provided on the upper surface; the sliding clamping device is slidably fitted in the clamping device sliding groove; the bottom end of the sliding clamping device is fixedly connected to the loading plate located inside the loading clamping frame; the loading plate can completely fit with the wing surface of the wing test piece, so as to evenly distribute the loading weight to the surface of the wing test piece and avoid damage to the wing test piece due to stress concentration;

[0013] By controlling the sliding clamp to slide along the sliding groove of the clamp, the loading plate is driven to move along its chord direction on the upper surface of the wing test piece, thereby adjusting the loading position of the wing test piece to approximate the equivalent position of the aerodynamic load center of the wing test piece under different working conditions to the greatest extent.

[0014] Furthermore, the sliding clamp is equipped with a rotating bearing and a fixing knob that are slidably connected to both ends of the sliding groove of the clamp;

[0015] The sliding clamp slides relative to the clamp sliding groove through the rotary bearing, so that the sliding clamp can only slide along the clamp sliding groove;

[0016] The fixing knob is used to fix the sliding clamp and the loading plate relative to the loading clamping frame.

[0017] Furthermore, the loading plate is a 3D printed flat panel component, the central part of which can bear more than 50kg; the upper edge of the loading plate is fixedly connected to the sliding clamp.

[0018] Furthermore, both the loading suspension rope and the infusion bag suspension rope are attached to the loading clamping frame on both sides.

[0019] Furthermore, the wing test piece fixture is composed of a clamping fixture, a fixture support platform, and a suspension beam support frame;

[0020] The suspension beam support frame is fixedly installed on the top of the tooling support platform;

[0021] The top suspension beam is slidably installed on the top of the suspension beam support frame;

[0022] The clamping fixture is fixedly installed on the fixture support platform; the clamping fixture is provided with an airfoil through-hole groove and a through-hole groove; the airfoil through-hole groove is used to install the wing root of the wing test piece; the through-hole groove is used to install the air inlet of the wing test piece.

[0023] Furthermore, a sliding groove is provided at the top of the suspension beam support frame;

[0024] The top suspension beam includes a suspension beam arm and a suspension beam slide rail; the suspension beam slide rail is welded to the lower edge of one end of the suspension beam arm, and the suspension beam slide rail is slidably placed in the sliding groove, so that the suspension beam arm can only slide along the spanwise direction of the wing test piece.

[0025] Furthermore, the suspension beam support frame is made of high-strength carbon steel and has an overall portal beam structure.

[0026] Furthermore, the tooling support platform is fixed to the ground by four square vertical beams, and its levelness is corrected using a level.

[0027] Furthermore, the clamping fixture is fixedly installed on the fixture support platform by bolts.

[0028] Compared with the prior art, the technical solution of the present invention has the following beneficial effects:

[0029] 1. Compared with the traditional rough loading of flat surfaces on the wing, the flexible straight wing stiffness test loading device of the present invention can achieve higher precision equivalent loading of rigid and flexible wings under different working conditions through the counterweight loading device. The loading method of using loading infusion bags can significantly increase the loading weight. Compared with the traditional sandbag loading method, the infusion loading can achieve stepless loading of the wing, greatly improving the flexibility of loading.

[0030] 2. The flexible straight wing stiffness test loading device of the present invention achieves a gentle loading force transmission method through the loading clamping frame, sliding clamp, clamp sliding groove and loading plate. Compared with the traditional single-point suspension loading method, the loading weight of the infusion bag can be loaded onto the wing surface more smoothly and accurately, preventing local damage to the wing test piece due to unreasonable loading under heavy load conditions.

[0031] 3. The loading plate of the flexible straight wing stiffness test loading device of the present invention is a 3D printed structural part. It can print a loading plate that perfectly fits the shape of the wing surface profile according to the loading displacement. The loading load is closer to the aerodynamic load distribution of the wing under typical working conditions, thereby improving the accuracy and reliability of the load test.

[0032] 4. The flexible straight wing stiffness test loading device of the present invention can be applied to the load test of both rigid and flexible wings. In particular, for heavily loaded flexible wings, the counterweight loading device has a higher surface fit to the flexible wing and can flexibly test the upper and lower surfaces of the wing to simulate the aerodynamic load under flight conditions under positive and negative angles of attack.

[0033] The flexible straight wing stiffness test loading device of the present invention can be widely applied in the field of flexible body aircraft performance testing technology. Attached Figure Description

[0034] Figure 1 This is a general layout diagram of the loading device for testing the stiffness of the flexible straight wing of the present invention;

[0035] Figure 2 This is a schematic diagram of the wing test piece tooling table and suspension beam of the flexible straight wing stiffness test loading device of the present invention;

[0036] Figures 3-5 This is a schematic diagram of the counterweight loading device of the flexible straight wing stiffness test loading device of the present invention;

[0037] Figures 6-8 This is a schematic diagram illustrating the working principle of the flexible straight wing stiffness test loading device of the present invention.

[0038] Figure label:

[0039] 1-Wing test piece fixture, 2-Top suspension beam, 3-Counterweight loading device, 4-Data monitoring and storage system, 101-Wing test piece, 11-Clamping fixture, 12-Fitting support platform, 13-Suspension beam support frame, 21-Suspension beam arm, 22-Suspension beam slide rail, 31-Loading clamping frame, 32-Sliding clamp, 33-Clamping clamp sliding groove, 34-Loading plate, 35-Force gauge, 36-Loading infusion bag, 37-Infusion hose, 38-Pump controller, 501-Infusion bag suspension rope, 502-Loading suspension rope, 601-Rewinding motor Detailed Implementation

[0040] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0041] In the description of this invention, it should be understood that the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances. Furthermore, in the description of this invention, unless otherwise stated, "multiple" refers to two or more. "And / or" describes the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A existing alone, A and B existing simultaneously, and B existing alone. The character " / " generally indicates that the preceding and following related objects have an "or" relationship.

[0042] like Figure 1-5 As shown, this embodiment of the invention provides a loading device for testing the stiffness of a flexible straight wing. The loading device includes a wing test piece fixture 1, a top suspension beam 2, a counterweight loading device 3, and a data monitoring and storage system 4. The wing test piece fixture 1 serves as the main support platform for the entire loading device, and is used to tightly clamp the wing root of the wing test piece 101. The top suspension beam 2 extends horizontally and is slidably mounted on the top of the wing test piece fixture 1 along the spanwise direction of the wing test piece 101, forming a rigid cantilever beam, and is located above the wing test piece 101. The top suspension beam 2 is placed in the same direction as the spanwise direction of the wing test piece 101.

[0043] like Figure 3 , Figure 4 and Figure 5As shown, the counterweight loading device 3 is used to apply equivalent aerodynamic loads to the wing test piece 101 simulating different working conditions, and includes multiple loading clamping frames 31, force gauges 35, loading infusion bags 36, infusion hoses 37, pump controllers 38, infusion bag suspension ropes 501, loading suspension ropes 502, and winding motors 602. The force gauges 35, loading infusion bags 36, infusion hoses 37, infusion bag suspension ropes 501, loading suspension ropes 502, and winding motors 602 are all corresponding one-to-one with the loading clamping frames 31, that is, each loading position on the wing test piece 101 is equipped with a counterweight loading device 31. A loading clamping frame 31 is provided. To achieve loading at each loading position, a loading infusion bag 36, an infusion bag suspension rope 501, a force gauge 35, an infusion tubing 37, a loading suspension rope 502, and a winding motor 602, each corresponding to the loading clamping frame 31, are also required. The corresponding loading clamping frame 31, force gauge 35, loading infusion bag 36, infusion tubing 37, infusion bag suspension rope 501, loading suspension rope 502, and winding motor 602 form a set of counterweight loading mechanisms. The pump controller 38 is simultaneously connected to each loading infusion bag 36, using a... A pump controller 38 controls multiple sets of counterweight loading mechanisms; a winding motor 602 is fixedly installed on the top suspension beam 2 and located directly above the corresponding loading clamping frame 31; multiple loading clamping frames 31 are distributed at intervals along the spanwise direction of the wing test piece 101 and are fitted onto the loading positions of the wing test piece 101, and are connected to the winding motor 602 via loading suspension ropes 502; the winding motor 602 is used to adjust the loading height at each loading position of the wing test piece 101 in real time by winding the loading suspension ropes 502; the lower edge of the loading clamping frame 31 is suspended by an infusion bag attached to both sides. Rope 501 connects to force gauge 35, which is suspended at the bottom of loading clamping frame 31 via infusion bag suspension rope 501. Loading infusion bags 36 are suspended at the bottom of force gauge 35 and connected to pump controller 38 via infusion tubing 37. Pump controller 38 can individually control the liquid weight of each loading infusion bag 36, thus controlling the liquid input and output of all connected loading infusion bags 36, thereby controlling the loading speed and weight of each set of counterweight loading devices 3, achieving complete loading of the entire wing test piece 101. Data monitoring and storage system 4 is connected to force gauge 35 to monitor the loading weight of each loading infusion bag 36 in real time to ensure high-precision loading. Loading suspension rope 502 and infusion bag suspension rope 501 are both attached to loading clamping frame 31 on both sides.

[0044] like Figure 4As shown, the aforementioned counterweight loading device 3 also includes a sliding clamp 32, a clamp sliding groove 33, and a loading plate 34, each corresponding to a loading clamping frame 31. The loading clamping frame 31 is a hollow airfoil clamping frame structure, and a clamp sliding groove 33 extending along the chord direction of the wing test piece 101 is provided on its upper surface. The sliding clamp 32 is slidably fitted within the clamp sliding groove 33. The bottom end of the sliding clamp 32 is fixedly connected to a loading plate 34 located inside the loading clamping frame 31. The loading plate 34 can completely fit against the wing surface of the wing test piece 101, and is used to load the wing test piece 101. The load is evenly distributed and transferred to the surface of the wing test piece 101, avoiding damage to the wing test piece 101 due to stress concentration. By controlling the sliding clamp 32 to slide along the clamp sliding groove 33, the loading plate 34, which is fixed to the sliding clamp 32, moves along its chord direction on the upper surface of the wing test piece 101, thereby simulating and adjusting the loading position (load center) of the wing test piece 101. Adjusting the loading position of the wing test piece 101 is intended to approximate the equivalent position of the aerodynamic load pressure center of the wing test piece 101 under different working conditions to the greatest extent.

[0045] The aforementioned sliding clamp 32 is equipped with a rotating bearing and a fixing knob that are slidably connected to both ends of the clamp sliding groove 33; the sliding clamp 32 slides relative to the clamp sliding groove 33 through the rotating bearing, so that the sliding clamp 32 can only slide along the clamp sliding groove 33; the fixing knob is used to fix the sliding clamp 32 and the loading plate 34 relative to the loading clamping frame 31.

[0046] The loading plate 34 is a 3D-printed flat component, with its central portion capable of bearing over 50kg. The upper edge of the loading plate 34 is bolted to the sliding clamp 32. One side of the loading plate 34 is attached to the surface of the wing test piece 101. Using a 3D-printed loading plate 34 attached to the surface of the wing test piece 101 allows for a more even distribution of the load corresponding to the infusion bag 36 onto the surface of the wing test piece 101. Compared to the traditional single-point suspension method, the load distribution is smoother and gentler, preventing damage to the wing test piece 101 caused by excessive local stress concentration near the suspension point due to the excessive weight of the infusion bag 36.

[0047] like Figure 2As shown, the aforementioned wing test piece fixture 1 consists of a clamping fixture 11, a fixture support platform 12, and a suspension beam support frame 13. The suspension beam support frame 13 is fixedly installed on the top of the fixture support platform 12. The top suspension beam 2 is slidably installed on the top of the suspension beam support frame 13. A sliding groove is provided on the top of the suspension beam support frame 13. The top suspension beam 2 includes a suspension beam arm 21 and a suspension beam slide rail 22. The lower edge of one end of the suspension beam arm 21 is welded with the suspension beam slide rail 22, which is slidably placed in the sliding groove at the top of the suspension beam support frame 13. Through the tight engagement between the suspension beam slide rail 22 and the sliding groove, the suspension beam arm 21 can only slide along the spanwise direction of the wing test piece 101.

[0048] The clamping fixture 11 is fixedly installed on the fixture support platform 12 by bolts. The clamping fixture 11 is used to tightly clamp the wing root part of the wing test piece 101. The clamping fixture 11 is provided with an airfoil through-hole groove and a through-hole groove. The through-hole groove is provided along the clamping direction of the wing test piece 101 (i.e., the spanwise direction of the wing test piece 101). The airfoil through-hole groove is used to install the wing root of the wing test piece 101. The clamping fixture 11 is provided with through-hole grooves arranged regularly on the top and bottom. The through-hole grooves are used to install the air inlet and auxiliary devices of the wing test piece 101 to prevent crushing damage.

[0049] The suspension beam support frame 13 is made of high-strength carbon steel and has an overall portal beam structure. The tooling support platform 12 is fixed to the ground by four square vertical beams and its levelness is corrected using a level. The clamping fixture 11 is fixedly installed on the tooling support platform 12 by bolts.

[0050] The aforementioned flexible straight wing stiffness test loading device controls the winding of the loading suspension rope 502 through the winding motor 602 on the suspension beam arm 21, thereby adjusting the height of the loading clamping frame 31 connected to it in real time to adapt to the loading height of different parts of the wing test piece 101 under different working conditions. Before the counterweight loading device 3 loads, the winding motor 602 pulls the loading suspension rope 502 to suspend the loading clamping frame 31. The loading clamping frame 31 is fitted onto the wing test piece 101 and suspended in the air. At this time, there is no liquid in the loading infusion bag 36. When loading starts, the pump controller 38 pumps loading liquid into the loading infusion bag 36 through the infusion hose 37 until the weight of the loading infusion bag 36 is equal to the loading counterweight under the current working condition and the pump stops. Then, the winding motor 602 activates the release unlocking function, the loading suspension rope 502 is in a slack state, and the loading clamping frame 31 will freely adhere to the surface of the wing test piece 101. The weight of the loading infusion bag 36 is fully applied to the corresponding loading position of the wing test piece 101 through the loading plate 34, completing the full loading.

[0051] like Figure 6 , Figure 7 and Figure 8As shown, the specific working principle of the above-mentioned flexible straight wing stiffness test loading device is as follows:

[0052] First, install the wing test piece fixture 1 and fix it to the ground test area. Secure it to the ground with bolts and adjust the level of the wing test piece fixture 11 by using a level.

[0053] Then, the wing test piece 101 is clamped by the wing test piece fixture 1 and adjusted to the corresponding position; the position of the top suspension beam 2 is adjusted by the suspension beam slide rail 22 so that it is flush with the wing test piece 101 and the length is basically the same. The counterweight loading device 3 is installed. Before the counterweight loading device 3 is loaded, the winding motor 602 is controlled to pull the loading suspension rope 502 to suspend the counterweight loading device 3. The loading clamping frame 31 is placed on the wing test piece 101 and suspended in the air. At this time, there is no liquid in the loading infusion bag 36.

[0054] When loading begins, the pump controller 38 pumps loading liquid into the loading infusion bag 36 through the infusion hose 37 until the weight of the loading infusion bag 36 equals the loading counterweight under the current working condition, at which point the pumping stops. During this process, the target weight of each loading infusion bag 36 is monitored in real time by the force gauge 35 and the data monitoring and storage system 4 to ensure high-precision loading. Then, the winding motor 602 activates the release unlock function, the loading suspension rope 502 is in a slack state, and the counterweight loading device 3 freely adheres to the surface of the wing test piece 101. The weight of the loading infusion bag 36 is fully applied to the corresponding loading position of the wing test piece 101 through the loading plate 34, completing the full loading. By repeating the above steps, equivalent loading is applied to the wing test piece 101 under each typical working condition, and the displacement of the wing test piece 101 at different positions is measured and the loading weight is recorded, thus completing the load-bearing test of a high aspect ratio straight wing.

[0055] Obviously, those skilled in the art can make various modifications and variations to the embodiments of the present invention without departing from the spirit and scope of the invention. Therefore, if these modifications and variations fall within the scope of the claims of the present invention and their equivalents, the present invention also intends to include these modifications and variations.

[0056] In summary, the above are merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A loading device for testing the stiffness of a flexible straight wing, characterized in that, This includes a wing test piece fixture, a top suspension beam, a counterweight loading device, and a data monitoring and storage system; The wing test piece fixture is used to tightly clamp the wing root of the wing test piece; The top suspension beam extends horizontally and can be slidably mounted on the top of the wing test piece fixture along the spanwise direction of the wing test piece, forming a rigid cantilever beam, and is located above the wing test piece. The counterweight loading device is used to apply equivalent aerodynamic loads to wing test pieces simulating different working conditions, and includes multiple loading clamping frames, a force gauge, a loading infusion bag, an infusion tubing, a pump controller, an infusion bag suspension rope, a loading suspension rope, and a winding motor; the force gauge, the loading infusion bag, the infusion tubing, the infusion bag suspension rope, the loading suspension rope, and the winding motor each correspond one-to-one with the loading clamping frame; the winding motor is fixedly installed on the top suspension beam and located directly above the corresponding loading clamping frame; the multiple loading clamps The holding frame is distributed at intervals along the spanwise direction of the wing test piece and fitted onto the loading positions of the wing test piece, and is connected to the winding motor via the loading suspension rope; the winding motor is used to adjust the loading height at each loading position of the wing test piece in real time by winding the loading suspension rope; the force gauge is suspended from the bottom end of the loading clamping frame via the infusion bag suspension rope; the loading infusion bag is suspended from the bottom end of the force gauge and is connected to the pump controller via the infusion hose; the pump controller can individually control the liquid weight of each loading infusion bag; The data monitoring and storage system is connected to the force gauge and is used to monitor the loading weight of each loading infusion bag in real time to ensure high-precision loading. The counterweight loading device also includes a sliding clamp, a clamp sliding groove, and a loading plate; The loading clamping frame is a hollow airfoil clamping frame structure, and a clamping device sliding groove extending along the chord direction of the wing test piece is provided on the upper surface; the sliding clamping device is slidably fitted in the clamping device sliding groove; the bottom end of the sliding clamping device is fixedly connected to the loading plate located inside the loading clamping frame; the loading plate can completely fit with the wing surface of the wing test piece, so as to evenly distribute the loading weight to the surface of the wing test piece and avoid damage to the wing test piece due to stress concentration; By controlling the sliding clamp to slide along the sliding groove of the clamp, the loading plate is driven to move along its chord direction on the upper surface of the wing test piece, thereby adjusting the loading position of the wing test piece to achieve the purpose of maximally simulating the equivalent position of the aerodynamic load center of the wing test piece under different working conditions.

2. The flexible straight wing stiffness test loading device as described in claim 1, characterized in that, The sliding clamp is equipped with a rotating bearing and a fixing knob that are slidably connected to both ends of the sliding groove of the clamp. The sliding clamp slides relative to the clamp sliding groove through the rotary bearing, so that the sliding clamp can only slide along the clamp sliding groove; The fixing knob is used to fix the sliding clamp and the loading plate relative to the loading clamping frame.

3. The flexible straight wing stiffness test loading device as described in claim 1, characterized in that, The loading plate is a 3D printed flat panel component, the central part of which can bear more than 50kg; the upper edge of the loading plate is fixedly connected to the sliding clamp.

4. The flexible straight wing stiffness test loading device as described in claim 1, characterized in that, Both the loading suspension rope and the infusion bag suspension rope are attached to the loading clamping frame on both sides.

5. The flexible straight wing stiffness test loading device as described in any one of claims 1-4, characterized in that, The wing test piece fixture consists of a clamping fixture, a fixture support platform, and a suspension beam support frame. The suspension beam support frame is fixedly installed on the top of the tooling support platform; The top suspension beam is slidably installed on the top of the suspension beam support frame; The clamping fixture is fixedly installed on the fixture support platform; the clamping fixture is provided with an airfoil through-hole groove and a through-hole groove; the airfoil through-hole groove is used to install the wing root of the wing test piece; the through-hole groove is used to install the air inlet of the wing test piece.

6. The flexible straight wing stiffness test loading device as described in claim 5, characterized in that, The top of the suspension beam support frame is provided with a sliding groove; The top suspension beam includes a suspension beam arm and a suspension beam slide rail; the suspension beam slide rail is welded to the lower edge of one end of the suspension beam arm, and the suspension beam slide rail is slidably placed in the sliding groove, so that the suspension beam arm can only slide along the spanwise direction of the wing test piece.

7. The flexible straight wing stiffness test loading device as described in claim 5, characterized in that, The suspension beam support frame is made of high-strength carbon steel and has an overall portal beam structure.

8. The flexible straight wing stiffness test loading device as described in claim 5, characterized in that, The tooling support platform is fixed to the ground by four square vertical beams, and its levelness is corrected using a level.

9. The flexible straight wing stiffness test loading device as described in claim 5, characterized in that, The clamping fixture is fixedly installed on the fixture support platform by bolts.

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