Dynamic loading device for folding wing

Abstract

The invention relates to a folding wing dynamic loading device, and belongs to the field of folding wing loading tests. Comprising two wings, a mechanism bracket, a bottom plate, a supporting wheel assembly and two groups of loading mechanisms, wherein the bottom plate is of a flat plate-shaped structure which is horizontally arranged; the supporting wheel assembly is arranged at the bottom of the bottom plate to support and move the bottom plate; the mechanism support is vertically installed on the side edge of the upper surface of the bottom plate. The two wings are horizontally and symmetrically mounted below the mechanism bracket; the upper surfaces of the roots of the two wings are installed on the top of the mechanism support through a U-shaped frame. The two groups of loading mechanisms are symmetrically mounted on the upper surface of the bottom plate; each group of loading mechanism corresponds to one wing; each group of loading mechanism is connected with the corresponding wing to realize triaxial dynamic loading of the corresponding wing; loads are applied to the missile wing through the loading device according to the sequence that the loads change along with the unfolding position, and the dynamic load borne by the missile wing in the unfolding process is simulated.

Description

Technical Field

[0001] The invention belongs to the field of folding wing loading test and relates to a folding wing dynamic loading device. Background Art

[0002] In order to reduce the space occupied by missiles and increase the payload, many missiles use folding wings. The wings are folded and placed in the launch tube or hung on the aircraft's pylons. After launch, the wings are quickly unfolded to the designed position and locked under the action of the unfolding mechanism. When unfolding, it is necessary to ensure that the folding wings meet the requirements of the designed unfolding time, unfolding angle and unfolding synchronization. After unfolding in place, they must be able to be reliably locked and conform to the aerodynamic shape design of the entire missile. Whether the unfolding state of the folding wings is correct determines the success or failure of the missile flight. The aerodynamic load acting on the wing surface is a key factor affecting whether the folding wings can be unfolded normally. The aerodynamic load of the wing surface is an important indicator of structural design and component selection. Therefore, determining the aerodynamic load during the unfolding process of the folding wings is of great significance to the design of the folding wings. The unfolding of the folding wings is a dynamic process. At each state point, the aerodynamic force on the wing surface is different. The current common practice is to install folding wings on an aircraft model and conduct a folding wing deployment test in a wind tunnel to assess the deployment time, angle and other indicators of the folding wings. Wind tunnel tests are costly and difficult to coordinate. For high-speed aircraft, the size of the wind tunnel is difficult to meet the full-scale deployment test, and it becomes difficult to assess the actual indicators of the folding wing deployment. Summary of the invention

[0003] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art and propose a folding wing dynamic loading device, which applies load to the wing according to the sequence of load changes with the unfolding position, so as to simulate the dynamic load borne by the wing during the unfolding process.

[0004] The solution of the present invention is:

[0005] A folding wing dynamic loading device, comprising two wings, a mechanism bracket, a bottom plate, a support wheel assembly and two sets of loading mechanisms;

[0006] Among them, the base plate is a horizontally arranged flat plate structure; the support wheel assembly is arranged at the bottom of the base plate to realize the support and movement of the base plate; the mechanism bracket is vertically installed on the side of the upper surface of the base plate; the two wings are horizontally and symmetrically installed below the mechanism bracket; the root upper surfaces of the two wings are installed on the top of the mechanism bracket through a U-shaped frame; two groups of loading mechanisms are symmetrically installed on the upper surface of the base plate; each group of loading mechanisms corresponds to one wing; each group of loading mechanisms is connected to the corresponding wing to realize three-axial dynamic loading of the corresponding wing.

[0007] In the above-mentioned folding wing dynamic loading device, the loading mechanism includes a linear electric cylinder, a rocker arm, a rocker arm support, a lateral loading motor, a wing fixture, a force measurement component, a wing tip fixture, a displacement sensor and an angle encoder;

[0008] Among them, the lateral loading motor is installed on the upper surface of the base plate; the output shaft of the lateral loading motor is vertically upward; the rocker arm is a horizontal plate structure; one end of the rocker arm is sleeved on the output shaft of the lateral loading motor; the angle encoder is arranged at the top of the lateral loading motor; the rocker arm support is vertically arranged at the bottom of the rocker arm, and the top of the rocker arm support is in contact with the lower surface of the rocker arm, and the bottom of the rocker arm support is in contact with the upper surface of the base plate; the linear electric cylinder is vertically installed in the middle position of the upper surface of the rocker arm; the force measurement component is installed at the top output end of the linear electric cylinder; the wing fixture is installed on the top of the force measurement component, and the wing fixture clamps the middle part of the corresponding wing; the wingtip fixture is clamped at the wing tip position of the corresponding wing; the wingtip fixture is connected to the end of the rocker arm through a vertically arranged displacement sensor.

[0009] In the above-mentioned folding wing dynamic loading device, the loading of the corresponding wing in the vertical direction is achieved by extending the output shaft of the linear electric cylinder; and the measurement of the three-axis loading force is achieved by the force measurement component.

[0010] In the above-mentioned folding wing dynamic loading device, the two wings are set closed in the initial state; during the process of the wing rotating and opening, the rocker arm is driven to rotate synchronously by the lateral loading motor; there is a synchronization error during the synchronous rotation of the wing and the rocker arm, generating horizontal force along the wing axis direction and horizontal force perpendicular to the wing axis direction.

[0011] In the above-mentioned folding wing dynamic loading device, the rotation angle of the rocker arm is monitored by an angle encoder; and the rotation position of the rocker arm and the wing is monitored by a displacement sensor.

[0012] In the above-mentioned folding wing dynamic loading device, the top of the rocker arm support is fixedly connected to the lower surface of the rocker arm; the bottom of the rocker arm support is a universal wheel structure; the rocker arm support is able to follow the rocker arm relative to the rocker arm; the rocker arm support is arranged at a corresponding position below the linear electric cylinder.

[0013] In the above-mentioned folding wing dynamic loading device, the force measurement assembly includes a normal force sensor, a normal sensor mounting flange, a tangential force sensor, a tangential force sensor mounting flange, a flexible beam and a flexible beam mounting nut;

[0014] Among them, the upper end of the normal force sensor is connected to the wing clamp with screws, and the lower end of the normal force sensor is installed on the normal sensor mounting flange with screws; the normal sensor mounting flange is an inverted L-shaped structure; the flexible beam is set horizontally; the positioning section at the front end of the flexible beam passes through the positioning hole on the vertical side wall of the normal sensor mounting flange and is tightened by the flexible beam mounting nut; the rear end of the flexible beam is tightened in the threaded hole of the tangential force sensor; the tangential force sensor is installed on the tangential force sensor mounting flange with screws; the tangential force sensor mounting flange is installed on the output end of the linear electric cylinder with nuts.

[0015] In the above-mentioned folding wing dynamic loading device, the flexible beam includes a rear end threaded section, a normal flexible hinge and a front end threaded section; wherein the normal flexible hinge is a rectangular structure arranged axially horizontally; the rear end threaded section is coaxially installed at the axial rear end of the normal flexible hinge; the front end threaded section is coaxially installed at the axial front end of the normal flexible hinge; the rear end threaded section is tightened in the threaded hole of the tangential force sensor; the front end threaded section passes through the vertical side wall of the flexible beam mounting nut; the plane where the normal flexible hinge is located is parallel to the horizontal reference plane; the installation direction of the flexible beam is adjusted by installing an adjustment gasket between the rear end threaded section and the tangential force sensor.

[0016] In the above-mentioned folding wing dynamic loading device, the loading process of the loading device is as follows:

[0017] The wing rotates open, and the feedback signal of the wing rotation position is used as the input of the lateral loading motor; after the angle encoder detects that the lateral loading motor has reached the position, the control mode is automatically switched to force control; the lateral loading motor continues to move, and when the composite load sequence of the wing horizontal force value feedback from the force measurement component requires it, the loading motor maintains the current position; while the lateral loading motor moves, the linear electric cylinder moves upward, and when the composite load sequence of the wing normal force value feedback from the force measurement component requires it, the linear electric cylinder maintains the current position; after the wing horizontal force and normal force are loaded, the above cycle is repeated to continue loading the wing load at the next position.

[0018] In the above-mentioned folding wing dynamic loading device, the control period of the lateral loading motor is 5 milliseconds to ensure the continuity of the loading process.

[0019] The beneficial effects of the present invention compared with the prior art are:

[0020] (1) The folding wing dynamic loading test method designed by the present invention effectively solves the problem that ground test equipment cannot fully simulate the aerodynamic force during the wing deployment process;

[0021] (2) The present invention uses industrial automation products such as servo motors, displacement sensors, angle encoders, force sensors, etc. to form an electromechanical system based on a force-position hybrid control method, which has low cost, high reliability, and high loading accuracy, effectively solving the problems of high cost, long cycle, and poor flexibility of wind tunnel testing;

[0022] (3) The present invention integrates a normal loading unit, a lateral loading unit, a force feedback unit and a displacement measurement unit, and divides the load borne by the folding wing during the unfolding process into the normal force of the wing and the tangential force of the wing, wherein the tangential force is the combined force of the axial force and the lateral force. The loading device applies a load to the wing in a sequence in which the load changes with the unfolding position, simulating the dynamic load borne by the wing during the unfolding process. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 This is a front view of the folding wing dynamic loading device of the present invention;

[0024] Figure 2 A top view of the folding wing dynamic loading device of the present invention;

[0025] Figure 3 It is a side view of the folding wing dynamic loading device of the present invention;

[0026] Figure 4 It is a schematic diagram of the force measurement assembly of the present invention;

[0027] Figure 5 It is a schematic diagram of the flexible beam structure of the present invention. DETAILED DESCRIPTION

[0028] The present invention will be further described below in conjunction with the embodiments.

[0029] The present invention provides a folding wing dynamic loading device, which uses a ground test device to simulate the load borne by the folding wing during the unfolding process, and evaluates the unfolding performance of the folding wing mechanism. It changes the previous wind tunnel unfolding test method, uses ground equipment to simulate the aerodynamic load on the wing surface, greatly reduces the test cost, and improves the test efficiency.

[0030] The folding wing dynamic loading device is composed of a frame, a normal loading unit, a lateral loading unit, a force feedback unit and a displacement measuring unit.

[0031] The frame serves as the basis of the entire test device, including a mechanism bracket 21, a base plate 22 and a support wheel assembly 23. The mechanism bracket 21 is welded to the base plate 22, and the support wheel assembly 23 is installed on the base plate 22 by screws; the folding wing 1 is installed on the frame by screws.

[0032] The normal loading unit is a linear electric cylinder 33 mounted on the rocker arm 36 using screws, and the screw at the output end of the linear electric cylinder 33 is used to install the force measurement component 32.

[0033] The lateral loading unit includes a rocker arm 36, a rocker arm support 37 and a lateral loading motor 39. The rocker arm 36 is connected to the lateral loading motor 39 with screws, and the rocker arm support 37 is installed on the rocker arm 36 with screws to support the entire rocker arm 36 and prevent excessive overturning torque from damaging the loading motor 39.

[0034] The force feedback unit includes a wing fixture 31 and a force measurement assembly 32, which are used to measure the load borne by the wing and provide force feedback for the control system.

[0035] Folding wing dynamic loading device, such as Figure 1 , Figure 2 , Figure 3 As shown, it specifically includes two wings 1, a mechanism bracket 21, a base plate 22, a support wheel assembly 23 and two groups of loading mechanisms. Among them, the base plate 22 is a horizontally arranged flat plate structure; the support wheel assembly 23 is arranged at the bottom of the base plate 22 to support and move the base plate 22; the mechanism bracket 21 is vertically installed at the side of the upper surface of the base plate 22; the two wings 1 are horizontally symmetrically installed below the mechanism bracket 21; the root upper surfaces of the two wings 1 are installed on the top of the mechanism bracket 21 through a U-shaped frame; two groups of loading mechanisms are symmetrically installed on the upper surface of the base plate 22; each group of loading mechanisms corresponds to one wing 1; each group of loading mechanisms is connected to the corresponding wing 1 to achieve triaxial dynamic loading of the corresponding wing 1.

[0036] The loading mechanism includes a linear electric cylinder 33 , a rocker arm 36 , a rocker arm support 37 , a lateral loading motor 39 , a wing fixture 31 , a force measurement component 32 , a wingtip fixture 34 , a displacement sensor 35 and an angle encoder 38 . Among them, the lateral loading motor 39 is installed on the upper surface of the base plate 22; the output shaft of the lateral loading motor 39 is vertically upward; the rocker arm 36 is a horizontal plate structure; one end of the rocker arm 36 is sleeved on the output shaft of the lateral loading motor 39; the angle encoder 38 is arranged at the top of the lateral loading motor 39; the rocker arm support 37 is vertically arranged at the bottom of the rocker arm 36, and the top of the rocker arm support 37 contacts the lower surface of the rocker arm 36, and the bottom of the rocker arm support 37 contacts the upper surface of the base plate 22; the linear electric cylinder 33 is vertically installed in the middle position of the upper surface of the rocker arm 36; the force measurement component 32 is installed at the top output end of the linear electric cylinder 33; the wing fixture 31 is installed on the top of the force measurement component 32, and the wing fixture 31 clamps the middle part of the corresponding wing 1; the wingtip fixture 34 is clamped at the wing tip position of the corresponding wing 1; the wingtip fixture 34 is connected to the end of the rocker arm 36 through a vertically arranged displacement sensor 35. The top of the rocker arm support 37 is fixedly connected to the lower surface of the rocker arm 36; the bottom of the rocker arm support 37 is a universal wheel structure; the rocker arm support 37 is able to follow the rocker arm 36; the rocker arm support 37 is arranged at a corresponding position below the linear electric cylinder 33.

[0037] The output shaft of the linear electric cylinder 33 is extended to realize loading of the corresponding wing 1 in the vertical direction; and the force measurement component 32 is used to realize measurement of the three-axis loading force.

[0038] In the initial state, the two wings 1 are closed; during the process of the wing 1 rotating and opening, the rocker arm 36 is driven to rotate synchronously by the lateral loading motor 39; there is a synchronization error during the synchronous rotation of the wing 1 and the rocker arm 36, generating a horizontal force along the axis direction of the wing 1 and a horizontal force perpendicular to the axis direction of the wing 1.

[0039] The rotation angle of the rocker arm 36 is monitored by the angle encoder 38 ; the rotation position of the rocker arm 36 and the wing 1 is monitored by the displacement sensor 35 .

[0040] like Figure 4 As shown, the force measurement assembly 32 includes a normal force sensor 321, a normal sensor mounting flange 322, a tangential force sensor 323, a tangential force sensor mounting flange 324, a flexible beam 325 and a flexible beam mounting nut 326;

[0041] Among them, the upper end of the normal force sensor 321 is connected to the wing clamp 31 by screws, and the lower end of the normal force sensor 321 is installed on the normal sensor mounting flange 322 by screws; the normal sensor mounting flange 322 is an inverted L-shaped structure; the flexible beam 325 is arranged horizontally; the positioning section at the front end of the flexible beam 325 passes through the positioning hole on the vertical side wall of the normal sensor mounting flange 322, and is tightened by the flexible beam mounting nut 326; the rear end of the flexible beam 325 is tightened in the threaded hole of the tangential force sensor 323; the tangential force sensor 323 is installed on the tangential force sensor mounting flange 324 by screws; the tangential force sensor mounting flange 324 is installed on the output end of the linear electric cylinder 33 by nuts.

[0042] like Figure 5 As shown, the flexible beam 325 includes a rear end threaded segment 3251, a normal flexible hinge 3252 and a front end threaded segment 3253; wherein the normal flexible hinge 3252 is a rectangular structure axially horizontally arranged; the rear end threaded segment 3251 is coaxially installed at the axial rear end of the normal flexible hinge 3252; the front end threaded segment 3253 is coaxially installed at the axial front end of the normal flexible hinge 3252; the rear end threaded segment 3251 is tightened in the threaded hole of the tangential force sensor 323; the front end threaded segment 3253 passes through the vertical side wall of the flexible beam mounting nut 326; the plane where the normal flexible hinge 3252 is located is parallel to the horizontal reference plane; the installation direction of the flexible beam 325 is adjusted by installing an adjustment gasket between the rear end threaded segment 3251 and the tangential force sensor 323.

[0043] The loading process of the loading device is:

[0044] Wing 1 rotates open, and the feedback signal of the rotation position of wing 1 is used as the input of the lateral loading motor 39; after the angle encoder 38 detects that the lateral loading motor 39 has reached the position, the control mode is automatically switched to force control; the lateral loading motor 39 continues to move, and when the composite load sequence of the horizontal force value of wing 1 fed back by the force measurement component 32 requires, the loading motor 39 maintains the current position; while the lateral loading motor 39 moves, the linear electric cylinder 33 moves upward, and when the composite load sequence of the normal force value of wing 1 fed back by the force measurement component 32 requires, the linear electric cylinder 33 maintains the current position; after the horizontal force and normal force of wing 1 are loaded, the above cycle is repeated to continue loading the wing 1 load at the next position.

[0045] The control period of the transverse loading motor 39 is 5 milliseconds to ensure the continuity of the loading process.

[0046] The test principle of the present invention is as follows: the load borne by the folding wing during the unfolding process is divided into the normal force of the wing and the tangential force of the wing, wherein the tangential force is the resultant force of the axial force and the lateral force. The load is applied to the wing by a loading device in a sequence in which the load changes with the unfolding position, simulating the dynamic load borne by the wing during the unfolding process. The displacement and the resultant force of the axial force and the lateral force corresponding to the displacement are used as the control input of the transverse loading motor 39, and the normal force corresponding to the displacement is used as the input of the normal loading unit 33. The loading of the normal force of the wing is realized by the normal loading unit, and the displacement of the linear electric cylinder 33 is controlled to control the magnitude of the normal force of the wing; the tangential force of the wing is converted into the torque that the transverse loading unit needs to provide, and the magnitude of the tangential force of the wing is controlled by the displacement of the transverse loading motor 39 and the loading position of the rocker arm 36.

[0047] The unfolding position fed back by the folding wing is used as the position input of the loading device to achieve displacement synchronization. At the same time, a force sensor is used as a measuring element to feedback the load on the wing. According to the force-position hybrid control algorithm, the loading device and the folding wing are unfolded synchronously while the designed load is applied to the wing in real time.

[0048] The folding wing dynamic loading test method designed in the present invention effectively solves the problem that ground test equipment cannot fully simulate the aerodynamic force exerted on the wing during the unfolding process.

[0049] The present invention uses industrial automation products such as servo motors, displacement sensors, angle encoders, force sensors, etc. to form an electromechanical system based on a force-position hybrid control method. It has low cost, high reliability, and high loading accuracy, and effectively solves the problems of high cost, long cycle, and poor flexibility of wind tunnel tests.

[0050] The present invention integrates a normal loading unit, a lateral loading unit, a force feedback unit and a displacement measurement unit, and divides the load borne by the folding wing during the unfolding process into the normal force of the wing and the tangential force of the wing, wherein the tangential force is the combined force of the axial force and the lateral force. The loading device applies a load to the wing in a sequence in which the load changes with the unfolding position, simulating the dynamic load borne by the wing during the unfolding process.

[0051] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A folding wing dynamic loading device, characterized in that: It comprises two wings (1), a mechanism bracket (21), a base plate (22), a support wheel assembly (23) and two sets of loading mechanisms; The bottom plate (22) is a flat plate-shaped structure arranged horizontally; the support wheel assembly (23) is arranged at the bottom of the bottom plate (22) to support and move the bottom plate (22); the mechanism bracket (21) is vertically installed at the side of the upper surface of the bottom plate (22); the two wings (1) are horizontally symmetrically installed below the mechanism bracket (21); the root upper surfaces of the two wings (1) are installed on the top of the mechanism bracket (21) through a U-shaped frame; two groups of loading mechanisms are symmetrically installed on the upper surface of the bottom plate (22); each group of loading mechanisms corresponds to one wing (1); each group of loading mechanisms is connected to the corresponding wing (1) to achieve triaxial dynamic loading of the corresponding wing (1).

2. A folding wing dynamic loading device according to claim 1, characterized in that: The loading mechanism comprises a linear electric cylinder (33), a rocker arm (36), a rocker arm support (37), a lateral loading motor (39), a wing fixture (31), a force measurement component (32), a wing tip fixture (34), a displacement sensor (35) and an angle encoder (38); The lateral loading motor (39) is mounted on the upper surface of the bottom plate (22); the output shaft of the lateral loading motor (39) is vertically upward; the rocker arm (36) is a horizontal plate-shaped structure; one end of the rocker arm (36) is sleeved on the output shaft of the lateral loading motor (39); the angle encoder (38) is arranged at the top of the lateral loading motor (39); the rocker arm support (37) is vertically arranged at the bottom of the rocker arm (36), and the top of the rocker arm support (37) is in contact with the lower surface of the rocker arm (36), and the bottom of the rocker arm support (37) is in contact with the lower surface of the rocker arm (36). The wing (1) is in contact with the upper surface of the base plate (22); the linear electric cylinder (33) is vertically mounted at the middle position of the upper surface of the rocker arm (36); the force measuring assembly (32) is mounted at the top output end of the linear electric cylinder (33); the wing fixture (31) is mounted on the top of the force measuring assembly (32), and the wing fixture (31) clamps the middle part of the corresponding wing (1); the wing tip fixture (34) is clamped at the wing tip position of the corresponding wing (1); the wing tip fixture (34) is connected to the end of the rocker arm (36) through a vertically arranged displacement sensor (35).

3. A folding wing dynamic loading device according to claim 2, characterized in that: The output shaft of the linear electric cylinder (33) is extended to realize loading of the corresponding wing (1) in the vertical direction; and the force measurement component (32) is used to realize measurement of the three-axis loading force.

4. A folding wing dynamic loading device according to claim 3, characterized in that: In the initial state, the two wings (1) are closed; during the process of the wings (1) rotating and opening, the rocker arm (36) is driven to rotate synchronously by a transverse loading motor (39); during the synchronous rotation of the wings (1) and the rocker arm (36), there is a synchronization error, generating a horizontal force along the axis direction of the wings (1) and a horizontal force perpendicular to the axis direction of the wings (1).

5. A folding wing dynamic loading device according to claim 4, characterized in that: The rotation angle of the rocker arm (36) is monitored by an angle encoder (38); and the rotation position of the rocker arm (36) and the wing (1) is monitored by a displacement sensor (35).

6. A folding wing dynamic loading device according to claim 1, characterized in that: The top of the rocker arm support (37) is fixedly connected to the lower surface of the rocker arm (36); the bottom of the rocker arm support (37) is a universal wheel structure; the rocker arm support (37) can follow the rocker arm (36); the rocker arm support (37) is arranged at a corresponding position below the linear electric cylinder (33).

7. A folding wing dynamic loading device according to claim 5, characterized in that: The force measurement assembly (32) comprises a normal force sensor (321), a normal sensor mounting flange (322), a tangential force sensor (323), a tangential force sensor mounting flange (324), a flexible beam (325) and a flexible beam mounting nut (326); The upper end of the normal force sensor (321) is connected to the wing clamp (31) by screws, and the lower end of the normal force sensor (321) is mounted on the normal sensor mounting flange (322) by screws; the normal sensor mounting flange (322) is an inverted L-shaped structure; the flexible beam (325) is arranged horizontally; the positioning section at the front end of the flexible beam (325) passes through the positioning hole on the vertical side wall of the normal sensor mounting flange (322) and is tightened by the flexible beam mounting nut (326); the rear end of the flexible beam (325) is tightened in the threaded hole of the tangential force sensor (323); the tangential force sensor (323) is mounted on the tangential force sensor mounting flange (324) by screws; and the tangential force sensor mounting flange (324) is mounted on the output end of the linear electric cylinder (33) by nuts.

8. A folding wing dynamic loading device according to claim 7, characterized in that: The flexible beam (325) comprises a rear end threaded section (3251), a normal flexible hinge (3252) and a front end threaded section (3253); wherein the normal flexible hinge (3252) is a rectangular parallelepiped structure arranged axially and horizontally; the rear end threaded section (3251) is coaxially mounted at the axial rear end of the normal flexible hinge (3252); the front end threaded section (3253) is coaxially mounted at the axial front end of the normal flexible hinge (3252); the rear end threaded section (3251) is screwed into the threaded hole of the tangential force sensor (323); the front end threaded section (3253) passes through the vertical side wall of the flexible beam mounting nut (326); the plane where the normal flexible hinge (3252) is located is parallel to the horizontal reference plane; the mounting direction of the flexible beam (325) is adjusted by installing an adjustment gasket between the rear end threaded section (3251) and the tangential force sensor (323).

9. A folding wing dynamic loading device according to claim 8, characterized in that: The loading process of the loading device is: The wing (1) rotates open, and the feedback signal of the rotation position of the wing (1) is used as the input of the lateral loading motor (39); after the angle encoder (38) detects that the lateral loading motor (39) has reached the position, the control mode is automatically switched to force control; the lateral loading motor (39) continues to move, and when the composite load sequence of the horizontal force value of the wing (1) fed back by the force measurement component (32) requires, the loading motor (39) maintains the current position; while the lateral loading motor (39) moves, the linear electric cylinder (33) moves upward, and when the composite load sequence of the normal force value of the wing (1) fed back by the force measurement component (32) requires, the linear electric cylinder (33) maintains the current position; after the horizontal force and the normal force of the wing (1) are loaded, the above cycle is repeated to continue loading the load of the wing (1) at the next position.

10. A folding wing dynamic loading device according to claim 9, characterized in that: The control period of the transverse loading motor (39) is 5 milliseconds to ensure the continuity of the loading process.

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