A passive servo loading device for deformable wings and its working method

Abstract

This invention belongs to the field of aerospace equipment, and specifically relates to a passive servo loading device and its working method for deformable wings. The loading device includes: a support frame, a test wing support, a test wing surface, a high-pressure cylinder assembly, and multiple passive loading modules. The test wing support is located on both sides of the support frame, and the test wing surface is mounted on the support. The multiple passive loading modules are mounted on the support frame, and are used to adjust the tension of the steel wire ropes. Each passive loading module includes a connecting assembly, a pulley assembly, a loading assembly, a measuring assembly, and a load-bearing square tube. The connecting assembly is located on the test wing surface and is connected to multiple steel wire ropes. The pulley assembly and the load-bearing square tube are staggered on the support frame. This servo loading device adopts a modular design, with single parts, a simple structure, good interchangeability, convenient installation, and low cost, reducing the preparation cycle and also reducing the risk.

Description

Technical Field

[0001] This invention belongs to the field of aerospace equipment, and in particular relates to a passive servo loading device for deformable wings and its working method. Background Technology

[0002] Folding-wing aircraft can adaptively transform according to the flight environment and combat mission requirements, enabling versatile flight paths, altitudes, and speeds to maximize flight performance. The performance of the wing structure directly impacts the overall aircraft performance, making performance testing a crucial part of the aircraft design and manufacturing process.

[0003] Airfoil structures include both structural surfaces such as stabilizers and movable surfaces such as flaps, slats, and ailerons. For structural surfaces, it is essential to test their load-bearing capacity; for movable surfaces, in addition to testing their load-bearing capacity, it is also necessary to test the mechanism's movement capability and reliability within the designed flight envelope.

[0004] In general, these tests all require the wing surface to be under certain flight loads. Therefore, these tests can be conducted through wind tunnel experiments, test flights, etc. However, these methods are costly, have long preparation cycles, and flight tests also have certain risks. Summary of the Invention

[0005] Therefore, the technical problem to be solved by the present invention is to overcome the problems of high testing costs, long preparation cycles, and certain dangers in flight testing in the prior art, thereby providing a passive servo loading device and working method for deformable wings.

[0006] To address the aforementioned technical problems, this invention provides a passive servo loading device for deformable wings, comprising: a support frame, a test wing support, a test wing surface, a high-pressure cylinder assembly, and multiple passive loading modules; the test wing support is located on both sides of the support frame, and a test wing surface is provided on the test wing support; the multiple passive loading modules are located on the support frame, and the passive loading modules are used to adjust the tension of the steel wire ropes; each passive loading module includes a connecting assembly, a pulley assembly, a loading assembly, a measuring assembly, and a load-bearing square tube; the connecting assembly is located on the test wing surface and is connected to the multiple steel wire ropes respectively; the pulley assembly and the load-bearing square tube are offset on the support frame; the loading assembly and the measuring assembly are both located inside the load-bearing square tube; the steel wire rope passes through the pulley assembly and is connected to the loading assembly; the high-pressure cylinder assembly is located on the support frame and the test wing support, and the high-pressure cylinder assembly is used to drive the test wing surface to rotate.

[0007] Furthermore, the connecting assembly includes a wing-rope connector, two short pins, two tie rods, two single-ear support shafts, a double-ear support shaft, and a long pin. The wing-rope connector is disposed on the test wing surface. One end of the wing-rope connector is provided with two tie rods, which are respectively connected to the wing-rope connector via two short pins. One single-ear support shaft is disposed inside the wing-rope connector, and the other single-ear support shaft is disposed at the end of the two tie rods away from the wing-rope connector. The double-ear support shaft is disposed at the other end of the wing-rope connector via a long pin. The two single-ear support shafts and the double-ear support shaft are respectively connected to one end of the three steel wire ropes.

[0008] Furthermore, the pulley assembly includes two sets of pulleys, a pulley spindle, a pulley seat, a pulley seat base plate, a cable outlet clamp, an I-beam pressure plate, and an adjustable bracket; the two sets of pulleys are mounted on the pulley seat via the pulley spindle, the pulley seat is mounted on the pulley seat base plate, the pulley seat base plate is connected to the adjustable bracket, and the adjustable bracket is mounted on the support frame via the cable outlet clamp and the I-beam pressure plate.

[0009] Furthermore, the loading assembly includes an adapter plate, two loading pulley seats, a guide pulley, a loading pulley spindle, a double clamp for the wire rope, a wire rope connector, a tension spring, a tension sensor, a spherical bearing, a lead screw, a lead screw nut, and a lead screw nut support. The adapter plate is located on the inner wall of the supporting square tube. The pulley spindle passes through the guide pulley and is located on the loading pulley seat. The loading pulley seat is located on the adapter plate. The other end of the wire rope passes through the guide pulley. The wire rope is connected to the double clamp for the wire rope. The double clamp for the wire rope is connected to one end of the wire rope connector. The other end of the wire rope connector is connected to the tension spring. The tension spring is connected to the tension sensor. The tension sensor is connected to the lead screw through the spherical bearing. The lead screw and the lead screw nut are screwed together. The lead screw nut is located on the lead screw nut support. The lead screw nut support is connected to the supporting square tube.

[0010] Furthermore, the measuring component includes an optical axis, a wire displacement sensor, a wire displacement sensor base, a flange linear bearing, an L-shaped connector, and an open-type retaining ring; the wire displacement sensor is connected to the wire displacement sensor base, the wire displacement sensor base is mounted on the lead screw nut support, one end of the wire displacement sensor is connected to the L-shaped connector, the other end of the L-shaped connector is connected to the lead screw, the optical axis passes through the L-shaped connector and is fixed on the lead screw nut support via the flange linear bearing, is connected to the L-shaped connector, and is locked by the retaining ring, and the flange linear bearing is mounted on the lead screw nut support.

[0011] Furthermore, the high-pressure cylinder assembly includes a pressurized air tank, a cylinder assembly, and a damper assembly. The pressurized air tank is located on one side of the support frame and connected to the cylinder assembly. The cylinder assembly and the damper assembly are located on the test wing support.

[0012] Furthermore, the cylinder assembly includes an encoder, an encoder mount, an encoder coupling, an angle measuring adapter, a cylinder mount, a cylinder, a column force sensor, a wire encoder mount, and a wire encoder; the cylinder mount is mounted on the test wing support, the cylinder is mounted on the cylinder mount, the extended end of the cylinder is connected to the column force sensor, the other end of the column force sensor is connected to the test wing, the encoder is connected to one side of the test wing support via the encoder mount, the encoder is connected to one end of the encoder coupling, the other end of the encoder coupling is connected to the angle measuring adapter, and the encoder coupling angle measuring adapter is connected to the test wing.

[0013] Furthermore, the damper assembly includes a hydraulic damper, a column force sensor, a fisheye connector, and a damper mounting base; the test wing is connected to one end of the hydraulic damper, the other end of the hydraulic damper is connected to the column force sensor, and is connected to the damper mounting base via the fisheye connector.

[0014] Furthermore, the support frame includes an H-beam steel frame, an H-beam steel clamp, a front loading module bracket, a rear loading module bracket, and an H-beam steel pressure plate; the H-beam steel clamp is mounted on the H-beam steel frame on the front loading module bracket, and the H-beam steel clamp is used to support the pulley assembly; the rear loading module bracket is located close to the front loading module bracket and is mounted on the H-beam steel frame.

[0015] This invention also provides a working method for a passive servo loading device with a deformable wing, comprising: three steel wire ropes respectively connected to a connecting assembly and transferred to the test wing surface through the connecting assembly; each steel wire rope is led out from the loading assembly, changes direction through a pulley assembly, and connects to the connecting assembly; during the servo loading test, the preload on the steel wire ropes can be adjusted by adjusting the loading assembly or increasing the number of passive loading modules to change the magnitude and direction of the resultant force of the three steel wire ropes connected to the test wing surface, thereby simulating the changing aerodynamic loads experienced by the test wing surface during deployment.

[0016] The technical solution of this invention has the following advantages:

[0017] The present invention provides a passive servo loading device for deformable wings, comprising: a support frame, a test wing support, a test wing, a high-pressure cylinder assembly, and multiple passive loading modules; the test wing support is disposed on both sides of the support frame, and a test wing is provided on the test wing support; the multiple passive loading modules are disposed on the support frame, and the passive loading modules are used to adjust the tension of the steel wire ropes; each passive loading module includes a connecting assembly, a pulley assembly, a loading assembly, a measuring assembly, and a bearing square tube; the connecting assembly is disposed on the test wing and is connected to the multiple steel wire ropes respectively; the pulley assembly and the bearing square tube are offset on the support frame; the loading assembly and the measuring assembly are both disposed inside the bearing square tube; the steel wire rope passes through the pulley assembly and is connected to the loading assembly; the high-pressure cylinder assembly is disposed on the support frame and the test wing support, and the high-pressure cylinder assembly is used to drive the test wing to rotate.

[0018] By placing test wing supports on both sides of the support frame, the stability of the test wing is ensured. A passive loading module is installed on the support frame to adjust the tension of the wire rope. The connecting assembly connects to the test wing and the wire rope; the pulley assembly changes the direction of the wire rope; the loading assembly adjusts the magnitude and direction of the resultant force of the wire rope; and the measuring assembly measures the tension. A high-pressure cylinder assembly then drives the test wing to rotate, thus completing the follow-up loading test of the test wing.

[0019] This passive servo loading device for deformable wings adjusts the tension of the steel wire rope by using a loading component to traction it, and adjusts the direction of the tension by positioning pulley components. This allows for various torque simulation effects around the test wing's axis of rotation. This design provides a large range of adjustment for load strength and direction, resulting in more comprehensive load environment simulation. Furthermore, the loading component and its components individually change the magnitude and direction of the force on each steel wire rope. The principle is simple and controllable. Simultaneously, this servo loading device adopts a modular design, with single components, a simple structure, good interchangeability, convenient installation, and low cost, reducing preparation time and risk.

[0020] The summary section is provided to present the chosen concepts in a simplified form, which will be further described in the detailed description below. The summary section is not intended to identify essential or necessary features of this disclosure, nor is it intended to limit the scope of this disclosure. Attached Figure Description

[0021] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0022] Figure 1 A schematic diagram of the structure of the passive servo loading device for deformable wings provided by the present invention;

[0023] Figure 2 A schematic diagram of the test wing surface support for the passive servo loading device for deformable wings provided by the present invention;

[0024] Figure 3 A schematic diagram of the support frame of the passive servo loading device for deformable wings provided by the present invention;

[0025] Figure 4 A schematic diagram of the passive loading module of the deformable wing passive follow-up loading device provided by the present invention;

[0026] Figure 5 A schematic diagram of the connection assembly of the deformable wing passive follow-up loading device provided by the present invention;

[0027] Figure 6 A perspective view of the connecting components of the deformable wing passive follow-up loading device provided by the present invention;

[0028] Figure 7 A schematic diagram of the pulley assembly of the passive follow-up loading device for deformable wings provided by the present invention;

[0029] Figure 8 A schematic diagram of the loading component of the passive servo loading device for deformable wings provided by the present invention;

[0030] Figure 9 A schematic diagram of the measurement component of the passive servo loading device for deformable wings provided by the present invention;

[0031] Figure 10 A schematic diagram of the high-pressure cylinder assembly of the passive servo loading device for deformable wings provided by the present invention;

[0032] Figure 11 A schematic diagram of the cylinder assembly of the passive servo loading device for deformable wings provided by the present invention;

[0033] Figure 12 A schematic diagram of the damper assembly of the passive follow-up loading device for deformable wings provided by the present invention.

[0034] Explanation of reference numerals in the attached figures:

[0035] 1. Support frame; 2. Test wing support; 3. Test wing; 4. High-pressure cylinder assembly; 5. Passive loading module; 6. Steel wire rope; 7. H-beam support; 8. Fixed connection plate; 9. H-beam clamp; 10. Front loading module bracket; 11. Rear loading module bracket; 12. H-beam pressure plate; 13. Connecting assembly; 14. Pulley assembly; 15. Loading assembly; 16. Measuring assembly; 17. Bearing square tube; 8. Wing-rope connector; 19. Short pin; 20. Tie rod; 21. Single-ear support shaft; 22. Double-ear support shaft; 23. Long pin; 24. Copper sleeve; 25. Pulley; 26. Pulley spindle; 27. Pulley seat; 28. Pulley seat base plate; 29. ​​Cable exit clamp; 30. I-beam pressure plate; 31. Adjustable bracket; 32. Adapter plate; 33. Loading pulley seat; 34. Guide pulley; 35. Loading pulley spindle 36. Wire rope double clamp; 37. Pin shaft; 38. Wire rope connector; 39. Tension spring; 40. Tension sensor; 41. Spherical bearing; 42. Lead screw; 43. Lead screw nut; 44. Lead screw nut support; 45. Optical shaft; 46. Wire displacement sensor; 47. Wire displacement sensor base; 48. Flange linear bearing; 49. L-type connector; 50. Open-type retaining ring; 51. Shaft snap ring; 52. Pressurized air tank; 53. Cylinder assembly; 54. Damper assembly; 55. Encoder; 56. Encoder mounting base; 57. Encoder coupling; 58. Angle measurement adapter; 59. Cylinder mounting base; 60. Cylinder; 61. Column force sensor; 62. Wire encoder mounting base; 63. Wire encoder; 64. Hydraulic damper; 65. Column force sensor; 66. Fisheye connector; 67. Damper mounting base. Detailed Implementation

[0036] In the following description, only certain exemplary embodiments are briefly described. As those skilled in the art will recognize, the described embodiments can be modified in various ways without departing from the spirit or scope of this disclosure. Therefore, the drawings and description are to be considered exemplary in nature and not restrictive.

[0037] In the description of this disclosure, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing this disclosure and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this disclosure. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the stated features. In the description of this disclosure, "a plurality of" means two or more, unless otherwise explicitly specified.

[0038] In the description of this disclosure, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "joint" should be interpreted broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections, electrical connections, or connections that allow for communication; they can refer to direct connections or indirect connections through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this disclosure according to the specific circumstances.

[0039] In this disclosure, unless otherwise expressly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0040] The following disclosure provides numerous different embodiments or examples for implementing various structures of this disclosure. To simplify the disclosure, specific examples of components and arrangements are described below. These are merely examples and are not intended to limit the scope of this disclosure. Furthermore, reference numerals and / or letters may be repeated in different examples; such repetition is for simplification and clarity and does not in itself indicate a relationship between the various embodiments and / or arrangements discussed. In addition, various specific examples of processes and materials are provided in this disclosure, but those skilled in the art will recognize the application of other processes and / or the use of other materials.

[0041] The preferred embodiments of this disclosure are described below with reference to the accompanying drawings. It should be understood that the preferred embodiments described herein are for illustration and explanation only and are not intended to limit this disclosure.

[0042] Please see Figures 1 to 12 As shown, the present invention provides a passive follow-up loading device for deformable wings, comprising: a support frame 1, a test wing surface support 2, a test wing surface 3, a high-pressure cylinder assembly 4, and multiple passive loading modules 5; the test wing surface support 2 is disposed on both sides of the support frame 1, and the test wing surface 3 is provided on the test wing surface support 2; the multiple passive loading modules 5 are disposed on the support frame 1, and the passive loading modules 5 are used to adjust the tension of the steel wire rope 6; each passive loading module 5 includes a connecting assembly 13, a pulley assembly 14, a loading assembly 15, and a measuring assembly 1. 6. A supporting square tube 17, a connecting assembly 13 is disposed on the test wing surface 3, the connecting assembly 13 is connected to a plurality of steel wire ropes 6 respectively, a pulley assembly 14 and a supporting square tube 17 are offsetly disposed on the support frame 1, a loading assembly 15 and a measuring assembly 16 are both disposed inside the supporting square tube 17, the steel wire ropes 6 pass through the pulley assembly 14 and are connected to the loading assembly 15; a high-pressure cylinder assembly 4 is disposed on the support frame 1 and the test wing surface bracket 2, the high-pressure cylinder assembly 4 is used to drive the test wing surface 3 to rotate.

[0043] By placing the test wing support 2 on both sides of the support frame 1, and simultaneously supporting the test wing 3, the stability of the test wing 3 is ensured. A passive loading module 5 is installed on the support frame 1 to adjust the tension of the wire rope 6. The connecting assembly 13 connects to the test wing 3 and the wire rope 6, the pulley assembly 14 can change the direction of the wire rope 6, the loading assembly 15 is used to adjust the magnitude and direction of the resultant force of the wire rope 6, and the measuring assembly 16 is used to measure the magnitude of the tension. The high-pressure cylinder assembly 4 then drives the test wing 3 to rotate, thereby completing the follow-up loading test of the test wing 3.

[0044] This passive servo loading device for deformable wings adjusts the tension of the steel wire rope 6 by using the loading component 15 and the position of the pulley assembly 14 to adjust the direction of the tension in the steel wire rope 6. This allows for various torque simulation effects around the test wing's axis of rotation. This design provides a large range of adjustment for load strength and direction, resulting in a more comprehensive simulation of the load environment. Furthermore, the loading component 15 and its components can be used to change the magnitude and direction of the force on each steel wire rope 6. The principle is simple and control is convenient. Simultaneously, this servo loading device adopts a modular design, with single components, a simple structure, good interchangeability, convenient installation, and low cost, reducing the preparation period and also lowering the risk.

[0045] The passive loading module 5 consists of three sets, two of which are located on one side of the support frame 1, and the other on the other side. The three sets of passive loading modules 5 are connected to three steel wire ropes 6.

[0046] In some alternative embodiments, the connecting assembly 13 includes a wing-rope connector 18, two short pins 19, two tie rods 20, two single-ear support pins 21, a double-ear support pin 22, a long pin 23, and a copper sleeve 24.

[0047] The wing-rope connector 18 is bolted to the test wing surface 3. One end of the wing-rope connector 18 is provided with two pull rods 20. The two pull rods 20 are respectively connected to the wing-rope connector 18 through two short pins 19. One single-ear support shaft 21 is located inside the wing-rope connector 18, and the other single-ear support shaft 21 is located at the end of the two pull rods away from the wing-rope connector 18. The double-ear support shaft 22 is located at the other end of the wing-rope connector 18 through a long pin 23. The two single-ear support shafts 21 and the double-ear support shaft 22 are respectively connected to one end of the three steel wire ropes 6.

[0048] The copper sleeve 24 is fitted onto the short pin 19 and inserted into the pull rod 20 and the wing-rope connector 18; at the same time, the copper sleeve 24 is also fitted onto the long pin 23 and inserted into the wing-rope connector 18 and the double-ear support shaft 22.

[0049] In some optional embodiments, the pulley assembly 14 includes two sets of pulleys 25, a pulley spindle 26, a pulley seat 27, a pulley seat base plate 28, a cable outlet clamp 29, an I-beam pressure plate 30, and an adjustable bracket 31;

[0050] Specifically, two deep groove ball bearings are respectively installed in two sets of pulleys 25, passing through the pulley spindle 26. One end of the deep groove ball bearing abuts against the pulley spindle 26, and the other end is fixed by a circlip 51. Then, the two sets of pulleys 25 are set on the pulley seat 27 through the pulley spindle 26. The pulley seat 27 is set on the pulley seat base plate 28. The pulley seat base plate 28 is connected to the adjustable bracket 31. The adjustable bracket 31 is set on the support frame 1 through the cable end clamp 29 and the I-beam pressure plate 30.

[0051] In some optional embodiments, the loading assembly 15 includes an adapter plate 32, two guide pulleys 34, a loading pulley spindle 35, a wire rope double clamp 36, a wire rope connector 38, a tension spring 39, a tension sensor 40, a joint bearing 41, a lead screw 42, a lead nut 43, and a lead screw nut support 44.

[0052] The adapter plate 32 is disposed on the inner wall of the bearing square tube 17. The pulley spindle 26 passes through the guide pulley 34 and is disposed on the loading pulley seat 33. The loading pulley seat 33 is disposed on the adapter plate 32. The other end of the wire rope 6 passes through the guide pulley 34. The wire rope 6 is connected to the wire rope double clamp 36. The wire rope double clamp 36 is connected to one end of the wire rope connector 38. The other end of the wire rope connector 38 is connected to one end of the tension spring 39. The other end of the tension spring 39 is connected to the connecting nut. The connecting nut is connected to the tension sensor 40 by threads. The tension sensor 40 is connected to the lead screw 42 by the joint bearing 41. The lead screw 42 is screwed with the lead screw nut 43. The lead screw nut 43 is disposed on the lead screw nut support 44. The lead screw nut support 44 is connected to the bearing square tube 17, thereby completing the fixed installation of the loading assembly 15 inside the bearing square tube 17. The tension spring 39 is used to pull the steel wire rope 6, which in turn pulls the test wing surface 3 to simulate the aerodynamic load on the wing surface.

[0053] The deep groove ball bearing is installed in the guide pulley 34 and is mounted on the pulley seat 27 through the pulley spindle 26.

[0054] In some optional embodiments, the measuring component 16 includes an optical axis 45, a wire displacement sensor 46, a wire displacement sensor base 47, a flange linear bearing 48, an L-shaped connector 49, and an open-type retaining ring 50. The wire displacement sensor 46 is bolted to the wire displacement sensor base 47, and the wire displacement sensor base 47 is bolted to the lead screw nut support 44. One end of the wire displacement sensor 46 is threaded to the L-shaped connector 49, and the other end of the L-shaped connector 49 is connected to the lead screw 42 and secured with a snap ring. The optical axis 45 passes through the L-shaped connector 49 and the flange linear bearing 48 and is fixed to the lead screw nut support 44, connected to the L-shaped connector 49, and locked by the retaining ring. The flange linear bearing 48 is bolted to the lead screw nut support 44. After fixing, it can measure the displacement of the lead screw 42 as the pull rope is stretched.

[0055] In some optional embodiments, the high-pressure cylinder assembly 4 includes a pressurized gas storage tank 52, a cylinder assembly 53, and a damper assembly 54. The pressurized gas storage tank 52 is located on one side of the support frame 1 and connected to the cylinder assembly 53. The cylinder assembly 53 and the damper assembly 54 are located on the test wing support 2, thus completing the connection of the high-pressure cylinder assembly 4 and enabling the transmission of high-pressure gas in the gas cylinder.

[0056] Among them, there are two sets of cylinder assemblies 53, which are symmetrically arranged on the test wing support 2.

[0057] Specifically, the cylinder assembly 53 includes an encoder 55, an encoder mount 56, an encoder coupling 57, an angle measuring adapter 58, a cylinder mount 59, a cylinder 60, a column force sensor 61, a wire encoder mount 62, and a wire encoder 63.

[0058] The cylinder mounting base 59 is bolted to the test wing support 2. The cylinder 60 is mounted on the cylinder mounting base 59. The extended end of the cylinder 60 is threadedly connected to the column force sensor 61. The other end of the column force sensor 61 is connected to the rotating shaft of the test wing 3. The encoder 55 is connected to one side of the test wing support 2 via the encoder mounting base 56. The encoder 55 is connected to one end of the encoder coupling 57. The other end of the encoder coupling 57 is connected to the angle measuring adapter 58. The encoder coupling 57 and the angle measuring adapter 58 are connected to the rotating shaft of the test wing 3.

[0059] A high-pressure cylinder 60 is arranged at the test wing drive position, and the high-pressure cylinder 60 is used as the drive source for pyrotechnic equivalent loading.

[0060] In some optional embodiments, the damper assembly 54 includes a hydraulic damper 64, a column force sensor 61, a fisheye connector 66, and a damper mounting base 67; the test wing 3 is connected to one end of the hydraulic damper 64, the other end of the hydraulic damper 64 is connected to the column force sensor 61, and is connected to the damper mounting base 67 via the fisheye connector 66.

[0061] In some optional embodiments, the support frame 1 includes an H-beam steel frame, six H-beam steel plates 9, three front loading module brackets 10, three rear loading module brackets 11, and twelve H-beam steel pressure plates 12.

[0062] The H-shaped steel clamp 9 is mounted on the H-shaped steel frame at the front loading module bracket 10. The H-shaped steel clamp 9 is used to support the pulley assembly 14. The rear loading module bracket 11 is located close to the front loading module bracket 10 and is mounted on the H-shaped steel frame.

[0063] Two identical H-beam clamps, each 9 points long, are fixed and clamped to the left and right sides of the H-beam frame and the two middle vertical beams with bolts and nuts; the position and number can be designed according to the required simulated torque.

[0064] Two H-beam steel plates 9 are used to support a set of pulley assemblies 14. A front loading module bracket 10 and two H-beam steel pressure plates 12 are bolted to the left and right sides of the H-beam steel frame and one of the two middle vertical beams. The rear loading module bracket 11 is installed next to the front loading module bracket 10 on the left and right sides of the H-beam steel frame and on the outer vertical beam, forming a support frame 1 for supporting the remaining components.

[0065] In some optional embodiments, the test wing support 2 includes: two H-shaped steel supports 7 and a fixed connecting plate 8. The H-shaped steel supports 7 are provided with two sets of equally spaced holes, and the fixed connecting plate 8 is provided with a series of corresponding holes for connecting to the test wing 3 by screws and bolts. The H-shaped steel supports 7 are symmetrically connected to the fixed connecting plate 8 to form the test wing support 2.

[0066] The present invention also provides a working method for using the aforementioned deformable wing passive follow-up loading device, comprising:

[0067] Three steel wire ropes 6 are respectively connected to the connecting assembly 13 and transferred to the test wing surface 3 through the connecting assembly 13. Each steel wire rope 6 is led out from the loading assembly 15, changes direction through the pulley assembly 14, and is connected to the connecting assembly 13.

[0068] During the follow-up loading test, the preload on the wire rope 6 can be adjusted by adjusting the loading component 15 or increasing the number of passive loading modules 5, thereby changing the magnitude and direction of the resultant force of the three wire ropes 6 connected to the test wing 3, and simulating the changing aerodynamic loads experienced by the test wing 3 during deployment.

[0069] The working method of this deformable wing passive follow-up loading device is as follows: three steel wire ropes 6 are connected to the connecting assembly 13 via a pulley assembly 14 composed of pulleys 25, and then transferred to the test wing surface 3 via the connecting assembly 13. Each steel wire rope 6 is led out from the steel wire rope connector 38 at one end of the tension spring 39, changes direction after passing through the guide pulley 34, passes through the pulley assembly 14 below the adjustable bracket 31 and connects to the single-ear support shaft 21 and the double-ear support shaft 22, thereby connecting to the connecting assembly 13. The connecting assembly 13 is fixed to the test wing surface 3, realizing the connection between the steel wire rope 6, the test wing surface 3 and the loading assembly 15.

[0070] During the follow-up loading test, the tension of the tension spring 39 can be changed by rotating the lead screw 42, thereby adjusting the preload on the wire rope 6 or increasing the number of passive loading modules 5, ultimately changing the magnitude and direction of the resultant force of the wire rope 6 connected to the test wing 3, simulating the changing aerodynamic loads experienced by the test wing 3 during deployment.

[0071] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.

Claims

1. A passive servo loading device for deformable wings, characterized in that, include: Support frame (1), test wing support (2), test wing (3), high-pressure cylinder assembly (4), multiple passive loading modules (5); The test wing support (2) is located on both sides of the support frame (1), and the test wing (3) is provided on the test wing support (2). Multiple passive loading modules (5) are located on the support frame (1). The passive loading modules (5) are used to adjust the tension of the wire rope (6). The passive loading module (5) includes a connecting component (13), a pulley component (14), a loading component (15), a measuring component (16), and a load-bearing square tube (17). The connecting component (13) is located on the test wing surface (3). The connecting component (13) is connected to multiple steel wire ropes (6). The pulley component (14) and the load-bearing square tube (17) are offset on the support frame (1). The loading component (15) and the measuring component (16) are both located inside the load-bearing square tube (17). The steel wire rope (6) passes through the pulley component (14) and is connected to the loading component (15). The high-pressure cylinder assembly (4) is mounted on the support frame (1) and the test wing support (2). The high-pressure cylinder assembly (4) is used to drive the test wing (3) to rotate. The connecting assembly (13) includes a wing-rope connector (18), two short pins (19), two tie rods (20), two single-ear support pins (21), a double-ear support pin (22), and a long pin (23). The wing-rope connector (18) is located on the test wing surface (3). One end of the wing-rope connector (18) is provided with two pull rods (20). The two pull rods (20) are connected to the wing-rope connector (18) through two short pins (19). One single-ear support shaft (21) is located inside the wing-rope connector (18). Another single-ear support shaft (21) is located at the end of the two pull rods (20) away from the wing-rope connector (18). The double-ear support shaft (22) is located at the other end of the wing-rope connector (18) through a long pin (23). The two single-ear support shafts (21) and the double-ear support shaft (22) are respectively connected to one end of three steel wire ropes (6).

2. The passive servo loading device for deformable wings according to claim 1, characterized in that, The pulley assembly (14) includes two sets of pulleys (25), a pulley spindle (26), a pulley seat (27), a pulley seat base plate (28), a cable outlet clamp (29), an I-beam pressure plate (30), and an adjustable bracket (31). The two sets of pulleys (25) are mounted on the pulley seat (27) via the pulley spindle (26). The pulley seat (27) is mounted on the pulley seat base plate (28). The pulley seat base plate (28) is connected to the adjustable bracket (31). The adjustable bracket (31) is mounted on the support frame (1) via the cable outlet clamp (29) and the I-beam pressure plate (30).

3. The passive servo loading device for deformable wings according to claim 2, characterized in that, The loading assembly (15) includes an adapter plate (32), two loading pulley seats (33), a guide pulley (34), a loading pulley spindle (35), a wire rope double clamp (36), a wire rope connector (38), a tension spring (39), a tension sensor (40), a spherical bearing (41), a lead screw (42), a lead nut (43), and a lead screw nut support (44). The adapter plate (32) is located on the inner wall of the load-bearing square tube (17). The pulley spindle (26) passes through the guide pulley (34) and is located on the loading pulley seat (33). The loading pulley seat (33) is located on the adapter plate (32). The other end of the wire rope (6) passes through the guide pulley (34). The wire rope (6) is connected to the wire rope double clamp (36). The wire rope double clamp (36) is connected to one end of the wire rope connector (38). The other end of the wire rope connector (38) is connected to the tension spring (39). The tension spring (39) is connected to the tension sensor (40). The tension sensor (40) is connected to the lead screw (42) through the joint bearing (41). The lead screw (42) is screwed with the lead nut (43). The lead nut (43) is located on the lead screw nut support (44). The lead screw nut support (44) is connected to the bearing square tube (17).

4. The passive servo loading device for deformable wings according to claim 3, characterized in that, The measuring component (16) includes an optical axis (45), a wire displacement sensor (46), a wire displacement sensor base (47), a flange linear bearing (48), an L-shaped connector (49), and an open-type retaining ring (50). The wire displacement sensor (46) is connected to the wire displacement sensor base (47), which is located on the screw nut support (44). The wire displacement sensor (46) is connected to one end of the L-shaped connector (49), and the other end of the L-shaped connector (49) is connected to the screw (42). The optical axis (45) passes through the L-shaped connector (49) and the flange linear bearing (48) and is fixed on the screw nut support (44). It is connected to the L-shaped connector (49) and locked by the retaining ring. The flange linear bearing (48) is located on the screw nut support (44).

5. A passive servo loading device for deformable wings according to any one of claims 1-4, characterized in that, The high-pressure cylinder assembly (4) includes a pressurized air tank (52), a cylinder assembly (53), and a damper assembly (54). The pressurized air tank (52) is located on one side of the support frame (1) and connected to the cylinder assembly (53). The cylinder assembly (53) and the damper assembly (54) are located on the test wing support (2).

6. The passive servo loading device for deformable wings according to claim 5, characterized in that, The cylinder assembly (53) includes an encoder (55), an encoder mount (56), an encoder coupling (57), an angle measuring adapter (58), a cylinder mount (59), a cylinder (60), a column force sensor (61), a wire encoder (63) (55) mount, and a wire encoder (63) (55); the cylinder mount (59) is mounted on the test wing support (2), and the cylinder (60) is mounted on the cylinder mount (59). The extension of the cylinder (60) The output end is connected to the column force sensor (61), the other end of the column force sensor (61) is connected to the test wing surface (3), the encoder (55) is connected to one side of the test wing surface bracket (2) through the encoder mounting base (56), the encoder (55) is connected to one end of the encoder coupling (57), the other end of the encoder coupling (57) is connected to the angle measuring adapter (58), and the encoder coupling (57) and the angle measuring adapter (58) are connected to the test wing surface (3).

7. The passive servo loading device for deformable wings according to claim 6, characterized in that, The damper assembly (54) includes a hydraulic damper (64), a column force sensor (61), a fisheye connector (66), and a damper mounting base (67); the test wing (3) is connected to one end of the hydraulic damper (64), the other end of the hydraulic damper (64) is connected to the column force sensor (61), and is connected to the damper mounting base (67) through the fisheye connector (66).

8. The passive servo loading device for deformable wings according to claim 1, characterized in that, The supporting frame (1) includes an H-beam frame, an H-beam clamp (9), a front loading module bracket (10), a rear loading module bracket (11), and an H-beam pressure plate (12). The H-beam steel clamp (9) is set on the H-beam steel frame at the front loading module bracket (10). The H-beam steel clamp (9) is used to support the pulley assembly (14). The rear loading module bracket (11) is set close to the front loading module bracket (10) and is set on the H-beam steel frame.

9. A method for operating the passive servo loading device for deformable wings according to any one of claims 1-8, characterized in that, include: Three steel wire ropes (6) are respectively connected to the connecting assembly (13) and transferred to the test wing surface (3) through the connecting assembly (13). Each steel wire rope (6) is led out from the loading assembly (15), changes direction through the pulley assembly (14), and is connected to the connecting assembly (13). During the follow-up loading test, the preload on the wire rope (6) can be adjusted by adjusting the loading component (15) or increasing the number of passive loading modules (5), thereby changing the magnitude and direction of the resultant force of the three wire ropes (6) connected to the test wing (3) to simulate the changing aerodynamic loads experienced by the test wing (3) during deployment.

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