Test stand for wings

Abstract

The utility model relates to a test bench for wing. The test bench for wing includes test device, and test device includes frame assembly and is located on frame assembly main part and rotor loading component, and rotor loading component includes first rotor actuating cylinder, and first rotor actuating cylinder is used for connecting frame assembly and tilt rotor, and the tilt angle of first rotor actuating cylinder is same with the tilt angle of tilt rotor, to simulate the tension of tilt rotor to wing, and first rotor actuating cylinder can be detachably connected to the different position of frame assembly, to change the tilt angle of first rotor actuating cylinder of connecting frame assembly and tilt rotor after the tilt angle change of tilt rotor. The test bench can carry out static strength test to the wing of tilt rotor eVTOL.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to a test bench for an airfoil. Background Technology

[0002] With the explosive progress of electric drive and power battery technologies, electric vertical takeoff and landing (eVTOL) aircraft, as a new type of electric aircraft, have also developed rapidly in recent years. More and more eVTOL R&D and design organizations and supporting supply chain units are emerging both domestically and internationally. The main characteristics of tiltrotor eVTOLs are: 1) Unlike traditional aircraft that use piston or turbine engines for flight power, eVTOLs mainly rely on electrically driven devices distributed throughout the fuselage to drive the rotor rotation, providing the lift and forward thrust required for flight; 2) They can take off and land vertically like helicopters, and can also cruise at high forward speeds like fixed-wing aircraft; 3) Some or all of the rotors and corresponding electric drive devices can rotate forward and backward around the tilt axis, changing the direction of the thrust provided by the rotor.

[0003] For aircraft development, safety is paramount. To ensure that eVTOL products meet airworthiness requirements, research and development units need to conduct extensive strength tests on aircraft components and the entire aircraft during the development phase to obtain structural load-bearing capacity data and verify its safety. The vast majority of these strength tests need to be conducted on ground test benches. However, existing testing techniques are mostly applied to traditional fixed-wing aircraft or helicopters; currently, there is no strength testing scheme specifically for the wing components of tiltrotor eVTOLs. Utility Model Content

[0004] Therefore, it is necessary to provide a test bench for the wings of tiltrotor electric vertical take-off and landing aircraft.

[0005] This utility model provides a test bench for an airfoil. The airfoil includes two symmetrically arranged airfoil structures. Each airfoil structure includes an airfoil body connected to the fuselage and a tilting rotor rotatably connected to the side of the airfoil body away from the fuselage. During the rotation of the tilting rotor relative to the airfoil body, the tilting angle of the tilting rotor changes accordingly. The test bench includes a test device corresponding to the airfoil structure. The test device includes: Frame components used to support the wing structure; A main loading component, disposed on the frame component, is used to apply loads to the wing body; and A rotor loading assembly, disposed on the frame assembly, is used to apply a load to the tilt rotor. The rotor loading assembly includes a first rotor actuator cylinder, which connects the frame assembly and the tilt rotor. The tilt angle of the first rotor actuator cylinder is the same as the tilt angle of the tilt rotor to simulate the pull of the tilt rotor on the wing. The first rotor actuator cylinder can be detachably connected to different positions on the frame assembly so that the tilt angle of the first rotor actuator cylinder connecting the frame assembly and the tilt rotor can change accordingly after the tilt angle of the tilt rotor changes.

[0006] In one embodiment, the rotor loading assembly further includes a second rotor actuator and a connecting rod. The connecting rod is disposed on the tilt rotor. The first rotor actuator is used to connect the frame assembly and the connecting rod. The connecting rod is perpendicular to the first rotor actuator and parallel to the axis of rotation of the tilt rotor. The second rotor actuator is used to connect the frame assembly and the end of the connecting rod. The tilt direction of the second rotor actuator is opposite to that of the first rotor actuator. There are two second rotor actuators, which are arranged in parallel and spaced apart to simulate the torque of the tilt rotor on the wing. The second rotor actuators can be detachably connected to different positions of the frame assembly so that when the connection position of the first rotor actuator with the frame assembly changes, the connection position of the second rotor actuator with the frame assembly changes accordingly.

[0007] In one embodiment, the rotor loading assembly further includes a loading joint for mounting on the tilting rotor, and the connecting rod is mounted on the loading joint.

[0008] In one embodiment, the frame assembly includes a frame base and a frame gantry. The frame base is used to support the wing, and the frame gantry is disposed on the frame base. The two vertical beams of the frame gantry are located on the front and rear sides of the wing. The first rotor actuator can be detachably connected to different positions of the frame gantry, and the second rotor actuator can be detachably connected to different positions of the frame gantry.

[0009] In one embodiment, there are multiple frame gantry gates, and in the left and right directions of the wing structure, the multiple frame gantry gates are arranged at intervals according to the rib structure positions of the wing structure. The frame gantry located at the head of the tilting rotor is a rotor gantry. The first rotor actuator can be detachably connected to different positions of the rotor gantry, and the second rotor actuator can be detachably connected to different positions of the rotor gantry.

[0010] In one embodiment, the frame assembly further includes a follower bump assembly, the follower bump assembly comprising two follower bumps detachably connected to different positions of the rotor gantry, and the two second rotor actuators being detachably connected to the two follower bumps respectively; and / or The frame assembly further includes a gantry beam extending along the arrangement direction of the plurality of frame gantry gates, the gantry beam being disposed on at least one of the frame gantry gates; and / or The rotor gantry is provided with uniformly distributed standard through holes, which allows the first rotor actuator cylinder and the standard through holes at different positions to be detachably connected to different positions of the rotor gantry, and also allows the second rotor actuator cylinder and the standard through holes at different positions to be detachably connected to different positions of the rotor gantry.

[0011] In one embodiment, the frame base, the frame gantry, the gantry beam, and the follower protrusion are all formed by splicing modular long beams, with the splicing positions of two long beams connected by bolts, and the standard through holes are evenly distributed on the long beams; and / or The frame base is provided with a clamping joint that is connected to the connecting bolts of the wing body. The wing body is fixed to the frame base by the connected connecting bolts and the clamping joint.

[0012] In one embodiment, the first rotor actuator is used to connect the frame assembly to the head of the tilt rotor, the head of the tilt rotor having a centerline parallel to the first rotor actuator, and the first rotor actuator being eccentrically disposed from the centerline.

[0013] In one embodiment, at least one of the main loading assembly and the rotor loading assembly includes a loading plate, and at least one of the main loading assembly and the rotor loading assembly includes a matching actuator, the matching actuator being parallel to the vertical direction, and the matching actuator being used to connect the frame assembly and at least one of the loading plates.

[0014] In one embodiment, the loading plate includes a lower engaging portion and an upper engaging portion, which are respectively used to abut against the lower and upper sides of the wing. After the lower engaging portion and the upper engaging portion abut against the lower and upper sides of the wing, the distance between the lower engaging portion and the upper engaging portion in the fore-and-aft direction of the wing is divided into a forward distance, a middle distance, and a rear distance, with the rear distance being greater than the middle distance to allow the movement of the wing's movable control surfaces.

[0015] In one embodiment, both the lower locking portion and the upper locking portion include an outer locking plate, an inner locking plate, and a pad disposed between the outer locking plate and the inner locking plate. The mid-distance is the distance between the inner locking plate of the lower locking portion and the inner locking plate of the upper locking portion, and the rear distance is the distance between the outer locking plate of the lower locking portion and the outer locking plate of the upper locking portion.

[0016] In one embodiment, the front spacing and the rear spacing are the same; and / or The inner clamping plate is a conformal wooden block, and the rigidity of the outer clamping plate and the pad block is greater than that of the inner clamping plate; and / or The loading plate also includes a locking screw, and in the fore-and-aft direction of the wing, the front and rear ends of the lower locking part and the upper locking part are connected by the locking screw.

[0017] In one embodiment, the main loading assembly includes at least one first main loading assembly and at least one second main loading assembly. The first main loading assembly includes one loading plate and one matching actuator cylinder. The second main loading assembly includes two loading plates, one matching actuator cylinder, and a loading lever connecting the two loading plates and one matching actuator cylinder.

[0018] In one embodiment, there are two test devices, each corresponding to one of the two wing structures of the wing, and the frame assemblies of the two test devices are connected.

[0019] In the aforementioned wing test rig, the main loading assembly applies loads to the wing fuselage, enabling the application of aerodynamic loads on the wing surface. The rotor loading assembly applies loads to the tilt rotor, enabling the application of dynamic loads on the tilt rotor. When both the main loading assembly and the rotor loading assembly operate simultaneously, the aerodynamic loads on the wing surface (achieved through loading plates) and the dynamic loads on the tilt rotor can be applied simultaneously, which better matches the stress characteristics of a tiltrotor electric vertical takeoff and landing (eVTOL) aircraft wing. Furthermore, the first rotor actuator cylinder used to apply loads to the tilt rotor can be detachably connected to different positions on the frame assembly. This allows the tilt angle between the frame assembly and the first rotor actuator cylinder to change accordingly with changes in the tilt angle of the tilt rotor, thus meeting the structural static strength testing requirements of the tilt rotor at different tilt angles. Therefore, the aforementioned wing test rig can conduct static strength tests on the wings of tiltrotor eVTOL aircraft, filling a gap in the current industry for ground strength testing schemes for such aircraft. Attached Figure Description

[0020] Various other advantages and benefits will become apparent to those skilled in the art upon reading the detailed description of the preferred embodiments below. The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of this application. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings: Figure 1 This is a schematic diagram of the structure of a test bench for an airfoil according to an embodiment of the present invention; Figure 2 This is a partial structural schematic diagram of a test bench for an airfoil according to an embodiment of the present invention; Figure 3 This is a partial structural schematic diagram of a test bench for an airfoil according to an embodiment of the present invention; Figure 4 This is a schematic diagram of four-dimensional forces on a test bench for an airfoil according to an embodiment of the present invention; Figure 5 This is a schematic diagram of the loading plate of a test bench for an airfoil according to an embodiment of the present invention; Figure 6 This is a schematic diagram of the structure of a wing testing system according to an embodiment of the present invention. Detailed Implementation

[0021] To make the above-mentioned objectives, features, and advantages of this application more apparent and understandable, the specific embodiments of this application are described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of this application. However, this application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this application. Therefore, this application is not limited to the specific embodiments disclosed below.

[0022] In the description of this application, it should be understood that, where they appear, the terms “center,” “longitudinal,” “lateral,” “length,” “width,” “thickness,” “upper,” “lower,” “front,” “rear,” “left,” “right,” “vertical,” “horizontal,” “top,” “bottom,” “inner,” “outer,” “clockwise,” “counterclockwise,” “axial,” “radial,” and “circumferential” indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this application 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. Therefore, they should not be construed as limitations on this application.

[0023] Furthermore, where applicable, 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 technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0024] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," "fixing," etc., shall be interpreted broadly. For example, they may refer to a fixed connection, a detachable connection, or an integral part; they may refer to a mechanical connection or an electrical connection; they may refer to a direct connection or an indirect connection through an intermediate medium; they may refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0025] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0026] It should be noted that, if an element is described as "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. When an element is described as "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.

[0027] like Figure 1 and Figure 2 As shown, this utility model discloses a test bench 10 for an aircraft wing. The test bench 10 is used to test the static strength of the wing 20 of a tiltrotor electric vertical takeoff and landing aircraft.

[0028] The wing 20 of the tiltrotor electric vertical takeoff and landing (eVTOL) aircraft comprises two symmetrical wing structures 22, namely the left wing 22a and the right wing 22b. Each wing structure 22 includes a wing fuselage 222 and a tiltrotor 224. The wing fuselage 222 is connected to the fuselage. The tiltrotor 224 is rotatably connected to the side of the wing fuselage 222 furthest from the fuselage. During the rotation of the tiltrotor 224 relative to the wing fuselage 222, the tilt angle of the tiltrotor 224 changes accordingly.

[0029] The wing test bench 10 includes test devices 10a corresponding to the wing structures 22, which are used to perform static strength tests on the wing structures 22. In this embodiment, there are two test devices 10a, each corresponding to one of the two wing structures 22 of the wing 20. Thus, in some tests, the wing test bench 10 can simultaneously perform static strength tests on both left and right wing structures 22 of the wing 20, thereby improving test efficiency (it is understood that in other tests, when the wing test bench 10 has two test devices 10a, only one of the two wing structures 22 can be tested). It is understood that in other embodiments, the wing test bench 10 may also include only one test device 10a.

[0030] In this embodiment, the test apparatus 10a includes a frame assembly 300, a main loading assembly 400, and a rotor loading assembly 500. The frame assembly 300 supports the wing structure 22. The main loading assembly 400 is mounted on the frame assembly 300 and applies load to the wing body 222. The rotor loading assembly 500 is mounted on the frame assembly 300 and applies load to the tilt rotor 224. The rotor loading assembly 500 includes a first rotor actuator cylinder 510. The first rotor actuator cylinder 510 connects the frame assembly 300 and the tilt rotor 224, and the tilt angle of the first rotor actuator cylinder 510 is the same as the tilt angle of the tilt rotor 224 to simulate the tension of the tilt rotor 224 on the wing structure 22. The first rotor actuator 510 can be detachably connected to different positions of the frame assembly 300 so that the tilt angle of the first rotor actuator 510 connecting the frame assembly 300 and the tilt rotor 224 can change accordingly after the tilt angle of the tilt rotor 224 changes.

[0031] In the aforementioned test rig 10 for the wing, the main loading assembly 400 is used to apply loads to the wing body 222, which can realize the application of aerodynamic loads on the wing surface 20. The rotor loading assembly 500 is used to apply loads to the tilt rotor 224, which can realize the application of dynamic loads on the tilt rotor 224. When the main loading assembly 400 and the rotor loading assembly 500 work simultaneously, the aerodynamic loads on the wing surface 20 (achieved through the loading plate 10) and the dynamic loads on the tilt rotor 224 can be applied simultaneously, which is more in line with the force characteristics of the wing 20 of a tilt rotor electric vertical take-off and landing aircraft. Furthermore, the first rotor actuator 510, used to apply load to the tilt rotor 224, can be detachably connected to different positions of the frame assembly 300. This allows the tilt angle between the frame assembly 300 and the first rotor actuator 510 to change accordingly as the tilt angle of the tilt rotor 224 changes, thus meeting the structural static strength test requirements of the tilt rotor 224 at different tilt angles. Therefore, the aforementioned wing test bench 10 can conduct static strength tests on the wing 20 of a tilt rotor electric vertical takeoff and landing aircraft, filling a gap in the current industry for ground strength testing schemes for such aircraft.

[0032] In this embodiment, the tiltrotor 224 has a head 224a and a wing 224b. The head 224a is rotatably connected to the wing body 222. The wing 224b is located on the side of the head 224a away from the wing body 222. The head 224a has a centerline a parallel to the first rotor actuator 510. The first rotor actuator 510 is used to connect the frame assembly 300 and the head 224a. This better conforms to the force characteristics of the wing 20 of a tiltrotor electric vertical takeoff and landing aircraft. It can be understood that in other embodiments, the first rotor actuator 510 can also be used to connect the frame assembly 300 and the wing 224b.

[0033] It should be noted that the front end of the nose 224a is circular, and the centerline a is a straight line passing through the center of the front end circle. When the tiltrotor 224 is in a horizontal state, that is, when the tiltrotor 224 is not tilted, the centerline a is located in the fore-and-aft direction of the wing 20. During the rotation of the tiltrotor 224 relative to the wing-body 222, the tilt angle of the tiltrotor 224 changes accordingly, that is, the tilt angle of the centerline a changes accordingly.

[0034] In this embodiment, the first rotor actuator 510 is eccentrically positioned relative to the centerline a. Thus, in a three-dimensional Cartesian coordinate system, the first rotor actuator 510 can simulate both the pulling force of the tilt rotor 224 on the wing structure 22 in one direction (the first direction) and the torque of the tilt rotor 224 on the wing structure 22 in the other two directions (the second and third directions), which better reflects the force characteristics of the wing 20 of a tilt rotor electric vertical takeoff and landing aircraft. It is understood that in other embodiments, the first rotor actuator 510 may also be collinear with the centerline a.

[0035] In this embodiment, the rotor loading assembly 500 further includes a second rotor actuator 520 and a connecting rod 530. The connecting rod 530 is mounted on the tilt rotor 224. A first rotor actuator 510 connects the frame assembly 300 to the connecting rod 510. The connecting rod 530 is perpendicular to the first rotor actuator 510 and parallel to the axis of rotation b of the tilt rotor 224 (the axis of rotation b is located in the left-right direction of the wing 20). The second rotor actuator 520 connects the frame assembly 300 to the end of the connecting rod 510, and the tilt direction of the second rotor actuator 520 is opposite to that of the first rotor actuator 510. There are two second rotor actuators 520. The two second rotor actuators 520 are arranged in parallel and spaced apart to simulate the torque exerted by the tilt rotor 224 on the wing structure 22. The second rotor actuator 520 can be detachably connected to different positions of the frame assembly 300 so that when the first rotor actuator 510 changes its connection position with the frame assembly 300, the second rotor actuator 520 changes its connection position with the frame assembly 300 accordingly.

[0036] Thus, a first rotor actuator 510 and two second rotor actuators 520 constitute a multi-dimensional force composite loading structure.

[0037] When the first rotor actuator 510 is eccentrically set with respect to the centerline a, the first rotor actuator 510 can simulate both the pulling force of the tilt rotor 224 on the wing structure 22 in a certain direction (first direction) and the torque of the tilt rotor 224 on the wing structure 22 in the other two directions (second direction and third direction). The two second rotor actuators 520 can simulate the torque of the tilt rotor 224 on the wing structure 22 in one direction (first direction) (the forces applied by the two second rotor actuators 520 are in opposite directions; one second rotor actuator 520 applies a force towards the connecting rod 530, and the other second rotor actuator 520 applies a force away from the connecting rod 530), thus achieving four-dimensional force ( Figure 4 As shown, the simulation of one pull and three torques is more consistent with the force characteristics of the wing 20 of the tiltrotor electric vertical take-off and landing aircraft, and can minimize the number of rotor actuators, simplify the structure and reduce costs.

[0038] When the first rotor actuator 510 is collinear with the centerline a, the first rotor actuator 510 can simulate the pulling force of the tilt rotor 224 on the wing structure 22 in a certain direction, and the two second rotor actuators 520 can simulate the torque of the tilt rotor 224 on the wing structure 22 in a certain direction. It can be understood that when it is necessary to apply torque in more directions, a torque loading system similar to that composed of two second rotor actuators 520 (including two parallel rotor actuators with opposite directions of the applied forces) can be added to achieve the simulation of four-dimensional forces.

[0039] In this embodiment, the rotor loading assembly 500 further includes a loading connector 540. The loading connector 540 is disposed at the head 224a of the tilt rotor 224. A connecting rod 530 is disposed on the loading connector 540. This facilitates the placement of a first rotor actuator 510 and two second rotor actuators 520 on the head 224a of the tilt rotor 224.

[0040] In this embodiment, as Figure 1 and Figure 2 As shown, the frame assembly 300 includes a frame base 310 and a frame gantry 320. The frame base 310 supports the wing structure 22. The frame gantry 320 is mounted on the frame base 310, and its two vertical beams 322 are located on the front and rear sides of the wing structure 22, respectively, meaning the wing structure 22 passes through the frame gantry 320. A first rotor actuator cylinder 510 is detachably connected to different positions of the frame gantry 320. A second rotor actuator cylinder 520 is also detachably connected to different positions of the frame gantry 320. This facilitates the detachable connection of both the first and second rotor actuator cylinders to different positions of the frame assembly 300. It is understood that in other embodiments, at least one of the first and second rotor actuator cylinders 510 may also be detachably connected to different positions of the frame base 310, thereby applying a load to the wing structure 22 from the bottom.

[0041] In this embodiment, the frame assemblies 300 of the two test devices 10a are connected. This allows the wing test rig 10 to have better overall integrity.

[0042] In this embodiment, there are multiple frame gates 320, which are arranged at intervals along the left and right directions of the wing structure 22. Specifically, in this embodiment, the multiple frame gates 320 are arranged at intervals according to the rib positions of the wing structure 22. The frame gate 320 located at the head 224a is the rotor gate 320a. The first rotor actuator cylinder 510 and the second rotor actuator cylinder 520 can be detachably connected to different positions of the rotor gate 320a. This makes it very convenient for the first rotor actuator cylinder 510 and the second rotor actuator cylinder 520 to be detachably connected to different positions of the frame assembly 300.

[0043] In this embodiment, the frame assembly 300 further includes a gantry beam 330. The gantry beam 330 extends along the arrangement direction of the plurality of frame gantry beams 320. The gantry beam 330 is disposed on at least one frame gantry beam 320. It can be understood that in other embodiments, the wing structure 22 may not pass through the frame gantry beam 320, but at least one frame gantry beam 320 may be provided on the front and rear sides of the wing structure 22 respectively. The two vertical beams 322 of the frame gantry beam 320 are arranged in the left and right directions of the wing structure 22, and the gantry beam 330 extends along the front and rear directions of the wing structure 22, with both ends connected to the two frame gantry beams 320 respectively. In this case, the first rotor actuator cylinder 510 may be detachably connected to different positions of the gantry beam 330, and the second rotor actuator cylinder 520 may also be detachably connected to different positions of the gantry beam 330.

[0044] In this embodiment, the frame assembly 300 further includes a follower protrusion group 340. The follower protrusion group 340 includes two follower protrusions 342 that can be detachably connected to different positions on the rotor gantry 320a. The two second rotor actuator cylinders 520 are detachably connected to the two follower protrusions 342 respectively. Thus, when adjusting the position of the second rotor actuator cylinder 520, the follower protrusions 342 can move together with the second rotor actuator cylinder 520, making it easier for the two second rotor actuator cylinders 520 to adjust their positions synchronously.

[0045] In this embodiment, the frame assembly 300 further includes a horizontal protrusion group 350. The horizontal protrusion group 350 includes two horizontal protrusions 352 connected to the rotor gantry 320a. When the tilt rotor 224 is in a horizontal state, the two second rotor actuator cylinders 520 are detachably connected to the two horizontal protrusions 352 respectively. When the tilt rotor 224 is in a tilting state, the two second rotor actuator cylinders 520 are detachably connected to the two follower protrusions 342 respectively. In this way, the connection method between the second rotor actuator cylinders 520 and the rotor gantry 320a can be more flexible.

[0046] In this embodiment, standard through holes are evenly distributed on the frame gantry 320, gantry beam 330, follower protrusion 342, and horizontal protrusion 352, so that the first rotor actuator cylinder 510 can be detachably connected to different positions of the frame assembly 300 through the standard through holes at different positions, and the second rotor actuator cylinder 520 can be detachably connected to different positions of the frame assembly 300 through the standard through holes at different positions. It is understood that in other embodiments, auxiliary connectors such as snap-fit ​​devices can also be used to detachably connect the first rotor actuator cylinder 510 and the second rotor actuator cylinder 520 to different positions of the frame assembly 300. In this case, the standard through holes can be omitted.

[0047] In this embodiment, the first rotor actuator 510 has a first mounting base 512. The first mounting base 512 has a first through hole. After the bolt passes through the standard through hole and the first through hole on the rotor gantry 320a, it is locked by a nut, thereby realizing the detachable connection of the first rotor actuator 510 to the rotor gantry 320a. The second rotor actuator 520 has a second mounting base 532. The second mounting base 532 has a second through hole. After the bolt passes through the standard through hole and the second through hole on the follower protrusion 342 or the horizontal protrusion 352, it is locked by a nut, thereby realizing the detachable connection of the second rotor actuator 520 to the rotor gantry 320a. Specifically, after the bolt passes through the standard through hole on the follower protrusion 342 or the horizontal protrusion 352 and the standard through hole on the rotor gantry 320a, it is locked by a nut, thereby realizing the detachable connection of the follower protrusion 342 or the horizontal protrusion 352 to the rotor gantry 320a.

[0048] In this embodiment, the frame base 310, frame gantry 320, and gantry crossbeam 330 are all formed by splicing modular long beams. The splicing positions of two long beams are connected by bolts. Standard through holes are evenly distributed on the long beams. This improves the convenience and compatibility of the wing test bench 10. The lengths of any two modular long beams can be the same or different, but their height and width are the same.

[0049] In this embodiment, as Figure 1 and Figure 3 As shown, a clamping connector 360 is provided on the frame base 310. The clamping connector 360 is used to connect with the connecting bolts of the wing structure 22 itself, so that the wing structure 22 is fixed to the frame base 310. In this way, it is very convenient to fix the wing structure 22 to the frame base 310. Specifically, in this embodiment, there are connecting bolts on both the front and rear sides of the end of the wing body 222 that is connected to the fuselage, and clamping connectors 360 are provided at the positions of the frame base 310 corresponding to the connecting bolts. In this way, it is convenient to firmly fix the wing structure 22 to the frame base 310. More specifically, in this embodiment, there are two clamping connectors 360, and the two clamping connectors 360 are located on the front and rear sides of the end of the wing body 222 that is connected to the fuselage.

[0050] In this embodiment, both the main loading assembly 400 and the rotor loading assembly 500 include a loading plate and a matching actuator. The matching actuator is used to connect the frame assembly 300 and at least one loading plate. Specifically, the main loading assembly 400 includes a loading plate 410 and a matching actuator 420. The rotor loading assembly 500 includes a loading plate 550 and a matching actuator 560. The loading plate 410 is disposed on the wing body 222. The loading plate 550 is disposed on the wing portion 224b of the tilt rotor 224. The matching actuator 420 (560) is parallel to the vertical direction. The matching actuator 420 is used to connect the frame assembly 300 and the loading plate 410. The matching actuator 560 is used to connect the frame assembly 300 and the loading plate 550. This better conforms to the force characteristics of the wing 20 of a tilt rotor electric vertical takeoff and landing aircraft. It is understood that in other embodiments, one of the main loading assembly 400 and the rotor loading assembly 500 may include a loading plate and a matching actuator, while the other may load the load through other structures.

[0051] In this embodiment, as Figure 2 and Figure 5 As shown, the loading plate 410 includes a lower engaging portion 412 and an upper engaging portion 414. The lower engaging portion 412 and the upper engaging portion 414 are respectively used to abut against the lower and upper sides of the wing structure 22. In this way, it is very convenient for the loading plate 410 to be connected to the wing structure 22.

[0052] In this embodiment, the loading plate 410 further includes a locking screw 416. In the front-rear direction of the wing structure 22, the front and rear ends of the lower locking portion 412 and the upper locking portion 414 are connected by the locking screw 416. This facilitates the connection of the lower locking portion 412 and the upper locking portion 414. It is understood that in other embodiments, the lower locking portion 412 and the upper locking portion 414 can also be connected by a snap-fit ​​structure located at the front and rear ends.

[0053] In this embodiment, after the lower engaging portion 412 and the upper engaging portion 414 abut against the lower and upper sides of the wing structure 22 respectively, the distance between the lower engaging portion 412 and the upper engaging portion 414 in the longitudinal direction of the wing structure 22 is divided into a forward distance, a middle distance, and a rear distance. The rear distance is greater than the middle distance and allows the movable control surface 22a of the wing structure 22 to move. That is, the rear distance is large enough that the lower engaging portion 412 and the upper engaging portion 414 will not interfere with the movement of the movable control surface 22a. Thus, during the process of the matching actuator 420 (560) applying a load to the wing structure 22 through the loading plate 410, the movable control surface 22a of the wing structure 22 can freely deflect up and down, which is more in line with the force characteristics of the wing 20 of the tiltrotor electric vertical take-off and landing aircraft.

[0054] In this embodiment, the lower engaging portion 412 includes an outer engaging plate 412a, an inner engaging plate 412b, and a pad 412c disposed between the outer engaging plate 412a and the inner engaging plate 412b. The upper engaging portion 414 includes an outer engaging plate 414a, an inner engaging plate 414b, and a pad 414c disposed between the outer engaging plate 414a and the inner engaging plate 414b. The front, rear, and rear ends of the outer engaging plates 412a of the lower engaging portion 412 and the outer engaging plates 414a of the upper engaging portion 414 are connected by engaging screws 416. The mid-distance is the distance between the inner engaging plates 412b of the lower engaging portion 412 and the inner engaging plates 414b of the upper engaging portion 414. The rear distance is the distance between the outer engaging plates 412a of the lower engaging portion 412 and the outer engaging plates 414a of the upper engaging portion 414. This design facilitates a rear spacing greater than the mid-spacing, allowing for movement of the movable control surfaces 22a of the wing structure 22. Furthermore, the use of multi-layered components in both the lower locking portion 412 and the upper locking portion 414 allows for more efficient material selection, ensuring that the structural strength, weight, and rigidity of the components in contact with the wing structure 22 are balanced, preventing damage to the wing structure 22 during testing. It is understood that in other embodiments, the lower locking portion 412 and the upper locking portion 414 may also consist of only one component.

[0055] In this embodiment, the front spacing and the rear spacing are the same. This makes it very convenient to manufacture the lower engaging portion 412 and the upper engaging portion 414. It is understood that in other embodiments, the front spacing may also be the same as the middle spacing.

[0056] In this embodiment, the lower engaging portion 412 has two pads 412c, which are located at both ends of the inner engaging plate 412b in the front-back direction. The upper engaging portion 414 has two pads 414c, which are also located at both ends of the inner engaging plate 414b in the front-back direction. This better balances the structural strength and weight of the lower engaging portion 412 and the upper engaging portion 414. It is understood that in other embodiments, the number of pads 412c (414c) may be one or more.

[0057] In this embodiment, the inner locking plate 412b (414b) is a conformal pad. The stiffness of the outer locking plate 412a (414a) and the pad 412c (414c) is greater than that of the inner locking plate 412b (414b). Specifically, the outer locking plate 412a (414a) and the pad 412c (414c) are made of steel. This better balances the structural strength, weight, and stiffness of the components in contact with the wing structure 22 of the lower locking part 412 and the upper locking part 414. It is understood that in other embodiments, the inner locking plate 412b (414b) can be made of other materials with similar stiffness to the conformal pad.

[0058] In this embodiment, as Figure 1 and Figure 2 As shown, the main loading assembly 400 includes at least one first main loading assembly 400a and at least one second main loading assembly 400b. The first main loading assembly 400a includes a loading plate 410 and a matching actuator cylinder 420. The second main loading assembly 400b includes two loading plates 410, a matching actuator cylinder 420, and a loading lever 430 connecting the two loading plates 410 and the matching actuator cylinder 420. The loading lever 430 can proportionally distribute the load output by the matching actuator cylinder 420 onto the two loading plates 410 (the connection point between the matching actuator cylinder 420 and the loading lever 430 divides the loading lever 430 into two segments, the proportion of which is determined by the length ratio of the two segments). The main loading assembly 400, including at least one first main loading assembly 400a and at least one second main loading assembly 400b, allows for greater flexibility in testing. Furthermore, the combination of one matching actuator cylinder 420 with two loading plates 410 reduces the number of matching actuator cylinders 420, simplifies the structure, and lowers costs. It is understood that in other embodiments, the main loading component 400 may also include a third main loading component, which may include a matching actuator 420 and multiple (three or more) loading plates 410.

[0059] In this embodiment, in the second main loading assembly 400b, the matching actuating cylinder 420 and the loading lever 430 are connected by a steel wire 440. This facilitates the connection between the matching actuating cylinder 420 and the loading lever 430. In the second main loading assembly 400b, the loading lever 430 and the matching actuating cylinder 420 are connected by a steel wire 450. This further facilitates the connection between the loading lever 430 and the matching actuating cylinder 420.

[0060] In this embodiment, in the rotor loading assembly 500, the loading plate 550 and the matching actuator cylinder 560 are connected by a steel wire 570. This makes it easier to connect the loading plate 550 and the matching actuator cylinder 560.

[0061] In this embodiment, force sensors 600 are provided at the extension and retraction ends of all actuator cylinders. This facilitates the acquisition of the applied load.

[0062] like Figure 6As shown, this utility model also provides a wing testing system. The wing testing system has a test execution area 700 and a test control area 800. A safe isolation distance exists between the test execution area 700 and the test control area 800. The test execution area 700 is mainly used for actual loading of the wing 20. The test execution area 700 includes the aforementioned wing test bench 10 and the wing 20. The main function of the test control area 800 is to allow test operators to control the test process and collect test data. The test control area 800 includes a data analyzer 810, a loading computer 820, and a loading controller 830, etc. During the test, the operator in the test control area 800 issues a loading command through the loading computer 820. The loading controller 830 encodes the loading command and sends it to at least one actuator on the wing test bench 10 in the test execution area 700 to apply actuation loading to the wing 20. Simultaneously, the force sensor 600 on the actuator feeds back the actual loading magnitude to the data analyzer 810, allowing the loading computer 820 to control the loading force in real time.

[0063] In this embodiment, the test execution area 700 also includes a sensor assembly 710. The sensor assembly 710 can feed back parameters such as strain and displacement of the wing 20 to the data analyzer 810, so that the loading computer 820 can analyze whether the wing 20 has passed the test.

[0064] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0065] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of this patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. A test bench for an aircraft wing, the wing comprising two symmetrical wing structures, each wing structure including a wing body connected to a fuselage and a tilt rotor rotatably connected to the side of the wing body away from the fuselage, wherein the tilt angle of the tilt rotor changes accordingly during rotation relative to the wing body, characterized in that... The test device includes a test apparatus corresponding to the wing structure, the test apparatus comprising: Frame components used to support the wing structure; A main loading component, disposed on the frame component, is used to apply loads to the wing body; and A rotor loading assembly, disposed on the frame assembly, is used to apply a load to the tilt rotor. The rotor loading assembly includes a first rotor actuator cylinder, which connects the frame assembly and the tilt rotor. The tilt angle of the first rotor actuator cylinder is the same as the tilt angle of the tilt rotor to simulate the pull of the tilt rotor on the wing. The first rotor actuator cylinder can be detachably connected to different positions on the frame assembly so that the tilt angle of the first rotor actuator cylinder connecting the frame assembly and the tilt rotor can change accordingly after the tilt angle of the tilt rotor changes.

2. The test rig for an airfoil as described in claim 1, characterized in that, The rotor loading assembly further includes a second rotor actuator and a connecting rod. The connecting rod is mounted on the tilt rotor. The first rotor actuator connects the frame assembly to the connecting rod. The connecting rod is perpendicular to the first rotor actuator and parallel to the axis of rotation of the tilt rotor. The second rotor actuator connects the frame assembly to the end of the connecting rod. The tilt direction of the second rotor actuator is opposite to that of the first rotor actuator. There are two second rotor actuators, which are arranged in parallel and spaced apart to simulate the torque exerted by the tilt rotor on the wing. The second rotor actuators can be detachably connected to different positions on the frame assembly so that when the connection position of the first rotor actuator with the frame assembly changes, the connection position of the second rotor actuator with the frame assembly changes accordingly.

3. The test rig for wings as described in claim 2, characterized in that, The rotor loading assembly further includes a loading joint, which is used to mount the tilting rotor, and the connecting rod is mounted on the loading joint.

4. The test rig for an airfoil as described in claim 2, characterized in that, The frame assembly includes a frame base and a frame gantry. The frame base is used to support the wing, and the frame gantry is disposed on the frame base. The two vertical beams of the frame gantry are located on the front and rear sides of the wing. The first rotor actuator can be detachably connected to different positions of the frame gantry, and the second rotor actuator can be detachably connected to different positions of the frame gantry.

5. The test rig for an airfoil as described in claim 4, characterized in that, There are multiple frame gantry gates. In the left and right directions of the wing structure, the multiple frame gantry gates are arranged at intervals according to the rib structure positions of the wing structure. The frame gantry located at the head of the tilting rotor is a rotor gantry. The first rotor actuator can be detachably connected to different positions of the rotor gantry, and the second rotor actuator can be detachably connected to different positions of the rotor gantry.

6. The test rig for an airfoil as described in claim 5, characterized in that, The frame assembly further includes a follower protrusion group, which includes two follower protrusions detachably connected to different positions on the rotor gantry. The two second rotor actuators are detachably connected to the two follower protrusions respectively; and / or The frame assembly further includes a gantry beam extending along the arrangement direction of the plurality of frame gantry gates, the gantry beam being disposed on at least one of the frame gantry gates; and / or The rotor gantry is provided with uniformly distributed standard through holes, which allows the first rotor actuator cylinder to be detachably connected to different positions of the rotor gantry through the standard through holes at different locations, and also allows the second rotor actuator cylinder to be detachably connected to different positions of the rotor gantry through the standard through holes at different locations.

7. The test rig for an airfoil as described in claim 6, characterized in that, The frame base, the frame gantry, and the gantry beam are all formed by splicing modular long beams. The splicing positions of two long beams are connected by bolts, and the standard through holes are evenly distributed on the long beams; and / or The frame base is provided with a clamping joint that is connected to the connecting bolts of the wing body. The wing body is fixed to the frame base by the connected connecting bolts and the clamping joint.

8. The test rig for an airfoil as described in any one of claims 1-7, characterized in that, The first rotor actuator cylinder is used to connect the frame assembly and the head of the tilt rotor. The head of the tilt rotor has a centerline parallel to the first rotor actuator cylinder, and the first rotor actuator cylinder is eccentrically disposed from the centerline.

9. The test rig for an airfoil as described in claim 1, characterized in that, At least one of the main loading assembly and the rotor loading assembly includes a loading plate, and at least one of the main loading assembly and the rotor loading assembly includes a matching actuator cylinder, which is parallel to the vertical direction and is used to connect the frame assembly and at least one of the loading plates.

10. The test rig for an airfoil as described in claim 9, characterized in that, The loading plate includes a lower engaging portion and an upper engaging portion, which are respectively used to abut against the lower and upper sides of the wing. After the lower engaging portion and the upper engaging portion abut against the lower and upper sides of the wing, the distance between the lower engaging portion and the upper engaging portion in the fore-and-aft direction of the wing is divided into a forward distance, a middle distance and a rear distance. The rear distance is greater than the middle distance to allow the movement of the wing's movable control surfaces.

11. The test rig for an airfoil as described in claim 10, characterized in that, Both the lower locking portion and the upper locking portion include an outer locking plate, an inner locking plate, and a pad disposed between the outer locking plate and the inner locking plate. The middle spacing is the distance between the inner locking plate of the lower locking portion and the inner locking plate of the upper locking portion, and the rear spacing is the distance between the outer locking plate of the lower locking portion and the outer locking plate of the upper locking portion.

12. The test rig for an airfoil as described in claim 11, characterized in that, The front spacing and the rear spacing are the same; and / or The inner clamping plate is a conformal wooden block, and the rigidity of the outer clamping plate and the pad block is greater than that of the inner clamping plate; and / or The loading plate also includes a locking screw, and in the fore-and-aft direction of the wing, the front and rear ends of the lower locking part and the upper locking part are connected by the locking screw.

13. The test rig for an airfoil as described in any one of claims 9-12, characterized in that, The main loading assembly includes at least one first main loading assembly and at least one second main loading assembly. The first main loading assembly includes one loading plate and one matching actuator. The second main loading assembly includes two loading plates, one matching actuator, and a loading lever connecting the two loading plates and one matching actuator.

14. The test rig for an airfoil as described in claim 1, characterized in that, There are two test devices, each corresponding to one of the two wing structures of the wing, and the frame assemblies of the two test devices are connected.

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