Airplane hydraulic actuator cylinder testing device

Abstract

The utility model relates to the technical field of hydraulic actuator cylinder testing, in particular to an airplane hydraulic actuator cylinder testing device which comprises a workbench, two symmetrically-arranged positioning sliding grooves are formed in the workbench and located on the same straight line, and a connecting sliding block is clamped in each positioning sliding groove in a sliding mode. The top of each connecting sliding block is connected with a clamping mechanism. Each clamping mechanism comprises a base plate seat, the base plate seat is fixedly connected to the top of the connecting sliding block, the top of the base plate seat is vertically and movably connected with a bearing frame, the bearing frame is connected with a limiting mechanism, the limiting mechanism is connected with the bottom of the cover plate piece, and the limiting mechanism can be vertically adjusted in a telescopic mode; one side of each bearing frame is provided with a horizontally-arranged light hole, the other side of each bearing frame is connected with an infrared emitter, and the infrared emitters and the light holes on the two bearing frames are correspondingly arranged. Whether the hydraulic actuator cylinder is in a horizontal state or not can be judged in an auxiliary mode according to whether light penetrates through the light hole or not and the light deviation condition.

Description

A test device for aircraft hydraulic actuators Technical Field

[0001] This utility model relates to the field of hydraulic actuator testing technology, specifically to an aircraft hydraulic actuator testing device. Background Technology

[0002] Hydraulic actuators consist of components such as a cylinder, liner, piston, and rubber seals. They are a common type of actuator in hydraulic transmission systems, enabling reciprocating motion of working mechanisms. Due to their simple structure and reliable operation, they are widely used in the aviation field, such as for controlling aircraft control surfaces, extending and retracting landing gear, flaps, and speed brakes, and operating aircraft engine exhaust nozzles, thrust reversers, intake cones, and fuel pumps.

[0003] Given the critical role of hydraulic actuators in aircraft operation, their quality control is extremely stringent. Before being put into actual aircraft use, they must undergo a rigorous testing process to determine whether they meet the qualification standards.

[0004] However, existing testing devices on the market have significant technical flaws. After fixing the hydraulic actuator, it is difficult to ensure that the cylinder body and piston remain on the same horizontal line. This problem causes the hydraulic actuator to inevitably bear additional torsional forces in the fixed state. Due to the precise internal structure of the hydraulic actuator, even a slight torsional force can interfere with the relative position and movement of its internal parts, thus affecting key indicators such as pressure transmission and piston movement smoothness throughout the testing process. Ultimately, this leads to deviations in the test results, failing to accurately reflect the actual performance of the hydraulic actuator. Summary of the Invention

[0005] To address the technical problem that existing testing devices struggle to ensure the cylinder and piston remain on the same horizontal line when fixing the hydraulic actuator, leading to torsional forces on the hydraulic actuator and affecting test results, this invention provides an aircraft hydraulic actuator testing device.

[0006] To achieve the above objectives, the technical solution adopted by this utility model is as follows:

[0007] A testing device for an aircraft hydraulic actuator includes a worktable with two symmetrically arranged positioning grooves on the worktable, the two positioning grooves being on the same straight line, and a connecting slider being slidably engaged inside each positioning groove; a clamping mechanism is connected to the top of each connecting slider; each clamping mechanism includes a base plate fixedly connected to the top of the connecting slider, and a support frame vertically movably connected to the top of the base plate, the top surface of the support frame being a concave arc-shaped structure, the support frame being connected to a limiting mechanism, the limiting mechanism being connected to the bottom of a cover plate, the limiting mechanism being vertically adjustable, and the bottom surface of the cover plate being a convex arc-shaped structure; a horizontally arranged light-transmitting hole is opened on one side of the support frame, and an infrared emitter is connected to the other side, the infrared emitter being positioned on the side of the support frame opposite to the other support frame, and the infrared emitters and light-transmitting holes on the two support frames being correspondingly arranged.

[0008] The above structural design incorporates symmetrical positioning grooves and connecting sliders on the worktable, facilitating easy adjustment of the distance between the two clamping mechanisms to accommodate aircraft hydraulic actuators of varying lengths. The clamping mechanism features a concave top surface of the support frame and a convex bottom surface of the cover plate, which, when combined, better conform to the cylindrical shape of the hydraulic actuator, providing stable support and fixation. The support frame's height is adjustable, with a light-transmitting hole on one side and an infrared emitter on the other. The corresponding light-transmitting holes and infrared emitters on the two support frames allow for the assessment of whether the hydraulic actuator is horizontal by observing whether light passes through the light-transmitting hole and the light deflection. This solves the problem in existing technologies where it is difficult to ensure the cylinder and piston are on the same horizontal line, reducing the torsional force on the hydraulic actuator due to positional deviations and improving the accuracy of test results.

[0009] As a preferred implementation of an aircraft hydraulic actuator testing device, detection panels are symmetrically fixed on the left and right sides of the top of the workbench. A light meter plate is fixedly connected to the opposite sides of the two detection panels. A scale is set on the side of the light meter plate, and the light meter plate is positioned opposite the light-transmitting hole.

[0010] With the above structural design, when infrared light passes through the light-transmitting hole and shines on the light-measuring plate, the operator can accurately observe the subtle changes in the position of the infrared light irradiation according to the scale on the scale. This allows for a more intuitive and accurate quantification of the degree of infrared light deviation, precise judgment of whether the hydraulic actuator is horizontal, and provides a clear numerical reference for adjusting its position.

[0011] As a preferred implementation of an aircraft hydraulic actuator testing device, the test panel has a U-shaped cross-section.

[0012] With the above structural design, the hole in the middle of the "U"-shaped detection panel saves materials and does not hinder the extension and retraction of the hydraulic actuator.

[0013] As a preferred implementation of an aircraft hydraulic actuator test device, the base plate is provided with a vertically arranged drive screw and linkage screw inside. The drive screw and linkage screw pass through the top of the base plate and can rotate synchronously. The drive screw and linkage screw on the same base plate are threadedly connected to the same support frame.

[0014] With the above structural design, a drive screw and a linkage screw are installed inside the base plate and can rotate synchronously. The two are threadedly connected to the same support frame. By rotating the drive screw and the linkage screw, the height of the support frame can be adjusted smoothly and synchronously. Therefore, when fixing the hydraulic actuator, the height can be easily adjusted according to the actual situation of the hydraulic actuator to make it better level. This effectively avoids the hydraulic actuator from being subjected to torsional force due to inconsistent height, and improves the stability of fixing and the accuracy of test results.

[0015] As a preferred implementation of an aircraft hydraulic actuator testing device, a servo motor is fixedly installed at the bottom of the base plate, and the output end of the servo motor is connected to the bottom end of the drive screw.

[0016] By adopting the above structural scheme, the rotation of the drive screw can be precisely controlled by the servo motor, thereby precisely controlling the lifting height of the support frame. This makes the height adjustment of the hydraulic actuator more accurate when it is fixed, further ensuring that the hydraulic actuator is in a horizontal position, reducing the impact of torsional force on the test, and ensuring that the test results truly reflect the performance of the hydraulic actuator.

[0017] As a preferred implementation of an aircraft hydraulic actuator test device, a connecting gear plate is fixedly connected to the outer surface of the drive screw, a driven gear plate is fixedly connected to the outer surface of the linkage screw, a gear belt is connected between the connecting gear plate and the driven gear plate, and the connecting gear plate, the driven gear plate and the gear belt are located inside the base plate.

[0018] By adopting the above structural scheme, the synchronous rotation of the drive screw and the linkage screw can be achieved, ensuring the stability of the support frame during the lifting process and avoiding the tilting of the support frame due to asynchronous rotation of the screws. This allows the hydraulic actuator to be stably fixed in a horizontal position, improving the reliability of the testing device for fixing and testing the hydraulic actuator.

[0019] As a preferred implementation of an aircraft hydraulic actuator testing device, a control component is connected to one side of the top of the workbench, and the control component is electrically connected to a servo motor.

[0020] With the above structural design, the servo motor can be easily operated through the control components, such as controlling the forward and reverse rotation and speed of the motor. This allows for flexible and precise adjustment of the support frame height, enabling staff to adjust the fixed position of the hydraulic actuator according to actual testing needs, thereby improving the operability of the testing process and the accuracy of the test results.

[0021] As a preferred implementation of an aircraft hydraulic actuator testing device, the limiting mechanism includes two connecting slide rods, which are symmetrically fixed on the left and right sides of the bottom of the cover plate. The bottom end of the connecting slide rod slides downward through the support frame and connects with the return spring, and the top end of the return spring abuts against the bottom of the support frame.

[0022] With the above structural design, when fixing the hydraulic actuator, the return spring can provide a certain elastic pressure when the hydraulic actuator is placed between the support frame and the cover plate, so that the cover plate fits the hydraulic actuator better and avoids damage to the hydraulic actuator. At the same time, it can make the support frame and the cover plate firmly clamp the hydraulic actuator.

[0023] As a preferred implementation of an aircraft hydraulic actuator testing device, the bottom of each connecting slider is hinged to the top of the adjusting plate via an adjusting shaft. The tail ends of the two adjusting plates are respectively hinged to the opposite sides of the same connecting plate. A vertical limiting slot is provided in the center of the connecting plate. An adjusting screw is threaded inside the limiting slot. The top of the adjusting screw is rotatably connected to the bottom surface of the worktable. A support base is fixedly provided at the bottom of the worktable. The bottom end of the adjusting screw passes through the support base and is connected to the output end of the adjusting motor. The adjusting motor is installed on the bottom surface of the support base.

[0024] With the above structural design, when the adjusting motor drives the adjusting screw to rotate, it can drive the connecting plate to move up and down, thereby changing the position of the connecting slider in the positioning groove through the adjusting plate. The two connecting sliders can slide synchronously and smoothly along their respective positioning grooves under the drive of the same adjusting motor.

[0025] As a preferred implementation of an aircraft hydraulic actuator testing device, the cross-section of the connecting slider is a cross-shaped structure.

[0026] The above structural design improves the sliding stability of the connecting slider.

[0027] The beneficial effects of this utility model include:

[0028] The corresponding arrangement of the light-transmitting holes on the support frame of the clamping mechanism with the infrared emitter constructs a simple and efficient horizontal detection system. Utilizing the linear propagation characteristics of infrared light, by detecting whether the infrared light can pass smoothly through the light-transmitting holes, it is possible to intuitively determine whether the front and rear ends of the hydraulic actuators on the two support frames are on the same horizontal line. If not, the height of each support frame can be adjusted to bring the front and rear ends of the hydraulic actuators to the same horizontal line. This solves the problem in existing technologies where it is difficult to ensure that the front and rear ends of the hydraulic actuators are on the same horizontal line, reduces the torsional force borne by the hydraulic actuators due to positional deviations, and improves the accuracy of test results. Attached Figure Description

[0029] To more clearly illustrate the technical solution of this utility model, the drawings used in the description will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0030] Figure 1 is a three-dimensional structural schematic diagram of the aircraft hydraulic actuator cylinder testing device in a specific embodiment of this utility model.

[0031] Figure 2 is a three-dimensional structural schematic diagram of the aircraft hydraulic actuator cylinder testing device in a specific embodiment of this utility model.

[0032] Figure 3 is a three-dimensional structural diagram of the drive mechanism in a specific embodiment of this utility model;

[0033] Figure 4 is a three-dimensional structural diagram of the linkage mechanism in a specific embodiment of this utility model;

[0034] Figure 5 is a cross-sectional schematic diagram of the substrate base in a specific embodiment of this utility model;

[0035] Figure 6 is a three-dimensional structural diagram of the detection panel in a specific embodiment of this utility model.

[0036] List of components and reference numerals:

[0037] 1. Worktable; 2. Control components; 3. Support base; 4. Positioning slide; 5. Connecting slider; 6. Adjusting shaft; 7. Adjusting plate; 8. Connecting plate; 9. Limiting through slot; 10. Adjusting screw; 11. Adjusting motor; 12. Base plate; 13. Servo motor; 14. Drive screw; 15. Connecting gear plate; 16. Gear belt; 17. Linkage screw; 18. Bearing frame; 19. Infrared emitter; 20. Light-transmitting hole; 21. Cover plate; 22. Connecting slide rod; 23. Return spring; 24. Detection panel; 25. Light meter plate; 26. Scale; 27. Driven gear plate. Detailed Implementation

[0038] To make the objectives, features, and advantages of this utility model more apparent and understandable, the technical solutions of this utility model will be clearly and completely described below with reference to the accompanying drawings of the specific embodiments. Obviously, the embodiments described below are only some embodiments of this utility model, and not all embodiments. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0039] Referring to Figures 1-6, this embodiment proposes an aircraft hydraulic actuator testing device, including a worktable 1. The worktable 1 has two symmetrically arranged positioning grooves 4, which are located on the same straight line. Each positioning groove 4 has a connecting slider 5 slidably engaged inside it. The cross-section of the connecting slider 5 is a "+" shaped structure. The two connecting sliders 5 can move along the positioning grooves 4 under the drive of the driving mechanism.

[0040] The drive mechanism includes an adjusting shaft 6, an adjusting plate 7, a connecting plate 8, an adjusting screw 10, and an adjusting motor 11. The bottom of each connecting slider 5 is hinged to the top of the adjusting plate 7 via the adjusting shaft 6. The tail ends of the two adjusting plates 7 are respectively hinged to opposite sides of the same connecting plate 8. A vertical limiting slot 9 is formed in the center of the connecting plate 8, and the adjusting screw 10 is threaded into the limiting slot 9. The top of the adjusting screw 10 is rotatably connected to the bottom surface of the worktable 1. A support base 3 is fixedly provided at the bottom of the worktable 1. The bottom end of the adjusting screw 10 passes through the support base 3 and is connected to the output end of the adjusting motor 11. The adjusting motor 11 is mounted on the bottom surface of the support base 3. When the adjusting motor 11 drives the adjusting screw 10 to rotate, it can move the connecting plate 8 up and down, thereby changing the position of the connecting slider 5 within the positioning groove 4 via the adjusting plate 7. The two connecting sliders 5 can slide synchronously and smoothly along their respective positioning grooves 4 under the drive of the same adjusting motor 11.

[0041] Each connecting slider 5 is connected to a clamping mechanism at its top; each clamping mechanism includes a base plate 12, which is fixedly connected to the top of the connecting slider 5. A support frame 18 is vertically movably connected to the top of the base plate 12, and the height of the support frame 18 is adjustable. The top surface of the support frame 18 is a concave arc-shaped structure. The support frame 18 is connected to a limiting mechanism, which is connected to the bottom of the cover plate 21. The limiting mechanism can be vertically extended and retracted. The bottom surface of the cover plate 21 is a convex arc-shaped structure. The support frame 18 and the cover plate 21 work together to better fit the cylindrical shape of the hydraulic actuator, providing stable support and fixation.

[0042] The limiting mechanism includes two connecting slide rods 22, which are symmetrically fixed on the left and right sides of the bottom of the cover plate 21. The bottom ends of the connecting slide rods 22 slide downward through the support frame 18 and connect with the return spring 23. The top end of the return spring 23 abuts against the bottom of the support frame 18. When fixing the hydraulic actuator, when the hydraulic actuator is placed between the support frame 18 and the cover plate 21, the return spring 23 can provide a certain elastic pressure, so that the cover plate 21 fits the hydraulic actuator better, avoiding damage to the hydraulic actuator, and at the same time, it can make the support frame 18 and the cover plate 21 firmly clamp the hydraulic actuator.

[0043] A horizontally positioned light-transmitting hole 20 is opened on one side of the support frame 18, and an infrared emitter 19 is connected to the other side. The infrared emitter 19 is positioned on the side of the support frame 18 opposite to another support frame 18, with the infrared emitters 19 and light-transmitting holes 20 on the two support frames 18 corresponding to each other. By transmitting and receiving infrared light, whether the light passes through the light-transmitting hole 20 and the light deflection can be used to help determine whether the hydraulic actuator cylinder is in a horizontal state. This solves the problem in the prior art that it is difficult to ensure that the cylinder and piston are on the same horizontal line, reduces the torsional force borne by the hydraulic actuator cylinder due to positional deviation, and improves the accuracy of test results.

[0044] Symmetrically fixed "U"-shaped detection panels 24 are mounted on the left and right sides of the top of the workbench 1. Measuring plates 25 are fixedly connected to the opposite sides of each of the two detection panels 24. A scale 26 is mounted on the side of each measuring plate 25, and the measuring plates 25 are positioned opposite the light-transmitting holes 20. When infrared light passes through the light-transmitting holes 20 and shines onto the measuring plates 25, the operator can precisely observe subtle changes in the position of the infrared light by referring to the scale on the scale 26. This allows for a more intuitive and accurate quantification of the infrared light's offset, precisely determining whether the hydraulic actuator is level, and providing a clear numerical reference for adjusting its position.

[0045] To achieve vertical movement of the support frame 18, the base plate 12 is equipped with a vertically arranged drive screw 14 and a linkage screw 17. The drive screw 14 and the linkage screw 17 extend from the top of the base plate 12 and can rotate synchronously under the action of the linkage mechanism. The drive screw 14 and the linkage screw 17 on the same base plate 12 are threadedly connected to the same support frame 18. The linkage mechanism includes a servo motor 13, a connecting gear plate 15, a driven gear plate 27, and a gear belt 16. The servo motor 13 is fixedly mounted on the bottom of the base plate 12, and the output end of the servo motor 13 is connected to the bottom end of the drive screw 14. The connecting gear plate 15 is fixedly connected to the outer surface of the drive screw 14, and the driven gear plate 27 is fixedly connected to the outer surface of the linkage screw 17. A gear belt 16 connects the connecting gear plate 15 and the driven gear plate 27. The connecting gear plate 15, the driven gear plate 27, and the gear belt 16 are located inside the base plate 12. Powered by the servo motor 13, the rotation of the drive screw 14 can be precisely controlled. The linkage screw 17 rotates synchronously with the drive screw 14 under the action of the connecting gear plate 15, the driven gear plate 27, and the gear belt 16. The synchronous rotation of the drive screw 14 and the linkage screw 17 allows for smooth and precise adjustment of the height of the support frame 18, ensuring that the support frame 18 does not tilt. Therefore, when fixing the hydraulic actuator, the height can be easily adjusted according to the actual situation of the hydraulic actuator, ensuring it is better positioned horizontally. This effectively avoids the hydraulic actuator being subjected to torsional forces due to inconsistent heights, improving the stability of the fixing and the accuracy of the test results.

[0046] A control component 2 is connected to one side of the top of the workbench 1. The control component 2 is electrically connected to the servo motor 13 and can also be electrically connected to the regulating motor 11. The control component 2 allows for convenient operation of the servo motor 13 and the regulating motor 11, such as controlling the forward and reverse rotation and speed of the motors. This enables flexible and precise adjustment of the height of the support frame 18 and the movement of the connecting slider 5, facilitating the adjustment of the fixed position of the hydraulic actuator cylinder according to actual testing needs, thereby improving the operability of the testing process and the accuracy of the test results.

[0047] Work process:

[0048] Based on the length of the hydraulic actuator cylinder to be tested, the control component 2 starts the adjustment motor 11, which drives the adjustment screw 10 to rotate, causing the connecting plate 8 to move up and down. Then, the adjustment plate 7 makes the two connecting sliders 5 slide synchronously and smoothly in the positioning groove 4, and adjusts the distance between the two clamping mechanisms.

[0049] Pull up the cover plate 21 and place both ends of the hydraulic actuator cylinder on the two support frames 18 respectively, with the concave arc surface of the support frame 18 contacting the hydraulic actuator cylinder. Lower the cover plate 21, which moves downward under the action of the connecting slide rod 22 and the return spring 23. The return spring 23 provides elastic pressure, allowing the convex arc surface of the cover plate 21 to better fit the hydraulic actuator cylinder, firmly clamping it while avoiding damage.

[0050] Based on the actual situation of the hydraulic actuator, the servo motor 13 is started by the control component 2. The servo motor 13 drives the drive screw 14 to rotate. The linkage screw 17 rotates synchronously with the drive screw 14 under the action of the connecting gear plate 15, the driven gear plate 27 and the gear belt 16, so as to smoothly and accurately adjust the height of each support frame 18, so that the two ends of the hydraulic actuator are better in a horizontal position.

[0051] Infrared emitter 19 emits infrared rays. If the hydraulic actuator is horizontal, the infrared rays pass through the light-transmitting hole 20 and illuminate the corresponding light-measuring plate 25. If it is not horizontal, the infrared rays will deflect. The operator uses the scale 26 on the side of the light-measuring plate 25 to precisely observe the subtle changes in the position of the infrared rays and determine whether the hydraulic actuator is horizontal. If the hydraulic actuator is not horizontal, based on the infrared ray deflection, the servo motor 13 is adjusted again via control component 2 to adjust the height of the support frame 18 so that both ends of the hydraulic actuator are on the same horizontal line, and then the hydraulic actuator is tested.

[0052] The above description of the disclosed embodiments enables those skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A testing device for aircraft hydraulic actuators, comprising a workbench (1), characterized in that, Two symmetrically arranged positioning grooves (4) are opened on the worktable (1). The two positioning grooves (4) are located on the same straight line. A connecting slider (5) is slidably engaged inside each positioning groove (4). A clamping mechanism is connected to the top of each connecting slider (5). Each clamping mechanism includes a base plate seat (12). The base plate seat (12) is fixedly connected to the top of the connecting slider (5). A support frame (18) is vertically movably connected to the top of the base plate seat (12). The top surface of the support frame (18) is a concave arc-shaped structure. (18) is connected to the limiting mechanism, which is connected to the bottom of the cover plate (21). The limiting mechanism can be vertically extended and adjusted. The bottom surface of the cover plate (21) is a convex arc-shaped structure. A horizontally arranged light-transmitting hole (20) is opened on one side of the support frame (18), and an infrared emitter (19) is connected to the other side. The infrared emitter (19) is set on the side opposite to the support frame (18) and the other support frame (18). The infrared emitter (19) and the light-transmitting hole (20) on the two support frames (18) are correspondingly set.

2. The aircraft hydraulic actuator testing device according to claim 1, characterized in that, The top of the workbench (1) is symmetrically fixed with detection panels (24) on the left and right sides. The two detection panels (24) are fixedly connected with light measuring plates (25) on opposite sides. The side of the light measuring plate (25) is equipped with a scale (26). The light measuring plate (25) is opposite to the light-transmitting hole (20).

3. The aircraft hydraulic actuator testing device according to claim 2, characterized in that, The cross-section of the detection panel (24) is a "U" shaped structure.

4. The aircraft hydraulic actuator testing device according to claim 1, characterized in that, The substrate base (12) is provided with a vertically arranged drive screw (14) and linkage screw (17). The drive screw (14) and linkage screw (17) pass through the top of the substrate base (12) and can rotate synchronously. The drive screw (14) and linkage screw (17) on the same substrate base (12) are threadedly connected to the same support frame (18).

5. The aircraft hydraulic actuator testing device according to claim 4, characterized in that, A servo motor (13) is fixedly mounted on the bottom of the base plate (12), and the output end of the servo motor (13) is connected to the bottom end of the drive screw (14).

6. The aircraft hydraulic actuator testing device according to claim 5, characterized in that, A connecting gear plate (15) is fixedly connected to the outer surface of the drive screw (14), and a driven gear plate (27) is fixedly connected to the outer surface of the linkage screw (17). A gear belt (16) is connected between the connecting gear plate (15) and the driven gear plate (27). The connecting gear plate (15), the driven gear plate (27) and the gear belt (16) are located inside the base plate (12).

7. The aircraft hydraulic actuator testing device according to claim 5, characterized in that, A control component (2) is connected to one side of the top of the workbench, and the control component (2) is electrically connected to the servo motor (13).

8. The aircraft hydraulic actuator testing device according to claim 1, characterized in that, The limiting mechanism includes two connecting slide rods (22), which are symmetrically fixed on the left and right sides of the bottom of the cover plate (21). The bottom end of the connecting slide rod (22) slides downward through the support frame (18) and is connected to the return spring (23). The top end of the return spring (23) abuts against the bottom of the support frame (18).

9. The aircraft hydraulic actuator testing device according to claim 1, characterized in that, The bottom of each connecting slider (5) is hinged to the top of the adjusting plate (7) via the adjusting shaft (6). The tail ends of the two adjusting plates (7) are respectively hinged to the opposite sides of the same connecting plate (8). A vertical limiting through groove (9) is provided in the center of the connecting plate (8). An adjusting screw (10) is threaded inside the limiting through groove (9). The top of the adjusting screw (10) is rotatably connected to the bottom surface of the workbench (1). A support base (3) is fixedly provided at the bottom of the workbench (1). The bottom end of the adjusting screw (10) passes through the support base (3) and is connected to the output end of the adjusting motor (11). The adjusting motor (11) is installed on the bottom surface of the support base (3).

10. The aircraft hydraulic actuator testing device according to claim 9, characterized in that, The cross-section of the connecting slider (5) is a cross shape.

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