Aircraft actuator simulation loading test platform and method

Abstract

The present invention discloses a simulated loading test platform and method for aircraft actuators, and relates to the field of control systems. The platform includes an actuator test bench, a loading spring group, and a fixed rear support arranged on the top of a fixed platform; in the actuator test bench, the top of the first base is provided with a fixed support, a movable support, a stiffness simulator, and an actuator rear moving seat in axial order, the top of the second base is slidably connected to the actuator front moving seat, a grating scale and an inertia simulator are fixed on the side, and a tested actuator is provided between the actuator front moving seat and the actuator rear moving seat. The present invention can simulate the actual working state of the actuator during the loading test, obtain more accurate working data, and make the test results more real and reliable. The platform adopts a combination of rigid tooling and flexible tooling, has a compact structure, is sturdy and durable, can quickly reconstruct and adjust the positioner to adapt to different actuator shapes, and greatly shortens the actuator loading test process time.

Description

Technical Field

[0001] The present invention belongs to the field of control systems, and in particular relates to an aircraft actuator simulation loading test platform and method. Background Art

[0002] Actuators are key components for active vibration control and a crucial link in active control systems. Their function is to exert control force on the controlled object according to a defined control law. Traditional actuator testing methods rely on manual reading and recording, which is inefficient, labor-intensive, and produces inaccurate test results, making them difficult to meet the needs of today's real-world production and daily life. Researching actuator testing schemes has important engineering applications and practical significance.

[0003] Research on actuator systems is relatively early abroad. Lockheed Martin in the United States tested and researched actuators with varying system architectures and power levels on its C130 and C141 transport aircraft. The Airbus A380, a commercial wide-body aircraft, incorporates actuators to reduce weight, providing superior flight control performance and a higher safety margin. Researchers designed a prototype using a fixed-displacement, variable-speed configuration for testing, validating the dynamic performance and advantages of a symmetrical actuator system.

[0004] China has achieved certain results in the field of structural optimization and algorithm optimization of actuators. The team of Academician Yang Huayong of Zhejiang University has successfully applied electric hydrostatic actuators to hydraulic elevators and injection molding machines. Beihang University has analyzed actuators for different applications, and the research content covers simulation analysis and actuator algorithm optimization, and has achieved certain research results. Taiyuan University of Technology has solved the problems of reduced control performance and energy saving caused by the flow asymmetry of the asymmetric cylinder of the actuator. Beihang University has completed the loading test of the electric hydrostatic actuator using a spring test bench and conducted dynamic performance tests.

[0005] While extensive experimental research has been conducted both domestically and internationally on actuator structural design, manufacturing processes, and control algorithms, achieving considerable success, current researchers rarely incorporate actual actuator operating conditions into their load testing, making it difficult to obtain accurate test data. Therefore, it is necessary to design an actuator-specific loading platform that can perform load tests on actuators under actual operating conditions and analyze the actuator's actual performance based on the collected data. Summary of the Invention

[0006] The present invention aims to overcome the shortcomings of the prior art and provide a platform and method for simulated loading testing of aircraft actuators. This invention addresses the inconvenience of manual operation, low accuracy, and low efficiency during actuator testing. The simulation platform offers convenient and quick adjustment, is suitable for real-time simulation of a variety of actuators, and features secure and reliable locking, significantly reducing the testing burden.

[0007] The specific technical solutions adopted in the present invention are as follows:

[0008] In a first aspect, the present invention provides an aircraft actuator simulation loading test platform, comprising an actuator test platform, a loading spring assembly, and a fixed rear support disposed on top of a fixed platform, wherein the actuator test platform and the fixed rear support are coaxially disposed and connected by a loading spring assembly capable of providing axial elastic force.

[0009] The actuator test bench includes a first base and a second base fixed to the upper surface of the fixed platform; the top of the first base is provided with a fixed support, a movable support and an actuator rear moving seat in sequence along the axial direction, the movable support and the actuator rear moving seat can slide axially along the first base, a stiffness simulator is provided between the movable support and the actuator rear moving seat, and the movable support is connected to the actuator rear moving seat through an adjusting screw; the top of the second base is slidably connected to the actuator front moving seat, and a grating scale is fixed on the side, and the reading head of the grating scale can move synchronously with the actuator front moving seat; an inertia simulator is provided on the side of the actuator front moving seat, and a measured actuator is provided between the actuator and the actuator rear moving seat, and the distance between the actuator front moving seat and the actuator rear moving seat can be changed by rotating the adjusting screw to adapt to the installation of actuators of different sizes to be measured.

[0010] Preferably, the loading spring group includes a loading spring, a force sensor, a spring seat and a first flange; several of the loading springs are arranged along the circumference of the spring seat, all the loading springs are arranged in parallel and the direction of the elastic force is the same as the axial direction of the spring seat, so as to realize bidirectional loading of tension and compression; the two ends of the spring seat are respectively connected to the force sensors at their respective ends through the first flange, and the force sensors are used to measure the elastic force of the loading spring during the test.

[0011] Furthermore, the loading spring is a rectangular spring.

[0012] Preferably, the first base and the second base are coaxially arranged with a gap between them; linear guide rails are coaxially arranged on the upper surfaces of the first base and the second base for realizing the sliding of the movable support, the actuator rear movable seat and the actuator front movable seat.

[0013] Preferably, both ends of the actuator to be tested are hinged to the actuator front moving seat and the actuator rear moving seat respectively through actuator supports.

[0014] Preferably, a handwheel is threadedly connected to the adjusting screw between the fixed support and the movable support.

[0015] Preferably, the stiffness simulator includes a second flange, a deformation plate and a joint; the two deformation plates are arranged in parallel and spaced apart, and the centers of the plate surfaces are detachably connected to the second flanges by nuts; the second flange is located on the outside of the deformation plate and is connected to the rear movable seat or movable support of the actuator; the upper and lower parts of the plate surface of the deformation plate are respectively provided with strip holes, and the strip holes are slidably connected with joints, and the joints are fixed in position in the strip holes by nuts; the two deformation plates are hinged to each other between the joints on the same side.

[0016] Preferably, the inertia simulator comprises an inertia weight installation frame and weights; the inertia weight installation frame is fixedly connected to the side of the actuator front moving seat and has a groove structure, in which a plurality of weights are detachably loaded.

[0017] Preferably, the actuator front movable seat, the actuator to be tested, the actuator rear movable seat, the stiffness simulator, the movable support and the fixed support are coaxially arranged in sequence along the horizontal direction.

[0018] In a second aspect, the present invention provides a testing method using any of the aircraft actuator simulation loading test platforms described in the first aspect, specifically as follows:

[0019] The fixed rear support is connected to the outer side of the actuator rear movable seat of the actuator test bench by loading the spring group; the stiffness simulator is adjusted to the stiffness required for the test by adjusting the position of the joint in the long hole of the stiffness simulator, and then the stiffness simulator is installed between the movable support and the actuator rear movable seat; the adjusting screw is turned to make the actuator rear movable seat slide along the linear guide rail of the first base to adjust the distance between the actuator rear movable seat and the actuator front movable seat, and then the two ends of the actuator to be tested are respectively connected through the actuator support and the actuator The rear movable seat of the inertia simulator is connected to the front movable seat of the actuator, so that the fixed rear support, the loading spring group, the front movable seat of the actuator, the actuator under test, the rear movable seat of the actuator, the stiffness simulator, the movable support and the fixed support are coaxially arranged; the mass of the weight in the inertia simulator is changed to obtain the required inertia size, and the installation position and zero point of the grating scale and the force sensor in the loading spring group are calibrated; the aircraft actuator simulation loading test platform is started, the data obtained from the grating scale and the force sensor are recorded and analyzed, and the test of the actuator under test is completed.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] 1) The platform of the present invention can simulate the actual working state of the actuator to perform loading tests, obtain more accurate working data, and make the test results more real and reliable; 2) The present invention can quickly adjust the stiffness and inertia with high efficiency and safety, reduce fastener damage, and alleviate the burden on workers; 3) The platform of the present invention adopts a combination of rigid tooling and flexible tooling, which can quickly reconstruct and adjust the positioner to adapt to different actuator shapes, eliminating a lot of special tooling and greatly shortening the actuator loading test process time; 4) The platform of the present invention has a compact structure, is sturdy and durable, and saves installation space. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 This is a schematic diagram of an aircraft actuator simulation loading test platform;

[0023] Figure 2 is an axonometric view of the loaded spring group;

[0024] Figure 3 It is an axonometric view of the actuator test bench;

[0025] Figure 4 is the axonometric view of the stiffness simulator;

[0026] Figure 5 It is an axonometric view of the inertia simulator;

[0027] The accompanying drawings in the figure are marked as: actuator test bench 101, fixed platform 102, loading spring group 103, fixed rear support 104, loading spring 105, force sensor 106, spring seat 107, first flange 108, first base 1, second base 2, linear guide 3, fixed support 4, movable support 5, adjusting screw 6, handwheel 7, actuator rear moving seat 8, actuator support 9, actuator front moving seat 10, actuator under test 11, grating scale 12, inertia simulator 13, stiffness simulator 14, second flange 15, nut 16, deformation plate 17, joint 18, inertia weight mounting frame 19, weight 20. DETAILED DESCRIPTION

[0028] The present invention will be further described and illustrated below with reference to the accompanying drawings and specific embodiments. The technical features of each embodiment of the present invention may be combined accordingly, provided that there is no conflict between them.

[0029] The present invention provides an aircraft actuator simulation loading test platform, which mainly includes an actuator test bench 101, a fixed platform 102, a loading spring group 103 and a fixed rear support 104.

[0030] The structure and connection method of each component will be described in detail below.

[0031] In the present invention, Figure 1As shown, the actuator test bench 101, the loading spring group 103 and the fixed rear support 104 are all arranged on the top of the fixed platform 102. The actuator test bench 101 and the fixed rear support 104 are coaxially arranged and connected by the loading spring group 103. The loading spring group 103 can provide axial elastic force during the test process.

[0032] As a preferred embodiment of the present invention, the fixed platform 102 utilizes a welded steel plate structure, which is sturdy and durable, capable of withstanding weight and vibration, resisting deformation during actuator testing, and meeting the requirements for combined actuator loading testing. The fixed rear support 104 secures the mounting position of the loading spring assembly 103 and is sturdy and durable, capable of withstanding the bidirectional loading forces of the loading spring assembly 103 during testing.

[0033] As a preferred embodiment of the present invention, Figure 2 As shown, the loading spring assembly 103 primarily comprises a loading spring 105, a force sensor 106, a spring seat 107, and a first flange 108. Multiple loading springs 105 are arranged circumferentially around the spring seat 107. All loading springs 105 are arranged parallel to one another, and their elastic forces are aligned with the axial direction of the spring seat 107, enabling bidirectional loading in both tension and compression. First flanges 108 are mounted at each end of the spring seat 107, and force sensors 106 are mounted on the outer sides of each of the two first flanges 108. These force sensors 106 measure the elastic force of the loading springs 105 during testing, enabling real-time monitoring of force changes.

[0034] Specifically, the loading spring 105 may be a rectangular spring, thereby meeting the requirements of bidirectional loading of tension and compression, being able to withstand a loading force of 20 tons, and meeting the test requirements of the actuator under test.

[0035] In the present invention, Figure 3As shown, the actuator test bench 101 mainly includes a first base 1, a second base 2, a fixed support 4, a movable support 5, an actuator rear moving seat 8, an actuator front moving seat 10, a tested actuator 11, a grating ruler 12 and an inertia simulator 13. Among them, the first base 1 and the second base 2 are fixed to the upper surface of the fixed platform 102. The top of the first base 1 is provided with a fixed support 4, a movable support 5 and an actuator rear moving seat 8 in sequence along the axial direction. The movable support 5 and the actuator rear moving seat 8 can slide axially along the first base 1. A stiffness simulator 14 is provided between the movable support 5 and the actuator rear moving seat 8. The movable support 5 is connected to the actuator rear moving seat 8 through an adjusting screw 6. The top of the second base 2 is slidably connected to the actuator front moving seat 10, and a grating ruler 12 is fixed on the side. The reading head of the grating ruler 12 can move synchronously with the actuator front moving seat 10. An inertia simulator 13 is provided on the side of the actuator front moving seat 10, and a measured actuator 11 is provided between the actuator front moving seat 10 and the actuator rear moving seat 8. By rotating the adjusting screw 6, the distance between the actuator front moving seat 10 and the actuator rear moving seat 8 can be changed to adapt to the installation of measured actuators 11 of different sizes.

[0036] In a preferred embodiment of the present invention, the two ends of the actuator under test 11 are hingedly connected to the actuator front movable base 10 and the actuator rear movable base 8 via an actuator support 9, respectively, to ensure the installation and fixation of the actuator under test 11. The actuator support 9 can be replaced with different specifications and sizes to meet the requirements of different actuator interfaces. The mounting interface with the actuator (including the actuator under test 11, the actuator front movable base 10, and the actuator rear movable base 8) can be compatible with single-ear and double-ear structures.

[0037] As a preferred embodiment of the present invention, the first base 1 and the second base 2 are coaxially arranged with a gap therebetween. A linear guide 3 is provided on the upper surface of the first base 1 for sliding the movable support 5 and the actuator rear movable base 8 along the first base 1; a linear guide 3 is provided on the upper surface of the second base 2 for sliding the actuator front movable base 10 along the second base 2. The two linear guides 3 provided on the first base 1 and the second base 2 are coaxial, enabling the movable support 5, the actuator rear movable base 8, and the actuator front movable base 10 to remain coaxial during sliding.

[0038] As a preferred embodiment of the present invention, a handwheel 7 is threadedly connected to the adjustment screw 6 between the fixed support 4 and the movable support 5. In actual use, the handwheel 7 can be operated to rotate the nut mounted on the fixed support 4, thereby moving the screw 6 and the movable support 5 forward and backward, causing the stiffness simulator 14 and the actuator rear movable base 8 to move together, facilitating the installation of actuators 9 of different lengths and sizes, thereby meeting the requirement for adjustable bracket installation position.

[0039] As a preferred embodiment of the present invention, the grating ruler 12 is installed on the side of the front moving seat 10 of the actuator, which can save space and accurately obtain the displacement during the test process.

[0040] In a preferred embodiment of the present invention, the first and second bases 1 and 2 utilize a welded steel plate structure, ensuring durability and preventing loosening and breakage during installation and testing. Furthermore, wiring holes and troughs are provided on the sides of the first and second bases 1 and 2 to facilitate the routing of test bench cables based on the power requirements of the force sensor 106 and the actuator under test 11.

[0041] As a preferred embodiment of the present invention, Figure 4 As shown, the stiffness simulator 14 can adjust the stiffness of the stiffness simulator by adjusting the position of the joint between the deformation plates, and mainly includes a second flange 15, a deformation plate 17 and a joint 18. Specifically, the two deformation plates 17 are parallel and arranged at a certain interval, and the centers of the plate surfaces of the two deformation plates 17 are detachably connected to the second flange 15 through nuts 16. The second flange 15 is located on the outside of the deformation plate 17 and is connected to the rear movable seat 8 or the movable support 5 of the actuator. Strip holes are respectively provided on the upper and lower parts of the plate surface of the deformation plate 17, and a joint 18 is slidably connected in the strip hole. The joint 18 is fixed in position in the strip hole by the nut 16. The two deformation plates 17 are hinged to each other between the joints 18 on the same side.

[0042] As a preferred embodiment of the present invention, Figure 5 As shown, the inertia simulator 13 can adjust the inertia by adjusting the quantity, quality, and position of the weights 20. The inertia simulator 13 primarily comprises an inertia weight mounting frame 19 and weights 20. The inertia weight mounting frame 19 is fixedly connected to the side of the actuator's front moving base 10 and comprises a recessed structure. Multiple weights 20 are removably mounted within the frame. During use, the inertia is adjusted by varying the quantity, quality, and mounting position of the weights.

[0043] As a preferred embodiment of the present invention, the actuator front movable seat 10, the tested actuator 11, the actuator rear movable seat 8, the stiffness simulator 14, the movable support 5 and the fixed support 6 are coaxially arranged in sequence along the horizontal direction.

[0044] The specific working principle of the present invention is as follows:

[0045] The actuator test structure of the present invention is mainly composed of a stiffness simulator, an inertia simulator, and a grating ruler. The stiffness adjustment of the stiffness simulator can be achieved by changing the position of the joint between the deformed plates, which has high reliability, simple operation, and a large stiffness adjustment range. The stiffness simulator can also move the movable support by a handwheel to match the installation of actuators of different sizes, thereby achieving adjustable installation position. The inertia adjustment of the inertia simulator can be achieved by changing the number, mass, and position of the weights, which is simple to operate, has a long service life, high accuracy, and can be adjusted at any time. The grating ruler is installed on the side of the front movable seat of the actuator, and the displacement can be accurately obtained. The actuator testing method is to connect the actuator test bench and the fixed rear support using a loading spring group, which can realize tensile and compression bidirectional loading tests. The force sensor outside the loading spring group can obtain the change in force during the test. The fixed platform withstands the vibration and weight during the actuator joint loading test, and is sturdy and durable.

[0046] The working process of the aircraft actuator simulation loading test platform of the present invention is roughly as follows:

[0047] 1. Fix the fixed platform on the ground;

[0048] 2. Install the actuator test bench and the fixed rear support on the fixed platform and connect them through the loading spring group;

[0049] 3. Fix the actuator to be tested between the front moving seat and the rear moving seat of the actuator through the actuator support;

[0050] 4. Calibrate the installation position and zero point of the grating scale and force sensor before measurement;

[0051] 5. Install the stiffness simulator and adjust the position of the joints between the deformed plates to the required stiffness for the test;

[0052] 6. Install the inertia simulator, add appropriate weights to the weight installation frame, and fix them in the appropriate position to obtain the required inertia;

[0053] 7. Install the bolts to complete the positioning and assembly of the actuator test bench;

[0054] 8. Start the aircraft actuator simulation test platform, record and analyze the data obtained by the grating scale and force sensor, and complete the test of the actuator under test.

[0055] Specifically, the working process is as follows:

[0056] The fixed rear support 104 is docked and connected to the outer side of the actuator rear movable seat 8 of the actuator test bench 101 via a loading spring assembly 103. By adjusting the position of the joint 18 in the elongated hole of the stiffness simulator 14, the stiffness simulator 14 is adjusted to the required stiffness for the test. The stiffness simulator 14 is then installed between the movable support 5 and the actuator rear movable seat 8. The adjusting screw 6 is rotated to slide the actuator rear movable seat 8 along the linear guide rail of the first base 1 to adjust the distance between the actuator rear movable seat 8 and the actuator front movable seat 10. The two ends of the actuator to be tested 11 are then connected to the actuator rear movable seat 8 and the actuator front movable seat 10 via the actuator support 9, respectively, so that the fixed rear support 104, the loading spring assembly 103, the actuator front movable seat 10, the actuator to be tested 11, the actuator rear movable seat 8, the stiffness simulator 14, the movable support 5, and the fixed support 6 are coaxially arranged. The mass of the weight 20 in the inertia simulator 13 is changed to obtain the desired inertia. The installation position and zero point of the grating scale 12 and the force sensor 106 in the loading spring assembly 103 are calibrated. The aircraft actuator simulated loading test platform is activated, and the data obtained from the grating scale 12 and the force sensor 106 are recorded and analyzed to complete the test of the actuator 11 under test.

[0057] This invention simulates the actual operating state of an actuator during loading tests, obtaining more accurate operating data and ensuring more reliable test results. The simulation platform utilizes a combination of rigid and flexible tooling, resulting in a compact, durable structure. The positioner can be quickly reconfigured and adjusted to accommodate different actuator shapes, significantly shortening the actuator loading test process.

[0058] The embodiment described above is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Persons skilled in the art may make various changes and modifications without departing from the spirit and scope of the present invention. Therefore, any technical solution obtained by equivalent substitution or equivalent transformation falls within the scope of protection of the present invention.

Claims

1. An aircraft actuator simulation loading test platform, characterized in that: The invention comprises an actuator test bench (101), a loading spring group (103) and a fixed rear support (104) arranged on the top of a fixed platform (102); the actuator test bench (101) and the fixed rear support (104) are coaxially arranged and connected via a loading spring group (103) capable of providing axial elastic force; The actuator test bench (101) comprises a first base (1) and a second base (2) fixed to the upper surface of a fixed platform (102); a fixed support (4), a movable support (5) and an actuator rear movable seat (8) are sequentially provided on the top of the first base (1) along the axial direction; the movable support (5) and the actuator rear movable seat (8) can slide axially along the first base (1); a stiffness simulator (14) is provided between the movable support (5) and the actuator rear movable seat (8); the movable support (5) is connected to the actuator rear movable seat (8) by adjusting the screw (6) ) connection; the top of the second base (2) is slidably connected to the actuator front moving seat (10), and a grating ruler (12) is fixed on the side, and the reading head of the grating ruler (12) can move synchronously with the actuator front moving seat (10); an inertia simulator (13) is provided on the side of the actuator front moving seat (10), and a measured actuator (11) is provided between the actuator front moving seat (10) and the actuator rear moving seat (8), and the distance between the actuator front moving seat (10) and the actuator rear moving seat (8) can be changed by rotating the adjusting screw (6) to adapt to the installation of measured actuators (11) of different sizes.

2. The aircraft actuator simulation loading test platform according to claim 1, characterized in that: The loading spring group (103) comprises a loading spring (105), a force sensor (106), a spring seat (107) and a first flange (108); a plurality of the loading springs (105) are arranged along the circumference of the spring seat (107), all the loading springs (105) are arranged in parallel and the elastic force direction is the same as the axial direction of the spring seat (107), so as to realize bidirectional loading of tension and compression; the two ends of the spring seat (107) are respectively connected to the force sensors (106) at their respective ends through the first flange (108), and the force sensors (106) are used to measure the elastic force of the loading spring (105) during the test.

3. The aircraft actuator simulation loading test platform according to claim 2, characterized in that: The loading spring (105) is a rectangular spring.

4. The aircraft actuator simulation loading test platform according to claim 1, characterized in that: The first base (1) and the second base (2) are coaxially arranged with a gap therebetween; a linear guide rail (3) is coaxially arranged on the upper surfaces of the first base (1) and the second base (2) for realizing the sliding of the movable support (5), the actuator rear movable seat (8) and the actuator front movable seat (10).

5. The aircraft actuator simulation loading test platform according to claim 1, characterized in that: The two ends of the actuator (11) to be tested are respectively hinged to the actuator front moving seat (10) and the actuator rear moving seat (8) through the actuator support (9).

6. The aircraft actuator simulation loading test platform according to claim 1, characterized in that: A hand wheel (7) is threadedly connected to the adjusting screw (6) between the fixed support (4) and the movable support (5).

7. The aircraft actuator simulation loading test platform according to claim 1, characterized in that: The stiffness simulator (14) includes a second flange (15), a deformation plate (17) and a joint (18); the two deformation plates (17) are arranged in parallel and spaced apart, and the center of the plate surface is detachably connected to the second flange (15) through a nut (16); the second flange (15) is located on the outside of the deformation plate (17) and is connected to the actuator rear movable seat (8) or the movable support (5); the upper and lower parts of the plate surface of the deformation plate (17) are respectively provided with strip holes, and the strip holes are slidably connected with the joint (18), and the joint (18) is fixed in position in the strip holes by the nut (16); the two deformation plates (17) are hinged to each other between the joints (18) located on the same side.

8. The aircraft actuator simulation loading test platform according to claim 1, characterized in that: The inertia simulator (13) comprises an inertia weight installation frame (19) and weights (20); the inertia weight installation frame (19) is fixedly connected to the side of the actuator front moving seat (10), is a groove structure, and has a plurality of weights (20) detachably loaded therein.

9. The aircraft actuator simulation loading test platform according to claim 1, characterized in that: The actuator front movable seat (10), the actuator to be tested (11), the actuator rear movable seat (8), the stiffness simulator (14), the movable support (5) and the fixed support (4) are coaxially arranged in sequence along the horizontal direction.

10. A testing method using the aircraft actuator simulation loading test platform according to any one of claims 1 to 9, characterized in that: The details are as follows: The fixed rear support (104) is docked and connected to the outer side of the actuator rear movable seat (8) of the actuator test bench (101) by loading the spring group (103); the stiffness simulator (14) is adjusted to the stiffness required for the test by adjusting the position of the joint (18) in the long hole of the stiffness simulator (14), and then the stiffness simulator (14) is installed between the movable support (5) and the actuator rear movable seat (8); the adjusting screw (6) is rotated to make the actuator rear movable seat (8) slide along the linear guide rail of the first base (1) to adjust the distance between the actuator rear movable seat (8) and the actuator front movable seat (10), and then the two ends of the actuator (11) to be tested are respectively connected through the actuator support (9) and the actuator rear movable seat (8) is connected to the actuator front movable seat (10), so that the fixed rear support (104), the loading spring group (103), the actuator front movable seat (10), the actuator to be tested (11), the actuator rear movable seat (8), the stiffness simulator (14), the movable support (5) and the fixed support (4) are coaxially arranged; the mass of the weight (20) in the inertia simulator (13) is changed to obtain the required inertia size, and the installation position and zero point of the grating ruler (12) and the force sensor (106) in the loading spring group (103) are calibrated; the aircraft actuator simulation loading test platform is started, the data obtained by the grating ruler (12) and the force sensor (106) are recorded and analyzed, and the test of the actuator to be tested (11) is completed.

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