Aircraft actuator simulation loading test platform and method

Abstract

The invention discloses an aircraft actuator simulation loading test platform and method, and relates to the field of control systems. The platform comprises an actuator test board arranged at the top of the fixed platform, a loading spring group and a fixed rear support; in the actuator test bench, the top of a first base is sequentially provided with a fixed support, a movable support, a rigidity simulator and an actuator rear moving seat in the axial direction, the top of a second base is slidably connected with an actuator front moving seat, a grating ruler and an inertia simulator are fixed to the side face of the second base, and a tested actuator is arranged between the actuator front moving seat and the actuator rear moving seat. According to the invention, the real working state of the actuator can be simulated in the loading test, more accurate working data can be obtained, and the test result is more real and reliable. The platform adopts a mode of combining a rigid tool and a flexible tool, is compact in structure, firm and durable, can quickly reconstruct and adjust the positioner so as to adapt to different actuator appearances, and greatly shortens the time of an actuator loading test process.

Description

Technical Field

[0001] The 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] The actuator is a key component for implementing active vibration control and an important part of the active control system. Its function is to exert control force on the controlled object according to the determined control law. The traditional actuator testing method is manual reading and manual recording, which is inefficient, labor-intensive, and the obtained test results are inaccurate, which is difficult to meet the needs of today's actual production and life. Researching actuator testing schemes has important engineering application value and practical significance.

[0003] Foreign countries have conducted research on actuator systems earlier. Lockheed Corporation in the United States installed actuators with different system structures and power levels on transport aircraft C130 and C141 for testing and research. Airbus A380 is a commercial wide-body aircraft. The use of actuators reduces the weight of the aircraft, bringing better flight control performance and higher safety margins to the aircraft. Some researchers designed a prototype with a fixed displacement and variable speed configuration for testing, and verified the dynamic performance and advantages of the symmetrical actuator system through experiments.

[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 successfully applied electric hydrostatic actuators to hydraulic elevators and injection molding machines. Beihang University analyzed actuators for different applications, and the research content covered simulation analysis and actuator algorithm optimization, and achieved certain research results. Taiyuan University of Technology solved the problems of decreased control performance and energy saving caused by the flow asymmetry of the asymmetric cylinder of the actuator. Beihang University used a spring test bench to complete the loading test of the electric hydrostatic actuator and conducted a dynamic performance test.

[0005] Although a lot of experimental research has been conducted in the structural design, manufacturing process, control algorithm and other aspects of the actuator at home and abroad, and certain results have been achieved. However, in terms of the loading test of the actuator, current researchers rarely combine the actual working conditions of the actuator to carry out loading tests during the test process, making it difficult to obtain accurate test data. Therefore, it is necessary to design a loading platform for the actuator, carry out loading tests on the actuator in combination with the actual working conditions, and analyze the actual performance of the actuator in combination with the collected data. Summary of the invention

[0006] The purpose of the present invention is to overcome the defects in the prior art and provide an aircraft actuator simulation loading test platform and method. The present invention solves the problems of inconvenient manual operation, low accuracy and low efficiency in the actuator testing process. The simulation platform is easy and fast to adjust, suitable for real-time simulation of various actuators, and has a secure and reliable locking, which greatly reduces the test burden.

[0007] The specific technical solutions adopted by 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 group and a fixed rear support arranged on the top of a fixed platform, wherein the actuator test platform and the fixed rear support are coaxially arranged and connected via a loading spring group capable of providing axial elastic force;

[0009] The actuator test bench includes a first base and a second base fixed on the upper surface of a fixed platform; a fixed support, a movable support and a rear movable seat of the actuator are sequentially arranged on the top of the first base along the axial direction, the movable support and the rear movable seat of the actuator can slide axially along the first base, a stiffness simulator is arranged between the movable support and the rear movable seat of the actuator, and the movable support is connected to the rear movable seat of the actuator through an adjusting screw; a front movable seat of the actuator is slidably connected to the top of the second base, a grating ruler is fixed on the side, and a reading head of the grating ruler can move synchronously with the front movable seat of the actuator; an inertia simulator is arranged on the side of the front movable seat of the actuator, and a measured actuator is arranged between the front movable seat of the actuator and the rear movable seat of the actuator, and the distance between the front movable seat of the actuator and the rear movable seat of the actuator 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; a plurality 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 to achieve 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 sensor is 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 therebetween; 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, two ends of the tested actuator are respectively hinged to the actuator front moving seat and the actuator rear moving seat through the actuator support.

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

[0015] Preferably, the stiffness simulator comprises a second flange, a deformation plate and a joint; the two deformation plates are arranged in parallel and spaced apart, and the center of the plate surface is detachably connected to the second flange 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 the strip holes by nuts; the two deformation plates are hinged to each other between the joints located 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 front moving seat of the actuator and is a groove structure, in which a plurality of weights are detachably loaded.

[0017] Preferably, the actuator front moving seat, the tested actuator, the actuator rear moving 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, which is as follows:

[0019] The fixed rear support is connected to the outer side of the actuator rear moving 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 moving seat; the adjusting screw is turned to make the actuator rear moving seat slide along the linear guide rail of the first base to adjust the distance between the actuator rear moving seat and the actuator front moving seat, and then the two ends of the actuator to be tested are respectively connected through the actuator support and the actuator front moving seat. The rear moving seat of the inertia simulator is connected with the front moving seat of the actuator, so that the fixed rear support, the loading spring group, the front moving seat of the actuator, the actuator to be tested, the rear moving 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 by the grating scale and the force sensor are recorded and analyzed, and the test of the actuator to be tested 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 reduce 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 It is a schematic diagram of the aircraft actuator simulation loading test platform;

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

[0024] Figure 3 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 the axonometric view of the inertia simulator;

[0027] The reference numerals in the figure are: 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, tested actuator 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 is further described and illustrated below in conjunction with the accompanying drawings and specific embodiments. The technical features of each embodiment of the present invention can be combined accordingly without conflicting with each other.

[0029] The present invention provides an aircraft actuator simulation loading test platform, which mainly comprises 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, if 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.

[0032] As a preferred embodiment of the present invention, the fixed platform 102 adopts a steel plate welding structure, which is strong and durable, can withstand weight and vibration, resist deformation during actuator testing, and meet the test requirements of actuator joint loading. The fixed rear support 104 can fix the installation position of the loading spring group 103, is strong and durable, and can withstand the bidirectional loading force of the loading spring group 103 during the test.

[0033] As a preferred embodiment of the present invention, Figure 2 As shown, the loading spring group 103 mainly includes a loading spring 105, a force sensor 106, a spring seat 107 and a first flange 108. Multiple loading springs 105 are arranged along the circumference of the spring seat 107, and all loading springs 105 are arranged in parallel with each other and the elastic force direction is the same as the axial direction of the spring seat 107, thereby realizing tension and compression bidirectional loading. First flanges 108 are respectively installed at both ends of the spring seat 107, and force sensors 106 are respectively installed on the outside of the two first flanges 108. The force sensor 106 is used to measure the elastic force of the loading spring 105 during the test, and can obtain the change of force in real time.

[0034] Specifically, the loading spring 105 can be a rectangular spring, so as to meet the requirements of bidirectional loading of tension and compression, and can withstand a loading force of 20 tons, thus meeting the test requirements of the actuator under test.

[0035] In the present invention, if 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] As a preferred embodiment of the present invention, the two ends of the tested actuator 11 are respectively hinged with the actuator front moving seat 10 and the actuator rear moving seat 8 through the actuator support 9 to meet the installation and fixation of the tested actuator 11. The actuator support 9 can be replaced with different specifications and sizes to meet the requirements of different actuator interfaces, and the installation interface with the actuator (including the tested actuator 11, the actuator front moving seat 10 and the actuator rear moving seat 8) can match the 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 arranged on the upper surface of the first base 1 for realizing the sliding of the movable support 5 and the actuator rear movable seat 8 along the first base 1; a linear guide 3 is arranged on the upper surface of the second base 2 for realizing the sliding of the actuator front movable seat 10 along the second base 2. The two linear guides 3 arranged on the first base 1 and the second base 2 are coaxial, which can make the movable support 5, the actuator rear movable seat 8 and the actuator front movable seat 10 always remain coaxial when sliding.

[0038] As a preferred embodiment of the present invention, a hand wheel 7 is threadedly connected to the adjusting screw 6 between the fixed support 4 and the movable support 5. In actual use, the hand wheel 7 can be operated to rotate the nut installed on the fixed support 4, move the screw 6, and move the movable support 5 forward and backward, so that the stiffness simulator 14 and the actuator rear movable seat 8 move together, so as to install the actuators 9 of different lengths and sizes to meet the requirement that the bracket installation position can be adjusted.

[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.

[0040] As a preferred embodiment of the present invention, the first base 1 and the second base 2 are welded steel plates to meet the characteristics of being strong and durable, and to avoid loosening and damage during installation and testing. In addition, wiring holes and wiring grooves are provided on the sides of the first base 1 and the second base 2, which can meet the requirements of the bench debugging cable arrangement according to the power supply requirements of the force sensor 106 and the actuator 11 under test.

[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 outer side of the deformation plate 17 and is connected to the rear movable seat 8 or the movable support 5 of the actuator. The upper and lower parts of the plate surface of the deformation plate 17 are respectively provided with strip holes, and the joints 18 are slidably connected in the strip holes, and the joints 18 are fixed in position in the strip holes by nuts 16. The two deformation plates 17 are hinged to each other between the joints 18 located 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 mainly includes 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 and is a groove structure. A plurality of weights 20 are detachably loaded inside. When in use, the inertia adjustment function is achieved by changing the quantity, quality and installation position of the weights.

[0043] As a preferred embodiment of the present invention, the actuator front moving seat 10, the tested actuator 11, the actuator rear moving 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 hand wheel to match the installation of actuators of different sizes, so that the installation position can be adjusted. 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 with a loading spring group, so as to realize tensile and compressive 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 dock them through the loading spring group;

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

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

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

[0052] 6. Install the inertia simulator, add appropriate amount of 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 connected to the outer side of the actuator rear moving seat 8 of the actuator test bench 101 by docking through the loading spring group 103. The stiffness simulator 14 is adjusted to the required stiffness 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 moving seat 8. The adjusting screw 6 is rotated to make the actuator rear moving seat 8 slide along the linear guide rail of the first base 1 to adjust the distance between the actuator rear moving seat 8 and the actuator front moving seat 10, and then the two ends of the actuator 11 to be tested are connected to the actuator rear moving seat 8 and the actuator front moving seat 10 through the actuator support 9, respectively, so that the fixed rear support 104, the loading spring group 103, the actuator front moving seat 10, the actuator 11 to be tested, the actuator rear moving 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 required inertia, 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, and the data obtained by the grating ruler 12 and the force sensor 106 are recorded and analyzed to complete the test of the actuator 11 under test.

[0057] The present invention can simulate the real working state of the actuator in the loading test, obtain more accurate working data, and make the test results more real and reliable. The simulation 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.

[0058] The above-described embodiment is only a preferred solution of the present invention, but it is not intended to limit the present invention. A person skilled in the relevant technical field may make various changes and modifications without departing from the spirit and scope of the present invention. Therefore, any technical solution obtained by equivalent replacement or equivalent transformation falls within the protection scope 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 arranged 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 arranged 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 a screw rod (6) ) connection; the second base (2) is slidably connected to the top of 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 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 tension and compression bidirectional loading; 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; the upper surfaces of the first base (1) and the second base (2) are coaxially arranged with linear guide rails (3) 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) comprises 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 outer side 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 joint (18) is slidably connected in the strip hole, and the joint (18) is fixed in position in the strip hole through a 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) and is a groove structure, with a plurality of weights (20) detachably loaded inside.

9. The aircraft actuator simulation loading test platform according to claim 1, characterized in that: The actuator front moving seat (10), the tested actuator (11), the actuator rear moving seat (8), the stiffness simulator (14), the movable support (5) and the fixed support (6) are coaxially arranged in sequence along the horizontal direction.

10. A test 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 connected to the outer side of the actuator rear movable seat (8) of the actuator test bench (101) by loading a 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); 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); 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) connected to the actuator front moving seat (10), so that the fixed rear support (104), the loading spring group (103), the actuator front moving seat (10), the actuator (11) to be tested, the actuator rear moving 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 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 (11) to be tested is completed.

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