A flight control actuator inner hole coating service performance evaluation system and method

Abstract

The present invention is a system and method for evaluating the service performance of the inner hole coating of a flight control actuator, which belongs to the field of detection devices for aircraft; it includes an actuator sample, a variable piston module, and an abrasive particle lifting module; the inner hole wall of the actuator sample is provided with a wear-resistant coating as the object to be evaluated; the variable piston module is suitable for testing actuators of different apertures by adjusting the radial size; the variable piston module is placed in the inner hole of the actuator sample, and is controlled by a driving module to reciprocate axially in the inner hole of the actuator sample, thereby generating friction with the inner hole coating of the actuator sample; the abrasive particle lifting module is installed at the bottom of the actuator, and is driven to rotate by the flow of lubricating oil in the actuator, and the abrasive particles sunk to the bottom are lifted by rotation to simulate the abrasive wear of the actuator during actual use. The present invention solves the need to evaluate the performance of the inner hole coating of the actuator, and at the same time realizes the versatility of the piston through the variable piston module.

Description

Technical Field

[0001] The invention belongs to the field of aircraft detection devices, and in particular relates to a system and method for evaluating the service performance of a coating on an inner hole of a flight control actuator. Background Art

[0002] The actuating cylinder of an aircraft engine is a key transmission component of the flight control system. Its structure is mainly composed of cylinder, piston, piston rod, flow regulator, nozzle and other parts. Its main function is to drive the piston to reciprocate through the pressure difference at both ends of the piston, and then the piston rod drives the actuator to move, thereby changing the nozzle cross-sectional area. The performance and life of the actuator directly affect the performance and life of the engine, and then affect the maneuverability and safety of the aircraft.

[0003] In order to improve the service life of the actuator, a wear-resistant coating can be prepared on the inner hole of the actuator to solve the problems of corrosion and wear that may occur during the operation of the actuator. With the development of new surface coating technologies such as PVD, flame spraying, and laser cladding, the development of coatings for the inner holes of actuators has become a new research hotspot, which brings about a new problem, that is, how to quickly, conveniently and accurately detect and evaluate the performance of the coating and predict its service life. At present, the life test of the actuator coating is mostly flight test, which has a long test cycle and high cost, which significantly affects the research and development progress of coating design and optimization, that is, the performance and life of the developed actuator coating cannot be evaluated in time.

[0004] Currently, when performing life tests on actuator coatings, it is necessary to design test specimens based on the actuator model being tested. The piston used is a fixed structure and cannot be applied to test experiments on different actuators, resulting in high testing costs. In addition, the actual abrasive wear cannot be simulated during the test, resulting in errors in the life test results.

[0005] Therefore, it is necessary to provide a flight control actuator inner hole coating service performance evaluation system to solve the above problems. Summary of the invention

[0006] Technical issues to be solved:

[0007] In order to avoid the shortcomings of the prior art, the present invention provides a system and method for evaluating the service performance of the inner hole coating of a flight control actuator. By simulating temperature changes and wear environments, the use environment of the inner hole coating of the actuator can be accurately simulated, so as to evaluate the performance of the coating in the simulated environment to meet the need for evaluating the performance of the inner hole coating of the actuator. At the same time, the universality of the test piston is achieved through the variable piston module, which can shorten the development time of the flight control actuator as a whole and reduce the development cost.

[0008] The technical solution of the present invention is: a flight control actuator inner hole coating service performance evaluation system, including an actuator sample, a variable piston module, and an abrasive lifting module.

[0009] The inner hole wall of the actuator cylinder sample is provided with a wear-resistant coating, which is used as the object to be evaluated; the cylinder wall is provided with an oil inlet and an oil outlet for injecting lubricating oil required for actuation;

[0010] The variable piston module is suitable for testing actuators with different bore diameters by adjusting the radial dimension; the variable piston module is placed in the inner bore of the actuator sample, and is controlled by the driving module to reciprocate along the axial direction in the inner bore of the actuator sample, thereby generating friction with the coating of the inner bore of the actuator sample;

[0011] The abrasive particle lifting module is installed at the bottom of the actuator cylinder and is driven to rotate by the flow of lubricating oil in the actuator cylinder. The abrasive particles sunk to the bottom are lifted by rotation to simulate the abrasive wear during the actual use of the actuator cylinder.

[0012] A further technical solution of the present invention is: the variable piston module includes a piston with adjustable outer diameter and a piston ring mounted on its outer circumference. The piston ring is designed in series, including piston rings of various materials and sizes, which are used to meet the detection requirements of actuators with different apertures, or to complete comparative detection of grinding materials by replacing piston rings of different materials.

[0013] A further technical solution of the present invention is: the outer diameter adjustable piston includes a piston rod and a separate piston installed on its head, the separate piston includes a plurality of separate piston units arranged along the circumferential direction, each separate piston unit is installed on the circumferential surface of the piston rod head through a movable connection component, and the movable connection component is used to realize the contraction and outward expansion toward the piston rod to obtain an outer circumferential surface with different radial sizes; the end of the piston rod is connected to the drive module.

[0014] A further technical solution of the present invention is that the radial cross section of the split piston unit is fan-shaped, and each split piston unit forms an integral circular ring when folded, and its inner and outer arc surfaces are respectively located on the same circumferential surface when expanded.

[0015] A further technical solution of the present invention is: the movable connection assembly includes a piston groove, a pulley, and a piston connecting rod; the piston groove is an axial groove uniformly distributed on the piston rod head along the circumferential direction, and its number and position correspond one-to-one to the separate piston unit; one end of the piston connecting rod is slidingly hinged to the piston groove through a pulley, and the other end is hinged to the separate piston unit; when the axial position of the separation piston in the piston rod remains unchanged, the radial size of the separation piston is adjusted by adjusting the sliding position of one end of the piston connecting rod in the piston groove to adapt to actuators of different apertures; after adjustment into place, a locking mechanism is used to position it.

[0016] A further technical solution of the present invention is that the actuating cylinder is fixedly mounted on the base plate by a clamp, and its axial direction is perpendicular to the base plate.

[0017] A further technical solution of the present invention is: it also includes a piston motion limit module, which is arranged parallel to and opposite to the actuator cylinder, and is provided with a piston limit groove parallel to the axial direction of the actuator cylinder, and an adapter slider is slidably connected in the piston limit groove; one end of the slider is vertically connected to the end of the piston rod through a connecting rod, and the other end is connected to the driving module; the reciprocating motion of the slider is controlled by the driving module, and the motion trajectory stroke of the slider is limited by the piston limit groove, so that the piston rod completes reciprocating motion within the set stroke.

[0018] A further technical solution of the present invention is: the abrasive lifting module includes a rotating shaft and a plurality of fan blades evenly distributed around the shaft, and the rotating shaft is rotatably connected to the bottom of the actuator.

[0019] A method for evaluating the service performance of the inner hole coating of a flight control actuator cylinder, the specific steps are as follows:

[0020] Measure the inner hole size of the actuator sample to be tested, and adjust the radial size of the deformable piston module according to the inner hole size;

[0021] Building the flight control actuator inner hole coating service performance evaluation system and fixing the actuator specimen;

[0022] Lubricating oil of different temperatures is input into the actuator through the actuator oil inlet to simulate the working conditions of the actuator in different working environments;

[0023] Start the driving module to control the variable piston module to reciprocate in the actuator cylinder, and perform a wear test on the inner hole coating of the actuator cylinder;

[0024] The surface damage of the coating after the test was detected, and the service performance of the coating on the inner hole of the actuator was evaluated.

[0025] A further technical solution of the present invention is: the method for adjusting the radial size of the variable piston module is: first, selecting an adaptive piston ring according to the inner hole size of the actuator sample to be tested; then determining the maximum outer diameter of the separate piston according to the inner diameter size of the selected piston ring; thereafter, adjusting the radial distance between the separate piston unit and the piston rod by contraction / expansion, thereby obtaining the determined maximum outer diameter of the separate piston, thereby completing the adjustment of the radial size of the variable piston module; finally, positioning the movable connection assembly by a locking mechanism.

[0026] Beneficial Effects

[0027] The beneficial effects of the present invention are:

[0028] 1. The flight control actuator inner hole coating service performance evaluation system of the present invention is easy to install as a whole, and can simulate the working environment of the aircraft engine actuator in ground tests and detect the performance of its inner hole coating.

[0029] 2. The present invention adopts a variable piston module, changes the radial size of the piston by adjusting the piston connector, and designs the piston ring into a series of products of different sizes and different materials. By changing the size of the piston, piston rings of different sizes can be replaced to meet the detection requirements of actuators with different apertures; therefore, there is no need to design a separate piston structure for coating testing of actuators with different apertures, which reduces design time and design costs.

[0030] 3. The present invention can lift the abrasive particles that may be generated during the friction process through the abrasive lifting module, simulating the influence of abrasive wear on the inner hole coating; making the detection test closer to the actual applicable working conditions and improving the accuracy of the coating service performance evaluation. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 The present invention is a schematic structural diagram of a flight control actuator inner hole coating service performance evaluation system in an embodiment of the present invention.

[0032] Figure 2 Schematic diagram of the structure of the abrasive lifting module in an embodiment of the present invention.

[0033] Figure 3 It is a schematic diagram of the structure of a modified piston module in an embodiment of the present invention.

[0034] Explanation of the reference numerals in the accompanying drawings: 1. chuck body; 2. movable claw; 3. oil inlet of actuator; 4. actuator specimen; 5. piston rod; 6. connecting rod; 7. piston limit slide; 8. slider; 9. oil outlet of actuator; 10. bolt; 11. base plate; 12. fan blade; 13. piston ring; 14. piston slide; 15. pulley; 16. upper stop ring; 17. threaded rod; 18. piston connecting rod; 19. lower stop ring; 20. nut; 21. separate piston. DETAILED DESCRIPTION

[0035] The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, but should not be construed as limiting the present invention.

[0036] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0037] At present, when the life test of the actuator coating is carried out, it is necessary to design the test specimen based on the model of the tested actuator. The piston used is a fixed structure, which cannot be applied to different actuator test experiments, and the test cost is high. In addition, the real abrasive wear cannot be simulated during the test, which leads to errors in the life test results. The present invention provides a flight control actuator inner hole coating service performance evaluation system, including an actuator specimen, a deformable piston module, and an abrasive lifting module. The inner hole wall of the actuator specimen is provided with a wear-resistant coating as the object to be evaluated; the cylinder wall is opened There are an oil inlet and an oil outlet for injecting the lubricating oil required for actuation; the variable piston module is suitable for testing actuators of different apertures by adjusting the radial size; the variable piston module is placed in the inner hole of the actuator sample, and is controlled by the driving module to reciprocate axially in the inner hole of the actuator sample, thereby generating friction with the coating of the inner hole of the actuator sample; the abrasive particle lifting module is installed at the bottom of the actuator, and is driven to rotate by the flow of lubricating oil in the actuator, and the abrasive particles sunk to the bottom are lifted by rotation to simulate the abrasive wear of the actuator during actual use conditions.

[0038] It also includes a piston movement limit module, which is arranged parallel to and opposite to the actuator cylinder, and is provided with a piston limit slot parallel to the axial direction of the actuator cylinder, and an adaptor slider is slidably connected in the piston limit slot; one end of the slider is vertically connected to the end of the piston rod through a connecting rod, and the other end is connected to the driving module; the reciprocating motion of the slider is controlled by the driving module, and the motion trajectory stroke of the slider is limited by the piston limit slot, so that the piston rod completes the reciprocating motion within the set stroke.

[0039] Specifically, the variable piston module includes a piston with adjustable outer diameter and a piston ring mounted on its outer circumference. The piston ring is designed in series, including piston rings of various materials and sizes, which are used to meet the detection requirements of actuators with different apertures, or to complete comparative detection of grinding materials by replacing piston rings of different materials.

[0040] The outer diameter adjustable piston includes a piston rod and a separate piston installed on its head. The separate piston includes a plurality of separate piston units arranged along the circumferential direction. Each separate piston unit is installed on the circumferential surface of the piston rod head through a movable connection component. The movable connection component is used to realize the contraction and expansion toward the piston rod to obtain an outer circumferential surface with different radial sizes. The end of the piston rod is connected to the drive module.

[0041] The radial cross section of the separation piston unit is fan-shaped. When the separation piston units are folded together, they form an integral circular ring. When they are expanded outward, their inner and outer arc surfaces are respectively located on the same circumferential surface.

[0042] The movable connection assembly includes a piston groove, a pulley, and a piston connecting rod; the piston groove is an axial groove uniformly distributed on the piston rod head along the circumferential direction, and the number and position of the piston groove correspond to the separate piston unit one by one; one end of the piston connecting rod is slidingly hinged to the piston groove through a pulley, and the other end is hinged to the separate piston unit; when the axial position of the separate piston on the piston rod remains unchanged, the radial size of the separate piston is adjusted by adjusting the sliding position of one end of the piston connecting rod in the piston groove to adapt to actuators of different apertures; after adjustment, a locking mechanism is used to position it.

[0043] The above technical solution is further described below in conjunction with the accompanying drawings:

[0044] Reference Figure 1 As shown, the present embodiment is a flight control actuator inner hole coating service performance evaluation system, comprising a base plate 11, a fixture, an actuator sample 4, a deformable piston module, a piston motion limit module, and an abrasive lifting module; wherein the base plate 11 is used to fix the fixture and the piston motion limit module; the fixture uses a three-jaw chuck device to fix and clamp the actuator sample to prevent the sample from shaking during the test, resulting in uneven force on the inner hole coating when the piston moves, affecting the experimental results; the chuck body 1 of the three-jaw chuck is fixedly connected to the base plate 11 by a bolt structure, and the actuator sample 4 is placed on the chuck body 1, and is clamped and positioned by three movable jaws 2 to ensure that the actuator sample 4 is accurately positioned and the stability of the actuator sample 4 to be tested during the experiment is ensured;

[0045] The piston motion limiting module includes a connecting rod 6, a piston limiting slide groove 7, a slider 8, and a bolt 10. The piston limiting slide groove 7 is fixedly connected to the bottom plate 11 through a bolt structure. The slider 8 is installed in the piston limiting slide groove 7, one end of which is connected to the piston rod 5 through the connecting rod 6, and the other end is fixedly connected to the driving module. The piston rod 5 is driven by the connecting rod 6 to drive the piston device to move. When the reciprocating driving module drives the slider 8, due to the limitation of the piston limiting slide groove 7, the slider 8 moves along the piston limiting slide groove 7, so that the connecting rod 6 fixedly connected to the slider 8 and the piston device connected to the connecting rod 6 can only reciprocate in the vertical direction.

[0046] Reference Figure 3As shown, the deformable piston module includes a piston rod 5, a piston ring 13, a piston slide 14, a pulley 15, an upper stop ring 16, a threaded rod 17, a piston connecting rod 18, a lower stop ring 19, a nut 20, and a separate piston 21. The deformable piston module is installed in the actuator cylinder sample 4 and is connected to the slider 8 in the piston movement limit module through the connecting rod 6, so that the piston can only move in the vertical direction during movement, ensuring uniform friction between the piston device and the actuator cylinder sample 4. Among them, the piston slide 14, the pulley 15, and the piston connecting rod 18 constitute a movable connection assembly, and the upper stop ring 16, the threaded rod 17, the lower stop ring 19, the nut 20, and the separate piston 21 constitute a locking mechanism. The pulley 15 is rotatably connected to the piston connecting rod 18 through a rotating shaft, and is slidably connected to the piston slide 14 through the rotating shaft, so that the pulley 15 can roll and displace in the piston slide 14. Each separate piston unit in the separate piston 21 is connected to the piston rod 5 through the piston connecting rod 18, and the separate piston is expanded or contracted by the rolling of the pulley 15 in the piston groove 14. The locking mechanism cooperates with the movable connection component to limit its deformation or movement after positioning; the upper stop ring 16 and the lower stop ring 19 are respectively mounted on the piston rod 5 and on both sides of the pulley 15, and the upper ring surface of the lower stop ring 16 has a plurality of threaded blind holes in the circumferential direction, and the upper ring surface of the lower stop ring 19 has a plurality of through holes coaxial with the threaded blind holes in the circumferential direction; one end of the plurality of threaded rods 17 passes through the through holes of the lower stop ring 19 and is screwed into the threaded blind holes of the upper stop ring 16, and the other end is connected with a nut 20 by threading; when the radial size of the separate piston 21 is After confirmation, the nut 20 is rotated to push the lower stop ring to move upward and contact the lower part of the piston connecting rod 18. At this time, the roller 15 is in contact with the upper stop ring 16. When the separation piston 21 has an expansion tendency, the piston ring 13 will prevent it from expanding. When the separation piston 21 has a contraction tendency, its roller 15 is blocked by the upper stop ring 16 and cannot move upward. At the same time, when the piston connecting rod 18 contracts, its position will be restricted by the lower stop ring 19 and cannot contract, thereby preventing the movement of the separation piston 21 after the size is determined. The piston ring 13 is assembled on the separation piston 21. After determining the size of the separation piston 21, piston rings 13 of different sizes and materials can be selected to meet the inspection of the inner hole coating of the actuator with different apertures.

[0047] Reference Figure 2 As shown in the figure, the abrasive particle lifting module is installed at the bottom of the actuator cylinder. When the piston moves and the lubricating oil flows in and out, the lubricating oil in the actuator cylinder will flow, driving the bottom fan blades to rotate, preventing the wear debris that may be generated during friction from accumulating at the bottom of the actuator cylinder. The actuator cylinder sample of the device simulates different types of wear of the aero-engine actuator cylinder through the reciprocating motion of the piston and the abrasive particle lifting module.

[0048] The specific operation process is as follows:

[0049] Step 1, measuring the inner hole size of the actuator sample to be tested, adjusting the size of the separation piston 21, and installing the piston ring on the separation piston;

[0050] Specifically, the inner hole size of the actuator sample 4 is measured, and the piston connecting rod 16 is pushed to make the pulley 15 move in the piston groove 14, so as to change the size of the separation piston 21 to meet the test requirements; after determining the size of the separation piston 21, the pulley 15 is fixed by the locking mechanism to limit its movement in the groove 14, thereby fixing the relative size of the separation piston 21; the piston ring 13 is installed on the separation piston 21 of the selected size to complete the setting of the piston device.

[0051] Step 2: Build the experimental device and fix the sample;

[0052] Specifically, the chuck body 1 is fixedly connected to the bottom plate 11 by bolts, the actuator sample 4 is placed on the chuck body 1 and fixed by the movable claw 2 to ensure the stability of the actuator sample during the experiment; the piston limit slide groove 7 is fixedly connected to the bottom plate 11 by bolts 10, the slider 8 is installed in the piston limit slide groove 7, and connected to the piston rod 5 in the piston device by the connecting rod 6. The piston device is installed in the actuator sample 4 to complete the construction of the device.

[0053] Step 3: Input lubricating oil at different temperatures to simulate the working conditions of the actuator under different working environments;

[0054] Specifically, during the test, the lubricating oil is pumped from the oil tank into the actuator through the actuator oil inlet 3. The oil tank is provided with a thermometer and a temperature adjustment device, which can change the temperature of the input lubricating oil according to different working environments to meet the testing requirements under different working environments. The lubricating oil in the actuator sample 4 is pumped from the actuator oil outlet 9, filtered by the filtration system, and then flows back to the oil tank.

[0055] Step 4, connecting the experimental device to the reciprocating motion device, so that the piston can reciprocate in the actuator cylinder, and performing a wear test on the inner hole coating of the actuator cylinder;

[0056] Specifically, the slider 8 is connected to the reciprocating motion device, so that the slider 8 reciprocates in the piston limit slide groove 7, and the piston rod 5 is driven to move through the connecting rod 6, so that the piston device reciprocates in the actuator cylinder sample 4. During the test, when the lubricating oil enters the cylinder from the actuator cylinder oil inlet 3 and flows out from the actuator cylinder oil outlet 9, the lubricating oil will push the fan blade 12 installed at the bottom of the actuator cylinder sample 4, so that the wear debris deposited at the bottom is lifted, and the wear debris and the lubricating oil are mixed to a certain extent, so as to achieve the function of simulating the abrasive wear phenomenon that may occur in actual work.

[0057] Step 5: Detect the surface damage of the coating after the test and evaluate the service performance of the coating on the inner hole of the actuator.

[0058] Specifically: check the flatness, finish, color, gloss and other indicators of the coating to ensure the quality of the coating; detect the thickness of the coating to ensure that it meets the relevant standards and regulations; detect the degree of bonding between the coating and the substrate to ensure that the coating will not fall off or crack during the working process; detect the hardness and wear degree of the coating to evaluate its wear resistance and scratch resistance; detect the corrosion degree of the coating in the working environment to ensure that it can effectively protect the substrate. Combined with the above tests, a comprehensive evaluation of the service performance of the coating is carried out.

[0059] At this point, the evaluation of the service performance of the actuator inner hole coating has been completed.

[0060] In summary, the present embodiment provides a flight control actuator inner hole coating service performance evaluation system and method, which utilizes the reciprocating motion of a piston device in the actuator to simulate the wear of the piston on the actuator inner hole coating, and combines an abrasive lifting module and an oil port to simulate the temperature and wear environment of the actuator in actual applications, so that the test environment of the actuator inner hole coating evaluation system is more in line with the actual use environment. Therefore, when performing a service performance evaluation, the service performance of the actuator to be tested can be more accurately predicted, thereby achieving timely evaluation of the developed actuator inner hole coating; the size of the piston device can be adjusted by adjusting the separate piston 17, that is, the service performance evaluation of inner hole coatings of different sizes under different test conditions is achieved.

[0061] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations on the present invention. A person skilled in the art may change, modify, replace and modify the above embodiments within the scope of the present invention without departing from the principles and intent of the present invention.

Claims

1. A flight control actuator inner hole coating service performance evaluation system, characterized by: It includes an actuator sample, a variable piston module, and an abrasive particle lifting module. The inner hole wall of the actuator sample is provided with a wear-resistant coating as the object to be evaluated; an oil inlet and an oil outlet are opened on the cylinder wall for injecting lubricating oil required for actuation; the variable piston module is suitable for testing actuators of different apertures by adjusting the radial dimension; the variable piston module is placed in the inner hole of the actuator sample, and is controlled by the driving module to reciprocate axially in the inner hole of the actuator sample, so as to generate friction with the inner hole coating of the actuator sample; the abrasive particle lifting module is installed at the bottom of the actuator, and is driven to rotate by the flow of lubricating oil in the actuator, and the abrasive particles sunk to the bottom are lifted by rotation to simulate the abrasive wear of the actuator in actual use conditions; The variable piston module includes an outer diameter adjustable piston and a piston ring sleeved on its outer circumference. The piston ring is designed in series, including piston rings of various materials and sizes, which are used to meet the detection requirements of actuators with different apertures, or to complete comparative detection of grinding materials by replacing piston rings of different materials; The outer diameter adjustable piston includes a piston rod and a separate piston mounted on its head, the separate piston includes a plurality of separate piston units arranged along the circumferential direction, each separate piston unit is mounted on the circumferential surface of the piston rod head through a movable connection assembly, and the movable connection assembly is used to realize the contraction and expansion toward the piston rod to obtain the outer circumferential surface with different radial sizes; the end of the piston rod is connected to the driving module; The radial cross section of the split piston unit is fan-shaped, and each split piston unit forms an integral circular ring when folded, and its inner and outer arc surfaces are respectively located on the same circumferential surface when expanded; The movable connection assembly includes a piston groove, a pulley, and a piston connecting rod; the piston groove is an axial groove uniformly distributed on the piston rod head along the circumferential direction, and the number and position of the piston groove correspond to the separate piston unit one by one; one end of the piston connecting rod is slidingly hinged to the piston groove through a pulley, and the other end is hinged to the separate piston unit; when the axial position of the separate piston on the piston rod remains unchanged, the radial size of the separate piston is adjusted by adjusting the sliding position of one end of the piston connecting rod in the piston groove to adapt to actuators of different apertures; after adjustment, a locking mechanism is used to position it.

2. According to claim 1, a flight control actuator inner hole coating service performance evaluation system is characterized by: The actuating cylinder is fixedly mounted on the base plate by a clamp, and its axial direction is perpendicular to the base plate.

3. According to claim 1, a flight control actuator inner hole coating service performance evaluation system is characterized by: It also includes a piston movement limit module, which is arranged parallel to and opposite to the actuator cylinder, and is provided with a piston limit slot parallel to the axial direction of the actuator cylinder, and an adaptor slider is slidably connected in the piston limit slot; one end of the slider is vertically connected to the end of the piston rod through a connecting rod, and the other end is connected to the driving module; the reciprocating motion of the slider is controlled by the driving module, and the motion trajectory stroke of the slider is limited by the piston limit slot, so that the piston rod completes the reciprocating motion within the set stroke.

4. According to claim 1, a flight control actuator inner hole coating service performance evaluation system is characterized by: The abrasive grain lifting module comprises a rotating shaft and a plurality of fan blades evenly distributed in the circumference thereof, and the rotating shaft is rotatably connected to the bottom of the actuator cylinder.

5. A method for evaluating the service performance of the inner hole coating of a flight control actuator, characterized in that The specific steps are as follows: measuring the inner hole size of the actuator sample to be tested, and adjusting the radial size of the deformable piston module according to the inner hole size; building the flight control actuator inner hole coating service performance evaluation system as described in any one of claims 1 to 4, and fixing the actuator sample; inputting lubricating oil of different temperatures into the actuator through the actuator oil inlet to simulate the working conditions of the actuator in different working environments; The drive module is started to control the deformable piston module to perform reciprocating motion in the actuator cylinder, and the wear test of the inner hole coating of the actuator cylinder is carried out; the surface damage of the coating after the test is detected, and the service performance of the inner hole coating of the actuator cylinder is evaluated.

6. The flight control actuator inner hole coating service performance evaluation method according to claim 5, characterized in that: The radial dimension adjustment method of the variable piston module is as follows: first, a matching piston ring is selected according to the inner hole size of the actuator sample to be tested; then, the maximum outer diameter of the separate piston is determined according to the inner diameter size of the selected piston ring; thereafter, the radial distance between the separate piston unit and the piston rod is adjusted by contraction / expansion, thereby obtaining the determined maximum outer diameter of the separate piston, thereby completing the adjustment of the radial dimension of the variable piston module; finally, the movable connection assembly is positioned by a locking mechanism.

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