Fretting frictional wear testing device and method for aviation transmission part

Abstract

The invention discloses an aviation transmission part fretting friction wear test device and method, and belongs to the field of aerospace manufacturing, and the device comprises a supporting assembly, an axial force loading assembly, a transverse vibration assembly, a first test piece and a second test piece; the supporting assembly comprises a vibration platform, a first support and a second support, the first support is fixed on the vibration platform, the axial force loading assembly comprises a sliding plate, a servo motor, a lead screw and a nut, the sliding plate is in sliding connection with the vibration platform, the servo motor is connected with the lead screw, the nut is fixedly connected with the sliding plate, and the second support is fixed on the sliding plate; the transverse vibration assembly comprises a variable frequency motor, an eccentric wheel, a connecting rod, a vibration rod and a limiting plate, the variable frequency motor is fixed to the sliding plate, the eccentric wheel comprises a rotating shaft and an eccentric shaft, the variable frequency motor is in transmission connection with the rotating shaft, and one end of the connecting rod is rotationally connected with the eccentric shaft while the other end is rotationally connected with the vibration rod; therefore, the working condition of the aviation transmission part in a transverse vibration environment can be simulated.

Description

Technical Field

[0001] The present invention belongs to the technical field of aerospace manufacturing, and particularly relates to a fretting friction and wear test device and method for an aerospace transmission component. Background Art

[0002] In the aerospace field, aerospace transmission components are core components that ensure the safe operation of aerospace equipment. Common aerospace transmission components include spline pairs, gear pairs, and rack pairs, etc.

[0003] Generally, aerospace transmission components will face complex environments such as high-frequency fretting, high temperature, salt spray corrosion, and alternating loads. When aerospace transmission components are in the above complex environments, they are prone to fretting friction and wear, which may lead to the easy failure of aerospace transmission components. Among them, fretting friction and wear refers to the friction and wear that occur on the surface of aerospace transmission components under small vibrations or relative movements.

[0004] In order to improve the reliability of aerospace transmission components, it is necessary to use a friction and wear test device to test and analyze aerospace transmission components. Currently, common friction and wear test devices are composed of a machine table and a hydraulic rod. The aerospace transmission component is fixed on the machine table, and the hydraulic rod applies a force to the aerospace transmission component, which can simulate the load received by the aerospace transmission component during operation. By measuring the deformation and wear of the aerospace transmission component, the fretting friction and wear analysis of the aerospace transmission component can be realized. However, this device has a simple structure and limited applicable working conditions, and cannot simulate the working conditions of aerospace transmission components in a lateral vibration environment. Summary of the Invention

[0005] In order to solve the above problems existing in the prior art, the present invention provides a fretting friction and wear test device and method for an aerospace transmission component. The technical problems to be solved by the present invention are realized through the following technical solutions: In a first aspect, the present invention provides a fretting friction and wear test device for an aerospace transmission component, including a support assembly, an axial force loading assembly, a lateral vibration assembly, a first test piece, and a second test piece; The support assembly includes a vibration platform, a first support, and a second support. The first test piece is installed on the first support, the second test piece is installed on the second support, the first test piece and the second test piece are inserted and matched, and the first support is fixed on the vibration platform; The axial force loading assembly includes a sliding plate, a servo motor, a lead screw, and a nut. The sliding plate is slidably connected to the vibration platform, the servo motor is connected to the lead screw, the nut is sleeved on the lead screw and is threadedly connected to the lead screw, the nut is fixedly connected to the sliding plate, the second support is fixed on the sliding plate, the first support and the second support are arranged in sequence along the length direction of the vibration platform, the lead screw is arranged along the length direction of the vibration platform, the servo motor drives the lead screw to rotate, and when the lead screw rotates, it drives the second support to move towards or away from the first support; The lateral vibration assembly includes a variable-frequency motor, an eccentric wheel, a connecting rod, a vibration rod, and a limiting plate. The variable-frequency motor is fixed on the sliding plate. The eccentric wheel includes a rotating shaft and an eccentric shaft. The variable-frequency motor is in transmission connection with the rotating shaft. One end of the connecting rod is rotatably connected to the eccentric shaft, and the other end is rotatably connected to the vibration rod. The limiting plate is fixed on the sliding plate. The limiting plate includes a bottom plate and a vertical plate. A first through hole is provided on the vertical plate and is arranged along the width direction of the vibration platform. A limiting member is provided on the bottom plate, and a second through hole is provided on the limiting member. The first through hole and the second through hole are coaxially arranged. The vibration rod is inserted through the first through hole and the second through hole at the same time, and the vibration rod presses against the second support.

[0006] In an embodiment of the present invention, a temperature and humidity control box and a salt spray corrosion simulation box are further included. The temperature and humidity control box includes a first box body. A semiconductor refrigeration sheet, an electric heating wire, an ultrasonic humidifier, and a dehumidifier are provided in the first box body. When simulating the temperature and humidity environment, the first test piece and the second test piece are located in the first box body. The salt spray corrosion simulation box includes a second box body. A nozzle for spraying salt spray is provided in the second box body. When simulating the salt spray corrosion environment, the first test piece and the second test piece are located in the second box body.

[0007] In an embodiment of the present invention, a torsion loading assembly is further included. The torsion loading assembly includes a torsion motor, a magnetic powder clutch, and a torque sensor. The first support includes a first seat body and a first connecting shaft. The first connecting shaft is rotatably connected to the first seat body. The first test piece is installed at the end of the first connecting shaft. The second support includes a second seat body and a second connecting shaft. The second connecting shaft is fixedly connected to the second seat body. The second test piece is installed at the end of the second connecting shaft. The torsion motor, the magnetic powder clutch, and the torque sensor are connected in sequence. The torsion motor is in transmission connection with the first connecting shaft.

[0008] In an embodiment of the present invention, an information acquisition component and a data processing system are further included. The information acquisition component includes a six-axis force sensor, a laser displacement sensor, an acceleration sensor, an infrared thermal imager, and a white light interferometer. The data processing system is used to control the rotation speeds of the servo motor, the variable-frequency motor, and the torsion motor according to the data collected by the information acquisition component.

[0009] In an embodiment of the present invention, the support assembly further includes a bracket and an elastic buffer assembly. The vibration platform is installed on the bracket. The elastic buffer assembly is arranged between the vibration platform and the bracket.

[0010] Second aspect, the present invention also provides a method for testing fretting friction and wear of an aviation transmission component, which is applied to the aviation transmission component fretting friction and wear test device provided by the above solution. The test device includes a support assembly, an axial force loading assembly, a lateral vibration assembly, a first test piece, and a second test piece. The support assembly includes a first support and a second support; The method includes: Prepare the first test piece and the second test piece; Install the prepared first test piece and second test piece on the first support and the second support respectively; Apply axial force loading to the first test piece and the second test piece through the axial force loading assembly; Apply lateral vibration to the first test piece and the second test piece through the lateral vibration assembly.

[0011] In an embodiment of the present invention, the axial force loading assembly includes a servo motor, and the lateral vibration assembly includes a variable frequency motor; The aviation transmission component fretting friction and wear test device further includes a torsional loading assembly. The torsional loading assembly includes a torsional motor, a magnetic powder clutch, and a torque sensor. The first support includes a first seat body and a first connecting shaft. The first connecting shaft is rotatably connected to the first seat body. The first test piece is installed at the end of the first connecting shaft. The second support includes a second seat body and a second connecting shaft. The second connecting shaft is fixedly connected to the second seat body. The second test piece is installed at the end of the second connecting shaft. The torsional motor, the magnetic powder clutch, and the torque sensor are connected in sequence and are in transmission connection with the first connecting shaft; The method further includes: Determine the first parameters of the first test piece and the second test piece. The first parameters include axial force, lateral amplitude, lateral frequency, torque, ambient temperature, ambient humidity, and acoustic emission signal characteristic values; Input the determined first parameters into the trained BP neural network model. The BP neural network model outputs second parameters, and the second parameters include axial force adjustment amount, lateral amplitude adjustment amount, lateral frequency adjustment amount, and torque adjustment amount; Based on the second parameters, adjust the rotational speeds of the servo motor, the variable frequency motor, and the torsional motor.

[0012] In an embodiment of the present invention, the BP neural network model includes an input layer, a hidden layer, and an output layer; The input parameters of the input layer Satisfy the first formula, and the first formula is: ; Wherein, is the axial force at the current moment, is the lateral amplitude at the current moment, is the lateral frequency at the current moment, is the torque at the current moment, is the temperature at the current moment, is the humidity at the current moment, is the eigenvalue of the acoustic emission signal at the current moment; The hidden layer uses the Sigmoid activation function , where, is the input value, and the number of neurons in the hidden layer is , and the output of the hidden layer satisfies the second formula, and the second formula is: ; where, represents the hidden layer, is the th neuron in the input layer to the hidden layer in the th neuron's weight, is the input parameter of the th neuron in the input layer, is the bias of the th neuron in the hidden layer , is the number of neurons in the input layer; The output parameter of the output layer is the loading parameter to be adjusted. The output layer uses the linear activation function. The output parameter of the th neuron in the output layer satisfies the third formula, and the third formula is: ; where, represents the output layer, is the th neuron in the hidden layer to the output layer in the th neuron's weight, is the bias of the th neuron in the output layer , is the number of neurons in the output layer.

[0013] In an embodiment of the present invention, the training process of the BP neural network model includes: Based on the training samples, continuously adjust the weights and biases through the error backpropagation algorithm to minimize the error between the network output and the expected output, where the error function uses the mean square error , and the error function is: ; where, is the number of training samples, is the th expected output of the th sample, is the th network output of the

[0014] In an embodiment of the present invention, the method further includes: Calculating the friction coefficient between the first test piece and the second test piece; Measuring the wear volume of the first test piece and the second test piece; Performing fatigue life prediction on the first test piece and the second test piece.

[0015] Compared with the prior art, the beneficial effects of the present invention are: In the above solution of the present application, the fretting friction and wear test device for aviation transmission components includes a support assembly, an axial force loading assembly, a lateral vibration assembly, a first test piece, and a second test piece; the support assembly includes a vibration platform, a first support, and a second support. The first test piece is installed on the first support, and the second test piece is installed on the second support. The first test piece and the second test piece are inserted and matched with each other, and the first support is fixed on the vibration platform; the axial force loading assembly includes a sliding plate, a servo motor, a lead screw, and a nut. The sliding plate is slidably connected to the vibration platform. The servo motor is connected to the lead screw. The nut is sleeved on the lead screw and is threadedly connected to the lead screw. The nut is fixedly connected to the sliding plate. The second support is fixed on the sliding plate. The first support and the second support are arranged in sequence along the length direction of the vibration platform. The lead screw is arranged along the length direction of the vibration platform. The servo motor drives the lead screw to rotate. When the lead screw rotates, it drives the second support to move towards or away from the first support; the lateral vibration assembly includes a variable-frequency motor, an eccentric wheel, a connecting rod, a vibrating rod, and a limiting plate. The variable-frequency motor is fixed on the sliding plate. The eccentric wheel includes a rotating shaft and an eccentric shaft. The variable-frequency motor is drivingly connected to the rotating shaft. One end of the connecting rod is rotatably connected to the eccentric shaft, and the other end is rotatably connected to the vibrating rod; the limiting plate is fixed on the sliding plate. The limiting plate includes a bottom plate and a vertical plate. The vertical plate is provided with a first through hole, and the first through hole is arranged along the width direction of the vibration platform. The bottom plate is provided with a limiting member, and the limiting member is provided with a second through hole. The first through hole and the second through hole are coaxially arranged. The vibrating rod is inserted through the first through hole and the second through hole at the same time, and the vibrating rod presses against the second support. With this structure, the servo motor can drive the lead screw to rotate. When the lead screw rotates, it drives the nut to move axially along it. When the nut moves, it drives the sliding plate to move axially along the lead screw. When the sliding plate moves, it drives the second support to move towards the first support. When the second support moves towards the first support, the second test piece on the second support applies pressure to the first test piece on the first support, so as to be able to simulate the working condition of the aviation transmission component when it is subjected to an axial load. The variable-frequency motor can drive the rotating shaft to rotate. When the rotating shaft rotates, it drives the eccentric wheel to rotate around the rotating shaft. When the eccentric wheel rotates, it drives the eccentric shaft to rotate. When the eccentric shaft rotates, it drives one end of the connecting rod to rotate around the rotating shaft, and further drives the other end of the connecting rod to apply a pulling force or a pushing force to the vibrating rod, so that the vibrating rod can move horizontally back and forth in the first through hole and the second through hole. When the vibrating rod moves horizontally back and forth, it can continuously apply a lateral force to the second support, causing the second support and the second test piece to vibrate laterally, so as to be able to simulate the working condition of the aviation transmission component in a lateral vibration environment, and improve the applicable range of the fretting friction and wear test device for aviation transmission components.

[0016] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Description of the Drawings

[0017] Figure 1 is a front view of the test device in the embodiment of the present invention; Figure 2 It is a schematic diagram of the back of the test device in an embodiment of the present invention; Figure 3 It is a schematic diagram of the test device provided with a torsional loading component in an embodiment of the present invention; Figure 4 It is a schematic diagram of the first test piece and the second test piece in an embodiment of the present invention Figure 1 ; Figure 5 It is a schematic diagram of the first test piece and the second test piece in an embodiment of the present invention Figure 2 ; Figure 6 It is a schematic diagram of the lateral vibration component in an embodiment of the present invention Figure 1 ; Figure 7 It is a schematic diagram of the lateral vibration component in an embodiment of the present invention Figure 2 .

[0018] Reference numerals: 1 - support component, 11 - vibration platform, 12 - first support, 13 - second support, 14 - bracket, 15 - elastic buffer component, 2 - axial force loading component, 21 - sliding plate, 22 - servo motor, 23 - lead screw, 3 - lateral vibration component, 31 - variable frequency motor, 32 - eccentric wheel, 33 - connecting rod, 34 - vibrating rod, 35 - limiting plate, 36 - limiting member, 4 - first test piece, 5 - second test piece, 6 - torsional loading component, 61 - torsional motor, 62 - magnetic powder clutch, 63 - torque sensor. Detailed implementation manners

[0019] The following further describes the present invention in detail with reference to specific embodiments, but the implementation manners of the present invention are not limited thereto.

[0020] Embodiment 1: Please refer to Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 and Figure 7, an embodiment of the present invention provides a fretting friction and wear test device for an aviation transmission component, including a support assembly 1, an axial force loading assembly 2, a lateral vibration assembly 3, a first test piece 4, and a second test piece 5; the support assembly 1 includes a vibration platform 11, a first support 12, and a second support 13. The first test piece 4 is installed on the first support 12, the second test piece 5 is installed on the second support 13, the first test piece 4 and the second test piece 5 are inserted and matched, and the first support 12 is fixed on the vibration platform 11; the axial force loading assembly 2 includes a sliding plate 21, a servo motor 22, a lead screw 23, and a nut. The sliding plate 21 is slidably connected to the vibration platform 11. The servo motor 22 is connected to the lead screw 23. The nut is sleeved on the lead screw 23 and is threadedly connected to the lead screw 23. The nut is fixedly connected to the sliding plate 21. The second support 13 is fixed on the sliding plate 21. The first support 12 and the second support 13 are arranged in sequence along the length direction of the vibration platform 11. The lead screw 23 is arranged along the length direction of the vibration platform 11. The servo motor 22 drives the lead screw 23 to rotate. When the lead screw 23 rotates, it drives the second support 13 to move towards or away from the first support 12; the lateral vibration assembly 3 includes a variable frequency motor 31, an eccentric wheel 32, a connecting rod 33, a vibration rod 34, and a limiting plate 35. The variable frequency motor 31 is fixed on the sliding plate 21. The eccentric wheel 32 includes a rotating shaft and an eccentric shaft. The variable frequency motor 31 is drivingly connected to the rotating shaft. One end of the connecting rod 33 is rotatably connected to the eccentric shaft, and the other end is rotatably connected to the vibration rod 34; the limiting plate 35 is fixed on the sliding plate 21. The limiting plate 35 includes a bottom plate and a vertical plate. A first through hole is provided on the vertical plate. The first through hole is arranged along the width direction of the vibration platform 11. A limiting member 36 is provided on the bottom plate. A second through hole is provided on the limiting member 36. The first through hole and the second through hole are coaxially arranged. The vibration rod 34 is inserted through the first through hole and the second through hole at the same time, and the vibration rod 34 presses against the second support.

[0021] In an alternative embodiment, as Figure 4 shown, the aviation transmission component is a spline pair. When the spline pair is in a complex environment such as high-frequency fretting, high temperature, salt spray corrosion, and alternating load, the contact surface between the internal spline and the external spline in the spline pair will undergo fretting friction and wear, which will lead to the easy failure of the spline pair. At this time, the first test piece 4 is an internal spline, the second test piece 5 is an external spline, and the internal spline and the external spline are inserted and matched.

[0022] In another alternative embodiment, the aviation transmission component is a gear pair or a rack and pinion pair. When the gear pair or the rack and pinion pair is in a complex environment such as high-frequency fretting, high temperature, salt spray corrosion, and alternating load, the contact surface between the two gears in the gear pair will undergo fretting friction and wear, which will lead to the easy failure of the gear pair; the contact surface between the gear and the rack in the rack and pinion pair will undergo fretting friction and wear, which will lead to the easy failure of the rack and pinion pair. At this time, as Figure 5As shown, since the planar rack can reproduce to a certain extent the force characteristics of the gear pair or rack pair under actual working conditions, two planar racks are used in this embodiment for the fretting friction and wear test. Among them, the first test piece 4 includes a first fixture and two first clamping plates. Both of the two first clamping plates are installed on the first fixture, and first transverse planar racks are provided on both of the two first clamping plates. The second test piece 5 includes a second fixture and a second clamping plate. The second clamping plate is installed on the second fixture, and second transverse planar racks are provided on both the upper surface and the lower surface of the second clamping plate. The second clamping plate is located between the two first clamping plates, and the first transverse planar rack and the second transverse planar rack are meshed with each other.

[0023] In some embodiments of the present application, the power of the servo motor 22 is 15 kW, the lead of the lead screw 23 is 10 mm, the axial tension between the first test piece 4 and the second test piece 5 is monitored in real time by a force sensor. The range of the force sensor is 200 kN, and the accuracy is 0.1%. In this way, an axial force loading of 0 kN - 200 kN can be achieved.

[0024] In some embodiments of the present application, the rotational speed of the variable-frequency motor 31 can be adjusted within the range of 100 r / min to 3000 r / min. A multi-stage reduction gear set can be arranged between the variable-frequency motor 31 and the eccentric wheel 32. By reducing the speed through the multi-stage reduction gear set, the rotational speed of the eccentric wheel 32 can be reduced and the torque can be increased. The multi-stage reduction gear set can adopt involute cylindrical gears. The involute cylindrical gears are processed by high-precision grinding, and the tooth surface hardness can reach HRC58 - 62, so as to ensure the stability and accuracy of the transmission.

[0025] In some embodiments of the present application, the eccentricity of the eccentric wheel 32 can be accurately adjusted within the range of 0.5 mm - 5 mm. The connecting rod 33 can be made of high-strength alloy steel, and the surface of the connecting rod 33 is nitrided, which can improve its wear resistance and fatigue resistance.

[0026] In the above solution of the present application, the fretting friction and wear test device for aviation transmission components includes a support assembly 1, an axial force loading assembly 2, a transverse vibration assembly 3, a first test piece 4, and a second test piece 5; the support assembly 1 includes a vibration platform 11, a first support 12, and a second support 13. The first test piece 4 is installed on the first support 12, the second test piece 5 is installed on the second support 13, the first test piece 4 and the second test piece 5 are inserted and matched, and the first support 12 is fixed on the vibration platform 11; the axial force loading assembly 2 includes a sliding plate 21, a servo motor 22, a lead screw 23, and a nut. The sliding plate 21 is slidably connected to the vibration platform 11, the servo motor 22 is connected to the lead screw 23, the nut is sleeved on the lead screw 23 and is threadedly connected to the lead screw 23, the nut is fixedly connected to the sliding plate 21, the second support 13 is fixed on the sliding plate 21, the first support 12 and the second support 13 are arranged in sequence along the length direction of the vibration platform 11, the lead screw 23 is arranged along the length direction of the vibration platform 11, and the servo motor 22 drives the lead screw 23 to rotate. When the lead screw 23 rotates, it drives the second support 13 to move towards or away from the first support 12; the transverse vibration assembly 3 includes a variable-frequency motor 31, an eccentric wheel 32, a connecting rod 33, a vibrating rod 34, and a limiting plate 35. The variable-frequency motor 31 is fixed on the sliding plate 21. The eccentric wheel 32 includes a rotating shaft and an eccentric shaft. The variable-frequency motor 31 is drivingly connected to the rotating shaft. One end of the connecting rod 33 is rotatably connected to the eccentric shaft, and the other end is rotatably connected to the vibrating rod 34; the limiting plate 35 is fixed on the sliding plate 21. The limiting plate 35 includes a bottom plate and a vertical plate. A first through hole is provided on the vertical plate, and the first through hole is arranged along the width direction of the vibration platform 11. A limiting member 36 is provided on the bottom plate, and a second through hole is provided on the limiting member 36. The first through hole and the second through hole are coaxially arranged. The vibrating rod 34 is inserted through the first through hole and the second through hole at the same time, and the vibrating rod 34 presses against the second support. With this structure, the servo motor 22 can drive the lead screw 23 to rotate. When the lead screw 23 rotates, it drives the nut to move along its axial direction. When the nut moves, it drives the sliding plate 21 to move along the axial direction of the lead screw 23. When the sliding plate 21 moves, it drives the second support 13 to move towards the first support 12. When the second support 13 moves towards the first support 12, the second test piece 5 on the second support 13 applies pressure to the first test piece 4 on the first support 12, so as to be able to simulate the working condition of the aviation transmission component when it is subjected to an axial load.The variable frequency motor 31 can drive the rotating shaft to rotate. When the rotating shaft rotates, it drives the eccentric wheel to rotate around the rotating shaft. When the eccentric wheel rotates, it drives the eccentric shaft to rotate. When the eccentric shaft rotates, it drives one end of the connecting rod 33 to rotate around the rotating shaft, thereby driving the other end of the connecting rod 33 to apply a pulling force or a thrust to the vibration rod 34, so that the vibration rod 34 can repeatedly move laterally in the first perforation and the second perforation. When the vibration rod 34 moves, it can continuously apply a lateral force to the second support 13, so that the second support 13 and the second test piece 5 vibrate laterally, thereby simulating the working conditions of the aviation transmission components in a lateral vibration environment, thereby improving the scope of application of the micro-motion friction and wear test device for aviation transmission components.

[0027] In some embodiments of the present application, the test device further includes a temperature and humidity control box and a salt spray corrosion simulation box; the temperature and humidity control box includes a first box, in which a semiconductor cooling sheet, an electric heating wire, an ultrasonic humidifier and a dehumidifier are arranged, and when the temperature and humidity environment simulation is performed, the first test piece 4 and the second test piece 5 are located in the first box; the salt spray corrosion simulation box includes a second box, in which a nozzle for spraying salt spray is arranged, and when the salt spray corrosion environment simulation is performed, the first test piece 4 and the second test piece 5 are located in the second box. With this structure, the temperature in the first box can be regulated by the semiconductor cooling sheet and the electric heating wire, and the humidity in the second box can be regulated by the ultrasonic humidifier and the dehumidifier, so that the working conditions of the first test piece 4 and the second test piece 5 under different temperature and humidity conditions can be simulated. By spraying salt spray into the second box through the nozzle, a salt spray corrosion environment can be formed in the second box, so that the working conditions of the first test piece 4 and the second test piece 5 in the salt spray corrosion environment can be simulated, further improving the scope of application of the test device.

[0028] In some embodiments of the present application, Figure 3 As shown, the test device also includes a torsion loading assembly 6, which includes a torsion motor 61, a magnetic powder clutch 62 and a torque sensor 63; the first support 12 includes a first seat body and a first connecting shaft, the first connecting shaft and the first seat body are rotatably connected, and the first test piece 4 is installed at the end of the first connecting shaft; the second support 13 includes a second seat body and a second connecting shaft, the second connecting shaft and the second seat body are fixedly connected, and the second test piece 5 is installed at the end of the second connecting shaft; the torsion motor 61, the magnetic powder clutch 62 and the torque sensor 63 are connected in sequence, and the torsion motor 61 is connected to the first connecting shaft in a transmission manner. With this structure, the first connecting shaft can be controlled to rotate by the torsion motor 61 and the magnetic powder clutch 62, and the torque can be detected in real time by the torque sensor 63, so that the working conditions of the first test piece 4 and the second test piece 5 when receiving torque can be accurately simulated.

[0029] In some embodiments of the present application, the test device further includes an information acquisition component and a data processing system; the information acquisition component includes a six-axis force sensor, a laser displacement sensor, an acceleration sensor, an infrared thermal imager, and a white light interferometer; the data processing system is configured to control the rotational speeds of the servo motor 22, the variable-frequency motor 31, and the torsion motor 61 according to the data acquired by the information acquisition component. With this structure, the axial force between the first test piece 4 and the second test piece 5 can be detected by the six-axis force sensor, the lateral amplitude between the first test piece 4 and the second test piece 5 can be detected by the laser displacement sensor, the lateral vibration acceleration of the first test piece 4 and the second test piece 5 can be detected by the acceleration sensor, and thus the lateral vibration frequency of the first test piece 4 and the second test piece 5 can be obtained. The temperature distribution map on the first test piece 4 and the second test piece 5 can be obtained by the infrared thermal imager, and the three-dimensional topography features of the first test piece 4 and the second test piece 5 can be acquired by the white light interferometer, so as to facilitate the measurement of the wear volume of the first test piece 4 and the second test piece 5. The data processing system controls the rotational speeds of the servo motor 22, the variable-frequency motor 31, and the torsion motor 61 according to the data acquired by the information acquisition component, which can realize the adaptive adjustment of the servo motor 22, the variable-frequency motor 31, and the torsion motor 61, and further can realize the adaptive adjustment of the axial load, the lateral vibration, and the torque, improving the test accuracy of the test device.

[0030] In some embodiments of the present application, the six-axis force sensor is an existing high-precision sensor capable of simultaneously measuring forces in three directions and torques in three directions. The six-axis force sensor in this embodiment can be disposed between the first test piece 4 and the first connecting shaft, or between the second test piece 5 and the second connecting shaft.

[0031] In some embodiments of the present application, the laser displacement sensor is an existing non-contact high-precision measurement sensor. The acceleration sensor is an existing sensor for measuring the acceleration and vibration of an object. The infrared thermal imager is an existing device that detects the infrared radiation emitted by an object and converts it into a temperature distribution image.

[0032] In some embodiments of the present application, the white light interferometer is an existing optical measuring instrument that uses the principle of white light interference to perform nanoscale measurements on the three-dimensional topography, roughness, and step height of an object surface.

[0033] In some embodiments of the present application, the data processing system can be a central processing unit (CPU).

[0034] In some embodiments of the present application, such as Figure 1 and Figure 3As shown, the support assembly 1 further includes a bracket 14 and an elastic buffer assembly 15. The vibration platform 11 is installed on the bracket 14, and the elastic buffer assembly 15 is arranged between the vibration platform 11 and the bracket 14. With this structure, by utilizing the elastic effect of the elastic buffer assembly 15, the impact force between the vibration platform 11 and the bracket 14 can be reduced, and the overall stability of the test device can be improved.

[0035] In some embodiments of the present application, the elastic buffer assembly 15 can be composed of a plurality of springs and dampers.

[0036] In some embodiments of the present application, the test device can achieve axial force loading of 5 kN to 200 kN, can achieve lateral vibration loading with a lateral amplitude of 0.1 mm to 5 mm and a lateral vibration frequency of 0.1 Hz to 50 Hz, and can achieve torque loading of 100 N·m to 5000 N·m.

[0037] Embodiment Two: The present invention also provides a method for testing fretting friction and wear of an aviation transmission component, which is applied to the aviation transmission component fretting friction and wear test device provided in the above Embodiment One. The aviation transmission component fretting friction and wear test device includes a support assembly, an axial force loading assembly, a lateral vibration assembly, a first test piece, and a second test piece. The support assembly includes a first support and a second support; The method includes: Preparing the first test piece and the second test piece; Respectively installing the prepared first test piece and the second test piece on the first support and the second support; Performing axial force loading on the first test piece and the second test piece through the axial force loading assembly; Applying lateral vibration to the first test piece and the second test piece through the lateral vibration assembly.

[0038] For the beneficial effects of Embodiment Two of the present invention and its various implementation manners, reference can be made to the analysis of the beneficial effects in Embodiment One and its various implementation manners, which will not be elaborated here.

[0039] In some embodiments of the present application, the materials of the first test piece and the second test piece can be Ti-6Al-4V titanium alloy or 300M ultra-high strength steel, and the machining accuracy is controlled within IT6 level.

[0040] In some embodiments of the present application, the axial force loading assembly includes a servo motor, and the lateral vibration assembly includes a variable frequency motor; The fretting friction and wear test device for aviation transmission components further includes a torsional loading assembly. The torsional loading assembly includes a torsional motor, a magnetic powder clutch, and a torque sensor. The first support includes a first body and a first connecting shaft. The first connecting shaft is rotatably connected to the first body. The first test piece is installed at the end of the first connecting shaft. The second support includes a second body and a second connecting shaft. The second connecting shaft is fixedly connected to the second body. The second test piece is installed at the end of the second connecting shaft. The torsional motor, the magnetic powder clutch, and the torque sensor are connected in sequence and are in transmission connection with the first connecting shaft; The method further includes: Determine the first parameters of the first test piece and the second test piece. The first parameters include axial force, lateral amplitude, lateral frequency, torque, ambient temperature, ambient humidity, and acoustic emission signal eigenvalue; Input the determined first parameters into the trained BP neural network model. The BP neural network model outputs second parameters. The second parameters include axial force adjustment amount, lateral amplitude adjustment amount, lateral frequency adjustment amount, and torque adjustment amount; Based on the second parameters, adjust the rotational speeds of the servo motor, the variable frequency motor, and the torsional motor. By using this method, by inputting the determined first parameters into the trained BP neural network model, the BP neural network model outputs second parameters, and based on the second parameters, adjusting the rotational speeds of the servo motor, the variable frequency motor, and the torsional motor, the adaptive adjustment of the servo motor, the variable frequency motor, and the torsional motor can be realized. Furthermore, the adaptive adjustment of the axial load, the lateral vibration, and the torque can be realized, and the test accuracy of the test device can be improved.

[0041] In some embodiments of the present application, the BP neural network model includes an input layer, a hidden layer, and an output layer; The input parameters of the input layer Satisfy the first formula. The first formula is: ; Wherein, is the axial force at the current moment, is the lateral amplitude at the current moment, is the lateral frequency at the current moment, is the torque at the current moment, is the temperature at the current moment, is the humidity at the current moment, is the acoustic emission signal eigenvalue at the current moment; The hidden layer uses the Sigmoid activation function , wherein, is the Sigmoid activation function, is the input value. The number of neurons in the hidden layer is , and the output of the hidden layer Satisfy the second formula, where the second formula is: ; Wherein, represents the hidden layer, is the th neuron in the input layer to the hidden layer in the th neuron's weight, is the input parameter of the th neuron in the input layer, is the bias of the th neuron in the hidden layer ; is the number of neurons in the input layer; The output parameter of the output layer is the loading parameter to be adjusted. The output layer uses a linear activation function. The output parameter of the th neuron in the output layer ; Wherein, represents the output layer, is the th neuron in the hidden layer to the output layer in the th neuron's weight, is the bias of the th neuron in the output layer ; is the number of neurons in the output layer. By using this method, a BP neural network model can be trained to facilitate the adaptive adjustment of servo motors, variable-frequency motors, and torsion motors.

[0042] In some embodiments of the present application, the Sigmoid activation function is an existing non-linear activation function, which is mainly used to map the input value between 0 and 1.

[0043] In some embodiments of the present application, the output parameter of the output layer is the loading parameter that the test device needs to adjust. The loading parameters include the axial force adjustment amount , the lateral amplitude adjustment amount , the lateral frequency adjustment amount , the torque adjustment amount , etc.

[0044] In some embodiments of the present application, the training process of the BP neural network model includes: Based on the training samples, the weights and biases are continuously adjusted through the error backpropagation algorithm to minimize the error between the network output and the expected output. Among them, the error function uses the mean square error ; ; Among them, is the number of training samples, is the th expected output of the th sample, is the th network output of the

[0045] th sample. By using this method, the output accuracy of the BP neural network model can be improved, and further, the adjustment accuracy of the axial load, lateral vibration, and torque can be improved.

[0046] In some embodiments of the present application, during the training phase, the training samples can be the historical data of the test device. That is, before the test phase, the test device is used to perform multiple tests, and the results of each test are used as training samples. Then, during the test phase, the test device is used to perform real-time tests, and the real-time test results are input into the trained BP neural network model to obtain the loading parameters that need to be adjusted by the test device.

[0047] In some embodiments of the present application, the characteristic value of the acoustic emission signal refers to the key parameter extracted from the acoustic emission signal that can reflect the internal damage or deformation characteristics of the material or structure. In the embodiments of the present application, a piezoelectric acoustic emission sensor can be used to detect the characteristic values of the acoustic emission signals of the first test piece and the second test piece.

[0048] In some embodiments of the present application, the method further includes: calculating the friction coefficients of the first test piece and the second test piece; measuring the wear volumes of the first test piece and the second test piece; predicting the fatigue life of the first test piece and the second test piece. By using this method, the wear states of the first test piece and the second test piece can be predicted, so as to realize early warning of faults and avoid interruption of the test due to sudden faults.

[0049] In some embodiments of the present application, when calculating the friction coefficient of the first test piece and the second test piece, the friction coefficient can be calculated according to Coulomb's friction law through the fourth formula. , and the fourth formula is: ; where, is the frictional force, is the normal force.

[0050] In actual tests, the components of the frictional force and the normal force can be measured by a six-axis force sensor. Assuming that the tangential force components measured by the six-axis force sensor are and , then the frictional force can be calculated through the fifth formula, and the fifth formula is: ; Therefore, the friction coefficient is: .

[0051] In some embodiments of the present application, when measuring the wear volume of the first test piece and the second test piece, a white light interferometer can be used to obtain the three-dimensional point cloud data of the worn surfaces of the first test piece and the second test piece. Then, the point cloud data is preprocessed, and the preprocessing includes operations such as denoising and filtering. Finally, the wear volume of the first test piece and the second test piece is calculated by the integration method.

[0052] where, assuming that the three-dimensional point cloud data of the worn surfaces of the first test piece and the second test piece can be expressed as , where , is a positive integer, is the height difference of the th point relative to the unworn surface. The worn area is divided into several small grids, and the area of each small grid is . The wear volume can be obtained through the sixth formula, and the sixth formula is: .

[0053] In some embodiments of the present application, when predicting the fatigue life of the first test piece and the second test piece, the fatigue damage can be calculated according to Miner's linear cumulative damage theory through the seventh formula, and the seventh formula is: ; where, is the actual number of cycles at the th stress level, is the The fatigue life corresponding to the stress level of grade is the number of levels of different stress levels. When = 1, it is considered that the first test piece or the second test piece has fatigue failure. In practical applications, the stress levels at different times are measured by stress sensors, and the corresponding fatigue life is determined by combining with the S-N curve (stress-life curve) of the material, and then the damage values are accumulated to predict the remaining fatigue life of the first test piece or the second test piece.

[0054] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the present invention.

[0055] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present invention, "a plurality of" means two or more unless otherwise specifically defined.

[0056] In the present invention, unless otherwise clearly defined and limited, the terms "mounted", "connected", "connected", "fixed", etc. should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the internal communication of two elements or the interaction relationship between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0057] The above content is a further detailed description of the present invention in combination with specific preferred embodiments, and it cannot be determined that the specific implementation of the present invention is only limited to these descriptions. For those of ordinary skill in the art of the present invention, without departing from the concept of the present invention, several simple deductions or substitutions can still be made, and all should be regarded as belonging to the protection scope of the present invention.

Claims

1. A fretting friction and wear test device for an aviation transmission component, characterized in that It includes a support assembly, an axial force loading assembly, a lateral vibration assembly, a first test piece, and a second test piece; The support assembly includes a vibration platform, a first support and a second support, the first test piece is mounted on the first support, the second test piece is mounted on the second support, the first test piece and the second test piece are plug-fitted, and the first support is fixed on the vibration platform; The axial force loading assembly includes a sliding plate, a servo motor, a lead screw and a nut, the sliding plate is slidably connected to the vibration platform, the servo motor is connected to the lead screw, the nut is sleeved on the lead screw and is threadedly connected to the lead screw, the nut is fixedly connected to the sliding plate, the second support is fixed to the sliding plate, the first support and the second support are sequentially arranged along the length direction of the vibration platform, the lead screw is arranged along the length direction of the vibration platform, the servo motor drives the lead screw to rotate, and when the lead screw rotates, the second support is driven to move toward or away from the first support; The lateral vibration assembly comprises a variable frequency motor, an eccentric wheel, a connecting rod, a vibration rod and a limit plate, the variable frequency motor is fixed on the sliding plate, the eccentric wheel comprises a rotating shaft and an eccentric shaft, the variable frequency motor is transmission-connected to the rotating shaft, one end of the connecting rod is rotationally connected to the eccentric shaft, and the other end is rotationally connected to the vibration rod; The limiting plate is fixed on the sliding plate, and the limiting plate includes a bottom plate and a vertical plate. The vertical plate is provided with a first through hole, and the first through hole is arranged along the width direction of the vibration platform. The bottom plate is provided with a limiting member, and the limiting member is provided with a second through hole. The first through hole and the second through hole are coaxially arranged, and the vibration rod is inserted into the first through hole and the second through hole at the same time, and the vibration rod is pressed against the second support.

2. The fretting friction and wear test device for the aviation transmission component according to claim 1, wherein It also includes a temperature and humidity control chamber and a salt spray corrosion simulation chamber; The temperature and humidity control box comprises a first box body, in which a semiconductor cooling sheet, an electric heating wire, an ultrasonic humidifier and a dehumidifier are arranged. When the temperature and humidity environment simulation is performed, the first test piece and the second test piece are located in the first box body; The salt spray corrosion simulation box includes a second box body, in which a nozzle for spraying salt spray is arranged. When a salt spray corrosion environment simulation is performed, the first test piece and the second test piece are located in the second box body.

3. The fretting friction and wear test device for the aviation transmission component according to claim 2, characterized in that, Also included is a torsion loading assembly, the torsion loading assembly including a torsion motor, a magnetic powder clutch and a torque sensor; The first support comprises a first seat body and a first connecting shaft, the first connecting shaft and the first seat body are rotatably connected, and the first test piece is installed at an end of the first connecting shaft; The second support comprises a second seat body and a second connecting shaft, the second connecting shaft and the second seat body are fixedly connected, and the second test piece is installed at an end of the second connecting shaft; The torsion motor, magnetic powder clutch and torque sensor are connected in sequence, and the torsion motor is drivingly connected to the first connecting shaft.

4. The fretting friction and wear test device for an aviation transmission component according to claim 3, wherein, It also includes information collection components and data processing systems; The information acquisition component includes a six-axis force sensor, a laser displacement sensor, an acceleration sensor, an infrared thermal imager, and a white light interferometer; The data processing system is used to control the rotational speeds of the servo motor, the variable-frequency motor, and the torsional motor according to the data collected by the information acquisition component.

5. The fretting friction and wear test device for an aviation transmission component according to claim 1, characterized in that, The support component further includes a bracket and an elastic buffer component. The vibration platform is mounted on the bracket, and the elastic buffer component is disposed between the vibration platform and the bracket.

6. A fretting friction and wear test method for an aviation transmission component, characterized in that Applied to the fretting friction and wear test device for aviation transmission components as described in any one of the above claims 1 to 5, the test device includes a support component, an axial force loading component, a lateral vibration component, a first test piece, and a second test piece. The support component includes a first support and a second support; The method includes: Preparing a first test piece and a second test piece; Respectively mounting the prepared first test piece and the second test piece on the first support and the second support; Applying an axial force to the first test piece and the second test piece through the axial force loading component; Applying a lateral vibration to the first test piece and the second test piece through the lateral vibration component.

7. The fretting friction and wear test method for an aviation transmission component according to claim 6, wherein, The axial force loading component includes a servo motor, and the lateral vibration component includes a variable-frequency motor; The fretting friction and wear test device for aviation transmission components further includes a torsional loading component. The torsional loading component includes a torsional motor, a magnetic powder clutch, and a torque sensor. The first support includes a first seat body and a first connecting shaft. The first connecting shaft is rotatably connected to the first seat body. The first test piece is mounted at the end of the first connecting shaft. The second support includes a second seat body and a second connecting shaft. The second connecting shaft is fixedly connected to the second seat body. The second test piece is mounted at the end of the second connecting shaft. The torsional motor, the magnetic powder clutch, and the torque sensor are connected in sequence and are in transmission connection with the first connecting shaft; The method further includes: Determining a first parameter of the first test piece and the second test piece. The first parameter includes an axial force, a lateral amplitude, a lateral frequency, a torque, an ambient temperature, an ambient humidity, and an acoustic emission signal characteristic value; Inputting the determined first parameter into a trained BP neural network model. The BP neural network model outputs a second parameter. The second parameter includes an axial force adjustment amount, a lateral amplitude adjustment amount, a lateral frequency adjustment amount, and a torque adjustment amount; Based on the second parameter, adjusting the rotational speeds of the servo motor, the variable-frequency motor, and the torsional motor.

8. The fretting friction and wear test method for the aviation transmission component according to claim 7, wherein, The BP neural network model includes an input layer, a hidden layer, and an output layer; The input parameters of the input layer satisfy the first formula, and the first formula is: ； Among them, is the axial force at the current moment, is the lateral amplitude at the current moment, is the lateral frequency at the current moment, is the torque at the current moment, is the temperature at the current moment, is the humidity at the current moment, is the eigenvalue of the acoustic emission signal at the current moment; The hidden layer uses the Sigmoid activation function , where is the input value, and the number of neurons in the hidden layer is . The output of the hidden layer satisfies the second formula, and the second formula is: ； Among them, represents the hidden layer, is the weight from the th neuron of the input layer to the th neuron in the hidden layer, and is the input parameter of the th neuron of the input layer, is the bias of the th neuron in the hidden layer, and is the number of neurons in the input layer; The output parameters of the output layer are the loading parameters to be adjusted. The output layer uses a linear activation function, and the output parameter of the nth neuron in the output layer satisfies the third formula, which is: ； Among them, represents the output layer, is the weight from the th neuron of the hidden layer to the th neuron in the output layer, and is the bias of the th neuron in the output layer, and is the number of neurons in the output layer.​​ 9. The fretting friction and wear test method for the aviation transmission component according to claim 8, characterized in that The training process of the BP neural network model includes: Based on the training samples, the weights and biases are continuously adjusted through the error backpropagation algorithm to minimize the error between the network output and the expected output. Among them, the mean squared error is used as the error function , and the error function is: ； Among them, is the number of training samples, is the th expected output of the th sample, represents the expectation, is the th network output of the th sample.

10. The fretting friction and wear test method for the aviation transmission component according to claim 6, characterized in that The method further includes: Calculating the friction coefficients of the first test piece and the second test piece; Measuring the wear volumes of the first test piece and the second test piece; Performing fatigue life prediction on the first test piece and the second test piece.

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