A device and method for testing fretting friction and wear of aviation transmission components

Abstract

The present invention discloses a micro-friction and wear testing device and method for aviation transmission components, which belongs to the field of aerospace manufacturing. The device comprises a support assembly, an axial force loading assembly, a lateral vibration assembly, a first test piece and a second test piece. The support 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 slidably connected to the vibration platform, the servo motor is connected to the lead screw, the nut is fixedly connected to the sliding plate, and the second support is fixed on the sliding plate; 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, thereby simulating the working condition of the aviation transmission component in a lateral vibration environment.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace manufacturing technology, and in particular relates to a device and method for testing the fretting friction and wear of aviation transmission components. Background Art

[0002] In the aerospace industry, transmission components are key elements that ensure the safe operation of aerospace equipment. Common transmission components include splines, gears, and racks.

[0003] Typically, aircraft transmission components are exposed to complex environments such as high-frequency micro-motion, high temperatures, salt spray corrosion, and alternating loads. When these conditions are present, aircraft transmission components are prone to fretting wear and tear, which can lead to failure. Fretting wear refers to the friction and wear that occurs on the surface of aircraft transmission components due to small vibrations or relative motion.

[0004] To improve the reliability of aircraft transmission components, friction and wear testing devices are required for testing and analysis. Currently, common friction and wear testing devices consist of a machine platform and a hydraulic rod. The aircraft transmission component is fixed to the machine platform, and the hydraulic rod applies force to the aircraft transmission component, simulating the loads it experiences during operation. By measuring the deformation and wear of the aircraft transmission component, micro-motion friction and wear analysis of the aircraft transmission component can be performed. However, this device has a simple structure and is applicable to limited operating conditions. It cannot simulate the operating conditions of aircraft 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 device and method for testing the fretting friction and wear of aviation transmission components. The technical problems to be solved by the present invention are achieved through the following technical solutions:

[0006] In a first aspect, the present invention provides a fretting friction and wear testing device for aviation transmission components, comprising a support assembly, an axial force loading assembly, a lateral vibration assembly, a first test piece, and a second test piece;

[0007] 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 plug-fitted together, and the first support is fixed on the vibration platform;

[0008] 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, it drives the second support to move toward or away from the first support;

[0009] The transverse vibration assembly includes a variable frequency motor, an eccentric wheel, a connecting rod, a vibration rod and a limit plate. The variable frequency motor is fixed to the sliding plate. The eccentric wheel includes a rotating shaft and an eccentric shaft. The variable frequency motor and the rotating shaft are transmission-connected. One end of the connecting rod is rotationally connected to the eccentric shaft, and the other end is rotationally connected to the vibration rod.

[0010] 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. 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, 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.

[0011] In one embodiment of the present invention, it also includes a temperature and humidity control box and a salt spray corrosion simulation box;

[0012] The temperature and humidity control box includes a first box body, in which a semiconductor cooling plate, an electric heating wire, an ultrasonic humidifier, and a dehumidifier are arranged. When performing a temperature and humidity environment simulation, the first test piece and the second test piece are located in the first box body;

[0013] The salt spray corrosion simulation box includes a second box body, in which a nozzle for spraying salt spray is provided. When performing salt spray corrosion environment simulation, the first test piece and the second test piece are located in the second box body.

[0014] In one embodiment of the present invention, a torsion loading assembly is further included, and the torsion loading assembly includes a torsion motor, a magnetic powder clutch and a torque sensor;

[0015] The first support includes a first base body and a first connecting shaft, the first connecting shaft and the first base body are rotatably connected, and the first test piece is installed at an end of the first connecting shaft;

[0016] The second support includes a second base body and a second connecting shaft, the second connecting shaft is fixedly connected to the second base body, and the second test piece is installed at an end of the second connecting shaft;

[0017] The torsion motor, the magnetic powder clutch and the torque sensor are connected in sequence, and the torsion motor is transmission-connected to the first connecting shaft.

[0018] In one embodiment of the present invention, it also includes an information collection component and a data processing system;

[0019] The information collection components include six-dimensional force sensors, laser displacement sensors, acceleration sensors, infrared thermal imagers, and white light interferometers;

[0020] The data processing system is used to control the speed of the servo motor, the variable frequency motor and the torsion motor according to the data collected by the information collection component.

[0021] In one embodiment of the present invention, the support assembly further includes a bracket and an elastic buffer assembly, the vibration platform is mounted on the bracket, and the elastic buffer assembly is arranged between the vibration platform and the bracket.

[0022] In a second aspect, the present invention further provides a method for testing fretting friction and wear of aircraft transmission components, which is applied to the fretting friction and wear testing device for aircraft transmission components provided in the above-mentioned solution. The testing 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.

[0023] Methods include:

[0024] preparing a first test piece and a second test piece;

[0025] Installing the prepared first test piece and second test piece on the first support and the second support respectively;

[0026] Applying axial force loading to the first test piece and the second test piece through an axial force loading assembly;

[0027] Transverse vibration is applied to the first test piece and the second test piece by a transverse vibration assembly.

[0028] In one embodiment of the present invention, the axial force loading assembly includes a servo motor, and the lateral vibration assembly includes a variable frequency motor;

[0029] The fretting friction and wear testing device for aviation transmission components also includes a torsion loading assembly, which includes a torsion motor, a magnetic powder clutch, and a torque sensor. The first support includes a first base body and a first connecting shaft, the first connecting shaft and the first base body are rotatably connected, and the first test piece is mounted on the end of the first connecting shaft. The second support includes a second base body and a second connecting shaft, the second connecting shaft and the second base body are fixedly connected, and the second test piece is mounted on the end of the second connecting shaft. The torsion motor, the magnetic powder clutch, and the torque sensor are sequentially connected and transmission-connected to the first connecting shaft.

[0030] The method also includes:

[0031] Determining first parameters of the first test piece and the second test piece, the first parameters including axial force, transverse amplitude, transverse frequency, torque, ambient temperature, ambient humidity, and acoustic emission signal characteristic values;

[0032] Inputting the determined first parameter into the trained BP neural network model, the BP neural network model outputs second parameters, the second parameters including an axial force adjustment amount, a lateral amplitude adjustment amount, a lateral frequency adjustment amount, and a torque adjustment amount;

[0033] Based on the second parameter, the rotational speeds of the servo motor, the variable frequency motor, and the torsion motor are adjusted.

[0034] In one embodiment of the present invention, the BP neural network model includes an input layer, a hidden layer and an output layer;

[0035] Input parameters of the input layer Satisfies the first formula, the first formula is:

[0036] ;

[0037] in, is the axial force at the current moment, is the horizontal amplitude at the current moment, is the horizontal frequency at the current moment, is the torque at the current moment, is the current temperature, is the humidity at the current moment, is the characteristic value of the acoustic emission signal at the current moment;

[0038] The hidden layer uses the Sigmoid activation function ,in, is the input value, and the number of neurons in the hidden layer is , the output of the hidden layer Satisfies the second formula, the second formula is:

[0039] ;

[0040] in, represents the hidden layer, The input layer neurons to the hidden layer Middle The weights of neurons, The input layer The input parameters of neurons, For the hidden layer Middle The bias of a neuron, is the number of neurons in the input layer;

[0041] Output parameters of the output layer For the loading parameters that need to be adjusted, the output layer uses a linear activation function. The output parameters of neurons Satisfies the third formula, the third formula is:

[0042] ;

[0043] in, represents the output layer, For the hidden layer neurons to the output layer Middle The weights of neurons, For the output layer Middle The bias of a neuron, is the number of neurons in the output layer.

[0044] In one embodiment of the present invention, the training process of the BP neural network model includes:

[0045] Based on the training samples, the weights and biases are continuously adjusted through the error back propagation algorithm to minimize the error between the network output and the expected output. The error function uses the mean square error , the error function is:

[0046] ;

[0047] in, is the number of training samples, For the The first sample The expected output, Express expectations, For the The first sample Network output.

[0048] In one embodiment of the present invention, the method further comprises:

[0049] Calculating the friction coefficient of the first test piece and the second test piece;

[0050] measuring the wear volume of the first test piece and the second test piece;

[0051] Fatigue life prediction is performed on the first test piece and the second test piece.

[0052] Compared with the prior art, the present invention has the following beneficial effects:

[0053] In the above scheme of the present application, the micro-friction and wear testing 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, the second test piece is installed on the second support, the first test piece and the second test piece are plug-in 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 and the vibration platform are slidably connected, the servo motor and the lead screw are connected, the nut is sleeved on the lead screw and is threadedly connected to the lead screw, the nut and the sliding plate are fixedly connected, 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, and the lead screw is arranged along the length direction of the vibration platform. The vibration platform is set in the length direction, and the servo motor drives the screw to rotate, and when the screw rotates, it drives the second support to move toward or away from the first support; the transverse vibration component includes a frequency conversion motor, an eccentric wheel, a connecting rod, a vibration rod and a limit plate, the frequency conversion motor is fixed on the sliding plate, the eccentric wheel includes a rotating shaft and an eccentric shaft, the frequency conversion motor and the rotating shaft are transmission-connected, 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 limit plate is fixed on the sliding plate, and the limit plate 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, a limit piece is provided on the bottom plate, a second through-hole is provided on the limit piece, the first through-hole and the second through-hole are coaxially arranged, 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. With this structure, a servo motor can drive the lead screw to rotate, which, when the lead screw rotates, drives the nut to move axially. 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 toward the first support. When the second support moves toward the first support, the second test piece on the second support applies pressure to the first test piece on the first support, thereby simulating the working condition of an aviation transmission component subjected to an axial load. A variable frequency motor can drive the rotating shaft to rotate, which, when the rotating shaft rotates, drives the eccentric wheel to rotate about the rotating shaft. When the eccentric wheel rotates, it drives the eccentric shaft. When the eccentric shaft rotates, it drives one end of the connecting rod to rotate about the rotating shaft, thereby driving the other end of the connecting rod to apply a tensile force or a thrust to the vibrating rod, causing the vibrating rod to repeatedly move laterally within the first and second perforations. During this repeated lateral movement, the vibrating rod continuously applies a lateral force to the second support, causing the second support and the second test piece to vibrate laterally, thereby simulating the working condition of an aviation transmission component subjected to a lateral vibration environment, thereby expanding the applicability of the fretting friction and wear testing device for aviation transmission components.

[0054] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0055] Figure 1 is a front schematic diagram of a testing device according to an embodiment of the present invention;

[0056] Figure 2 is a schematic diagram of the back of a testing device according to an embodiment of the present invention;

[0057] Figure 3 is a schematic diagram of a test device provided with a torsion loading assembly according to an embodiment of the present invention;

[0058] Figure 4 Schematic diagram of the first test piece and the second test piece in the embodiment of the present invention Figure 1 ;

[0059] Figure 5 Schematic diagram of the first test piece and the second test piece in the embodiment of the present invention Figure 2 ;

[0060] Figure 6 Schematic diagram of the lateral vibration component in the embodiment of the present invention Figure 1 ;

[0061] Figure 7 Schematic diagram of the lateral vibration component in the embodiment of the present invention Figure 2 .

[0062] Figure markings: 1-support assembly, 11-vibration platform, 12-first support, 13-second support, 14-bracket, 15-elastic buffer assembly, 2-axial force loading assembly, 21-sliding plate, 22-servo motor, 23-screw, 3-lateral vibration assembly, 31-frequency conversion motor, 32-eccentric wheel, 33-connecting rod, 34-vibration rod, 35-limiting plate, 36-limiting member, 4-first test piece, 5-second test piece, 6-torsion loading assembly, 61-torsion motor, 62-magnetic powder clutch, 63-torque sensor. DETAILED DESCRIPTION

[0063] The present invention will be further described in detail below with reference to specific examples, but the embodiments of the present invention are not limited thereto.

[0064] Example 1:

[0065] See Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 、 Figure 5 、 Figure 6 and Figure 7The embodiment of the present invention provides a micro-motion friction and wear testing device for aviation transmission components, comprising 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 comprises a vibration platform 11, a first support 12 and a second support 13, the first test piece 4 is mounted on the first support 12, the second test piece 5 is mounted on the second support 13, the first test piece 4 and the second test piece 5 are plug-fitted, and the first support 12 is fixed to the vibration platform 11; the axial force loading assembly 2 comprises 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 to the sliding plate 21, the first support 12 and the second support 13 are sequentially arranged 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 toward 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 vibration rod 34 and a limit 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 transmission-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 limit plate 35 is fixed on the sliding plate 21, and the limit plate 35 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 11. The bottom plate is provided with a limit member 36, and the limit member 36 is provided with a second through-hole. The first through-hole and the second through-hole are coaxially arranged. The vibration rod 34 is simultaneously inserted into the first through-hole and the second through-hole, and the vibration rod 34 is pressed against the second support.

[0066] In an optional embodiment, as Figure 4 As shown, the aviation transmission component is a spline pair. When the spline pair is in a complex environment such as high-frequency micro-motion, high temperature, salt spray corrosion and alternating load, the contact surface between the inner spline and the outer spline in the spline pair will undergo micro-motion friction and wear, which will cause the spline pair to fail easily. At this time, the first test piece 4 is an inner spline, and the second test piece 5 is an outer spline, and the inner spline and the outer spline are plug-in matched.

[0067] In another optional embodiment, the aviation transmission component is a gear pair or a rack pair. When the gear pair or rack pair is in a complex environment such as high-frequency micro-motion, high temperature, salt spray corrosion, and alternating loads, the contact surface between the two gears in the gear pair will undergo micro-motion friction and wear, which will easily cause the gear pair to fail; the contact surface between the gear and rack in the rack pair will undergo micro-motion friction and wear, which will easily cause the rack pair to fail. At this time, if Figure 5As shown, since the plane rack can reproduce the force characteristics of the gear pair or rack pair under actual working conditions to a certain extent, this embodiment uses two plane racks to perform micro-friction and wear tests, wherein the first test piece 4 includes a first fixture and two first plywoods, the two first plywoods are both installed on the first fixture, and the two first plywoods are both provided with a first transverse plane rack, the second test piece 5 includes a second fixture and a second plywood, the second plywood is installed on the second fixture, and the upper surface and lower surface of the second plywood are both provided with a second transverse plane rack, the second plywood is located between the two first plywoods, and the first transverse plane rack and the second transverse plane rack are meshed.

[0068] In some embodiments of the present application, the power of the servo motor 22 is 15kW, the lead of the screw 23 is 10mm, and 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 200kN and the accuracy is 0.1%. In this way, axial force loading of 0KN-200KN can be achieved.

[0069] In some embodiments of the present application, the speed of the variable frequency motor 31 can be adjusted within a range of 100 rpm to 3000 rpm. A multi-stage reduction gear set can be provided between the variable frequency motor 31 and the eccentric wheel 32. This multi-stage reduction gear set reduces the speed of the eccentric wheel 32 and increases torque. The multi-stage reduction gear set can utilize involute cylindrical gears. These involute cylindrical gears undergo high-precision grinding, achieving a tooth surface hardness of HRC 58-62, thereby ensuring transmission stability and accuracy.

[0070] In some embodiments of the present application, the eccentricity of the eccentric wheel 32 can be precisely adjusted within the range of 0.5mm-5mm, the connecting rod 33 can be made of high-strength alloy steel, and the surface of the connecting rod 33 is nitrided to improve its wear resistance and fatigue resistance.

[0071] In the above scheme of the present application, the micro-friction and wear testing device for aviation transmission components includes 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 plug-fitted, 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 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 screw 23, the nut is sleeved on the screw 23 and is threadedly connected to the 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 screw 23 is arranged along the length direction of the vibration platform 11, and the servo motor 22 drives the screw 23 to rotate. When the screw 23 rotates, the second support 13 is driven to move toward 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 limit 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 transmission-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 limit plate 35 is fixed on the sliding plate 21, the limit 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 limit piece 36 is provided on the bottom plate, a second through-hole is provided on the limit piece 36, the first through-hole and the second through-hole are coaxially arranged, the vibration rod 34 is simultaneously inserted into the first through-hole and the second through-hole, and the vibration rod 34 is pressed against the second support. With this structure, the servo motor 22 can drive the screw 23 to rotate. When the 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 screw 23. When the sliding plate 21 moves, it drives the second support 13 to move toward the first support 12. When the second support 13 moves toward 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, thereby simulating the working conditions of aviation transmission components when they are subjected to axial loads.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, and then drives the other end of the connecting rod 33 to apply a pulling force or a pushing force 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 applicability of the aviation transmission component micro-friction and wear test device.

[0072] In some embodiments of the present application, the test device further includes a temperature and humidity control chamber and a salt spray corrosion simulation chamber; the temperature and humidity control chamber includes a first chamber, in which a semiconductor cooling plate, an electric heating wire, an ultrasonic humidifier, and a dehumidifier are provided. When a temperature and humidity environment simulation is performed, the first test piece 4 and the second test piece 5 are located in the first chamber; the salt spray corrosion simulation chamber includes a second chamber, in which a nozzle for spraying salt spray is provided. When a salt spray corrosion environment simulation is performed, the first test piece 4 and the second test piece 5 are located in the second chamber. With this structure, the temperature in the first chamber can be controlled by the semiconductor cooling plate and the electric heating wire, and the humidity in the second chamber can be controlled by the ultrasonic humidifier and the dehumidifier, thereby simulating the operating conditions of the first test piece 4 and the second test piece 5 under different temperature and humidity conditions. By spraying salt spray into the second chamber through the nozzle, a salt spray corrosion environment can be formed in the second chamber, thereby simulating the operating conditions of the first test piece 4 and the second test piece 5 in a salt spray corrosion environment, further improving the applicability of the test device.

[0073] 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 support body and a first connecting shaft, which are rotatably connected to the first support body, and the first test piece 4 is mounted on the end of the first connecting shaft. The second support 13 includes a second support body and a second connecting shaft, which are fixedly connected to the second support body, and the second test piece 5 is mounted on the end of the second connecting shaft. The torsion motor 61, magnetic powder clutch 62, and torque sensor 63 are connected in sequence, and the torsion motor 61 is in transmission connection with the first connecting shaft. With this structure, the torsion motor 61 and magnetic powder clutch 62 can control the rotation of the first connecting shaft, and the torque sensor 63 can detect the torque in real time, thereby accurately simulating the operating conditions of the first and second test pieces 4 and 5 when subjected to torque.

[0074] In some embodiments of the present application, the testing apparatus further includes an information acquisition component and a data processing system; the information acquisition component includes a six-dimensional force sensor, a laser displacement sensor, an acceleration sensor, an infrared thermal imager, and a white light interferometer; and the data processing system is used to control the rotational speeds of the servo motor 22, the variable frequency motor 31, and the torsion motor 61 based on the data collected by the information acquisition component. With this structure, the six-dimensional force sensor can be used to detect the axial force between the first test piece 4 and the second test piece 5, the laser displacement sensor can be used to detect the lateral amplitude of the first test piece 4 and the second test piece 5, the acceleration sensor can be used to detect the lateral vibration acceleration of the first test piece 4 and the second test piece 5, and thus the lateral vibration frequency of the first test piece 4 and the second test piece 5 can be obtained. The infrared thermal imager can be used to obtain the temperature distribution on the first test piece 4 and the second test piece 5, and the white light interferometer can be used to obtain the three-dimensional topographic features of the first test piece 4 and the second test piece 5, 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 speed of the servo motor 22, the variable frequency motor 31 and the torsion motor 61 according to the data collected by the information acquisition component, thereby realizing adaptive adjustment of the servo motor 22, the variable frequency motor 31 and the torsion motor 61, and further realizing adaptive adjustment of the axial load, lateral vibration and torque, thereby improving the test accuracy of the test device.

[0075] In some embodiments of the present application, a six-axis force sensor is a high-precision sensor that can simultaneously measure forces and moments 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.

[0076] In some embodiments of the present application, a laser displacement sensor is an existing non-contact, high-precision measurement sensor. An acceleration sensor is an existing sensor used to measure the acceleration and vibration of an object. An infrared thermal imager is an existing device that detects infrared radiation emitted by an object and converts it into a temperature distribution image.

[0077] 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 nanometer-level measurement of the three-dimensional topography, roughness, and step height of an object surface.

[0078] In some embodiments of the present application, the data processing system may be a central processing unit (CPU).

[0079] In some embodiments of the present application, 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 mounted on the bracket 14, and the elastic buffer assembly 15 is disposed between the vibration platform 11 and the bracket 14. With this structure, the elastic effect of the elastic buffer assembly 15 can reduce the impact force between the vibration platform 11 and the bracket 14, thereby improving the overall stability of the testing device.

[0080] In some embodiments of the present application, the elastic buffer assembly 15 may be composed of a plurality of springs and dampers.

[0081] In some embodiments of the present application, the testing device can achieve axial force loading of 5kN~200kN, can achieve lateral vibration loading with a lateral amplitude of 0.1mm~5mm and a lateral vibration frequency of 0.1Hz~50Hz, and can achieve torque loading of 100N·m~5000N·m.

[0082] Example 2:

[0083] The present invention also provides a method for testing fretting friction and wear of aircraft transmission components, which is applied to the fretting friction and wear testing device for aircraft transmission components provided in the first embodiment. The fretting friction and wear testing device for aircraft 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 first support and a second support.

[0084] Methods include:

[0085] preparing a first test piece and a second test piece;

[0086] Installing the prepared first test piece and second test piece on the first support and the second support respectively;

[0087] Applying axial force loading to the first test piece and the second test piece through an axial force loading assembly;

[0088] Transverse vibration is applied to the first test piece and the second test piece by a transverse vibration assembly.

[0089] The beneficial effects of the second embodiment of the present invention and its various implementations can be analyzed with reference to the beneficial effects of the first embodiment and its various implementations, and will not be repeated here.

[0090] In some embodiments of the present application, the materials of the first test piece and the second test piece may be Ti-6Al-4V titanium alloy or 300M ultra-high strength steel, and the processing accuracy is controlled within IT6 level.

[0091] 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;

[0092] The fretting friction and wear testing device for aviation transmission components also includes a torsion loading assembly, which includes a torsion motor, a magnetic powder clutch, and a torque sensor. The first support includes a first base body and a first connecting shaft, the first connecting shaft and the first base body are rotatably connected, and the first test piece is mounted on the end of the first connecting shaft. The second support includes a second base body and a second connecting shaft, the second connecting shaft and the second base body are fixedly connected, and the second test piece is mounted on the end of the second connecting shaft. The torsion motor, the magnetic powder clutch, and the torque sensor are sequentially connected and transmission-connected to the first connecting shaft.

[0093] The method also includes:

[0094] Determining first parameters of the first test piece and the second test piece, the first parameters including axial force, transverse amplitude, transverse frequency, torque, ambient temperature, ambient humidity, and acoustic emission signal characteristic values;

[0095] Inputting the determined first parameter into the trained BP neural network model, the BP neural network model outputs second parameters, the second parameters including an axial force adjustment amount, a lateral amplitude adjustment amount, a lateral frequency adjustment amount, and a torque adjustment amount;

[0096] Based on the second parameter, the speed of the servo motor, variable frequency motor, and torsion motor is adjusted. Using this method, by inputting the determined first parameter into a trained BP neural network model, the BP neural network model outputs the second parameter. Based on the second parameter, the speed of the servo motor, variable frequency motor, and torsion motor is adjusted. This method can achieve adaptive adjustment of the servo motor, variable frequency motor, and torsion motor, and further achieve adaptive adjustment of axial load, lateral vibration, and torque, thereby improving the test accuracy of the test device.

[0097] In some embodiments of the present application, the BP neural network model includes an input layer, a hidden layer, and an output layer;

[0098] Input parameters of the input layer Satisfies the first formula, the first formula is:

[0099] ;

[0100] in, is the axial force at the current moment, is the horizontal amplitude at the current moment, is the horizontal frequency at the current moment, is the torque at the current moment, is the current temperature, is the humidity at the current moment, is the characteristic value of the acoustic emission signal at the current moment;

[0101] The hidden layer uses the Sigmoid activation function ,in, is the Sigmoid activation function, is the input value, and the number of neurons in the hidden layer is , the output of the hidden layer Satisfies the second formula, the second formula is:

[0102] ;

[0103] in, represents the hidden layer, The input layer neurons to the hidden layer Middle The weights of neurons, The input layer The input parameters of neurons, For the hidden layer Middle The bias of a neuron, is the number of neurons in the input layer;

[0104] Output parameters of the output layer For the loading parameters that need to be adjusted, the output layer uses a linear activation function. The output parameters of neurons Satisfies the third formula, the third formula is:

[0105] ;

[0106] in, represents the output layer, For the hidden layer neurons to the output layer Middle The weights of neurons, For the output layer Middle The bias of a neuron, is the number of neurons in the output layer. 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.

[0107] In some embodiments of the present application, the Sigmoid activation function is an existing nonlinear activation function, which is mainly used to map input values to between 0 and 1.

[0108] In some embodiments of the present application, the output parameters of the output layer are The loading parameters that need to be adjusted for the test device include the axial force adjustment amount , lateral amplitude adjustment , horizontal frequency adjustment , torque adjustment wait.

[0109] In some embodiments of the present application, the training process of the BP neural network model includes:

[0110] Based on the training samples, the weights and biases are continuously adjusted through the error back propagation algorithm to minimize the error between the network output and the expected output. The error function uses the mean square error ;

[0111] ;

[0112] in, is the number of training samples, For the The first sample The expected output, Express expectations, For the The first sample This method can improve the output accuracy of the BP neural network model, and thus improve the adjustment accuracy of axial load, lateral vibration and torque.

[0113] In some embodiments of the present application, during the training phase, the training samples may be historical data of the test device, that is, before the test phase, multiple tests are performed using the test device, and the results of each test are used as training samples. Then, during the test phase, real-time testing is performed using the test device, 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.

[0114] In some embodiments of the present application, the characteristic value of the acoustic emission signal refers to a key parameter extracted from the acoustic emission signal that can reflect the internal damage or deformation characteristics of the material or structure. In some 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.

[0115] In some embodiments of the present application, the error back propagation algorithm is an existing core method for training artificial neural networks, which optimizes network parameters (weights and biases) through gradient descent to minimize the error between the predicted output and the true value. The error back propagation algorithm can perform error calculation through the above-mentioned error function.

[0116] In some embodiments of the present application, the method further comprises:

[0117] Calculating the friction coefficient of the first test piece and the second test piece;

[0118] measuring the wear volume of the first test piece and the second test piece;

[0119] Fatigue life prediction is performed on the first and second test pieces. This method can predict the wear state of the first and second test pieces, thereby providing early warning of failures and avoiding test interruptions due to sudden failures.

[0120] In some embodiments of the present application, when calculating the friction coefficient between the first test piece and the second test piece, the friction coefficient can be calculated according to Coulomb's friction law using the fourth formula: , the fourth formula is:

[0121] ;

[0122] in, is the friction force, It is positive pressure.

[0123] In actual testing, the friction force and normal pressure components can be measured by the six-axis force sensor. Assume that the tangential force component measured by the six-axis force sensor is and , then the friction force It can be calculated by the fifth formula, which is:

[0124] ;

[0125] Therefore, the friction coefficient for:

[0126] .

[0127] In some embodiments of the present application, when measuring the wear volumes of the first and second test pieces, a white light interferometer can be used to obtain three-dimensional point cloud data of the wear surfaces of the first and second test pieces. The point cloud data is then preprocessed, including operations such as denoising and filtering, and the wear volumes of the first and second test pieces are finally calculated using an integration method.

[0128] It is assumed that the three-dimensional point cloud data of the wear surfaces of the first test piece and the second test piece can be expressed as ,in, , is a positive integer, It is The height difference of each point relative to the unworn surface divides the worn area into several small grids, and the area of each small grid is Wear volume It can be obtained by the sixth formula, which is:

[0129] .

[0130] 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 by the seventh formula according to Miner's linear cumulative damage theory. , the seventh formula is:

[0131] ;

[0132] in, For the The actual number of cycles under the stress level, For the The fatigue life corresponding to the first stress level is is the series of different stress levels. = 1, fatigue failure is considered to have occurred in the first or second specimen. In practical applications, stress levels at different times are measured by stress sensors, and the corresponding fatigue life is determined by combining the material's SN curve (stress-life curve). The damage values are then accumulated to predict the remaining fatigue life of the first or second specimen.

[0133] 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 to 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 device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0134] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature identified as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, "plurality" means two or more, unless otherwise specifically defined.

[0135] In the present invention, unless otherwise expressly specified or limited, the terms "mounted," "connected," "connect," "fixed," etc. should be understood broadly. For example, they may refer to fixed connection, detachable connection, or integration; mechanical connection or electrical connection; direct connection or indirect connection through an intermediate medium; internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0136] The above is a further detailed description of the present invention in conjunction with specific preferred embodiments, and the specific implementation of the present invention should not be considered to be limited to these descriptions. For those skilled in the art of the present invention, without departing from the concept of the present invention, several simple deductions or substitutions can be made, which should be considered to fall within the scope of protection of the present invention.

Claims

1. A fretting friction and wear testing device for aviation transmission components, characterized in that: comprising 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 together, and the first support is fixed to the vibration platform; The axial force loading assembly includes a sliding plate, a servo motor, a lead screw and a nut, the sliding plate and the vibration platform are slidably connected, the servo motor and the lead screw are connected, the nut is sleeved on the lead screw and threadedly connected to the lead screw, the nut and the sliding plate are fixedly connected, 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 transverse vibration assembly includes a variable frequency motor, an eccentric wheel, a connecting rod, a vibration rod and a limit plate, the variable frequency motor is fixed to the sliding plate, the eccentric wheel includes 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 testing device for aviation transmission components according to claim 1, characterized in that: It also includes a temperature and humidity control chamber and a salt spray corrosion simulation chamber; The temperature and humidity control box includes a first box body, in which a semiconductor cooling plate, an electric heating wire, an ultrasonic humidifier, and a dehumidifier are installed. When performing temperature and humidity environment simulation, 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 provided. When performing salt spray corrosion environment simulation, the first test piece and the second test piece are located in the second box body.

3. The fretting friction and wear testing device for aviation transmission components 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 includes a first base and a first connecting shaft, the first connecting shaft and the first base are rotatably connected, and the first test piece is installed at an end of the first connecting shaft; The second support includes a second base body and a second connecting shaft, the second connecting shaft and the second base 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 in transmission connection with the first connecting shaft.

4. The fretting friction and wear testing device for aviation transmission components according to claim 3, characterized in that: It also includes information collection components and data processing systems; The information acquisition component includes a six-dimensional 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 speed of the servo motor, the variable frequency motor and the torsion motor according to the data collected by the information collection component.

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

6. A method for testing fretting friction and wear of aviation transmission components, characterized in that: The fretting friction and wear testing device for aviation transmission components according to any one of claims 1 to 5 is applied thereto, the testing device comprising a support assembly, an axial force loading assembly, a lateral vibration assembly, a first test piece, and a second test piece, wherein the support assembly comprises a first support and a second support; The method comprises: preparing a first test piece and a second test piece; Mounting the prepared first test piece and the second test piece on the first support and the second support respectively; Applying axial force loading to the first test piece and the second test piece by using the axial force loading assembly; Transverse vibration is applied to the first test piece and the second test piece by the transverse vibration assembly.

7. The method for testing fretting friction and wear of aviation transmission components according to claim 6, characterized in that: The axial force loading assembly includes a servo motor, and the lateral vibration assembly includes a variable frequency motor; The fretting friction and wear testing device for aviation transmission components further includes a torsion loading assembly, which 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 and the first seat body are rotatably connected, and the first test piece is mounted on the end of the first connecting shaft. The second support 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 is mounted on the end of the second connecting shaft. The torsion motor, the magnetic powder clutch, and the torque sensor are sequentially connected and are in driving connection with the first connecting shaft. The method further comprises: Determining first parameters of the first test piece and the second test piece, the first parameters including axial force, transverse amplitude, transverse frequency, torque, ambient temperature, ambient humidity, and acoustic emission signal characteristic values; Inputting the determined first parameter into a trained BP neural network model, the BP neural network model outputting second parameters, the second parameters including 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, the rotational speeds of the servo motor, the variable frequency motor, and the torsion motor are adjusted.

8. The method for testing fretting friction and wear of aviation transmission components according to claim 7, characterized in that: The BP neural network model includes an input layer, a hidden layer and an output layer; The input parameters of the input layer Satisfies the first formula, which is: ； in, is the axial force at the current moment, is the horizontal amplitude at the current moment, is the horizontal frequency at the current moment, is the torque at the current moment, is the current temperature, is the humidity at the current moment, is the characteristic value of the acoustic emission signal at the current moment; The hidden layer uses the Sigmoid activation function ,in, is the input value, and the number of neurons in the hidden layer is , the output of the hidden layer Satisfies the second formula, which is: ； in, represents the hidden layer, The input layer neurons to the hidden layer Middle The weights of neurons, The input layer The input parameters of neurons, For the hidden layer Middle The bias of a neuron, is the number of neurons in the input layer; The output parameters of the output layer is the loading parameter that needs to be adjusted. The output layer adopts a linear activation function. The output parameters of neurons Satisfies the third formula, which is: ； in, represents the output layer, The hidden layer neurons to the output layer Middle The weights of neurons, For the output layer Middle The bias of a neuron, is the number of neurons in the output layer.

9. The method for testing fretting friction and wear of aviation transmission components 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 back propagation algorithm to minimize the error between the network output and the expected output. The error function uses the mean square error , the error function is: ； in, is the number of training samples, For the The first sample The expected output, Express expectations, For the The first sample Network output.

10. The method for testing fretting friction and wear of aviation transmission components according to claim 6, characterized in that: The method further comprises: calculating the friction coefficients of the first test piece and the second test piece; measuring the wear volume of the first test piece and the second test piece; Fatigue life prediction is performed on the first test piece and the second test piece.

Images