Aviation wing leading edge rubber ice friction wear test device and test method

Abstract

The invention belongs to the technical field of rubber friction and wear testing, and particularly relates to an aviation wing leading edge rubber ice friction and wear testing device and a testing method.The aviation wing leading edge rubber ice friction and wear testing device comprises a low-temperature box, a temperature sensor and a humidity sensor are arranged on the inner wall of the low-temperature box, and a refrigerating machine and a humidifier connected with the low-temperature box are arranged outside the low-temperature box; the temperature sensor, the humidity sensor, the refrigerator and the humidifier are all electrically connected with the control unit; a loading device is arranged in the low-temperature box, a sensor is arranged at the output end of the loading device, a pressing plate for fixing a sample is arranged on the force sensor in an overlapping manner, and the clamp, the loading device and the force sensor are electrically connected with a control unit; an ice mold which can horizontally move and rotate in the low-temperature box and can fix ice blocks is arranged in the low-temperature box. According to the invention, the blank of the ice friction test of the wing leading edge rubber in the prior art is filled, and the problem of insufficient test under extremely low temperature and high humidity conditions in the prior art is solved.

Description

Technical Field

[0001] The invention belongs to the technical field of rubber friction and wear testing, and in particular relates to a device and a method for testing the friction and wear of rubber ice on the leading edge of an aircraft wing. Background Art

[0002] Aviation wing leading edge rubber is a material specially designed to protect the leading edge of the wing. Its main function is to reduce friction and wear under freezing conditions. In the daily operation of aircraft, rubber materials are mainly used to provide wear resistance, anti-icing and drag reduction performance. However, under extremely low temperature and high humidity conditions, the anti-icing effect of the wing leading edge rubber is limited, and icing may still occur. The impact of high-speed airflow causes the ice layer to generate friction on the rubber surface, and the rapid temperature change causes the ice layer to form and melt repeatedly, further aggravating the wear of the rubber. The ice layer after freezing is hard and sharp, and it will significantly increase friction and wear when it comes into contact with rubber, thereby affecting the safety and flight efficiency of aircraft. Therefore, in the research and development process of the leading edge of the aircraft wing, the ice friction coefficient of the wing leading edge rubber is one of the important indicators for evaluating the comprehensive performance of the aircraft wing.

[0003] At present, specialized testing equipment and methods for the ice friction coefficient of wing leading edge rubber are relatively rare. Most existing friction and wear testers are mainly used for material testing under conventional environments, and it is difficult to accurately simulate the extreme low temperature and high humidity environment of the wing leading edge during flight. Therefore, existing testing equipment and methods have many limitations in ice friction coefficient testing, such as imprecise environmental control, inconsistent ice generation and application conditions, and difficulty in capturing the true behavior of rubber under dynamic ice friction. In order to deeply study and evaluate the performance of wing leading edge rubber under ice friction and wear, it is urgent to develop specialized testing equipment and methods to make up for the shortcomings of existing technologies. Summary of the invention

[0004] In order to solve the above technical problems, the present invention provides an aircraft wing leading edge rubber ice friction and wear testing device and testing method.

[0005] The purpose of the present invention is to achieve the following technical solutions. According to the present invention, an aircraft wing leading edge rubber ice friction and wear test device includes a low temperature box, a temperature sensor and a humidity sensor are arranged on the inner wall of the low temperature box, a refrigerator and a humidifier connected to the low temperature box are arranged outside the low temperature box, and the temperature sensor, humidity sensor, refrigerator, and humidifier are all electrically connected to the control unit; a loading device is arranged in the low temperature box, a sensor is arranged at the output end of the loading device, a pressure plate and a clamp for fixing the sample are superimposed on the force sensor, and the loading device and the force sensor are electrically connected to the control unit; an ice mold that can move horizontally and rotate in the low temperature box and can fix ice cubes is arranged in the low temperature box.

[0006] Furthermore, the humidity sensor and temperature sensor are connected to an external control unit via a low-temperature resistant cable, and the low-temperature resistant cable is led out through a sealed interface of the low-temperature box; the low-temperature box is connected to an external refrigerator and humidifier via corresponding insulating conduits.

[0007] Furthermore, the loading device is fixedly connected to the friction positioning test bench, the friction positioning test bench is connected to the upper part of the support rod by bolts, the support rod is fixed to the sample fixing table by bolts, and the sample fixing table is fixed to the base at the bottom of the low temperature box by bolts.

[0008] Furthermore, the loading device adopts a hydraulic system with a hydraulic cylinder as an output device. The lower end of the force sensor is connected to the upper surface of the output shaft of the loading device through bolts, and the upper end is connected to the pressure plate. The force sensor can accurately measure the friction resistance on the pressure plate and transmit the friction resistance value to the data acquisition device in the control unit. The fixture is connected to the top of the pressure plate through bolts, the sample to be tested is set between the pressure plate and the fixture, and a through hole is set in the middle of the fixture.

[0009] Furthermore, the clamp fixes the sample on the pressing plate through bolts and gaskets, and an anti-slip pad is provided on the surface where the clamp matches the sample.

[0010] Furthermore, the ice mold is arranged on the rotating shaft of the rotating motor, and the rotating motor is arranged on a slider in the low temperature box; the slider is a slider on a ball screw structure, the ball screw is connected to the movable motor, and the movable motor is fixed in the low temperature box; a rotation controller and a front and rear movable controller are arranged on the outer wall of the low temperature box, and are electrically connected to the corresponding rotating motor and movable motor respectively.

[0011] Furthermore, the top of the ice mold is a fixed head, which is connected to the rotating shaft of the rotating motor. The lower part of the fixed head is slidably provided with a plurality of mold petals distributed around the axis of the ice mold. The plurality of mold petals combine to form a complete mold. The plurality of mold petals can move synchronously centrifugally or centrifugally. The shape of the inner cavity surrounded by the middle of the mold petals is the shape of the required ice cube. The inner cavity of the mold petals extends to the upper and lower ends and passes through the mold. The cavity in the upper part of the mold is the shape of the middle cavity after proportional enlargement, and the cavity in the lower part of the mold petal is the shape of the middle cavity after proportional reduction. A clamp is slidably provided at the bottom of each mold petal, and a channel connected to a conduit and communicating with the inner cavity of the ice mold is provided inside the fixed head. The transported ice cubes enter the inner cavity of the ice mold through the conduit and the channel.

[0012] Furthermore, an ice maker is arranged outside the low-temperature box, and the ice maker transports the ice cubes generated by the ice maker to the mold inside the low-temperature box through a conduit, and a heating wire is installed in the wall of the conduit.

[0013] A method for testing the friction and wear of rubber ice on the leading edge of an aircraft wing comprises the following steps:

[0014] Prepare the wing leading edge rubber sample, cut it into a circle with a diameter of 3 cm, make the edge of the sample smooth and free of burrs, and clean the sample surface with anhydrous ethanol;

[0015] Clamp the processed rubber sample in the clamp and pressure plate of the sample fixing mechanism to ensure that the sample is fixed and will not move during the test;

[0016] The low-temperature box is sealed, the low-temperature control device is started, and the temperature and humidity in the low-temperature box are adjusted to the preset conditions. The temperature sensor and the humidity sensor monitor the environment in the box in real time, and the data is fed back to the control unit to automatically adjust the refrigeration and humidification process to maintain the stability of the environment in the low-temperature box;

[0017] Set a consistent ice cube on the ice mold, rotate and move the ice mold to adjust the position of the ice cube, place the sample against the ice cube through the loading device and apply a certain pressure, control the forward and backward movement of the ice cube to ensure that the ice cube is evenly applied to the sample surface, so that sliding friction can be generated between the ice cube and the sample;

[0018] The loading device applies pressure according to the preset test parameters, and the force sensor records the friction between the ice cube and the sample surface in real time. The data is transmitted to the data acquisition device for real-time recording and analysis;

[0019] Through data processing and analysis, the ice friction and wear characteristics of the wing leading edge rubber are obtained.

[0020] Compared with the prior art, the present invention is beneficial in that:

[0021] The present invention provides an aviation wing leading edge rubber ice friction and wear test device and test method, which fills the gap in the prior art of wing leading edge rubber ice friction test and solves the problem of insufficient testing in the prior art under extremely low temperature and high humidity conditions. The device can accurately control the temperature and humidity in the low temperature box 1 by constructing a low temperature control device to simulate the actual use environment; by designing a sample fixing mechanism, the sample is prevented from moving, the stability and reliability of the sample during the test are ensured, and a certain pressure can be provided; by an ice cube applying device, consistent ice cubes are generated and accurately applied to the sample surface; by a friction force measurement system, ice cubes can be accurately applied to the sample and friction force data can be collected in real time, and friction force data can be recorded and analyzed in real time to ensure the accuracy and repeatability of the test results. The coordinated work of various systems can accurately evaluate the friction and wear characteristics of aircraft wing leading edge rubber under ice, obtain more accurate and reliable ice friction coefficient test results, and provide reliable data support for its design and optimization in practical applications, so as to improve the design and performance of wing leading edge rubber, and provide a solid scientific basis for the anti-icing design, optimization and performance evaluation of aircraft wing leading edge rubber materials, help improve the wear resistance and anti-icing effect of aircraft wings under extreme flight conditions, and improve flight safety and efficiency.

[0022] The above description is only an overview of the technical solution of the present invention. In order to more clearly understand the technical means of the present invention, it can be implemented in accordance with the contents of the specification. In order to make the above and other purposes, features and advantages of the present invention more obvious and easy to understand, the following specifically cites a preferred embodiment and describes it in detail with the accompanying drawings as follows. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 It is an overall schematic diagram of an embodiment of an aircraft wing leading edge rubber ice friction and wear testing device of the present invention;

[0024] Figure 2 for Figure 1 Schematic diagram of the structure of the medium and low temperature control device;

[0025] Figure 3 for Figure 1 Schematic diagram of the structure of the sample fixing mechanism;

[0026] Figure 4 for Figure 1 A schematic diagram of the structure of the ice applying device;

[0027] Figure 5 for Figure 4 Cross-sectional view of the medium ice mold.

[0028] [Reference Signs]

[0029] 1-low temperature box, 2-base, 3-control unit, 4-ice maker, 5-sample fixing mechanism, 6-ice cube applying device, 7-stand, 101-humidity sensor, 102-temperature sensor, 103-refrigerator, 104-humidifier, 501-sample fixing table, 502-support rod, 503-loading device, 504-friction positioning test bench, 505-force sensor, 506-pressing plate, 507-clamp, 601-moving motor, 602-sliding guide, 603-rotating motor, 604-ice mold, 6041-fixed head, 6042-mold flap, 605-rotation controller, 606-forward and backward movement controller, 607-ice cube, 608-catheter, 609-grip. DETAILED DESCRIPTION

[0030] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0031] An embodiment of an aircraft wing leading edge rubber ice friction and wear testing device of the present invention is as follows: Figures 1 to 5 The test device includes a low temperature box 1, a base 2, a control unit 3, an ice maker 4, a sample fixing mechanism 5, an ice cube applying device 6, and a stand 7. Figure 1 shown.

[0032] The cryogenic box 1 is used to simulate the actual use environment of the friction and wear of the rubber ice on the leading edge of the aircraft wing. The temperature and humidity of the environment in the cryogenic box 1 are accurately adjusted and maintained by a cryogenic control device. The cryogenic control device includes a humidity sensor 101, a temperature sensor 102, a refrigerator 103, and a humidifier 104. The humidity sensor 101 and the temperature sensor 102 are arranged on the inner wall of the cryogenic box 1 for real-time monitoring of the internal environmental parameters. The humidity sensor and the temperature sensor are connected to the external control unit 3 through a low-temperature resistant cable. The low-temperature resistant cable is led out through the sealing interface of the cryogenic box body to maintain the sealing of the cryogenic box 1, and the data is transmitted to the control unit 3 through the low-temperature resistant cable. The cryogenic box 1 is connected to the external refrigerator 103 and humidifier 104 through the corresponding insulating conduits. The refrigerator 103 is connected to the reserved interface of the cryogenic box 1 through the insulating conduit to ensure that the cold air is stably delivered to the cryogenic box 1. The humidifier 104 is connected to the cryogenic box 1 through another insulating conduit to ensure that the moisture is evenly distributed. The refrigerator 103 and the humidifier 104 are fixed to the special mounting seat outside the cryogenic box 1 by bolts and brackets, such as Figure 2As shown, its stability and working efficiency are guaranteed, and the refrigerant 103, the humidifier 104 are connected to the control unit 3 through a cable. The control unit 3 displays the temperature and humidity in real time according to the data fed back by the humidity sensor 101 and the temperature sensor 102, and adjusts the operating status of the refrigerator 103 and the humidifier 104 to ensure the stability and accuracy of the environment in the low temperature box, accurately adjust the temperature and humidity in the low temperature box 1, and realize the real-time monitoring and adjustment of the test environment and the parameters in the low temperature box 1 during the test process, which effectively guarantees the controllability and consistency of the environmental conditions during the test process.

[0033] like Figure 3As shown, the sample fixing mechanism 5 includes a sample fixing table 501, a support rod 502, a loading device 503, a friction positioning test table 504, a force sensor 505, a pressure plate 506 and a clamp 507. The sample fixing table 501 is fixed to the base 2 at the bottom of the low temperature box 1 by bolts, providing a stable base for the sample fixing mechanism 5. The support rod 502 is fixed above the sample fixing table 501 by bolt connection, providing a vertical support force to prevent tilting or displacement during the test. The friction positioning test table 504 is connected to the upper part of the support rod 502 by bolts to ensure that the sample remains stable when pressure is applied and friction testing is performed. The loading device 503 is fixedly connected to the friction positioning test table 504 above. In this embodiment, the loading device 503 can adopt a hydraulic system with a hydraulic cylinder as an output device, and its output shaft shrinks and extends in the up and down directions. The sample is subjected to a controllable pressure by the loading device 503 to simulate the friction and wear environment under actual working conditions. The loading device 503 is electrically connected to the control unit 3, and the positive pressure applied by the loading device 503 is precisely controlled by the control unit 3 to ensure the uniform transmission of pressure and the stability of the device. The lower end of the force sensor 505 is connected to the upper surface of the output shaft of the loading device 503 by bolts, and the upper end is connected to the pressing plate 506. The force sensor 505 is electrically connected to the control unit 3. The force sensor 505 can accurately measure the friction resistance on the pressing plate 506 and transmit the friction resistance value to the data acquisition device in the control unit 3. The clamp 507 is connected to the top of the pressing plate 506 by bolts, and the sample to be tested (rubber) is set between the pressing plate 506 and the clamp 507, and the sample to be tested is firmly clamped to prevent it from moving or falling off during the test, thereby ensuring the accuracy of the test results. A through hole is set in the middle of the clamp 507 to expose the sample to be tested, so that ice cubes can be inserted into the through hole to contact and rub with the sample. The clamp 507 is made of low-temperature resistant material, and the wing leading edge rubber sample is fixed on the pressing plate by bolts and gaskets. The surface of the fixture 507 in contact with the sample is also equipped with an anti-skid pad to enhance friction, prevent the sample to be tested from moving during the test, and ensure the stability and precise positioning of the sample to be tested in a low temperature and high humidity environment. When the output shaft of the loading device 503 moves upward, the sample to be tested is sent to a position in contact with the ice block 607, and then continues to move upward, directly transmitting the loading force to the force sensor 505 connected thereto through the bolt, and uniformly transmitting the applied force to the pressing plate 506 through the force sensor 505; the pressing plate 506 then uniformly applies the force to the test sample to ensure the accurate transmission and distribution of the loading force during the test. In addition, during the test, the control unit 3 applies the loading force to the force sensor 505 and the pressing plate 506 through the loading device 503, so the positive pressure applied by the loading device 503 is known; the force sensor 505 monitors and records the friction resistance between the sample to be tested and the ice block in real time, so as to accurately quantify the friction coefficient.The data measured by the force sensor 505 is transmitted to the data acquisition device in the control unit 3, thereby realizing automatic control of the test process and accurate recording of data. The control unit 3 can calculate the friction coefficient between the ice and the rubber through the applied pressure and the friction resistance measured by the force sensor 505, realize automatic control of data acquisition and the test process, and ensure the accuracy and reliability of the test.

[0034] like Figure 4 As shown, the ice cube applying device includes an ice maker 4, a moving motor 601, a sliding guide rail 602, a rotating motor 603, an ice mold 604, a rotating controller 605, and a forward and backward moving controller 606. The ice maker 4 is located outside the low temperature box 1, and the ice cubes generated by the ice maker 4 are transported to the inside of the low temperature box 1 through a conduit 608. For the convenience of transportation, the ice generated by the ice maker 4 is usually mixed with water and then transported to the inside of the low temperature box 1. A heating wire is installed in the wall of the conduit 608 to prevent the ice cubes from freezing and clogging during the transportation process, and to help maintain the shape and size of the ice cubes.

[0035] The moving motor 601 is installed on the side stand at the top of the low temperature box 1, and realizes the precise movement of the ice mold 604 by driving the sliding guide rail 602. The sliding guide rail 602 is fixed on the top of the low temperature box 1. In this embodiment, the sliding guide rail 602 adopts a ball screw structure, the rotating motor 603 is fixed on the slider of the ball screw, and the ice mold 604 is fixed on the rotating shaft of the rotating motor 603. The moving motor 601 drives the ball screw to rotate, and then drives the slider to move, thereby moving the rotating motor 603 and the ice mold 604. The ice maker 4 is connected to the cooling system through a refrigerant pipeline, and the generated ice cubes 607 are transported from the ice maker 4 to the ice mold 604 through a conduit 608, and the ice cubes 607 remain in a solid state in the conduit 608. The rotation controller 605 and the forward and backward movement controller 606 are respectively fixed on the base, and are respectively electrically connected to the corresponding rotating motor 603 and the moving motor 601, and are used to adjust the position and angle of the ice mold 604. The rotation controller 605 controls the ice mold 604 to rotate in the horizontal direction, and the forward and backward movement controller 606 controls the forward and backward movement of the ice mold 604 to ensure the precise positioning and movement of the ice cube to obtain accurate friction test results. The ice mold 604 is provided with cooling channels inside, which are evenly distributed inside the mold to ensure that the ice cube 607 maintains a consistent shape and size during the freezing process. After the ice cube 607 is further solidified and formed in the ice mold 604, the ice cube fits tightly against the inner wall of the ice mold so that the ice cube 607 meets the required shape; the position of the ice cube 607 is locked by the clamping mechanism of the ice mold 604 (such as the clamping claw 609) to ensure that it will not be displaced or loosened during the test, thereby ensuring the stability and consistency of the ice cube during the test, thereby improving the accuracy and reliability of the data.

[0036] The shape of the inner cavity of the ice mold 604 is determined according to the shape of the ice block that produces sliding friction with the aircraft wing rubber. Figure 5 The shape shown is used as an example for explanation. The top of the ice mold 604 is a fixed head 6041, and the fixed head 6041 is connected to the rotating shaft of the rotating motor 603. The lower part of the fixed head 6041 is slidably provided with multiple mold petals 6042 distributed around the axis of the ice mold 604. The multiple mold petals 6042 are combined into a complete mold, and the multiple mold petals 6042 move synchronously centrifugally or centrifugally. The shape of the inner cavity surrounded by the middle part of the mold petal 6042 is the shape of the required ice cube. At the same time, the inner cavity of the mold petal 6042 extends to the upper and lower ends and passes through the mold. The cavity in the upper part of the mold is the shape of the middle cavity after proportional enlargement, and the cavity in the lower part of the mold petal 6042 is the shape of the middle cavity after proportional reduction. The principle of the movement of the mold petal 6042 on the fixed head 6041 is the same as the principle of the movement of the jaws on the three-jaw chuck, which can be driven by hydraulic or electric means, and will not be repeated here. The bottom of each mold flap 6042 is provided with a clamping claw 609 for sliding. The sliding principle of the clamping claw 609 on the mold flap 6042 is the same as the sliding principle of the mold flap 6042 on the fixed head 60401, which will not be repeated here. A channel connected to the conduit 608 and connected to the inner cavity of the ice mold 604 is provided inside the fixed head 6041, and the transported ice cube enters the inner cavity of the ice mold 604 through the channel. Since the shape of the ice cube 607 after being made in the ice maker 4 has preliminarily met the requirements, the ice cube 607 directly enters the middle cavity after entering the inner cavity of the ice mold 604, and the shape of the ice cube is further standardized in the middle cavity. After the shape is standardized, the mold flap 6042 is loosened for a certain distance, so that the ice cube 607 can move downward for a distance, so that the ice cube 607 can move to extend out of the ice mold 604, and pass through the clamping claw 609, and the clamping claw 609 clamps the ice cube to achieve the fixation of the ice cube 607. The water in the ice-water mixture flows out from the gaps in the ice mold 604. The ice mold 604 is then rotated and moved, and the sample is then placed against the ice block 607, so that the relative position of the ice block 607 and the sample to be tested can simulate the actual friction situation. For ease of explanation, Figure 5 The shape of the hollow cavity is simplified to a conical cavity, and in practical applications, it can be set according to the shape of the actual ice cube. The ice cube applying device can be used to process the ice cube into an ice cube that meets the test requirements before clamping and fixing.

[0037] The force sensor 505, the loading device 503, the ice cube applying device, and the control unit 3 in the sample fixing mechanism 5 together constitute a friction force measurement system. The data acquisition device is connected to the force sensor through a signal cable, collects and processes friction force data in real time, and cooperates with the control unit 3 to automatically manage the loading device 503 and the data acquisition device, thereby ensuring automation and precise control during the test process. The friction between the ice cube and the sample to be tested is measured by the force sensor 505, and the friction coefficient is calculated by the friction force and the pressure applied by the loading device 503.

[0038] In other embodiments, the ball screw structure of the sliding guide rail can be replaced with an ordinary slide rail, the rotary motor is fixed on the slider of the slide rail, and the movable motor is replaced with a linear motor. The output shaft of the linear motor is connected to the slider to drive the rotary motor to move.

[0039] In other embodiments, the ice mold can be removed and only the clamping claws are retained. After the ice cubes are clamped with the clamping claws, the low temperature box is closed and the test is started.

[0040] Based on the above-mentioned aircraft wing leading edge rubber ice friction and wear testing device, the present invention proposes an aircraft wing leading edge rubber ice friction and wear testing method, comprising the following steps:

[0041] First, prepare the wing leading edge rubber sample and cut it into a circle with a diameter of 3 cm. Make sure the edge of the sample is smooth and free of burrs. Clean the surface of the sample with anhydrous ethanol to remove dust and grease, and ensure that its surface is dry and free of pollution.

[0042] Clamp the processed rubber sample in the clamp 507 and the pressing plate 506 of the sample fixing mechanism 4 to ensure that the sample is fixed and will not move during the test. The sample fixing mechanism 4 provides stable support through the base 2 and the support rod 502 to ensure the accurate positioning of the sample during the test;

[0043] The low temperature box 1 is sealed, the low temperature control device is started, the temperature and humidity in the low temperature box are adjusted to the preset conditions, the temperature sensor and the humidity sensor monitor the environment in the box in real time, and the data is fed back to the control unit 3, and the refrigeration and humidification process is automatically adjusted to maintain the stability of the environment in the low temperature box;

[0044] The ice cubes 607 generated by the ice maker 4 are transported to the ice mold 604 through the conduit to obtain consistent ice cubes. The contact between the ice cubes 607 and the sample surface is accurately positioned by moving the motor 601 and rotating the motor 603. The rotation controller 605 adjusts the angle of the ice cubes 607 so that the angle between the ice cubes 607 and the sample is reasonably set. The sample is pressed against the ice cubes and a certain pressure is applied by the loading device. The forward and backward movement controller 606 controls the forward and backward movement of the ice cubes by moving the motor 607 to ensure that the ice cubes are evenly applied to the sample surface, so that sliding friction can be generated between the ice cubes 607 and the sample.

[0045] The loading device 503 applies a certain pressure according to the preset test parameters, and the force sensor 505 records the friction between the ice cube and the sample surface in real time, and the data is transmitted to the data acquisition device for real-time recording and analysis;

[0046] Through data processing and analysis, the ice friction and wear characteristics of the wing leading edge rubber are obtained.

[0047] The present invention provides an aviation wing leading edge rubber ice friction and wear test device and test method, which fills the gap in the prior art of wing leading edge rubber ice friction test and solves the problem of insufficient testing in the prior art under extremely low temperature and high humidity conditions. The device can accurately control the temperature and humidity in the low temperature box 1 by constructing a low temperature control device to simulate the actual use environment; by designing a sample fixing mechanism, the sample is prevented from moving, the stability and reliability of the sample during the test are ensured, and a certain pressure can be provided; by an ice cube applying device, consistent ice cubes are generated and accurately applied to the sample surface; by a friction force measurement system, ice cubes can be accurately applied to the sample and friction force data can be collected in real time, and friction force data can be recorded and analyzed in real time to ensure the accuracy and repeatability of the test results. The coordinated work of various systems can accurately evaluate the friction and wear characteristics of aircraft wing leading edge rubber under ice, obtain more accurate and reliable ice friction coefficient test results, and provide reliable data support for its design and optimization in practical applications, so as to improve the design and performance of wing leading edge rubber, and provide a solid scientific basis for the anti-icing design, optimization and performance evaluation of aircraft wing leading edge rubber materials, help improve the wear resistance and anti-icing effect of aircraft wings under extreme flight conditions, and improve flight safety and efficiency.

[0048] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. An aircraft wing leading edge rubber ice friction and wear test device, comprising a low temperature box, characterized in that: A temperature sensor and a humidity sensor are arranged on the inner wall of the low temperature box, a refrigerator and a humidifier connected to the low temperature box are arranged outside the low temperature box, and the temperature sensor, humidity sensor, refrigerator and humidifier are all electrically connected to the control unit; a loading device is arranged in the low temperature box, a sensor is arranged at the output end of the loading device, a pressing plate and a clamp for fixing the sample are superimposed on the force sensor, and the loading device and the force sensor are electrically connected to the control unit; an ice mold is arranged in the low temperature box, which can move horizontally and rotate in the low temperature box and can fix ice cubes.

2. The aircraft wing leading edge rubber ice friction and wear testing device according to claim 1, characterized in that: The humidity sensor and the temperature sensor are connected to an external control unit via a low-temperature resistant cable, which is led out through a sealed interface of the low-temperature box; the low-temperature box is connected to an external refrigerator and humidifier via corresponding insulating conduits.

3. The aircraft wing leading edge rubber ice friction and wear testing device according to claim 1, characterized in that: The loading device is fixedly connected to the friction positioning test bench, the friction positioning test bench is connected to the upper part of the support rod by bolts, the support rod is fixed to the sample fixing table by bolts, and the sample fixing table is fixed to the base at the bottom of the low temperature box by bolts.

4. The aircraft wing leading edge rubber ice friction and wear testing device according to claim 1, characterized in that: The loading device adopts a hydraulic system with a hydraulic cylinder as an output device. The lower end of the force sensor is connected to the upper surface of the output shaft of the loading device through bolts, and the upper end is connected to the pressure plate. The force sensor can accurately measure the friction resistance on the pressure plate and transmit the friction resistance value to the data acquisition device in the control unit. The fixture is connected to the top of the pressure plate through bolts, the sample to be tested is set between the pressure plate and the fixture, and a through hole is set in the middle of the fixture.

5. The aircraft wing leading edge rubber ice friction and wear testing device according to claim 4, characterized in that: The clamp fixes the sample on the pressing plate through bolts and gaskets, and an anti-slip pad is arranged on the surface where the clamp matches the sample.

6. The aircraft wing leading edge rubber ice friction and wear testing device according to claim 1, characterized in that: The ice mold is arranged on the rotating shaft of the rotating motor, and the rotating motor is arranged on a slider in the low temperature box; the slider is a slider on a ball screw structure, the ball screw is connected to the moving motor, and the moving motor is fixed in the low temperature box; a rotating controller and a front and rear moving controller are arranged on the outer side wall of the low temperature box, and are electrically connected to the corresponding rotating motor and moving motor respectively.

7. The aircraft wing leading edge rubber ice friction and wear testing device according to claim 6, characterized in that: The top of the ice mold is a fixed head, which is connected to the rotating shaft of the rotating motor. The lower part of the fixed head is slidably provided with a plurality of mold petals distributed around the axis of the ice mold. The plurality of mold petals are combined into a complete mold. The plurality of mold petals can move synchronously centrifugally or centrifugally. The shape of the inner cavity surrounded by the middle of the mold petals is the shape of the required ice cube. The inner cavity of the mold petals extends to the upper and lower ends and passes through the mold. The cavity in the upper part of the mold is the shape of the middle cavity enlarged in proportion, and the cavity in the lower part of the mold petal is the shape of the middle cavity reduced in proportion. A clamp is slidably provided at the bottom of each mold petal, and a channel connected to a conduit and communicating with the inner cavity of the ice mold is provided inside the fixed head. The transported ice cubes enter the inner cavity of the ice mold through the conduit and the channel.

8. The aircraft wing leading edge rubber ice friction and wear testing device according to claim 7, characterized in that: An ice maker is arranged outside the low-temperature box, and the ice cubes generated by the ice maker are transported to the ice mold inside the low-temperature box through a conduit, and a heating wire is arranged in the wall of the conduit.

9. A method for testing the friction and wear of rubber ice on the leading edge of an aircraft wing, characterized in that: The following steps are involved: Prepare the wing leading edge rubber sample, cut it into a circle with a diameter of 3 cm, make the edge of the sample smooth and free of burrs, and clean the sample surface with anhydrous ethanol; Clamp the processed rubber sample in the clamp and pressure plate of the sample fixing mechanism to ensure that the sample is fixed and will not move during the test; The low-temperature box is sealed, the low-temperature control device is started, and the temperature and humidity in the low-temperature box are adjusted to the preset conditions. The temperature sensor and the humidity sensor monitor the environment in the box in real time, and the data is fed back to the control unit to automatically adjust the refrigeration and humidification process to maintain the stability of the environment in the low-temperature box; Set a consistent ice cube on the ice mold, rotate and move the ice mold to adjust the position of the ice cube, place the sample against the ice cube through the loading device and apply a certain pressure, control the forward and backward movement of the ice cube to ensure that the ice cube is evenly applied to the sample surface, so that sliding friction can be generated between the ice cube and the sample; The loading device applies pressure according to the preset test parameters, and the force sensor records the friction between the ice cube and the sample surface in real time. The data is transmitted to the data acquisition device for real-time recording and analysis; Through data processing and analysis, the ice friction and wear characteristics of the wing leading edge rubber are obtained.

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