Aircraft Coating Abrasion Resistance Simulation Testing Device

Abstract

This utility model discloses a simulation testing device for the wear resistance of aircraft coatings, belonging to the technical field of testing devices. The utility model includes a housing, with a multi-station clamping assembly and an environmental simulation assembly fixedly connected to the inner cavity of the housing. The multi-station clamping assembly includes a connecting plate, and a placement plate is fixedly connected to the surface of the connecting plate. This utility model effectively improves testing efficiency through the multi-station clamping assembly, solving the problem of long testing times at a single station in existing devices. The connecting plate provides stable support for the placement plate. Within the mounting groove on the placement plate, a lead screw rotates flexibly under the action of a bearing, driving the clamping plate to move. Combined with the positioning plate, multiple samples can be securely clamped simultaneously. This allows multiple parallel experiments or comparative tests of different coating formulations to be carried out concurrently, significantly shortening the overall testing time, meeting batch testing requirements, and ensuring the stability of sample clamping, avoiding the impact of clamping problems on test results.

Description

Technical Field

[0001] This utility model belongs to the technical field of testing devices, and in particular relates to a simulation testing device for the wear resistance performance of aircraft coatings. Background Technology

[0002] In the aerospace industry, the wear resistance of aircraft surface coatings directly affects the durability, aerodynamic performance, and maintenance costs of the fuselage structure. When flying at high altitudes, aircraft must withstand the test of low-pressure and low-temperature environments for extended periods, while also facing wear conditions such as airflow erosion and impact from tiny particles. Therefore, simulation tests of coating wear resistance must rigorously reproduce the actual flight environment.

[0003] Existing aircraft coating wear resistance testing devices mostly adopt a single-station clamping structure, which can only test one sample at a time. For scenarios that require multiple parallel experiments or comparative tests of different coating formulations, the time consumption is greatly increased, which cannot meet the needs of batch testing. Furthermore, it cannot accurately reproduce the low-pressure and low-temperature environment at an altitude of 10,000 meters, resulting in deviations between the test environment and actual working conditions.

[0004] To address these issues, we have provided an aircraft coating abrasion resistance simulation testing device. Utility Model Content

[0005] The purpose of this invention is to provide a simulation testing device for the wear resistance of aircraft coatings. By combining an environmental simulation component and a multi-station clamping component, it solves the problem that existing testing devices mostly use a single-station clamping structure and cannot accurately reproduce the low-pressure and low-temperature environment at an altitude of 10,000 meters, resulting in deviations between the testing environment and actual working conditions.

[0006] To solve the above-mentioned technical problems, this utility model is achieved through the following technical solution.

[0007] This utility model relates to a simulation testing device for the wear resistance of aircraft coatings, comprising a housing. A multi-station clamping assembly and an environmental simulation assembly are fixedly connected to the inner cavity of the housing. The multi-station clamping assembly includes a connecting plate, a placement plate fixedly connected to the surface of the connecting plate, a positioning plate fixedly connected to one side of the placement plate, and an installation groove formed on the surface of the placement plate. A lead screw is fixedly connected to the inner cavity of the installation groove via a bearing, and a clamping plate is threadedly connected to the surface of the lead screw. The environmental simulation assembly includes a rotary motor fixedly connected to the back of the clamping plate, mounting seats fixedly connected to both sides of the rotary motor, and one side of the mounting seat fixedly connected to the back of the housing. A heat exchange tube is fixedly connected to the inner cavity of the housing, with both ends of the heat exchange tube extending through to the back of the housing and communicating with an external compressor. A solenoid valve is fixedly connected to the bottom of the back of the housing, and a vacuum tube is connected to the back of the solenoid valve. The other end of the vacuum tube is connected to a vacuum pump. A sandblasting pipe is connected to the bottom of the surface of the housing, and the other end of the sandblasting pipe is connected to an external sandblasting machine. A temperature sensor and a pressure sensor are fixedly connected to the inner wall of the housing.

[0008] The present invention is further configured such that the box body includes an outer shell, an inner liner is fixedly connected to the inner cavity of the outer shell, a cover plate is hinged to the surface of the outer shell, and a sealing block is fixedly connected to the back of the cover plate. The sealing block is in close contact with the inner wall of the inner liner. The outer shell and the inner liner enhance the structural strength and thermal insulation performance of the box body. The cover plate is connected by a hinge for easy opening and closing, and the sealing block ensures the airtightness of the box body, preventing the environmental parameters inside the box from being affected by the outside world.

[0009] The present invention is further configured such that the heat exchange tube is sleeved on the surface of the inner liner, and the inner liner is made of pure copper. The heat exchange tube sleeved on the surface of the inner liner can exchange heat with the inner liner more efficiently, improve the temperature regulation efficiency, and the inner liner made of pure copper has good thermal conductivity, which helps the temperature inside the box to quickly reach the set value.

[0010] The present invention is further configured such that the sandblasting pipe is fixedly connected to the bottom of the cover plate surface. The sandblasting pipe is fixed to the bottom of the cover plate surface, which facilitates the accurate introduction of sand particles into the box when the cover plate is closed, ensuring the rationality of the sandblasting position and better simulating the impact condition of particulate matter.

[0011] The present invention is further configured such that there are two temperature sensors and two pressure sensors, which are arranged in a circumferentially spaced manner. The two temperature sensors and two pressure sensors arranged in a circumferentially spaced manner can more comprehensively monitor the temperature and pressure at different locations inside the chamber, thereby improving the accuracy of environmental parameter monitoring.

[0012] The present invention is further configured such that support legs are fixedly connected to both sides of the bottom of the outer shell, and mounting holes are provided at the bottom of the support legs. The support legs provide stable support for the box, making it more stable, and the mounting holes facilitate fixing the box in a designated position to prevent the box from shaking during the test.

[0013] The present invention is further configured such that a controller and a handle are fixedly connected to the surface of the cover plate respectively. The controller is electrically connected to the electrical equipment through wires. The controller can centrally control each electrical device, making it convenient for operators to adjust test parameters. The handle facilitates the opening and closing of the cover plate, improving the ease of use of the device.

[0014] The present invention is further configured such that a throttle is fixedly connected to one end of the lead screw located outside the mounting groove. The surface of the throttle is provided with anti-slip texture. The throttle makes it easy for the operator to rotate the lead screw. The anti-slip texture increases the friction between the hand and the throttle, preventing slippage during rotation and making the adjustment of the clamping plate more effortless and convenient.

[0015] The present invention has the following beneficial effects.

[0016] 1. This utility model effectively improves the testing efficiency through a multi-station clamping assembly, solving the problem of long testing time at a single station in existing devices. The connecting plate provides stable support for the placement plate. In the mounting slot on the placement plate, the lead screw rotates flexibly under the action of the bearing, driving the clamping plate to move. Combined with the positioning plate, multiple samples can be firmly clamped at the same time. This allows multiple parallel experiments or comparative tests of different coating formulations to be carried out simultaneously, greatly shortening the overall testing time, meeting the needs of batch testing, and ensuring the stability of sample clamping, avoiding the impact of clamping problems on test results.

[0017] 2. The environmental simulation component of this utility model can accurately reproduce the high-altitude flight environment of an aircraft, overcoming the shortcomings of insufficient environmental simulation accuracy in existing devices. The rotary motor provides power for the operation of related structures, the heat exchange tube works with the external compressor to regulate the temperature inside the chamber, the solenoid valve, vacuum tube and vacuum pump work together to control the air pressure, the sandblasting pipe is connected to an external sandblasting machine to simulate particle impact, and the temperature sensor and pressure sensor monitor environmental parameters in real time to ensure that environmental parameters such as low pressure and low temperature inside the chamber are consistent with the actual flight conditions, thereby improving the accuracy of test results. Attached Figure Description

[0018] To more clearly illustrate the technical solutions of the embodiments of this utility model, the accompanying drawings used in the description of the embodiments will be briefly introduced below.

[0019] Figure 1 A three-dimensional view of a device for simulating the abrasion resistance of aircraft coatings.

[0020] Figure 2This is a rear view schematic diagram of an aircraft coating abrasion resistance simulation test device.

[0021] Figure 3 This is a schematic diagram of the unfolded test device for simulating the wear resistance of aircraft coatings.

[0022] Figure 4 This is a schematic cross-sectional view of a part of the aircraft coating wear resistance simulation test device.

[0023] Figure 5 A three-dimensional schematic diagram of the multi-station clamping components in an aircraft coating wear resistance simulation testing device.

[0024] In the attached diagram: 1. Housing; 11. Outer shell; 12. Inner liner; 13. Cover plate; 14. Support leg; 15. Controller; 2. Multi-station clamping assembly; 21. Connecting plate; 22. Placement plate; 23. Positioning plate; 24. Mounting slot; 25. Lead screw; 26. Clamping plate; 3. Environmental simulation assembly; 31. Rotary motor; 32. Heat exchange tube; 33. Solenoid valve; 34. Vacuum tube; 35. Sandblasting tube; 36. Temperature sensor; 37. Pressure sensor. Detailed Implementation

[0025] The technical solutions of the present utility model will be described below with reference to the accompanying drawings. The described embodiments are only some embodiments of the present utility model, and not all embodiments.

[0026] Example 1

[0027] Please see Figure 1-5 This utility model is a simulation testing device for the wear resistance of aircraft coatings, including a housing 1. A multi-station clamping assembly 2 and an environmental simulation assembly 3 are fixedly connected to the inner cavity of the housing 1. The multi-station clamping assembly 2 includes a connecting plate 21, a placement plate 22 fixedly connected to the surface of the connecting plate 21, a positioning plate 23 fixedly connected to one side of the placement plate 22, and an installation groove 24 formed on the surface of the placement plate 22. A lead screw 25 is fixedly connected to the inner cavity of the installation groove 24 via a bearing. A clamping plate 26 is threadedly connected to the surface of the lead screw 25. The environmental simulation assembly 3 includes a rotary motor 31 fixedly connected to the back of the clamping plate 26. Both sides of the rotary motor 31 are fixedly connected to mounting bases. One side of the mounting base is fixedly connected to the back of the housing 1. A heat exchange tube 32 is fixedly connected to the inner cavity of the housing 1. Both ends of the heat exchange tube 32 extend to the back of the housing 1 and are connected to an external compressor. A solenoid valve 33 is fixedly connected to the bottom of the back of the housing 1. A vacuum tube 34 is connected to the back of the solenoid valve 33. The other end of the vacuum tube 34 is connected to a vacuum pump. A sandblasting tube 35 is connected to the bottom of the surface of the housing 1. The other end of the sandblasting tube 35 is connected to an external sandblasting machine. A temperature sensor 36 and a pressure sensor 37 are fixedly connected to the inner wall of the housing 1.

[0028] Specifically: the placement plate 22 is used to carry the test sample. A positioning plate 23 is fixedly connected to one side of the placement plate 22. The positioning plate 23 can position one side of the sample. The mounting groove 24 provides installation space for the lead screw 25 and the clamping plate 26. The inner cavity of the mounting groove 24 is fixedly connected to the lead screw 25 through the bearing. The lead screw 25 can rotate smoothly under the support of the bearing. The surface of the lead screw 25 is threadedly connected to the clamping plate 26. The heat exchange tube 32 can regulate the temperature inside the chamber 1 through heat exchange. The solenoid valve 33 can control the opening and closing of the vacuum tube 34. The vacuum tube 34 is used to extract air from the chamber 1. The sandblasting tube 35 can introduce sand particles into the chamber 1. The temperature sensor 36 and the pressure sensor 37 are used to monitor the temperature and pressure inside the chamber 1 in real time.

[0029] Example 2

[0030] Please see Figure 1-5 Based on Embodiment 1, the housing 1 includes an outer shell 11, an inner liner 12 fixedly connected to the inner cavity of the outer shell 11, a cover plate 13 hinged to the surface of the outer shell 11, a sealing block fixedly connected to the back of the cover plate 13, the sealing block being in close contact with the inner wall of the inner liner 12, a heat exchange tube 32 sleeved on the surface of the inner liner 12, the inner liner 12 being made of pure copper, a sandblasting tube 35 fixedly connected to the bottom of the surface of the cover plate 13, two temperature sensors 36 and two pressure sensors 37 arranged in a circumferentially spaced manner, support legs 14 fixedly connected to both sides of the bottom of the outer shell 11, mounting holes being provided at the bottom of the support legs 14, a controller 15 and a handle fixedly connected to the surface of the cover plate 13 respectively, the controller 15 being electrically connected to electrical equipment via wires, a throttle fixedly connected to one end of the lead screw 25 located outside the mounting groove 24, the surface of the throttle being provided with anti-slip texture.

[0031] Specifically: the outer shell 11 and inner liner 12 enhance the structural strength and insulation performance of the chamber 1; the cover 13 is hinged for easy opening and closing; the sealing block ensures the airtightness of the chamber 1, preventing external influences on the internal environmental parameters; the heat exchange tube 32 is fitted onto the surface of the inner liner 12, enabling more efficient heat exchange and improving temperature regulation efficiency; the pure copper inner liner 12 has good thermal conductivity, helping the temperature inside the chamber 1 to quickly reach the set value; the sandblasting tube 35 is fixed to the bottom of the cover 13 surface, facilitating accurate introduction of sand particles into the chamber 1 when the cover 13 is closed, ensuring the rationality of the sandblasting position and better simulating particulate impact conditions; the two are spaced apart. The circumferentially arranged temperature sensor 36 and pressure sensor 37 can more comprehensively monitor the temperature and pressure at different locations inside the chamber 1, improving the accuracy of environmental parameter monitoring. The support leg 14 provides stable support for the chamber 1, making it more stable. The mounting hole makes it easy to fix the chamber 1 in a designated position, preventing the chamber 1 from shaking during the test. The controller 15 can centrally control various electrical devices, making it convenient for operators to adjust test parameters. The handle facilitates the opening and closing of the cover plate 13, improving the ease of use of the device. The throttle makes it easy for operators to turn the screw 25. The anti-slip texture increases the friction between the hand and the throttle, preventing slippage during rotation, making the adjustment of the clamping plate 26 more effortless and convenient.

[0032] The working principle of this utility model is as follows: First, the screw 25 is rotated by the throttle to make the clamping plate 26 cooperate with the positioning plate 23, fixing multiple test samples on the placement plate 22. The cover plate 13 is closed, and the sealing block ensures that the chamber 1 is sealed. The external compressor is started by the controller 15, and the heat exchange tube 32 starts to work to adjust the temperature inside the chamber 1. At the same time, the vacuum pump is started to extract air from the chamber 1 through the vacuum tube 34 and the solenoid valve 33 to adjust the air pressure. The temperature sensor 36 and the pressure sensor 37 transmit the temperature and pressure information inside the chamber 1 to the controller 15 in real time so that the operator can monitor and adjust it to make the chamber 1 form a low-pressure and low-temperature environment like that of an aircraft flying at high altitude. Then, the external sandblasting machine is started, and sand particles enter the chamber 1 through the sandblasting pipe 35 to simulate the working conditions of airflow scouring and impact of small particles. At the same time, the rotating motor 31 drives the multi-station clamping assembly 2 to rotate, thereby driving the sample to rotate at high speed to simulate the flight speed and perform wear resistance test on the sample. After the test is completed, all equipment is turned off, the cover plate 13 is opened and the sample is taken out.

[0033] The preferred embodiments of the present utility model disclosed above are only used to help illustrate the present utility model. The preferred embodiments do not describe all the details in detail, nor do they limit the present utility model to the specific implementation methods described. The present specification selects and specifically describes these embodiments in order to better explain the principle and practical application of the present utility model, so that those skilled in the art can better understand and utilize the present utility model.

Claims

1. A device for simulating the wear resistance of an aircraft coating, comprising a box (1), characterized in that: The inner cavity of the box (1) is fixedly connected to a multi-station clamping assembly (2) and an environmental simulation assembly (3); The multi-station clamping assembly (2) includes a connecting plate (21), a placement plate (22) is fixedly connected to the surface of the connecting plate (21), a positioning plate (23) is fixedly connected to one side of the placement plate (22), an installation groove (24) is opened on the surface of the placement plate (22), a lead screw (25) is fixedly connected to the inner cavity of the installation groove (24) through a bearing, and a clamping plate (26) is threadedly connected to the surface of the lead screw (25). The environmental simulation component (3) includes a rotary motor (31) fixedly connected to the back of the clamping plate (26). Both sides of the rotary motor (31) are fixedly connected to mounting bases. One side of the mounting base is fixedly connected to the back of the housing (1). The inner cavity of the housing (1) is fixedly connected to a heat exchange tube (32). Both ends of the heat exchange tube (32) extend through to the back of the housing (1) and are connected to an external compressor. The bottom of the back of the housing (1) is fixedly connected to a solenoid valve (33). The back of the solenoid valve (33) is connected to a vacuum tube (34). The other end of the vacuum tube (34) is connected to a vacuum pump. The bottom of the surface of the housing (1) is connected to a sandblasting pipe (35). The other end of the sandblasting pipe (35) is connected to an external sandblasting machine. The inner wall of the housing (1) is fixedly connected to a temperature sensor (36) and a pressure sensor (37).

2. The aircraft coating wear performance simulation test apparatus of claim 1, wherein: The box (1) includes an outer shell (11), an inner liner (12) is fixedly connected to the inner cavity of the outer shell (11), a cover plate (13) is hinged to the surface of the outer shell (11) by a hinge, a sealing block is fixedly connected to the back of the cover plate (13), and the sealing block is in close contact with the inner wall of the inner liner (12).

3. The aircraft coating wear resistance simulation testing device according to claim 2, characterized in that: The heat exchange tube (32) is fitted onto the surface of the inner liner (12), which is made of pure copper.

4. The aircraft coating wear resistance simulation testing device according to claim 2, characterized in that: The sandblasting pipe (35) is fixedly connected to the bottom of the surface of the cover plate (13).

5. The aircraft coating abrasion resistance simulation testing device according to claim 2, characterized in that: The number of temperature sensors (36) and pressure sensors (37) is two, and they are arranged in a circumferentially spaced manner.

6. The aircraft coating wear resistance simulation testing device according to claim 2, characterized in that: Support legs (14) are fixedly connected to both sides of the bottom of the outer shell (11), and mounting holes are provided at the bottom of the support legs (14).

7. The aircraft coating wear resistance simulation testing device according to claim 2, characterized in that: The surface of the cover plate (13) is fixedly connected to a controller (15) and a handle, and the controller (15) is electrically connected to an electrical device via a wire.

8. The aircraft coating abrasion resistance simulation testing device according to claim 1, characterized in that: The screw (25) is fixedly connected to a throttle at one end outside the mounting groove (24), and the surface of the throttle is provided with anti-slip texture.

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