System and method for comprehensive environmental simulation test of rotating parts

Abstract

The application provides a comprehensive environment simulation test system for rotating parts, comprising a vacuum cabin, a high-low temperature test subsystem arranged in the vacuum cabin and provided with a first temperature control assembly for cooling the vacuum cabin and a second temperature control assembly for heating the vacuum cabin, a high vacuum obtaining subsystem connected with the vacuum cabin for adjusting the vacuum degree of the vacuum cabin, a micro-gravity simulation subsystem arranged in the vacuum cabin and provided with a magnetic suspension bearing connected with the rotating part to be tested, a dynamic torque test subsystem provided with a driving motor, a magnetic powder brake and at least one shaft coupling, the driving motor and the magnetic powder brake being connected with the rotating part to be tested in the vacuum cabin through the shaft coupling and at least one magnetic fluid dynamic sealing device, and a dynamic parameter measurement subsystem arranged in the vacuum cabin and provided with at least one measurement unit for obtaining the dynamic parameters of the rotating part to be tested. Therefore, the application can improve the effectiveness of the space environment simulation test of the rotating part.

Description

Technical Field

[0001] This invention relates to the field of space environment simulation technology, and in particular to a comprehensive environmental simulation test system and test method for rotating components. Background Technology

[0002] With the continuous development of the space industry, humans are spending longer and longer periods in orbit, placing increasingly stringent demands on the performance indicators of spacecraft to withstand complex space environments. Taking a typical space robotic arm gear transmission system as an example, the combined effects of multiple factors such as alternating high / low temperatures, vacuum, and microgravity in space significantly affect the service performance of the space gear transmission system. Conducting thorough environmental simulation tests is a key technical step in evaluating the reliability and lifespan of space gear transmission systems.

[0003] Given that conventional microgravity simulation techniques such as air flotation, suspension, and drop tower methods are difficult to conduct and implement under thermal vacuum conditions, thermal vacuum tests and microgravity simulation tests of spacecraft rotating components, represented by the gear transmission system of space robotic arms, are currently conducted sequentially. There is no mature joint simulation technology of thermal vacuum-microgravity-dynamic torque, which affects the effectiveness of space environment simulation tests for the next generation of high-parameter space mechanisms.

[0004] In conclusion, the existing methods cannot meet the experimental requirements in practical use, so it is necessary to improve them. Summary of the Invention

[0005] To address the aforementioned shortcomings, the present invention aims to provide a comprehensive environmental simulation test system and method for rotating components, which can build a simulated working condition test platform for a space gear transmission system that comprehensively simulates high vacuum, microgravity, temperature alternation, and dynamic torque, thereby improving the effectiveness of space environment simulation tests for next-generation rotating components.

[0006] To achieve the above objectives, the present invention provides a comprehensive environmental simulation test system for rotating components, comprising:

[0007] Vacuum chamber;

[0008] The high and low temperature test subsystem is placed inside the vacuum chamber and is equipped with a first temperature control component and a second temperature control component. The first temperature control component is used to cool down the vacuum chamber, and the second temperature control component is used to heat up the vacuum chamber.

[0009] A high vacuum acquisition subsystem is connected to the vacuum chamber for adjusting the vacuum level of the vacuum chamber;

[0010] A microgravity simulation subsystem is placed inside the vacuum chamber and is equipped with a magnetic levitation bearing. The magnetic levitation bearing is connected to the rotating component under test to simulate a microgravity environment for the rotating component under test through magnetic levitation.

[0011] The dynamic torque test subsystem includes a drive motor, a magnetic powder brake, and at least one coupling. The drive motor and the magnetic powder brake are connected to the rotating component under test inside the vacuum chamber through the coupling and at least one magnetohydrodynamic sealing device.

[0012] A dynamic parameter measurement subsystem is placed inside the vacuum chamber and is equipped with at least one measurement unit, which is used to acquire the dynamic parameters of the rotating component under test.

[0013] Optionally, the high and low temperature test subsystem switches between a first operating mode and a second operating mode based on the temperature distribution gradient between the rotating component under test and the magnetic levitation bearing, wherein:

[0014] In the first operating mode, the first temperature control component operates to cool the vacuum chamber;

[0015] In the second operating mode, the second temperature control component operates to heat the vacuum chamber.

[0016] Optionally, the first temperature control component includes a heat sink module and a liquid nitrogen module, wherein the liquid nitrogen module is connected to the heat exchange pipeline of the heat sink module for supplying liquid nitrogen to the heat exchange pipeline for heat exchange and cooling; and / or

[0017] The second temperature control component is a thermal radiation lamp array.

[0018] Optionally, the high vacuum acquisition subsystem consists of a backing mechanical pump and a molecular pump.

[0019] Optionally, the rotating component to be tested is a planar gear train, and the magnetic levitation bearing is located in the middle region of the gear shaft of the planar gear train. The magnetic levitation bearing is also equipped with a displacement sensor for real-time acquisition of the gap between the rotor and the magnetic pole of the magnetic levitation bearing, and the magnetic pole coil current of the magnetic levitation bearing is adjusted based on the acquisition data of the displacement sensor.

[0020] Optionally, the microgravity simulation subsystem further includes a protective bearing, and the clearance of the protective bearing is smaller than the gap between the magnetic poles of the magnetic levitation bearing and the rotor; and / or

[0021] It also includes a cold plate for heat conduction with the magnetic pole coil of the magnetic levitation bearing.

[0022] Optionally, the drive motor is connected through the vacuum chamber to the magnetohydrodynamic sealing device via a first coupling, and the magnetic powder brake is connected through a second coupling to the rotor of the drive motor that passes through the vacuum chamber via the magnetohydrodynamic sealing device.

[0023] Optionally, a first torque sensor is installed on the output end of the drive motor, and a second torque sensor is installed on the input end of the magnetic powder brake.

[0024] Optionally, the measurement unit is a high-speed camera, which is used to monitor the dynamic information of the rotating component under test; and / or

[0025] The dynamic parameter measurement subsystem also includes a light source for illuminating the target position of the rotating component under test.

[0026] A test method for a comprehensive environmental simulation test system based on any one of the rotating components described above is also provided, comprising the following steps:

[0027] The vacuum level and test temperature of the vacuum chamber are adjusted by the high vacuum acquisition subsystem and the high and low temperature test subsystem, respectively.

[0028] The microgravity simulation subsystem is activated to suspend the rotating component under test at the center of the magnetic levitation bearing.

[0029] During the operation of the microgravity simulation subsystem, the drive motor and the magnetic powder brake of the dynamic torque test subsystem are activated to drive the rotating component under test;

[0030] The dynamic parameters of the rotating component under test are obtained by at least one of the measurement units of the dynamic parameter measurement subsystem.

[0031] The comprehensive environmental simulation test system for rotating components of the present invention includes a vacuum chamber; a high and low temperature test subsystem, placed inside the vacuum chamber and equipped with a first temperature control component and a second temperature control component, the first temperature control component being used to cool the vacuum chamber and the second temperature control component being used to heat the vacuum chamber; a high vacuum acquisition subsystem, connected to the vacuum chamber for adjusting the vacuum level of the vacuum chamber; a microgravity simulation subsystem, placed inside the vacuum chamber and equipped with a magnetic levitation bearing, the magnetic levitation bearing being connected to the rotating component under test for simulating a microgravity environment for the rotating component under test through magnetic levitation; a dynamic torque test subsystem, equipped with a drive motor, a magnetic powder brake and at least one coupling, the drive motor and the magnetic powder brake being connected to the rotating component under test inside the vacuum chamber through the coupling and at least one magnetohydrodynamic sealing device; and a dynamic parameter measurement subsystem, placed inside the vacuum chamber and equipped with at least one measurement unit, the measurement unit being used to acquire the dynamic parameters of the rotating component under test. Thus, this invention can build a simulated working condition test platform for a space gear transmission system that integrates high vacuum, microgravity, temperature alternation, and dynamic torque simulation, thereby improving the effectiveness of space environment simulation tests for rotating components. Attached Figure Description

[0032] Figure 1This is an overall schematic diagram of the comprehensive environmental simulation test system for the rotating component provided in an embodiment of the present invention;

[0033] Figure 2 A schematic diagram of the microgravity simulation subsystem of the comprehensive environmental simulation test system for the rotating component provided in an embodiment of the present invention;

[0034] Figure 3 A three-dimensional schematic diagram of one embodiment of the microgravity simulation subsystem of the comprehensive environmental simulation test system for the rotating component provided in an embodiment of the present invention;

[0035] Figure 4 A flowchart illustrating the steps of a test method for a comprehensive environmental simulation test system based on the rotating component, as provided in an embodiment of the present invention;

[0036] Figure 5 A detailed flowchart of the comprehensive environmental simulation test system for the rotating component provided in an embodiment of the present invention. Detailed Implementation

[0037] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0038] It should be noted that references to "an embodiment," "embodiment," "example embodiment," etc., in this specification refer to the described embodiment including specific features, structures, or characteristics, but not every embodiment must include these specific features, structures, or characteristics. Furthermore, such expressions do not refer to the same embodiment. Moreover, when describing specific features, structures, or characteristics in conjunction with embodiments, whether or not explicitly described, it is indicated that incorporating such features, structures, or characteristics into other embodiments is within the knowledge of those skilled in the art.

[0039] Furthermore, certain terms are used in the specification and subsequent claims to refer to specific components or parts. Those skilled in the art will understand that manufacturers may use different names or terms to refer to the same component or part. This specification and subsequent claims do not distinguish components or parts by differences in name, but rather by differences in function. The terms "comprising" and "including" used throughout the specification and subsequent claims are open-ended and should be interpreted as "including but not limited to." Additionally, the term "connection" here includes any direct and indirect electrical connection means. Indirect electrical connection means include connections made through other means.

[0040] Figure 1 This invention illustrates a comprehensive environmental simulation test system for rotating components according to an embodiment of the present invention. The system includes a vacuum chamber 5, a high and low temperature test subsystem, a high vacuum acquisition subsystem, a microgravity simulation subsystem, a dynamic torque test subsystem, and a dynamic parameter measurement subsystem, wherein:

[0041] The high and low temperature test subsystem is located inside the vacuum chamber 5 and is equipped with a first temperature control component and a second temperature control component. The first temperature control component is used to cool down the vacuum chamber 5, and the second temperature control component is used to heat up the vacuum chamber 5. The high vacuum acquisition subsystem is connected to the vacuum chamber 5 to adjust the vacuum level of the vacuum chamber 5. The microgravity simulation subsystem is located inside the vacuum chamber 5 and is equipped with a magnetic levitation bearing 12. The magnetic levitation bearing 12 is connected to the rotating component under test to simulate a microgravity environment for the rotating component under test through magnetic levitation. The dynamic torque test subsystem is equipped with a drive motor 1, a magnetic powder brake 20, and at least one coupling 2. The drive motor 1 and the magnetic powder brake 20 are connected to the rotating component under test inside the vacuum chamber 5 through the coupling 2 and at least one magnetohydrodynamic sealing device 4. The dynamic parameter measurement subsystem is located inside the vacuum chamber and is equipped with at least one measurement unit. The measurement unit is used to acquire the dynamic parameters of the rotating component under test. This involves constructing a comprehensive simulation test platform integrating high vacuum, microgravity, temperature alternation, and dynamic torque through high and low temperature test subsystems, high vacuum acquisition subsystems, microgravity simulation subsystems, dynamic torque test subsystems, and dynamic parameter measurement subsystems, thereby improving the effectiveness of space environment simulation tests for rotating components.

[0042] The rotating component to be tested is the product to be tested, specifically a gear product used under high vacuum industrial control.

[0043] Furthermore, the high and low temperature test subsystem switches between a first operating mode and a second operating mode based on the temperature distribution gradient between the rotating component under test and the magnetic levitation bearing, wherein:

[0044] In the first operating mode, the first temperature control component operates to cool the vacuum chamber 5; in the second operating mode, the second temperature control component operates to heat the vacuum chamber 5. This embodiment can obtain the temperature distribution gradient of the rotating component and the magnetic levitation bearing under test through thermal structural finite element analysis, thereby providing a theoretical basis for subsequent precise temperature control based on the obtained temperature distribution gradient.

[0045] Preferably, the first temperature control component in this embodiment includes a heat sink module 10 and a liquid nitrogen module. The liquid nitrogen module is connected to the heat exchange pipeline of the heat sink module 10 to deliver liquid nitrogen to the heat exchange pipeline for heat exchange and cooling. Specifically, the output end of the liquid nitrogen module is connected to the liquid nitrogen module through a liquid nitrogen valve 17, and the "cold" background environment inside the vacuum chamber 5 is controlled by filling the heat sink module 10 with liquid nitrogen.

[0046] Preferably, the second temperature control component in this embodiment is a thermal radiation lamp array, such as an infrared lamp array; that is, the high-temperature section of the magnetic levitation bearing 12 and the rotating component under test in the vacuum chamber 5 is controlled by turning on the thermal radiation lamp array. A cooling screen 13 is also provided in the vacuum chamber 5 to reduce the impact of the thermal radiation of the rotating component under test on the temperature of the adjacent magnetic levitation bearing 12, so as to improve the stable levitation capability of the magnetic levitation bearing.

[0047] The high vacuum acquisition subsystem consists of a fore-stage mechanical pump 7 and a molecular pump 6. The fore-stage mechanical pump 7 and molecular pump 6 are specifically selected based on the vacuum requirements within the vacuum chamber 5, providing pumping equipment to achieve the required vacuum level within the vacuum chamber. Simultaneously, the dynamic sealing structure of the vacuum chamber 5 is incorporated to achieve and maintain the vacuum level within the chamber under rotor rotation conditions. To meet the requirements for high pressure differential and long-life dynamic sealing performance, the dynamic sealing structure of the vacuum chamber 5 in this embodiment preferably adopts a magnetohydrodynamic sealing device 4. Through optimization of its structural parameters, the long-life requirement of the dynamic seal is met, thus maintaining the vacuum level within the vacuum chamber 5 under rotor rotation conditions.

[0048] In this embodiment, the vacuum level of the vacuum chamber 5 is measured by resistance gauge 15 and ionization gauge 16, and the operation of the forestage mechanical pump 7 and molecular pump 6 is controlled based on the real-time measured vacuum level.

[0049] See Figures 2-3 In an optional embodiment, the rotating component under test is a planar gear train. This example uses a planar gear train as a typical rotating component. The magnetic levitation bearing 12 is located in the middle region of the gear shaft of the planar gear train. The planar gear train includes at least one gear 22 to be tested. Using a gear train structure allows the two ends of the shaft of the gear 22 to be free, avoiding the influence of rigid or flexible rotor connections on the whirling or radial runout during rotor rotation, which is beneficial for achieving stable levitation of the gear rotor by the magnetic levitation bearing. The gear pairs 8 on both sides of the gear 22 to be tested in the figure can adopt a "horizontal layout," or they can adopt a layout similar to... Figure 3 The "top-bottom layout" shown has the advantage that the center distance of the gear pair 8 can be adjusted more easily. When the magnetic levitation bearing 12 is arranged in the gear rotor structure, it should be ensured as much as possible that the magnetic levitation bearing 12 is located in the middle area of ​​the gear shaft 8 to avoid the influence of the off-center load effect on the stable levitation performance of the magnetic levitation bearing 12 during gear meshing.

[0050] This embodiment achieves stable levitation of the gear pair test piece in the gear train by using the magnetic levitation bearing 12, which can solve the technical problem of controllable gravity simulation of dynamic meshing gears under thermal vacuum conditions and improve the effectiveness of space environment simulation test of the new generation of high-parameter space mechanism.

[0051] The magnetic levitation bearing 12 is also equipped with a displacement sensor 21 for real-time acquisition of the gap between the rotor and the magnetic poles of the magnetic levitation bearing 12, and the current of the magnetic pole coil of the magnetic levitation bearing 12 is adjusted based on the data acquired by the displacement sensor 21. Specifically, the displacement sensor 21 within the structure of the magnetic levitation bearing 12 can acquire the gap between the rotor and the magnetic poles of the magnetic levitation bearing 12 in real time, and the magnetic force of the magnetic poles of the magnetic levitation bearing 12 can be controlled by controlling the current in the magnetic pole coil of the magnetic levitation bearing 12. This allows for control of the eddy current during the rotation of the gear rotor, as well as the influence of the radial force, normal force, and axial force generated during the meshing of the gear pair 8 on the rotor's motion trajectory, ensuring that the gear rotor is stably suspended in the central position region of the magnetic levitation bearing 12.

[0052] In this embodiment, the planar gear train is supported by mechanical bearing 23.

[0053] Furthermore, the microgravity simulation subsystem also includes a protective bearing 14, the clearance of which is smaller than the gap between the magnetic poles of the magnetic levitation bearing 12 and the rotor. By setting the clearance of the protective bearing 14 to be smaller than the gap between the magnetic poles of the magnetic levitation bearing 12 and the rotor, the safety of the magnetic levitation bearing is protected during start-up, shutdown, and variable load phases of the magnetic levitation system. Simultaneously, considering the significant heat generated by the magnetic levitation bearing 12 due to the current flow, this embodiment also includes a cold plate 9 for heat conduction with the magnetic pole coil of the magnetic levitation bearing. Specifically, the cold plate 9 is connected to the metal support for the magnetohydrodynamic seal, dissipating the heat generated on the magnetohydrodynamic magnetic pole coil due to the current flow through heat conduction, thereby achieving precise thermal control of the magnetohydrodynamic seal device 4.

[0054] This embodiment includes a first coupling and a second coupling, both of which are rigid couplings 2. The drive motor 1 is connected to the magnetohydrodynamic sealing device 4 on the vacuum chamber 5 through the first coupling. The magnetic powder brake 20 is connected to the rotor of the drive motor 1 that passes through the vacuum chamber through the magnetohydrodynamic sealing device 4 through the second coupling. In other words, this embodiment achieves structural penetration through the vacuum chamber 5 by setting the magnetohydrodynamic sealing device 4 on the vacuum chamber 5. The output end of the drive motor 1 is connected to the magnetohydrodynamic sealing device 4 through the first coupling, and the gear rotor used to drive the planar gear train exits through the magnetohydrodynamic sealing device 4 on the other side. The rotor driven by the drive motor 1 passes through the vacuum chamber through the magnetohydrodynamic sealing device 4. Correspondingly, the other section of the rotor exits through the vacuum chamber from the other side through the magnetohydrodynamic sealing device and is connected to the magnetic powder brake 20 through the second coupling. The shaft system of the entire system should be strictly aligned during installation to avoid instability of the test system due to poor installation accuracy, thereby improving the stability of the test system.

[0055] The magnetic powder brake 20 is mounted on the precision lifting platform 19, and is also equipped with a photoelectric encoder 18 for measuring the angle.

[0056] Furthermore, a first torque sensor 3 is installed on the output end of the drive motor 1, and a second torque sensor 3 is installed on the input end of the magnetic powder brake 20. The torque sensor 3 installed on the output end of the drive motor 1 is used to test the torque generated when the drive motor 1 is working; the torque sensor 3 installed on the input end of the magnetic powder brake 20 is used to test the torque at the load end of the system; and the gear train transmission efficiency can be calculated by using the values ​​measured by the torque sensors at the input and output ends.

[0057] Optionally, the measurement unit is a high-speed camera 24, which is used to monitor the dynamic information of the rotating component under test. The dynamic parameter measurement subsystem also includes a light source 25 for illuminating the target position of the rotating component under test. That is, the dynamic parameter measurement subsystem consists of the light source 25 and the high-speed camera 24. During operation, the light source 25 first illuminates the side of the gear pair 22 under test, and then the high-speed camera 24 records the gear meshing process. Real-time monitoring is conducted on the strain of the gear teeth during meshing under the combined effects of high and low temperature alternation, vacuum, microgravity, and dynamic torque. The stress changes during gear meshing are then calculated from the strain. This embodiment uses high-speed photography technology to monitor the stress-strain of the gear teeth during meshing under the combined effects of complex spatial environments in real time, developing a non-contact method for calculating and reconstructing the strain field, stress field, and displacement field of the rotating gear disk surface under high-speed rotation conditions.

[0058] The comprehensive environmental simulation test system for rotating components provided in this embodiment includes a high and low temperature test subsystem, a high vacuum acquisition subsystem, a microgravity simulation subsystem, a dynamic torque test subsystem, and a dynamic parameter measurement subsystem. Specifically, the high and low temperature test subsystem studies the temperature field distribution within the vacuum chamber, designs the lamp array and heat sink structure and layout, and achieves precise temperature control within the vacuum chamber to simulate the high and low temperature environment of space. The high vacuum acquisition subsystem studies vacuum system configuration, flow guide design, material gas venting, and magnetohydrodynamic sealing technology to obtain a high vacuum environment in space. The microgravity simulation subsystem studies the use of magnetic levitation bearings in suspended gear trains to achieve microgravity simulation under the meshing state of space gears. The dynamic torque test subsystem studies the relationship between excitation current and the torque, braking capacity, and response time of the magnetic powder brake to achieve dynamic torque follow-up control of the gear system. The dynamic parameter measurement subsystem monitors the stress-strain state of the gear teeth during gear meshing under the influence of complex space environmental effects in real time.

[0059] Figures 4-5 The present invention illustrates a test method for a comprehensive environmental simulation test system based on the above-described rotating component, comprising the following steps:

[0060] S101: Adjust the vacuum level and test temperature of the vacuum chamber through the high vacuum acquisition subsystem and the high and low temperature test subsystem, respectively.

[0061] S102: Activate the microgravity simulation subsystem to suspend the rotating component under test at the center of the magnetic levitation bearing.

[0062] S103: During the operation of the microgravity simulation subsystem, the drive motor and magnetic powder brake of the dynamic torque test subsystem are activated to drive the rotating component under test.

[0063] S104: The dynamic parameters of the rotating component under test are obtained through at least one measurement unit of the dynamic parameter measurement subsystem.

[0064] In practice, when using the test system of this embodiment to conduct high and low temperature-vacuum-microgravity-dynamic torque simulation tests on rotating components, the following steps are followed:

[0065] (1) Operating procedures for high vacuum generation system

[0066] The magnetohydrodynamic sealing device 4 was installed on the outside of the vacuum chamber 5 using a transition flange, and the leakage performance of the magnetohydrodynamic sealing device 4 was tested at different rotational speeds of the rotor passing through the chamber using the helium injection method.

[0067] After the performance of the magnetohydrodynamic sealing device 4 is debugged, turn on the front mechanical pump 7 of the test system to pump the pressure in the vacuum chamber 5 to 10 Pa or below, and then turn on the molecular pump 6 to pump the vacuum degree in the vacuum chamber 5 to the required vacuum degree.

[0068] By performing the above steps in sequence, the high vacuum level required for the vacuum chamber 5 test can be obtained.

[0069] (2) Operating procedures for high and low temperature test system

[0070] In the low-temperature section, the heat sink 10 is used to control the temperature of the gear pair 22 under test through thermal radiation. At the same time, the temperature of the magnetic levitation bearing 12 is monitored. When the heat generated after its own coil is energized cannot balance the low-temperature radiation of the heat sink 10, causing it to be at a low temperature that it cannot withstand, the thermal radiation lamp array 11 is turned on to control the temperature of the magnetic levitation bearing 12. A cold screen 13 is set in the area of ​​the magnetic levitation bearing 12 near the middle of the gear pair 22 under test, which can be used to shield the influence of the thermal radiation lamp array 11 on the temperature of the gear pair 22 under test.

[0071] At room temperature, close the liquid nitrogen valve 17 of the heat sink 10 and the thermal radiation lamp array 11, allowing the gear-magnetic levitation device to naturally return to room temperature and stabilize for a period of time.

[0072] In the high-temperature section, the thermal radiation lamp array 11 is used only to heat and control the gear pair 22 under test to the target temperature. A cold shield 13 in the low-temperature section is used to block the thermal radiation from the thermal radiation lamp array 11 heating the gear pair 22 under test from affecting the adjacent magnetic levitation bearing 12. During this period, the liquid nitrogen inlet valve of the heat sink 10 needs to be opened simultaneously to provide a "cold" background environment. The temperature of the magnetic levitation bearing 12 is controlled by the thermal radiation from the heat sink 10, preventing the coil of the magnetic levitation bearing 12 from overheating and the impact of the thermal radiation from the gear pair 22 under test on the magnetic pole performance of the magnetic levitation bearing 12.

[0073] The above steps are repeated cyclically to control the high and low temperatures of the gear-magnetic levitation bearing system inside the vacuum chamber and achieve precise temperature control.

[0074] (3) Operating procedures for dynamic torque test system and microgravity simulation test system

[0075] The operation processes of the dynamic torque test subsystem and the microgravity simulation subsystem overlap. The specific operation steps are as follows:

[0076] Once the vacuum level and temperature inside the vacuum chamber 5 reach the required level, the magnetic levitation bearing 12 is activated. The rotor of the gear pair 22 to be tested in the gear train is first suspended to the center position of the magnetic levitation bearing 12 as the initial state.

[0077] Start the drive motor 1 and set the speed to the required speed; then start the magnetic powder brake 20 and set it to the required torque.

[0078] By controlling the magnitude of the coil current of the magnetic levitation bearing 12, the magnetic force of the magnetic poles of the magnetic levitation bearing 12 is adjusted, thereby achieving stable levitation of the gear rotor system.

[0079] A displacement sensor 21 is used to monitor the rotor's motion trajectory in real time during gear meshing, and compares it with the rotor's displacement in the magnetic levitation bearing 12 in the initial state. If the monitored rotor motion trajectory deviates, the process returns to the previous step. After adjusting the current value in the magnetic levitation bearing coil according to the rotor motion trajectory, the current step is started sequentially. This process is repeated iteratively until the rotor motion trajectory coincides with the initial state, indicating that stable levitation of the typical rotating component, the gear pair, has been achieved in a thermal vacuum environment.

[0080] By sequentially performing steps (1) to (3), the microgravity simulation of a typical rotating component, the gear pair, can be achieved under the combined environment of high and low temperatures, vacuum, and dynamic torque.

[0081] In summary, the high and low temperature-vacuum-microgravity-dynamic torque simulation test system for rotating components provided by this invention achieves stable levitation of the gear pair test piece in the gear train through magnetic levitation bearings. It can solve the technical problem of controllable gravity simulation of dynamically meshing gears under thermal vacuum conditions, and improve the effectiveness of space environment simulation tests for next-generation high-parameter space mechanisms. At the same time, it uses high-speed photography technology to monitor the stress-strain of the gear teeth during gear meshing under the combined effects of complex space environment in real time, and develops a non-contact method for calculating and reconstructing the strain field, stress field and displacement field of the rotating gear disk surface under high-speed rotation conditions.

[0082] Of course, the present invention may have other various embodiments. Without departing from the spirit and essence of the present invention, those skilled in the art can make various corresponding changes and modifications according to the present invention, but these corresponding changes and modifications should all fall within the protection scope of the appended claims.

Claims

1. A comprehensive environmental simulation test system for rotating components, characterized in that, Including: Vacuum chamber; The high and low temperature test subsystem is placed inside the vacuum chamber and is equipped with a first temperature control component and a second temperature control component. The first temperature control component is used to cool down the vacuum chamber, and the second temperature control component is used to heat up the vacuum chamber. A high vacuum acquisition subsystem is connected to the vacuum chamber for adjusting the vacuum level of the vacuum chamber; A microgravity simulation subsystem is placed inside the vacuum chamber and is equipped with a magnetic levitation bearing. The magnetic levitation bearing is connected to the rotating component under test to simulate a microgravity environment for the rotating component under test through magnetic levitation. The dynamic torque test subsystem includes a drive motor, a magnetic powder brake, and at least one coupling. The drive motor and the magnetic powder brake are connected to the rotating component under test inside the vacuum chamber through the coupling and at least one magnetohydrodynamic sealing device. A dynamic parameter measurement subsystem is placed inside the vacuum chamber and is equipped with at least one measurement unit. The measurement unit is used to acquire the dynamic parameters of the rotating component under test. The rotating component under test is a planar gear train. The magnetic levitation bearing is located in the middle region of the gear shaft of the planar gear train. The magnetic levitation bearing is also equipped with a displacement sensor for real-time acquisition of the gap between the rotor and the magnetic pole of the magnetic levitation bearing. The magnetic pole coil current of the magnetic levitation bearing is adjusted based on the data acquired by the displacement sensor.

2. The comprehensive environmental simulation test system for rotating components according to claim 1, characterized in that, The high and low temperature test subsystem switches between a first operating mode and a second operating mode based on the temperature distribution gradient of the rotating component under test and the magnetic levitation bearing, wherein: In the first operating mode, the first temperature control component operates to cool the vacuum chamber; In the second operating mode, the second temperature control component operates to heat the vacuum chamber.

3. The comprehensive environmental simulation test system for rotating components according to claim 1 or 2, characterized in that, The first temperature control component includes a heat sink module and a liquid nitrogen module. The liquid nitrogen module is connected to the heat exchange pipeline of the heat sink module to deliver liquid nitrogen to the heat exchange pipeline for heat exchange and cooling; and / or The second temperature control component is a thermal radiation lamp array.

4. The comprehensive environmental simulation test system for rotating components according to claim 1, characterized in that, The high vacuum acquisition subsystem consists of a backing mechanical pump and a molecular pump.

5. The comprehensive environmental simulation test system for rotating components according to claim 1, characterized in that, The microgravity simulation subsystem also includes a protective bearing, and the clearance of the protective bearing is smaller than the gap between the magnetic poles of the magnetic levitation bearing and the rotor; and / or It also includes a cold plate for heat conduction with the magnetic pole coil of the magnetic levitation bearing.

6. The comprehensive environmental simulation test system for rotating components according to claim 1, characterized in that, The drive motor is connected to the magnetohydrodynamic sealing device on the vacuum chamber via a first coupling, and the magnetic powder brake is connected to the rotor of the drive motor via a second coupling, which passes through the vacuum chamber via the magnetohydrodynamic sealing device.

7. The comprehensive environmental simulation test system for rotating components according to claim 6, characterized in that, A first torque sensor is installed on the output end of the drive motor, and a second torque sensor is installed on the input end of the magnetic powder brake.

8. The comprehensive environmental simulation test system for rotating components according to claim 1, characterized in that, The measurement unit is a high-speed camera, which is used to monitor the dynamic information of the rotating component under test; and / or The dynamic parameter measurement subsystem also includes a light source for illuminating the target position of the rotating component under test.

9. A test method for a comprehensive environmental simulation test system based on the rotating component according to any one of claims 1 to 8, characterized in that, Including the following steps: The vacuum level and test temperature of the vacuum chamber are adjusted by the high vacuum acquisition subsystem and the high and low temperature test subsystem, respectively. The microgravity simulation subsystem is activated to suspend the rotating component under test at the center of the magnetic levitation bearing. During the operation of the microgravity simulation subsystem, the drive motor and the magnetic powder brake of the dynamic torque test subsystem are activated to drive the rotating component under test; The dynamic parameters of the rotating component under test are obtained by at least one of the measurement units of the dynamic parameter measurement subsystem.

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