Spacecraft ground air damping characteristic evaluation test system and method

Abstract

The application provides a spacecraft ground air damping characteristic evaluation test system and method, comprising: a vacuum subsystem, a micro-vibration measurement subsystem and a micro-vibration excitation subsystem; the vacuum subsystem is used for providing a vacuum environment for a spacecraft to be tested; the micro-vibration measurement subsystem is used for measuring micro-vibration response and noise data at a target position of the spacecraft to be tested; and the micro-vibration excitation subsystem is used for performing transfer function and frequency response test on a disturbance source single machine in an entire cabin state of the spacecraft to be tested, and obtaining micro-vibration transmission characteristics of the spacecraft to be tested; through the vacuum subsystem, the micro-vibration measurement subsystem and the micro-vibration excitation subsystem, the spacecraft ground air damping characteristic test can be efficiently and accurately realized, and the test efficiency and accuracy are improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of spacecraft air damping characteristic test, and particularly relates to a spacecraft ground air damping characteristic evaluation test system and method. BACKGROUND

[0002] With the spacecraft structure becoming increasingly large and complex, the space mission becoming increasingly precise, and the large flexibility and light weight becoming the development features of the spacecraft structure, especially for the load equipment with extremely high directivity requirement, such as a space optical camera, the requirement for the working environment is very high, and the micro-vibration environment can cause the camera optical axis shaking, the camera body torsion, the rigid displacement and deformation of the optical element, and the influence on the camera imaging quality cannot be ignored. The spacecraft damping characteristic is one of the key factors affecting the optical axis shaking, however, the complex structure, the low-frequency mode density, and the strong coupling between the systems and the environment make the spacecraft damping characteristic complex, and the damping coefficient obtained through the conventional ground micro-vibration test is composed of the cabin damping and the air damping, but the influence of the air on the cabin damping characteristic based on the micro-vibration measurement data correction cannot be obtained.

[0003] Therefore, how to evaluate and test the spacecraft ground air damping characteristic becomes a technical problem to be solved by the person skilled in the art. SUMMARY

[0004] The present application provides a spacecraft ground air damping characteristic evaluation test system and method, which solves the defects of low efficiency and poor accuracy of the spacecraft ground air damping characteristic evaluation test in the prior art.

[0005] In a first aspect, the present application provides a spacecraft ground air damping characteristic evaluation test system, comprising: a vacuum subsystem, a micro-vibration measurement subsystem and a micro-vibration excitation subsystem.

[0006] The vacuum subsystem is used to provide a vacuum environment for a spacecraft to be tested.

[0007] The micro-vibration measurement subsystem is used to measure the micro-vibration response and noise data at a target position of the spacecraft to be tested.

[0008] The micro-vibration excitation subsystem is used to test the transfer function and frequency response of the spacecraft to be tested in the whole-cabin state of the disturbance source single machine, and obtain the micro-vibration transfer characteristic of the spacecraft to be tested.

[0009] According to the spacecraft ground air damping characteristic evaluation test system provided by the present application, the vacuum subsystem comprises: a rough pumping unit, a high vacuum module, a molecular pump module, a pressure recovery module, and a vacuum measurement and residual gas analysis module.

[0010] The roughing pump group is used for pumping the high vacuum module to a vacuum environment.

[0011] The molecular pump module, the booster module and the vacuum measurement and residual gas analysis module are used for analyzing the high vacuum module.

[0012] According to the application, a spacecraft ground air damping characteristic evaluation test system is provided, and the micro-vibration measurement subsystem comprises a data acquisition module, a micro-vibration sensor and an acoustic sensor.

[0013] The micro-vibration sensor and the acoustic sensor are used for collecting micro-vibration response and noise data of the spacecraft to be tested.

[0014] The data acquisition system is used for receiving and processing the micro-vibration response and noise data.

[0015] According to the application, a spacecraft ground air damping characteristic evaluation test system is provided, and the micro-vibration excitation subsystem comprises a line excitation module and a power amplifier.

[0016] The power amplifier is used for adjusting test data of the spacecraft to be tested by the excitation module, obtaining micro-vibration transfer characteristics and sending the data to the data acquisition system.

[0017] According to the application, a spacecraft ground air damping characteristic evaluation test system is provided, and the micro-vibration excitation subsystem comprises a line excitation module and a power amplifier.

[0018] The test support is used for placing the spacecraft to be tested.

[0019] In a second aspect, the application further provides a spacecraft ground air damping characteristic evaluation test method, which is applied to the spacecraft ground air damping characteristic evaluation test system as described in any one of the above aspects, and the method comprises the following steps.

[0020] The spacecraft to be tested is placed outside the vacuum subsystem, and the micro-vibration measurement subsystem and the micro-vibration excitation subsystem are used to test background noise, micro-vibration response and transfer characteristics of the spacecraft to be tested in a normal state to obtain test data in the normal state.

[0021] After the test in the normal state is completed, the spacecraft to be tested is placed inside the vacuum subsystem, and the micro-vibration measurement subsystem and the micro-vibration excitation subsystem are used to test background noise, micro-vibration response and transfer characteristics of the spacecraft to be tested in a soundproof state to obtain test data in the soundproof state.

[0022] After the test in the soundproof state is completed, the spacecraft to be tested is placed inside the vacuum subsystem, and the inside of the vacuum subsystem is kept in a vacuum state, and the spacecraft to be tested is tested for background noise, micro-vibration response and transmission characteristics in a vacuum state by the micro-vibration measurement subsystem and the micro-vibration excitation subsystem, to obtain test data in a vacuum state;

[0023] The test data in the normal state, the test data in the soundproof state and the test data in the vacuum state are processed to determine the air damping characteristics of the spacecraft to be tested.

[0024] According to the spacecraft ground air damping characteristic evaluation test method provided by the application, the spacecraft to be tested is placed outside the vacuum subsystem, and the spacecraft to be tested is tested for background noise, micro-vibration response and transmission characteristics in a normal state by the micro-vibration measurement subsystem and the micro-vibration excitation subsystem, to obtain test data in a normal state, which comprises:

[0025] The test support is placed outside the vacuum subsystem;

[0026] The spacecraft to be tested is connected with the test support to establish a boundary state;

[0027] The micro-vibration measurement sensor is pasted and connected with the data acquisition system, and the micro-vibration measurement subsystem parameter setting and on-off test are carried out;

[0028] The background noise, micro-vibration response and transmission characteristic test working condition is carried out;

[0029] After the test working condition is implemented, the test data in the normal state is obtained.

[0030] According to the spacecraft ground air damping characteristic evaluation test method provided by the application, the spacecraft to be tested is placed inside the vacuum subsystem, and the spacecraft to be tested is tested for background noise, micro-vibration response and transmission characteristics in a soundproof state by the micro-vibration measurement subsystem and the micro-vibration excitation subsystem, to obtain test data in a soundproof state, which comprises:

[0031] The test support is placed inside the vacuum subsystem;

[0032] The spacecraft to be tested is connected with the test support, and the connection state is consistent with the normal state;

[0033] The cable connected with the micro-vibration measurement subsystem is connected, and the micro-vibration measurement subsystem parameter setting and on-off test are carried out;

[0034] Close the channel of the vacuum subsystem, keep the vacuum subsystem inside normal pressure state, keep the whole device in shutdown silence state, eliminate the vibration interference of external device on the test;

[0035] Develop background noise, micro-vibration response and transmission characteristic test working condition implementation;

[0036] After the test working condition implementation, open the channel of the vacuum subsystem, and obtain the test data under the sound insulation state.

[0037] According to the spacecraft ground air damping characteristic evaluation test method provided by the application, the spacecraft to be tested is placed in the vacuum subsystem, and the vacuum subsystem inside is kept in a vacuum state, the background noise, micro-vibration response and transmission characteristic test of the spacecraft to be tested in the vacuum state are carried out through the micro-vibration measurement subsystem and the micro-vibration excitation subsystem, and the test data in the vacuum state are obtained, comprising:

[0038] The test support is placed in the vacuum subsystem;

[0039] The spacecraft to be tested is connected with the test support, and the connection state is consistent with the normal state and the sound insulation state;

[0040] The cable of the micro-vibration measurement subsystem is connected, and the micro-vibration measurement subsystem parameter setting and turn-on test are carried out;

[0041] The channel of the vacuum subsystem is closed, and vacuum is extracted, the unit device is closed, the whole device is kept in shutdown silence state, and the vibration interference of external device on the test is eliminated;

[0042] Develop background noise, micro-vibration response and transmission characteristic test working condition implementation;

[0043] After the test working condition implementation, the system is re-pressurized, air is filled, and the test data in the vacuum state are obtained.

[0044] According to the spacecraft ground air damping characteristic evaluation test method provided by the application, before the channel of the vacuum subsystem is closed and vacuum is extracted, the method further comprises:

[0045] The test equipment in the micro-vibration measurement subsystem and the micro-vibration excitation subsystem is temperature monitored.

[0046] In a third aspect, the application further provides an electronic device, comprising a memory, a processor and a computer program stored in the memory and executable on the processor, and the processor executes the program to realize the spacecraft ground air damping characteristic evaluation test method as described above.

[0047] In a fourth aspect, the present application also provides a non-transitory computer-readable storage medium having stored thereon a computer program, which, when executed by a processor, implements the spacecraft ground air damping characteristic evaluation test method according to any one of the above.

[0048] In a fifth aspect, the present application also provides a computer program product comprising a computer program, which, when executed by a processor, implements the spacecraft ground air damping characteristic evaluation test method according to any one of the above.

[0049] The spacecraft ground air damping characteristic evaluation test system provided by the present application comprises a vacuum subsystem, a micro-vibration measurement subsystem and a micro-vibration excitation subsystem; the vacuum subsystem is used to provide a vacuum environment for a spacecraft to be tested; the micro-vibration measurement subsystem is used to measure micro-vibration response and noise data at a target position of the spacecraft to be tested; and the micro-vibration excitation subsystem is used to test the transfer function and frequency response of a disturbance source single machine in an overall cabin state of the spacecraft to be tested, so as to obtain the micro-vibration transfer characteristic of the spacecraft to be tested. Through the vacuum subsystem, the micro-vibration measurement subsystem and the micro-vibration excitation subsystem, the spacecraft ground air damping characteristic can be efficiently and accurately tested, and the test efficiency and accuracy are improved.

[0050] The spacecraft ground air damping characteristic evaluation test method of the present application has the characteristics of the above system, and thus can achieve the same effect. BRIEF DESCRIPTION OF DRAWINGS

[0051] In order to more clearly illustrate the technical solutions in the present application or prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description are some embodiments of the present application, and for those skilled in the art, other drawings can also be obtained without creative labor.

[0052] Figure 1 is a structural schematic diagram of the spacecraft ground air damping characteristic evaluation test system provided by the present embodiment;

[0053] Figure 2 is a flowchart of the spacecraft ground air damping characteristic evaluation test method provided by the present embodiment;

[0054] Figure 3 is a structural schematic diagram of the electronic device provided by the present embodiment. DETAILED DESCRIPTION

[0055] In order to make the objects, technical solutions and advantages of the present application clearer, the technical solutions in the present application will be described clearly and completely below in conjunction with the drawings in the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the protection scope of the present application.

[0056] Figure 1 FIG. 1 is a structural schematic diagram of a spacecraft ground air damping characteristic evaluation test system provided by the present embodiment.

[0057] As shown in Figure 1 FIG. 1, the spacecraft ground air damping characteristic evaluation test system provided by the present embodiment comprises a vacuum subsystem, a micro-vibration measurement subsystem and a micro-vibration excitation subsystem. The vacuum subsystem is used to provide a vacuum environment for a spacecraft to be tested. The micro-vibration measurement subsystem is used to measure micro-vibration response and noise data at a target position of the spacecraft to be tested. The micro-vibration excitation subsystem is used to test the transfer function and frequency response of a disturbance source single machine in the whole cabin state of the spacecraft to be tested, and to obtain the micro-vibration transfer characteristic of the spacecraft to be tested.

[0058] In a specific implementation process, the spacecraft to be tested is defined as a spacecraft to be tested. The mutual cooperation of the vacuum subsystem, the micro-vibration measurement subsystem and the micro-vibration excitation subsystem can realize the testing of the spacecraft to be tested in three different states, so as to test and analyze the air damping characteristics of the spacecraft based on the test results in the three different states. The three different states include a normal state in which the spacecraft to be tested is irrelevant to the vacuum subsystem, i.e. the spacecraft to be tested is outside the vacuum subsystem; an acoustic insulation state in which the spacecraft to be tested is inside the vacuum subsystem but not in a vacuum condition; and a vacuum state in which the spacecraft to be tested is inside the vacuum subsystem and the inside is pumped to a vacuum. The micro-vibration response and transfer characteristic in the three different states can better realize the testing of the ground air damping characteristics of the spacecraft. When the spacecraft to be tested is tested, it is placed at a test position by a test support.

[0059] The vacuum subsystem comprises a rough pumping unit, a high-vacuum module, a molecular pump module, a re-compression module and a vacuum measurement and residual gas analysis module. The rough pumping unit is used to pump the high-vacuum module to a vacuum environment, and can pump a container from normal pressure to 1 Pa or less within 4-6 h, so as to provide a vacuum environment for the spacecraft to be tested. The molecular pump module, the re-compression module and the vacuum measurement and residual gas analysis module are used to analyze the high-vacuum module.

[0060] The micro-vibration measurement subsystem includes: a data acquisition module, a micro-vibration sensor, and an acoustic sensor; the micro-vibration sensor and the acoustic sensor are used to acquire micro-vibration response and noise data of the spacecraft under test; the data acquisition system is used to receive and process the micro-vibration response and noise data.

[0061] The micro-vibration excitation subsystem includes a line excitation module and a power amplifier; the power amplifier is used to adjust the test data of the spacecraft under test in the excitation module, acquire the micro-vibration transmission characteristics and send them to the data acquisition system.

[0062] The vacuum subsystem is primarily used for testing the spacecraft under both isolated and vacuum conditions. When the subsystem is filled with gas, simple sound insulation tests are performed, as it isolates the spacecraft from external noise interference. When the gas inside the subsystem is evacuated to a vacuum, vacuum tests are conducted to simulate the micro-vibrations of the spacecraft in a vacuum environment. The relevant parameters of the internal equipment in both the micro-vibration excitation subsystem and the micro-vibration measurement subsystem are kept consistent across all test conditions to ensure the accuracy and reliability of the final test results.

[0063] Based on the same general inventive concept, this invention also protects a test method for evaluating the ground air damping characteristics of a spacecraft.

[0064] Figure 2 This is a flowchart illustrating the spacecraft ground air damping characteristic evaluation test method provided in this embodiment.

[0065] like Figure 2 As shown, the spacecraft ground air damping characteristic evaluation and testing method provided in this embodiment can be executed by any of the spacecraft ground air damping characteristic evaluation and testing systems described above. The method mainly includes the following steps:

[0066] 201. Place the spacecraft under test outside the vacuum subsystem, and use the micro-vibration measurement subsystem and micro-vibration excitation subsystem to test the background noise, micro-vibration response and transmission characteristics of the spacecraft under normal conditions to obtain test data under normal conditions.

[0067] In a specific implementation process, the spacecraft under test was tested for background noise, micro-vibration response, and transmission characteristics under three different conditions. The first test was conducted under normal conditions, and the specific procedure is as follows:

[0068] The test support is placed outside the vacuum subsystem; the spacecraft to be tested is connected with the test support to establish the boundary state; the surrounding ground equipment is in the shutdown state to ensure that the environment is in the optimal state; the micro-vibration measuring sensor is pasted and connected with the data acquisition system, the micro-vibration measuring system parameter setting and the on-off test are carried out; the background noise, micro-vibration response and transmission characteristic test working condition implementation is carried out; after the test working condition implementation is completed, the test data in the normal state is obtained.

[0069] 202、After the test in the normal state is completed, the spacecraft to be tested is placed inside the vacuum subsystem, the background noise, micro-vibration response and transmission characteristic test in the soundproof state is carried out on the spacecraft to be tested through the micro-vibration measuring system and the micro-vibration excitation system, and the test data in the soundproof state is obtained.

[0070] After the test data in the normal state is obtained, the test support is placed inside the vacuum subsystem; the spacecraft to be tested is connected with the test support, the connection and the boundary state are consistent with those in the normal state; the cable of the micro-vibration measuring system is connected, the micro-vibration measuring system parameter setting and the on-off test are carried out; the channel of the vacuum subsystem is closed, the normal pressure state in the vacuum subsystem is maintained, the overall equipment is in the shutdown silent state, the vibration interference of external equipment on the test is eliminated, the vacuum subsystem plays a certain soundproof role; the background noise, micro-vibration response and transmission characteristic test working condition implementation is carried out; after the test working condition implementation is completed, the channel of the vacuum subsystem is opened, and the test data in the soundproof state is obtained.

[0071] 203、After the test in the soundproof state is completed, the spacecraft to be tested is placed inside the vacuum subsystem, and the vacuum state in the vacuum subsystem is maintained, the background noise, micro-vibration response and transmission characteristic test in the vacuum state is carried out on the spacecraft to be tested through the micro-vibration measuring system and the micro-vibration excitation system, and the test data in the vacuum state is obtained.

[0072] After the test data in the soundproof state is obtained, the test support is placed inside the vacuum subsystem; the spacecraft to be tested is connected with the test support, the connection and the boundary state are consistent with those in the normal state and the soundproof state; the cable of the micro-vibration measuring system is connected, the micro-vibration measuring system parameter setting and the on-off test are carried out; the temperature of the test equipment in the micro-vibration measuring system and the micro-vibration excitation system is monitored; the channel of the vacuum subsystem is closed, and the system is vacuumized to a vacuum degree below 1 Pa, the unit equipment is closed, the overall equipment is in the shutdown silent state, and the vibration interference of external equipment on the test is eliminated; the background noise, micro-vibration response and transmission characteristic test working condition implementation is carried out; after the test working condition implementation is completed, the system is re-pressurized, and air is filled, and the test data in the vacuum state is obtained.

[0073] 204、Processing the test data in the normal state, the test data in the sound insulation state and the test data in the vacuum state to determine the air damping characteristics of the spacecraft to be tested.

[0074] Finally, the data in the three test states are compared and analyzed as a whole to evaluate the air damping characteristics of the spacecraft and obtain the influence of the atmospheric environment on the damping characteristics of the spacecraft.

[0075] Figure 3 is a structural schematic diagram of an electronic device provided by the embodiment.

[0076] As shown in Figure 3 , the electronic device can include a processor 310, a communications interface 320, a memory 330 and a communications bus 340, wherein the processor 310, the communications interface 320 and the memory 330 complete mutual communication through the communications bus 340. The processor 310 can invoke a logical instruction in the memory 330 to execute a spacecraft ground air damping characteristic evaluation test method, which includes: placing a spacecraft to be tested outside a vacuum subsystem, testing the background noise, micro-vibration response and transmission characteristics of the spacecraft to be tested in a normal state through a micro-vibration measurement subsystem and a micro-vibration excitation subsystem to obtain test data in the normal state; after completing the test in the normal state, placing the spacecraft to be tested inside the vacuum subsystem, testing the background noise, micro-vibration response and transmission characteristics of the spacecraft to be tested in a sound insulation state through the micro-vibration measurement subsystem and the micro-vibration excitation subsystem to obtain test data in the sound insulation state; after completing the test in the sound insulation state, placing the spacecraft to be tested inside the vacuum subsystem and keeping the vacuum subsystem inside in a vacuum state, testing the background noise, micro-vibration response and transmission characteristics of the spacecraft to be tested in the vacuum state through the micro-vibration measurement subsystem and the micro-vibration excitation subsystem to obtain test data in the vacuum state; processing the test data in the normal state, the test data in the sound insulation state and the test data in the vacuum state to determine the air damping characteristics of the spacecraft to be tested.

[0077] In addition, the logic instructions in the memory 330 described above can be implemented in the form of a software function unit and sold or used as an independent product, which can be stored in a computer readable storage medium. Based on such understanding, the technical solutions of the present application essentially or the part that contributes to the prior art or part of the technical solutions can be embodied in the form of a software product, which is stored in a storage medium, including a plurality of instructions to make a computer device (which can be a personal computer, a server, or a network device, etc.) execute all or part of the steps of the method described in various embodiments of the present application. The foregoing storage medium includes: a U disk, a mobile hard disk, a read-only memory (ROM, Read-Only Memory), a random access memory (RAM, Random Access Memory), a magnetic disk or an optical disk, and various media that can store program codes.

[0078] In another aspect, the present application also provides a computer program product, which comprises a computer program, the computer program can be stored on a non-transitory computer readable storage medium, and the computer program can be executed by a processor to enable a computer to perform the spacecraft ground air damping characteristic evaluation test method provided by the above-mentioned method, which comprises: placing a spacecraft to be tested outside a vacuum subsystem, testing the background noise, micro-vibration response and transmission characteristics of the spacecraft to be tested in a normal state by a micro-vibration measurement subsystem and a micro-vibration excitation subsystem, and obtaining test data in the normal state; after completing the test in the normal state, placing the spacecraft to be tested inside the vacuum subsystem, testing the background noise, micro-vibration response and transmission characteristics of the spacecraft to be tested in a soundproof state by the micro-vibration measurement subsystem and the micro-vibration excitation subsystem, and obtaining test data in the soundproof state; after completing the test in the soundproof state, placing the spacecraft to be tested inside the vacuum subsystem and keeping the vacuum subsystem in a vacuum state, testing the background noise, micro-vibration response and transmission characteristics of the spacecraft to be tested in a vacuum state by the micro-vibration measurement subsystem and the micro-vibration excitation subsystem, and obtaining test data in the vacuum state; processing the test data in the normal state, the test data in the soundproof state and the test data in the vacuum state, and determining the air damping characteristics of the spacecraft to be tested.

[0079] In yet another aspect, the present application also provides a non-transitory computer readable storage medium having stored thereon a computer program, which, when executed by a processor, implements the spacecraft ground air damping characteristic evaluation test method provided by the above method, and the method comprises: placing a spacecraft to be tested outside a vacuum subsystem, performing background noise, micro-vibration response and transfer characteristic tests on the spacecraft to be tested in a normal state by a micro-vibration measurement subsystem and a micro-vibration excitation subsystem, to obtain test data in the normal state; after the test in the normal state is completed, placing the spacecraft to be tested inside the vacuum subsystem, performing background noise, micro-vibration response and transfer characteristic tests on the spacecraft to be tested in a soundproof state by the micro-vibration measurement subsystem and the micro-vibration excitation subsystem, to obtain test data in the soundproof state; after the test in the soundproof state is completed, placing the spacecraft to be tested inside the vacuum subsystem, keeping the vacuum subsystem in a vacuum state, and performing background noise, micro-vibration response and transfer characteristic tests on the spacecraft to be tested in a vacuum state by the micro-vibration measurement subsystem and the micro-vibration excitation subsystem, to obtain test data in the vacuum state; and processing the test data in the normal state, the test data in the soundproof state and the test data in the vacuum state, to determine the air damping characteristic of the spacecraft to be tested.

[0080] The device embodiments described above are merely illustrative, wherein the units described as separate components can or can not be physically separated, and the components displayed as units can or can not be physical units, i.e., can be located in one place or distributed on multiple network units. Part or all of the modules can be selected to achieve the purpose of the embodiment scheme according to actual needs. Those skilled in the art can understand and implement without creative labor.

[0081] From the above description of the embodiments, those skilled in the art can clearly understand that the embodiments can be realized by means of software plus necessary universal hardware platforms, and of course can also be realized by hardware. Based on such understanding, the above technical solutions, essentially or in terms of the contribution to the prior art, can be embodied in the form of a software product, which can be stored in a computer readable storage medium, such as a ROM / RAM, a magnetic disk, an optical disk, etc., and includes a plurality of instructions to make a computer device (which can be a personal computer, a server, or a network device, etc.) execute the methods described in the various embodiments or some parts of the embodiments.

[0082] It should be pointed out finally that the above embodiments are only used to illustrate the technical solutions of the present application, but not to limit the same; and although the present application has been described in detail with reference to the foregoing embodiments, it should be appreciated by those skilled in the art that the technical solutions recorded in the foregoing embodiments can be modified, or some technical features thereof can be replaced equivalently; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. A spacecraft ground air damping characteristic evaluation test system, characterized by, The application relates to a spacecraft ground air damping characteristic evaluation test system and a method thereof. The system comprises a vacuum subsystem, a micro-vibration measurement subsystem and a micro-vibration excitation subsystem. The vacuum subsystem is used for providing a vacuum environment for a spacecraft to be tested. The micro-vibration measurement subsystem is used for measuring micro-vibration response and noise data at a target position of the spacecraft to be tested. The micro-vibration excitation subsystem is used for performing a transfer function and frequency response test on a spacecraft to be tested in a whole-cabin state of a disturbance source, and obtaining micro-vibration transfer characteristics of the spacecraft to be tested. The vacuum subsystem comprises a rough pumping unit, a high-vacuum module, a molecular pump module, a pressure recovery module and a vacuum measurement and residual gas analysis module; the rough pumping unit is used for pumping the high-vacuum module to a vacuum environment; the molecular pump module, the pressure recovery module and the vacuum measurement and residual gas analysis module are used for analyzing the high-vacuum module. The micro-vibration measurement subsystem comprises a data acquisition module, a micro-vibration sensor and an acoustic sensor; the micro-vibration sensor and the acoustic sensor are used for acquiring micro-vibration response and noise data of the spacecraft to be tested; and the data acquisition module is used for receiving and processing the micro-vibration response and noise data. The micro-vibration excitation subsystem comprises a line excitation module and a power amplifier; the power amplifier is used for adjusting test data of the spacecraft to be tested by the excitation module, and sending the micro-vibration transfer characteristics to the data acquisition module.

2. The spacecraft ground air damping characteristics evaluation test system of claim 1, wherein, The application further comprises a test support. The test support is used for placing the spacecraft to be tested.

3. A spacecraft ground air damping characteristic evaluation test method characterized by, The application is applied to the spacecraft ground air damping characteristic evaluation test system and the method thereof. The spacecraft to be tested is placed outside the vacuum subsystem, and background noise, micro-vibration response and transfer characteristics of the spacecraft to be tested are tested in a normal state by the micro-vibration measurement subsystem and the micro-vibration excitation subsystem, so as to obtain test data in the normal state. After the test in the normal state is completed, the spacecraft to be tested is placed inside the vacuum subsystem, and background noise, micro-vibration response and transfer characteristics of the spacecraft to be tested are tested in a soundproof state by the micro-vibration measurement subsystem and the micro-vibration excitation subsystem, so as to obtain test data in the soundproof state. After the test in the soundproof state is completed, the spacecraft to be tested is placed inside the vacuum subsystem, and the inside of the vacuum subsystem is kept in a vacuum state, and background noise, micro-vibration response and transfer characteristics of the spacecraft to be tested are tested in a vacuum state by the micro-vibration measurement subsystem and the micro-vibration excitation subsystem, so as to obtain test data in the vacuum state. The test data in the normal state, the test data in the soundproof state and the test data in the vacuum state are processed, and air damping characteristics of the spacecraft to be tested are determined.

4. The spacecraft ground air damping characteristics evaluation test method according to claim 3, characterized by, The spacecraft to be tested is placed outside the vacuum subsystem, and background noise, micro-vibration response and transfer characteristics of the spacecraft to be tested are tested in a normal state by the micro-vibration measurement subsystem and the micro-vibration excitation subsystem, so as to obtain test data in the normal state, which comprises the following steps. The test support is placed outside the vacuum subsystem. The spacecraft to be tested is connected with the test support to establish a boundary state; The micro-vibration measuring sensor is pasted and connected with the data acquisition module, the micro-vibration measuring subsystem is set and turned on for testing; The background noise, micro-vibration response and transmission characteristic test working condition is implemented; After the test working condition is implemented, the test data in the normal state is obtained.

5. The spacecraft ground air damping characteristics evaluation test method according to claim 4, characterized by, The spacecraft to be tested is placed in the vacuum subsystem, the background noise, micro-vibration response and transmission characteristic test of the spacecraft to be tested in the soundproof state is carried out by the micro-vibration measuring subsystem and the micro-vibration excitation subsystem, and the test data in the soundproof state is obtained, including: The test support is placed in the vacuum subsystem; The spacecraft to be tested is connected with the test support, and the connection state is consistent with the normal state; The cable of the micro-vibration measuring subsystem is connected, the micro-vibration measuring subsystem is set and turned on for testing; The channel of the vacuum subsystem is closed, the internal pressure of the vacuum subsystem is kept, the whole device is kept in the shutdown silent state, and the vibration interference of external equipment on the test is eliminated; The background noise, micro-vibration response and transmission characteristic test working condition is implemented; After the test working condition is implemented, the channel of the vacuum subsystem is opened, and the test data in the soundproof state is obtained.

6. The spacecraft ground air damping characteristics evaluation test method according to claim 5, wherein, The spacecraft to be tested is placed in the vacuum subsystem, and the internal pressure of the vacuum subsystem is kept in the vacuum state, the background noise, micro-vibration response and transmission characteristic test of the spacecraft to be tested in the vacuum state is carried out by the micro-vibration measuring subsystem and the micro-vibration excitation subsystem, and the test data in the vacuum state is obtained, including: The test support is placed in the vacuum subsystem; The spacecraft to be tested is connected with the test support, and the connection state is consistent with the normal state and the soundproof state; The cable of the micro-vibration measuring subsystem is connected, the micro-vibration measuring subsystem is set and turned on for testing; The channel of the vacuum subsystem is closed, and the vacuum is extracted, the unit equipment is closed, the whole device is kept in the shutdown silent state, and the vibration interference of external equipment on the test is eliminated; The background noise, micro-vibration response and transmission characteristic test working condition is implemented; After the test working condition is implemented, the system is re-pressurized, and the air is filled, and the test data in the vacuum state is obtained.

7. The spacecraft ground air damping characteristics evaluation test method according to claim 6, wherein, Before the channel of the vacuum subsystem is closed and the vacuum is extracted, the method further includes: The temperature of the test equipment in the micro-vibration measuring subsystem and the micro-vibration excitation subsystem is monitored.

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