System and method for evaluating and testing ground air damping characteristics of spacecraft

Abstract

The invention provides a spacecraft ground air damping characteristic evaluation test system and method. The spacecraft ground air damping characteristic evaluation test 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 the 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 testing the transfer function and frequency response of a disturbance source single machine of a spacecraft to be tested in a whole cabin state, and obtaining the micro-vibration transfer characteristics of the spacecraft to be tested. The test of the ground air damping characteristics of the spacecraft can be efficiently and accurately realized, and the test efficiency and accuracy are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of spacecraft air damping characteristic testing, and in particular to a spacecraft ground air damping characteristic evaluation testing system and method. Background Art

[0002] As spacecraft structures become larger and more complex, and space missions become more sophisticated, high flexibility and light weight have become the development characteristics of spacecraft structures. In particular, payload equipment with extremely high directivity requirements, such as space optical cameras, has very high requirements for the working environment. The micro-vibration environment will cause camera optical axis jitter, camera body torsion, rigid displacement and deformation of optical components, etc., which have an impact on camera imaging quality that cannot be ignored. The damping characteristics of spacecraft are one of the key factors affecting optical axis jitter. However, factors such as complex structure, dense low-frequency modes, and strong coupling between various systems and the environment make the damping characteristics of spacecraft complex. The damping coefficient obtained by conventional ground micro-vibration tests consists of cabin damping and air damping, but there is a problem that the effect of air on the cabin damping characteristics corrected based on micro-vibration measurement data cannot be proposed.

[0003] Therefore, how to evaluate and test the ground air damping characteristics of spacecraft has become a technical problem that technical personnel in this field urgently need to solve. Summary of the invention

[0004] The present invention provides a system and method for evaluating and testing the ground air damping characteristics of a spacecraft, so as to solve the defects of low efficiency and poor accuracy of the evaluation and testing of the ground air damping characteristics of a spacecraft in the prior art.

[0005] In a first aspect, the present invention provides a spacecraft ground air damping characteristic evaluation and testing 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 the spacecraft to be tested;

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

[0008] The micro-vibration excitation subsystem is used to perform transfer function and frequency response tests on the spacecraft to be tested with a single disturbance source in a whole cabin state, so as to obtain the micro-vibration transfer characteristics of the spacecraft to be tested.

[0009] According to a spacecraft ground air damping characteristics evaluation and testing system provided by the present invention, the vacuum subsystem comprises: a roughing unit, a high vacuum module, a molecular pump module, a re-pressurization module, and a vacuum measurement and residual gas analysis module;

[0010] The rough pumping unit is used to pump the high vacuum module into a vacuum environment;

[0011] The molecular pump module, the re-pressurization module, and the vacuum measurement and residual gas analysis module are used to analyze the high vacuum module.

[0012] According to a spacecraft ground air damping characteristic evaluation and testing system provided by the present invention, 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 to collect micro-vibration response and noise data of the spacecraft to be tested;

[0014] The data acquisition system is used to receive and process the micro-vibration response and noise data.

[0015] According to a spacecraft ground air damping characteristics evaluation and testing system provided by the present invention, the micro-vibration excitation subsystem includes a line excitation module and a power amplifier;

[0016] The power amplifier is used to adjust the test data of the spacecraft to be tested by the excitation module, obtain the micro-vibration transfer characteristics and send them to the data acquisition system.

[0017] A spacecraft ground air damping characteristics evaluation and testing system provided by the present invention also includes a test bracket;

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

[0019] In a second aspect, the present invention further provides a method for evaluating and testing the ground air damping characteristics of a spacecraft, which is applied to the ground air damping characteristics evaluation and testing system for a spacecraft as described in any one of the above items, and the method comprises:

[0020] 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 under normal conditions are tested by the micro-vibration measurement subsystem and the micro-vibration excitation subsystem to obtain test data under normal conditions;

[0021] After completing the test under the normal state, the spacecraft to be tested is placed inside the vacuum subsystem, and the background noise, microvibration response and transfer characteristics of the spacecraft to be tested under the sound insulation state are tested by the microvibration measurement subsystem and the microvibration excitation subsystem to obtain test data under the sound insulation state;

[0022] After completing the test under the sound insulation state, the spacecraft to be tested is placed inside the vacuum subsystem, and the vacuum subsystem is kept in a vacuum state, and the background noise, microvibration response and transfer characteristics of the spacecraft to be tested under a vacuum state are tested by the microvibration measurement subsystem and the microvibration excitation subsystem to obtain test data under a vacuum state;

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

[0024] According to a method for evaluating and testing the ground air damping characteristics of a spacecraft provided by the present invention, the spacecraft to be tested is placed outside the vacuum subsystem, and the background noise, micro-vibration response and transfer characteristics of the spacecraft to be tested under normal conditions are tested by a micro-vibration measurement subsystem and a micro-vibration excitation subsystem to obtain test data under normal conditions, including:

[0025] Place the test stand outside the vacuum subsystem;

[0026] Connecting the spacecraft to be tested to the test stand to establish a boundary state;

[0027] Paste the micro-vibration measurement sensor and connect it to the data acquisition system to set the micro-vibration measurement subsystem parameters and conduct a continuity test;

[0028] Carry out background noise, micro-vibration response and transfer characteristics test conditions;

[0029] After the test conditions are implemented, the test data under normal conditions are obtained.

[0030] According to a method for evaluating and testing the ground air damping characteristics of a spacecraft provided by the present invention, the spacecraft to be tested is placed inside the vacuum subsystem, and the background noise, microvibration response and transfer characteristics of the spacecraft to be tested are tested under a sound insulation state by using the microvibration measurement subsystem and the microvibration excitation subsystem to obtain test data under a sound insulation state, including:

[0031] placing the test bracket inside the vacuum subsystem;

[0032] Connecting the spacecraft to be tested to the test bracket, wherein the connection state is consistent with the normal state;

[0033] Connect the cables of the micro-vibration measurement subsystem to perform parameter setting and conduction test of the micro-vibration measurement subsystem;

[0034] Close the channel of the vacuum subsystem, maintain the internal pressure of the vacuum subsystem, keep the whole equipment in a shutdown and silent state, and eliminate the vibration interference of external equipment to the test;

[0035] Carry out background noise, micro-vibration response and transfer characteristics test conditions;

[0036] After the test conditions are completed, the channel of the vacuum subsystem is opened to obtain the test data under the sound insulation state.

[0037] According to a method for evaluating and testing the ground air damping characteristics of a spacecraft provided by the present invention, 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 background noise, microvibration response and transfer characteristics of the spacecraft to be tested under a vacuum state are tested by the microvibration measurement subsystem and the microvibration excitation subsystem to obtain test data under a vacuum state, including:

[0038] placing the test bracket inside the vacuum subsystem;

[0039] Connecting the spacecraft to be tested to the test bracket, wherein the connection state is consistent with the normal state and the sound insulation state;

[0040] Connect the cables of the micro-vibration measurement subsystem to perform parameter setting and conduction test of the micro-vibration measurement subsystem;

[0041] Close the channel of the vacuum subsystem, evacuate the vacuum, shut down the unit equipment, keep the whole equipment in a shutdown and silent state, and eliminate the vibration interference of external equipment to the test;

[0042] Carry out background noise, micro-vibration response and transfer characteristics test conditions;

[0043] After the test conditions are completed, the system is re-pressurized and filled with air to obtain test data under vacuum conditions.

[0044] According to a method for evaluating and testing the ground air damping characteristics of a spacecraft provided by the present invention, before closing the channel of the vacuum subsystem and evacuating the vacuum, the method further includes:

[0045] Temperature monitoring is performed on the test equipment in the micro-vibration measurement subsystem and the micro-vibration excitation subsystem.

[0046] In a third aspect, the present invention further provides an electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the program, the test method for evaluating the ground air damping characteristics of a spacecraft as described in any one of the above-mentioned methods is implemented.

[0047] In a fourth aspect, the present invention further provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements any of the above-described test methods for evaluating the ground air damping characteristics of a spacecraft.

[0048] In a fifth aspect, the present invention further provides a computer program product, comprising a computer program, which, when executed by a processor, implements any of the above-mentioned test methods for evaluating the ground air damping characteristics of a spacecraft.

[0049] The present invention provides a spacecraft ground air damping characteristic evaluation and testing system, comprising: 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 the spacecraft to be tested; the micro-vibration measurement subsystem is used to measure the micro-vibration response and noise data at the target position of the spacecraft to be tested; the micro-vibration excitation subsystem is used to perform transfer function and frequency response tests of a single disturbance source in a whole cabin state on the spacecraft to be tested, and obtain the micro-vibration transfer characteristics of the spacecraft to be tested. Through the vacuum subsystem, the micro-vibration measurement subsystem and the micro-vibration excitation subsystem, the ground air damping characteristics of the spacecraft can be tested efficiently and accurately, thereby improving the test efficiency and accuracy.

[0050] The spacecraft ground air damping characteristics evaluation test method of the present invention has the characteristics of the above-mentioned system and can therefore achieve the same effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0051] In order to more clearly illustrate the technical solutions in the present invention or the prior art, a brief introduction will be given below to the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0052] Figure 1 is a schematic diagram of the structure of a spacecraft ground air damping characteristic evaluation and testing system provided in this embodiment;

[0053] Figure 2 is a flow chart of a method for evaluating and testing the ground air damping characteristics of a spacecraft provided in this embodiment;

[0054] Figure 3 It is a schematic diagram of the structure of the electronic device provided in this embodiment. DETAILED DESCRIPTION

[0055] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0056] Figure 1 It is a structural schematic diagram of the spacecraft ground air damping characteristics evaluation test system provided in this embodiment.

[0057] like Figure 1 As shown, the spacecraft ground air damping characteristic evaluation and testing system provided by the embodiment of the present invention includes: a vacuum subsystem, a micro-vibration measurement subsystem and a micro-vibration excitation subsystem. Among them, the vacuum subsystem is used to provide a vacuum environment for the spacecraft to be tested; the micro-vibration measurement subsystem is used to measure the micro-vibration response and noise data at the target position of the spacecraft to be tested; the micro-vibration excitation subsystem is used to perform transfer function and frequency response tests on the spacecraft to be tested with a single disturbance source in the whole cabin state, and obtain the micro-vibration transfer characteristics of the spacecraft to be tested.

[0058] In a specific implementation process, the spacecraft to be tested is defined as the spacecraft to be tested. The cooperation among 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 the normal state that is unrelated to the vacuum subsystem, that is, the spacecraft to be tested is outside the vacuum subsystem; the soundproof state that the spacecraft to be tested is in the vacuum subsystem but not in vacuum conditions; and the vacuum state that the spacecraft to be tested is in the vacuum subsystem and the interior is evacuated to vacuum. The micro-vibration response and transmission characteristics of the three different states can better realize the testing of the ground air damping characteristics of the spacecraft. When testing the spacecraft to be tested, it is placed in the test position by the test bracket.

[0059] The vacuum subsystem includes: roughing unit, high vacuum module, molecular pump module, re-pressurization module, and vacuum measurement and residual gas analysis module; the roughing unit is used to pump the high vacuum module to a vacuum environment, and can pump the container from normal pressure to less than 1Pa within 4-6 hours, providing a vacuum environment for the spacecraft to be tested. The molecular pump module, re-pressurization module, and 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 collect the micro-vibration response and noise data of the spacecraft to be tested; and 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 to be tested by the excitation module, obtain the micro-vibration transfer characteristics and send them to the data acquisition system.

[0062] The vacuum subsystem is mainly used to implement the test of the spacecraft under isolation and vacuum. When the gas inside the vacuum subsystem is maintained, a simple sound insulation test is performed, and the vacuum subsystem is used to isolate the interference of external noise. When the gas inside the vacuum subsystem is evacuated to a vacuum, a vacuum test is performed to simulate the micro-vibration of the spacecraft in a vacuum environment. The relevant parameters of the internal equipment of the micro-vibration excitation subsystem and the micro-vibration measurement subsystem are kept consistent under different test conditions to ensure the accuracy and reliability of the final test results.

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

[0064] Figure 2 It is a flow chart of the spacecraft ground air damping characteristics evaluation test method provided in this embodiment.

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

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

[0067] In a specific implementation process, the background noise, micro-vibration response and transfer characteristics of the spacecraft under test are tested in three different states. First, the test is carried out under normal conditions. The specific process is as follows:

[0068] Place the test bracket outside the vacuum subsystem; connect the spacecraft to be tested to the test bracket to establish the boundary state; the surrounding ground equipment is turned off to ensure that the environment is in the optimal state; paste the micro-vibration measurement sensor and connect it to the data acquisition system to set the micro-vibration measurement subsystem parameters and conduct a conduction test; carry out background noise, micro-vibration response and transfer characteristics test conditions; after the test conditions are completed, obtain the test data under normal conditions.

[0069] 202. After completing the test under normal conditions, the spacecraft to be tested is placed inside the vacuum subsystem, and the background noise, micro-vibration response and transfer characteristics of the spacecraft to be tested under the sound insulation state are tested by the micro-vibration measurement subsystem and the micro-vibration excitation subsystem to obtain the test data under the sound insulation state.

[0070] After obtaining the test data under normal conditions, place the test bracket inside the vacuum subsystem; connect the spacecraft to be tested to the test bracket, and keep the connection and boundary conditions consistent with normal conditions; connect the cables of the micro-vibration measurement subsystem, and perform parameter setting and conduction test on the micro-vibration measurement subsystem; close the channel of the vacuum subsystem, maintain the vacuum subsystem at normal pressure, and keep the entire equipment in a shutdown and silent state to eliminate vibration interference from external equipment to the test, so that the vacuum subsystem can play a certain role in sound insulation; carry out background noise, micro-vibration response and transfer characteristic test conditions; after the test conditions are completed, open the channel of the vacuum subsystem to obtain the test data under the sound insulation state.

[0071] 203. After completing the test under the sound insulation state, the spacecraft to be tested is placed inside the vacuum subsystem and the vacuum subsystem is kept in a vacuum state. The background noise, micro-vibration response and transfer characteristics of the spacecraft to be tested under the vacuum state are tested by the micro-vibration measurement subsystem and the micro-vibration excitation subsystem to obtain the test data under the vacuum state.

[0072] After obtaining the test data under the sound insulation state, place the test bracket inside the vacuum subsystem; connect the spacecraft to be tested to the test bracket, and keep the connection and boundary states consistent with the normal state and the sound insulation state; connect the cables of the micro-vibration measurement subsystem, set the parameters of the micro-vibration measurement subsystem and conduct the continuity test; monitor the temperature of the test equipment in the micro-vibration measurement subsystem and the micro-vibration excitation subsystem; close the channel of the vacuum subsystem, evacuate the system to a vacuum degree below 1Pa, shut down the unit equipment, keep the entire equipment in the shutdown and silent state, and eliminate the vibration interference of external equipment on the test; carry out background noise, micro-vibration response and transfer characteristic test conditions; after the test conditions are completed, the system is re-pressurized and filled with air to obtain the test data under the vacuum state.

[0073] 204. The test data under normal conditions, the test data under sound insulation conditions and the test data under vacuum conditions are processed to determine the air damping characteristics of the spacecraft to be tested.

[0074] Finally, an overall comparative analysis of the data under the three test conditions is conducted to evaluate the air damping characteristics of the spacecraft in order to obtain the impact of the atmospheric environment on the damping characteristics of the spacecraft.

[0075] Figure 3 It is a schematic diagram of the structure of the electronic device provided in this embodiment.

[0076] like Figure 3 As shown, the electronic device may include: a processor 310, a communication interface 320, a memory 330 and a communication bus 340, wherein the processor 310, the communication interface 320 and the memory 330 communicate with each other through the communication bus 340. The processor 310 may call the logic instructions in the memory 330 to execute a method for evaluating the ground air damping characteristics of a spacecraft, the method comprising: placing the spacecraft to be tested outside the vacuum subsystem, and testing the background noise, microvibration response and transfer characteristics of the spacecraft to be tested under normal conditions through a microvibration measurement subsystem and a microvibration excitation subsystem to obtain test data under normal conditions; after completing the test under the normal conditions, placing the spacecraft to be tested inside the vacuum subsystem, and testing the background noise of the spacecraft to be tested under sound insulation conditions through the microvibration measurement subsystem and the microvibration excitation subsystem. , micro-vibration response and transfer characteristics tests to obtain test data under the sound insulation state; after completing the test under the sound insulation state, the spacecraft to be tested is placed inside the vacuum subsystem, and the vacuum subsystem is kept in a vacuum state, and the background noise, micro-vibration response and transfer characteristics tests under the vacuum state are performed on the spacecraft to be tested by the micro-vibration measurement subsystem and the micro-vibration excitation subsystem to obtain test data under the vacuum state; the test data under the normal state, the test data under the sound insulation state and the test data under the vacuum state are processed to determine the air damping characteristics of the spacecraft to be tested.

[0077] In addition, the logic instructions in the above-mentioned memory 330 can be implemented in the form of a software functional unit and can be stored in a computer-readable storage medium when it is sold or used as an independent product. Based on such an understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art or the part of the technical solution, can be embodied in the form of a software product, and the computer software product is stored in a storage medium, including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present invention. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk and other media that can store program codes.

[0078] On the other hand, the present invention also provides a computer program product, which includes a computer program. The computer program can be stored on a non-transitory computer-readable storage medium. When the computer program is executed by a processor, the computer can execute the spacecraft ground air damping characteristic evaluation test method provided by the above-mentioned methods, and the method includes: placing the spacecraft to be tested outside the vacuum subsystem, and performing background noise, micro-vibration response and transfer characteristic tests on the spacecraft to be tested under normal conditions through a micro-vibration measurement subsystem and a micro-vibration excitation subsystem to obtain test data under normal conditions; after completing the test under the normal condition, placing the spacecraft to be tested inside the vacuum subsystem, and performing micro-vibration measurement subsystem on the spacecraft to be tested. The system and the micro-vibration excitation subsystem perform background noise, micro-vibration response and transfer characteristic tests on the spacecraft to be tested under the sound insulation state to obtain test data under the sound insulation state; after completing the test under the sound insulation state, the spacecraft to be tested is placed inside the vacuum subsystem, and the vacuum subsystem is kept in a vacuum state, and the background noise, micro-vibration response and transfer characteristic tests on the spacecraft to be tested under the vacuum state are performed by the micro-vibration measurement subsystem and the micro-vibration excitation subsystem to obtain test data under the vacuum state; the test data under the normal state, the test data under the sound insulation state and the test data under the vacuum state are processed to determine the air damping characteristics of the spacecraft to be tested.

[0079] On the other hand, the present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, is implemented to execute the spacecraft ground air damping characteristic evaluation test method provided by the above-mentioned methods, the method comprising: placing the spacecraft to be tested outside the vacuum subsystem, and performing background noise, microvibration response and transfer characteristic tests on the spacecraft to be tested under normal conditions through a micro-vibration measurement subsystem and a micro-vibration excitation subsystem to obtain test data under normal conditions; after completing the test under the normal conditions, placing the spacecraft to be tested inside the vacuum subsystem, and performing background noise, microvibration response and transfer characteristic tests on the spacecraft to be tested through the micro-vibration measurement subsystem and the micro-vibration excitation subsystem to obtain test data under normal conditions; The spacecraft to be tested is tested for background noise, micro-vibration response and transfer characteristics under a sound insulation state to obtain test data under a sound insulation state; after completing the test under the sound insulation state, the spacecraft to be tested is placed inside the vacuum subsystem, and the vacuum subsystem is kept in a vacuum state, and the background noise, micro-vibration response and transfer characteristics of the spacecraft to be tested in a vacuum state are tested by the micro-vibration measurement subsystem and the micro-vibration excitation subsystem to obtain test data under a vacuum state; the test data under the normal state, the test data under the sound insulation state and the test data under the vacuum state are processed to determine the air damping characteristics of the spacecraft to be tested.

[0080] The device embodiments described above are merely illustrative, wherein the units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they may be located in one place, or they may be distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the scheme of this embodiment. Ordinary technicians in this field can understand and implement it without paying creative labor.

[0081] Through the description of the above implementation methods, those skilled in the art can clearly understand that each implementation method can be implemented by means of software plus a necessary general hardware platform, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solution is essentially or the part that contributes to the prior art can be embodied in the form of a software product, and the computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a disk, an optical disk, etc., including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or some parts of the embodiments.

[0082] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A spacecraft ground air damping characteristics evaluation and testing system, characterized in that: include: Vacuum subsystem, micro-vibration measurement subsystem and micro-vibration excitation subsystem; The vacuum subsystem is used to provide a vacuum environment for the spacecraft to be tested; The micro-vibration measurement subsystem is used to measure the micro-vibration response and noise data at the target position of the spacecraft to be tested; The micro-vibration excitation subsystem is used to perform transfer function and frequency response tests on the spacecraft to be tested with a single disturbance source in a whole cabin state, so as to obtain the micro-vibration transfer characteristics of the spacecraft to be tested.

2. The spacecraft ground air damping characteristics evaluation and testing system according to claim 1, characterized in that: The vacuum subsystem includes: a roughing unit, a high vacuum module, a molecular pump module, a re-pressurization module, and a vacuum measurement and residual gas analysis module; The rough pumping unit is used to pump the high vacuum module into a vacuum environment; The molecular pump module, the re-pressurization module, and the vacuum measurement and residual gas analysis module are used to analyze the high vacuum module.

3. The spacecraft ground air damping characteristics evaluation and testing system according to claim 1, characterized in that: 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 collect micro-vibration response and noise data of the spacecraft to be tested; The data acquisition system is used to receive and process the micro-vibration response and noise data.

4. The spacecraft ground air damping characteristics evaluation and testing system according to claim 3, characterized in that: 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 to be tested by the excitation module, obtain the micro-vibration transfer characteristics and send them to the data acquisition system.

5. The spacecraft ground air damping characteristics evaluation and testing system according to claim 1, characterized in that: Also included is a test stand; The test bracket is used for placing the spacecraft to be tested.

6. A method for evaluating and testing the ground air damping characteristics of a spacecraft, characterized in that: Applied to the spacecraft ground air damping characteristic evaluation test system as claimed in any one of claims 1 to 5, the method comprises: 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 under normal conditions are tested by the micro-vibration measurement subsystem and the micro-vibration excitation subsystem to obtain test data under normal conditions; After completing the test under the normal state, the spacecraft to be tested is placed inside the vacuum subsystem, and the background noise, microvibration response and transfer characteristics of the spacecraft to be tested under the sound insulation state are tested by the microvibration measurement subsystem and the microvibration excitation subsystem to obtain test data under the sound insulation state; After completing the test under the sound insulation state, the spacecraft to be tested is placed inside the vacuum subsystem, and the vacuum subsystem is kept in a vacuum state, and the background noise, microvibration response and transfer characteristics of the spacecraft to be tested under a vacuum state are tested by the microvibration measurement subsystem and the microvibration excitation subsystem to obtain test data under a vacuum state; The test data under the normal state, the test data under the sound insulation state and the test data under the vacuum state are processed to determine the air damping characteristics of the spacecraft to be tested.

7. The spacecraft ground air damping characteristic evaluation and testing method according to claim 6, characterized in that: 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 under normal conditions by using the micro-vibration measurement subsystem and the micro-vibration excitation subsystem to obtain test data under normal conditions, including: Place the test stand outside the vacuum subsystem; Connecting the spacecraft to be tested to the test stand to establish a boundary state; Paste the micro-vibration measurement sensor and connect it to the data acquisition system to set the micro-vibration measurement subsystem parameters and conduct a continuity test; Carry out background noise, micro-vibration response and transfer characteristics test conditions; After the test conditions are implemented, the test data under normal conditions are obtained.

8. The spacecraft ground air damping characteristic evaluation and testing method according to claim 7, characterized in that: The step of placing the spacecraft to be tested inside the vacuum subsystem, and testing the background noise, microvibration response, and transfer characteristics of the spacecraft to be tested under a sound insulation state through the microvibration measurement subsystem and the microvibration excitation subsystem to obtain test data under a sound insulation state includes: placing the test bracket inside the vacuum subsystem; Connecting the spacecraft to be tested to the test bracket, wherein the connection state is consistent with the normal state; Connect the cables of the micro-vibration measurement subsystem to perform parameter setting and conduction test of the micro-vibration measurement subsystem; Close the channel of the vacuum subsystem, maintain the internal pressure of the vacuum subsystem, keep the whole equipment in a shutdown and silent state, and eliminate the vibration interference of external equipment to the test; Carry out background noise, micro-vibration response and transfer characteristics test conditions; After the test conditions are completed, the channel of the vacuum subsystem is opened to obtain the test data under the sound insulation state.

9. The spacecraft ground air damping characteristics evaluation and testing method according to claim 8, characterized in that: The spacecraft to be tested is placed inside the vacuum subsystem, and the vacuum subsystem is kept in a vacuum state, and background noise, micro-vibration response and transfer characteristics of the spacecraft to be tested under a vacuum state are tested by the micro-vibration measurement subsystem and the micro-vibration excitation subsystem to obtain test data under a vacuum state, including: placing the test bracket inside the vacuum subsystem; Connecting the spacecraft to be tested to the test bracket, wherein the connection state is consistent with the normal state and the sound insulation state; Connect the cables of the micro-vibration measurement subsystem to perform parameter setting and conduction test of the micro-vibration measurement subsystem; Close the channel of the vacuum subsystem, evacuate the vacuum, shut down the unit equipment, keep the whole equipment in a shutdown and silent state, and eliminate the vibration interference of external equipment to the test; Carry out background noise, micro-vibration response and transfer characteristics test conditions; After the test conditions are completed, the system is re-pressurized and filled with air to obtain test data under vacuum conditions.

10. The spacecraft ground air damping characteristics evaluation and testing method according to claim 9, characterized in that: Before closing the channel of the vacuum subsystem and evacuating the vacuum, the method further comprises: Temperature monitoring is performed on the test equipment in the micro-vibration measurement subsystem and the micro-vibration excitation subsystem.

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