Method for testing autonomous tracking and pointing precision of spaceborne antenna

Abstract

The invention discloses a satellite-borne antenna autonomous tracking and pointing precision testing method. The method comprises the steps that an antenna autonomous tracking and pointing precision measuring system is built; calibrating and verifying the antenna autonomous tracking and pointing precision measurement system; and testing and verifying the pointing precision of the antenna to be tested in the autonomous tracking process based on the antenna autonomous tracking pointing precision measurement system completing calibration verification. According to the method disclosed by the invention, a measurement system is built based on an inclinometer inertial gravity field measurement principle, specific measurement steps are given, and the pointing precision of the dual-axis rotation autonomous tracking process of the antenna to be measured is comprehensively fitted by respectively measuring the pointing precision of the azimuth axis and the pitch axis of the antenna to be measured in the autonomous tracking process.

Description

Technical Field

[0001] The invention belongs to the technical field of deep space exploration, and in particular relates to a method for testing the autonomous tracking and pointing accuracy of a satellite-borne antenna. Background Art

[0002] In deep space exploration missions represented by future deep space probes, satellite-borne antennas are required to autonomously track relay satellites to achieve real-time control instructions and digital signal transmission. This type of satellite-borne antenna generally uses a directional antenna form, and the antenna beam needs to point to the direction of the relay satellite in real time, and needs to have autonomous tracking capabilities. In order to verify the accuracy of the pointing accuracy of the antenna's autonomous tracking process, it is necessary to simulate the antenna's autonomous tracking process on the ground and complete the test of the antenna's pointing accuracy during the autonomous tracking process. This test task belongs to the dynamic test mode, that is, the antenna rotates intermittently during the entire test process, and the interval between each rotation action is very short, with a minimum of less than 1 minute. Using the traditional theodolite test method, it is impossible to measure the pointing accuracy of each rotation action of the antenna in a short time; the laser tracker test method can only measure the pointing accuracy of the single-axis motion process in real time. When the active axis rotation process drives the follower axis to rotate, it is impossible to give the pointing accuracy of the active axis and the follower axis in real time. Therefore, constrained by the measurement methods of theodolite and laser tracker, the traditional pointing accuracy measurement method cannot meet the needs of dynamic test tasks.

[0003] Taking into account the process of the antenna autonomously tracking the relay satellite, the many rotation times of the antenna, the short rotation intervals, the simultaneous dual-axis movement of the antenna and other constraints, in order to meet the mission requirements in the field of deep space exploration, it is necessary to complete the pointing accuracy test and verification of the antenna autonomous tracking process on the ground. Existing technologies and results cannot meet the mission requirements. Summary of the invention

[0004] The technology of the present invention solves the problem: overcomes the shortcomings of the prior art, provides a method for testing the pointing accuracy of a satellite-borne antenna autonomous tracking, builds a measurement system based on the inertial gravity field measurement principle of an inclinometer, and provides specific measurement steps. By respectively measuring the pointing accuracy of the azimuth axis and the pitch axis of the antenna to be tested during the autonomous tracking process, the pointing accuracy of the dual-axis rotation autonomous tracking process of the antenna to be tested is comprehensively fitted.

[0005] In order to solve the above technical problems, the present invention discloses a method for testing the autonomous tracking and pointing accuracy of a satellite-borne antenna, comprising:

[0006] Build an antenna autonomous tracking and pointing accuracy measurement system;

[0007] Calibrate and verify the antenna autonomous tracking and pointing accuracy measurement system;

[0008] Based on the antenna autonomous tracking pointing accuracy measurement system that has completed calibration and verification, the pointing accuracy of the antenna under test during the autonomous tracking process is tested and verified.

[0009] In the above-mentioned satellite-borne antenna autonomous tracking and pointing accuracy test method, the antenna to be tested has a two-dimensional rotation function, and the rotation mechanism of the antenna to be tested includes: an azimuth axis responsible for the azimuth rotation of the antenna to be tested and an elevation axis responsible for the pitch rotation of the antenna to be tested.

[0010] In the above-mentioned satellite-borne antenna autonomous tracking and pointing accuracy test method, the antenna autonomous tracking and pointing accuracy measurement system includes: a computer terminal device, an inclinometer and an integrated interface unit;

[0011] The inclinometer is used to measure the rotation angle of the antenna under test under different working conditions and send the measured rotation angle to the computer terminal device;

[0012] The computer terminal device is used to process and analyze the received rotation angle to obtain the pointing accuracy test result of the autonomous tracking process of the antenna to be tested; and generate an antenna rotation instruction;

[0013] The integrated interface unit is used to output the antenna rotation instruction to the antenna to be tested, so as to realize the rotation control of the antenna to be tested.

[0014] In the above-mentioned satellite-borne antenna autonomous tracking and pointing accuracy test method, the antenna autonomous tracking and pointing accuracy measurement system is calibrated and verified, including:

[0015] Step 21, controlling the antenna to be tested to a first working condition, and measuring the actual rotation angle of the antenna to be tested under the first working condition by using a theodolite and an inclinometer respectively; comparing the actual rotation angle of the antenna to be tested under the first working condition measured by the theodolite with the actual rotation angle of the antenna to be tested under the first working condition measured by the inclinometer, and if the consistency of the measurement results of the theodolite and the inclinometer is not greater than a set value, executing step 22;

[0016] Step 22, controlling the antenna to be tested to a second working condition, and measuring the actual rotation angle of the antenna to be tested under the second working condition by means of a theodolite and an inclinometer respectively; comparing the actual rotation angle of the antenna to be tested under the second working condition measured by the theodolite with the actual rotation angle of the antenna to be tested under the second working condition measured by the inclinometer, and if the consistency between the measurement results of the theodolite and the inclinometer is not greater than a set value, executing step 23;

[0017] Step 23, controlling the antenna to be tested to the third working condition, and measuring the actual rotation angle of the antenna to be tested under the third working condition by the theodolite and the inclinometer respectively; comparing the actual rotation angle of the antenna to be tested under the third working condition measured by the theodolite with the actual rotation angle of the antenna to be tested under the third working condition measured by the inclinometer, and if the consistency of the measurement results of the theodolite and the inclinometer is not greater than the set value, executing step 24;

[0018] Step 24, control the antenna to be tested to the fourth working condition, and measure the actual rotation angle of the antenna to be tested under the fourth working condition by the theodolite and the inclinometer respectively; compare the actual rotation angle of the antenna to be tested under the fourth working condition measured by the theodolite with the actual rotation angle of the antenna to be tested under the fourth working condition measured by the inclinometer; if the consistency of the measurement results of the theodolite and the inclinometer is not greater than the set value, the calibration verification of the antenna autonomous tracking and pointing accuracy measurement system is completed.

[0019] In the above-mentioned satellite-borne antenna autonomous tracking and pointing accuracy test method,

[0020] The first working condition refers to the working condition where the azimuth axis points at an angle of 0°;

[0021] The second working condition includes: working conditions where the azimuth axis pointing angles are ±30°, ±60° and ±90°;

[0022] The third working condition refers to the working condition where the pitch axis pointing angle is 0°;

[0023] The fourth working condition includes: working conditions where the pitch axis pointing angles are ±30°, ±60° and ±90°.

[0024] In the above-mentioned satellite-borne antenna autonomous tracking and pointing accuracy test method, the set value is 0.02°.

[0025] In the above-mentioned satellite-borne antenna autonomous tracking and pointing accuracy test method, based on the antenna autonomous tracking and pointing accuracy measurement system that has completed calibration and verification, the pointing accuracy of the antenna to be tested in the autonomous tracking process is tested and verified, including:

[0026] Based on the antenna autonomous tracking pointing accuracy measurement system that has completed calibration verification, the pointing accuracy of the antenna to be tested under working conditions A and B is tested and verified;

[0027] After completing the pointing accuracy test and verification of the antenna under test under working conditions A and B, a rotation command carrying a specified pointing angle is sent to the antenna under test through the integrated interface unit to simulate the autonomous tracking working mode of the antenna under test;

[0028] In the simulated autonomous tracking working mode, each time the antenna to be tested completes its rotation according to the specified pointing angle indicated by the rotation instruction, the actual rotation angle of the antenna to be tested is measured by the inclinometer, and the actual rotation angle measured by the inclinometer is compared with the theoretical specified pointing angle; based on the comparison result, the pointing accuracy test verification result of the autonomous tracking process of the antenna to be tested is given.

[0029] In the above-mentioned satellite-borne antenna autonomous tracking and pointing accuracy test method,

[0030] Working condition A is: the azimuth axis and the pitch axis rotate simultaneously; the azimuth axis rotates clockwise, the rotation angle range is -90°~+90°, and the rotation angle is 1° each time; the pitch axis rotates clockwise first and then counterclockwise, the rotation angle range is 0°~+90°, +90°~0°, and the rotation angle is 1° each time;

[0031] Working condition B is: the azimuth axis and the pitch axis rotate simultaneously; the azimuth axis rotates counterclockwise, the rotation angle range is +90°~-90°, and the rotation angle is 1° each time; the pitch axis rotates counterclockwise first and then clockwise, the rotation angle range is +90°~0°, 0°~+90°, and the rotation angle is 1° each time.

[0032] In the above-mentioned test method for the autonomous tracking pointing accuracy of the satellite-borne antenna, when testing and verifying the pointing accuracy of the antenna to be tested under working conditions A and B:

[0033] Both working conditions A and B were measured twice, with the pointing accuracy of one axis measured each time;

[0034] After the measurement is completed, the maximum value of the measurement data obtained by the inclinometer is compared with the technical indicators of the pointing accuracy of the antenna to be tested; if the maximum value of the measurement data obtained by the inclinometer meets the technical indicators of the pointing accuracy of the antenna to be tested, a rotation command carrying a specified pointing angle is sent to the antenna to be tested through the integrated interface unit to simulate the autonomous tracking working mode of the antenna to be tested.

[0035] In the above-mentioned satellite-borne antenna autonomous tracking pointing accuracy test method, in the simulated autonomous tracking working mode: the test is repeated twice; finally, the comparison results of the azimuth axis and the pitch axis are comprehensively compared to give the pointing accuracy test verification result of the autonomous tracking process of the antenna to be tested.

[0036] The present invention has the following advantages:

[0037] (1) The present invention discloses a method for testing the pointing accuracy of satellite-borne antenna autonomous tracking. The conventional theodolite and laser tracker measurement methods cannot meet the measurement task requirements of simultaneous dual-axis rotation of the antenna and short rotation time interval. The method solves the problems of large number of rotations of the antenna in autonomous tracking, short rotation time interval, and high antenna pointing accuracy. The measurement time is shortened, and the pointing accuracy result of each rotation process is read in real time. The measurement accuracy is better than 0.02°.

[0038] (3) The present invention discloses a method for testing the autonomous tracking and pointing accuracy of a satellite-borne antenna, which can realize the testing of the pointing accuracy of the dual-axis rotation autonomous tracking process of the antenna to be tested by using only one set of inclinometers. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Figure 1 It is a block diagram of a system for measuring the antenna's autonomous tracking and pointing accuracy in an embodiment of the present invention;

[0040] Figure 2 is a schematic structural diagram of an antenna to be tested in an embodiment of the present invention;

[0041] Figure 3 It is a schematic diagram of the assembly relationship between an antenna to be tested and an inclinometer in an embodiment of the present invention;

[0042] Figure 4 It is a schematic diagram of the assembly relationship between another antenna to be tested and the inclinometer in an embodiment of the present invention. DETAILED DESCRIPTION

[0043] In order to make the objectives, technical solutions and advantages of the present invention more clear, the embodiments disclosed in the present invention will be further described in detail below with reference to the accompanying drawings.

[0044] In this embodiment, the method for testing the autonomous tracking and pointing accuracy of the satellite-borne antenna includes:

[0045] Step 1: Build an antenna autonomous tracking and pointing accuracy measurement system.

[0046] In this embodiment, if Figure 1 As shown, the antenna autonomous tracking pointing accuracy measurement system mainly includes: a computer terminal device 1, an inclinometer 3 and an integrated interface unit 4. Among them, the inclinometer 3 is used to measure the rotation angle of the antenna 2 to be tested under different working conditions, and send the measured rotation angle to the computer terminal device 1 via a wireless transmission method (such as Bluetooth); the measurement accuracy of the inclinometer 3 is ±0.02°. The computer terminal device 1 is used to process and analyze the received rotation angle to obtain the pointing accuracy test result of the autonomous tracking process of the antenna 2 to be tested; and generate an antenna rotation instruction. The integrated interface unit 4 is used to output the antenna rotation instruction to the antenna 2 to be tested, so as to realize the rotation control of the antenna 2 to be tested.

[0047] Further, such as Figure 2 As shown, the antenna 2 to be tested has a two-dimensional rotation function, and the rotation mechanism of the antenna 2 to be tested includes: an azimuth axis 21 responsible for the azimuth rotation of the antenna 2 to be tested and an elevation axis 22 responsible for the elevation rotation of the antenna 2 to be tested.

[0048] Step 2: Calibrate and verify the antenna autonomous tracking and pointing accuracy measurement system.

[0049] In this embodiment, it is first necessary to verify the accuracy of the antenna autonomous tracking pointing accuracy measurement system. The specific implementation steps are as follows:

[0050] Sub-step 21, control the antenna 2 to be measured to the first working condition, measure the actual rotation angle of the antenna 2 to be measured under the first working condition by the theodolite and the inclinometer 3 respectively; compare the actual rotation angle of the antenna 2 to be measured under the first working condition measured by the theodolite with the actual rotation angle of the antenna 2 to be measured under the first working condition measured by the inclinometer 3, if the consistency of the measurement results of the theodolite and the inclinometer 3 is not greater than the set value (such as 0.02°), execute step 22. Among them, the first working condition refers to: the working condition where the azimuth axis 21 points to an angle of 0°. The purpose of this step is to ensure that the axis of the inclinometer 3 is parallel to the axis of the azimuth axis 21 (the parallelism is not less than 0.02°). If the consistency of the measurement results of the theodolite and the inclinometer 3 is greater than the set value, it is necessary to adjust the measurement accuracy of the entire measurement system by means of padding gaskets, changing the installation position of the inclinometer 3, etc.

[0051] Step 22, control the antenna 2 to be tested to the second working condition, measure the actual rotation angle of the antenna 2 to be tested under the second working condition by the theodolite and the inclinometer 3 respectively; compare the actual rotation angle of the antenna 2 to be tested under the second working condition measured by the theodolite with the actual rotation angle of the antenna 2 to be tested under the second working condition measured by the inclinometer 3, if the consistency of the measurement results of the theodolite and the inclinometer 3 is not greater than the set value, execute step 23. Among them, the second working condition includes: the conditions where the pointing angles of the azimuth axis 21 are ±30°, ±60° and ±90°. The purpose of this step is to realize the calibration of the rotation pointing accuracy of the azimuth axis 21 by measuring.

[0052] Step 23, control the antenna 2 to be tested to the third working condition, measure the actual rotation angle of the antenna 2 to be tested under the third working condition by the theodolite and the inclinometer 3 respectively; compare the actual rotation angle of the antenna 2 to be tested under the third working condition measured by the theodolite with the actual rotation angle of the antenna 2 to be tested under the third working condition measured by the inclinometer 3, if the consistency of the measurement results of the theodolite and the inclinometer 3 is not greater than the set value, execute step 24. Among them, the third working condition refers to: the working condition where the pitch axis 22 points to an angle of 0°. The purpose of this step is to ensure that the axis of the inclinometer 3 is parallel to the axis of the pitch axis 22.

[0053] Step 24, control the antenna 2 to be tested to the fourth working condition, measure the actual rotation angle of the antenna 2 to be tested under the fourth working condition by the theodolite and the inclinometer 3 respectively; compare the actual rotation angle of the antenna 2 to be tested under the fourth working condition measured by the theodolite with the actual rotation angle of the antenna 2 to be tested under the fourth working condition measured by the inclinometer 3. If the consistency of the measurement results of the theodolite and the inclinometer 3 is not greater than the set value, the calibration verification of the antenna autonomous tracking pointing accuracy measurement system is completed. Among them, the fourth working condition includes: the pointing angles of the pitch axis 22 are ±30°, ±60° and ±90°. The purpose of this step is to realize the measurement and calibration of the rotation pointing accuracy of the pitch axis 22.

[0054] At this point, the calibration and verification of the antenna autonomous tracking and pointing accuracy measurement system has been completed.

[0055] Step 3: Based on the antenna autonomous tracking pointing accuracy measurement system that has completed calibration verification, the pointing accuracy of the antenna 2 under test during the autonomous tracking process is tested and verified.

[0056] In this embodiment, before testing and verifying the pointing accuracy of the autonomous tracking process of the antenna 2 to be tested, it is also necessary to test the pointing accuracy of the full-angle rotation working condition of the antenna 2 to be tested. The purpose of this test is to verify the accuracy of the pointing accuracy of the full-angle rotation of the antenna to be tested in the non-autonomous tracking working mode. The specific implementation method is as follows: Based on the antenna autonomous tracking pointing accuracy measurement system that has completed calibration verification, the pointing accuracy of the antenna 2 to be tested under working conditions A and B is tested and verified. Among them, working condition A is: the azimuth axis 21 and the pitch axis 22 rotate simultaneously; the azimuth axis 21 rotates clockwise, the rotation angle range is -90° to +90°, and the rotation angle is 1° each time; the pitch axis 22 rotates clockwise first and then counterclockwise, the rotation angle range is 0° to +90°, +90° to 0°, and the rotation angle is 1° each time. Working condition B is: the azimuth axis 21 and the pitch axis 22 rotate simultaneously; the azimuth axis 21 rotates counterclockwise, the rotation angle range is +90°~-90°, and the rotation angle is 1° each time; the pitch axis 22 rotates counterclockwise first and then clockwise, the rotation angle range is +90°~0°, 0°~+90°, and the rotation angle is 1° each time. Since the pointing accuracy of only one axis can be tested at a time, working conditions A and working conditions B are measured twice, and the pointing accuracy of one axis is measured each time. After the measurement is completed, the maximum value of the measurement data obtained by the inclinometer 3 is compared with the technical indicators of the pointing accuracy of the antenna 2 to be tested; if the maximum value of the measurement data obtained by the inclinometer 3 meets the technical indicators of the pointing accuracy of the antenna 2 to be tested, the steps of testing and verifying the pointing accuracy of the autonomous tracking process of the antenna 2 to be tested are performed.

[0057] The specific implementation process of testing and verifying the pointing accuracy of the antenna 2 under test in the autonomous tracking process is as follows: after completing the pointing accuracy test and verification of the antenna 2 under test under working conditions A and B, the rotation instruction carrying the specified pointing angle is sent to the antenna 2 under test through the integrated interface unit 4 to simulate the autonomous tracking working mode of the antenna 2 under test. Among them, in the simulated autonomous tracking working mode, each time the antenna 2 under test completes the rotation according to the specified pointing angle indicated by the rotation instruction, the actual rotation angle of the antenna 2 under test is measured by the inclinometer 3, and the actual rotation angle measured by the inclinometer 3 is compared with the theoretical specified pointing angle; according to the comparison result, the pointing accuracy test verification result of the autonomous tracking process of the antenna 2 under test is given. Since the pointing accuracy of only one axis can be tested at a time, it is necessary to repeat the test twice; finally, the comparison results of the azimuth axis 21 and the pitch axis 22 are combined to give the pointing accuracy test verification result of the autonomous tracking process of the antenna 2 under test.

[0058] It should be noted that when measuring the pointing accuracy of the azimuth axis 21, the inclinometer 3 is fixed at the output end of the azimuth axis 21. Figure 3 When measuring the pointing accuracy of the pitch axis 22, the inclinometer 3 is fixed at the output end of the pitch axis 22, such as Figure 4 The dual-axis rotation of the antenna to be tested drives the inclinometer on one axis to rotate.

[0059] In summary, the method for testing the pointing accuracy of the autonomous tracking of satellite-borne antennas in the present invention can be applied to the pointing accuracy test of the autonomous tracking process of antennas, and is suitable for the pointing accuracy test of the dynamic rotation process of antennas in scenarios such as a large number of antenna rotation actions, a short rotation action interval, and simultaneous dual-axis antenna actions. The method of the present invention has been verified on-orbit, and the measurement accuracy is better than 0.02°.

[0060] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

[0061] The contents not described in detail in the specification of the present invention belong to the common knowledge of the professionals in this field.

Claims

1. A method for testing the autonomous tracking and pointing accuracy of a satellite-borne antenna, characterized in that: include: Build an antenna autonomous tracking and pointing accuracy measurement system; Calibrate and verify the antenna autonomous tracking and pointing accuracy measurement system; Based on the antenna autonomous tracking pointing accuracy measurement system that has completed calibration verification, the pointing accuracy of the antenna (2) under test during the autonomous tracking process is tested and verified.

2. The method for testing the autonomous tracking and pointing accuracy of a satellite-borne antenna according to claim 1, characterized in that: The antenna to be tested (2) has a two-dimensional rotation function, and the rotation mechanism of the antenna to be tested (2) comprises: an azimuth axis (21) responsible for the azimuth rotation of the antenna to be tested (2) and an elevation axis (22) responsible for the elevation rotation of the antenna to be tested (2).

3. The method for testing the autonomous tracking and pointing accuracy of a satellite-borne antenna according to claim 2, characterized in that: An antenna autonomous tracking pointing accuracy measurement system comprises: a computer terminal device (1), an inclinometer (3) and an integrated interface unit (4); An inclinometer (3) is used to measure the rotation angle of the antenna to be measured (2) under different working conditions, and send the measured rotation angle to the computer terminal device (1); The computer terminal device (1) is used to process and analyze the received rotation angle to obtain the pointing accuracy test result of the autonomous tracking process of the antenna to be tested (2); and to generate an antenna rotation instruction; The integrated interface unit (4) is used to output an antenna rotation instruction to the antenna to be tested (2) to realize rotation control of the antenna to be tested (2).

4. The method for testing the autonomous tracking and pointing accuracy of a satellite-borne antenna according to claim 3, characterized in that: Calibrate and verify the antenna autonomous tracking and pointing accuracy measurement system, including: Step 21, controlling the antenna (2) to be tested to a first working condition, and measuring the actual rotation angle of the antenna (2) to be tested under the first working condition respectively by means of a theodolite and an inclinometer (3); comparing the actual rotation angle of the antenna (2) to be tested under the first working condition measured by the theodolite with the actual rotation angle of the antenna (2) to be tested under the first working condition measured by the inclinometer (3); if the consistency of the measurement results of the theodolite and the inclinometer (3) is not greater than a set value, executing step 22; Step 22, controlling the antenna to be tested (2) to a second working condition, and measuring the actual rotation angle of the antenna to be tested (2) under the second working condition respectively by means of the theodolite and the inclinometer (3); comparing the actual rotation angle of the antenna to be tested (2) under the second working condition measured by the theodolite with the actual rotation angle of the antenna to be tested (2) under the second working condition measured by the inclinometer (3); if the consistency of the measurement results of the theodolite and the inclinometer (3) is not greater than a set value, executing step 23; Step 23, controlling the antenna (2) to be tested to a third working condition, and measuring the actual rotation angle of the antenna (2) to be tested under the third working condition respectively by means of the theodolite and the inclinometer (3); comparing the actual rotation angle of the antenna (2) to be tested under the third working condition measured by the theodolite with the actual rotation angle of the antenna (2) to be tested under the third working condition measured by the inclinometer (3); if the consistency of the measurement results of the theodolite and the inclinometer (3) is not greater than the set value, executing step 24; Step 24, controlling the antenna (2) to be tested to a fourth working condition, measuring the actual rotation angle of the antenna (2) to be tested under the fourth working condition respectively by means of the theodolite and the inclinometer (3); comparing the actual rotation angle of the antenna (2) to be tested under the fourth working condition measured by the theodolite with the actual rotation angle of the antenna (2) to be tested under the fourth working condition measured by the inclinometer (3); if the consistency of the measurement results of the theodolite and the inclinometer (3) is not greater than the set value, the calibration verification of the antenna autonomous tracking pointing accuracy measurement system is completed.

5. The method for testing the autonomous tracking and pointing accuracy of a satellite-borne antenna according to claim 4, characterized in that: The first working condition refers to a working condition where the azimuth axis (21) points at an angle of 0°; The second working condition includes working conditions where the azimuth axis (21) points at angles of ±30°, ±60° and ±90°; The third working condition refers to a working condition in which the pitch axis (22) is pointing at an angle of 0°; The fourth working condition includes working conditions where the pointing angles of the pitch axis (22) are ±30°, ±60° and ±90°.

6. The method for testing the autonomous tracking and pointing accuracy of a satellite-borne antenna according to claim 4, characterized in that: The set value is 0.02°.

7. The method for testing the autonomous tracking and pointing accuracy of a satellite-borne antenna according to claim 1, characterized in that: Based on the antenna autonomous tracking pointing accuracy measurement system that has completed calibration and verification, the pointing accuracy of the antenna (2) under test during the autonomous tracking process is tested and verified, including: Based on the antenna autonomous tracking pointing accuracy measurement system that has completed calibration verification, the pointing accuracy of the antenna to be tested (2) under working conditions A and B is tested and verified; After completing the pointing accuracy test and verification of the antenna to be tested (2) under working conditions A and B, a rotation instruction carrying a specified pointing angle is sent to the antenna to be tested (2) through the integrated interface unit (4), simulating the autonomous tracking working mode of the antenna to be tested (2); In the simulated autonomous tracking working mode, each time the antenna to be tested (2) completes rotation according to the designated pointing angle indicated by the rotation instruction, the actual rotation angle of the antenna to be tested (2) is measured by the inclinometer (3), and the actual rotation angle measured by the inclinometer (3) is compared with the theoretical designated pointing angle; based on the comparison result, the pointing accuracy test verification result of the autonomous tracking process of the antenna to be tested (2) is given.

8. The method for testing the autonomous tracking and pointing accuracy of a satellite-borne antenna according to claim 7, characterized in that: Working condition A is: the azimuth axis (21) and the pitch axis (22) rotate simultaneously; the azimuth axis (21) rotates clockwise, the rotation angle range is -90° to +90°, and the rotation angle is 1° each time; the pitch axis (22) rotates clockwise first and then counterclockwise, the rotation angle range is 0° to +90°, +90° to 0°, and the rotation angle is 1° each time; Working condition B is: the azimuth axis (21) and the pitch axis (22) rotate simultaneously; the azimuth axis (21) rotates counterclockwise, the rotation angle range is +90° to -90°, and the rotation angle is 1° each time; the pitch axis (22) rotates counterclockwise first and then clockwise, the rotation angle range is +90° to 0°, 0° to +90°, and the rotation angle is 1° each time.

9. The method for testing the autonomous tracking and pointing accuracy of a satellite-borne antenna according to claim 7, characterized in that: When testing and verifying the pointing accuracy of the antenna (2) under working conditions A and B: Both working conditions A and B were measured twice, with the pointing accuracy of one axis measured each time; After the measurement is completed, the maximum value of the measurement data obtained by the inclinometer (3) is compared with the technical index of the pointing accuracy of the antenna to be measured (2); if the maximum value of the measurement data obtained by the inclinometer (3) meets the technical index of the pointing accuracy of the antenna to be measured (2), a rotation instruction carrying a specified pointing angle is sent to the antenna to be measured (2) through the integrated interface unit (4), so as to simulate the autonomous tracking working mode of the antenna to be measured (2).

10. The method for testing the autonomous tracking and pointing accuracy of a satellite-borne antenna according to claim 7, characterized in that: In the simulated autonomous tracking working mode: the test is repeated twice; finally, the comparison results of the azimuth axis (21) and the pitch axis (22) are integrated to provide the pointing accuracy test verification result of the autonomous tracking process of the antenna (2) to be tested.

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