Overhead satellite continuous tracking system

Abstract

The utility model discloses an overhead satellite continuous tracking system, and belongs to the technical field of satellite communication. The antenna comprises a box body, a pitch angle adjusting assembly rotatably arranged at the top of the box body, a feed source assembly arranged on the pitch angle adjusting assembly, an antenna surface arranged on the feed source assembly, an azimuth angle adjusting assembly arranged at the bottom of the box body, and at least three groups of telescopic supporting legs arranged around the bottom of the azimuth angle adjusting assembly. The rotation angle of the antenna surface on the box body along with the pitch angle adjusting assembly is 0-90 degrees; when the satellite passes through the top, the adjusting end point moment of the telescopic supporting leg is consistent with the adjusting end point moment of the azimuth angle adjusting assembly. According to the utility model, the inclination angle of the parabolic antenna is changed by changing the length of the supporting legs, and the azimuth angle of the parabolic antenna is changed by combining the azimuth adjusting assembly, so that the continuous tracking of the parabolic antenna aiming at a top-crossing satellite is realized, the communication continuity in the satellite top-crossing process is ensured, and the requirement of uninterrupted and continuous work of satellite signals and data is met.

Description

Technical Field

[0001] The utility model relates to the technical field of satellite communications, in particular to an overhead satellite continuous tracking system. Background Art

[0002] The main strength of future satellite communications lies in low-orbit communications. Ships far from land must be equipped with low-orbit satellite communication terminals. Ground terminals tracking low-orbit satellites face major challenges such as no beacons, fast transit, and frequent switching, which requires key technology research such as terminal rapid capture, tracking, and satellite overhead environment.

[0003] For communication satellites, especially low-orbit communication satellites, low-angle satellite capture and tracking and the satellite's overhead motion relative to the antenna are inevitable.

[0004] The following methods are usually used in the prior art to solve the problem of overhead tracking: using an XY turntable, an AEC mount or ACE mount with a third axis added to the AE mount, program overhead tracking, and tilting the azimuth axis of the antenna column. These four solutions are basically proposed for antennas that are installed stationarily on the ground. The XY turntable that can track overhead in the ground station antenna has a low-angle tracking blind spot in pitch, and the AE mount without a low-elevation blind spot has an overhead tracking blind spot. They cannot be simply copied and used on ships. Moreover, the above-mentioned antenna mount turntables cannot be simply integrated. The structure must meet the requirements of the motion range and speed, and have a suitable control system to meet the needs of the use environment. Utility Model Content

[0005] The utility model aims to provide an overhead satellite continuous tracking system to solve the problem of blind spots when the existing ground terminal continuously tracks non-synchronous satellites.

[0006] The technical solution of the utility model to solve the above technical problems is as follows:

[0007] A system for continuously tracking overhead satellites comprises: a box, a pitch angle adjustment component rotatably arranged on the top of the box, a feed component arranged on the pitch angle adjustment component, an antenna surface arranged on the feed component, an azimuth angle adjustment component arranged at the bottom of the box, and at least three groups of telescopic support legs arranged around the bottom of the azimuth angle adjustment component; the rotation angle of the antenna surface on the box along with the pitch angle adjustment component is 0° to 90°; when the satellite passes overhead, the adjustment end point moment of the telescopic support legs is consistent with the adjustment end point moment of the azimuth angle adjustment component.

[0008] Furthermore, the number of the telescopic support legs is 3, and the box includes a corresponding front side and a rear side, wherein two groups of telescopic support legs are close to the front side and the other group is close to the rear side; or, two groups of telescopic support legs are close to the rear side and the other group is close to the front side.

[0009] Furthermore, a pitch angle adjustment storage bin is provided at the top of the box body near the front side, and the pitch angle adjustment storage bin extends to the top and the front side of the box body.

[0010] Furthermore, the pitch angle adjustment component is rotatably arranged in the pitch angle adjustment storage bin.

[0011] Furthermore, the feed assembly comprises a sub-reflector and a feed support rod, and two ends of the feed support rod are respectively connected to the sub-reflector and the pitch angle adjustment assembly.

[0012] Furthermore, the antenna surface includes a central disk and a main reflection surface surrounding the central disk, and the central disk is arranged on the feed support rod.

[0013] Furthermore, the second angle adjustment value of the above-mentioned azimuth adjustment component is 0.1-0.8 times the first angle adjustment value. The first angle adjustment value is the angle adjustment value required for the azimuth adjustment component to track overhead satellites when the telescopic support legs are not adjusted. The second angle adjustment value is the angle value changed by the azimuth adjustment component when the telescopic support legs are adjusted when tracking overhead satellites.

[0014] Furthermore, the second angle adjustment value of the azimuth angle adjustment component is 0.2-0.6 times the first angle adjustment value.

[0015] Furthermore, the second angle adjustment value of the azimuth angle adjustment component is 0.2-0.5 times the first angle adjustment value.

[0016] Furthermore, a receiving groove for receiving the telescopic supporting legs is provided at the bottom of the azimuth adjustment assembly.

[0017] The utility model has the following beneficial effects:

[0018] (1) The housing of the portable terminal is limited by the adjustable range of the pitch angle adjustment component (0° to 90°). When a satellite passes overhead, the azimuth angle adjustment component is required to rotate the housing to a certain angle, even 180°, to continue tracking the satellite. During the period of rotation of the azimuth angle adjustment component, the parabolic antenna is not aligned with the satellite, resulting in interruption of communication during this period. The utility model changes the inclination angle of the parabolic antenna by changing the length of the supporting legs, and at the same time changes the azimuth angle of the parabolic antenna in combination with the azimuth angle adjustment component, thereby achieving continuous tracking of the parabolic antenna aligned with the satellite passing overhead, ensuring the continuity of communication during the satellite passing overhead, and meeting the requirements of uninterrupted and continuous operation of satellite signals and data.

[0019] (2) The telescopic support legs of the utility model can be stored in the receiving groove of the box body. When the placement position is flat and does not need to be telescoped, they can be directly stored in the receiving groove. When the placement position is uneven or needs to be telescoped, they can be taken out of the receiving groove. This not only expands the applicable scenarios of the portable terminal, but also does not require additional settings and carrying brackets, thereby improving the compactness of the portable terminal and facilitating the carrying of the portable terminal.

[0020] (3) The utility model can realize a continuous tracking antenna system without an overhead "blind spot" without increasing additional hardware costs, and the control process is simple, thus solving the problem of "overhead" continuous tracking in the antenna working airspace. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 Schematic diagram of the structure of the overhead satellite continuous tracking system of Example 1;

[0022] Figure 2 This is a schematic diagram of the connection structure between the feed assembly and the antenna surface of Example 1;

[0023] Figure 3 Schematic diagram of the method for continuously tracking an overhead satellite according to Embodiment 3;

[0024] Figure 4 Schematic diagram of the method for continuous tracking of overhead satellites in Example 4.

[0025] In the figure: 1-box; 11-front side; 12-rear side; 13-pitch angle adjustment storage compartment; 2-pitch angle adjustment assembly; 3-feed assembly; 4-antenna surface; 5-azimuth angle adjustment assembly; 6-telescopic support leg. DETAILED DESCRIPTION

[0026] The principles and features of the present invention are described below in conjunction with the accompanying drawings. The examples given are only used to explain the present invention and are not used to limit the scope of the present invention.

[0027] Embodiment 1:

[0028] Please refer to Figure 1 and Figure 2 This embodiment provides a system for continuously tracking overhead satellites, which includes: a box 1, a pitch angle adjustment component 2 rotatably arranged on the top of the box 1, a feed component 3 arranged on the pitch angle adjustment component 2, an antenna surface 4 arranged on the feed component 3, an azimuth angle adjustment component 5 arranged at the bottom of the box 1, and at least three groups of telescopic support legs 6 arranged around the bottom of the azimuth angle adjustment component 5. The box 1 is the box 1 of the portable terminal, and other components of the portable terminal, such as a power supply, an interface, etc., are not described in detail here.

[0029] The box body 1 includes a corresponding front side 11 and a rear side 12. The front side 11 is used to carry the box body 1, for example, by providing a shoulder strap on the box body 1, so that the box body 1 can be directly carried on the back. A pitch angle adjustment storage bin 13 is provided at the top of the box body 1 near the front side 11, and the pitch angle adjustment storage bin 13 extends to the top of the box body 1 and the front side 11. The pitch angle adjustment component 2 is rotatably arranged in the pitch angle adjustment storage bin 13, and the adjustment direction is perpendicular to the front side 11 and the rear side 12. The pitch angle adjustment component 2 can select any structure that can achieve pitch change, for example, it can select a method of combining a motor with a rotating shaft, or a method of combining a motor and a rotating shaft with a gear set, etc.

[0030] The feed assembly 3 includes a sub-reflector and a feed support rod, and the two ends of the feed support rod are respectively connected to the sub-reflector and the pitch angle adjustment assembly 2. The antenna surface 4 includes a center disk and a main reflection surface surrounding the center disk, and the center disk is arranged on the feed support rod. The antenna surface 4 and the feed assembly 3 rotate with the rotation of the pitch angle adjustment assembly 2, and the rotation range is 0° to 90°. In this embodiment, when the feed assembly 3 is located in the width direction of the box 1, the rotation angle is 0° at this time, and when the feed assembly 3 is located in the height direction of the box 1, the rotation angle is 90° at this time.

[0031] The azimuth adjustment component 5 is used to support the box body 1 and realize the azimuth adjustment of the box body 1, that is, the box body 1 rotates around the azimuth adjustment component 5. When the azimuth of the antenna needs to be changed, the azimuth adjustment component 5 drives the box body 1 to rotate as a whole, so as to realize the change of the azimuth of the antenna located on the box body 1. The angle adjustment range of the azimuth adjustment component 5 is 0-360°. At the same time, the second angle adjustment value of the azimuth adjustment component 5 is 0.1-0.8 times of the first angle adjustment value, preferably 0.2-0.6 times or 0.2-0.5 times. The first angle adjustment value is the angle adjustment value required for the azimuth adjustment component 5 to track the overhead satellite when the telescopic support leg 6 is not adjusted, and the second angle adjustment value is the angle value changed by the azimuth adjustment component 5 when the telescopic support leg 6 is adjusted when tracking the overhead satellite. The azimuth adjustment component 5 can select any structure that can change the azimuth, for example, it can be selected as a motor, whose output shaft drives the box body 1 to rotate, or a motor combined with a gear set can be selected.

[0032] In this embodiment, the number of telescopic support legs 6 is 3, and the three groups of telescopic support legs 6 are arranged in a triangle around the bottom of the azimuth adjustment component 5, and the telescopic support legs 6 extend to the outside of the box 1, which can not only improve the support stability of the box 1, but also facilitate adjustment. At the same time, the telescopic support legs 6 are also hinged with the azimuth adjustment component 5. Specifically, two groups of telescopic support legs 6 are close to the front side 11, and the other group is close to the rear side 12. Obviously, the three groups of telescopic support legs 6 are preferably arranged in an acute triangle, which can improve the support stability. At the same time, the three groups of telescopic support legs 6 can be arranged at any position at the bottom of the azimuth adjustment component 5 (provided that the triangular arrangement is satisfied), for example, two groups of telescopic support legs 6 are close to the rear side 12, and the other group is close to the front side 11. The arrangement of the three groups of telescopic support legs 6 facilitates the continuous tracking of overhead satellites.

[0033] In other embodiments of the present invention, the number of the telescopic supporting legs 6 may be greater than 3, and all the telescopic supporting legs 6 are arranged at the bottom of the azimuth adjustment assembly 5 in a surrounding manner.

[0034] The telescopic support leg 6 can be manual, electric, hydraulic, etc. The specific structure belongs to the prior art and will not be described here.

[0035] In order to facilitate the carrying of the portable terminal, in the present embodiment, a receiving groove for accommodating the telescopic support leg 6 is provided at the bottom of the azimuth adjustment component 5. The telescopic support leg 6 can be accommodated in the receiving groove or taken out from the receiving groove as needed to support and adjust the entire portable terminal, thereby expanding the applicable scenarios of the portable terminal.

[0036] When a satellite passes overhead, the parabolic antenna pitch angle adjustment component 2 is limited by the adjustable angle range and cannot be aligned with the satellite in time. The azimuth angle adjustment component 5 needs to rotate the box 1 to a certain angle (sometimes even 180°) to track the satellite. During the period when the azimuth angle adjustment component 5 completes the angle rotation, the antenna surface 4 is not aligned with the satellite, resulting in interrupted communication during this period. To solve this problem, this embodiment uses the method of adjusting the length of the telescopic support leg 6 to cooperate with the azimuth angle adjustment component 5 and the pitch angle adjustment component 2 to ensure that the antenna surface 4 is continuously aligned with the satellite when the satellite passes overhead, thereby achieving continuous and uninterrupted satellite communication.

[0037] In this embodiment, the adjustment end point moment of the corresponding telescopic support leg 6 is consistent with the adjustment end point moment of the azimuth adjustment component 5. There are many ways to achieve the consistency between the adjustment end point moment of the azimuth adjustment component 5 and the adjustment end point moment of the corresponding telescopic support leg 6. For example, the received satellite signal strength is used as a criterion, the adjustment rate of the telescopic support leg 6 and the adjustment step size of the azimuth adjustment component 5 are set in the program, and when the pitch adjustment component 2 does not need to maintain 90°, it can be considered that the satellite has passed the top, and this moment is taken as the end point.

[0038] Specifically, when a satellite passes overhead, the corresponding telescopic support legs 6 are adjusted to tilt the entire box 1 in the direction in which the satellite will move. Combined with the angle adjustment of the pitch angle adjustment component 2 and the azimuth angle adjustment component 5, the antenna surface 4 can continuously track the satellite signal when the satellite passes overhead.

[0039] Embodiment 2:

[0040] When a satellite passes overhead, the parabolic antenna pitch angle adjustment component 2 is limited by the adjustable angle range and cannot be aligned with the satellite in time. The azimuth angle adjustment component 5 needs to rotate the box 1 to a certain angle (sometimes even 180°) to track the satellite. During the period when the azimuth angle adjustment component 5 completes the angle rotation, the antenna surface 4 is not aligned with the satellite, resulting in interrupted communication during this period. To solve this problem, this embodiment uses the method of adjusting the length of the telescopic support leg 6 to cooperate with the azimuth angle adjustment component 5 and the pitch angle adjustment component 2 to ensure that the antenna surface 4 is continuously aligned with the satellite when the satellite passes overhead, thereby achieving continuous and uninterrupted satellite communication.

[0041] This embodiment provides a method for continuously tracking overhead satellites based on the overhead satellite continuous tracking system of Embodiment 1, comprising the following steps:

[0042] S1: When the placement position is reached, the length of each telescopic support leg 6 is adjusted to ensure that the box 1 is placed firmly and in a horizontal position;

[0043] S2: Control the azimuth angle adjustment component 5 and the elevation angle adjustment component 2 to make the antenna surface 4 face the satellite and make the antenna surface 4 move with the movement of the satellite;

[0044] S3: When the satellite passes overhead, the corresponding telescopic support legs 6 are adjusted to tilt the entire box 1 in the direction of satellite movement. While adjusting, the azimuth angle adjustment component 5 is started to rotate and tilt the box 1. During this process, the pitch angle adjustment component 2 is kept working so that the antenna surface 4 moves with the movement of the satellite, thereby achieving continuous tracking of the satellite passing overhead.

[0045] Among them, in step S3, the adjustment end point moment of the corresponding telescopic support leg 6 is consistent with the adjustment end point moment of the azimuth angle adjustment component 5. At this time, due to the cooperation of the telescopic support leg 6, the second angle adjustment value of the azimuth angle adjustment component 5 will be much smaller than the first angle adjustment value of the azimuth angle adjustment component 5 when the telescopic support leg 6 is not cooperated. It can be specifically determined according to the telescopic amount of the telescopic support leg 6 in the placement position. Preferably, the second angle adjustment value is 0.1 to 0.8 times, 0.2 to 0.6 times, or 0.2 to 0.5 times the first angle adjustment value. By taking the above measures, the continuous tracking of the overhead satellite by the antenna surface 4 can be ensured, and continuous communication can be ensured without interruption.

[0046] Embodiment 3:

[0047] When a satellite passes overhead, the parabolic antenna pitch angle adjustment component 2 is limited by the adjustable angle range and cannot be aligned with the satellite in time. The azimuth angle adjustment component 5 needs to rotate the box 1 to a certain angle (sometimes even 180°) to track the satellite. During the period when the azimuth angle adjustment component 5 completes the angle rotation, the antenna surface 4 is not aligned with the satellite, resulting in interrupted communication during this period. To solve this problem, this embodiment uses the method of adjusting the length of the telescopic support leg 6 to cooperate with the azimuth angle adjustment component 5 and the pitch angle adjustment component 2 to ensure that the antenna surface 4 is continuously aligned with the satellite when the satellite passes overhead, thereby achieving continuous and uninterrupted satellite communication.

[0048] Please refer to Figure 3 This embodiment provides a method for continuously tracking an overhead satellite based on the overhead satellite continuous tracking system of embodiment 1, comprising the following steps:

[0049] S1: When the placement position is reached, the length of each telescopic support leg 6 is adjusted to ensure that the box 1 is placed firmly and in a horizontal position; at this time, the three upper end points of the three groups of telescopic support legs 6 are A, B, and C, respectively, forming △ABC, and the three lower end points of the three groups of telescopic support legs 6 are D, E, and F, respectively, forming △DEF. are respectively the projection lengths of the three groups of telescopic supporting legs 6 on plane ABC before adjustment;

[0050] S2: Control the azimuth angle adjustment component 5 and the elevation angle adjustment component 2 to make the antenna surface 4 face the satellite and make the antenna surface 4 move with the movement of the satellite;

[0051] S3: When the satellite passes overhead, and the direction of the satellite passing overhead is along the direction D→A (i.e., along the direction of the corresponding telescopic support leg 6), the length of the telescopic support leg 6 is adjusted, and the projection angle is changed from Shortened to The entire box 1 is tilted in the direction of satellite movement, with a tilt angle of θ1, where θ1 is the angle change between △ABC and triangle △DEF. The azimuth angle adjustment component 5 is started while adjusting, so that the box 1 rotates and tilts at the same time. During this process, the pitch angle adjustment component 2 is kept working so that the antenna surface 4 moves with the movement of the satellite, thereby achieving continuous tracking of overhead satellites.

[0052] Among them, in step S3, the adjustment end point moment of the corresponding telescopic support leg 6 is consistent with the adjustment end point moment of the azimuth angle adjustment component 5. At this time, due to the cooperation of the telescopic support leg 6, the second angle adjustment value of the azimuth angle adjustment component 5 will be much smaller than the first angle adjustment value of the azimuth angle adjustment component 5 when the telescopic support leg 6 is not cooperated. It can be specifically determined according to the telescopic amount of the telescopic support leg 6 in the placement position. Preferably, the second angle adjustment value is 0.1 to 0.8 times, 0.2 to 0.6 times, or 0.2 to 0.5 times the first angle adjustment value. By taking the above measures, the continuous tracking of the overhead satellite by the parabolic antenna can be ensured, and continuous communication can be ensured without interruption.

[0053] When the number of telescopic support legs 6 is greater than 3 groups, the corresponding telescopic support legs 6 are adjusted to ensure that the entire box 1 is tilted in the direction of satellite movement.

[0054] Embodiment 4:

[0055] When a satellite passes overhead, the parabolic antenna pitch angle adjustment component 2 is limited by the adjustable angle range and cannot be aligned with the satellite in time. The azimuth angle adjustment component 5 needs to rotate the box 1 to a certain angle (sometimes even 180°) to track the satellite. During the period when the azimuth angle adjustment component 5 completes the angle rotation, the antenna surface 4 is not aligned with the satellite, resulting in interrupted communication during this period. To solve this problem, this embodiment uses the method of adjusting the length of the telescopic support leg 6 to cooperate with the azimuth angle adjustment component 5 and the pitch angle adjustment component 2 to ensure that the antenna surface 4 is continuously aligned with the satellite when the satellite passes overhead, thereby achieving continuous and uninterrupted satellite communication.

[0056] Please refer to Figure 4 This embodiment provides a method for continuously tracking an overhead satellite based on the overhead satellite continuous tracking system of embodiment 1, comprising the following steps:

[0057] S1: When the placement position is reached, the length of each telescopic support leg 6 is adjusted to ensure that the box 1 is placed firmly and in a horizontal position; at this time, the three upper end points of the three groups of telescopic support legs 6 are I, J, and K, respectively, forming △IJK, and the three lower end points of the three groups of telescopic support legs 6 are L, M, and N, respectively, forming △LMN. They are respectively the projection lengths of the three sets of telescopic supporting legs 6 on the plane IJK before adjustment;

[0058] S2: Control the azimuth angle adjustment component 5 and the elevation angle adjustment component 2 to make the antenna surface 4 face the satellite and make the antenna surface 4 move with the movement of the satellite;

[0059] S3: When the satellite passes overhead, and the direction of the satellite passing overhead is between IJ and KN (i.e., along the direction between the two corresponding sets of telescopic support legs 6), the lengths of the two corresponding sets of telescopic support legs 6 are adjusted, and the projection angle is changed from Shortened to Shortened to The entire box 1 is tilted in the direction of satellite movement, with a tilt angle of θ2, where θ2 is the angle change between △IJK and △LMN. The azimuth angle adjustment component 5 is started while adjusting, so that the box 1 rotates and tilts at the same time. During this process, the pitch angle adjustment component 2 is kept working so that the antenna surface 4 moves with the movement of the satellite, thereby achieving continuous tracking of overhead satellites.

[0060] Among them, in step S3, the adjustment end point moment of the corresponding telescopic support leg 6 is consistent with the adjustment end point moment of the azimuth angle adjustment component 5. At this time, due to the cooperation of the telescopic support leg 6, the second angle adjustment value of the azimuth angle adjustment component 5 will be much smaller than the first angle adjustment value of the azimuth angle adjustment component 5 when the telescopic support leg 6 is not cooperated. It can be specifically determined according to the telescopic amount of the telescopic support leg 6 in the placement position. Preferably, the second angle adjustment value is 0.1 to 0.8 times, 0.2 to 0.6 times, or 0.2 to 0.5 times the first angle adjustment value. By taking the above measures, the continuous tracking of the overhead satellite by the parabolic antenna can be ensured, and continuous communication can be ensured without interruption.

[0061] When the number of telescopic support legs 6 is greater than 3 groups, the corresponding telescopic support legs 6 are adjusted to ensure that the entire box 1 is tilted in the direction of satellite movement.

[0062] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A continuous tracking system for overhead satellites, characterized in that: include: A box (1), a pitch angle adjustment component (2) rotatably arranged on the top of the box (1), a feed component (3) arranged on the pitch angle adjustment component (2), an antenna surface (4) arranged on the feed component (3), an azimuth angle adjustment component (5) arranged at the bottom of the box (1), and at least three groups of telescopic support legs (6) arranged around the bottom of the azimuth angle adjustment component (5); the antenna surface (4) rotates on the box (1) at an angle of 0° to 90° along with the pitch angle adjustment component (2); when a satellite passes overhead, the adjustment end point moment of the telescopic support legs (6) coincides with the adjustment end point moment of the azimuth angle adjustment component (5).

2. The overhead satellite continuous tracking system according to claim 1, characterized in that: The number of the telescopic supporting legs (6) is 3, and the box body (1) comprises a corresponding front side (11) and a rear side (12), wherein two groups of the telescopic supporting legs (6) are close to the front side (11), and the other group is close to the rear side (12); or, two groups of the telescopic supporting legs (6) are close to the rear side (12), and the other group is close to the front side (11).

3. The overhead satellite continuous tracking system according to claim 2, characterized in that: The box body (1) is provided with a pitch angle adjustment storage bin (13) at the top near the front side (11), and the pitch angle adjustment storage bin (13) extends to the top of the box body (1) and the front side (11).

4. The overhead satellite continuous tracking system according to claim 3, characterized in that: The pitch angle adjustment component (2) is rotatably arranged in the pitch angle adjustment storage bin (13).

5. The overhead satellite continuous tracking system according to claim 1, characterized in that: The feed assembly (3) comprises a sub-reflector and a feed support rod, and two ends of the feed support rod are respectively connected to the sub-reflector and the pitch angle adjustment assembly (2).

6. The overhead satellite continuous tracking system according to claim 5, characterized in that: The antenna surface (4) comprises a central disk and a main reflection surface surrounding the central disk, and the central disk is arranged on the feed source support rod.

7. The overhead satellite continuous tracking system according to any one of claims 1 to 6, characterized in that: The second angle adjustment value of the azimuth angle adjustment component (5) is 0.1-0.8 times the first angle adjustment value, the first angle adjustment value being the angle adjustment value required for the azimuth angle adjustment component (5) to track an overhead satellite when the telescopic support leg (6) is not adjusted, and the second angle adjustment value being the angle value changed by the azimuth angle adjustment component (5) when the telescopic support leg (6) is adjusted when tracking an overhead satellite.

8. The overhead satellite continuous tracking system according to claim 7, characterized in that: The second angle adjustment value of the azimuth angle adjustment component (5) is 0.2-0.6 times the first angle adjustment value.

9. The overhead satellite continuous tracking system according to claim 7, characterized in that: The second angle adjustment value of the azimuth angle adjustment component (5) is 0.2-0.5 times the first angle adjustment value.

10. The overhead satellite continuous tracking system according to claim 7, characterized in that: The bottom of the azimuth angle adjustment component (5) is provided with a receiving groove for receiving the telescopic supporting leg (6).

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