CN117937092B - Over-top satellite continuous tracking system and over-top satellite continuous tracking method - Google Patents
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Abstract
The invention discloses a continuous tracking system and a continuous tracking method for an overhead satellite, belonging to the technical field of satellite communication, comprising the following steps: the device comprises a box body, a pitch angle adjusting assembly, a feed source assembly, an antenna surface, an azimuth angle adjusting assembly and at least three groups of telescopic supporting legs, wherein the pitch angle adjusting assembly is rotatably arranged at the top of the box body; the rotation angle of the antenna surface along with the pitch angle adjusting component on the box body is 0-90 degrees; the telescopic support legs extend to the outer side of the box body. According to the invention, the inclination angle of the parabolic antenna is changed by changing the length of the supporting leg, and the azimuth angle of the parabolic antenna is changed by combining the azimuth angle adjusting component, so that the continuous tracking of the parabolic antenna aiming at the overhead satellite is realized, the communication continuity in the overhead satellite process is ensured, and the requirement of uninterrupted continuous operation of satellite signals and data is realized.
Description
Technical Field
The invention relates to the technical field of satellite communication, in particular to an overhead satellite continuous tracking system and an overhead satellite continuous tracking method.
Background
The main force of future satellite communication is low orbit communication, and ships far away from land must be equipped with low orbit satellite communication terminals. The ground terminal tracking low orbit satellite faces the main challenges of no beacon, fast transit, frequent switching and the like, and the key technical researches of the terminal rapid capturing, tracking, satellite transit environment and the like are required.
For communication satellites, particularly low-orbit communication satellites, there is inevitably a phenomenon in which satellites at low angles acquire tracking and the satellites move excessively with respect to the antenna.
In the prior art, the following methods are generally adopted to solve the problem of over-top tracking: the X-Y turntable, the A-E seat frame and the A-E-C seat frame or the A-C-E seat frame of a third shaft are used, and the azimuth axis of the antenna upright post is inclined after the procedure is carried out. The four schemes are basically provided aiming at antennas which are installed and used on the ground in a static way, an X-Y type turntable which can be used for tracking through the top in the ground station antenna is provided with a pitching low-angle tracking blind area, an A-E seat frame without a low-elevation angle blind area is provided with a top tracking blind area, and the antenna can not be simply moved to a ship for use. In addition, the antenna mount turntable cannot be simply integrated, and the requirements of reaching the movement range and the movement speed are required to be structurally met, and a set of applicable control system can be provided to meet the requirements of the use environment.
Disclosure of Invention
The invention aims to provide an overhead satellite continuous tracking system and an overhead satellite continuous tracking method, which are used for solving the problem that the existing ground terminal has dead angles when continuously tracking a non-synchronous satellite.
The technical scheme for solving the technical problems is as follows:
An overhead satellite continuous tracking system comprising: the device comprises a box body, a pitch angle adjusting assembly, a feed source assembly, an antenna surface, an azimuth angle adjusting assembly and at least three groups of telescopic supporting legs, wherein the pitch angle adjusting assembly is rotatably arranged at the top of the box body; the rotation angle of the antenna surface along with the pitch angle adjusting component on the box body is 0-90 degrees; the telescopic supporting legs extend to the outer side of the box body;
when the satellite is over-jacked, the corresponding telescopic supporting legs are adjusted, so that the whole box body is inclined towards the moving direction of the satellite, and the antenna continuously tracks satellite signals when the satellite is over-jacked by combining the angle adjustment of the pitch angle adjusting assembly and the azimuth angle adjusting assembly.
Further, the box comprises a front side and a rear side which correspond to each other, a pitch angle adjusting storage bin is arranged at the top of the box close to the front side, the pitch angle adjusting storage bin extends to the top and the front side of the box, and the pitch angle adjusting assembly is rotatably arranged in the pitch angle adjusting storage bin.
Further, the number of the telescopic support legs is 3, wherein two groups of telescopic support legs are close to the front side, and the other group of telescopic support legs are close to the rear side.
Further, the feed source assembly comprises a secondary reflector and a feed source supporting rod, and two ends of the feed source supporting rod are respectively connected with the secondary reflector and the pitch angle adjusting assembly.
Further, the antenna surface comprises a center plate and a main reflecting surface surrounding the center plate, and the center plate is arranged on the feed source supporting rod.
Further, when the satellite passes the top, the adjusting end point moment of the corresponding telescopic supporting leg is consistent with the adjusting end point moment of the azimuth angle adjusting assembly.
Further, the second angle adjustment value of the azimuth angle adjustment assembly is 0.1-0.8 times of the first angle adjustment value, the first angle adjustment value is an angle adjustment value required by the azimuth angle adjustment assembly to track the overhead satellite when the telescopic supporting leg is not adjusted, and the second angle adjustment value is an angle value changed by the azimuth angle adjustment assembly under the condition that the telescopic supporting leg is adjusted when the overhead satellite is tracked.
The continuous tracking method of the overhead satellite based on the continuous tracking system of the overhead satellite is characterized by comprising the following steps:
s1: when the box body reaches the placement position, the length of each telescopic supporting leg is adjusted, the box body is ensured to be placed stably, and the box body is ensured to be in a horizontal position;
S2: controlling the azimuth angle adjusting assembly 5 and the pitch angle adjusting assembly 2 so that the antenna faces the satellite and moves along with the movement of the satellite;
s3: when the satellite passes the top, the corresponding telescopic supporting legs are adjusted, so that the whole box body inclines towards the moving direction of the satellite, the azimuth angle adjusting assembly is started while adjusting, the box body inclines while rotating, and in the process, the pitch angle adjusting assembly is kept to work continuously, the antenna surface moves along with the movement of the satellite, and continuous tracking of the satellite passing the top is realized.
Further, in the step S3, the adjustment end point time of the corresponding telescopic support leg is consistent with the adjustment end point time of the azimuth angle adjustment assembly.
Further, in the step S3, the second angle adjustment value of the azimuth angle adjustment assembly is 0.1-0.8 times the first angle adjustment value, and the first angle adjustment value is an angle adjustment value required by the azimuth angle adjustment assembly to track the overhead satellite when the telescopic supporting leg is not adjusted.
The invention has the following beneficial effects:
(1) The casing of the portable terminal is limited by the adjustable range (0 DEG to 90 DEG) of the pitch angle adjusting assembly, when the satellite is overtopped, the azimuth angle adjusting assembly is required to rotate the casing by a certain angle, even 180 DEG, so that the satellite can be continuously tracked, and during the period of rotation of the azimuth angle adjusting assembly, the parabolic antenna is not aligned with the satellite, so that communication is interrupted during the period of time. According to the invention, the inclination angle of the parabolic antenna is changed by changing the length of the supporting leg, and the azimuth angle of the parabolic antenna is changed by combining the azimuth angle adjusting component, so that the continuous tracking of the parabolic antenna aiming at the overhead satellite is realized, the communication continuity in the overhead satellite process is ensured, and the requirement of uninterrupted continuous operation of satellite signals and data is realized.
(2) The invention can realize continuous tracking antenna system without overhead dead zone without adding extra hardware cost, and has simple control flow, thus solving the problem of overhead continuous tracking of antenna working airspace.
Drawings
FIG. 1 is a schematic diagram of the overhead satellite continuous tracking system of embodiment 1;
fig. 2 is a schematic diagram of a connection structure between a feed assembly and an antenna face in embodiment 1;
FIG. 3 is a schematic diagram of an overhead satellite continuous tracking method of embodiment 3;
fig. 4 is a schematic diagram of an overhead satellite continuous tracking method of embodiment 4.
In the figure: 1-a box body; 11-front side; 12-rear side; 13-pitch angle adjusting storage bin; 2-pitch angle adjustment assembly; a 3-feed component; 4-antenna face; a 5-azimuth adjustment assembly; and 6-telescopic supporting legs.
Detailed Description
The principles and features of the present invention are described below with reference to the drawings, the examples are illustrated for the purpose of illustrating the invention and are not to be construed as limiting the scope of the invention.
Example 1:
Referring to fig. 1 and 2, the present embodiment provides an overhead satellite continuous tracking system, which includes: the device comprises a box body 1, a pitch angle adjusting component 2 arranged at the top of the box body 1 in a rotating mode, a feed source component 3 arranged on the pitch angle adjusting component 2, an antenna surface 4 arranged on the feed source component 3, an azimuth angle adjusting component 5 arranged at the bottom of the box body 1 and at least three groups of telescopic supporting legs 6 arranged at the bottom of the azimuth angle adjusting component 5 in a surrounding mode. The case 1 is a case 1 of the portable terminal, and other components of the portable terminal, such as a power supply, an interface, etc., are not described herein.
The case 1 includes a front side 11 and a rear side 12, where the front side 11 is used for carrying the case 1 on a back, for example, by providing a back strap on the case 1, and directly carrying the case 1 on a back. The top that box 1 is close to front side 11 is equipped with pitch angle and adjusts storage bin 13, and pitch angle adjusts storage bin 13 and extends to the top and the front side 11 of box 1. The pitch angle adjusting assembly 2 is rotatably arranged in the pitch angle adjusting storage bin 13, and the adjusting direction is vertical to the front side 11 and the rear side 12. The pitch angle adjustment assembly 2 may be selected from any configuration that allows for pitch variation, for example, a motor in combination with a shaft, a motor, a shaft in combination with a gear set, etc.
The feed source assembly 3 comprises a subreflector and a feed source supporting rod, and two ends of the feed source supporting rod are respectively connected with the subreflector and the pitch angle adjusting assembly 2. The antenna surface 4 comprises a central disc and a main reflecting surface surrounding the central disc, and the central disc is arranged on the feed support rod. The antenna surface 4 and the feed assembly 3 rotate along with the rotation of the pitch angle adjusting assembly 2, and the rotation range is 0-90 degrees. In this embodiment, the rotation angle is 0 ° when the feed assembly 3 is located in the width direction of the case 1, and is 90 ° when the feed assembly 3 is located in the height direction of the case 1.
The azimuth angle adjusting assembly 5 is used for supporting the case 1 and realizing azimuth angle adjustment of the case 1, i.e. the case 1 rotates around the azimuth angle adjusting assembly 5. When the azimuth angle of the antenna needs to be changed, the azimuth angle adjusting assembly 5 drives the box body 1 to integrally rotate, so that the change of the azimuth angle of the antenna on the box body 1 is realized, the angle adjusting range of the azimuth angle adjusting assembly 5 is 0-360 degrees, meanwhile, the second angle adjusting value of the azimuth angle adjusting assembly 5 is 0.1-0.8 times of the first angle adjusting value, the first angle adjusting value is the angle adjusting value required by the azimuth angle adjusting assembly 5 to track the overhead satellite when the telescopic supporting leg 6 is not adjusted, and the second angle adjusting value is the angle value changed by the azimuth angle adjusting assembly 5 under the condition that the telescopic supporting leg 6 is adjusted when the overhead satellite is tracked. The azimuth angle adjusting assembly 5 may be any structure capable of changing azimuth, for example, a motor, an output shaft of which drives the case 1 to rotate, or a mode of combining a motor with a gear set, etc.
In this embodiment, the quantity of flexible supporting leg 6 is 3, and 3 flexible supporting leg 6 of group are triangle-shaped around setting up in the bottom of azimuth angle adjusting part 5 to flexible supporting leg 6 extends to the outside of box 1, not only can improve the supporting stability to box 1, still is convenient for adjust, simultaneously, flexible supporting leg 6 still articulates with azimuth angle adjusting part 5. Specifically, two sets of telescopic support legs 6 are near the front side 11, and the other set is near the rear side 12, and it is obvious that 3 sets of telescopic support legs 6 are preferably arranged in an acute triangle manner, so as to improve the stability of the support, and at the same time, 3 sets of telescopic support legs 6 can be arranged at the bottom of the azimuth angle adjusting assembly 5 according to any position (provided that the triangle arrangement is satisfied). The arrangement of 3 groups of telescopic supporting legs 6 facilitates the adjustment of continuous tracking of overhead satellites.
In other embodiments of the invention, the number of telescopic support legs 6 may also be greater than 3, all telescopic support legs 6 being arranged in a surrounding manner at the bottom of the azimuth angle adjustment assembly 5.
The telescopic support leg 6 may be manual, electric, hydraulic, etc., and the specific structure thereof belongs to the prior art, and will not be described herein.
When the satellite is over-topped, the over-topped satellite cannot be aligned timely due to the limitation of the angle adjustable range of the parabolic antenna pitch angle adjusting assembly 2, and the azimuth angle adjusting assembly 5 is required to rotate the box body 1 by a certain angle (sometimes even by 180 degrees) so as to be possible to track the over-topped satellite. And during the time that the azimuth adjustment assembly 5 is completing the angular rotation, communication is interrupted during this time because the antenna face 4 is not aligned with the overhead satellite. In order to solve the problem, the embodiment adopts a mode of adjusting the length of the telescopic supporting legs 6 to be matched with the azimuth angle adjusting assembly 5 and the pitch angle adjusting assembly 2 to ensure that the antenna surface 4 is continuously aligned with the satellite when the satellite is overtravel, thereby realizing continuous uninterrupted satellite communication.
In the present embodiment, the adjustment end time of the corresponding telescopic support leg 6 is kept identical to the adjustment end time of the azimuth angle adjustment assembly 5. There are many ways to achieve that the adjustment end time of the azimuth angle adjusting component 5 is consistent with the adjustment end time of the corresponding telescopic supporting leg 6, for example, the received satellite signal strength is used as a criterion, the adjustment speed of the telescopic supporting leg 6 and the adjustment step length of the azimuth angle adjusting component 5 are set in a program, and when the pitch angle adjusting component 2 does not need to keep 90 degrees, the satellite can be considered to pass through the top, and the moment is used as the end time.
Specifically, when the satellite is over-jacked, the corresponding telescopic supporting legs 6 are adjusted, so that the whole box body 1 inclines towards the moving direction of the satellite, and the antenna surface 4 continuously tracks satellite signals when the satellite is over-jacked by combining the angle adjustment of the pitch angle adjustment assembly 2 and the azimuth angle adjustment assembly 5.
Example 2:
When the satellite is over-topped, the over-topped satellite cannot be aligned timely due to the limitation of the angle adjustable range of the parabolic antenna pitch angle adjusting assembly 2, and the azimuth angle adjusting assembly 5 is required to rotate the box body 1 by a certain angle (sometimes even by 180 degrees) so as to be possible to track the over-topped satellite. And during the time that the azimuth adjustment assembly 5 is completing the angular rotation, communication is interrupted during this time because the antenna face 4 is not aligned with the overhead satellite. In order to solve the problem, the embodiment adopts a mode of adjusting the length of the telescopic supporting legs 6 to be matched with the azimuth angle adjusting assembly 5 and the pitch angle adjusting assembly 2 to ensure that the antenna surface 4 is continuously aligned with the satellite when the satellite is overtravel, thereby realizing continuous uninterrupted satellite communication.
The embodiment provides an overhead satellite continuous tracking method based on the overhead satellite continuous tracking system of embodiment 1, which comprises the following steps:
s1: when the box body reaches the placement position, the length of each telescopic supporting leg 6 is adjusted, so that the box body 1 is ensured to be placed stably, and the box body 1 is ensured to be in a horizontal position;
s2: controlling the azimuth angle adjusting assembly 5 and the pitch angle adjusting assembly 2 to enable the antenna surface 4 to face the satellite, and enabling the antenna surface 4 to move along with the movement of the satellite;
s3: when the satellite is overturned, the corresponding telescopic supporting legs 6 are adjusted, so that the whole box body 1 inclines towards the moving direction of the satellite, the azimuth angle adjusting assembly 5 is started while adjusting, the box body 1 inclines while rotating, and in the process, the pitch angle adjusting assembly 2 is kept to work continuously, the antenna surface 4 moves along with the movement of the satellite, and continuous tracking of the overturned satellite is realized.
In step S3, the adjustment end point time of the corresponding telescopic support leg 6 is consistent with the adjustment end point time of the azimuth angle adjustment assembly 5. At this time, the second angle adjustment value of the azimuth angle adjustment assembly 5 is far smaller than the first angle adjustment value of the azimuth angle adjustment assembly 5 when the telescopic support leg 6 is not engaged due to the engagement of the telescopic support leg 6, and can be specifically determined according to the telescopic amount of the telescopic support leg 6 at the placement position, preferably, the second angle adjustment value is 0.1-0.8 times, or 0.2-0.6 times, or 0.2-0.5 times of the first angle adjustment value. By adopting the measures, the antenna surface 4 can ensure continuous tracking of the overhead satellite and continuous communication without interruption.
Example 3:
When the satellite is over-topped, the over-topped satellite cannot be aligned timely due to the limitation of the angle adjustable range of the parabolic antenna pitch angle adjusting assembly 2, and the azimuth angle adjusting assembly 5 is required to rotate the box body 1 by a certain angle (sometimes even by 180 degrees) so as to be possible to track the over-topped satellite. And during the time that the azimuth adjustment assembly 5 is completing the angular rotation, communication is interrupted during this time because the antenna face 4 is not aligned with the overhead satellite. In order to solve the problem, the embodiment adopts a mode of adjusting the length of the telescopic supporting legs 6 to be matched with the azimuth angle adjusting assembly 5 and the pitch angle adjusting assembly 2 to ensure that the antenna surface 4 is continuously aligned with the satellite when the satellite is overtravel, thereby realizing continuous uninterrupted satellite communication.
Referring to fig. 3, the present embodiment provides an overhead satellite continuous tracking method based on the overhead satellite continuous tracking system of embodiment 1, which includes the following steps:
S1: when the box body reaches the placement position, the length of each telescopic supporting leg 6 is adjusted, so that the box body 1 is ensured to be placed stably, and the box body 1 is ensured to be in a horizontal position; at this time, the three upper end points of the 3 groups of telescopic support legs 6 are A, B, C respectively to enclose DeltaABC, the three lower end points of the 3 groups of telescopic support legs 6 are D, E, F respectively to enclose DeltaDEF, 、、The projection lengths of the lengths of 3 groups of telescopic supporting legs 6 on a plane ABC before adjustment are respectively;
s2: controlling the azimuth angle adjusting assembly 5 and the pitch angle adjusting assembly 2 to enable the antenna surface 4 to face the satellite, and enabling the antenna surface 4 to move along with the movement of the satellite;
s3: when the satellite is over-jacked, and the satellite over-jacked direction is along the direction D-A (namely along the direction of the corresponding telescopic supporting leg 6), the length of the telescopic supporting leg 6 is adjusted, and the projection angle is defined by Shortened toThe whole box body 1 is inclined to the satellite moving direction, and the inclination angle is that，In order to adjust the angle variation between delta ABC and triangle delta DEF, the azimuth angle adjusting component 5 is started at the same time to enable the box body 1 to incline while rotating, and in the process, the pitch angle adjusting component 2 is kept to work continuously, so that the antenna surface 4 moves along with the movement of the satellite, and continuous tracking of the overhead satellite is realized.
In step S3, the adjustment end point time of the corresponding telescopic support leg 6 is consistent with the adjustment end point time of the azimuth angle adjustment assembly 5. At this time, the second angle adjustment value of the azimuth angle adjustment assembly 5 is far smaller than the first angle adjustment value of the azimuth angle adjustment assembly 5 when the telescopic support leg 6 is not engaged due to the engagement of the telescopic support leg 6, and can be specifically determined according to the telescopic amount of the telescopic support leg 6 at the placement position, preferably, the second angle adjustment value is 0.1-0.8 times, or 0.2-0.6 times, or 0.2-0.5 times of the first angle adjustment value. By adopting the measures, the continuous tracking of the parabolic antenna to the overhead satellite can be ensured, and continuous communication is ensured not to be interrupted.
When the number of the telescopic supporting legs 6 is more than 3 groups, the corresponding telescopic supporting legs 6 are adjusted, and the whole box body 1 is ensured to incline towards the satellite moving direction.
Example 4:
When the satellite is over-topped, the over-topped satellite cannot be aligned timely due to the limitation of the angle adjustable range of the parabolic antenna pitch angle adjusting assembly 2, and the azimuth angle adjusting assembly 5 is required to rotate the box body 1 by a certain angle (sometimes even by 180 degrees) so as to be possible to track the over-topped satellite. And during the time that the azimuth adjustment assembly 5 is completing the angular rotation, communication is interrupted during this time because the antenna face 4 is not aligned with the overhead satellite. In order to solve the problem, the embodiment adopts a mode of adjusting the length of the telescopic supporting legs 6 to be matched with the azimuth angle adjusting assembly 5 and the pitch angle adjusting assembly 2 to ensure that the antenna surface 4 is continuously aligned with the satellite when the satellite is overtravel, thereby realizing continuous uninterrupted satellite communication.
Referring to fig. 4, the present embodiment provides an overhead satellite continuous tracking method based on the overhead satellite continuous tracking system of embodiment 1, which includes the following steps:
s1: when the box body reaches the placement position, the length of each telescopic supporting leg 6 is adjusted, so that the box body 1 is ensured to be placed stably, and the box body 1 is ensured to be in a horizontal position; at this time, the three upper end points of the 3 groups of telescopic supporting legs 6 are I, J, K respectively to enclose DeltaIJK, the three lower end points of the 3 groups of telescopic supporting legs 6 are L, M, N respectively to enclose DeltaLMN, 、、The projection lengths of the lengths of 3 groups of telescopic supporting legs 6 on a plane IJK before adjustment are respectively;
s2: controlling the azimuth angle adjusting assembly 5 and the pitch angle adjusting assembly 2 to enable the antenna surface 4 to face the satellite, and enabling the antenna surface 4 to move along with the movement of the satellite;
s3: when the satellite is over-jacked, and the satellite over-jacked direction is between IJ and KN (i.e. along the direction between the two corresponding groups of telescopic supporting legs 6), the lengths of the two corresponding groups of telescopic supporting legs 6 are adjusted, and the projection angle is defined by Shortened to，Shortened toThe whole box body 1 is inclined to the satellite moving direction, and the inclination angle is that，For the angle variation between DeltaIJK and DeltaLMN, the azimuth angle adjusting component 5 is started while adjusting, so that the box body 1 is inclined while rotating, and in the process, the pitch angle adjusting component 2 is kept to work continuously, so that the antenna surface 4 moves along with the movement of the satellite, and continuous tracking of the overhead satellite is realized.
In step S3, the adjustment end point time of the corresponding telescopic support leg 6 is consistent with the adjustment end point time of the azimuth angle adjustment assembly 5. At this time, the second angle adjustment value of the azimuth angle adjustment assembly 5 is far smaller than the first angle adjustment value of the azimuth angle adjustment assembly 5 when the telescopic support leg 6 is not engaged due to the engagement of the telescopic support leg 6, and can be specifically determined according to the telescopic amount of the telescopic support leg 6 at the placement position, preferably, the second angle adjustment value is 0.1-0.8 times, or 0.2-0.6 times, or 0.2-0.5 times of the first angle adjustment value. By adopting the measures, the continuous tracking of the parabolic antenna to the overhead satellite can be ensured, and continuous communication is ensured not to be interrupted.
When the number of the telescopic supporting legs 6 is more than 3 groups, the corresponding telescopic supporting legs 6 are adjusted, and the whole box body 1 is ensured to incline towards the satellite moving direction.
The foregoing description of the preferred embodiments of the invention is not intended to limit the invention to the precise form disclosed, and any such modifications, equivalents, and alternatives falling within the spirit and scope of the invention are intended to be included within the scope of the invention.
Claims (10)
1. An overhead satellite continuous tracking system, comprising: the device comprises a box body (1), a pitch angle adjusting component (2) rotationally arranged at the top of the box body (1), a feed source component (3) arranged on the pitch angle adjusting component (2), an antenna surface (4) arranged on the feed source component (3), an azimuth angle adjusting component (5) arranged at the bottom of the box body (1) and at least three groups of telescopic supporting legs (6) surrounding the bottom of the azimuth angle adjusting component (5); the rotation angle of the antenna surface (4) on the box body (1) along with the pitch angle adjusting component (2) is 0-90 degrees; the telescopic supporting legs (6) extend to the outer side of the box body (1);
When the satellite is overturned, the corresponding telescopic supporting legs (6) are adjusted, so that the whole box body (1) inclines towards the moving direction of the satellite, and the antenna surface (4) continuously tracks satellite signals when the satellite is overturned by combining the angle adjustment of the pitch angle adjustment assembly (2) and the azimuth angle adjustment assembly (5).
2. The overhead satellite continuous tracking system according to claim 1, wherein the box (1) comprises a front side (11) and a rear side (12) corresponding to each other, a pitch angle adjustment storage bin (13) is arranged at the top of the box (1) close to the front side (11), the pitch angle adjustment storage bin (13) extends to the top of the box (1) and the front side (11), and the pitch angle adjustment assembly (2) is rotatably arranged in the pitch angle adjustment storage bin (13).
3. The overhead satellite continuous tracking system according to claim 2, wherein the number of telescopic support legs (6) is 3, wherein two sets of telescopic support legs (6) are close to the front side (11) and the other set are close to the rear side (12).
4. The overhead satellite continuous tracking system according to claim 1, wherein the feed assembly (3) comprises a sub-reflector and a feed support bar, both ends of which are connected to the sub-reflector and the pitch angle adjusting assembly (2), respectively.
5. The overhead satellite continuous tracking system of claim 4 wherein the antenna face (4) comprises a central disk and a primary reflective face surrounding the central disk, the central disk being disposed on the feed support bar.
6. The overhead satellite continuous tracking system according to any one of claims 1 to 5, characterized in that the adjustment end point of the corresponding telescopic support leg (6) coincides with the adjustment end point of the azimuth angle adjustment assembly (5) when the satellite is overhead.
7. The overhead satellite continuous tracking system of claim 6, wherein the second angle adjustment value of the azimuth angle adjustment assembly (5) is 0.1-0.8 times the first angle adjustment value, the first angle adjustment value being an angle adjustment value required by the azimuth angle adjustment assembly (5) to track an overhead satellite when the telescoping support leg (6) is not adjusted, the second angle adjustment value being an angle value changed by the azimuth angle adjustment assembly (5) when the telescoping support leg (6) is adjusted when the overhead satellite is tracked.
8. A method of continuous tracking of an overhead satellite based on the overhead satellite continuous tracking system of any one of claims 1 to 7, comprising the steps of:
s1: when the box body reaches the placement position, the length of each telescopic supporting leg (6) is adjusted, the box body (1) is ensured to be placed stably, and the box body (1) is ensured to be in a horizontal position;
S2: controlling the azimuth angle adjusting component (5) and the pitch angle adjusting component (2) to enable the antenna surface (4) to face the satellite, and enabling the antenna surface (4) to move along with the movement of the satellite;
S3: when the satellite is overturned, the corresponding telescopic supporting legs (6) are adjusted, so that the whole box body (1) is inclined towards the moving direction of the satellite, the azimuth angle adjusting assembly (5) is started while the adjustment is carried out, the box body (1) is rotated and inclined, and in the process, the pitch angle adjusting assembly (2) is kept to work continuously, the antenna surface (4) moves along with the movement of the satellite, and continuous tracking of the overturned satellite is realized.
9. The method according to claim 8, wherein in step S3, the adjustment end point time of the corresponding telescopic support leg (6) coincides with the adjustment end point time of the azimuth angle adjustment assembly (5).
10. The method according to claim 9, wherein in step S3, the second angle adjustment value of the azimuth angle adjustment assembly (5) is 0.1-0.8 times the first angle adjustment value, and the first angle adjustment value is an angle adjustment value required by the azimuth angle adjustment assembly (5) to track the overhead satellite when the telescopic support leg (6) is not adjusted.
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