CN112994779B - Single-station double-satellite time overlapping task tracking method, system, terminal and medium - Google Patents
Single-station double-satellite time overlapping task tracking method, system, terminal and medium Download PDFInfo
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- H—ELECTRICITY
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Abstract
The invention discloses a method, a system, a terminal and a medium for tracking a single-station double-satellite time overlapping task, which comprise the following steps: obtaining time windows of two low-earth orbit satellite transit ground stations in preset time according to the executed satellite orbit data, wherein the time windows comprise a first time window and a second time window, the time window of the first low-earth orbit satellite transit ground station is the first time window, and the time window of the second low-earth orbit satellite transit ground station is the second time window; extracting two task time windows with time conflicts in the first time window and the second time window according to a judgment condition of time overlapping; the problem of the satellite-ground communication time utilization ratio of the single-station double-satellite system is low is solved. The invention has the advantages that: the communication duration of the tracking task with partially overlapped time is prolonged, and the method is suitable for the application scene of a single-station double-satellite system; the flow is simple, the satellite-ground communication time utilization rate is high, and the satellite-ground communication time can be maximally prolonged.
Description
Technical Field
The invention relates to the technical field of satellite planning ground receiving station tasks, in particular to a single-station double-satellite time overlapping task tracking method, a system, a terminal and a medium.
Background
When a single satellite ground station carries out a tracking task of a low-orbit satellite, if the tracking task time windows of a double-satellite system consisting of two adjacent low-orbit satellites are partially overlapped, because the tracking task is carried out by the constraint that the satellite ground station system needs to preset the system state for a period of time before each tracking task, usually only one time window of one low-orbit satellite can be selected to execute the tracking task, so that the utilization efficiency of the limited communication time of the satellite and the ground when the satellite passes through the ground station is reduced, and the defect that the utilization rate of the satellite-ground communication time of the single-station double-satellite system is low is caused.
Disclosure of Invention
Therefore, a single-station double-satellite time-overlapping task tracking method needs to be designed, and aims to overcome the defect that the satellite-ground communication time utilization rate of a single-station double-satellite system in the prior art is low.
The invention is realized by the following technical scheme:
in a first aspect, a single-station double-satellite time-overlapping task tracking method is provided, which includes the following steps:
s1: obtaining time windows of two low-earth-orbit satellite transit ground stations in preset time according to the executed satellite orbit data, wherein the time windows comprise a first time window and a second time window, the time window of the first low-earth-orbit satellite transit ground station is the first time window, and the time window of the second low-earth-orbit satellite transit ground station is the second time window;
s2: extracting two task time windows with time conflicts in the first time window and the second time window according to a judgment condition of time overlapping, and obtaining the time length of the previous time window, the time length of the next time window, the entry-exit azimuth angle of the previous time and the entry-exit azimuth angle of the next time of the corresponding two low-orbit satellites according to the two task time windows with time conflicts;
s3: obtaining the maximum time required by the rotation of the antenna according to the azimuth angle speed of the antenna, the entry and exit azimuth angle of the previous time and the entry and exit azimuth angle of the later time,
performing splicing analysis on the tracking task within the maximum time required by the rotation of the antenna to obtain the effective communication time of the splicing task;
s4: judging whether the communication time of the splicing task is the longest or not by sequencing the effective communication time of the splicing task, the time of the previous time window and the time of the next time window;
if the judgment result is negative, executing a first action, wherein the first action is to set a single satellite tracking task with the longest communication time;
and if so, executing a second action, wherein the second action is to formulate a double-star tracking task and splice the tracking guide file.
In the prior art, only one time window of one low-orbit satellite can be selected to perform a tracking task, so that the utilization efficiency of the satellite-ground limited communication time when the satellite passes through the ground station is reduced.
The method increases the time windows of two low-orbit satellites crossing the ground station within the preset time by executing satellite orbit data, and extracts the front time window and the rear time window with partial time overlap; splicing analysis of the tracking task is carried out according to the entry-exit azimuth angles of the two low-orbit satellites corresponding to the two time windows and the maximum time length covered by the two time windows, and a communication efficiency analysis result and a task planning strategy of the splicing task are obtained; when the tracking task is executed, splicing the two tracking guide files of the two stars into one file to be sent to an antenna tracking system; the method realizes the planning of the single-station double-satellite time overlapping tracking task, improves the communication duration of the tracking task with partially overlapped time, is suitable for the application scene of the single-station double-satellite system, has simple flow and high satellite-ground communication time utilization rate, and can maximally prolong the satellite-ground communication time.
Further, a minimum time interval between the first time window and the second time window is used as a time overlapping judgment condition.
When the time interval is smaller than the minimum time interval, the conflict can occur, otherwise, when the time interval is larger than the minimum time interval, the conflict can not occur.
Further, conducting guide file splicing according to the first action and the second action and sending the guide files to an antenna system for execution;
and conducting guide file splicing and sending the guide file to an antenna system for execution when the task is executed at the moment according to the communication time length comparison result.
Further, the splicing analysis of the tracking task is performed on the maximum time required by the rotation of the antenna, and the specific steps include:
s31: taking the difference between the starting time of the latter time window and the maximum time required by the rotation of the antenna as the time when the former time window should be ended in advance;
s32: obtaining the effective communication duration of the previous task after splicing according to the time that the previous time window is ended in advance obtained in the S31;
s33: and taking the sum of the effective communication time of the spliced previous task and the effective communication time of the spliced next task obtained in the step S32 as the effective communication time of the splicing task.
In a second aspect, a system for single-station two-satellite time-overlapping tracking task is provided, which includes:
a data acquisition module: the time window is used for executing the satellite orbit data to obtain two low-orbit satellite transit ground stations in preset time and comprises a first time window and a second time window;
an extraction module: the two task time windows are used for extracting two time conflicts existing in the first time window and the second time window, and the time length of the previous time window, the time length of the next time window, the entry and exit azimuth angle of the previous time and the entry and exit azimuth angle of the next time of the two corresponding low-orbit satellites are obtained according to the two task time windows with the time conflicts;
a processing and analyzing module: is used for processing the speed of the azimuth angle of the antenna, the entry and exit azimuth angle of the previous time and the entry and exit azimuth angle of the later time to obtain the maximum time required by the rotation of the antenna,
performing splicing analysis on the tracking task within the maximum time required by the rotation of the antenna to obtain the effective communication time of the splicing task;
a first judgment module: the time sequence unit is used for judging whether the communication time of the splicing task is the longest or not according to the sequencing of the effective communication time of the splicing task, the time length of the previous time window and the time length of the next time window;
if the judgment result is negative, executing a first action, wherein the first action is to set a single satellite tracking task with the longest communication time;
and if so, executing a second action, wherein the second action is to formulate a double-star tracking task and splice the tracking guide file.
Further, the device also comprises a second judgment module: and the minimum time interval between the first time window and the second time window is used as a judgment condition of time overlapping.
Further, the system also comprises an execution module: and the system is used for conducting guide file splicing on the judgment result and sending the guide file splicing to an antenna system for execution.
Further, the device also comprises an analysis module: the difference between the starting time of the latter time window and the maximum time required by the rotation of the antenna is used as the time when the former time window is ended in advance;
the effective communication duration of the previous task after splicing is obtained according to the time when the previous time window is ended in advance;
and the sum of the effective communication time of the spliced previous task and the effective communication time of the spliced next task is used as the effective communication time of the spliced task.
In a third aspect, a computer terminal is provided, which includes a memory, a processor, and a computer program stored in the memory and executable on the processor, and when the processor executes the computer program, the processor implements the method for tracking a single-station double-satellite time-overlapped task according to the first aspect; a memory including a computer readable program executable by the processor, the program being executable when run in the processor.
In a fourth aspect, a computer readable medium is provided, on which a computer program is stored, the computer program being executed by a processor and being capable of implementing a single-station two-satellite time-overlapping task tracking method according to the first aspect.
Compared with the prior art, the invention has the following advantages and beneficial effects:
1. the single-station double-satellite time overlapping task tracking method improves the communication duration of the tracking task with partially overlapped time, and is suitable for application scenes of a single-station double-satellite system.
2. The single-station double-satellite time overlapping task tracking method has the advantages of simple process, high satellite-ground communication time utilization rate and capability of prolonging the satellite-ground communication time to the maximum extent.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the principles of the invention. In the drawings:
FIG. 1 is a block flow diagram of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to examples and accompanying drawings, and the exemplary embodiments and descriptions thereof are only used for explaining the present invention and are not meant to limit the present invention.
Example 1
As shown in fig. 1, the present invention is a single-station two-satellite time-overlapping task tracking method, which is implemented by the following steps:
a1, setting a calculation time interval, and calling orbit data of two satellites to execute orbit calculation;
a2, acquiring tracking task time windows of two satellites in a set calculation period;
a3, obtaining an entry azimuth AzIa and an exit azimuth AzOa of the previous task a at the same time;
a4, the entry azimuth AzIb and the exit azimuth AzOb of the latter task b, and so on;
a5, setting T as the minimum time interval between two task time windows as the judgment condition of task time overlapping;
a6, the tracking start time of the previous task a is Ta1, and the tracking end time is Ta 2;
a7, the tracking start time of the next task b is Tb1, and the tracking end time is Tb 2;
a8, according to Tb1 and Ta2 and T and Tb2, judging that the two time windows of the previous task a and the next task b are overlapped;
a9, the task time length Ta of the previous task a is Ta2-Ta 1;
a10, and the task time length Tb of the next task b is Tb2-Tb 1;
a11, the azimuth velocity of the antenna is p;
a12, the time required for the antenna to rotate from the outbound orientation of the previous task a to the inbound orientation of the next task b is;
A13、T1＝||AzOa-AzIb|-180|/p；
a14, setting the effective communication time length Ts of the splicing task to (Tb1-T1-Ta1) + (Tb2-Tb 1);
a15, sorting the task duration Ta of the task a, the task duration Tb of the task b and the effective communication duration Ts of the splicing task;
a16, if Ts > Ta and Tb;
a17, setting the tracking end time of the previous task a as Tb 1-T1;
a18, setting the start time of the antenna tracking guide file data of the previous task a to be Ta1 and the end time to be Tb 1-T1;
a19, obtaining the tracking guide file data of the previous task a through satellite orbit calculation;
a20, splicing the tracking guide file data of the previous task a and the tracking guide file data of the next task b according to the time sequence to form tracking guide file data of a spliced task, and sending the tracking guide file data to an antenna system when the task is executed;
a21, if Ts < Ta or Tb;
a22, a single-satellite tracking task with the longest communication time is formulated, and when the task is executed at the time, the single-satellite tracking guide file data is sent to the antenna system.
By executing satellite time window calculation, under the judgment condition that the overlapping time is at least larger than a set value, acquiring two overlapping time windows meeting the condition, acquiring the time length of the previous time window, the time length of the next time window, the exit azimuth angle of the previous time window and the entry azimuth angle of the next time window according to the time windows, calculating the maximum time required by an antenna system from the exit position of the previous task to the entry position of the next task through the known antenna azimuth angle speed, calculating the ending time of the previous task according to the entry time of the next satellite to obtain the total time length of the spliced task and the effective communication time, respectively sequencing the previous time window, the next time window and the effective time window of the spliced task according to the effective communication time length, and formulating the double-satellite tracking task if the effective communication time of the spliced task is the longest, and splicing the tracking guide files, otherwise, establishing a single-satellite tracking task with the longest communication time, and executing the task when the task is in time.
The method is mainly used for a satellite ground station system only provided with single antenna receiving and transmitting, when aiming at the low-orbit double-satellite system communication, because the double-satellite system is designed to pass through the satellite ground stations in sequence and continuously, the situation that partial time overlapping occurs in time windows of front and back two satellites is caused, in order to effectively improve the utilization rate of satellite-ground communication time when the double satellites pass through the border and improve the communication time when the double satellites pass through the border, the method effectively prolongs the satellite-ground communication time of the double satellites by adopting a task splicing mode.
Example 2
As shown in fig. 1, a system for single-station two-satellite time overlapping tracking task includes:
a data acquisition module: the time window is used for executing the satellite orbit data to obtain two low-orbit satellites passing through the ground station within preset time and comprises a first time window and a second time window; the time window of the first low-earth orbit satellite transit ground station is a first time window, and the time window of the second low-earth orbit satellite transit ground station is a second time window;
an extraction module: the two task time windows are used for extracting the two time conflicts existing in the first time window and the second time window, and the time length of the previous time window, the time length of the next time window, the entry and exit azimuth angle of the previous time and the entry and exit azimuth angle of the next time of the two corresponding low-orbit satellites are obtained according to the two task time windows with the time conflicts;
a processing and analyzing module: used for processing the speed of the azimuth angle of the antenna, the entry and exit azimuth angles of the previous time and the entry and exit azimuth angles of the later time to obtain the maximum time required by the rotation of the antenna,
splicing analysis of the tracking task is carried out on the maximum time required by the rotation of the antenna, and the effective communication time of the splicing task is obtained;
a first judgment module: the device is used for judging whether the communication time of the splicing task is the longest or not according to the sequencing of the effective communication time of the splicing task, the time of the previous time window and the time of the next time window;
if the judgment result is negative, a single satellite tracking task with the longest communication time is formulated;
if the judgment result is yes, a double-star tracking task is formulated, and tracking guide files are spliced.
Preferably, the system further comprises a second judging module: and the minimum time interval between the first time window and the second time window is used as a judgment condition of time overlapping.
Preferably, the method further comprises the following steps: and the antenna system is used for conducting guide file splicing on the judgment result and sending the guide file splicing to the antenna system for execution.
Preferably, the device further comprises an analysis module: the time difference between the starting time of the latter time window and the maximum time required by the rotation of the antenna is used as the time when the former time window is to be ended in advance;
the system is used for acquiring the effective communication duration of the previous task after splicing according to the time when the previous time window is ended in advance;
and the method is used for taking the sum of the effective communication time of the spliced previous task and the effective communication time of the spliced next task as the effective communication time of the spliced task.
Example 3
A computer terminal comprising a memory, a processor and a computer program stored in the memory and executable on the processor, wherein the processor implements a single-station two-satellite time-overlapping task tracking method according to the first aspect when executing the program; a memory including a computer readable program executable by the processor, the program being executable when run in the processor.
Example 4
A computer readable medium having stored thereon a computer program for execution by a processor to implement a single station two star time overlapping task tracking system as in the first aspect.
The above embodiments are provided to further explain the objects, technical solutions and advantages of the present invention in detail, it should be understood that the above embodiments are merely exemplary embodiments of the present invention and are not intended to limit the scope of the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (8)
1. A single-station double-satellite time overlapping task tracking method is characterized by comprising the following steps:
s1: obtaining time windows of two low-orbit satellites passing through a ground station within preset time according to the executed satellite orbit data, wherein the time windows comprise a first time window and a second time window;
the time window of the first low-earth orbit satellite transit ground station is the first time window, and the time window of the second low-earth orbit satellite transit ground station is the second time window;
s2: extracting two task time windows with time conflicts in the first time window and the second time window according to a judgment condition of time overlapping, and obtaining the time length of the previous time window, the time length of the next time window, the entry-exit azimuth angle of the previous time and the entry-exit azimuth angle of the next time of the corresponding two low-orbit satellites according to the two task time windows with time conflicts;
s3: obtaining the maximum time required by the rotation of the antenna according to the azimuth angle speed of the antenna, the entry and exit azimuth angle of the previous time and the entry and exit azimuth angle of the later time,
performing splicing analysis on the tracking task within the maximum time required by the rotation of the antenna to obtain the effective communication time of the splicing task;
s4: judging whether the communication time of the splicing task is the longest or not by sequencing the effective communication time of the splicing task, the time of the previous time window and the time of the next time window;
if the judgment result is negative, executing a first action, wherein the first action is to make a single satellite tracking task with the longest communication time;
if the judgment result is yes, executing a second action, wherein the second action is to make a double-star tracking task and splice tracking guide files;
wherein the S3 includes the following substeps:
s31: taking the difference between the starting time of the latter time window and the maximum time required by the rotation of the antenna as the time when the former time window should be ended in advance;
s32: obtaining the effective communication duration of the previous task after splicing according to the time that the previous time window is ended in advance obtained in the S31;
s33: and taking the sum of the effective communication time of the spliced previous task and the effective communication time of the spliced next task obtained in the step S32 as the effective communication time of the splicing task.
2. The single-station double-star time-overlapped task tracking method according to claim 1, wherein in the step of S2, the minimum time interval between the first time window and the second time window is used as a time-overlapped decision condition.
3. The method for tracking a single-station double-satellite time-overlapped task according to claim 1, wherein in the step of S4, the boot files are spliced according to the first action and the second action and sent to an antenna system for execution.
4. A single-station, two-satellite time-overlapping task tracking system, comprising:
a data acquisition module: the time window is used for executing the satellite orbit data to obtain two low-orbit satellite transit ground stations in preset time and comprises a first time window and a second time window;
an extraction module: the two task time windows are used for extracting two time conflicts existing in the first time window and the second time window, and the time length of the previous time window, the time length of the next time window, the entry and exit azimuth angle of the previous time and the entry and exit azimuth angle of the next time of the two corresponding low-orbit satellites are obtained according to the two task time windows with the time conflicts;
a processing and analyzing module: the azimuth angle speed of the antenna, the entry and exit azimuth angle of the previous time and the entry and exit azimuth angle of the later time are processed to obtain the maximum time required by the rotation of the antenna;
an analysis module: the difference between the starting time of the latter time window and the maximum time required by the rotation of the antenna is used as the time when the former time window is ended in advance;
the effective communication duration of the previous task after splicing is obtained according to the time when the previous time window is ended in advance;
the effective communication duration of the spliced task is the sum of the effective communication duration of the previous task and the effective communication duration of the next task;
a first judgment module: the time sequence unit is used for judging whether the communication time of the splicing task is the longest or not according to the sequencing of the effective communication time of the splicing task, the time length of the previous time window and the time length of the next time window;
if the judgment result is negative, a single satellite tracking task with the longest communication time is formulated;
if the judgment result is yes, a double-star tracking task is formulated, and tracking guide files are spliced.
5. The single-station double-satellite time-overlapped task tracking system according to claim 4, further comprising a second judgment module: and the minimum time interval between the first time window and the second time window is used as a judgment condition of time overlapping.
6. The single-station double-star time-overlapped task tracking system according to claim 5, further comprising an execution module: and the system is used for conducting guide file splicing on the judgment result and sending the guide file splicing to an antenna system for execution.
7. A computer terminal comprising a memory, a processor and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement a single-station two-star time-overlapped task tracking method according to any one of claims 1 to 3.
8. A computer-readable medium, on which a computer program is stored, the computer program being executable by a processor to implement a single-station two-star time-overlapping task tracking method according to any one of claims 1 to 3.
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