CN-117341991-B - Satellite orbit change strategy planning method, device, equipment and storage medium

CN117341991BCN 117341991 BCN117341991 BCN 117341991BCN-117341991-B

Abstract

The application discloses a satellite orbit change strategy planning method, a device, equipment and a storage medium, wherein the method comprises the steps of initializing the initial time of a satellite and carrying out orbit period extrapolation, and taking the updated t time as the extrapolated time; initializing an orbit change mark as incomplete, calculating a first orbit parameter of a satellite at a t moment and a second orbit parameter of a target virtual satellite at the t moment, determining a relative orbit parameter of the satellite to the target virtual satellite, determining each orbit parameter correction mark according to the relative orbit parameter and a preset orbit threshold value, determining a corresponding orbit control sub-mode based on each orbit parameter correction mark, and determining an ignition parameter of the satellite based on the orbit control sub-mode and performing orbit change maneuver and orbit change phase adjustment when the orbit change mark is completed. According to the scheme, the corresponding orbit control sub-mode can be rapidly selected according to the current orbit changing requirement, and calculation and simulation verification of the electric-push orbit changing parameters can be rapidly generated, so that the satellite orbit changing accurately enters the preset orbit position.

Inventors

LI XINGANG
QI YU
HOU FENGLONG
PEI SHENGWEI
LI FENG

Assignees

中国空间技术研究院

Dates

Publication Date: 20260512
Application Date: 20231007

Claims (9)

1. A satellite orbit maneuver planning method, the method comprising: Initializing the initial time of a satellite and performing orbital period extrapolation, wherein t is updated to be the extrapolated time, and t is greater than 0; Initializing an orbit change mark as incomplete, calculating a first orbit parameter of a satellite at a time t and a second orbit parameter of a target virtual satellite at the time t, and determining a relative orbit parameter of the satellite to the target virtual satellite based on the first orbit parameter and the second orbit parameter; Determining each track parameter correction mark according to the relative track parameter and a preset track threshold value, and determining a corresponding track control sub-mode and a completion result of the track change mark based on each track parameter correction mark; according to the completion result of the track change mark and the track control sub-mode, track change maneuver and track change phase adjustment are carried out; the relative orbit parameters comprise relative semi-long axis flat root, relative eccentricity flat root, relative dip angle flat root, relative rising intersection point right ascent flat root, relative near place amplitude angle flat root, relative latitude amplitude angle flat root and relative eccentricity vector Ping Gen; determining each track parameter correction mark according to the relative track parameter and a preset track threshold value, wherein the track parameter correction mark comprises: when the absolute value of the relative semi-major axis flat root is larger than the preset relative semi-major axis flat root, determining that the semi-major axis flat root correction mark is 1, otherwise, determining that the semi-major axis flat root correction mark is 0; when the absolute value of the relative eccentricity flat root is larger than the preset relative eccentricity flat root, determining that the eccentricity flat root correction mark is 1, otherwise, determining that the eccentricity flat root correction mark is 0; When the absolute value of the root leveling of the amplitude angle of the relatively near place is larger than the preset root leveling of the amplitude angle of the relatively near place, determining that the root leveling correction mark of the amplitude angle of the near place is 1, otherwise, determining that the root leveling correction mark of the amplitude angle of the near place is 0; When the absolute value of the relative inclination angle flat root is larger than the preset relative inclination angle flat root, determining an inclination angle flat root correction mark as 1, otherwise, determining an inclination angle flat root correction mark as 0; and when the absolute value of the relative rising intersection point right ascent flat root is larger than the preset relative rising intersection point right ascent flat root, determining that the rising intersection point right ascent flat root correction mark is 1, otherwise, determining that the rising intersection point right ascent flat root correction mark is 0.
2. The method of claim 1, wherein each of the track parameter modification flags further comprises a first modification flag and a second modification flag, the method further comprising: When the eccentricity root flattening correction mark is 1 or the near-place amplitude angle root flattening correction mark is 1, determining that the first correction mark is 1, otherwise, determining that the first correction mark is 0; And when the first correction mark is 1 and the semilong axis flat root correction mark is 1, determining that the second correction mark is 1, otherwise, determining that the second correction mark is 0.
3. The method of claim 2, wherein determining the corresponding track sub-mode based on the track parameter correction flags comprises: Judging whether the second correction mark is 1 or not; If the second correction mark is 1, determining a corresponding track control sub-mode according to the inclination angle flat root correction mark and the rising intersection point right-angle flat root correction mark; And if the second correction mark is not 1, determining a corresponding track control sub-mode according to the correction mark of the semi-long axis flat root, the inclination angle flat root correction mark and the ascent point right ascent and descent flat root correction mark.
4. The method of claim 3, wherein determining a corresponding track sub-pattern based on the semi-major axis flat root revision flag, the dip flat root revision flag, and the rise intersection right ascent flat root revision flag comprises: Judging whether the correction mark of the semi-long axis flat root is 1 or not; if the correction mark of the semi-long axis flat root is 1, determining a corresponding track control sub-mode according to the inclination angle flat root correction mark and the rising intersection point right ascent flat root correction mark; If the correction mark of the semi-long axis flat root is not 1, determining a corresponding track control sub-mode according to the first correction mark, the inclination angle flat root correction mark and the rising intersection point right-angle flat root correction mark.
5. The method according to claim 1, wherein performing a track change maneuver and a track change phase adjustment process according to a result of the completion of the track change flag and the track control sub-mode comprises: when the completion result of the orbit change mark is completed, calculating the relative latitude amplitude angle of the satellite and the target orbit; comparing the absolute value of the relative latitude amplitude angle with a preset latitude amplitude angle; When the absolute value of the relative latitude amplitude angle is not larger than the preset latitude amplitude angle, adjusting the phase adjustment time by adopting an optimization algorithm, and initializing the orbit transfer mark to be incomplete again; And determining a corresponding track control sub-mode based on the first track parameter and the second track parameter again, and performing track changing maneuver and track changing phase adjustment processing until the absolute value of the relative latitude amplitude angle is not larger than a preset latitude amplitude angle.
6. The method of claim 5, wherein the rail sub-mode comprises at least one of: The joint correction of semi-long axis flat roots, the eccentricity flat roots and near-place amplitude angle flat roots and the independent correction of inclination flat roots are alternately executed; The combined correction of semi-long axis flat roots, the eccentricity flat roots and near-place amplitude angle flat roots and the independent correction of ascending points are alternately executed; Performing joint correction of semi-long axis flat root, eccentricity flat root and near place amplitude angle Ping Gen; alternately executing the independent correction semimajor axis Ping Gen and the independent correction dip angle flat root; alternately executing the right ascent point, the right ascent point and the flat root on the independent correction semimajor axis Ping Gen and the independent correction ascent point; Performing a separate correction of semi-major axis Ping Gen; alternately executing the joint correction of the eccentricity flat root and the near-place amplitude angle flat root and the independent correction of the inclination flat root; Alternately executing the joint correction of the eccentric rate flat root and the near-place amplitude angle flat root and the independent correction of the right ascent point and the left ascent point; Performing joint correction of the eccentricity flat root and near-place argument Ping Gen; Performing a separate correction of the tilt angle Ping Gen; Performing individual correction steps the intersection points are barely marked by flat roots.
7. A satellite orbit maneuver planning apparatus, the apparatus comprising: The initialization module is used for initializing the initial time of the satellite and performing orbital period extrapolation, and the updated time t is the extrapolated time t is greater than 0; The calculation module is used for initializing an orbit change mark to be incomplete, calculating a first orbit parameter of a satellite at t moment and a second orbit parameter of a target virtual satellite at t moment, and determining a relative orbit parameter of the satellite to the target virtual satellite based on the first orbit parameter and the second orbit parameter; The determining module is used for determining each track parameter correction mark according to the relative track parameter and a preset track threshold value and determining a corresponding track control sub-mode based on each track parameter correction mark; The orbit transfer module is used for determining the ignition parameters of the satellite based on the orbit control sub-mode when the orbit transfer mark is completed, and carrying out orbit transfer maneuver and orbit transfer phase adjustment; the relative orbit parameters comprise relative semi-long axis flat root, relative eccentricity flat root, relative dip angle flat root, relative rising intersection point right ascent flat root, relative near place amplitude angle flat root, relative latitude amplitude angle flat root and relative eccentricity vector Ping Gen; the determining module is used for: when the absolute value of the relative semi-major axis flat root is larger than the preset relative semi-major axis flat root, determining that the semi-major axis flat root correction mark is 1, otherwise, determining that the semi-major axis flat root correction mark is 0; when the absolute value of the relative eccentricity flat root is larger than the preset relative eccentricity flat root, determining that the eccentricity flat root correction mark is 1, otherwise, determining that the eccentricity flat root correction mark is 0; When the absolute value of the root leveling of the amplitude angle of the relatively near place is larger than the preset root leveling of the amplitude angle of the relatively near place, determining that the root leveling correction mark of the amplitude angle of the near place is 1, otherwise, determining that the root leveling correction mark of the amplitude angle of the near place is 0; When the absolute value of the relative inclination angle flat root is larger than the preset relative inclination angle flat root, determining an inclination angle flat root correction mark as 1, otherwise, determining an inclination angle flat root correction mark as 0; and when the absolute value of the relative rising intersection point right ascent flat root is larger than the preset relative rising intersection point right ascent flat root, determining that the rising intersection point right ascent flat root correction mark is 1, otherwise, determining that the rising intersection point right ascent flat root correction mark is 0.
8. A computer device comprising a memory, a processor and a computer program stored in the memory and executable on the processor, wherein the processor implements the satellite orbit maneuver planning method as claimed in any one of claims 1-6 when executing the computer program.
9. A computer readable storage medium having stored thereon a computer program for implementing the satellite orbit maneuver planning method as claimed in any one of claims 1-6.

Description

Satellite orbit change strategy planning method, device, equipment and storage medium Technical Field The present invention relates generally to the field of satellite orbit control technologies, and in particular, to a method, an apparatus, a device, and a storage medium for planning a satellite orbit maneuver. Background With the rapid development of satellite communication technology, the electric propulsion technology also develops rapidly, and is widely applied to the aspect of satellite orbit control, and the electric propulsion system has the characteristics of higher than impulse, less consumption of propellant and stronger orbit changing capability, so as to realize orbit maneuver control. At present, a direct optimization or indirect optimization method is adopted to plan an electric orbit transferring strategy, such as a genetic algorithm, however, the related electric orbit transferring strategy takes a long time, is difficult to model the limitation of satellite attitude pointing, attitude maneuver capability, single ignition duration, ground shadow and the like, is easy to generate the situation that the satellite orbit transferring accuracy is low due to the fact that the satellite orbit transferring cannot be converged to an optimal solution and the like. Disclosure of Invention In view of the foregoing drawbacks or shortcomings of the prior art, it is desirable to provide a satellite orbit maneuver planning method, apparatus, device and storage medium. In a first aspect, the present invention provides a satellite orbit maneuver planning method, which includes: Initializing the initial time of a satellite and performing orbital period extrapolation, wherein t is updated to be the extrapolated time, and t is greater than 0; Initializing an orbit change mark as incomplete, calculating a first orbit parameter of a satellite at a time t and a second orbit parameter of a target virtual satellite at the time t, and determining a relative orbit parameter of the satellite to the target virtual satellite based on the first orbit parameter and the second orbit parameter; Determining each track parameter correction mark according to the relative track parameter and a preset track threshold value, and determining a corresponding track control sub-mode and a completion result of the track change mark based on each track parameter correction mark; And carrying out track changing maneuver and track changing phase adjustment according to the completion result of the track changing mark and the track control sub-mode. In one embodiment, the relative orbit parameters include a relative semi-long axis flat root, a relative eccentricity flat root, a relative dip flat root, a relative elevation intersection right ascent flat root, a relative near place amplitude flat root, a relative latitude amplitude flat root, and a relative eccentricity vector Ping Gen; determining each track parameter correction mark according to the relative track parameter and a preset track threshold value, wherein the track parameter correction mark comprises: when the absolute value of the relative semi-major axis flat root is larger than the preset relative semi-major axis flat root, determining that the semi-major axis flat root correction mark is 1, otherwise, determining that the semi-major axis flat root correction mark is 0; when the absolute value of the relative eccentricity flat root is larger than the preset relative eccentricity flat root, determining that the eccentricity flat root correction mark is 1, otherwise, determining that the eccentricity flat root correction mark is 0; When the absolute value of the root leveling of the amplitude angle of the relatively near place is larger than the preset root leveling of the amplitude angle of the relatively near place, determining that the root leveling correction mark of the amplitude angle of the near place is 1, otherwise, determining that the root leveling correction mark of the amplitude angle of the near place is 0; When the absolute value of the relative inclination angle flat root is larger than the preset relative inclination angle flat root, determining an inclination angle flat root correction mark as 1, otherwise, determining an inclination angle flat root correction mark as 0; and when the absolute value of the relative rising intersection point right ascent flat root is larger than the preset relative rising intersection point right ascent flat root, determining that the rising intersection point right ascent flat root correction mark is 1, otherwise, determining that the rising intersection point right ascent flat root correction mark is 0. In one embodiment, each track parameter modification flag further includes a first modification flag and a second modification flag, and the method further includes: When the eccentricity root flattening correction mark is 1 or the near-place amplitude angle root flattening correction mark is 1, determining that the first corr