CN-115544668-B - Giant constellation collision early warning detection method, electronic equipment and storage medium

CN115544668BCN 115544668 BCN115544668 BCN 115544668BCN-115544668-B

Abstract

The invention relates to a collision early warning detection method of a giant constellation, electronic equipment and a storage medium, which comprises the following steps of S1, constructing a collision risk set according to the design of a protected giant constellation system, determining the possible collision crossing point and crossing point moment according to the design of the constellation system and the collision risk set, judging whether collision risk exists by utilizing a first satellite-to-ground distance H1 of a risk source satellite/fragment at the crossing point moment and a second satellite-to-ground distance H2 of a satellite of the protected giant constellation, and executing the two steps by adopting a parallel calculation strategy to finish collision risk judgment of all risk source satellites/fragments in the collision risk set and satellites of the protected giant constellation system. According to the invention, timeliness of collision possibility detection between the giant constellation and space debris is effectively improved, collision early warning detection efficiency facing the giant constellation in the future is improved, and the satellites are efficiently supported to perform maneuvering adjustment so as to implement collision avoidance.

Inventors

XI CHAO
YANG XIAO
WANG JIRONG
QIAO XUEYUAN
ZHANG QIANLIANG
DUAN KUN
ZHU JUNQING
SUN WANHAI
YANG BO
Fu Chuanguang
HU JIANGYAN

Assignees

航天恒星科技有限公司

Dates

Publication Date: 20260508
Application Date: 20221031

Claims (7)

1. A collision early warning detection method of a giant constellation comprises the following steps: Step S1, constructing a collision risk set according to the design of a protected giant constellation system; Step S2, determining the intersection points and the intersection point moments of possible collision according to the design of a constellation system and a collision risk set, wherein the method specifically comprises the following steps: Step S201, calculating the near-site and far-site heights of satellites/fragments, and determining the satellites/fragments having collision puncture areas with protected constellation orbits; Step S202, determining the intersection point of each track surface or extending track surface of the protected constellation and each track ring in the collision risk set; step S203, determining discrete moment of the crossing point based on the kepler rule and the crossing point of satellite operation; Step S3, determining whether there is a collision risk by using the first satellite-to-ground distance H1 of the risk source satellite/fragment at the moment of the intersection and the second satellite-to-ground distance H2 of the protected giant constellation satellite, which specifically includes: step S301, calculating a first satellite-ground distance H1 between satellites and the ground when a risk source satellite/fragment at the moment of the crossing point moves to the position of the crossing point in an orbit ring based on ephemeris data; step S302, selecting any protected satellite in the same orbit ring, and calculating the distance H2 between the satellites and the ground when the protected satellite moves to the corresponding intersection point based on ephemeris data; Step S303, judging whether the I H1-H2I is larger than a collision detection threshold, if yes, considering that no collision risk exists, and if no, executing step S304; Step S304, calculating the position coordinates of the risk source at the corresponding moment and the position coordinates of each satellite on the track surface by utilizing the discrete moment of the cross point; step S305, calculating the space distance between the risk source and each satellite, and judging whether the space distance is smaller than a collision detection threshold value, if so, the risk source is an object with collision risk; step S306, screening and recording objects with collision risks, and performing collision probability, collision approaching time and collision approaching distance evaluation calculation; and S4, executing the step S2 and the step S3 by adopting a parallel computing strategy, and completing collision risk judgment of all risk source satellites/fragments in the collision risk set and the protected satellites of the giant constellation system.
2. The method according to claim 1, characterized in that in said step S1, before performing the construction of the collision risk set, it further comprises: Step S101, determining the track height layer number of a constellation system according to design parameters of a protected giant constellation; step S102, calculating the near-place height and the far-place height of each sub-layer according to the orbit height and the eccentricity of the giant star sub-layer; step S103, determining the height of the upper side band and the height of the lower side band of the track band where the constellation system is located.
3. Method according to claim 2, characterized in that in said step S1 a set of collision risks is built, comprising in particular: Step S104, calculating the near-site and far-site heights of the satellites/fragments through loading the in-orbit satellite/fragment ephemeris data; Step S105, determining that satellites/fragments having collision puncture areas with the protected constellation orbit band, and constructing a collision risk set from the satellites/fragments having collision puncture areas.
4. A method according to claim 3, characterized in that in said step S105, it is determined that satellites/fragments are present that collide with the protected constellation orbit band in the puncture area, comprising in particular: If the distance point height of the satellite/fragment is larger than the upper sideband height of the protected constellation orbit band and the near point height is smaller than the upper sideband height, the satellite/fragment and the protected constellation orbit band have a puncture area; If the satellite/debris has a apogee height greater than the lower sideband height of the protected constellation orbit band and a perigee height less than the lower sideband height, then the satellite/debris and the protected constellation orbit band have a puncture area.
5. A method according to claim 3, further comprising, prior to performing step S2: Performing dimension reduction processing and classification on the satellite of the protected giant constellation system according to the track surface; performing dimension reduction treatment on satellites/fragments of the collision risk set according to the track surface and classifying the satellites/fragments; And combining the orbit planes of the classified satellites of the protected giant constellation system and the orbit planes of the classified satellites/fragments of the collision risk set into orbit rings respectively.
6. An electronic device comprising one or more processors, one or more memories, and one or more computer programs, wherein the processors are coupled to the memories, the one or more computer programs are stored in the memories, and when the electronic device is operated, the processors execute the one or more computer programs stored in the memories to cause the electronic device to perform a giant constellation collision warning detection method according to any of claims 1-5.
7. A computer readable storage medium storing computer instructions which, when executed by a processor, implement a method of collision early warning detection for a giant constellation according to any one of claims 1 to 5.

Description

Giant constellation collision early warning detection method, electronic equipment and storage medium Technical Field The invention relates to the field of spacecraft collision protection, in particular to a collision early warning detection method of a giant constellation, electronic equipment and a storage medium. Background With the increasing frequency of human aerospace activities, space debris and space debris problems have become a concern over widespread nations worldwide. In particular, in recent years, huge constellations are being implemented or planned worldwide, and most of the huge constellations and space debris are concentrated in the Low Earth Orbit (LEO) area. The probability of collision between the satellite and the space debris is increased, and the collision causes the satellite or the space debris to be split, so that more space debris can be generated, and the collision detection of the giant constellation and the debris is a problem which cannot be ignored. The existing collision screening detection mechanism adopts an approximation calculation mode of constellations and fragments, namely, the positions and the speeds of all satellites under the constellations are predicted in real time, the positions and the speeds of all fragments are predicted in real time, then, the space distance is calculated for every two satellites and fragments in a collision prediction time period, and if the space distance is lower than a set collision threshold value, collision is judged, otherwise, collision possibility does not exist. The CELESTRAK mesh's daily proximity report is also based on screening of collision pairs in this manner. The size of the low-orbit jumbo constellation varies from hundreds, thousands or even tens of thousands. The collision pairs are screened by directly applying a general violent approximation mode, and the parallel calculation is realized by depending on a large number of server supports, so that the requirements of collision screening and calculation in a prediction time period can be met. The popularization of research, simulation, demonstration and implementation of the low-orbit giant constellation has a certain limit. Therefore, under the condition of limited resources, there may be an encounter between the low-orbit giant constellation and the external constellation and space fragments on the moving track, how to predict such collision risk in advance, and a method for efficiently screening the collision of space objects is needed Disclosure of Invention In view of the above technical problems, the invention provides a collision early warning detection method, electronic equipment and storage medium for a giant constellation based on fully analyzing the orbit characteristics of a constellation satellite, which can greatly improve the collision early warning detection efficiency for the giant constellation in the future, and efficiently support the satellite for maneuver adjustment so as to implement collision avoidance. The technical scheme for realizing the purpose of the invention is that the collision early warning detection method of the giant constellation comprises the following steps: Step S1, constructing a collision risk set according to the design of a protected giant constellation system; s2, determining intersection points and intersection point moments at which collision is possible according to the design of a constellation system and a collision risk set; step S3, judging whether collision risks exist by using a first satellite-to-ground distance H1 of a risk source satellite/fragment at the moment of the cross point and a second satellite-to-ground distance H2 of a protected giant constellation satellite; and S4, executing the step S2 and the step S3 by adopting a parallel computing strategy, and completing collision risk judgment of all risk source satellites/fragments in the collision risk set and the protected satellites of the giant constellation system. According to one aspect of the present invention, before the constructing the collision risk set is performed in the step S1, the method further includes: Step S101, determining the track height layer number of a constellation system according to design parameters of a protected giant constellation; step S102, calculating the near-place height and the far-place height of each sub-layer according to the orbit height and the eccentricity of the giant star sub-layer; step S103, determining the height of the upper side band and the height of the lower side band of the track band where the constellation system is located. According to one aspect of the present invention, in the step S1, a collision risk set is constructed, specifically including: Step S104, calculating the near-site and far-site heights of the satellites/fragments through loading the in-orbit satellite/fragment ephemeris data; Step S105, determining that satellites/fragments having collision puncture areas with the protected conste