A satellite cluster configuration design method based on heuristic search

Abstract

The present invention discloses a satellite cluster configuration design method based on heuristic search. The method includes: dividing a large-scale satellite cluster into groups according to the total number of satellites in the large-scale satellite cluster, and converting the problem of rapid in-orbit configuration design of the large-scale satellite cluster into a method for configuring the group center set and a method for configuring the satellite set within the group; regarding each group as a whole for design, and determining the heuristic search principle of the central point satellites of each group relative to the E / I vector by establishing the relationship between R max / R min and N; after completing the configuration of the central satellites of each group, determining the heuristic search principle of the satellites within each group relative to the E / I vector according to the mutual relationship among the passive safety distance r min , the maximum distance r max and the number K of satellites within the group. Furthermore, the purpose of rapid in-orbit design of the large-scale satellite cluster configuration is achieved. The present invention can be widely applied to the field of satellite cluster configuration design.

Description

Technical Field

[0001] The present invention relates to the technical field of large-scale satellite constellation configuration design, and particularly to a satellite constellation configuration design method based on heuristic search. Background Art

[0002] Due to the large number of satellites in large-scale satellite constellations, it is difficult for traditional configuration numerical optimization methods to solve the problem of rapid on-orbit design of large-scale satellite constellation configurations. Based on the relative E / I vector method, by grouping large-scale satellite constellations, the configuration design of the central satellites of each group and the configuration design of the satellites within the group are completed respectively, and then the rapid on-orbit design of large-scale satellite constellation configurations can be realized. Summary of the Invention

[0003] In view of the above-mentioned defects of the prior art, the technical problem to be solved by the present invention is to provide a satellite constellation configuration design method based on heuristic search, which can realize the rapid on-orbit cluster configuration design that cannot be completed by traditional numerical optimization methods.

[0004] To achieve the above object, the present invention provides a satellite constellation configuration design method based on heuristic search, including:

[0005] S1. According to the total number of satellites M in the large-scale satellite constellation, the large-scale satellite constellation is divided into N groups, then the number of satellites in each group except the central satellite of the constellation is K = (M - N - 1) / N, and the design constraint is that the passive safety distance between any two central satellites of the groups and between the central satellite of the group and the central satellite of the constellation is greater than or equal to R min , and the maximum relative distance between any two central satellites of the groups and between the central satellite of the group and the central satellite of the constellation is less than or equal to R max ;

[0006] S2. Each group is regarded as a whole for design, and the heuristic search configuration principle of the relative E / I vector of the central satellite of each group is determined by establishing the relationship between R max / R min and N;

[0007] S3. After determining the configuration of the central satellite of each group, it is known that each group contains K = (M - N - 1) / N internal satellites. Then, according to the mutual relationship between the passive safety distance r min , the maximum distance r max of the satellites within each group and the number K of the satellites within the group, the heuristic search configuration principle of the relative E / I vector of the satellites within each group is determined;

[0008] S4. After completing the rapid design of the relative E / I vectors of the central satellite and the intra-group satellites in each group, verify through mathematical simulation whether the obtained large-scale satellite cluster configuration meets the passive safety distance and maximum distance constraint conditions within and between groups. If it meets, output the design result; if not, change the heuristic search configuration principle of the relative E / I vectors between and within groups until a feasible solution is obtained.

[0009] Preferably, in step 2, by establishing the relationship between R max / R min and N, determine the heuristic search configuration principle of the relative E / I vectors of the central satellites of each grouping center, specifically:

[0010] If R max / R min is greater than N, the relative E / I vector is configured as much as possible along the vertical axis of the relative E / I vector two-dimensional diagram of the relative cluster center satellite, and the greater the degree that R max / R min is greater than N, the relative E / I vector is configured as much as possible along the vertical axis closer to the relative E / I vector two-dimensional diagram of the relative cluster center satellite, in order to minimize the fuel consumption for configuration maintenance;

[0011] If R max / R min is less than N, the relative E / I vector is configured as much as possible on both sides of the vertical axis of the relative E / I vector diagram, and the greater the degree that R max / R min is less than N, the relative E / I vector is configured closer to both sides of the vertical axis of the relative E / I vector diagram, in order to configure as many grouping center satellites as possible.

[0012] Preferably, in step 3, based on the mutual relationship between the passive safety distance r min of the satellites within each group, the maximum distance r max and the number K of the satellites within the group, determine the heuristic search configuration principle of the relative E / I vectors of the satellites within each group, specifically:

[0013] If r max / r min is greater than K, the relative E / I vector of the satellites within the group is configured as much as possible along the vertical axis of the relative E / I vector two-dimensional diagram with respect to the central satellite within the group, and the greater the degree that r max / r min is greater than K, the relative E / I vector is configured as much as possible along the vertical axis closer to the relative E / I vector diagram of the relative central satellite within the group, in order to minimize the fuel consumption for configuration maintenance;

[0014] If r max / r minLess than K, and as much as possible on both sides of the longitudinal axis of the relative E / I vector diagram with respect to the relative E / I vector, and r max / r min The greater the degree of being less than K, the closer the relative E / I vector is to being arranged on both sides of the longitudinal axis of the relative E / I vector diagram, in order to arrange as many in-group member satellites as possible.

[0015] Preferably, if a feasible solution cannot be obtained in step 4 all the time, it is necessary to consider whether the initially selected constraint conditions are unreasonable, and it is necessary to change the inter-group and intra-group safety distances and the maximum distance constraints until a feasible solution is obtained.

[0016] The beneficial effects of the present invention are:

[0017] The present invention divides a large-scale cluster according to the inter-satellite distance relationship, decomposes the problem of rapid on-orbit configuration design of a large-scale satellite cluster into the design and control problems of the in-group central satellite and the in-group internal satellites, and proposes a configuration design method of heuristic search, realizing the goal of rapid on-orbit design of the configuration of a large-scale satellite cluster.

[0018] The concept, specific structure and technical effects of the present invention will be further described below in conjunction with the drawings to fully understand the purpose, features and effects of the present invention. Description of the Drawings

[0019] Figure 1 is a flowchart of the steps of the grouping concept of the large-scale satellite cluster system of the present invention.

[0020] Figure 2 is a flowchart of the steps of configuring the in-group central satellite of the present invention.

[0021] Figure 3 is a flowchart of the steps of configuring the in-group satellites of the present invention. Detailed Embodiments

[0022] Embodiment 1

[0023] Such as Figure 1As shown in the figure, the difficulty in the rapid in-orbit design and analytical control of the large-scale satellite cluster configuration lies in how to decompose the configuration design and control of the large-scale satellite cluster into the dynamic modeling and mechanism analysis of several small computational quantum problems. Considering that both the passive safety distance and the maximum inter-satellite distance in the configuration design and control objectives of the cluster system are closely related to the relative distance between satellites, the large-scale cluster is grouped according to the inter-satellite distance relationship, which not only conforms to the relative motion law between satellites but also greatly simplifies the configuration design and control problems of the large-scale cluster. Therefore, a grouping method for large-scale satellite clusters is proposed. In the large-scale satellite cluster system, several grouping center satellites are set up. Taking this center satellite as the grouping center, its maximum influence area is set. Within its influence area, only the relative motion relationship between the satellites within the influence sphere is considered. In this way, the large-scale satellite cluster is naturally grouped through spatial constraints. By studying the motion of the grouping center satellite and the relative motion of the satellites within the group, the motion state of the entire system can be obtained. During the configuration design process, only the configuration of the center point and the rapid configuration design method within the group need to be solved to complete the rapid configuration design of the system. At the same time, for configuration maintenance and reconstruction, by restricting the motion range of the satellites during the maintenance and reconstruction process to be within the group, it can be ensured that only the satellites within the group are relevant to the maintenance and reconstruction of the satellites within the group, and have nothing to do with the motion of the grouped satellites. Furthermore, the scale of the maintenance and reconstruction control problem is greatly reduced, making it possible for the rapid in-orbit design and analytical control of the large-scale satellite cluster configuration.

[0024] The problem of rapid in-orbit configuration design of large-scale satellite clusters can be decomposed into the design and control problems of the grouping center satellites and the satellites within the group. As shown in the following figure, by decomposing in the relative E / I vector space and further mapping to the maximum region cluster in three-dimensional space. In this way, by proposing a grouping method, the problem of configuration design and control of large-scale satellite clusters is transformed into the design problems of the grouping center set and the configuration set of the satellites within the group, making the rapid in-orbit configuration design of large-scale satellite clusters feasible.

[0025] Embodiment 2

[0026] Based on the grouping concept, for a large-scale satellite cluster system containing M satellites, the design constraints are that the passive safety distance between the satellites within the group is r min , and the maximum distance is r max , the passive safety distance between the grouping center point satellites is R min , and the maximum distance is R max , then the problem of rapid in-orbit configuration design of large-scale satellite clusters can be transformed into the problem of giving the configuration of the grouping center satellites relative to the E / I vector and the configuration of the satellites within the group relative to the E / I vector. The solution to this problem is as follows:

[0027] First, determine the configuration method of the grouping center satellites relative to the E / I vector. Considering that the passive safety distance between any two satellites within the group should be less than or equal to rmin , so the group can be regarded as a whole for design. By establishing the relationship between R max / R min and N, the heuristic search principle of the central satellite of the group relative to the E / I vector is determined. If R max / R min is greater than N, the relative E / I vector is configured as much as possible along the vertical axis of the two-dimensional diagram of the relative E / I vector of the satellite relative to the central satellite of the cluster. And the greater the degree that R max / R min is greater than N, the relative E / I vector is configured as much as possible along the vertical axis of the two-dimensional diagram of the relative E / I vector closer to the central satellite of the cluster, in order to minimize the fuel consumption for formation maintenance. If R max / R min is less than N, the relative E / I vector is configured as much as possible on both sides of the vertical axis of the relative E / I vector diagram. And the greater the degree that R max / R min is less than N, the relative E / I vector is configured closer to both sides of the vertical axis of the relative E / I vector diagram, in order to configure as many central satellites of the group as possible.

[0028] After determining the configuration of the central satellites of each group, it can be known that each group contains K = (M - N - 1) / N internal satellites. Then, based on the mutual relationship of the passive safety distance r min , the maximum distance r max and the number of satellites K in the group, the heuristic search configuration principle of the relative E / I vector of the satellites in each group is determined. If r max / r min is greater than K, the relative E / I vector of the satellites in the group is configured as much as possible along the vertical axis of the two-dimensional diagram of the relative E / I vector relative to the central satellite in the group. And the greater the degree that r max / r min is greater than K, the relative E / I vector is configured as much as possible along the vertical axis of the relative E / I vector diagram closer to the central satellite in the group, in order to minimize the fuel consumption for formation maintenance. If r max / r min is less than K, the relative E / I vector is configured as much as possible on both sides of the vertical axis of the relative E / I vector diagram. And the greater the degree that r max / r min is less than K, the relative E / I vector is configured closer to both sides of the vertical axis of the relative E / I vector diagram, in order to configure as many member satellites within the group as possible.

[0029] After completing the rapid design of the relative E / I vectors of each group of central satellites and intra-group satellites, verify through mathematical simulation whether the obtained large-scale satellite cluster configuration meets the passive safety distance and maximum distance constraint conditions for intra-group and inter-group. If it meets, output the design result. If it does not meet, change the heuristic search configuration principle of the relative E / I vectors between groups and within groups until a feasible solution is obtained. If a feasible solution cannot be obtained all the time, it is necessary to consider whether the initial selection of constraint conditions is unreasonable, and change the safety distance and maximum distance constraints between groups and within groups until a feasible solution is obtained.

[0030] The preferred specific embodiments of the present invention have been described in detail above. It should be understood that those of ordinary skill in the art can make many modifications and variations according to the concept of the present invention without creative labor. Therefore, all technical solutions that can be obtained by those skilled in the art in this technical field based on the concept of the present invention through logical analysis, reasoning or limited experiments on the basis of the prior art should be within the protection scope determined by the claims.

Claims

1. A satellite cluster configuration design method based on heuristic search, characterized in that, Including: S1. According to the total number of satellites M in the large-scale satellite cluster, the large-scale satellite cluster is divided into N groups. Then, the number of satellites in each group except the central satellite of the cluster is K = (M - N - 1) / N. The design constraint is that the passive safety distance between the central satellites of any two groups and between the central satellite of the group and the central satellite of the cluster is greater than or equal to the passive safety distance R between the central satellites of the groups min , and the maximum relative distance between the central satellites of any two groups and between the central satellite of the group and the central satellite of the cluster is less than or equal to the maximum distance R between the central satellites of the groups max ; S2. Treat each group as a whole for design, and determine the heuristic search configuration principle of the satellite at the center point of each group relative to the E / I vector by establishing the relationship between R max / R min and N; S3. After completing the configuration of each group's central satellite, it can be known that each group contains K = (M - N - 1) / N internal satellites. Then, based on the passive safety distance r of the satellites within each group min , the maximum distance r max and the mutual relationship of the number K of satellites within the group to determine the heuristic search configuration principle of the satellites within each group relative to the E / I vector; S4. After completing the rapid design of the relative E / I vectors of each group of central satellites and intra-group satellites, verify through mathematical simulation whether the obtained large-scale satellite cluster configuration meets the passive safety distance and maximum distance constraint conditions within and between groups. If it meets, output the design result; If it does not meet, change the heuristic search configuration principle of the relative E / I vectors between and within groups until a feasible solution is obtained.

2. The satellite cluster configuration design method based on heuristic search according to claim 1, characterized in that: In step S2, by establishing the relationship between R max / R min and N, the heuristic search configuration principle of each grouped center point satellite relative to the E / I vector is determined, specifically: If R max / R min is greater than N, the relative E / I vector is arranged as close as possible along the vertical axis of the two-dimensional diagram of the relative E / I vector with respect to the satellite at the relative cluster center, and the greater the degree that R max / R min is greater than N, the relative E / I vector is arranged as close as possible along the vertical axis of the two-dimensional diagram of the relative E / I vector closer to the satellite at the relative cluster center, so as to minimize the fuel consumption for formation maintenance as much as possible; If R max / R min is less than N, the relative E / I vectors are arranged as much as possible on both sides of the longitudinal axis of the relative E / I vector diagram, and the greater the degree that R max / R min is less than N, the relative E / I vectors are arranged closer to both sides of the longitudinal axis of the relative E / I vector diagram, so as to arrange as many grouping center satellites as possible.

3. The satellite cluster configuration design method based on heuristic search according to claim 1, characterized in that: In step S3, according to the passive safety distance r of satellites within each group min , the maximum distance r max and the mutual relationship of the number K of satellites within the group to determine the heuristic search configuration principle of the satellites within each group relative to the E / I vector, specifically: If r max / r min is greater than K, the relative E / I vectors of the satellites within the group are arranged as much as possible along the vertical axis of the relative E / I vector two-dimensional diagram with respect to the relative E / I vector of the central satellite within the group, and r max / r min is greater than K to a greater extent, the relative E / I vectors are arranged as much as possible along the vertical axis closer to the relative E / I vector diagram of the relative central satellite within the group, in order to minimize the fuel consumption for formation maintenance as much as possible; If r max / r min is less than K, the relative E / I vectors are arranged as far as possible on both sides of the longitudinal axis of the relative E / I vector diagram, and the greater the degree that r max / r min is less than K, the closer the relative E / I vectors are to being arranged on both sides of the longitudinal axis of the relative E / I vector diagram, in order to arrange as many in-group member satellites as possible.

4. The satellite cluster configuration design method based on heuristic search according to claim 1, characterized in that: In step S4, if a feasible solution cannot be obtained all the time, it is necessary to consider whether the initial constraint conditions are unreasonably selected, and change the safety distance and maximum distance constraints between and within groups until a feasible solution is obtained.

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