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A method and system for satellite on-orbit activity planning

A planning scheme and satellite technology, which is applied in the field of satellite remote sensing and can solve the problems of long computing time and low computing efficiency.

Active Publication Date: 2020-10-27
NAT UNIV OF DEFENSE TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The invention proposes a satellite on-orbit activity planning method to overcome the defects of low calculation efficiency and long operation time in the prior art. The method is based on priority rules and is an approximate method, combined with the satellite on-orbit activity planning problem Based on the actual engineering constraints in the satellite, a set of priority heuristic rules is designed based on the domain knowledge of satellite on-orbit activity planning, and finally a satisfactory planning scheme is obtained through independent discrete event simulation and iterative optimization process, taking into account high computational efficiency and planning solution quality

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  • A method and system for satellite on-orbit activity planning

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Embodiment 1

[0027] like figure 1 As shown, the embodiment of the present invention proposes a satellite on-orbit activity planning method, including the following steps:

[0028] S1, according to the numerical constraints of on-orbit resources and the logical constraints between on-orbit activities, a real-number nonlinear programming model is established to describe the satellite on-orbit activity planning problem;

[0029] In the satellite on-orbit activity planning problem, let M={A 1 ,A 2 ,...,A k ,...,A m} represents the set of m on-orbit activities, B t Denotes the set of activities executed in parallel on the satellite at time t, A l Indicates any activity sequence in the set of activity sequences formed by sequential logical relations. In order to make the entire time span (Makespan) as small as possible when all activities complete execution, the start time t of each activity is selected k (k=1,2,...,m) as design variables.

[0030] A real-number nonlinear programming mod...

Embodiment 2

[0107] The steps of this embodiment are basically the same as those of Embodiment 1, the main difference being that the initial parameters input in step S00 are different, and other steps are the same as those of Embodiment 1.

[0108] S00, input parameters, input the following extended on-orbit activity scenario parameters:

[0109] Compared with Table 1, Table 3 has expanded 29 new on-orbit activities, and there are a total of 61 on-orbit activities in the seven subsystems of the satellite. At this time, the maximum power consumption of the electric power resource that the satellite system can provide is 12W.

[0110] 61 on-orbit activity sets in the second embodiment of table 3

[0111]

[0112] The implementation steps of S01-S04 are exactly the same as those of the first embodiment above.

[0113] In this embodiment, the calculation results are as follows:

[0114] The value of objective function in the embodiment two of table 4

[0115]

[0116] Similarly, the ...

Embodiment 3

[0118] The steps of this embodiment are basically the same as those of Embodiment 1, the main difference being that the initial parameters input in step S00 are different, and other steps are the same as those of Embodiment 1.

[0119] S00, input parameters, input the scenario parameters of the on-orbit activities of the following expansion subsystems:

[0120]Compared with Table 3, Table 5 adds a new subsystem and continues to expand 19 on-orbit activities. There are a total of 80 on-orbit activities in the eight subsystems of the satellite. At this time, the maximum power consumption of the electric power resources that the satellite system can provide is still 12W.

[0121] 80 on-orbit activity sets in the third embodiment of Table 5

[0122]

[0123]

[0124] The implementation steps of S01-S04 are exactly the same as those of the second embodiment above.

[0125] In this embodiment, the calculation result is as follows:

[0126] The value of objective function in...

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Abstract

The invention discloses a method and a system for planning satellite on-orbit activities. The method comprises the following steps: 1) a mathematical model considering practical engineering constraints being established to mathematically describe the problem of satellite on-orbit activities planning; 2) establishing the domain knowledge model of satellite in-orbit activity planning based on predicate logic and designing a set of priority heuristic rules combined with domain knowledge; 3) according to the guidance of priority rules, an independent discrete event simulation being carried out toobtain a planning scheme that satisfies various constraints; 4) randomly adjusting the weight of each influence factor in the priority rule, and iteratively search for the better programming scheme with good performance. The invention can quickly obtain a satisfactory planning scheme of the satellite in-orbit activity planning problem with very small calculation cost in a very short time, and hasthe advantages of high calculation efficiency and the quality of the planning solution, correct and reasonable solution method, fast and effective calculation process, good applicability to practicalengineering tasks and the like.

Description

technical field [0001] The invention relates to the technical field of satellite remote sensing, in particular to a fast heuristic method based on priority rules for solving satellite on-orbit activity planning problems. Background technique [0002] As the geostationary orbit (hereinafter referred to as GEO) plays an increasingly important role in the fields of communication, remote sensing, and navigation, it is of great significance to use low-orbit (hereinafter referred to as LEO) satellite formations to monitor the beams of GEO satellites and to grasp the use of their frequency resources. Significance. In the GEO satellite beam monitoring mission, the successful execution of many operating instructions on the LEO satellite is required to ensure the smooth completion of the entire on-orbit mission. The basic operating instructions that can be directly executed on LEO satellites are collectively referred to as satellite in-orbit activities. Guided by certain planning go...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06Q10/06G06F30/20
CPCG06Q10/06315G06F30/20
Inventor 罗亚中梁军朱阅訸牟帅
Owner NAT UNIV OF DEFENSE TECH