Rapid target access calculation method based on satellite orbit characteristics
A technology of satellite orbit and calculation method, applied in the field of satellite mission planning, can solve the problems of complicated acquisition of target time window and difficult implementation of engineering
Pending Publication Date: 2020-07-10
SPACE STAR TECH CO LTD
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[0005] The purpose of the present invention is to provide a fast target access calculation method based on satellite orbit characteristics, which aims to solve the technical problems of complex acquisition of time windows for ground targets by existing satellites and difficult engineering implementation.
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[0044] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.
[0045] In addition, the descriptions involving "first", "second" and so on in the present invention are only for descriptive purposes, and should not be understood as indicating or implying their relative importance or implicitly indicating the number of indicated technical features. Thus, the features defined as "first" and "second" may explicitly or implicitly include at least one of these features. In addition, the technical solutions of the variou...
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The invention is applicable to the technical field of satellite mission planning, and discloses a rapid target access calculation method based on satellite orbit characteristics. The method comprisesthe following steps: obtaining an orbit distribution rule of a satellite in a complete orbit regression period according to the orbit characteristics of the satellite; calculating all orbit daily identifiers of the satellite in a complete orbit regression period; selecting a first orbit day identifier; judging whether the first track daily identifier can access the first target or not; obtaining ahistorical access calculation result of the satellite to the second target, and obtaining a corresponding relationship between a second orbit daily identifier corresponding to the historical access calculation result and the historical access calculation result; and determining an access calculation result corresponding to the first orbit day identifier. According to the obtaining method, the obtaining speed is greatly increased, all accessible obtaining results of the satellites for the targets in a complete orbit regression period can be quickly obtained, and the obtaining speed of the obtaining method is far greater than that of a conventional obtaining method under the conditions that the number of the satellites is large and the number of the targets is large.
Description
technical field [0001] The invention relates to the technical field of satellite mission planning, in particular to a fast target access calculation method based on satellite orbit characteristics. Background technique [0002] With the increasing number of satellites in orbit in my country, users' demand for multi-satellite and multi-objective missions is gradually increasing. Compared with the planning stage of observation tasks, in the planning stage, the accuracy requirements for satellite observation visibility are not very high, but the requirements for satellite observation timeliness are very high, and the visibility information of satellites to targets needs to be obtained quickly. [0003] The traditional method to obtain the time window of the satellite to the ground target is to track and sample the sub-satellite point data, and judge the visible time window of the satellite to the target at each sampling point successively. Although the obtained results are acc...
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Login to View More IPC IPC(8): G06F17/10
CPCG06F17/10Y02D30/70
Inventor 齐昕浒胡志杰陈彦斌陈浩一杨宏亮李媛博陈元伟李集林
Owner SPACE STAR TECH CO LTD