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Method and device for generating synchronous orbit satellite co-location strategy

A geostationary orbit satellite and strategy technology, applied in vehicle position/route/altitude control, 3D position/channel control, instruments, etc., can solve problems such as poor reliability, influence of ground test station positioning accuracy, etc., to improve relative position accuracy Effect

Pending Publication Date: 2020-08-18
中国卫通集团股份有限公司
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AI Technical Summary

Problems solved by technology

[0004] The technical problem solved by this application is: the reliability of the geostationary orbit satellite strategy generated in the prior art is poor and it is easily affected by the positioning accuracy of the ground test station

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  • Method and device for generating synchronous orbit satellite co-location strategy
  • Method and device for generating synchronous orbit satellite co-location strategy
  • Method and device for generating synchronous orbit satellite co-location strategy

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Embodiment Construction

[0059] Below in conjunction with accompanying drawing of description, the generation method of a kind of geostationary orbit satellite co-location strategy provided by the embodiment of the present application is described in further detail, and the specific implementation of the method may include the following steps (method flow is as follows: figure 1 shown):

[0060] Step 101, determine the system parameters of each geostationary orbit satellite at any fixed orbit position, and determine the longitude control interval of each geostationary orbit satellite according to the system parameters.

[0061] Specifically, in the solution provided by the embodiment of the present application, there are multiple geosynchronous orbits, and there are multiple geosynchronous orbit satellites operating on any fixed orbital position. System parameters include fixed-point longitude of each geostationary satellite, size of control box, orbit control cycle, orbit determination accuracy of gr...

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Abstract

The invention discloses a synchronous orbit satellite co-location strategy generation method and device, and the method comprises the steps: determining the system parameters of each synchronous orbitsatellite at any fixed point orbit position, and determining the longitude control interval of each synchronous orbit satellite according to the system parameters; determining an eccentricity ratio control interval of each synchronous orbit satellite according to the longitude control interval, and determining an eccentricity ratio vector according to the eccentricity ratio control interval; anddetermining an inclination angle vector and an included angle between the eccentricity ratio vector and the inclination angle vector, and generating a co-location strategy of the synchronous orbit satellite according to the included angle and a preset inclination angle isolation strategy. According to the invention, the technical problems that the reliability of the generated synchronous orbit satellite strategy in the prior art is poor and the synchronous orbit satellite strategy is easily influenced by the positioning precision of the ground test station are solved.

Description

technical field [0001] The present application relates to the technical field of on-orbit management of spacecraft, and in particular to a method and device for generating a geostationary orbit satellite co-location strategy. Background technique [0002] With the increasing number of geostationary orbit satellites, orbit resources are becoming more and more scarce. In order to save orbit resources, satellite operators will operate and manage two or more satellites at the same fixed longitude, that is, geosynchronous orbit satellites are co-located. How to ensure the safe operation of multiple satellites at the same fixed point longitude without the risk of collision is particularly important. [0003] In order to avoid collisions between multiple satellites, it is not only necessary to consider the problem of how to place multiple geosynchronous orbit satellites in a fixed-point orbital position, that is, the geosynchronous orbit satellite co-location strategy, wherein the ...

Claims

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Application Information

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IPC IPC(8): G05D1/10G08G9/02
CPCG05D1/104G08G9/02Y02D30/70
Inventor 许珩杨学猛赵悦张东旭
Owner 中国卫通集团股份有限公司
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