Navigation constellation on-orbit backup scheme optimization design method

An optimized design and backup technology, applied in the field of navigation constellations, can solve problems such as poor service performance of operating devices, and achieve the effect of enhancing stability and robustness and improving service performance.

Pending Publication Date: 2020-09-18
PLA PEOPLES LIBERATION ARMY OF CHINA STRATEGIC SUPPORT FORCE AEROSPACE ENG UNIV
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Problems solved by technology

[0003] The purpose of this application is to provide an optimal design method for the on-orbit backup scheme of the navigation constellation

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  • Navigation constellation on-orbit backup scheme optimization design method
  • Navigation constellation on-orbit backup scheme optimization design method
  • Navigation constellation on-orbit backup scheme optimization design method

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[0042] In order to make the objectives, technical solutions, and beneficial effects of the present invention clearer, the following further describes the present invention in detail with reference to the accompanying drawings and embodiments. It should be noted that the specific embodiments described here are only used to explain the present invention, but not to limit the present invention.

[0043] figure 1 It is a flowchart of the optimization design method for the on-orbit backup scheme of the navigation constellation of the present invention.

[0044] The optimization design method of the navigation constellation on-orbit backup scheme of the present invention includes:

[0045] Step 1. Determine the optimization variables, objective function and constraint conditions of the orbital position optimization model of the on-orbit backup star according to the parameters of the navigation constellation, specifically:

[0046] Taking the orbit position of the on-orbit backup star on eac...

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Abstract

The invention discloses a navigation constellation on-orbit backup scheme optimization design method. The optimization design method comprises the following steps: determining an optimization variable, an objective function and a constraint condition of an orbit position optimization model of an on-orbit backup satellite according to parameters of the navigation constellation; based on the orbit position optimization model of the on-orbit backup satellite, obtaining the optimal orbit position of the on-orbit backup satellite by using a multi-objective optimization algorithm; and in combinationwith the optimal orbit position of the on-orbit backup satellite, determining a replacement optimization model of the on-orbit backup satellite for replacing the faulty satellite, and determining anoptimal replacement method according to the replacement optimization model. According to the invention, the service performance of the navigation constellation can be remarkably improved, the stability and robustness of the navigation constellation are enhanced, and replacement of the faulty satellite can be completed with low energy in a short time.

Description

technical field [0001] The invention relates to an optimization design method for an on-orbit backup scheme of a navigation constellation, which belongs to the technical field of navigation constellations. Background technique [0002] In order to meet the strict requirements of the system on availability, continuity and integrity, the navigation constellation usually deploys several backup satellites in space. If a satellite in the constellation fails, it will be replaced by the on-orbit backup satellite. For example, the GPS (Global Positioning System) constellation deploys backup satellites near the satellite with the highest failure probability to form a "satellite pair", so that when one of the satellites fails, the backup satellite can achieve alignment through orbital maneuvering in a short period of time. Rapid replacement of failed satellites, thereby reducing the impact on users. The optimal design of the on-orbit backup scheme is related to the service performanc...

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Application Information

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IPC IPC(8): G06F30/15G06F30/20G01S19/03
CPCG01S19/03G06F30/15G06F30/20
Inventor 胡敏王许煜赵玉龙李玖阳肖龙龙李菲菲张学阳云朝明
Owner PLA PEOPLES LIBERATION ARMY OF CHINA STRATEGIC SUPPORT FORCE AEROSPACE ENG UNIV
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