A method of geo direct fixed-point launch orbit optimization

An optimization method and orbit technology, which can be applied to instruments, adaptive control, control/regulation systems, etc., can solve the problems of optimizing the design of complex trajectory of the launch orbit, and achieve the goal of improving the quality of entering orbit, improving the efficiency of launching, and reducing the cost of launching. Effect

Active Publication Date: 2022-07-29
BEIJING INST OF ASTRONAUTICAL SYST ENG
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Problems solved by technology

[0003] Due to the latitude limitation of the launch site, the GTO launch orbit is usually a launch orbit with a parking orbit. The optimal design of the launch orbit is a large-scale and complex trajectory optimization design problem.

Method used

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  • A method of geo direct fixed-point launch orbit optimization
  • A method of geo direct fixed-point launch orbit optimization
  • A method of geo direct fixed-point launch orbit optimization

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Embodiment Construction

[0072] The method of the present invention includes two processes of ballistic iterative calculation and NSGA-II launch trajectory optimization, wherein the ballistic iterative calculation process is included in the optimization process, which will be described in detail below.

[0073] like figure 2 As shown, a GEO direct fixed-point launch orbit optimization method includes the following steps:

[0074] Step 1. NSGA-II optimization parameter setting. The number of optimization variables Nvar is set to 4 in the method of the present invention; the number of optimization objective functions Func is set to 2 in the method of the present invention; the population size is Npop, and the method of the present invention is set to 80; ; Crossover rate Pcr and crossover distribution index dic, mutation rate Pmut and mutation distribution index dim.

[0075] Step 2: Optimize the setting of the variable value range. Considering the carrying capacity of the basic stage, set the value...

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Abstract

A GEO direct fixed-point launch orbit optimization method of the present invention includes the following steps: 1) setting NSGA-II optimization parameters; 2) setting the value range of optimization variables; 3) generating an initial population of launch orbit calculation parameter conditions; 4) generating launch orbit calculation Result population; 5) Generation of offspring population; 6) Generation of offspring population; 7) Next generation parent population; 8) Judgment of genetic termination.

Description

technical field [0001] The invention relates to an upper-level orbit design optimization method used for the launch of spacecraft such as satellites. Background technique [0002] Geostationary Orbit (GEO) satellite launch orbit design and optimization can improve the efficiency of space launch missions. In the conceptual design stage, determining the optimal overall parameters based on orbit optimization can maximize the design potential; in the actual flight orbit design stage, orbit optimization design can effectively improve payload quality and reduce launch costs. Most of the domestic experts and scholars' research is generally indirect access to orbit of GEO satellite launch orbit, and it is divided into two research modes: Geosynchronous Transfer Orbit (GTO) optimization for launch vehicle launch and GEO satellite fixed-point orbit change optimization. [0003] Due to the latitude limitation of the launch site, the GTO launch orbit is usually a launch orbit with a pa...

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Application Information

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Patent Type & AuthorityPatents(China)
IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor王传魁陈益周文勇王国辉焉彬张利宾郑莉莉叶成敏杜大程张苏闽肖泽宁冯荣宫长辉陈佳晔韩冬
OwnerBEIJING INST OF ASTRONAUTICAL SYST ENG