GEO direct fixed-point launching orbit optimization method

An optimization method and orbit technology, which can be applied to instruments, adaptive control, control/regulation systems, etc., and can solve problems such as optimization design of complex orbits of launch orbits.

Active Publication Date: 2020-10-23
BEIJING INST OF ASTRONAUTICAL SYST ENG
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AI Technical Summary

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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  • GEO direct fixed-point launching orbit optimization method
  • GEO direct fixed-point launching orbit optimization method
  • GEO direct fixed-point launching orbit optimization method

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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] Such as figure 2 As shown, a GEO direct fixed-point launch trajectory optimization method includes the following steps:

[0074] Step 1: NSGA-II optimizes parameter settings. The number of optimization variables Nvar is set, and the inventive method is set to 4; the optimized objective function number Func, the inventive method is set to 2; the population scale is Npop, and the inventive method is set to 80; the evolution algebra is Ngen, set to 10 ; Crossover rate Pcr and crossover distribution index dic, mutation rate Pmut and variation distribution index dim.

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

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Abstract

The invention discloses a GEO direct fixed-point launching orbit optimization method. The GEO direct fixed-point launching orbit optimization method comprises the following steps of: 1) setting NSGA-II optimization parameters; (2) setting an optimal variable value range; (3) generating a launch orbit calculation parameter condition initial population, (3) generating a launch orbit calculation result population; (5) generating a parent generation population; (6) generating a filial generation population; (7) generating a next parent generation population; and (8) judging genetic termination.

Description

technical field [0001] The invention relates to an upper-level orbit design optimization method used for launching satellites and other spacecraft. Background technique [0002] Geostationary Orbit (GEO, Geostationary Orbit) 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 the payload quality and reduce the launch cost. Most domestic experts and scholars research on indirect access to GEO satellite launch orbit, and can be 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...

Claims

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Application Information

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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