Optimization of attacking orbit for interception satellite with low continuous thrust

ZHAO Lin; LI Yu-ling; LIU Yuan; HAO Yong; WANG Yi-peng

doi:10.3788/OPE.20162401.0178

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Optimization of attacking orbit for interception satellite with low continuous thrust

更新时间：2020-08-13

- Optimization of attacking orbit for interception satellite with low continuous thrust
- Optics and Precision Engineering Vol. 24, Issue 1, Pages: 178-186(2016)
- 作者机构：
  
  哈尔滨工程大学自动化学院,黑龙江哈尔滨,150001
- 作者简介：
- 基金信息：
- DOI：10.3788/OPE.20162401.0178
  CLC： V19;TJ861
- Received：18 August 2015，
  
  Revised：12 November 2015，
  
  Published：25 January 2016
- 稿件说明：
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赵琳, 李玉玲, 刘源等. 连续小推力拦截卫星攻击轨道的优化[J]. 光学精密工程, 2016,24(1): 178-186

ZHAO Lin, LI Yu-ling, LIU Yuan etc. Optimization of attacking orbit for interception satellite with low continuous thrust[J]. Editorial Office of Optics and Precision Engineering, 2016,24(1): 178-186
赵琳, 李玉玲, 刘源等. 连续小推力拦截卫星攻击轨道的优化[J]. 光学精密工程, 2016,24(1): 178-186 DOI： 10.3788/OPE.20162401.0178.

ZHAO Lin, LI Yu-ling, LIU Yuan etc. Optimization of attacking orbit for interception satellite with low continuous thrust[J]. Editorial Office of Optics and Precision Engineering, 2016,24(1): 178-186 DOI： 10.3788/OPE.20162401.0178.

摘要

针对空间攻防中目标卫星周围由若干小卫星以编队形式绕飞的情况

研究了拦截卫星的轨道规划问题。以配备电推进的连续推力拦截卫星为对象

提出了基于遗传算法的拦截卫星攻击轨道寻优方法。以编队小卫星的动态防御模型作为环境模型

根据进攻轨道安全性和节省燃料的要求建立综合适应度函数

并对算法的编码方式、选择算子、交叉算子和变异算子进行了设计。基于MATLAB平台进行了仿真试验

结果表明

拦截卫星于650 s时击中目标卫星

总开机时间为410 s。提出的算法能够寻找到最优攻击路径

并且算法收敛性速度快

稳定性高。与同类的研究方法相比

该算法能够有效减少火箭开机时间

进而减轻了卫星在轨道机动过程中姿态调整的任务负荷。

Abstract

The attacking orbits of interception satellites were explored when target satellites flied with several small satellites in concomitant formation in anti-satellite combination. By taking an interception satellite with a low continuous thrust to transfer orbit for a researching object

an attacking orbit optimization method based on genetic algorithm was proposed. A dynamic defending model of the small formation satellite was taken as environment model

and comprehensive fitness function was constructed according to the requirements of orbit safety and fuel saving. Then

the coding method

selection operator

crossover operator and the mutation operator were designed for proposed algorithm. A simulation experiment was performed on the MATLAB platform. The simulation results show that the interception satellite hits the target satellite at 650 s

spending 410 s. The algorithm proposed searches an optimal attacking path and has a good convergence and stability. As compared with the same kind of optimization method

this algorithm effectively reduces the boot time of rockets

and reduces the task loads of orbit maneuver attitude control of the interception satellite.

关键词

Keywords

references

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