中国空间科学技术2024，Vol.44Issue(4)：102-110,9.DOI:10.16708/j.cnki.1000-758X.2024.0061
大椭圆停泊轨道出发的小行星防御航天器轨道优化
Orbit optimization for an asteroid-defense spacecraft departing from large elliptical parking orbit
王杰 1钟子凯 1袁浩 1宋海波1
作者信息
- 1. 国防科技大学空天科学学院,长沙 410073
- 折叠
摘要
Abstract
Kinetic impact is a means to deflect near-Earth asteroids(NEAs)and to reduce the risk of Earth being impacted by asteroids.An orbit optimization method for spacecraft departing from a large elliptical Earth parking orbit is proposed.Based on genetic algorithm,an optimization model is constructed,which takes the maximum deflection distance of the asteroid as the objective and considers nonlinear constraints on transfer time and fuel of spacecraft.Taking the asteroid 2019 PDC as the object,the genetic algorithm is used to optimize the global optimal solution of the departure date and transfer time of the spacecraft,and to calculate parameters of the large elliptical Earth parking orbit,Earth escape orbit and interplanetary transfer orbit.Meanwhile,Pork-chop plot of the asteroid deflection distance to departure date and transfer time is obtained using the traversing method,which verifies the effectiveness of the optimization algorithm.Results show that the proposed kinetic impact scenario and orbit optimization method can effectively deal with asteroids with diameters of 100 meters and a warning time of several years.The orbit design method and defense scenario proposed can provide a reference for NEAs defense,and lay a foundation for further precise design of spacecraft orbit parameters and implementation of engineering in-orbit verification.关键词
近地小行星/动能撞击/轨道优化/地球停泊轨道/遗传算法/小行星偏转Key words
near-Earth asteroid/kinetic impact/orbit optimization/Earth parking orbit/genetic algorithm/asteroid deflection分类
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王杰,钟子凯,袁浩,宋海波..大椭圆停泊轨道出发的小行星防御航天器轨道优化[J].中国空间科学技术,2024,44(4):102-110,9.
