近地小行星撞击偏转与评估轨迹协同优化  

Collaborative Optimization of Evaluation Trajectory and Impact Deflection for Near Earth Asteroid

作　　者：李海洋 尤伟 陈晓[1,2] 段晓闻 王海鹏[1,2] 彭玉明 LI Haiyang;YOU Wei;CHEN Xiao;DUAN Xiaowen;WANG Haipeng;PENG Yuming(Deep Space Exploration Laboratory,Hefei 230026,China;Shanghai Institute of Satellite Engineering,Shanghai 201109,China)

机构地区：[1]深空探测实验室,合肥230026 [2]上海卫星工程研究所,上海201109

出　　处：《深空探测学报(中英文)》2024年第6期551-558,共8页Journal Of Deep Space Exploration

基　　金：国家自然科学基金(12102265,U21B2050);上海市青年科技英才扬帆计划(21YF1446100);深空探测实验室前沿科研计划(GC04FY1003ZC3ZT-2325);上海航天青年基金(KJW-JT-QNKYJJ-2022-3)。

摘　　要：针对一箭双星形式一次实现对近地小行星撞击与伴飞问题,提出了两器轨迹协同优化模型,以两器加权速度增量最小为优化目标,给出了一箭双星发射、先伴飞再撞击的两器飞行轨迹优化框架,考虑发射C3、撞击相对速度、撞击太阳角度等约束,撞击器分别采用直接转移与地球借力两种转移形式。针对2025年发射窗口对15个候选小行星分别进行优化,仿真结果表明工程可行,可为小行星防御演示验证任务论证提供理论参考。Based on the problem of impacting and flying alongside a near-Earth asteroid with a single launch vehicle,a model for the coordinated optimization of the trajectories of two is proposed.The optimization objective is to minimize the weighted velocity increment of the two spacecraft.An optimization framework for the flight trajectories of the two spacecraft,which are by a single launch vehicle and fly alongside each other before impacting,is given.Constraints such as launch C3,the impact relative velocity,and the impact sun angle are considered.The impact probe can use two transfer forms,one is direct transfer and the other is Earth flyby.This paper has optimized 15 candidate asteroids in the 2025 window and provided feasible engineering design solutions.The results can provide theoretical reference for China's asteroid defense mission.

关 键 词：小行星防御 动能撞击 轨迹优化 一箭双星 

分 类 号：V448[航空宇航科学与技术—飞行器设计]