| 基于比例导引的空间交会寻的段飞行任务设计 |
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| 引用本文： | 李九人,李海阳,陈磊,唐国金.基于比例导引的空间交会寻的段飞行任务设计[J].飞行力学,2009,27(4). |
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| 作者姓名： | 李九人 李海阳 陈磊 唐国金 |
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| 作者单位： | 国防科技大学,航天与材料工程学院,湖南,长沙,410073 |
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| 摘 要： | 比例导引涉及的参数测量和控制手段简便,常被用作空间拦截的制导算法。基于该制导算法,在相对运动参数测量条件较弱的情况下,对空间交会对接寻的段飞行任务进行了设计。采用C-W制导算法,对寻的段飞行任务的标称轨道进行了设计。推导了基于固定推力发动机的比例导引轨道控制模型,并利用该模型对寻的段轨道进行了控制。通过仿真计算验证了所给出的比例导引模型的有效性。
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| 关 键 词： | 空间交会 寻的段 标称轨道 比例导引 |
Homing Mission Design of Space Rendezvous Based on Proportional Guidance |
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| LI Jiu-ren,LI Hai-yang,CHEN Lei,TANG Guo-jin.Homing Mission Design of Space Rendezvous Based on Proportional Guidance[J].Flight Dynamics,2009,27(4). |
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| Authors: | LI Jiu-ren LI Hai-yang CHEN Lei TANG Guo-jin |
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| Institution: | College of Aerospace and Material Engineering;NUDT;Changsha 410073;China |
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| Abstract: | The proportional guidance is always used in space intercept because its parameters measurement and control are convenient.Based on proportional guidance law,the homing mission design of RVD is researched on the suppose that the condition of parameters measurement is bad.The normal orbit in the homing phase is designed based on a C-W guidance law.The constant thrust proportional guidance is deduced,and which is used for the orbit control in the homing phase.The efficiency of the proportional guidance law pro... |
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| Keywords: | space rendezvous homing phase normal orbit proportional guidance |
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