| 轨道轰炸飞行器过渡段轨道设计与制导 |
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| 引用本文： | 胡正东,郭才发,曹渊,蔡洪.轨道轰炸飞行器过渡段轨道设计与制导[J].固体火箭技术,2009,32(5). |
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| 作者姓名： | 胡正东 郭才发 曹渊 蔡洪 |
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| 作者单位： | 1. 陆军武器装备体系研究国防科技重点实验室,北京,100012;国防科技大学,航天与材料工程学院,长沙,410073
2. 国防科技大学,航天与材料工程学院,长沙,410073 |
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| 摘 要： | 针对轨道轰炸飞行器(OBV)的过渡段轨道设计与制导技术进行了讨论.在初始点位置、再入点位置和再入角固定的前提下,根据冲量假设和二体理论设计了固定时间转移轨道,其实质在于制动点位置和制动速度的确定.为了消除设计偏差,提出了一种基于虚拟再入点补偿的有限推力制导方案,并简要分析了关机点参数的选取原则.对于耗尽关机的动力系统,通过运用能量管理技术实现了多余燃料的耗散.仿真结果验证了上述方法的有效性.
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| 关 键 词： | 轨道轰炸飞行器 固定时间转移轨道 虚拟再入点 有限推力制导 能量管理 |
Transition trajectory planning and guidance for orbital bombing vehicle |
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| HU Zheng-dong,GUO Cai-fa,CAO Yuan,CAI Hong.Transition trajectory planning and guidance for orbital bombing vehicle[J].Journal of Solid Rocket Technology,2009,32(5). |
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| Authors: | HU Zheng-dong GUO Cai-fa CAO Yuan CAI Hong |
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| Institution: | HU Zheng-dong1,2,GUO Cai-fa2,CAO Yuan2,CAI Hong2(1.National Key Laboratory of Sciece and Technology on Army Weapon Equipment System-of-system Reseach,Beijing 100012,China,2.College of Aerospace and Material Engineering,National University ofDefence Technology,Changsha 410073,China) |
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| Abstract: | The technique of transition trajectory planning and guidance for orbital bombing vehicle was discussed in this paper.On condition that initial location,reentry location and velocity inclination were constrained,a time-fixed transfer orbit was designed based on impulse hypothesis and two-body theory,which is substantial for deciding braking position and braking velocity.Then a scheme of limited thrust guidance with virtual reentry point compensation was put forward to eliminate planning error and the selecti... |
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| Keywords: | orbital bombing vehicle(OBV) time-fixed transfer orbit virtual reentry point limited thrust guidance energy management |
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