轨道轰炸飞行器过渡段轨道设计与制导  

Transition trajectory planning and guidance for orbital bombing vehicle

作　　者：胡正东[1,2] 郭才发[2] 曹渊[2] 蔡洪[2] 

机构地区：[1]陆军武器装备体系研究国防科技重点实验室,北京100012 [2]国防科技大学航天与材料工程学院,长沙410073

出　　处：《固体火箭技术》2009年第5期473-477,491,共6页Journal of Solid Rocket Technology

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。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 selection of shutdown parameter was analyzed briefly. For some power system with depleted shutdown, the redundant fuel could be dissipated by using energy management approach. Simulation results show effectiveness of the presented method .

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 

分 类 号：V474.28[航空宇航科学与技术—飞行器设计]