空天飞行器迭代制导初值生成方法研究  

Research on Initial Values of Newton Iterative Guidance for Aerospace Vehicles

作　　者：朱建文[1] 刘鲁华[1] 汤国建[1] 徐明亮[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《航天控制》2012年第3期61-64,共4页Aerospace Control

摘　　要：针对空天飞行器研究助推段牛顿迭代制导初值生成方法。采用牛顿迭代法求解助推段制导参数,推导了迭代制导算法公式。重点分析了影响收敛精度的主要因素,针对迭代初值对其有较大影响的问题,提出了将理论推导与数据插值融合的迭代初值求解算法。仿真结果表明,此算法可以实现空天飞行器助推段迭代初值与制导参数的快速生成,收敛精度满足设计要求。The Newton iterative method for boost phrase of aerospace vehicles is researched. This method is used to obtain guidance parameters and deduce the iterative formula. Meanwhile, by considering that the Newton iterative method is sensitive to the initial value of parameters, the generated methods is introduced for initial values on the basis of data interpolation and deducing. The simulation results show that it is feasible to obtain guidance parameters for aerospace vehicle rapidly with the algorithm proposed in the paper.

关 键 词：空天飞行器 助推段 制导 牛顿迭代 迭代初值 

分 类 号：V448.231[航空宇航科学与技术—飞行器设计]