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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。
A New Method of Initial Formation for Newton Iterative Guidance for Aero-Spacecraft. Newton iterative method is used to solve the guidance parameters of boost segment, and the formula of iterative guidance algorithm is deduced. Focusing on the analysis of the main factors affecting the accuracy of convergence, aiming at the problem that the initial value of iteration has a great influence on it, this paper proposes an iterative initial value solving algorithm which combines theoretical derivation with data interpolation. The simulation results show that this algorithm can realize the initial generation of iterative iteration and guidance parameters of the spacecraft, and the accuracy of convergence can meet the design requirements.