摘要
能量省、精度高的初制导优化算法是空间拦截制导的基础。考虑变轨发动机有限推力的条件时,空间拦截初制导的任务是实时计算推力作用时拦截器姿态角。采用自适应制导原理和相对运动动力学方法,推导了有限推力条件下空间拦截最优初制导方法,在此基础上,利用降阶迭代方法解算了推力误差和姿态误差条件下的初制导问题,提高了初制导精度。仿真结果表明,在10%的推力误差和2度的姿态误差条件下,该优化制导方法具有较高精度。研究结论对发展空间拦截制导技术有参考价值。
Space interception needs optimization initial guidance method which uses few propulsion and has high precision. Under the condition of engines＇ limited thrust, the task of initial guidance is real-time calculation of interceptor＇ s attitude. This paper used self-adaptive guidance principles and relative dynanics methods to prove a optimization initial guidance law of space interception with limited thrust, and then, used a degree reduction iterate method to solve the problem of initial guidance with thrust and attitude errors. Results of simulations shown that under the conditions of 10% thrust error and 2 degrees attitude error, this guidance method led to high precision. The conclusions of this paper will be helpful to research on precise guidance methods of space interception.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2008年第4期1263-1266,1289,共5页
Journal of Astronautics
基金
航天支撑技术基金(GFKD-2007-1)
关键词
空间拦截
优化
初制导
误差
降阶
迭代
Space interception
Optimization
Initial guidance
Error
Degree reduction
Iterate
