摘要
对大气层外自旋稳定微型拦截器的脉冲点火算法进行了研究。在考虑变质量后质心位置变化所产生的扰动力矩对拦截器姿态的干扰以及弹体自旋运动对直接力分量影响的基础上,建立了自旋稳定微型拦截器六自由度数学模型,结合比例导引律设计出拦截器脉冲发动机的点火算法。该点火算法可以在满足脱靶量要求的前提下减少脉冲发动机的消耗并降低对拦截器姿态运动的影响。仿真结果表明,该方法能有效实现微型拦截器在末制导段的精确制导控制。
The ability of an ignition algorithm to control a spinning extra-atmospheric interceptor with multi-pulse control is investigated.Firstly,a six-dimension model for spinning interceptor is established based on the impacts of centroid excursion.After analyzing the pulse control,impacts of lateral thrust on the motion of the spinning interceptor are presented.And the ignition control algorithm is presented for pulse thrusters based on proportional navigation.This arithmetic decreased the consumption of fuel and the infection of attitude on the premise of precise guidance.Simulation results show that this method can effectively implement precise guidance for interceptor at the terminal guidance stage.
出处
《航天控制》
CSCD
北大核心
2010年第1期53-57,共5页
Aerospace Control
关键词
微型拦截器
点火算法
自旋
末制导
脉冲发动机
Mini-interceptor
Ignition algorithm
Spinning
Final guidance
Pulse thruster
