摘要
针对直接力/气动力复合作用动能拦截弹的姿态控制问题,建立了拦截弹俯仰-偏航通道短周期运动模型;利用线性二次型最优跟踪控制理论结合姿控固体小火箭点火逻辑设计了复合控制系统,通过分析非线性容限得出了该系统对直接力偏差具有强鲁棒性的结论;姿控回路仿真表明系统具有快速响应特性及良好的跟踪性能,考虑侧喷干扰效应等实际条件的六自由度弹道仿真表明所设计的控制系统能够满足拦截末段直接碰撞要求。
An attitude control method of kinetic energy interceptor under blended operation of lateral thrust and aerodynamic force was developed and a short period movement model of interceptor was presented. A combined control system was designed,using linear quadratic optimal tracking control theory and the fire logic of attitude control missiles. Through analyzing the nonlinear tolerance,a conclusion was drawn that the system has strong robusticity to the thrust bias. Simulation results of attitude control and six-dimension intercept trajectory with lateral jet interaction show that the control method proposed has quick response characteristic and good tracking performance for guidance command,and it can meet the demands of direct interception in the terminal phase.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2010年第4期30-36,共7页
Journal of National University of Defense Technology
关键词
动能拦截弹
直接力/气动力复合控制
最优跟踪控制
点火逻辑
侧喷干扰
kinetic energy interceptor
lateral thrust/aerodynamic force blended control
optimal tracking control
fire logic
lateral jet interaction
