摘要
在导弹动力学模型中使用4个因子描述喷流干扰效应。在俯仰平面内设计了导弹的控制策略,设计思路强调导弹对指令的快速响应要求。姿控发动机的点火指令按等周期计算,通过分析导弹在一个点火周期内的动力学,用李雅普诺夫函数设计指令趋近律,最后得到了离散化的舵指令和脉冲姿控发动机点火指令。仿真结果表明,脉冲姿控发动机参与控制产生的脱靶量远远小于气动舵单独控制时产生的脱靶量,显示了控制策略的有效性及使用侧向推力装置的优势。
Four factors are used to describe the influence of jet interaction for the missile using impulse attitude control motors in the equations of motion. Considering quick response with little sacrifice on steady state tracking accuracy, a control policy is designed in pitch plane. The command to ignite motors is issued periodically. After analyzing the dynamics of the missile during one ignition period, the Lyapunov function is used to get the discrete elevator command and ignition command. Simulation results show that the miss when using impulsive attitude control motors is more less than that when aero-fin used alone, and hence the efficiency of control strategy and the superiority of using lateral thrust are verified.
出处
《系统工程与电子技术》
EI
CSCD
北大核心
2008年第9期1724-1729,共6页
Systems Engineering and Electronics
