研究导弹在发射后飞行阶段的控制律。首先建立导弹总体布局数学模型和气动模型 ,再分别对导弹的纵向、横向和滚转向的控制律进行分析 ,其中纵向分为下滑段、巡航段和末段制导俯冲段 ,并依次对每一阶段的控制律进行分析 ,最后 ,对下滑段升降舵控制律进行算例计算。实际应用表明 ,所设计的控制律是正确的 ,能够保证导弹最终精确击中目标。 To study the control law of missiles in the flight phase after launching. Firstly, the mathematical model and the aerodynamic model of the overall layout of the missile are established. Then the longitudinal, transverse and roll control laws of the missile are analyzed separately. The longitudinal direction is divided into the gliding section, the cruising section and the leading section of the cruise control section, The control law of the elevator is analyzed. Finally, the control law of the elevator in the sliding section is calculated. The practical application shows that the designed control law is correct and can ensure that the missile finally hit the target accurately.