空空导弹在大攻角飞行时参数呈现非线性,因此需要在非线性条件下设计制导律。对导弹-目标三维相对运动数学模型进行分析,建立了相对运动的非线性时变状态方程,采用滑模控制的方法对非线性时变状态方程进行求解,以设计三维非线性制导律,所设计制导律基于俯仰和偏航通道相互耦合的情况。对制导律进行仿真检验,结果显示目标视线角可以快速趋于稳定,该制导律可以满足导弹飞行时非线性情况。

Missiles will be flying under the condition of high angle of attack. To fit this condition, a new kind of 3-D non linear guidance law is needed. A time varying state space equation is built through the analyzing of the relative movement model between missile and target. With the analysis of the equation, the sliding control theory can be used to design the guidance law. Also the 3-D guidance law is designed under the condition that the pitching channel and yaw channel are strongly coupled. The simulation results show that the angles between missile and target can be fixed in a short time, this designed 3-D guidance law can fit the non linear flying condition.