A strategy of intercepting the near-space hypersonic aircraft is proposed, which is based on infrared window guidance, change the guidance law from side window constraint to the fixed lead angle, the sliding mode variable structure guidance law with prefix angle constraint is designed. First, setting up the dynamic model for the end of interceptor with direct force/aerodynamic control, deriving the integrated mathematical model of interceptor’s longitudinal guidance and control. Then, by using smooth sliding mode control, the interceptor’s variable structure guidance law with prefix angle constraint is designed. Last, the simulation results show that the designed guidance law can achieve high precision interception for hypersonic vehicle.

提出了一种基于红外窗口制导的近空高超音速飞机拦截策略，将制导律从侧窗约束改为固定的超前角，设计了带有前缀角约束的滑模变结构制导律。首先，建立具有直接力/空气动力控制的拦截器末端的动力学模型，得出拦截器纵向引导和控制的综合数学模型。然后，采用平滑滑模控制，设计了具有前缀角约束的拦截器变结构制导律。最后，仿真结果表明，所设计的制导律可以实现高超声速飞行器的高精度拦截。