Research on guidance law with terminal constraint based on optimum control

Abstract

It is required that the loitering aero vehicle with MEFP (Multi-Mode Explosively Formed Penetrator) in warhead plays its role to the largest extent in constraining the terminal angle. This article develops a guidance law that guarantees both the hitting target and its angle of fall. First relationship between the target and aircraft is established and its nonlinearity is linearized; next a parameter is introduced and through the change of reference point and the working on Riccati equation, the guidance law with optimum control method is achieved to gain the satisfied terminal angle. It is proved by simulation that the guidance law performs well in controlling terminal angle and the ballistic trajectory.