摘要：AbstractIn this paper, a State Dependent Riccati Equation (SDRE) based suboptimal guidance law is proposed for a stationary target. The main feature of this guidance law is that it controls state variation during mission while enabling the missile to satisfy all possible impact angle constraints in elevation. It also aligns the velocity vector of the missile with the body axis through pitch control, thus increasing the effectiveness of strike. The proposed law is verified through numerical simulations for a pitch controlled model taking into consideration maximum lateral acceleration and maximum moment input.
