Xin Wang, Junjie Gong, and Yuxin Wang
Angle constraint, optimal guidance law, optimum control
As air-to-surface missiles are affected by overload constraints, seeker sight angle measurement range, autopilot delay, interference, and other factors, they cannot cause fatal damage to the attacking target. Based on the optimal control theory, in this paper, the optimal control theory is used to study guidance accuracy with terminal landing angle constraints. Considering that the optimal control theory can consume the least energy, solve the constraint problem, and has the convenience and the optimisation of control quantity, an optimal guidance law with angle of fall constraint is proposed based on the optimal control theory in the case of arbitrary order guidance system without considering the system delay. The simulation results show that the guidance law can theoretically achieve any desired angle of fall, the miss distance is small, the trajectory is smooth, and the missile overload is relatively small. It can provide the theoretical basis for engineering practical application.
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