Predictor-Corrector Guidance Law Considering Multiple Terminal Constraints

The predictor-corrector guidance law has been widely used in many categories of guided weapons. It is usually applied to impact point prediction and control. To improve the performance of future weapons, it is required to ensure not only high impact accuracy, but also rigorous constraints on the terminal impact angle and angle of attack. In this paper, a new predictive method is proposed, in which the overload command of missile is designed in the form of quadratic polynomials. The terminal states of missile are predicted by integrating the equations of motion of missile, and the sensitivity matrix of terminal states with respect to the polynomial coefficients is determined by applying the small perturbation method. Then, the polynomial coefficients that determine the overload command are updated according to the predicted errors of terminal states. With the proposed method, the impact point, terminal impact angle and angle of attack can be controlled simultaneously. Numerical simulations are conducted, and the results show that the missile can achieve high impact accuracy with good satisfaction on the impact angle and angle of attack.