Parameterized Design of Impact-Angle-Constraints Guidance Law Based on Fully-Actuated System Theory

To satisfy the terminal impact-angle-constraints, a guidance law based on the Fully-Actuated System Theory (FAST) is proposed. Without compromising the fully actuated characteristics of the control system, a second-order fully actuated model is established to describe the missile's dynamics in the longitudinal plane and the missile-target kinematics. By selecting the line-of-sight(LOS) angle as the constraints condition, a proportional-derivative feedback control term and a compensation term based on FAST are designed. This approach increases the design flexibility of the system and reduces the complexity of controller design. To improve the guidance performance of the direct parameterization design method based on FAST, limits are introduced for the LOS angle and the missile-target distance. Simulation results demonstrate that the proposed method ensures the missile can stably hit the target and satisfy the impact-angle-constraints.