Polynomial Guidance Law Considering Impact Time, Impact Angle and Terminal Acceleration Constraints

This paper proposes a polynomial guidance law that simultaneously controls impact time, impact angle, and terminal acceleration. First, the line-of-sight (LOS) angle is represented as a high-order polynomial that satisfies multiple boundary conditions so that the resulting flight trajectory can satisfy terminal constraints. Then, the leading angle is selected as the controlled state, and the acceleration command is designed to ensure the stable tracking of the obtained flight trajectory. Finally, numerical simulations are performed, and the results show that the proposed method can achieve zero-miss under various constraints.