Polynomial Guidance with Impact Angle and Time Control

For impact angle and time control guidance (IATCG), the impact-time-control (ITC) accuracy is highly dependent on the estimated time-to-go of the underlying impact-angle-control (IAC) guidance law. This paper first employs a polynomial approach to derive an analytical solution for the time-to-go of missile under impact-angle-constrained guidance. Based on this solution, a polynomial guidance law for IAC with precise knowledge of time-to-go is developed. Subsequently, utilizing the polynomial IAC guidance as the basic law, an IATCG is proposed based on a fixed-time-convergent relative error dynamics method. Finally, the validity and effectiveness of the proposed guidance law are validated through numerical simulations.