Adaptive Finite-Time Guidance against a Maneuvering Target at a Designated Impact Time

This paper investigates the problem of intercepting a maneuvering target at a designated impact time. Firstly, a guidance model for intercepting a maneuvering target in the two-dimensional plane is established, and an expression for estimating the time-to-go for a maneuvering target is provided. Furthermore, an adaptive nonlinear guidance law with a designated impact time is designed based on the adaptive control theory and Lyapunov theory, and the stability of the guidance system is analyzed. After that, the proposed guidance law is extended to multiple missiles, enabling multiple missiles to attack a maneuvering target simultaneously or sequentially at specified times. Finally, numerical simulations are conducted to validate the effectiveness of the proposed guidance law.