Recently, numbers of study on impact-time-control and/or impact-angle-control guidance laws have been developed and guidance laws considering eld-of-view constraint have also been developed. In this dissertation, a novel approach for guidance law design to satisfy the impact-time constraint for a certain class of homing missiles. The proposed guidance law provides proper lateral acceleration commands that make the impact time error converge to zero by the time of impact. This scheme can be applied to any existing guidance law for which a formula of predicted time-to-go is available. By introducing a new form of error dynamics, the impact time error converges to zero within a nite time. Convergence of time-to-go errors is supported by Lyapunov stability. In order to consider the seeker's FOV constraint, time-varying guidance gain is suggested for the proposed guidance law. Moreover, certain feasible conditions of relationship between desired impact angle, time, and FOV limit are analyzed. The performance of the extended guidance laws is demonstrated by numerical simulation.