Impact-Angle-Control Guidance Law with Terminal Constraints on Curvature of Trajectory

This paper presents an impact-angle-control guidance law with terminal constraints on the curvature of missile trajectory. The formulation takes into account nonlinear kinematics and time-varying velocity, allowing for more general cases in which flight path angle may not be small throughout entire proposed optimal aims to minimize change rate pseudo-curvature, is defined as a weighting factors based flight-path range go. analysis shows that trajectories generated by this have simple polynomial form respect downrange. Numerical simulations demonstrate cost function parameter can used shape along