Terminal velocity and impact angle control based on generalized polynomial guidance

This paper proposes a novel approach to control terminal velocity and impact angle during a missile’s descent phase using a simple dynamic model. This approach involves obtaining the acceleration control command from the generalized polynomial after normalizing the residual range. Then the gradient descent method is used to predict the terminal velocity and adjust the guidance parameters. Finally, numerical simulation results show that the approach achieves the guidance objective under various constraints of terminal velocity and impact angle through.