Guidance and control for high dynamic rotating artillery rockets

The acceleration autopilot with a rate loop is the most commonly implemented autopilot, which has been extensively applied to high-performance missiles. Nevertheless, for spinning rockets, the design of the guidance and control modules is a challenging task because the rapid spinning of the body creates a heavy coupling between the normal and lateral rocket dynamics. Nonlinear modeling of the rocket dynamics, control design as well as guidance algorithms are performed in this paper. Moreover, discrete-time guidance and control algorithms for the terminal phase, which is based on proportional navigation, are performed. Finally, complete nonlinear simulations based on realistic scenarios are developed to demonstrate the robustness of the proposed solution with respect to uncertainty regarding launch, environment and rocket conditions. The performance of the proposed navigation, guidance and control system for a high-spin rocket leads to significant reductions in impact point dispersion.