Feedback Control of a Nonlinear Non-Minimum Phase Missile with Limited Modeling Information

Acceleration control of highly agile, fin-controlled missiles is a well-known non-minimum phase control problem. In this paper, the problem is revisited and a globally stable feedback control law using minimal model information is synthesized. No modifications to the output/or placement of a virtual inertial measurement unit are placed. The proposed control architecture is an extension of authors prior works for stabilizing non-minimum phase systems with full system information. In this paper the fundamental ideas are broadened to partial dynamic feedback control architecture and global stability using Lyapunov methods is proven. The control law is validated for a medium-fidelity generic missile model that is not approximately feedback linearizable. Simulation results presented in the paper demonstrate perfect output tracking while keeping all closed-loop signals bounded.

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