Abstract:
Designing missile autopilots is a challenging problem due to highly nonlinear uncertain aerodynamics, and stringent performance requirements. In this paper a robust adapt...Show MoreMetadata
Abstract:
Designing missile autopilots is a challenging problem due to highly nonlinear uncertain aerodynamics, and stringent performance requirements. In this paper a robust adaptive augmenting controller is designed for a generic non-minimum phase pitch-axis missile autopilot. The control system consists of a robust L2 gain optimal controller as a baseline and an incremental robust direct Model Reference Adaptive Control (MRAC). The baseline controller is designed using robust convex programming covering multiple operating regions. The main objective of designing a retrofit adaptive controller is to provide strong robust performance in presence of uncertainties such as parametric uncertainties, reduced control effectiveness, etc. Simulation tests are performed to assess stability and performance of nonlinear closed-loop adaptive system in presence of uncertainties in pitching moment and normal force coefficients, unmodeled time-delays, and variations in Mach number. In addition, results in simulations indicate satisfactory robustness in case of severe loss of control effectiveness event and uncertainty in pitch aerodynamic model.
Published in: 2016 American Control Conference (ACC)
Date of Conference: 06-08 July 2016
Date Added to IEEE Xplore: 01 August 2016
ISBN Information:
Electronic ISSN: 2378-5861