—Modern tactical missile systems are required to achieve high maneuverability and sufficient stability. As a result, the flight control design of a missile system is a creative process as it considers both performance requirements and performance limitations, which are inherently conflicting. Different modern control techniques handle such conflicting demands through the adjustment of cost weighting parameters between system internal states and control signals. The adjustment processes might need trials to tune the system performance to certain level at different operating conditions. This paper involves in the formulation of an optimal design approach that achieves the required level of robustness related to open-loop design requirements and system dynamic limits while minimizing the tracking error between the reference input and the system output. The proposed approach is based on a constrained optimization technique where the design parameters are automatically adjusted to the optimum tradeoff between the overall system performance and robustness. The effectiveness and feasibility of the proposed approach are demonstrated through a numerical example for the three-loop autopilot design.
—Optimal-robust state feedback, constraint optimization, frequency domain constraint, control effort constraint.
The authors are with School of Automation, University of Science and Technology, Nanjing 210094, China (e-mail: email@example.com, firstname.lastname@example.org, email@example.com).
Cite: Abd-Elatif M. A., Qian Longjun, and Bo Yuming, "Constrained-Optimal Based Loop-Shaping State Feedback Approach for Missile Autopilot Design," International Journal of Modeling and Optimization vol. 6, no. 3, pp. 128-135, 2016.