Formalizing a Robust Flight Control Design Technique with Application to a Highly Flexible Aircraft.

摘要

With many of the modern aircraft designed to be larger and lighter, there have been increasing interests in incorporating the structure mode when designing flight control system. Sliding mode control (SMC) is an approach to the design of control systems that shows significant robustness in the presence of large uncertainties in plant dynamics. In this study, formalized Multi-Input Mult-Output (MIMO) SMC based robust fight control system design procedure was introduced and presented. The study vehicle was selected to be the B-1 bomber, a highly flexible aircraft. The multi-input multi-output SMC design procedure was carried out using the study vehicle model. The structure modes of the aircraft was addressed. Finally, a pilot model was included to evaluate the robustness of the SMC design.