Reconfigurable Flight Control System for a STOL (Short Take-Off and Landing) Aircraft Using Quantitative Feedback Theory

摘要

Future aircraft may incorporate many control surfaces to meet stringent performance and aerodynamic efficiency requirements. These many surfaces increase the survivability of the aircraft by providing redundant control in the event of surface failures. The design of a flight control system that automatically redistributes control authority among the remaining surfaces in the event of failure is a significant challenge. A control law sufficiently robust to encompass the dynamic uncertainty, as well as surface failures, is desired. Quantitative Feedback Theory (QFT) developed by Dr. Isaac Horowitz promises to yield robustness without identification. QFT inherently includes uncertainty and control system failures within the design procedure. One a priori designs for acceptable system responses with uncertainty and failures, making QFT well suited for designing aircraft flight control systems. This thesis uses QFT in the design of a flight control system for a future Air Force Short-Take-Off-and Landing (STOL) experimental aircraft. The aircraft has additional control surfaces not found on current aircraft. Hence it provides an excellent platform for demonstrating reconfigurable flight control system design.