Generally, high performance requirements in terms of better efficiency (reduction in fuel consumption) and maneuverability, impose intrinsic instability on the aircraft. Then a Stability Augmentation System is required for its stabilization. Moreover, the aircraft must be safely controllable without any exceptional piloting skill. The requirements of stability and control are referred in literature as handling qualities. According to handling quality specifications, a feedback controller must be designed with robustness criteria with respect to flight conditions and sensor failure. A new design procedure of feedback controllers which allows the achievement of simultaneous stabilization, and provides some kind of fault tolerance with respect to sensor failure, are proposed. An application to the F4-E military aircraft is also presented.
Parameter Space Design of Robust Flight Control Systems
1990
13 pages
Report
No indication
English
Avionics , Computer Aided Design, CAD , Aircraft stability , Control systems design , Controllers , Fault tolerance , Feedback control , Flight control , Stability augmentation , Control configured vehicles , Controllability , F-4 aircraft , Flight conditions , Fuel consumption , Guidance sensors , Robustness (Mathematics) , System failures , Foreign technology
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