| Summary: | 碩士 === 國立成功大學 === 航空太空工程學系碩博士班 === 95 === Fuzzy logic modeling(FLM) is a method capable of analyzing non-linear physical problems with multi-variables, such as the problems of flying aircraft encountering to the clear air turbulence. This study adopts the FLM to analysis the data from flight data recorder(FDR) of an aircraft A300-600 which encountered a clear air turbulence during an international flight. After noise suppression process to the FDR data, the angle of attack, computed air speed, altitude, acceleration, control surface angle, etc., all show severe oscillations of the aircraft when encountering to the severe turbulence. After the FLM is employed, eight flight data(such as angle of attack and its rate of change, pitch rate, reduced frequency, elevator deflection, mach number, roll rate, computed air speed) are computed and the database of normal force coefficient is established. Under different values of the reduced frequencies (k=0.0, 0.10, 0.12, 0.15), the relationship of the aircraft normal force coefficient with the angle of attack are studied. In this study, detailed noise suppression process and the formation of aerodynamic variable databanks are presented. The results of this study, when aircraft encountering to the severe turbulence, shows the fast flying motion and its responses to the aircraft, which are useful to provide data for flight control design, to help pilots do the best control of the aircraft, and to promote the aims of the flight safety.
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