Abstract
The aim of this project is the identification of mathematical model of the F/A-18 active aeroelastic wing (AAW) research aircraft from flight tests by use of the subspace identification algorithm. The structural deflections in nine different locations on the aircraft structure are defined with third order Multiple Inputs Single Outputs linear state space systems for various Mach numbers and altitudes. The correlation coefficients between the flight test data output and the model estimated output was found to be near 100 % have values between 90 % and 100 %.
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