Date

2009-11-01

Author

Chen, Yong
Ulker, Fatma Demet
Nalbantoglu, Volkan
Wickramasinghe, Viresh
Zimcik, David
Yaman, Yavuz

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Following the program to lest a hybrid actuation system for high-agility aircraft buffeting load alleviation oil the full-scale F/A-18 vertical fin structure, an investigation has been performed to understand the aerodynamic effects of high-speed vortical flows on the dynamic characteristics of vertical fin structures. Extensive wind-tunnel tests have been conducted on a scaled model fill integrated with piezoelectric actuators and accelerometers to measure file aft-tip vibration responses under various freestream and vortical airflow conditions. Test results demonstrated that the airflow induced considerable lamping to the fill structure. which generally increased increased with airflow speed as well as the vertical fill angle of attack reactive to the airflow direction. Moreover. it was observed that at the angle of a attack of 10 deg, the high-speed airflow introduced large deflection to the smart fin structure and caused significant frequency shift to the vibration mode; the to nonlinear geometrical coupling of bending and torsional modes. These aerodynamic effects may adversely affect the performance and robustness of the closed-loop control laws developed based oil vertical fill dynamic model identified without considering the varying aerodynamic effects. To explore this problem, the structured singular values synthesis technique was adopted to develop robust control law using smart fill model identified without aerodynamic excitations and the aerodynamic effects oil the fill structure were assumed as smart fin parametric and dynamic uncertainties. The effectiveness and robust performance of the control law was demonstrated through extensive closed-loop wind-tunnel tests using various airflow conditions. This provided a verified control law design strategy for future flight tests or file full-scale aircraft buffeting load alleviation system.

Subject Keywords

System

URI

https://hdl.handle.net/11511/38337

Collections

Department of Aerospace Engineering, Article