9 July 1999 Fin-buffet alleviation via distributed piezoelectric actuators: full-scale demonstrator tests
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Abstract
Structural fin or wing vibrations are observed on high performance aircraft when flying at high angles of attach. The severity of the so-called buffeting vibration depends on the aircraft configuration and aerodynamic optimization of the configuration. The vibrations are caused by flow fluctuations resulting from flow separation at wings or from bursting of wing leading edge and front fuselage vortices. The resulting dynamic loads with maneuver loads lead to increased material fatigue and may require an augmented effort in aircraft maintenance.
© (1999) COPYRIGHT Society of Photo-Optical Instrumentation Engineers (SPIE). Downloading of the abstract is permitted for personal use only.
Reiner Manser, Reiner Manser, John Simpson, John Simpson, Juergen Becker, Juergen Becker, Johannes K. Duerr, Johannes K. Duerr, Erik Floeth, Erik Floeth, Ursula Herold-Schmidt, Ursula Herold-Schmidt, H. Stark, H. Stark, Helmut W. Zaglauer, Helmut W. Zaglauer, "Fin-buffet alleviation via distributed piezoelectric actuators: full-scale demonstrator tests", Proc. SPIE 3674, Smart Structures and Materials 1999: Industrial and Commercial Applications of Smart Structures Technologies, (9 July 1999); doi: 10.1117/12.351554; https://doi.org/10.1117/12.351554
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