Experimental and analytical investigations are described about using piezoelectric actuators for tailoring the aeroelastic response of a five-foot long, transport-style wing wind-tunnel model. The model consists of two primary structures: an exterior fiberglass shell used to obtain aerodynamic lift; and an interior composite plate that contains the piezoelectric actuators and acts as the main load carrying member. The shell is divided into six sections and is connected to interior plate at only two points per shell section. This method of assemblage reduces the effect the exterior shell has on the dynamics of the interior plate. In addition to the piezoelectric actuators, the model has a trailing edge aerodynamic control surface. The control surface is driven by an electric motor that is located outside the airstream at the wing root. Improvements in the flutter boundary as well as significant reductions in model response at dynamic pressures below flutter are demonstrated.
The pizoelectric aeroelastic response tailoring investigation: a status report
Smarter Verbundwerkstoff mit eingebetteten piezoelektrischen Aktoren für die aktive Schwingungsdämpfung von Flugzeugtragflächen
1995
12 Seiten, 16 Bilder, 2 Tabellen, 21 Quellen
Aufsatz (Konferenz)
Englisch
The Piezoelectric Aeroelastic Response Tailoring Investigation
British Library Conference Proceedings | 1995
|Results of Wind-Tunnel Testing from the Piezoelectric Aeroelastic Response Tailoring Investigation
British Library Conference Proceedings | 1996
|Aeroelastic tailoring for flutter constraints
TIBKAT | 1986
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