9 July 1999 Adaptive vibration damping of fin structures
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Abstract
Modern military aircraft are characterized by employment of optimized structural components. New demands on exploitation of lightweight construction technology will arise because even greater flexibility with increased maneuverability is desired. The structural integration of multifunctional, often called 'smart' elements, properly activated to e.g. reduce structural loading, offers great potential to necessary advances in military aircraft design. One major problem of modern military aircraft is the buffet loading on the fin structures. Flying the aircraft at high angles of attack allows vortices, evolving from the leading edge of the wing, to hit the fin and excite structural vibrations. This leads to structural attrition as well as a reduced aircraft maneuverability. With the aim to reduce these fin vibrations, an adaptive structure has been developed which is presented in this paper. A concept is discussed with which the vibrational loads are reduced by introduction of counteracting forces using an 'active interface'. This interface concept is characterized by the integration of active, piezoelectric elements directly into the bending support of the fin structure. To validate the stability of the interface FE calculations and extensive measurements on piezoceramic stack actuators have been performed. The manufactured interface was integrate in an existing test structure and realistically loaded. The result will be given in this presentation.
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Michael Stuwing, Delf Sachau, Elmar J. Breitbach, "Adaptive vibration damping of fin structures", Proc. SPIE 3674, Smart Structures and Materials 1999: Industrial and Commercial Applications of Smart Structures Technologies, (9 July 1999); doi: 10.1117/12.351571; https://doi.org/10.1117/12.351571
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