8 September 1993 Vibration attenuation of aircraft structures utilizing active materials
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The need for active vibration control for airborne laser systems was demonstrated during the late 1970s by the Airborne Laser Laboratory. Other possible applications include sonic fatigue alleviation, reduction of buffet induced fatigue, vibration control for embedded antennae, and active aeroelastic control. The purpose of this paper is to present an overview of active vibration control technology and its application to aircraft. Classification of classic aircraft vibration problems and currently available solutions are used to provide a framework for the study. Current solutions are classified as being either passive or active and by the methodology (modal modification or addition) used to reduce vibration. Possible applications for this technology in aircraft vibration control are presented within this framework to demonstrate the increased versatility active materials technologies provide the designer. An in- depth study of an active pylon to reduce wing/store vibration is presented as an example. Finally, perceived gaps in the existing technology base are identified and both on-going and future research plans in these areas are discussed.
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Gregory S. Agnes, Stephen R. Whitehouse, and John R. Mackaman "Vibration attenuation of aircraft structures utilizing active materials", Proc. SPIE 1917, Smart Structures and Materials 1993: Smart Structures and Intelligent Systems, (8 September 1993); doi: 10.1117/12.152774; https://doi.org/10.1117/12.152774

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