@article{e452d3fd2cf744ea99ceb655a3147543,
title = "Transonic aeroelastic instability suppression for a swept wing by targeted energy transfer",
abstract = "Targeted energy transfer is studied as a means for suppression of transonic aeroelastic instabilities of a wind-tunnel swept wing, with a focus on designing a lightweight nonlinear energy sink that improves the critical flutter condition. The aeroelastic response modes of the wing with a nonlinear energy sink coupled to the tip are identified and tested for robustness using a medium-fidelity computational aeroelasticity model, and confirm that robust suppression of transonic aeroelastic instabilities is achievable. Accordingly, a nonlinear energy sink is designed based on a parametric study, and its transonic aeroelastic effects are studied using medium- and high-fidelity models. The results of both models indicate an improvement in stability over a broad range of conditions; the high-fidelity model predicts an approximately 40% increase in the dynamic pressure at the critical stability condition. Finally, a prototype winglet-mounted nonlinear energy sink is modeled to examine its aeroelastic effects. The results show that the nonlinear-energy-sink design is robust, but the winglet design plays a critical role that must be considered in the overall effect.",
author = "Hubbard, {Sean A.} and Fontenot, {Raymond L.} and McFarland, {D. Michael} and Cizmas, {Paul G.A.} and Bergman, {Lawrence A.} and Strganac, {Thomas W.} and Vakakis, {Alexander F.}",
note = "Funding Information: The authors gratefully acknowledge the support and guidance from several organizations and individuals. Financial support was provided by the U.S. Air Force Office of Scientific Research (AFOSR) through the following Small Business Technology Transfer (STTR) contracts: Physics-Based Identification and Management of Aeroelastic Limit-Cycle Oscillations (LCO), Phase I, prime contract number FA9550-07-C-0070; and Physics-Based Identification and Management of Aeroelastic Limit-Cycle Oscillations (LCO), Phase 2, prime contract number FA9550-09-C-0057. Victor Giurgiutiu and David Stargel were the AFOSR Program Directors during the course of this work. The prime contractor for both phases of the STTR was NextGen Aeronautics, Inc., of Torrance, California. D. M. McFarland{\textquoteright}s participation was further supported by the Summer Faculty Program of the U.S. Air Force Research Laboratory with the guidance of Philip Beran. The model wind-tunnel wing that is the subject of this study was generously loaned to the authors by NASA. In addition, NASA provided the source code for CAPTSDv, the transonic small-disturbance aeroelastic model that was critical to this work. The authors would also like to acknowledge the late John W. Edwards for providing extensive CAPTSDv documentation and examples that were invaluable to this research. Finally, the University of Illinois at Urbana–Champaign authors would also like to thank D. J. Segalman of the Sandia National Laboratories who, when serving as Director of the Structural Mechanics Program of AFOSR, suggested this problem as an ideal application for targeted energy transfer, and supported the initial research effort leading to these results. Publisher Copyright: Copyright {\textcopyright} 2014 by Indian Institute of Space Science and Technology, Thiruvananthapuram, India. Published by the American Institute of Aeronautics and Astronautics, Inc.",
year = "2014",
month = sep,
day = "1",
doi = "10.2514/1.C032339",
language = "English (US)",
volume = "51",
pages = "1467--1482",
journal = "Journal of Aircraft",
issn = "0021-8669",
publisher = "American Institute of Aeronautics and Astronautics Inc. (AIAA)",
number = "5",
}