Computational study of aeroelastic limit cycles due to localized structural nonlinearities


Conference Paper

Copyright © 2018 by the American Institute of Aeronautics and Astronautics, Inc. Aeroelastic systems including all-moving control surfaces and aircraft wings with stores may experience limit cycling caused by nonlinear structural and/or aerodynamic mechanisms. These systems are examined here via two different and complementary models, with nonlinear wing-root and nonlinear wing-store attachments, respectively, subjected to linear potential flow aerodynamic forces. Limit-cycle responses are obtained through an efficient computational method based on harmonic balance by using the spatially localized (hence mathematically separable) nature of the assumed nonlinearities. Results pertaining to a cubic hardening or softening restoring force in stiffness or damping, freeplay, and Coulomb friction are discussed along with confirmatory time-marching responses for selected cases. Clear relationships are established between the linear flutter behavior and the limit-cycle responses corresponding to each nonlinearity. Overall, this work provides an improved understanding, as compared to prior work, of the beneficial and/or detrimental effects of various localized nonlinearities on the aeroelastic response of all-moving control surfaces and store-carrying aircraft wings.

Full Text

Duke Authors

Cited Authors

  • Padmanabhan, MA; Dowell, EH; Pasiliao, CL

Published Date

  • January 1, 2018

Published In

Volume / Issue

  • 55 / 4

Start / End Page

  • 1531 - 1541

International Standard Serial Number (ISSN)

  • 0021-8669

Digital Object Identifier (DOI)

  • 10.2514/1.C034645

Citation Source

  • Scopus