Transient response study on rolling effectiveness of multiple control surfaces


Journal Article

A study of the effectiveness of trailing- and leading-edge control surfaces has been made for a rolling wing-fuselage model. An experimental model and wind tunnel test are used to assess the theoretical results. The theoretical model includes the inherently nonlinear dry friction damping moment that is present between the spindle support and the experimental aeroelastic wing model. The roll trim equation of motion and the appropriate aeroelastic equations are solved for different combinations of leading- and trailing-edge control surface rotations using a reduced-order aerodynamic model based upon the fluid eigenmodes of three-dimensional vortex lattice aerodynamic theory. The focus is on the transient response of the system. The present paper provides new insights into the transient dynamic behavior and design of an adaptive aeroelastic wing using trailing- and leading-edge control surfaces. © 2004 Published by Elsevier Ltd.

Full Text

Duke Authors

Cited Authors

  • Tang, D; Li, A; Dowell, EH

Published Date

  • June 1, 2004

Published In

Volume / Issue

  • 19 / 5

Start / End Page

  • 621 - 634

International Standard Serial Number (ISSN)

  • 0889-9746

Digital Object Identifier (DOI)

  • 10.1016/j.jfluidstructs.2004.01.006

Citation Source

  • Scopus