Equations of motion of an aircraft wing modeled as a composite plate-beam model including the rigid-body motion

Samir A. Emam, Ali H. Nayfeh, Scott L. Hendricks

Research output: Contribution to conferencePaperpeer-review

Abstract

The equations of motion of an aircraft wing modeled as a composite beam are presented. The contribution of the rigid-body motion is taken into account; it affects the response of the wing, especially in maneuvers. The Hamilton principle is used to derive the equations of motion and the corresponding boundary conditions.

Original languageEnglish
Pages2205-2213
Number of pages9
Publication statusPublished - 2001
Event18th Biennial Conference on Mechanical Vibration and Noise - Pittsburgh, PA, United States
Duration: Sep 9 2001Sep 12 2001

Other

Other18th Biennial Conference on Mechanical Vibration and Noise
Country/TerritoryUnited States
CityPittsburgh, PA
Period9/9/019/12/01

ASJC Scopus subject areas

  • Modelling and Simulation
  • Mechanical Engineering
  • Computer Science Applications
  • Computer Graphics and Computer-Aided Design

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