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

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 conference › Paper › peer-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 language	English
Pages	2205-2213
Number of pages	9
Publication status	Published - 2001
Externally published	Yes
Event	18th Biennial Conference on Mechanical Vibration and Noise - Pittsburgh, PA, United States Duration: Sept 9 2001 → Sept 12 2001

Conference

Conference	18th Biennial Conference on Mechanical Vibration and Noise
Country/Territory	United States
City	Pittsburgh, PA
Period	9/9/01 → 9/12/01

ASJC Scopus subject areas

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

Cite this

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

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.",

author = "Emam, \{Samir A.\} and Nayfeh, \{Ali H.\} and Hendricks, \{Scott L.\}",

year = "2001",

language = "English",

pages = "2205--2213",

note = "18th Biennial Conference on Mechanical Vibration and Noise ; Conference date: 09-09-2001 Through 12-09-2001",

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T1 - Equations of motion of an aircraft wing modeled as a composite plate-beam model including the rigid-body motion

AU - Emam, Samir A.

AU - Nayfeh, Ali H.

AU - Hendricks, Scott L.

PY - 2001

Y1 - 2001

N2 - 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.

AB - 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.

UR - https://www.scopus.com/pages/publications/0035790860

UR - https://www.scopus.com/pages/publications/0035790860#tab=citedBy

M3 - Paper

AN - SCOPUS:0035790860

SP - 2205

EP - 2213

T2 - 18th Biennial Conference on Mechanical Vibration and Noise

Y2 - 9 September 2001 through 12 September 2001

ER -

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

Abstract

Conference

ASJC Scopus subject areas

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