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.

Volume Subject Area:
18th Biennial Conference on Mechanical Vibration and Noise
Topics:
Aircraft, Composite materials, Equations of motion, Wings, Boundary-value problems, Composite building materials
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