EQUATIONS OF MOTION OF AN AIRCRAFT WING MODELED AS A COMPOSITE PLATE-BEAM MODEL INCLUDING THE RIGID-BODY MOTION

摘要

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.