Abstract
The article describes a new approach of creating a finite element stick model for the purpose of the aircraft flutter analysis. The control surface properties are merged with a lifting surface element as a special degree of freedom (DOF). The number of DOF for the coordination system is increased from the classical 6DOF to 9DOF. A new beam element and concentrated mass element are present for the purpose of modal and flutter analysis. The advantage of this method lies in reducing the number of model nodes and introduction of a more appropriate arrangement of global mass matrix for eigen-value extraction. Quality of results is not affected. The paper also presents a verification example of a real sports aircraft.
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