Abstract
A Simplified analysis method, which can evaluate structural vibration properties of reusable launch vehicle, is considered a useful tool in the preliminary design phase. From this standpoint, we are developing a simplified wing vibration model by unsymmetrical finite plate element which corresponds to the wing structure with unsymmetrical cross section. In this paper, we are proposing a four-node plate element with unsymmetrical cross section based on the Bathe's MITC4 plate element. Demonstration analyses of the hollow double delta wing by our elements and their accuracies obtained by them are shown.
