航空宇宙機の翼断面構造の非対称性を考慮した簡易振動解析法に関する研究

摘要

A Simplified analysis method, which can evaluate structural vibration properties of reusable launch vehicle, is considereda useful tool in the preliminary design phase. From this standpoint, we are developing a simplified wing vibration modelby unsymmetrical finite plate element which corresponds to the wing structure with unsymmetrical cross section. In thispaper, we are proposing a four-node plate element with unsymmetrical cross section and variable thickness based onBathe’s MITC4 plate element. Demonstration analyses by our element and their accuracies obtained by them are shown.