本論文旨在進行複合式結構壓力容器設計及製造之探討,並利用CAE技術進行結構模態與結構剛性之探討,以供複合式結構壓力容器後續設計及製造之參考用。首先進行設計及製造之探討,整個過程包含火箭工作任務所需的幾何尺寸設計、鋁合金材料與纖維強化塑膠之複合材料的探討及選用、材料機械性質測試、鋁合金內襯的銲接及殘餘應力探討、碳纖維複合材料疊層之纏繞;設計、製造完成複合式結構壓力容器後,利用CAD及CAE技術建立有限元素模型,並以實驗所得模態參數為基準,利用逆向法求取纏繞的複合材料疊層之材料機械性質,利用最佳化材料機械性質之有限元素模型進行模態分析;複合式結構壓力容器之有限元素模型的等效性乃是經由量測重量、重心及實驗模態分析所得模態參數進行驗證比對,實驗所得模態參數主要驗證有限元素模型結構之質量與剛性的分佈;實驗模態分析完成後,藉由水靜壓力測試來確認設計、製造之複合式結構壓力容器所能承受之最大壓力有否達到火箭工作任務所需,並利用水靜壓力測試所得之應變與有限元素分析所得之應變進行比對,探討結構之弱點及剛性,提供後續設計之參考。
The purpose of this thesis is to investigate the design and fabrication of pressure tank by using hybrid structural model which consists of aluminum liner and fiber-reinforced plastics. A pressure tank is first fabricated by welding the seamless aluminum tube and bulkheads. Carbon fiber is then used to wrap the aluminum liner by using a winding machine. This hybrid structure exhibits an anisotropic material property which is critical to finite element modeling of composite laminates. A finite element model (FEM) of filament wound pressure tank is established. Experimental modal analysis (EMA) is adopted for the validation of the FEM by using inverse method. The natural frequencies and the associated mode shapes obtained from finite element analysis are compared with those of from EMA. Good correlation of these modal parameters between FEA and EMA verifies that the distributed mass and stiffness of the FEM are equivalent to the real structure of pressure tank. The validated FEM is then qualified for the further analysis. The Strain analysis and hydraulic test are also performed to evaluate the strength of pressure tank.