複合材料脹破式端蓋之設計

Abstract

本論文之目的在設計製造一脹破式複合材料飛彈發射箱前端蓋。『此端蓋必需可以承受發射箱外之外壓20psi及發射箱內之靜態內壓3psi以下不可破裂，但當發射箱內之動態內壓若達9psi以上時必須完全破裂』。且破裂模式需符合設計，依一定模式破壞，破裂面要求十分完整不得有殘屑。 在製造與實驗部份，我們利用玻璃纖維束及玻璃纖維布為主體製成端蓋。利用所構思的二套爆破裝置來量測端蓋所能承受之靜態內態、外壓、及動態內壓。 使用前後處理繪圖軟體MCS/PATRAN，來設計建立端蓋的幾何模型，經綱目分割後，再經由有限元素分析軟體MSC/NASTRAN 68.2作力學分析，以分析端蓋所能承受之靜態內壓、外壓、及動態內壓，再與實驗值作比較。

The purpose of this thesis is to design and manufacture a frangible composite material canister end over. The composite material canister end cover is capable to resist statical external pressure of 20psi and statical internal pressure of 3psi. On the other hand, the canister must fail when subjected to impulsive pressure of 9psi. The end cover can burst open and fracture into four fragments in accordance with a predestined failure pattern. The fragments of the end cover require to be integral and have no scourings. Methods for fabricating the composite material canister end covers are presented. Tests of canister covers subjected to statical internal pressure, statical external pressure and impulsive internal pressure were performed using two kinds of burst equipment. The softwares-PATRAN and NASTRAN is used to design and predict the burst strength of end covers. The results obtained from the finite element analysis and experiments are studied and discussed.