飛彈擔負國防之重要角色。然在執行掛載飛行任務多次後，可能 因為外力作用而產生細微的裂縫，影響其推力甚至發生爆炸。 本研究建立藥柱疲勞性質測試技術，量測得到藥柱在室溫(15℃) 時之疲勞應力範圍-壽限方程式及潛變應力-破壞時間方程式，並針對 藥柱之機械老化，發展了一套壽限評估方法。研究結果顯示，具黏彈 性質之藥柱，其壽限評估方式可採用類似潛變-疲勞之分析方式。當 變動應力歷程之應力均方根值在0.193~.230 MPa 時，利用潛變-疲勞 線性損傷累積加總法所預估之壽限，其與實驗值之誤差在三倍之內， 且趨近保守，顯示此法可適用於藥柱在機械力作用下之壽限評估。此 外在平均應力的修正模式方面，經比較實驗值與分析值後，顯示 Goodman 方程式較適用於等應力振幅及變動應力振幅歷程作用下之 平均應力修正。 Solid propellant is the main power source of rocket and missile. The failure of solid propellant often brings about a fatal damage of the system. In the project, we perform finite elements analysis with the residuals stress of influence in curing solid propellant, To compare with character with viscolastic and elstica. In addition to technology is built on fatigue test, An equation is built on measured which stress-age and creep-age in the room temperature. Then, a research to display Solid propellant that character is viscolastic similar creep- fatigue analysis with age to appraise. The age life prediction by creep- fatigue of liner damage summation methods is less than triple standard, and it is conservative. The method is useful for age life prediction with Solid propellant on influence of mechanical.
