本文所研究之分析種類共十二種，利用 ANSYS 有限元素軟體分 析覆晶球柵陣列構裝體覆晶封裝層及球柵陣列封裝層錫球之應力-應 變行為，比較Double Power Law、Hyperbolic Sine Law 及 Norton 三種 潛變模型所得結果並代入兩種疲勞壽命預測公式進行比較，並做成以 下之結論：
1. 等效層之使用可有效且快速的分析複雜結構，再配合次結構的模 擬分析可得到與單一模型分析雷同之結果。
2. 由等效下層錫球及完整下層錫球之次結構分析可知，其應變反應 以完整下層錫球較小，故完整錫球之壽命也相對較高，尚需經過 驗證以加強等效層分析之可靠性。
3. 覆晶封裝層錫球可能破壞位置為對角線上最遠之錫球或錫球分 佈密度交界處之斜對角最遠位置；球柵陣列封裝層錫球可能破壞 位置在覆晶封裝層填膠導角正下方。吾人亦預期此處為最先發生 疲勞破壞位置。
4. 在次結構的分析中，每種潛變模型之錫球最先產生疲勞破壞位置 不盡相同，覆晶封裝層錫球最先破壞的位置約為錫球下端、錫球 焊墊(solder mask)及填充底膠交界處；球柵陣列封裝層最先破壞
位置在上端與錫球銲墊之交界處。
5. 在覆晶封裝層中，其構造較球柵陣列封裝層複雜，所顯示之應力 及應變趨勢會有突然改變之狀況，塑性應變造成的疲勞壽命較球 柵陣列封裝層短，潛變應變造成的疲勞壽命則視潛變模型而有所 不同。
6. 在錫球結構分析中，發現 Double Power Law 模型在低溫停留期的 應力釋放產生時間較兩種穩態潛變模型慢，Norton 模型對於溫度 週次的反應上較為敏感。
7. 吾人比較彈性、塑性及潛變剪應變數據後發現，在 TCT 測試中潛 變應變較其他兩者大，故可知錫球之潛變行為是造成錫球疲勞行 為的主要成因。
8. 在 TCT 測試中，錫球的遲滯曲線在溫度循環第二周次後有逐漸穩 定收斂之趨勢，故選用第三週次溫度循環可得較穩定結果。
9. 比較本文使用的疲勞壽命公式計算結果，Modified Coffin-Manson 計算所得壽命較高。兩種方式皆顯示，使用 Hyperbolic Sine 模型 時覆晶封裝層有較高壽命，其餘兩種潛變模型皆為球柵陣列封裝 層有較高壽命。
10. 在 以 Modified Coffin-Mason 疲 勞 壽 命 公 式 計 算 疲 勞 壽 命 時 Double Power Law 模型的下層錫球有無窮壽命且以 Creep-Fatigue
疲勞壽命計算公式計算時其值亦偏高，此一結果並不合理，可能 原因為考慮暫態之潛變模型影響。
11. 整體模擬結果其壽命較 2D 模型為低，故本文以三方向彈性、塑 性及潛變剪應變之模擬結果尚需實驗結果進行驗證比對。
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