本文主要發展應用於固體火箭發動機推進劑退化燃面的模擬分析方法，並利用若干模式案例進行基礎數值驗證。較先進的模式所需的電腦輔助設計軟體也多，數學模式也較複雜。本研究只使用簡單的計算幾何方法亦可達到相同目的。首先考慮均勻推進劑燃燒速率問題，我們提出三種可行的數值方法：界面追蹤法、放射線法及最小距離法等三種數值方法。發現無論就演算難易度、模擬精度、計算效率及未來應用擴展性而言，最小距離法均較其他兩種便利。因此，運用最小距離法的特性，確實可作為模擬固體火箭發動機內彈道性能及應用於多維燃燒室流場模擬分析的基礎工具。 In the study, we have successfully developed practical surface tracking methods for simulating evolution of the grain geometry corresponding to the regression of the grain surface during the combustion of the solid propellant. Three methods, namely the front tracking, the emanating ray and the least distance methods, are proposed. The front tracking method is based on the Lagrangian approach, while both the emanating ray and the least distance methods are formulated from the Eulerian viewpoint. Three twodimensional test cases have been examined to compare the programming complexity, simulation accuracy and required CPU time of the proposed methods. It is found that the least distance method is superior to the other two methods in many numerical respects. The least distance method is recommended to track the regressing surface of a threedimensional cubical propellant. Comparison between the predicted erosive volume with the corresponding theoretical results yields satisfactory agreement.