固態火箭相較於液態、混合火箭，最大的不同就是開始燃燒後，無法 經由調節燃料或氧化劑的量，來控制推力，因此對於推進藥柱的製作過程， 及其燃燒特性都影響最終的推力表現。
本研究使用的推進劑係由山梨糖醇(Sorbitol)、硝酸鉀(Potassium nitrate)、三氧化二鐵粉(Ferric oxide powder)、鋁粉(Aluminum powder)所組 成，山梨糖醇為主燃料，經由加熱至熔點使其兼具黏著劑功能，硝酸鉀是 氧化劑，以及少量之金屬粉末做為催化劑，此類固態推進劑廣泛運用在較 低性能之火箭上。
本研究利用製作藥柱的方式製作藥條，先以基本山梨糖醇及硝酸鉀 為 主成分，製作出多組數且不同比例的藥條，於常壓下測定燃燒速率， 選出最 佳比例後，以同樣方式加入三氧化二鐵粉製作多組數藥條，測定 燃燒速率同 樣選出最佳比例，再加入不同比例鋁粉製作藥條，依前述方 式，進行燃燒速率的實驗，而圖中以時間與長度關係呈現。
除測定燃燒速率外，本研究會用最佳的成分比例製作藥柱，並安裝於 推進引擎進行推力測試，其中會使用不同口徑噴嘴的方式來改變燃燒室 壓力，並以時間與有效推力推算出總衝量(Total impulse)及比衝值(Isp)。

The major difference between solid rockets and liquid and hybrid rockets is that the thrust can't be controlled by adjusting the amount of fuel or oxidizer after ignited. Therefore, the manufacturing process of the propellant grains and its combustion properties affect the final performance of the thrust.
The propellant used in this study is composed of Sorbitol, Potassium nitrate, Ferric oxide powder, and Aluminum powder, with Sorbitol as the primary fuel, which is heated to the melting point for making it as an adhesive; Potassium nitrate as the oxidizer with small amount of metal powder is the catalyst. This solid propellant is widely applied in rockets with low performance.
In this study, we applied the method of making grain to produce the propellant strip with sorbitol and potassium nitrate as the main ingredients and to make a number of propellant strips with different ratios. The combustion rate was measured at atmospheric pressure to select the best proportion, and then a number of propellant strips were made by adding ferric oxide powder in the same way; the combustion rate was also measured to choose the best proportion, and a different proportion of aluminum powder was added to make propellant strips. The experiments of combustion rate were implemented as mentioned above, and the relationship between time and length was presented in the figure. In addition to the measurement of the burning rate, the propellant strips will be made with the best composition ratio and installed in the motor for thrust testing, which will employ different nozzle diameters to alter the chamber pressure and use the time and effective thrust to calculate the total impulse and the specific impulse (Isp).

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