近年來，混合火箭逐漸受到重視，因為其安全性與結構簡易，許多民間公司均發展過，且具有作為上層火箭及軌道推進器的潛力。在性能上，混合火箭比固體火箭表現較好，藥柱設計上也比較安全；在整體結構上，混合火箭比液態火箭安全。總體而言，混合火箭從學校到商業公司均可以以低成本且高安全性為目標之推進系統作為發展。以氧化劑層面為考量，液態氧雖然具有最高比衝，但是其儲存與運送較難處理；氧化亞氮為較安全之氧化劑，可以在大氣環境下運作，因為具有高蒸氣壓的特性，所以不需要額外加壓設備，貫徹混合火箭之簡單性的優點。混合火箭雖然具有以上許多優點，但是其點火系統較其他兩者困難，因為其需要先把固態藥柱加熱產生燃氣，接下來氧化劑噴注後給予足夠點火能量才能完成點火步驟，所以點火系統的設計為整體混合火箭之主要關鍵設計。在過去點火器的文獻中，固體點火器具有短時間內釋放高能量之優勢，在上層火箭上可短時間內進行脫節點火程序，可以避免氣動力對火箭姿態的影響，在點火器的選擇中也以不影響氧化劑噴注與減輕重量為前提下，選擇以發動機下游點火之噴焰式固體點火器為本研究之點火系統。本研究首先發展出一套適用於學校實驗室之安全固體藥製作程序，分析出固體藥密度對固體藥燃燒速度影響重大，故經過改良發展與均勻度佳與高密度之製藥過程。接著以能量釋放率及能量分布為主要因素為考量去設計固體點火器，計算出無建壓與有建壓之固體點火器的能量釋放率分別為33.4%和48.7%，接著以溫度分布實驗分析計算與實驗的能量釋放率的差異，設計出兩種固體點火器的實驗能量釋放率分別為21.5%及20.7%，最終以實驗驗證其設計標準之可用性，本設計標準可作為混合火箭之點火系統設計標準，可用於未來混合火箭之發展，對於不同推力大小之推進系統點火器設計的參考。

With the advantages of safety and simple structure, hybrid rocket has been widely used in the commercial companies and colleges recently. It also equips potential ability in upper-stage rocket and orbit thruster. Green propellants, such as hydrogen peroxide and nitrous oxide, has been more valued nowadays for the sake of environmental protection. Due to the characteristic of high vapor pressure in standard condition, we choose nitrous oxide to be oxidizer in hybrid rocket. Although sum of impressive merits in nitrous oxide hybrid rocket, designs of igniter become crucial steps during launch mission. Solid propellant igniter contains several advantages, like high energy density and low ignition delay, and ammonium perchlorate, which is one of solid propellants, attracts high performance in combustion. To design a solid propellant ignition system, it is crucial for ignition energy calculation and heat distribution estimation in hybrid rocket. Next, we evaluate the performance of solid propellants and calculate the total energy that solid propellants release by using chemical equilibrium application. And then, in order to verify whether the calculation of heat transfer fits the experiment of which, we plan to conduct grain surface temperature detective experiments. Finally, we find the range of total ignition energy in hybrid rocket and establish the procedures which apply in solid propellant igniter for hybrid rocket.

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