不論是太空的探討或海底的揭密，非吸氣（non-air breathing）式推進系統已是唯一的選擇。現今所使用的非吸氣式推進系統所用的氧化劑或是燃料常具有毒性，以過氧化氫分解後可產生高溫氧氣及水蒸氣，不具毒性無環境破壞性可作為單推進劑或是加入碳氫燃料燃燒成為推力、比衝值(ISP)更高的雙推進劑引擎。
本研究目的則在於建立以過氧化氫及煤油作為雙推進劑之熱機引擎燃燒器。探討的主要問題包含過氧化氫溶液的純化、高濃度過氧化氫分解觸媒以及加入煤油混合燃燒特性與燃燒室設計。所使用之過氧化氫濃度為85％，但是濃度高於50％之過氧化氫溶液市面上不易取得，在此吾人發展以蒸餾的方式純化，將過氧化氫以減壓加熱的方式加以純化，成功的將過氧化氫經八小時純化，將濃度50％提升至85％，若是再加長純化時間，則可將過氧化氫溶液純化至近100％。
過氧化氫需經過觸媒分解後方能產生高溫氧氣及水蒸氣以作為燃燒用，一般常使用的觸媒為銀，但是銀觸媒有需預熱的缺點。本研究嘗試使用不同種類的觸媒，如：二氧化錳、三氧化二錳及白金等觸媒作過氧化氫分解測試，測試中發現以白金有較好的反應效率。
本研究近一步整合高濃度過氧化氫及觸媒床設計，設計並測試過氧化氫-煤油雙推進劑燃燒室系統與測試設備，測試結果發現燃燒穩定，燃燒室可以穩定操作，並在燃燒室建立所需之壓力產生推力。

Non-air breathing propulsion systems find extensive applications in outer space exploration and under-water discovery activities. Traditional non-air breathing propulsion systems use toxic propellants such as hydrazine and HTBP. Nontoxic propellants, such as hydrogen peroxide, are considered as the “green propellants” for the new generation. High-concentration hydrogen peroxide can be used as the monopropellant as it generates high-temperature oxygen and superheat vapor when decomposed. Hydrogen peroxide can also be used as the oxidizer in the bipropellant system. Bipropellant systems, usually combining hydrogen peroxide with kerosene or other hydrocarbon fuels, can generate more specific impulse (ISP) and thrust than monopropellant.
The main objective of the current research is to develop a bipropellant thruster system using hydrogen peroxide and kerosene. There are several key technologies in this research needed to be surmounted, including process of distillation of low-grade hydrogen peroxide water solution into propellant-grade hydrogen peroxide, selection and tests of catalysts for hydrogen peroxide decomposition, design and test of a hydrogen peroxide-kerosene bipropellant combustor system.
High-concentration propellant-grade hydrogen peroxide distillation facility and process was developed based upon the method of sub-atmospheric heating distillation. After 8 hours of distillation, we can successfully increase the concentration of hydrogen peroxide form 50% to 85%. With extended period of distillation, the concentration can be further raised close to 100%.
Catalyst is usually used in the propulsion systems to enhance decomposition of hydrogen peroxide into oxygen and water vapor and generate thrust. In general, silver is most widely used as the catalyst for hydrogen peroxide decomposition. However, silver has its own drawbacks. For example, silver needs preheating before using. In this study, several catalysts were selected as the candidates and tested, including: silver, manganese oxide and platinum. The test result show that platinum has the best low-temperature activeness and highest temperature yield among the catalysts when tested in the room temperature.
The above-mentioned high-concentration hydrogen peroxide and catalyst bed design are integrated in the design and tests of the combustor of a hydrogen peroxide-kerosene bipropellant propulsion system. Test results show that the current design of a cyclone combustor can provide stable combustion and smooth combustor operation and build up chamber pressure required to generate thrust.

ndrews D., (1990), “Advantage of Hydrogen Peroxide as a Rocket Oxidant,” Journal of The British Interplanetary Society, Vol.43, pp.319-328.
Coxhill, Ian, (2000) “Development of an HTP/Kerosene Rocket Engine For Small Satellites,” 3rd International Hydrogen Peroxide Conference. Nov 2000. Gulfport,Mississippi, USA.
Jon, J, Richard, B, Malcolm, P, (1999) “Practical Experience with Hydrogen Peroxide Catalysts,” 1st Hydrogen Peroxide Propulsion workshop. July 1998, Univ. of Surrey.
Kappenstein, C. and Hydr, D. (1999) “Catalytic Decomposition of H2O2. Comparison of Unsupported and Alumina Supported Manganese Oxide Catalysts,” 1st Hydrogen Peroxide Propulsion workshop. July 1998, Univ. of Surrey.
Morlan, P.W., Wu, P.K., Fuller, R., Nejad, A.S. (1999) “Silver Screen catalyst Bed Design for a pressure Fed Liquid Fueled Upper Stage Engine” 1st Hydrogen Peroxide Propulsion workshop. July 1998, Univ. of Surrey.
Mitchell, B.C., Maxwell, W.H. (1993) “A Single Stage to Orbit Rocket With Non-Cryogenic Propellants” 29th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
Nimmerfroh, N., Walzer, E., (2000), “Hydrogen Peroxide: Manufacture, Quality, Safety, Transportation, and Handling,” Journal of Propulsion and Power, Vol.12, No.3, pp.574-579.
Pirault-Roy L, (2002) “Hydrogen Peroxide Decomposition on Various Supported Catalysts Effect of Stabilizers” Journal of Propulsion and Power, Vol.18, No.6, pp.1235-1241.
Rusek, J.J., (1996) “New Decomposition catalyst and Characterization Techniques for Rocket-Grade Hydrogen peroxide,” Journal of Propulsion and Power, Vol.12, No.3, pp.574-579.
Wernimont, E., Ventura, M., Garboden, G., and Mullens, P., “Past and Present Uses of Rocket Grade Hydrogen Peroxide,” General Kinetics, LLC Aliso Viejo.
Wu, P.K., Fuller, R.P., Morlan, P.W., Ruttle, D.W., Nejad, A.S., Anderson, W.E.(1999) “Development of a Pressure-Fed Rocket Engine Using Hydrogen Peroxide and JP-8,” 35th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibition.
劉俊夆(2001) “雙推進劑液態火箭設計與測試之研究,”國立成功大學航空太空工程學系碩士論文.
胡興中編譯“觸媒原理與應用,”高立圖書有限公司