火箭推進系統對於人類進入太空時代的發展有著非常重要的地位，而過去數十年應用於液態雙基推進及單基推進的聯胺雖然性能穩定，技術成熟，然而高度致癌性及毒性為其主要的缺點，因此近代隨著環境意識日漸提高，對環境無害的綠色推進劑被提出用來取代聯胺作為推進使用。

過氧化氫在早期便已經被應用於推進用途，例如在二次大戰時期作為潛艇引擎的氧化劑或V2火箭燃料泵浦的動力來源，在戰後則是有以過氧化氫為主要推進劑的雙基推進火箭(Black Knight)。雖然過氧化氫後來因為性能差距而被聯胺這類高毒性的推進劑所取代，然而由於過氧化氫無強烈毒性而且分解後僅會產生水蒸氣及氧氣，因此近代過氧化氫再次被重新提出作為綠色推進劑以取代高毒性的聯胺。過氧化氫不僅能使用於單基推進，也同樣能作為氧化劑用於雙基推進和混合推進，並且擁有高密度比衝(Density Isp)的優點。

而過氧化氫的使用一般會搭配觸媒幫助其分解產氣，過往最常使用的觸媒為銀，雖然銀觸媒擁有相當穩定的性能且加工容易，然而當應用於濃度92wt.%以上的過氧化氫時，會因為過氧化氫的絕熱分解溫度過高並且接近銀的熔點(960˚C)使其燒結(Sintering)，進而導致分解能力下降。為了使用更高濃度的95wt.%過氧化氫取得更好的效能，本研究將以白金觸媒取代銀觸媒，設計一具真空推力1N等級的單基推進器，並且以大氣測試、真空測試、預熱測試模擬推進器的不同使用環境。測試期間會擷取反應室壓力、反應室溫度訊號分析白金觸媒分解過氧化氫並且產氣升溫的能力，並且計算比衝值Isp評估整體推進器的能量轉換效率。

In this study, the green propellant hydrogen peroxide (H2O2) has replaced the toxic hydrazine (N2H4) in a 1N vacuum thrust mono-propellant thruster. In order to prevent the sintering of silver catalyst in the high concentration H2O2 (+92wt.%) due to the high decomposition temperature and the low melting point of silver (960˚C), the platinum catalyst has been used to decompose the 95wt.% H2O2 to acquire better performance. The mono-propellant thruster has underwent several tests, includes atmospheric tests, vacuum tests and preheated tests to simulate the operations under different environments. In the all tests, the chamber pressure achieved the designed condition of 11bar; in the atmospheric tests, the thrust was 0.62N with the Isp 105sec (85% efficiency), in the vacuum tests, the thrust was 0.84N with the Isp 140sec (95% efficiency), the difference of the above values is due to the test environment back pressure and heat loss. In the preheated cases, the chamber pressure rose faster than that of nonpreheated cases and had a shorter startup time. Besides, the chamber pressure resonant oscillation has been observed when the injector tube temperature was higher than the boiling point of H2O2. It is concluded that the platinum catalyst can efficiently decompose the H2O2 into high-pressure gas without sintering; with an appropriate expansion ratio of nozzle, the thrust should achieve the 1N vacuum thrust with designed 11bar chamber pressure.

[1] 許紘瑋, "台灣自主衛星推進器的研發", 科學發展, 542期, pp.29-37, 2018
[2] 陳建安,"過氧化氫觸媒雙推進劑熱機引擎之研發", 國立成功大學航空太空工程研究所碩士論文,2004
[3] E. Wernimont, M. Ventura, G. Garboden and P. Mullens, "Past and Present Uses of Rocket Grade Hydrogen Peroxide", 2nd International Hydrogen Peroxide Propulsion Conference, Purdue University, November 7‐10, 1999
[4] P. McRight, C. Popp, C. Pierce, A. Turpin, W. Urbanchock and M. J. Wilson, “Confidence Testing of Shell-405 and S-405 Catalysts in a Monopropellant Hydrazine Thruster”, 41th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, AIAA 2005-3952, Tucson, Arizona, 10-13 July 2005
[5] M. J. Wilson, “Demonstration Testing of a Long-Life 5-Lbf (22-N) MR-106L Monopropellant Hydrazine Rocket Engine Assembly”, 41th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, AIAA 2005-3954, Tucson, Arizona, 10-13 July 2005
[6] G. P. Sutton and O. Biblarz, Rocket Propulsion Elements, John Wiley & Sons, Inc, New Jersey, 2010
[7] E. Wernimont and P. Mullens, "Capabilities of Hydrogen Peroxide Catalyst Beds", 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, AIAA-00-3555, Huntsville, Alabama, 16-19 July 2000
[8] N.S. Davis, Jr and J. C. McCormick, " Design of Catalyst Packs for the Decomposition of Hydrogen Peroxide", AIAA, Vol. 10, pp.589-616, 1972
[9] M. Ventura and E. Wernimont, "Advancements in High Concentration Hydrogen Peroxide Catalyst Beds", 37th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, AIAA-01-3250, Salt Lake City, Utah, 8-11 July 2001
[10] S. Barley, P. L. Palmer and I. Coxhill, "Evaluating the Miniaturisation of a Monopropellant Thruster", 42th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, AIAA 2006-4549, Sacramento, California, 9-12 July 2006
[11] 陳韋康, "分段複合式觸媒應用於高效能過氧化氫單基推進器之探討",國立成功大學航空太空工程研究所碩士論文,2013
[12] K. Sobczak, P. Surmacz, B. Bartkowiak, A.Okninski, G. Rarata and D. Kublik et at., "Test Campaign of a Green Liquid Bi-propellant Rocket Engine Using Catalytically Decomposed 98% Hydrogen Peroxide as Oxidizer", 53th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, AIAA 2017-4926, Atlanta, GA, 10-12 July 2017
[13] T. R. Beutien, S. D. Heister, J.J. Rusek and S. Meyer, "CORDIERITE-BASED CATALYTIC BEDS FOR 98% HYDROGEN PEROXIDE", 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, AIAA 2002-3853, Indianapolis, Indiana, 7-10 July 2002
[14] R. Eloirdi, S. Rossignol, C. Kappenstein, D. Duprez and N. Pillet, “Design and Use of a Batch Reactor for Catalytic Decomposition of Propellants”, Journal of Propulsion And Power, Vol. 19, pp.213-219, 2003
[15] J. J. Rusek, “New Decomposition Catalysts and Characterization Techniques for Rocket-Grade Hydrogen Peroxide”, Journal of Propulsion And Power, Vol. 12, pp.574-579, 1996
[16] C. Bramanti, A. Cervone, L. Romeo, L. Torre, L. d’Agostino and G. Saccoccia, ” Experimental Characterization of Advanced Materials for the Catalytic Decomposition of Hydrogen Peroxide”, 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, AIAA 2006-5238, Sacramento, California, 9-12 July 2006
[17] L. Pirault-Roy, C. Kappenstein, M. Gu´erin, R. Eloirdi and N. Pillet, “Hydrogen Peroxide Decomposition on Various Supported Catalysts Effect of Stabilizers”, Journal of Propulsion And Power, Vol. 18, pp.1235-1241, 2002
[18] S. An and S. Kwon, “Scaling and Evaluation of Pt=Al2O3 Catalytic Reactor for Hydrogen Peroxide Monopropellant Thruster”, Journal of Propulsion And Power, Vol. 25, pp.1041-1045, 2009
[19] L. Romeo, L. Torre, A. Pasini, A. Cervone, L. d’Agostino and F. Calderazzo, “Performance of Different Catalysts Supported on Alumina Spheres for Hydrogen Peroxide Decomposition”, 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, AIAA 2007-5466, Cincinnati, OH, 8 - 11 July 2007
[20] H.Tian, T. Zhang, X. Sun, D. Laing and L. Lin, "Performance and deactivation of Ir/g-Al2O3 catalyst in the hydrogen peroxide monopropellant thruster", Elsevier, Applied Catalysis A: General 210, pp.55-62, 2001
[21] M. Summerfield, ” A Theory of Unstable Combustion in Liquid Propellant Rocket Systems”, Journal of the American Rocket Society, Vol. 21, No. 5, pp.108-114, 1951