隨著科技的發展，太空科技在這世界上占有舉足輕重的地位。 太空科技不僅可以代表國家科技的水準，也代表了國家的強盛。世界各國爭相探索太空這塊未知的領域，衛星成為了這極端嚴苛的環境條件下的主角，成為了人類的探索之眼，也成為了不可取代的軍事武器。
高濃度過氧化氫應用於衛星姿態控制推進器中所面臨最大的問題即是觸媒。由文獻中得知，銀觸媒對於過氧化氫有極佳的反應效率，但也因其低熔點的特性而無法承受高於92% 的過氧化氫而產生燒結，燒結的效應常常伴隨著低溫反應不完全、分解室壓力不穩定，進而造成流量供給不穩定。由文獻得知，而加入高耐熱性材料有助於提升銀觸媒的熔點，間接降低觸媒燒結的可能性。
本論文利用上述概念，利用銀觸媒搭配陶瓷材料開發出複合式銀觸媒、深入探討觸媒燒結之成因與誘發現象、建壓反應的影響因素。建立一觸媒衰退演變模組來評估觸媒燒結之解決方法，並藉由預測得的觸媒裝配方式來驗證解推論之正確性，解決長久以來無法突破的觸媒問題。
經過適當裝配的觸媒，不論冷啟動或熱啟動，其C*皆接近100%，冷啟動Isp為104.9 s，電磁閥作動加上建壓時間約100 ms。而熱啟動Isp為114.9 s，其電磁閥作動加上建壓時間約為50 ms。其具備有啟動時間短、壓力震盪穩定、觸媒床壓降小且反應效率高等特性，對過氧化氫單基推進氣是為成功的開發。

As the progress of science and technology, space explosion has become an outstanding cursor indexing the industrial development as well as a milestone symbolizing the overall power of a country. . Countries in the world is trying eagerly to expand their ambition to the space as soon as they step into developing countries and their economy is improved from poverty. Popularity of satellite and space technology significantly enhances the important role as the probing eyes of earth exploration and becomes the essential weapons threatening peace on the earth.
The most difficult problem for High Test Peroxide, which is used in monopropellant thruster for satellite, is the catalyst bed design. According to literature, silver has the best catalytic performance for HTP, but its low melting point usually sinters the silver catalyst bed during decomposition processes. A superior catalyst bed design has to deal with the balance of the highest specific impulse produced and life-span of the active catalyst bed performance. The sintering effect always accompanies with the incomplete decomposition in cold start and oscillation in chamber pressure. Even more, it will induce flow instability in the supplying system. In this thesis, we add some ceramic materials to increase the thermal resistance ability of catalyst bed, which names as composite silver catalyst. We design a HTP monopropellant thruster model for the test of the proposed catalyst; and discuss the factors influencing the decomposition processes and the deterioration of the catalyst bed. By anticipate packing, we can find an excellent result for our catalyst. No matter in cold start or hot fire, the C* efficiency in the catalyst is almost 100%. The Isp from cold start is 104.9 s; and Isp from hot fire is 114.9. The start transient is about 100ms and 50ms, which include the operation time of solenoid valve, from cold and hot fire. It is a successful development for H2O2 monopropellant thruster.

[1] http://cs.astrium.eads.net/sp/spacecraft-propulsion/hydrazine-thrusters/1n-thruster.html
[2] Walter, H., “Hydrogen Peroxide Rockets,” History of German Guided Missile Developments,” AGARDograph, edited by T. Benecke, and A. W. Quick, Vol. 20, Butterworths, London, 1956.G.
[3] Runckel, J. F., Willis, C. M., Salters, L. B., Jr., “Investigation of Catalyst Beds for 98-Percent- Concentration Hydrogen Peroxide,” NASA TN D-1808, 1963.
[4] Willis, C. M., “The Effect of Catalyst-Bed Arrangement on Thrust Buildup and Decay Time for a 90 Percent Hydrogen Peroxide Control Rocket,” NASA TN D-516, 1960.
[5] Sutton, G. P., Biblarz, O., ”Rocket Propulsion Elements”, 7th ed., Wiley-Interscience Publication, New York, 2001.
[6] Kuan, C.-K., “Indigenous Technology Development of an Advanced 100mN HTP Monopropellant Microthruster”, Master’s degree thesis, National Cheng Kung University, 2006
[7] Ventura, M. and Wernimont, E., “Advancements in High Concentration Hydrogen Peroxide Catalytic Beds,” AIAA Paper 01- 3250, July 2001.
[8] Pirault-Roy, L., Kappenstein, C., Guèrin, M., Eloirdi, R., and Pillet, N., “Hydrogen Peroxide Decomposition on Various Supported Catalysts Effect of Stabilizers,” Journal of Propulsion and Power, Vol. 18, No. 6, 2002, pp. 1235–1241
[9] Long, M.R., Rusek, J., “The characterization of the propulsive decomposition of hydrogen peroxide” AIAA-2000-3683, AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, 36th, Huntsville, AL, July 16-19, 2000
[10] Beutien, T., Heister, S., Rusek, J., Meyer, S., ” Cordierite-Based Catalytic Beds for 98% Hydrogen Peroxide”, AIAA-2002-3853, 38th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Indianapolis, Indiana, July 7-10, 2002
[11] Ali, S., Starbuck, T., Anderson, W.,, ” Hydrogen Peroxide Stability Margin”, AIAA-2003-4620, 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Huntsville, Alabama, July 20-23, 2003
[12] Pearson, N., Pourpoint, T., Anderson, W.E., “Vaporization and Decomposition of Hydrogen Peroxide Drops”, AIAA-2003-4621, 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Huntsville, Alabama, July 20-23, 2003
[13] Corpening, J., Heister, S., Anderson, W., Austin, B., “A Model for Thermal Decomposition of Hydrogen Peroxide”, AIAA-2004-3373, 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Fort Lauderdale, Florida, July 11-14, 2004
[14] Mok, J. S., Helms, W., Sisco, J., Anderson, W., “Thermal Decomposition of Hydrogen Peroxide, Part I: Experimental Results”, Journal of Propulsion and Power 2005, 0748-4658 vol.21 no.5 (942-953), doi: 10.2514/1.13284
[15] Corpening, J., Heister, S., Anderson, W., Austin, B., “Thermal Decomposition of Hydrogen Peroxide, Part 2: Modeling Studies”, Journal of Propulsion and Power 2006, 0748-4658 vol.22 no.5 (996-1005), doi: 10.2514/1.13285
[16] Ventura, M., Wernimont, E., Heister, S., Yuan, S., “Rocket Grade Hydrogen Peroxide (RGHP) for use in Propulsion and Power Devices - Historical Discussion of Hazards”, AIAA-2007-5468, 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Cincinnati, OH, July 8-11, 2007
[17] Blank, R., Pourpoint, T., Meyer, S., “Experimental Study of Flow Processes and Performance of a High Pressure Hydrogen Peroxide Catalyst Bed”, AIAA-2007-5469, 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Cincinnati, OH, July 8-11, 2007
[18] Scharlemann, C., Schiebl, M., Marhold, K., Tajmar, M., Miotti, P., Kappenstein, C., Batonneau, Y., Brahmi, R., Hunter, C., “Development and Test of a Miniature Hydrogen Peroxide Monopropellant Thruster,” 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Sacramento, AIAA Paper 2006-4550, 2006.
[19] Scharlemann, C., Schiebl, M., Amsüss, R., Tajmar, M., “Development of Miniaturized Green Propellant Based Mono- and Bipropellant Thrusters,” 43nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Cincinnati, OH July 2007
[20] An S., Lim, H., Kwon, S., “Hydrogen Peroxide Thruster Module for Microsatellites with Platinum Supported by Alumina as Catalyst”, AIAA-2007-5467, 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Cincinnati, OH, July 8-11, 2007
[21] An, S., Brahmi, R., Kwon, S., “Transient Behavior of H2O2 Thruster: Effect of Injector Type and Ullage Volume ”, Journal of Propulsion and Power 2009, 0748-4658 vol.25 no.6 (1357-1360), doi: 10.2514/1.46731
[22] An, S., and Kwon, S., “Scaling and Evaluation of Pt/Al2O3 Catalytic Reactor for Hydrogen Peroxide Monopropellant Thruster,” Journal of Propulsion and Power, Vol. 25, No. 5, 2009, pp. 1041-1045
[23] Cervone, A., Torre, d'Agostino, L., L., Musker, A. J., Roberts, G. T., Bramanti, C., Saccoccia, G., “Development of Hydrogen Peroxide Monopropellant Rockets” AIAA-2006-5239, 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Sacramento, California, July 9-12, 2006
[24] Bramanti, C., Cervone, A., Romeo, L., Torre, L., d’Agostino, L., Musker, A., Saccoccia, G., 2006, “Experimental Characterization of Advanced Materials for the Catalytic Decomposition of Hydrogen Peroxide”, AIAA Paper 2006-5238, 42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Sacramento, California, USA, July 9 - 12.
[25] Pasini, A., Torre, L., Romeo, L., Cervone, A., d'Agostino, L., Musker, A. J., Saccoccia, G., “Experimental Characterization of a 5 N Hydrogen Peroxide Monopropellant Thruster Prototype”, AIAA-2007-5465, 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Cincinnati, OH, July 8-11, 2007
[26] Pasini, A., Torre, L., Romeo, Luca, Cervone, A., d'Agostino, L., “Testing and Characterization of a Hydrogen Peroxide Monopropellant Thruster ”, Journal of Propulsion and Power 2008 , 0748-4658 vol.24 no.3 (507-515) doi: 10.2514/1.33121
[27] Torre, L., Pasini, A., Romeo, L., Cervone, A., d'Agostino, L., ” Performance of a Monopropellant Thruster Prototype Using Advanced Hydrogen Peroxide Catalytic Beds ”, Journal of Propulsion and Power 2009 , 0748-4658 vol.25 no.6 (1291-1299), doi: 10.2514/1.44354
[28] Pasini, A., Torre, L., Romeo, L., Cervone, A., d'Agostino, L., “Endurance Tests on Different Catalytic Beds for H2O2 Monopropellant Thrusters”, AIAA-2009-5472, 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Denver, Colorado, Aug. 2-5, 2009
[29] Chen, C.A., “Development of a Catalystic Hydrogen Peroxide Bipropellant Engine”, Master’s degree thesis, National Cheng Kung University, 2004
[30] Kuan, C.-K., Chen, G.-B., Chao, Y.-C., “Development and Ground Tests of a 100-Millinewton Hydrogen Peroxide Monopropellant Microthruster”, Journal of Propulsion and Power 2007, 0748-4658 vol.23 no.6 (1313-1320), doi: 10.2514/1.30440
[31] Chemical and Material Sciences Department, Rocketdyne, a Division of North American Aviation, Inc. Canoga Park, California Research Division, “Hydrogen Peroxide Handbook”, Edwards Air Force Base, California Air Force Systems Command United States Air Force, July, 1967.
[32] http://cameochemicals.noaa.gov/chris/KRS.pdf, “KRS”, June, 1999
[33] Yung-An Chan, Hung-Wei Hsu, Gung-Bang Chen, and Yei-Chin Chao, December, 2010, Study of Silver Catalyst Packing for a low-thrust Hydrogen Peroxide Monopropellant Thruster, Asia Pacific Conference on Combustion, Hyderabad, India, Dec, 2010
[34] Yung-An Chan, Hung-Wei Hsu, Yei-Chin Chao, July, 2011, Development of an HTP Monopropellant Thruster by Using Composite Silver Catalyst, 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, San Deigo, California, Jul 31 – Aug 3, 2011