W2燃料與過氧化氫推進劑組合具便宜、低毒性及自燃等特性；而液旋式噴注機構因其構造簡單且可於空腔內混合推進劑，故適合與W2/H2O2這類具較長點火延遲時間的準自燃推進劑組合搭配。本研究針對液旋式噴注機構的空腔幾何外形及噴注操作條件與熱燃點火特性的關係進行研究。實驗結果顯示在總流量3g/s~8g/s、O/F=1~4的操作範圍內，內徑小於10mm的噴注機構點火延遲時間較長，且不穩定；而內徑10mm之噴注機構，可在總流量6g/s~7g/s，O/F=4操作條件下，因足夠空腔體積及匹配的反應釋熱速率，具較短且固定的點火延遲時間(6g/s：1.6秒，7g/s：1.1秒)。實驗結果亦顯示，在此操作條件下，將噴注機構內空腔長度由30mm加長至60mm，有助於縮短點火延遲。另外，H2O2/W2燃燒後附著於噴注機構內壁之生成物有助於反應，可縮短點火延遲並擴展可點火範圍。整體實驗結果顯示，液旋式噴注機構與H2O2/W2的搭配是具發展潛力的雙基綠色火箭推進之噴注機構設計。

The combination of W2 (kerosene-based fuel) and hydrogen peroxide is kind of cheap, low toxicity and hypergolic propellant. Due to the simple configuration and which could mix propellant in the internal space, liquid-cyclonic injector could be the corresponding design for semi-hypergolic propellant such as H2O2/W2. In this research, the correlation of injector geometries, operation conditions, and hypergolic phenomena are discussed. The results show that longer ignition delay and unstable flame occurred where the inner diameter of injector under 10mm. Because of enough inner space and suitable heat releasing rate, more stable and shorter ignition delay occurred (6g/s:1.6sec, 7g/s:1.1sec) at the operation conditions which total flow rate are 6g/s~7g/s and O/F=4. The results also show that increasing of internal space of injection by lengthening injector from 30mm to 60mm encourage quick and stable ignition. In addition, the shorter ignition delay and wider ignition range are observed when the combustion products attached on wall of injector because they promote the decomposition of H2O2 and the heat release rate. In summary, the combination of liquid-cyclonic injector and H2O2/W2 is a potential design for green bipropellant rocket.

1.Sutton, G. P., “Rocket Propulsion Elements”, John Wiley & Sons, Inc., 1992.
2.Stechman, R. C. and Smith, J. A., “Monomethyl Hydrazine vs. Hydrazine Fuels: Test Results Using Flight Qualified 100 lbf and 5 lbf Bipropellant Engine Configurations”, AIAA-83-1257, 1983
3.Lewis, Richard J. Sr. Hazardous, “Chemicals Desk Reference”, 4thed. New York : John Wiley& Sons, 1997.
4.Melof, Brian M., and Grubelich, Mark C., “Investigation of Hypergolic Fuels with Hydrogen Peroxide” AIAA-2001-3837, 37thAIAA/ASME/SAE/ASEE Joint Propulsion Conference, July 8-11, 2001, Salt City, UT.
5.Palmer, R.K. “Development and Testing of Nontoxic, Hypergolic Miscible Fuels” Master Thesis, School of Aeronautics and Astronautics, Purdue University.
6.佘怡璇“煤油基燃料與過氧化氫自燃點火特性”成功大學航空太空工程學系碩士論文，2015
7.Wheatley, M., “Thermal Ignition Tutorial” Leeds University, Leeds, United Kingdom, LS2 9JT.
8.J. TAFFANEL AND LE FLOCH, Compt. Rend. Acad. Sci. Paris, 156(1913) 1544; 157(1913) 469,595.
9.Timothee L. Pourpoint ,William E. Anderson , “Hypergolic Reaction Mechanisms Of Catalytically Promoted Fuels With Rocket Grade Hydrogen Peroxide” Combustion Science and Technology, 2007
10.John A. Blevins, Rudy Gostowskit, Silvio ChianeseS “An Experimental Investigation of Hypergolic Ignition Delay of Hydrogen Peroxide with Fuel Mixtures” .AIAA,2004
11.N. K. RIZK and A. H. LEFEBVRE. "Internal flow characteristics of simplex swirl atomizers", Journal of Propulsion and Power, Vol. 1, No. 3 (1985), pp. 193-199.