本研究以無毒性的煤油基燃料與過氧化氫為雙基火箭推進劑組合，以兩階段衝擊式噴注器為噴注單元，設計100牛頓級推力之噴注盤。噴注單元設計過程以理論計算、冷流實驗觀察與開放空間點火實驗觀察兩階段衝擊式噴注單元於低推進劑流率時之霧化現象。
本研究之低流率噴注單元以傳統鑽床加工可得並具精確度之0.3mm孔徑噴嘴作為最小噴注孔徑，以推進劑達完全發展模式且管路壓差為4bar以上作為推進劑流率篩選條件。由冷流實驗觀察結果得知由上述條件限制之兩階段衝擊式噴注單元在推進劑總流率最低為11.5g/s時，可有較佳霧化特性。
本研究以PLIF方法觀察噴注單元設計條件對於液滴質量分布的影響，噴注單元設計條件為：噴注孔徑、噴注角度與兩衝擊點之間的距離，並以噴流的衝擊韋伯數作為無因次參數。觀察結果顯示，不同工作流體(煤油基燃料、乙醇、純水)在相同衝擊韋伯數時，有類似的液滴質量分布；相同的工作流體的衝擊韋伯數越高，液滴質量分布有越均勻的趨勢。將燃料與氧化劑之液滴質量分布以程式疊合，可預測推進劑混合效率、絕熱火焰溫度分布與特徵速度分布。噴注單元設計參數組合中，篩選具有較高平均特徵速度的預測值作為本研究的噴注單元設計。經篩選的噴注單元操作條件為；燃料流率2.3g/s配合0.3mm孔徑噴嘴以衝擊角度θ_F=40°置於噴注單元內對；氧化劑流率9.2g/s配合0.4mm孔徑噴嘴以衝擊角度θ_O=45°置於噴注單元外對；兩衝擊點相距5mm；由程式預測於第二衝擊點下10mm截面有最高平均特徵速度1560.6m/s。
開放空間點火實驗以設計完成的噴注單元進行，火焰觀察結果顯示，駐焰位置位於第二衝擊點下1mm，火焰長度約為40.5mm。最後，由程式將噴注單元預測結果整合設計為三組噴注單元之噴注盤，噴注盤於第二衝擊點下10mm之平均特徵速度預測值為1569.3m/s。

A two-stage impinging injector plate design for 100N thrust-level thruster was investigated in this thesis research. The plate was designated for kerosene base/hydrogen peroxide propellant system. Simulants were used in cold-flow experiments, and PLIF technique was adopted to observe the mass distribution of the impinging sprays from the injection unit in order to determine its mixing characteristics. The arrangement of the injection units on the injector plate was determined by optimizing their collected effect on the averaged characteristic velocity determined from the overall spray. The two-stage injection unit was composed by two like-doublet impinging injection orifices. The orifice size, impinging angle, and the distance between the two impinging points were the design variables in study. The results show that the mass distribution of the spray was crucially depending on the Weber number of the impinging liquid jets. The resulting injector plate of this study was composed by three injection units. In each unit, the first kerosene stage impinging angle was 40° with orifice diameter 0.3mm, and the second hydrogen peroxide stage impinging angle was 45° with orifice diameter 0.4mm, and the distance of the two impinging point was set to be 5mm. The anticipated average characteristic velocity of an injection unit and the injector plate were 1560.6m/s and 1569.3m/s, respectively. Hot-firing tests showed that the reaction zone of an injection unit is about 40.5 mm in length, and the flame stationed at about 1mm below the second impinging point.

1.George P. Sutton, O. Biblarz, “Rocket Propulsion Elements”, Seventh
edition, p197~p341,2007
2.W.E. Anderson, M.R. Long, S.D. Heister, “Liquid Bipropellant Injectors”,
Progress in Astronautics and Aeronautics, pp. 141-165,2004
3.M. F. Heidmann, R. J. Priem, J. C. Humphrey, “A Study of Sprays Formed
by Two Impinging Jets”NACA Technical Note 3835,1957
4.Arthur H. Lefebvre,“Atomization and Sprays”,Hemisphere Publishing
Corporation, pp.1-45, 1989
5.N. Dombrowski, P.C. Hooper, “A Study of the Sprays Formed by Impinging
Jets in Laminar and Turbulent Flow, ”Journal of Fluid Mechanics,
Vol.18 ,part 3, 1964,pp.392-400
6.Hohen. F. W., Rupe. J. H., and Sotter. J. G., “Liquid Phase Mixing of
Bipropellant Doublets,”California Inst. of Technology. April, 1972
7.Rupe. J.H., “A Correlation Between the Dynamic Properties of A Pair of
Impinging Streams and The Uniformity of Mixture ratio Distribution In The
Resulting Spray,”Jet Propulsion Lab., California Inst. of Technology.
Pasadena, March,1956
8.林瑋倫，“噴流孔徑對雙衝擊霧化之影響”，成功大學航太所碩士論文，
九十七學年度
9.王群凱，“兩階段衝擊式液態推進劑噴注系統設計”，成功大學航太所
碩士論文，一百零一學年度
10.佘怡璇，“煤油基燃料與過氧化氫自燃點火特性”，成功大學航太所
碩士論文，一百零四學年度
11.周靜遠，“500磅級推力之煤油與過氧化氫火箭引擎噴注器設計”，
成功大學航太所碩士論文，一百零五學年度