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和三衝擊式噴注器為噴注單元，設計50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，以及三衝擊式噴注器之點火和霧化特性。
本研究透過PLIF方法觀察噴注單元設計條件對於液滴質量分布的影響，在改變噴注單元之噴注角度、噴注單元組數等設計條件下，以等韋伯數流率作為模擬液之修正流率。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。經篩選的噴注單元預估核心推力為15.97牛頓，駐焰位置位於第二衝擊點下30mm，火焰長度約為110mm，駐焰位置之平均特徵速度為1595.1m/s。
三衝擊式噴注器之噴注盤設計，經過點火以及冷流實驗觀察最後得知，將噴注單元衝擊角度定為30度且操作混合比3.5時會有最好之霧化混合分布。混合比為3.5時預估核心推力為12.05牛頓，駐焰位置位於衝擊點下10mm，火焰長度約為97mm，駐焰位置之平均特徵速度為1568.8m/s。由實驗結果比較後，使用三衝擊式噴注器做為噴注盤設計，而噴注盤之整體平均特徵速度可達1570.0m/s，預估推力為38.16牛頓。

A two-stage impinging and triplet impinging injector plate design for 50N thrust-level thruster was investigated in this thesis research. The plate was designated for W2/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 and the triplet injector used in the study is the triplet O-F-O type. 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 results show that triplet impinging injector is better than two-stage impinging. The resulting injector plate of this study was composed by three injection units. In each unit, the hydrogen peroxide impinging angle was 30° with orifice diameter 0.3mm, and the W2 between them and was perpendicular to the ground with orifice diameter 0.3mm, and the distance of the two injectors was set to be 5mm. The anticipated average characteristic velocity of an injection unit and the injector plate were 1568.8m/s and 1570.0m/s,
respectively. Hot-firing tests showed that the reaction zone of an injection unit is about 97 mm in length, and the flame stationed at about 10mm below the impinging point.

1.George P. Sutton, O. Biblarz, “Rocket Propulsion Elements”, Seventh
edition, p197~p341,2007
2.M. F. Heidmann, R. J. Priem, J. C. Humphrey, “A Study of Sprays Formed
by Two Impinging Jets”NACA Technical Note 3835,1957
3.陳威丞，“衝擊噴流霧化混合之分析”，成功大學航太所博士論文，
九十六學年度
4.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
5.游芷均，“100牛頓級推力之煤油與過氧化氫推進器噴注器設計”，成功大學航太所碩士論文，一O五學年度
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.W.E. Anderson, M.R. Long, S.D. Heister, “Liquid Bipropellant Injectors”,
Progress in Astronautics and Aeronautics, pp. 141-165,2004
10. 林政學，“20牛頓級NTO/MMH液態推進器設計與實驗驗證”，成功大學航太所碩士論文，九十九學年度
11.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
12.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
13.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