固態推進劑燃燒特性實驗艙之設計製作與實驗結果

Design and Implementation of Strand Burner Chamber for Burning Characterization of Solid Propellant with Preliminary Experimental Results

金良曼(Rahman Hakim)

指導教授 ： 呉宗信

國立交通大學/工學院/機械工程系所/碩士(2016年)

摘要

在固體火箭發動機的回歸率的探空火箭最重要的因素。其中由固體火箭燃料回歸速率室壓力的函數確定的壓力穩定性。糖燃料，山梨糖醇基（KNSB），具有化學成分山梨醇（35％），硝酸鉀（65％）和氧化鐵（1％），為良好。為了預測燃燒率，低壓鋼絞線燃燒室的一個新的設計，用初步實驗結果完成。
對於股燃燒室靜態壓力模擬被ANSYS®V14進行;工作台使用1.5Watt連續激光精選並在2010年的SolidWorks®為KNSB燃料新的點火方法設計和供電用鏡頭聚焦在這個實驗中使用。燃燒時間和回歸率測量使用目測法600從石英玻璃的窗戶視線fps的高速攝像機。
AISI 1018為室材料的使用都適合在100大氣壓與安全係數（FOS）3.18承受。最低FOS 0.36是其中已被證明與在石英玻璃41.2Atm壓力的邊緣裂紋的石英窗口。燃氣燃燒產品涵蓋目測數額巨大，以獲得燃燒時間和回歸率。的壓力增加的增量是成功地由該緩衝罐覆蓋。

關鍵字

推進劑 ； 燃燒特性

並列摘要

Regression rate in solid rocket motor is the most important factor for the sounding rocket. The pressure stability which determined by the solid rocket fuel regression rate as the function of chamber pressure. Sugar fuel, Sorbitol based (KNSB), with chemical composition Sorbitol (35%), Potassium Nitrate (65%) and Iron Oxide (1%) as well. In order to predict the burning rate, a new design of Low Pressure Strand Burner Chamber was done with the preliminary experiment result.
A static pressure simulation for the strand burner chamber was done by ANSYS® V14; Workbench Featured and designed in Solidworks® 2010. A new ignition method for KNSB fuel by using 1.5Watt CW LASER and powered with focus lens are used in this experiment. Burning time and regression rate measurement are using visual method by 600fps high speed camera from the Quartz glass for the sight windows.
The usage of AISI 1018 for the chamber material are suitable to withstand in 100Atm with Factor of Safety (FOS) 3.18. The lowest FOS 0.36 is in the Quartz window which are proven with an edge crack on the Quartz glass for 41.2Atm pressure. A huge amount of gas combustion products covering visual measurement to get the burning time and regression rate. The increment of pressure increase is successfully covered by the buffer tank.

並列關鍵字

Regression Rate Measurement ； Strand Burner ； Sorbitol

參考文獻

1. Aziz. A., Mamat. R., Wan Ali. W. K., 2013., Development Of Strand Burner For Solid Propellant Burning Rate Studies., 2nd International Conference on Mechanical Engineering Research (ICMER 2013)

doi:10.1088/1757-899X/50/1/012048

2. Crawford, B. L. Jr., Huggett. C., Farrington. D., Wilfong. R. E., 1947., Direct Measurement of Burning Rates of Propellant Powders., Analytical Chemistry., Vol. 19., No. 9

4. Kubota, Naminosuke., 2002., Propellants and Explosives., Wiley-VCH GmbH & Co. KGaA., Japan., pp. 176

(Accessed 2016-01-21)