Preliminary study and design of hybrid rocket

C. M. Li, K. W. Shih, H. C. Liu, C. L. Chiu, J. M. Char, W. H. Lai, H. P. Chiu, T. S. Lee

研究成果: Article同行評審


The article presents a preliminary study and design of hybrid rocket which gaseous Oxygen is selected as oxidizers to react with solid HTPB fuel. In order to increase the efficiency and provide the space for the mixture and combustion of the air and propane of ignition system, a pre-combustion is added in front of the main combustion chamber of hybrid rocket. Before testing hybrid rocket, three different methods were used to heat up the HTPB fuel from one atmosphere and room temperature environment for the fundamental processes. The results show when the temperature reaches the flash point (450 °C) the HTPB fuel will bum continuously. One solid grain placed in a combustion chamber is then used for the investigation of the hybrid combustion. The result indicates that hybrid rocket will burn under 600 °C if the flow rate of oxidizers is supplied sufficiently.

頁(從 - 到)235-240
期刊Transactions of the Aeronautical and Astronautical Society of the Republic of China
出版狀態Published - 1999 9月

All Science Journal Classification (ASJC) codes

  • 航空工程


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