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

Research output: Contribution to journalArticlepeer-review


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.

Original languageEnglish
Pages (from-to)235-240
Number of pages6
JournalTransactions of the Aeronautical and Astronautical Society of the Republic of China
Issue number3
Publication statusPublished - 1999 Sep

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering


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