Abstract
The staged combustion hybrid rocket is under development by our research group since 1999. This hybrid rocket engine consists of two combustion chambers. The primary combustion chamber is the lower part of the very fuel tank itself filled with granular solid fuels. The fuel rich gas generated by the first stage combustion flows into the secondary combustion chamber, which is located in the bottom core part of the primary combustion chamber. The additional oxidizer is injected to the secondary combustion chamber in order to attain an optimal specific impulse by completing combustion. This new type engine is featured with a wide range throttling capability and an extensive freedom in selecting the fuel material. This paper deals with an outline of our preliminary experiments in addition to thesystems description.
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