Zezhong WANG  , Yi WU  , Xilong YU  , Xin LIN  , Fei Li

DoI Number XXX-YYY-ZZZ

Conference Number HiSST 2018_40401144

With H2O2/paraffin-based fuel as the propellant, the effects of fuel composition and post-combustion chamber length on combustion performance of hybrid rocket motor have been experimentally investigated. Since the mechanical strength of pure paraffin wax or paraffin-based fuel mixed with HTPB cannot satisfy the requirements of practical application of hybrid rocket motor, additives to pure paraffin fuel are necessary to enhance the mechanical property of paraffin-based fuel. It shows that the mechanical strength of paraffin-based fuels can be effectively enhanced by adding a variety of additives such as polymer waxes, hardeners, tackifier, etc. Regression rate of the paraffin based fuel with additives were then measured in the present work using a lab scale hybrid rocket motor. Experimental results have been compared with data of regression rate found in literature and with HTPB fuel. It is found that this novel fuel proposed in the present work has a much higher regression rate than traditional solid fuel (HTPB). In addition, by changing the length of post-combustion chamber, the effect of the length of post-combustion chamber on the combustion performance of paraffin-based fuel hybrid rocket motor has been investigated. The results show that even though fuel consumption increased with a shorter post-combustion chamber length, there are no significant differences in thrust and combustion pressure, meaning that the increase of post-combustion chamber length can effectively improves the combustion performance of hybrid rocket motor.

Read the full paper >

In Categories: Advanced Chemical Propulsion, HiSST 2018, Propulsion and Thrust Dynamics, Propulsion Systems and Components, Propulsion Technologies, Space Propulsion
Email
Print
LinkedIn
The paper above was part of  proceedings of a CEAS event and as such the author has signed a publication agreement to have their paper published in the repository. In the case this paper is found somewhere else CEAS always links to the other source.  CEAS takes great care in making the correct content available to the reader. If any mistakes are found  in the listings please contact us directly at papers@aerospacerepository.org and we will correct the listing promptly.  CEAS cannot be held liable either for mistakes in editorial or technical aspects, nor for omissions, nor for the correctness of the content. In particular, CEAS does not guarantee completeness or correctness of information contained in external websites which can be accessed via links from CEAS’s websites. Despite accurate research on the content of such linked external websites, CEAS cannot be held liable for their content. Only the content providers of such external sites are liable for their content. Should you notice any mistake in technical or editorial aspects of the CEAS site, please do not hesitate to inform us.