Development and Testing of a Static Hybrid Rocket

Horwill, Chris and Besley, Cliff (2004). Development and Testing of a Static Hybrid Rocket Honours Thesis, School of Engineering, The University of Queensland.

       
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Author Horwill, Chris
Besley, Cliff
Thesis Title Development and Testing of a Static Hybrid Rocket
School, Centre or Institute School of Engineering
Institution The University of Queensland
Publication date 2004
Thesis type Honours Thesis
Supervisor Richard Morgan
Total pages 491
Language eng
Subjects 0913 Mechanical Engineering
Formatted abstract
Hybrid rockets are a relatively new and limitedly researched field of rocketry that uses a solid fuel and a liquid phase oxidiser. Hybrids are becoming more popular due to their excellent safety and cost characteristics in comparison to other forms of rocketry. In 2003 Dean Pannell started the hybrid rocket project with the successful first firing of a hybrid rocket at University of Queensland. The goal of this project was the further optimisation and testing of the initial rocket and the design development and testing of a second larger test rig. These goals were undertaken and completed successfully. The second rig was designed for variation of multiple parameters such as fuel grain length, injector style (including both axial and tangential design), injector size as well fuel grain port design to name just a few. The oxidiser used for both rigs was nitrous oxide due to it’s excellent cost and safety attributes. The two fuels used were PVC and PMMA. Successful firings in the first semester reaffirmed the plausibility of the hybrid concept. Two firings collecting data were obtained using a PVC and nitrous oxide, oxidiser to fuel combination. A oxidiser mass flow rate of 0.05kg/s was obtained and an average thrust reading of 107N. The correlating ISP was 168 s the chamber pressure was an average of 0.65MPa. The observed O:F ratio was a fuel rich 2.45. The experimental regression rate formula was found to be 1.46*10-5 Go^ 0.6. Two firings were completed on the new static rig, one an axial injection PVC and N2O, the other an axial injection PMMA and N2O. The results obtained from this test were: for PVC, maximum thrust 443N, oxidiser mass flow rate of 0.215kg/s, maximum ISP of 172 s and a combustion pressure of 2.3MPa. The O:F ratio was found to be a oxidiser rich 4.13. For PMMA the maximum thrust obtained was 305 N, with an oxidiser mass flow rate of 0.22kg/s, a maximum ISP of 121 s and a combustion pressure of 1.58MPa. The O:F ratio was found to be a heavily oxidiser rich 12.7.
Keyword Static Hybrid Rocket

Document type: Thesis
Collection: UQ Theses (non-RHD) - UQ staff and students only
 
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