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http://dx.doi.org/10.6108/KSPE.2014.18.4.018

An Analysis and Reduction Design of Combustion Instability Generated in Hybrid Rocket Motor  

Lee, Jungpyo (Aerospace Engineering, Universidade de Brasilia)
Rhee, Sunjae (R&D Planning & Coordination Division, Korea Aerospace Research Institute)
Kim, Jinkon (School of Aerospace & Mechanical Engineering, Korea Aerospace University)
Moon, Heejang (School of Aerospace & Mechanical Engineering, Korea Aerospace University)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.18, no.4, 2014 , pp. 18-25 More about this Journal
Abstract
In this paper, the mechanism of the combustion instability which may occur in a hybrid rocket motor with a diaphragm was studied. And the new design for a hybrid motor grain was suggested. It could increase a regression rate of solid fuel, and reduce a large pressure oscillation in a hybrid rocket motor with a diaphragm. It was confirmed that the main mechanism of a large pressure oscillation was hole-tone, and it was caused by a collision between a diaphragm and a vortex which was generated in a pre-chamber. And 'Stepped Grain' design which had the mechanism for high regression rate in a motor with a diaphragm and could reduce a combustion instability was suggested.
Keywords
Hybrid Rocket; Diaphragm; Combustion Instability; Hole-tone; TC Coupled;
Citations & Related Records
Times Cited By KSCI : 1  (Citation Analysis)
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