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http://dx.doi.org/10.5139/JKSAS.2016.44.7.576

Fuel-rich Combustion with AP added Propellant in a Staged Hybrid Rocket Engine  

Lee, Dongeun (Department of Aerospace Engineering, Konkuk University)
Lee, Changjin (Department of Aerospace Engineering, Konkuk University)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.44, no.7, 2016 , pp. 576-584 More about this Journal
Abstract
In this study, AP added propellant has been proposed as a method of enhancing the low specific impulse performance found for staged hybrid rocket engine. Experimental tests were carried out to analyze and evaluate the effect of AP added propellant on specific impulse performance as well as fuel-rich combustion characteristics in a staged hybrid rocket engine. Upper limit of AP content in propellant was set to be 15 wt% to maintain the hybrid rocket engine advantages. As a result, 15 wt% AP added propellant showed 3% higher specific impulse performance compared to 0 wt% AP added propellant. Moreover, AP addition proved to offer less injected oxidizer mass flow, less O/F variation, and less combustion pressure while producing fuel-rich gas of the same combustion temperature. Future studies will carry out more combustion tests with metal additives to further enhance specific impulse.
Keywords
Staged Hybrid Rocket Engine; Ammonium Perchlorate; Fuel-rich Combustion;
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Times Cited By KSCI : 1  (Citation Analysis)
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