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http://dx.doi.org/10.6108/KSPE.2014.18.3.048

Design and Hot Fire Tests of the Pyrostarter for Liquid Rocket Engines  

Kang, Sang Hun (Department of Aerospace System Engineering, Sejong University)
Jang, Jesun (Supply System Team, Korea Aerospace Research Institute)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.18, no.3, 2014 , pp. 48-55 More about this Journal
Abstract
In present study, design and hot fire tests of the pryostarter are conducted. To prevent the turbopump RPM overshoot, regressive mass flow rate profile is applied. Sudden decrease of the mass flow rate at the end of the propellant burning is realized as well. Firing test results show good agreements with the design requirements. Through the study with ignition substance variations, combustion products and ignition performances are improved.
Keywords
Pyrostarter; Solid Propellant; Grain Design; Regressive Profile;
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Times Cited By KSCI : 1  (Citation Analysis)
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