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http://dx.doi.org/10.5139/JKSAS.2004.32.9.122

Performance Characteristics of Thrust Measurement System for Hot-Firing Test of Small Liquid Propulsion Engines  

Kim, In-Tae (한국항공우주연구원)
Huh, Hwan-Il (충남대학교 항공우주공학과)
Kim, Jeong-Soo (순천대학교 기계자동차공학부)
Jang, Ki-Won ((주)한화 대전공장)
Lee, Jae-Won ((주)한화 대전공장)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.32, no.9, 2004 , pp. 122-129 More about this Journal
Abstract
An accurate thrust measurement is one of the critical paths to the successful test and evaluation program of small liquid propulsion engines. This study describes the design factors for the development of thrust measurement system (TMS) as well as manufacturing practice of TMS hardware. We investigate characteristics of the TMS and its performance through hot-firing test of small liquid engine in a vacuum test cell which is capable of simulating 100,000 ft of altitude or higher. For performance test of TMS, we measure thrusts by changing propellant injection pressure at steady state firing mode as well as at pulse firing mode. Measured eigen frequency of the TMS is 67 Hz. Linearity test of the TMS shows good performance with less than 0.5% of linearity error.
Keywords
Thrust Measurement System; Hot-Firing Test; Performance Characteristics; Mono-propellant Thruster; Measurement Uncertainty Analysis;
Citations & Related Records
Times Cited By KSCI : 1  (Citation Analysis)
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