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Hot-Fire Test and Performance Evaluation of Small Liquid-Monopropellant Thrusters under a Vacuum Environment  

Kim Jeong Soo (순천대학교 기계자동차공학부)
Publication Information
Journal of the Korean Society of Propulsion Engineers / v.8, no.4, 2004 , pp. 84-90 More about this Journal
Abstract
A performance evaluation is made in terms of thrust, impulse bit. and specific impulses for a set of mono-propellant hydrazine thrusters producing 0.95 lbf of nominal thrust at an inlet pressure of 350 psia. With a brief description on the hot-firing test configuration and procedures. a typical data obtained from steady-state firing mode is given directly showing the variational behavior of propellant supply pressure, mass flow rate, vacuum condition, and thrust. The performance features are successfully compared to the reference criteria of 1-lbf standard mono-propellant rocket engine. Additionally. a statistical inter-thruster treatment is concisely depicted for the justification of selected thrusters as a grouped member of flight model for spacecraft propulsion system.
Keywords
Propellant Injection Pressure; Steady-State Firing; Pulse Mode Firing; Impulse Bit; Specific Impulse;
Citations & Related Records
Times Cited By KSCI : 2  (Citation Analysis)
연도 인용수 순위
1 Propellant, Hydrazine (Mono-propellant or High Purity Grade), MlL-PRF-26536E
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3 Carlson, R. A., Elmendorf, H. M., and Sackheim, R. L., 'NASA/TRW Standard 5 Newton Thruster,' AlAA Paper 77-962
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7 Kim, J. S., 'Verification Test Plan of Thrust Chamber Assembly (TCA),' K2D0-460-009, KOMPSAT-2 Program Document, 2002
8 Kim, J. S., 'Equipment Specification: Dual Thruster Module, Propulsion System Component,' K2-SP-460-009, KOMPSAT-2 Program Document, 2002