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․ Dae Seok Bae****ABSTRACT A liquid-monopropellant hydrazine thruster has several outsta nding advantages such as relatively-simple structure, long/stable propellant storability , clean exhaust products, and so on. Therefore hydrazine thruster has such a wide application as orb it and attitude control system (ACS) for space vehicles. A hydrazine thruster with the medium-level thrust to be used in the ACS of space launch vehicles (SLV) has been developed, and its ground firing test result is presented in terms of thrust, impulse bit, temperature, and chamber pressure. It is v erified through the performance test that the response and repeatability of thrust are very excellent, and the thrust efficiencies compared to its ideal requirement are larger than 93%.      ,   ,             .        ․,        ,  ,         .        ,      93%    .Key Words:Space Launch Vehicle(), Orbit/Attitude Control(  ), Liquid Rocket Engine(), Ground Firing Test(), Pulse Mode()

Pulse-mode Response Characteristics of a Small LRE for the Precise 3-axes Control of Flight Attitude in SLV