Test and Evaluation of a 70 N-class Hydrazine Thruster for Application to the Precise Attitude Control of Space Vehicles

摘要

A liquid-monopropellant hydrazine (N_2H_4) thruster has several outstanding advantages such as relatively simple structure, long/stable propellant storability, clean exhaust products, and so on. Therefore hydrazine thruster has a wide application up to date as an attitude control system (ACS) for a lot of space vehicles. A hydrazine thruster of medium-level thrust to be used in the ACS of space launch vehicles (SLV) has been developed, and its ground hot-firing test (HFT) result is presented in terms of thrust, specific impulse, temperature, and chamber pressure according to various propellant supply pressures (0.34 to 2.41 MPa). Nozzle jet image captured by infrared (IR) camera is examined for the qualitative observation of nozzle exhaust gases. It is experimentally ensured that the performance efficiencies are above 90% compared to its ideal requirements.