Abstract
Hydrazine is toxic and carcinogenic,which greatly increases the difficulty of application and no longer meets the needs of green aerospace.As a green propellant,the Ammonium Dinitra-mide(ADN)-based liquid propellant has the advantages of higher specific impulse,being non-toxic,pollution-free,and easy storage.However,an ADN-based space engine in orbit has exposed the problems of high-temperature deactivation of catalysts and cold-start failure.An active ignition technology—electric ignition technology was explored in this paper to break through the technical bottleneck of catalyst deactivation and the inability to a cold start.An experimental system of a constant-volume combustor for the ADN-based liquid propellant based on the electric ignition method was established.The electric ignition and combustion characteristics of the ADN-based liq-uid propellant in a volume combustor with an electric ignition method were studied.The influencing mechanisms of the ignition voltage and the electrode structure on the electric ignition characteristics of the ADN-based liquid propellant were investigated.An elevation of the ignition voltage could facilitate the ignition process of the ADN-based liquid propellant,curtail electric energy input and heating effect,while exerting an adverse impact on the combustion process of the propellant.An increase in the ignition voltage enhanced the ignition process of the propellant while simultane-ously suppressing its combustion process when utilizing mesh electrodes.Compared to the strip electrodes,the mesh electrodes increased the contact area between the electrodes and the propellant,increased the electric energy input power in the electric ignition process,and reduced the ignition delay time.The mesh electrodes could promote the combustion process of the propellant to a cer-tain extent.
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