Heat Transfer Characteristics with Boiling of the Propellant (N₂O₄) for Spacecraft Propulsion

Abstract

MON3 is used as a propellant for the bipropellant thruster in the spacecraft propulsion. MON3 is Nitrogen Tetroxide (N₂H₄) with 3wt% solution of NO. Heat transfer characteristics with boiling of the MON3 have been measured. The critical heat transfer was identified when the superheat temperature was around 50 ℃ (degree C) under different flow parameters. Pressure vibration from 8 to 22Hz frequency was observed in the specific flow parameters during the boiling of MON3. These frequencies are in good agreement with that of combustion perturbations observed in the test injector which simulated the actual bipropellant thrusters.