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This paper deals with the influence of variation in combustion chamber pressure on an arcjet plasma source for an arcjet-assisted thruster. Arcjets have been applied to chemical thrusters in order to promote combustion and augment performance. Some groups reported that combustion of solid propellant and monopropellant such as SHP163 was successfully sustained with arcjet. Arc discharge is, however, negatively influenced by variation in combustion chamber pressure. Hence, we propose to apply active control to arcjet-assisted chemical thruster in order to stabilize combustion. The controller design requires the response of arcjets to variation in combustion chamber pressure variation. In this study, we investigated the influence of step-like pressure change on arcjet exit using a combustion chamber simulator. In the combustion chamber simulator, pressure was suddenly increased from 0.1 to 0.35 MPa using a nitrogen-filled buffer with a burst diaphragm. For a pressure rise of 0.15 MPa with a time constant of 0.2 s, arc discharge was interrupted immediately after sudden rise in pressure of the combustion chamber simulator. From the results, arcjet was negatively affected by the combustion chamber pressure.

Response of the Arc Plasma Source to Combustion Chamber Pressure Fluctuation of the Small Size Thruster Using Plasma Support Combustion