An Experimental Steam Propulsion System for Spacecraft In-Situ Refueling Operations

摘要

A test apparatus was developed to prove the application of steam as a propulsion source for small spacecraft conducting in-situ resource utilization on small gravitational bodies. The apparatus consists of an instrumented aluminum tank outfitted with a heating system, solenoid valve, and SLA 3-D printed exhaust nozzle. Initial testing was performed on a thruster test stand at sea level atmospheric conditions at 10 bar and 160 degrees Celsius. Results show a mean measured thrust force of 6.7N and specific impulse of 73s with steam. Data extrapolation and calculations for an isentropic system indicate that the estimated thrust in a vacuum could be up to 12N with a specific impulse of 133s at the same steam conditions, which is potentially sufficient for use on a low-gravity body such as Ceres.