A study of parameters of a pulsed water jet electrothermal propulsion system for a nanosatellite

The paper presents results of experimental and numerical studies of paired startup of a pulse electrothermal propulsion system of a maneuverable nanosatellite with elastic pressurized propellant feed system. Used as the propellant was a mixture of distilled water and ethyl alcohol (40% by mass). To improve reliability of power switches supplying power to the autonomous heater of the micro-engine, the paired startup procedure was studied, which involved preliminary heating of the micro-engine with voltage applied, and the second startup without applying voltage. In order to obtain upper (increased) time values for propellant heating as compared with heating under vacuum and minimal time values for paired startup considering temperature drop by 70-100 °C for a micro-engine with a mass of ~20g and input power of 12-15 W, an experimental propulsion system was developed and experimental studies were conducted under normal atmospheric conditions. Theoretical studies were conducted for the paired startup of propulsion system in a 8 kg maneuverable nanosatellite with delta V budget of 30 m/s. Key design parameters were studied for the paired startup with adjustment factors for timing parameters and the inlet pressure at the nozzle throat section kn = 1; kn function show_eabstract() { $('#eabstract1').hide(); $('#eabstract2').show(); $('#eabstract_expand').hide(); }