Selection of project structure for nanosatellite propulsion system

This paper presents the results of theoretical and experimental research of a prototype of a propulsion system for periodical low-Earth orbit correction of research-and-educational nanosatellites. For that purpose, the prototype is to provide at least 20 m/s relative velocity for a 3U CubeSat with a mass not exceeding 4.5 kg. The personnel and environment safety were taken into account during testing and operation along with the ability to be launched as an associated payload by a Soyuz-series launch vehicle or from the ISS. An electro-thermal propulsion system (ResistoJet) was designed with nonfreezing mixture of ethanol and distilled water used as the working fluid. It is shown that a standard vehicle power system is capable of initiating one corrective thrust impulse per orbit with flight velocity change of about 0.1 m/s by introducing pulse energy storage units and allocating sufficient time for their charging in the flight profile. The propulsion system prototype was tested in atmospheric conditions. For that purpose shortened atmospheric nozzles were used. Testing was carried out using a zero-torque test-bench with high-speed cameras. The measured thrust value was in agreement with the calculated value of 44 mN.