Demonstration sample research impulse of the propulsion system of nanosatellite

Abstract

The aim of the research is to determine ways to create a pulse corrective propulsion systems of a maneuvering nanosatellite at the early stages of design when forming its design appearance on the basis of experimental and numerical studies of a demonstration sample with a multifunctional flow-through launch chamber and an micro resistojet of a transverse nozzle placement scheme. A pneumohydraulic scheme of a propulsion system with various chokes of a multifunctional flow-through starting chamber has been developed. Experimental and numerical studies of a demonstration sample of a propulsion system confirmed its operability and the possibility of achieving the specified characteristics by changing the interdependent main design parameters in terms of pressure, temperature, specific thrust pulses, duration of operation in various operating modes, and design parameters of a multifunctional flow-through launch chamber. Based on the results of experimental and numerical studies, a 3D model of an improved pulse propulsion system was developed.