Experimental research on low-cost cold gas propulsion for a space robot platform

The attitude and orbit control system of satellites and space probes plays a crucial role in missions. One commonly used attitude control method relies on small rocket thrusters. This paper focuses on experimental research into a low thrust, cold gas satellite thruster, which is the simplest solution in this group. A dedicated research stand was designed and built to measure the key parameters of the thruster: thrust and mass flow rate. The measurements were used to calculate specific impulse and to compare it against expected values. Dynamic parameters were also identified - delay time and valve opening time, and power consumption of the coil. Minimum impulse bit and maximum frequency of operation were determined through research with pulse width modulation. A multicycle experiment was conducted to investigate the effect of the number of cycles on thruster parameters. A detailed description of the research stand and measurement methods is given, followed by the results.