Abstract
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.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
