Abstract
The present research investigates a case study on thermal design and improvement of hydrazine monopropellant pipelines based on actual cases, in order to highlight the critical factors for thermal design when developing an onboard propulsion system for a satellite. A simple 1-D thermal math model was developed for thermal analysis using the lumped-parameter assumption, and three different thermal design cases of hydrazine propellant pipeline layouts were considered. By increasing heater power densities and applying modified worst cold boundary conditions for thermal analysis, the thermal design performance for the propellant pipelines of an actual satellite could be improved and verified through thermal vacuum test.After the successful operation of the pipeline heaters in the real space environment, some important lessons learned on thermal design improvements of hydrazine monopropellant pipeline layout could be attained from the present case study. These lessons learned will be useful for the future development of satellite onboard propulsion systems.
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.
