Abstract
A computational approach is devised for the design of propellant-settling systems in rockets and spacecraft for engine restart in low-gravity. Using a worst-case design approach, twelve numerical experiments are conducted simulating the liquid slosh dynamics during various mission scenarios of an orbital spacemaneuvering vehicle. The results indicate that both the liquid kinetic energy and center-of-gravity histories exhibit characteristic shapes that become asymptotic with time. Analysis of these parameters along with visual measurement of slosh wave magnitudes are used to determine the thruster burn times required to adequately settle propellant over the tank outlet. For the vehicle and tank studied, the settling time is a function of tank fill level and varies from 65-85 seconds. Background
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.
