Abstract
The use of electrodynamic tethers on-board satellites is a promising scientific prospect. While the theory describing such systems have been studied by numerous scientists and mathematicians, practical testing of these systems have been relatively unsuccessful and test data concerning the topic is limited. Low-cost CubeSats offer a cheap platform from which practical tests can be done which would contribute to advancements in the field. The design of an attitude determination and control system for such a CubeSat tether mission is discussed in this paper. This includes the design of a sensor capable of measuring the orientation of the tethered CubeSat pair using a CMOS imager. Further, the study includes the design of an active deployment system, mathematical modeling of the system, formulation of control-algorithms for controlling the tether-orientation, and full orbital simulations of the system.
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.
