Abstract
In this paper, the design of a fully magnetic attitude control subsystem for a picosat platform is discussed. The developed control law is based on a simple and reliable architecture, which can be easily implemented on small spacecrafts for de-tumbling and three-axis stabilization purposes. The subsystem design follows a practical engineering approach, exploiting global optimization methods, which lead to an integral actuation compliant with typical pointing accuracy requirements for picosat missions. Performance of the proposed attitude control subsystem is demonstrated by numerical simulations.
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.
