Abstract
In this paper we will derive feedback laws to stabilize the attitude motion of a rigid spacecraft in finite time. The laws are such that a cost functional measuring the overall angular velocity during the spacecraft motion is minimized. The implementation of these laws in an on-board attitude control system requires only autonomous attitude determination capabilities and no measurements of the angular velocities.
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.
