Abstract
The attitude determination problem of Earth Orientation gyro-less spacecraft is studied in this paper. Considering the sensitivity of the initial attitude error for EKF, a new non linear attitude determination filter is developed by using the Special Orthogonal Group SO (3) which avoids any algebraic reconstruction of the attitude from reference vectors. Lyapunov analysis results for the proposed the filter is derived that ensure global stability of the error. The simulation results show that the estimation of attitude and angular velocity converge to the real in the Earth Orientation mode.
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 callMore From: IOP Conference Series: Materials Science and Engineering
Disclaimer: 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.
