Abstract
PurposeThe purpose of this paper is to analyze the results of the Jacobian matrix linearization of the satellite attitude dynamics with modified Rodriguez parameters (MRP) as attitude representation.Design/methodology/approachThe satellite dynamics is linearized using Jacobian differentiation around origin and reference values of the MRP. The controller is designed through linear quadratic regulation approach.FindingsIt is found that, for both cases the overall system converges but there exists a tracking error. The error can be reduced by increasing the controller coefficients in both cases however cannot be eliminated. In the case of linearization around zero, the torque requirements are quite higher than the case of linearization around the reference attitude trajectory.Originality/valueThe attempt of Jacobian linearization of a satellite dynamics with the MRP as the attitude representation constitutes the value of this paper. In addition, the results obtained in the derivations may be used in future research.
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.
