Abstract
We consider an orbiting spacecraft which consists of a rigid body and a flexible body attached to it. The problem of simultaneous attitude control and vibration suppression of a flexible spacecraft is analyzed in this paper. We derive the equations of motion based on Lagrangian dynamics, taking the motion of instantaneous center of mass into consideration. In the result, we obtain a coupled system of linear partial differential equations governing the elastic vibration of the flexible body and linear ordinary differential equations governing the rotational motion of the rigid body. Since non-standard partial differential equations are derived as a model of the elastic vibration, we consider a finite-dimensional approximation of the solution and its convergence.
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.
