Abstract
The paper analyzes the attitude dynamics of a spacecraft while deploying large plate-like structures. Equations governing the rotational dynamics of the system and the lateral vibrations of the panels are obtained using a Lagrangian formulation. Even the linearized equations are unusually lengthy and involve time-varying coefficients. Hence they are integrated numerically for given length histories. Two types of axial extension—uniform and exponential—are considered. The system parameters are varied for the two procedures and their influence on the attitude dynamics is noted.
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.
