Abstract
In the process of deploying the wings of solar arrays of a spacecraft, natural transverse vibrations arise in them. The study of these vibrations is an urgent problem, since in some cases they are capable of disrupting the commutation of photoelectric converters. The transverse vibrations of the wing originate from the connection of its sections when locking (coupling) hinge devices. In this case, the kinetic energy of the sections is converted into the potential energy of natural vibrations of the solar array wing. This problem is traditionally solved by using a finite element model with subsequent calculations in the ANSYS program. The purpose of this study is to develop an approximate analytical method for mathematical modeling of the natural elastic vibrations of elements of the solar array wing arising in the process of its deploying.
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.
