Abstract
Finite element method using three-noded plate and shell element and 3D beam element in conjunction with mode superposition method is employed for studying the large dynamic displacement response of a typical payload fairing due to a typical separation impulse. Incremental technique is used for solving the geometric non-linear problem. Linear formulations are assumed and a step-by-step analysis is performed on the deformed state of each previous time step. The geometry is updated and the stiffness matrix recomputed after every finite time step and the eigenvalue analysis repeated. The formulations are validated using NASTRAN and NISA finite element packages. The results are compared with the linear analysis and the significance of the geometric non-linearity is stressed.
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.
