Abstract
Folding wings of UAV may lead to high bending and torsion deformation under flight load. In order to solve the problem, an improved folding wing mechanism is proposed, which makes support mechanism stiffness become enough big. By means of CATIA and ADAMS, a virtual prototype is set up, which can simulate dynamics of the deployment mechanism. Therefore the relationship among deployment time and friction coefficient and tension is arrived. Meanwhile finite element analysis is made on folding wing with support structure and without support structure by MSC.Nastran. And the results show that the stiffness and strength change obviously. Simulation results have a certain guiding significance for practical engineering application.
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.
