Abstract
Aerospace grade composite laminated shims are frequently used in aircraft structure assembly of parts made of advance composite materials with High Modulus of AS4 grade. The assembly of composite components requires extensive use of shims compared to metal assembly. The shim use at assembly stage is very time consuming process and poses challenges to maintain the product quality. This paper aims to bring out the statistical and finite element analysis of shims using gaps data taken out of prototype samples. Finite element analysis is carried out without shims and with shims of thickness of 0.8, 1.2 and 2.0 mm. The nature of variation of measured gap and the effect of shims on stress in the wing skin and spar due to static loading are assessed.
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 callMore From: International Journal of Vehicle Structures and Systems
Disclaimer: 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.
