Finite Element Simulation and Statistical Analysis of Laminated Composite Shims for Gaps in Aircraft Structures Assembly
Main Article Content
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.
Article Details
Issue
Section
Articles
Authors who publish with this journal agree to the following terms: a. Authors retain copyright and grant the journal right of first publication, with the work two years after publication simultaneously licensed under a Creative Commons Attribution License that allows others to share the work with an acknowledgement of the work's authorship and initial publication in this journal. b. Authors are able to enter into separate, additional contractual arrangements for the non-exclusive distribution of the journal's published version of the work (e.g., post it to an institutional repository or publish it in a book), with an acknowledgement of its initial publication in this journal. c. Authors are permitted and encouraged to post their work online (e.g., in institutional repositories or on their website) prior to and during the submission process, as it can lead to productive exchanges, as well as earlier and greater citation of published work (See The Effect of Open Access).