Optimisation for clamping force of aircraft composite structure assembly considering form defects and part deformations

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dc.contributor.authorZhang, Wei
dc.contributor.authorAn, Luling
dc.contributor.authorChen, Yuan
dc.contributor.authorXiong, Yeping
dc.contributor.authorLiao, Yabing
dc.date.accessioned2021-04-20T15:35:53Z
dc.date.available2021-04-20T15:35:53Z
dc.date.issued2021-04-15
dc.description.abstractGiven the existence of manufacturing defects and the accumulation of assembly errors, non-compliant assembly appears between components, especially for composite structure assembly. In the engineering application, the clamping force (CF) is often used to eliminate the clearance between mating components, but the improper CF may result in unwanted structure failure. Thus, on the premise of ensuring the safety of composite parts, this study proposes a procedure to systematically optimise the assembly CF. Firstly, the components mating surfaces were obtained by laser scanner, and the matching of actual surfaces was transformed and simplified based on ‘equivalent surface’ concept. Then, a mathematical optimisation model was established. The CF layout and magnitude were taken as variables, and the clearance elimination rate and the overall assembly force value were employed as objective functions. Finally, the improved genetic algorithm (GA) was used to solve this problem. A parametric finite element analysis (FEA) model was built, and model accuracy was verified by physical experiments. The finite element calculation and post-processing were carried out by Python script in ABAQUS®. Compared to the engineer’s traditional approach, the influence of form defects and part deformations were considered, which can help control the assembly stress well and ensure product performance.en_UK
dc.identifier.citationZhang W, An L, Chen Y, et al., (2021) Optimisation for clamping force of aircraft composite structure assembly considering form defects and part deformations. Advances in Mechanical Engineering, Volume 13, Issue 4, April 2021, pp. 1-13en_UK
dc.identifier.issn1687-8132
dc.identifier.urihttps://doi.org/10.1177/1687814021995703
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/16606
dc.language.isoenen_UK
dc.publisherHindawi Publishing Corporation / SAGEen_UK
dc.rightsAttribution 4.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/*
dc.subjectgenetic algorithmen_UK
dc.subjectpart deformationsen_UK
dc.subjectform defectsen_UK
dc.subjectaircraft assemblyen_UK
dc.subjectComposite damageen_UK
dc.titleOptimisation for clamping force of aircraft composite structure assembly considering form defects and part deformationsen_UK
dc.typeArticleen_UK

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