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

Optimisation for clamping force of aircraft composite structure assembly considering form defects and part deformations
Optimisation for clamping force of aircraft composite structure assembly considering form defects and part deformations
Given 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.
Composite damage, aircraft assembly, form defects, part deformations, genetic algorithm, aircraft assembley, form defects, genetic algorithm, part deformations
1687-8132
1-13
Zhang, Wei
5f0adb29-aa4e-4c9c-abd1-4bd55774563c
An, Luling
1b9b32d4-8a67-4e65-8e62-3cfac307e6bb
Chen, Yuan
845eef62-abbd-478c-ad09-a3dc2bcc6b1e
Xiong, Yeping
51be8714-186e-4d2f-8e03-f44c428a4a49
Liao, Yabing
7158c59b-58ed-49b3-b16d-1d0b54a51524
Zhang, Wei
5f0adb29-aa4e-4c9c-abd1-4bd55774563c
An, Luling
1b9b32d4-8a67-4e65-8e62-3cfac307e6bb
Chen, Yuan
845eef62-abbd-478c-ad09-a3dc2bcc6b1e
Xiong, Yeping
51be8714-186e-4d2f-8e03-f44c428a4a49
Liao, Yabing
7158c59b-58ed-49b3-b16d-1d0b54a51524

Zhang, Wei, An, Luling, Chen, Yuan, Xiong, Yeping and Liao, Yabing (2021) Optimisation for clamping force of aircraft composite structure assembly considering form defects and part deformations. Advances in Mechanical Engineering, 13 (4), 1-13. (doi:10.1177/1687814021995703).

Record type: Article

Abstract

Given 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.

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More information

Accepted/In Press date: 8 January 2021
e-pub ahead of print date: 15 April 2021
Published date: 15 April 2021
Keywords: Composite damage, aircraft assembly, form defects, part deformations, genetic algorithm, aircraft assembley, form defects, genetic algorithm, part deformations

Identifiers

Local EPrints ID: 448325
URI: http://eprints.soton.ac.uk/id/eprint/448325
ISSN: 1687-8132
PURE UUID: 6401810c-96c6-4eec-a293-c3f6b745e0d7
ORCID for Yeping Xiong: ORCID iD orcid.org/0000-0002-0135-8464

Catalogue record

Date deposited: 20 Apr 2021 16:32
Last modified: 26 Nov 2021 02:44

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Contributors

Author: Wei Zhang
Author: Luling An
Author: Yuan Chen
Author: Yeping Xiong ORCID iD
Author: Yabing Liao

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