Analysis of Allowable Assembly Forces for Composite Laminates

Composite structures have been widely used in aerospace field due to their low density, high strength, and high stiffness to weight ratio. In the aerospace field, composite laminates are widely used in the skin of the airplane. Due to the complexity of the composite molding process, and the difficul...

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Bibliographic Details
Published in:IOP conference series. Materials Science and Engineering 2019-10, Vol.647 (1), p.12011
Main Authors: Zhang, Tingyu, Zhang, Chong, Zhao, Jianshe, Guo, Anru
Format: Article
Language:English
Subjects:
Assembly
Composite structures
Deformation
Laminates
Machining
Mathematical analysis
Molding (process)
Optimization
Stiffness
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Summary:Composite structures have been widely used in aerospace field due to their low density, high strength, and high stiffness to weight ratio. In the aerospace field, composite laminates are widely used in the skin of the airplane. Due to the complexity of the composite molding process, and the difficulty of machining composite laminates, the manufacturing precision of the skin is usually not very high. Hence the assembly force is applied to the skin to ensure the composite laminates fit the framework in the assembly process of an airplane. However, too large assembly force leads to the assembly out of tolerance owning to the over deformation and leads to the stress of the skin out of tolerance. Therefore, this paper proposes a method of analyzing the allowable assembly force. With the help of mechanics and physics, the mechanical relationship between the assembly forces and the deformation of a skin is modeled. On the basis of the model and the experimental date of a skin assembly process, the mathematical relationship between the assembly forces and the deformation of the skin is established. The allowable assembly forces are determined based on the mathematical relationship and the allowable deformation. This paper provides an optimization methodology of assembly force optimization.
ISSN:1757-8981
1757-899X
DOI:10.1088/1757-899X/647/1/012011