Open AccessAnalysis of Allowable Assembly Forces for Composite Laminates
Author(s) -
Tingyu Zhang,
Chong Zhang,
Jianshe Zhao,
A. M. Guo
Publication year - 2019
Publication title -
iop conference series. materials science and engineering
Language(s) - English
Resource type - Journals
eISSN - 1757-899X
pISSN - 1757-8981
DOI - 10.1088/1757-899x/647/1/012011
Subject(s) - aerospace , deformation (meteorology) , composite number , stiffness , structural engineering , airplane , machining , molding (decorative) , mechanical engineering , specific strength , process (computing) , composite laminates , materials science , engineering , composite material , computer science , aerospace engineering , operating system
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.