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Received Nov 23, 2017; Accepted Jan 17, 2018
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1. Introduction
Advanced resin matrix composites have been widely used in aviation industry due to the special features such as high strength and stiffness, long life, and lightweight [1, 2]. As a kind of manufacturing process, filament winding was proposed to fabricate composite components. With the increased applications of composite wound components, there has been a growing desire for composites parts such as missile cones, rocket hull, pressure vessel, and other engineering fields [3, 4]. However, the residual stresses of composite part will be generated inevitably due to winding tension, thermal expansions, and chemical shrinkage reaction during the manufacturing process. It is well known that the high residual stresses will not only cause the microcracks and the eventual delamination between layers but also significantly reduce the ability to resist load [5–7]. Since the residual stresses of composite highly depend on the process parameters, it is necessary to investigate the stress development of composite components during the fabricating process.
Recently, a series of theoretical models have been developed for studying the stress state of the composite cylinder. Several researchers have previously investigated the development of stress induced by winding tension during the winding process based on the finite difference method and other numerical methods [8–10]. Nevertheless, the curing process is also a dominant factor which affects the residual stress distribution of composite during the whole manufacturing process. Therefore, based on the assumption of micromechanics, the thermal and chemical shrinkage stress models of the composite cylinder had been established during the curing process [11–14]. To accurately determine the residual stress model and predict the stress profile, some authors considered the coupling effects of winding tension and cure parameters on the residual stresses [15–18].
Compared with how to predict the residual stresses, designing process parameters to satisfy requirement of residual stresses has become more meaningful. Kim et al. [19] and Lee et al. [20] proposed a smart cure method to reduce the residual stresses in the thick wound composite cylinder by using finite element method. Ren et al. addressed a...