Finite element modeling of the filament winding process

A finite element model of the wet filament winding process was developed. In particular, a general purpose software for finite element analysis was used to calculate the fiber volume fraction under different process conditions. Several unique user defined subroutines were developed to modify the commercial code for this specific application, and the numerical result was compared with experimental data for validation. In order to predict the radial distribution of the fiber volume fraction within a wet wound cylinder, three unique user defined subroutines were incorporated into the commercial finite element code: a fiber consolidation/compaction model, a thermochemical model of the resin and a resin mixing model. The fiber consolidation model describes the influence of the external radial compaction pressure of a new layer as it is wound onto the surface of existing layers. The thermochemical model includes both the cure kinetics and viscosity of the resin. This model analyzes the composite properties and tracks the viscosity of the resin, which is a function of the degree of cure of the resin. The resin mixing model describes the mixing of “old” and “new” resin as plies are compacted. Validations were made by comparing image analysis data of fiber volume fraction in each ply for filament wound cylinders with the FEM results. The good agreement of these comparisons demonstrated that the FEM approach has can predict fiber volume fraction over a range of winding conditions. This approach, then, is an invaluable tool for predicting the effects of winding parameters on cylinder structural quality.     

Consolidation and Warpage Deformation Finite Element Analysis of Filament Wound Tubes

This paper presents a process model for simulating the manufacturing process of prepreg filament wound composite tubes developed based on the finite element analysis. The model relates the process variables, such as degree of cure, viscosity, material property and temperature etc., to the parameters characterizing (residual stresses, warpage deformation) the composite tube and the mandrel. From the simulating results, several important trends in both the data and model are observed (1) Low temperature will go with low reaction rate and the reaction starts under low temperature will later compared with high temperature; (2) The results using CHILE model after demolding will smaller than the one using linear elasticity which assumes a stress-free prior to cool-down. After the mandrel (mold) is removed, some residual stresses, especially hoop stress will be released. (3) Remarkable stress concentration appeared in the transition zone between the boss and cylinder. In order to prevent the structural failure due to interlaminar shear or delamination, both the outer surface of the cylinder and the inner of the boss should have the same ply orientation angle.     

考虑纤维体积含量变化的纤维缠绕厚壁柱形结构的等强度设计

纤维缠绕厚壁柱形管道或容器在缠绕张力作用下会使缠绕纤维层的应力状态不断变化,形成沿壁厚力学性能非均匀的结构。依据缠绕过程中的纤维束应力状态分析和纤维束本构关系,获得了纤维体积含量与所受应力状态的关系。基于正交各向异性本构关系和双层筒模型的离散叠加法,建立了给定缠绕张力确定纤维缠绕厚壁柱形结构剩余张力的计算方法,并计算了等张力缠绕纤维层的纤维体积含量沿壁厚的分布。利用Tsai-Wu失效准则研究了纤维体积含量非均匀的厚壁柱形结构的纤维层强度。研究表明:缠绕工艺使内层纤维体积含量和强度均略高于外层,纤维缠绕厚壁柱形结构的强度分析和设计时应考虑这种影响;利用变化的缠绕张力设计可以实现强度比沿壁厚的均匀分布。     

厚壁复合材料管纤维缠绕张力的神经网络设计方法

提出了一种纤维缠绕厚壁复合材料管的张力优化设计方法。介绍了纤维缠绕控制系统的工作原理, 并讨论了缠绕厚壁复合材料管成型质量的影响因素。针对厚壁复合材料管纤维缠绕过程, 利用弹性叠加原理建立了计算缠绕张力导致复合材料管残余内应力变化的模型和方法。分别比较了利用现有恒张力、 恒力矩和锥度张力三种常规模式缠绕厚壁复合材料管的内应力分布特性。设计了一种独特的神经网络结构, 并通过误差反向传播实现了对纤维缠绕张力的优化设计。以实验验证说明神经网络收敛优化过程的主要机制, 结果表明, 通过该神经网络优化的纤维缠绕张力能满足特殊内应力(如等应力)分布设计的需要。     

复合材料纤维张力缠绕预应力场动态特性

复合材料纤维张力缠绕技术通过提高纤维的张力水平可充分发挥纤维高强、高模优势,在成型过程中对结构进行预紧,成为解决高速转动部件径向变形大、界面强度低等问题新的有效途径。将每一层纤维的张力缠绕等效为一个含预应力复合材料薄环的叠加,基于正交各向异性复合材料缠绕层和各向同性金属芯模弹性变形理论,建立了纤维张力缠绕力学解析模型,得到芯模和缠绕层预应力场随缠绕层数及缠绕张力的变化规律,并通过复合材料纤维张力工艺试验验证了力学解析模型的正确性。研究发现了纤维张力缠绕中预应力“饱和”现象,并确定了影响张力缠绕预应力场的两个主要参数:缠绕层环径向刚度比E_θ/E_r和张力大小T（r）,为复合材料纤维张力缠绕成型工艺提供理论支撑。      

复合材料干纤维增强回转体结构缠绕线型设计

复合材料干纤维缠绕增强结构可解决纤维缠绕树脂基复合材料结构耐冲击性差、低温环境树脂易失效等问题。干纤维增强结构缠绕过程中,纤维束重叠、压缩导致干纤维缠绕增强层各处厚度不一,会对缠绕线型稳定性产生影响。为满足缠绕线型稳定,研究了测地线干纤维缠绕增强层厚度变化及分布规律,分析了纱带宽度、极孔尺寸及芯模结构等参数对增强层厚度的影响,考虑芯模厚度的变化,逐层更新干纤维缠绕增强结构数学模型,进行了缠绕轨迹计算,获得测地线缠绕线型。缠绕实验表明：理论仿真获得的复合材料干纤维缠绕增强容器增强层厚度准确,缠绕线型稳定,无滑纱现象,验证了纤维厚度与缠绕轨迹计算方法的可行性和干纤维增强层厚度仿真的正确性。     

纤维缠绕复合材料壳体刚度衰减模型数值模拟

应用微分几何理论,推导出纤维缠绕复合材料壳体的非测地线缠绕轨迹、包角方程及绕丝头运动方程,得到缠绕过程的动态仿真模拟数据。将封头处变化的缠绕角、厚度等实际工艺参数直接用于壳体结构的理论分析。采用叠层的增量本构关系,模拟层合板壳结构的损伤过程,建立了损伤后刚度衰减模型及刚度退化准则,并通过实验确定了刚度衰减系数。应用此模型对纤维缠绕复合材料压力容器进行了数值分析。结果表明:纤维缠绕复合材料压力容器封头处损伤会导致其弯曲刚度降低,这是影响轴向变形的重要因素。      

The hybrid-adjoint method: a semi-analytic gradient evaluation technique applied to composite cure cycle optimization

A method is presented for determining the optimal autoclave temperature history for pre-impregnated thermoset composites based on their failure performance. A coupled finite-element model that incorporates a thermochemical and incremental elastic analysis is used to predict the residual stress distribution at the edge of a thick composite beam. The optimal autoclave temperature is sought using a gradient-based optimization algorithm. The objective is designed to maximize the minimum failure load of the manufactured beam amongst a set of load cases, while the constraints are imposed to ensure that the composite is uniformly cured and does not sustain temperature damage during the manufacturing process. The hybrid-adjoint, a novel semi-analytic gradient evaluation technique is developed, that incorporates elements of both the adjoint and direct sensitivity methods. Results demonstrate that the method is highly accurate and competitive with a full adjoint approach for a moderate number of design variables.     

Advances in the development of built-in diagnostic system for filament wound composite structures

Monitoring the structural integrity of filament wound composite structures such as solid rocket motor cases and liquid fuel bottles can help prevent catastrophic failures and prolong their service life. An integrated structural health monitoring system has been developed by Acellent as a non-destructive evaluation tool for detecting hidden damage in filament wound composite structures. The system includes a built-in sensor network, supporting diagnostic hardware and data processing/analysis software. A prototype of a filament wound composite bottle with embedded SMART Layers has been fabricated successfully at NASA Marshall Space and Flight Center. This demonstrated the compatibility of the SMART Layer to filament winding process. Impact tests were performed on the prototype bottle to generate damage. A scan of the entire bottle by the distributed network of sensors using Acellent’s diagnostic system was able to locate the damage. The built-in signal processing and imaging techniques employed by the software demonstrated the ability of the software to display the impact damage with relative ease in the face of temperature change.     

多角度交替缠绕复合圆筒的剩余应力算法及水压试验

针对含薄壁钢内衬碳纤维增强聚合物基复合材料（CFRP）多角度交替缠绕复合圆筒的剩余应力计算问题,基于正交各向异性材料的厚壁圆筒理论和弹性叠加理论,提出了考虑卸去芯模影响的多角度交替缠绕下CFRP各层和钢内衬剩余应力的逐层叠加算法,研究了恒缠绕张力下,芯模厚度和螺旋层缠绕角对CFRP各层和钢内衬剩余应力的影响。计算表明：芯模厚度越大则CFRP层剩余应力越低,但芯模厚度过大将减弱缠绕张力对钢内衬的强化效应;螺旋层缠绕角约65°时,环向层剩余应力出现极小值,螺旋层剩余应力和内衬剩余应力均出现极大值。针对缠绕张力对钢内衬的强化效应,通过水压试验加载过程中钢内衬声发射特征与复合圆筒外壁应变测试,测得的钢内衬屈服载荷与理论预测值一致,基本证实了算法的有效性。为提高CFRP层缠绕质量,基于等剩余应力假设,提出了多角度交替缠绕张力制度优化设计思路,适用于内压管的张力制度优化。     

缠绕线型对缠绕复合材料圆管轴向拉伸失效的影响

采用细观刚度模型的有限元分析（FEA）与改进的逐渐累积损伤方法相结合,建立了缠绕复合材料圆管轴向拉伸失效的分析方法与流程,以揭示缠绕线型对缠绕复合材料损伤失效的影响。对沿圆周方向分布有1个、3个和5个单胞的3种不同线型的缠绕复合材料圆管试件进行轴向拉伸破坏实验,获得其失效形式、平均拉伸强度及其随缠绕线型的变化规律。研究表明：缠绕复合材料圆管轴向拉伸失效主要以丧失承载能力的功能失效为主,缠绕线型对其拉伸强度有一定的影响;数值分析结果表明,轴向拉伸过程中,主要损伤为基体开裂与基纤剪切,纤维交叉容易引起损伤起始与扩展。     

具有金属内衬复合材料纤维缠绕容器固化过程的数值模拟

基于固化反应动力学、热传导和复合材料层合理论, 采用了有限元分析方法, 对具有金属内衬的复合材料纤维缠绕压力容器在固化工艺过程中的温度和热应力分布及其变化规律进行了数值模拟。通过一典型容器数值分析, 表明在固化工艺过程中, 中容器内部的所有应力分量具有同时达到峰值的特征, 其中应力分量的峰值出现在固化降温阶段的初期。提出了数值模拟的方法和分析结论对复合材料结构设计师和工艺师合理制订金属内衬复合材料纤维缠绕容器的工艺标准具有一定的参考价值。      

纤维束张紧力缠绕复合材料飞轮初应力的三维数值分析

利用平面应力型全弹性模型的思想(即将纤维束张紧力缠绕看成多层复合材料薄环连续过盈装配的过程) , 建立了三维纤维束张紧力缠绕复合材料飞轮初应力分析模型, 并给出了基于面-面接触算法求解张紧力缠绕复合材料飞轮初应力的三维数值方法。算例分析表明, 三维数值分析得到的飞轮的环向初应力及径向初始压应力(数值) 均略低于平面应力模型的结果, 且这种差距随着飞轮轴向长度的增加而缓慢增大; 三维分析证实了平面应力模型关于张紧力缠绕复合材料飞轮的初应力分析有足够的精度。最后给出了三维模型轴向效应的表征方法。      

Cure behaviour of visible light activated dental composites

In this paper, the non-isothermal cure behaviour of a dental composite, activated by visible light, is described using a heat transfer model that, coupled with a reaction kinetic expression, is able to predict the temperature and the degree of reaction in the composite. The temperature and the degree of reaction profiles inside the composite are calculated, as a function of the cure time, taking into account the system geometry, the thermal diffusivity of the composite, and the resin reaction rate. Material properties, boundary and initial conditions and the kinetic behaviour are the input data of the heat transfer model. Once the degree of reaction is known, the glass transition temperature profiles across the thickness of the composite are calculated. Experimentally measured glass transition temperatures are used for the evaluation of an extinction coefficient capable of accounting for the effects of the light absorption through the thickness on the polymerization kinetics. Finally, the effects of the non-isothermal cure conditions on the application of these materials in dental restorations are discussed.     

Influence of filament winding parameters on composite vessel quality and strength

An experimental design investigation of manufacturing and design variables that affect composite vessel quality, strength, and stiffness was conducted. Eight 20-in. cylinders (with one additional cylinder as a replicate) were manufactured and tested for hoop strength, hoop stiffness, fiber and void volume fraction distribution through thickness, residual stress, and interlaminar shear strength. Material and processing variables were divided into five categories: (a) resin, (b) fiber, (c) fabrication process, (d) design, and (e) equipment. Five variables were selected (from a list of 12) for study using a 1/4 fractional factorial design of experiment setup. The five variables were: (a) winding tension, (b) stacking sequence, (c) winding-tension gradient, (d) winding time, and (e) cut-versus-uncut helicals.

Statistical analysis of the data shows that the composite vessel strength was affected by the manufacturing and design variables. In general, it was found that composite strength was significantly affected by the laminate stacking sequence, winding tension, winding-tension gradient, winding time, and the interaction between winding-tension gradient and winding time. The mechanism that increased composite strength was related to the strong correlation between fiber volume in the composite and vessel strength. Cylinders with high fiber volume in the hoop layers tended to deliver high fiber strength.     

Burst Pressure Prediction and Structure Reliability Analysis of Composite Overwrapped Cylinder

Based on strength design for thin-walled isotropic cylinders and mechanical properties for the composite material, the equation to predict burst pressure of the composite overwrapped cylinder is established. Based on the equation, a structure reliability model is proposed to estimate the reliability of composite overwrapped cylinder by the advanced first order and second moment (AFOSM) method. The layer thicknesses, spiral winding layer angles, and the internal pressure are treated as random variables which obey normal distribution. Results shows that, the reliability of composite cylinders is reduced with the thickness of winding layers decreasing, and the thickness of loop winding layers plays the leading role on the reliability analysis. When the composite cylinder is operated in a low-level pressure, the reliability is not sensitive to the variation of the angle of spiral winding layers. And there will be a superior reliability, when the angle of spiral winding layers is within a certain range. Reducing variance of random variables is feasible to improve the structure reliability. The research also employs a reliability-based optimal design in the perspective of thickness and angles of composite winding layers. The strength of the optimized cylinder has been raised by 0.7% on the premise of cost saving and weight loss.     

A Method for Cure Process Design of Thick Composite Components Manufactured by Closed Die Technology

During the manufacture of polymer-matrix composite components the cure degree must be uniform to have a good quality of the product. For thick composite components this condition is not often respected in fact the cure degree trend between the core and the external surface is different causing structural and geometrical/dimensional unconformities. In most cases, these problems are caused by a wrong design of cure process in terms of thermal cycle and tooling, therefore the cure cycle must be designed and optimized. The optimization of cure thermal cycle should include several performance criteria for the production system such as the targeted cure degree, the targeted maximum temperature of the part and the duration of the cure cycle as well as the production system limitations such as the maximum allowable heating rate, the maximum allowable cooling rate etc. This work aims to define by thermochemical phenomena a first step toward the definition of a method to optimize the cure degree of a thick composite components by focusing particular attention to the aspects of thermal degradations and residual stress.     

Self-reinforced poly(ethylene terephthalate) composites by hot consolidation of Bi-component PET yarns

Self-reinforced polymer composites or all-polymer composites have been developed to replace traditional glass-fibre-reinforced plastics (GFRP) with good lightweight, mechanical and interfacial properties and enhanced recyclability. Poly(ethylene terephthalate) (PET) is one of the most attractive polymers to be used in these fully recyclable all-polymer composites, in terms of cost and properties. In this work, unidirectional all-PET composites were prepared from skin–core structured bi-component PET multifilament yarns by a combined process of filament winding and hot-pressing. During hot-pressing, the thermoplastic copolyester skin or sheath layers were selectively melted to weld high-strength polyester cores together creating an all-PET composite. Physical properties of the resulting composites including thickness, density and void content were reported. The effect of processing parameters, i.e. consolidation temperature and pressure on mechanical properties and morphology was investigated in order to balance good interfacial adhesion with residual tensile properties of the composite.     

纤维缠绕环形压力容器线型设计与仿真

纤维缠绕环形容器要求满足线型稳定和结构优化两个条件.基于微分几何理论,提出了用于复合材料环形压力容器成型的纤维缠绕线型,分析了芯模和吐丝嘴的缠绕速比,给出了缠绕参数优化设计方法.在对优化线型进行分析的基础上,模拟环形容器的纤维缠绕过程,实现了环形容器成型的计算机优化与图形仿真.通过应用缠绕仿真系统,可以检验线型模式的正确性和可行性.结果表明,优化设计的线型模式精确可靠,满足纤维缠绕的基本要求,为微机控制环形容器缠绕奠定了理论基础.     

Damage Model and Progressive Failure Analyses for Filament Wound Composite Laminates

Recent improvements in manufacturing processes and materials properties associated with excellent mechanical characteristics and low weight have made composite materials very attractive for application on civil aircraft structures. However, even new designs are still very conservative, because the composite failure phenomenon is very complex. Several failure criteria and theories have been developed to describe the damage process and how it evolves, but the solution of the problem is still open. Moreover, modern filament winding techniques have been used to produce a wide variety of structural shapes not only cylindrical parts, but also “flat” laminates. Therefore, this work presents the development of a damage model and its application to simulate the progressive failure of flat composite laminates made using a filament winding process. The damage model was implemented as a UMAT (User Material Subroutine), in ABAQUS^TM Finite Element (FE) framework. Progressive failure analyses were carried out using FE simulation in order to simulate the failure of flat filament wound composite structures under different loading conditions. In addition, experimental tests were performed in order to identify parameters related to the material model, as well as to evaluate both the potential and the limitations of the model. The difference between numerical and the average experimental results in a four point bending set-up is only 1.6 % at maximum load amplitude. Another important issue is that the model parameters are not so complicated to be identified. This characteristic makes this model very attractive to be applied in an industrial environment.