Composite panels for reducing noise in air conditioning and ventilation systems

The plate silencer [1] that consists of an expansion chamber with two side-branch cavities covered by a light panel can achieve a desirable noise reduction in broadband theoretically. The concept is similar to drum silencer [Choy YS, Huang L. Experimental studies of drum-like silencer. J Acoust Soc Am 2002;112:2026–35]. To attain optimal noise reduction, either the membrane of the silencer should be of minimal weight while retaining very high tensile strength or the panel should be kept at very high bending stiffness that is dependent on its geometry and mechanical properties. To achieve such goal, various kinds of composite system such as carbon fibres or aluminum were mounted on light core foam to build a noise reflection panel. A design of composite panels which can provide a reduction in panel weight as well as enhance the bending stiffness, is introduced in this paper. Predictions of the new model are to be compared with the normal foam plate in the aspects of noise reflection capability and performance of noise abatement apart from the material properties.     

Numerical and experimental fatigue crack growth analysis in mode-I for repaired aluminum panels using composite material

Crack-front shape is an important parameter influencing the stress intensity factor and crack propagation rate in asymmetric repaired panels. In this study, the numerical and experimental fatigue crack growth behaviour of centrally cracked aluminum panels in mode-I condition repaired with single-side composite patches are investigated. It is shown that the crack growths non-uniformly from its initial location through the thickness of a single-side repaired panel. There is a good agreement between the propagated crack-front shapes obtained from finite element analysis with those obtained from the experiments for various repaired panels with different patch thicknesses. Furthermore, effects of plate and patch thickness on the crack growth life of the repaired panels are investigated. The experimental results show that the crack growth life of thin panels may increase up to 236% using a 16 layers patch. However, for thick panels, the life may extend about 21–35% using a 4 layers patch. Implementing of 8 and 16 layers patches has not a significant effect on the life extension of thick panels with respect to the 4 layers patch life.     

一种用于阻尼夹层板传声损失（TL）计算的等效参数法

本文给出一种用于阻尼夹层板传声损失（ＴＬ）计算的简化方法──等效参数法，将该方法应用于对称及非对称阻尼夹层板的ＴＬ计算，并与按照复杂的Ｃｈｏｎａｎ＆Ｋｕｇｏ关于复合板的波传递理论经数值计算得出的ＴＬ值进行了比较．结果表明：对于在噪声控制工程中人们感兴趣的频率范围，这种简化方法能够给出较为满意的结果．     

复合材料帽型加筋板轴压试验及承载能力预测

随着复合材料的广泛使用,复合材料帽型加筋板在飞机结构上的使用也越来越多。为研究复合材料帽型加筋板承受轴向压缩的能力,首先对不同蒙皮半径、蒙皮厚度及长桁间距的复合材料帽型加筋板进行了轴压试验,得到了局部屈曲载荷、破坏载荷与加筋板曲率系数、长桁间距的关系,然后,通过引入曲率修正系数,修正了现有加筋板屈曲载荷的工程估算公式;最后,利用分段处理法结合有效宽度概念改进了加筋板轴压极限承载的工程算法。结果表明:帽型复合材料加筋板局部屈曲载荷及最终破坏载荷与曲率系数正相关;改进的方法能对复合材料加筋板的极限承载进行准确预测。所得结果表明该方法为复合材料加筋板结构设计及载荷估算提供了一种新方法,具有一定的工程应用价值。      

碳纤维铝蜂窝夹芯复合结构隔声性能研究

铝蜂窝夹芯复合结构在航空工业、高速列车及汽车车体中得到越来越多的应用,其隔声性能对车内及机舱噪声有重要影响。建立了碳纤维铝蜂窝夹芯复合结构有限单元模型,用有限单元法计算了结构在声载荷激励下的响应,并计算分析了复合结构的隔声性能,分析了碳纤维复合面板厚度、面板层数、铺设角度、铝蜂窝芯层的厚度、铝蜂窝壁厚对隔声性能的影响。研究结果表明,面板采用碳纤维复合结构时,在小于1 000 Hz的低频段,相同面板厚度的铝蜂窝复合结构隔声性能比全铝合金材料的铝蜂窝夹芯复合结构有所降低,而且在高频段会出现隔声量更低的隔声低谷;相较于铝合金面板,复合结构的面板采用碳纤维复合材料时,能够实现整体结构轻量化也提高复合结构的隔声性能;各层之间按相对90°铺设时复合结构隔声性能最好;随着面板厚度的增加复合结构隔声性能增加,面板层总厚度不变的情况下,单层面板或者过多的层数都会使复合结构隔声性能降低。     

Fatigue Debonding Analysis of Repaired Aluminium Panels by Composite Patch using Interface Elements

Repaired panels with composite patches subjected to fatigue loading may fail due to the progressive debonding between the composite patch and aluminium panel. The objective of this paper is to study the initiation and propagation of a possible fatigue debonding in the adhesive layer while the crack also growths in the panel for single-side repaired aluminium panels. For this purpose three dimensional finite elements method with a thin layer solid like interface element is employed. Fracture mechanics approach is used for the analysis of crack growth in aluminium panel and the interface elements with fatigue constitutive law for mixed mode debonding growth in the adhesive layer. A user element routine and a damage model material routine were developed to include the interface element and to simulate the initiation and propagation of damage in adhesive layer under cyclic loading. It is shown that, the debonding propagation and crack growth rate of the repaired panels depend on the composite patch material and interface bonding properties significantly. It is also shown that using of patch material with higher elastic module leads to the faster damage or debonding growth in the adhesive layer during the fatigue loading.     

Experimental fatigue crack growth and crack-front shape analysis of asymmetric repaired aluminium panels with glass/epoxy composite patches

In this study, we investigate the experimental fatigue crack-growth behaviour of centrally cracked aluminium panels in mode-I condition which have been repaired with single-side composite patches. It shows that the crack growths non-uniformly from its initial location through the thickness of the single-side repaired panels. The propagated crack-front shapes are preformed for various repaired panels with different patch thicknesses. It is shown that there are considerable differences between the crack-front shapes obtained for thin repaired panels with various patch thicknesses. However, the crack-front shapes of thick repaired panels are not significantly changed with various patch thicknesses. Furthermore, effects of patch thickness on the crack growth life of the repaired panels are investigated for two typical thin and thick panel thicknesses. It shows that the crack growth life of thin panels may increase up to 236% using a 16 layers patch. However, for thick panels, the life may extended about 21–35% using a 4 layers patch, and implementing 8 and 16 layers patches has not a significant effect on the life extension with respect to the 4 layers patch life.     

The use of a controlled multiple quasi-static indentation test to characterise through-thickness penetration of composite panels

During the quasi-static indentation of thin composite panels, well-defined flaps (sometimes called “petals”) can develop on the exit face as a consequence of through-thickness penetration of the panel; such flaps can also be seen in impact tests. The flaps develop as four triangles, with the apex of each triangle at the point of impact. In this work, thin panels of CFRP with a 0/90 configuration have been subjected to quasi-static indentation tests and the development of the flaps has been monitored. The results show that the dependence of the flap compliance is proportional to the square of the flap length, which is in agreement with theoretical predictions. The determination of the compliance/crack-length relationship enables a toughness value for fracture of the composite panel to be derived that is directly relevant to through-thickness penetration of the panel.     

止裂层对陶瓷复合防弹插板冲击损伤行为研究

目的 研究冲击载荷下迎弹面覆盖止裂层的复合防弹插板陶瓷面板碎裂机理和抗侵彻性能。方法 对所设计的复合防弹插板进行空气炮打靶试验,构建冲击仿真有限元计算模型。结合试验和数值模拟,研究覆盖环氧树脂、凯夫拉平纹织物止裂层及无止裂层复合防弹插板的抗侵彻性能,分析不同冲击速度下复合防弹插板陶瓷损伤失效过程。采用内聚力单元对止裂层和陶瓷之间的黏结区域进行建模,分析黏结程度对陶瓷损伤和失效的影响。结果 止裂层表面约束的陶瓷在冲击过程中产生的径向裂纹随着撞击点附近的环向拉应力波的传播而延伸。止裂层黏结作用增强时,陶瓷的冲击缺口面积增大,但质量损失基本不变;迎弹面止裂层未对侵彻过程中子弹动能和复合防弹插板背凸情况产生显著影响。结论 止裂层在一定程度上能减少陶瓷质量损失,但也会造成更多的损伤,这种现象在高速情况下较为明显,且凯夫拉平纹织物止裂层所造成的损伤更多。相关研究工作可为陶瓷复合防弹板的设计提供参考。     

Response of flexible sandwich-type panels to blast loading

This paper reports on experimental and numerical investigations into the response of flexible sandwich-type panels when subjected to blast loading. The response of sandwich-type panels with steel plates and polystyrene cores are compared to panels with steel face plates and aluminium honeycomb cores. Panels are loaded by detonating plastic explosive discs in close proximity to the front face of the panel. The numerical model is used to explain the stress attenuation and enhancement of the panels with different cores when subjected to blast induced dynamic loading. The permanent deflection of the back plate is determined by the velocity attenuation properties (and hence the transmitted stress pulse) of the core. Core efficiency in terms of energy absorption is an important factor for thicker cores. For panels of comparable mass, those with aluminium honeycomb cores perform “better” than those with polystyrene cores.     

Precise bending stress analysis of corrugated-core,honeycomb-core and X-core sandwich panels

A semi-analytical method for bending analysis of corrugated-core, honeycomb-core and X-core sandwich panels is presented. The real displacement of sandwich panels is divided into the global displacement field and local displacement field. The discrete geometric nature of the core is taken into account by treating the core sheets as beams and the sandwich panel as composite structure of plates and beams with proper displacement compatibility. In the global displacement field, the governing equations of these sandwich panels are derived using energy variation principle and solved by employing Fourier series and the Galerkin approach. In the local displacement field, the face sheets under external loads are taken as a multi-span thin plate and the local bending response are then computed. Then the real bending responses are obtained by superposing these bending responses calculated in the two displacement fields and the structural stress fluctuation can be captured. Results from the proposed method agree well with available results in the literature and those from detailed finite element analysis. Furthermore, the mechanical properties of the three kinds of sandwich panels have been compared.     

Effect of physical and geometrical parameters on transverse low-velocity impact response of sandwich panels with a transversely flexible core

The effects of important physical and geometrical parameters on transverse low-velocity impact response of composite sandwich panels have been studied in this paper. Impacts are assumed to occur normally over the top and/or the bottom face sheets, at arbitrary locations and with different impactor masses and initial velocities. For deriving closed-form solutions for the contact force, displacements of the impactor and the panel in the transverse direction, the sandwich panel has been modeled as a discrete three-degrees-of-freedom dynamic system with equivalent masses and springs (SM). The dynamic response of the panel is based on the improved higher-order sandwich plate theory (IHSAPT) and both thick and thin panels have been analyzed. The effects of transverse flexibility of the core, and boundary conditions are considered. Also, the area of the contact patch between the impactor and the panel can be varied as it changes with contact duration. The numerical results of the analysis have been compared either with the available experimental results or with some theoretical results. It is established that the dynamic behavior of the sandwich panel depends on various parameters, such as the aspect ratio and the length-to-thickness ratio of the panel, core thickness, boundary conditions of the panel and impactor parameters like its potential energy, velocity and the location of contact point, etc.     

The influence of correlating material parameters of gradient foam core on free vibration of sandwich panel

For the sandwich panel with mass density gradient (DG) foam core, the Young's modulus of the core varies with the mass density along the thickness direction. To characterize the correlative effect of Young's modulus and mass density of the DG closed-cell foam material, a simplified formula is presented. Subsequently, based on a high-order sandwich plate theory for sandwich panel with homogeneous core, a new gradient sandwich model is developed by introducing a gradient expression of material properties. Finite element (FE) simulation is carried out in order to verify this model. The results show that the proposed model can predict well the free vibration of composite sandwich panel with the gradient core. Finally, the correlating effects of material parameters of the DG foam core on the natural frequencies of sandwich panel are investigated. It is found that the natural frequencies of sandwich panels decrease as the gradient changes of the DG foam cores increase under the condition of that the core masses keep constant.     

Static and fatigue bending behavior of pultruded GFRP sandwich panels with through-thickness fiber insertions

This paper presents the findings of a research program that was undertaken to evaluate the static and fatigue characteristics of an innovative 3-D glass fiber reinforced polymer (GFRP) sandwich panel proposed for civil infrastructure and transportation applications. The research consists of analytical modeling verified by experimental results. A rational analytical model is presented and used to evaluate the effective elastic modulus, shear modulus and degree of composite interaction of the panels to resist one-way bending. The experimental program was conducted in two phases to study the static and fatigue behavior of the panels. In the first phase a total of 730 sandwich beams were tested to evaluate the effect of different parameters on the fundamental behavior of the panel. The parameters considered include the pattern and density of through-thickness fiber insertions, the overall thickness of the panels, and the number of FRP plies in the face skins. The study indicates that the shear behavior and degree of composite interaction of the panels is sensitive to the configuration of the panel core. The second phase of the experimental program included testing of 24 additional sandwich panels to evaluate the fatigue behavior. The results of the experimental program indicate that the panels with stiffer cores generally exhibited a higher degree of degradation than panels with more flexible cores. The findings of this study indicate that the proposed panels represent a versatile construction system which can be configured to achieve the specific design demands for civil engineering infrastructure applications.     

An analytical model for composite sandwich panels with honeycomb core subjected to high-velocity impact

In this paper, an analytical model for perforation of composite sandwich panels with honeycomb core subjected to high-velocity impact has been developed. The sandwich panel consists of a aluminium honeycomb core sandwiched between two thin composite skins. The solution involves a three-stage, perforation process including perforation of the front composite skin, honeycomb core, and bottom composite skin. The strain and kinetic energy of the front and back-up composite skins and the absorbed energy of honeycomb core has been estimated. In addition, based on the energy balance and equation of motion the absorbed energy of sandwich panel, residual velocity of projectile, perforation time and projectile velocity have been obtained and compared with the available experimental tests and numerical model. Furthermore, effects of composite skins and aluminium honeycomb core on perforation resistance and ballistic performance of sandwich panels has been investigated.     

Fundamental frequency and design of the CFCF composite sandwich plate

The design efficiency of sandwich panels is often associated with the value of fundamental frequency. This paper investigates the free vibrations of rectangular sandwich plates having two adjacent edges fully clamped and the remaining two edges free (CFCF). The vibration analysis is performed by applying Hamilton’s principle in conjunction with the first-order shear deformation theory. The analytical solution determining the fundamental frequency of the plate is obtained using the generalised Galerkin method and verified by comparison with the results of finite element modal analysis. The approach developed in the paper and equations obtained are applied to the design of sandwich plates having composite facings and orthotropic core. Design charts representing the effects of the thickness of the facings and core on the mass of composite sandwich panel for a given value of the fundamental frequency are obtained.     

Development of a satellite structure with the sandwich T-joint

In this study, a monocoque satellite structure composed of many composite sandwich panels, which consist of two carbon fiber/epoxy composite faces and an aluminum honeycomb core, was designed to reduce structural mass and to improve static and dynamic structural rigidity. To join composite sandwich panels with T-shape joints, a new I-shape side insert, which was fixed inside the composite sandwich panel edge with film adhesive, was suggested. The composite sandwich panels were assembled with bolts using the through-the-thickness insert and the I-shape side insert. The flatwise tensile and compressive tests of the composite sandwich panels were performed with respect to the bonding pressure between the composite face and the aluminum honeycomb core to achieve an optimal bonding pressure. To investigate the joint characteristics of the composite faces and the I-shape side insert, cleavage peel tests were performed with respect to the bonding thickness. Also, a finite element model of the composite sandwich T-joint with the I-shape side insert was developed from experimental results of the impulse response tests and composite sandwich T-joint static tests. From the finite element analysis, the structural reliability of the monocoque composite sandwich satellite structure was verified.     

明胶鸟弹撞击复合材料蜂窝夹芯板试验

开展明胶鸟弹撞击复合材料蜂窝夹芯板试验,研究夹芯结构在软体高速冲击下的损伤形式,分析相关因素对结构动态响应结果的影响。通过CT扫描对复合材料蜂窝夹芯板内部进行检测可知,面板出现分层、基体开裂、纤维断裂、凹陷、向胞内屈曲等损伤形式,蜂窝芯出现芯材压溃、与面板脱粘的损伤形式;分析复合材料蜂窝夹芯板后面板的动态变形过程及撞击中心处位移-时间数据可知,复合材料蜂窝夹芯板在撞击过程中出现由全局弯曲变形主导和局部变形主导的两种变形模式;通过对比不同工况下的复合材料蜂窝夹芯板损伤程度可知,复合材料蜂窝夹芯板损伤程度随鸟弹撞击速度的增加而增大;蜂窝芯高度为10 mm的复合材料蜂窝夹芯板较蜂窝芯高度为5 mm的复合材料蜂窝夹芯板的损伤程度大;初始动能较大的球形鸟弹较圆柱形鸟弹对复合材料蜂窝夹芯板造成的冲击损伤程度更大。      

Enhancing the resistance of composite sandwich panels to localized forces for civil infrastructure and transportation applications

This paper presents the details of an experimental and numerical study that was conducted to evaluate different methods of increasing the punching resistance of glass fiber reinforced polymer (GFRP) composite sandwich panels with balsa wood cores. A total of four large-scale panels were subjected to concentrated loads in a two-way bending configuration. Different techniques of locally stiffening the panels were investigated including bonding a steel coupling plate to the loaded surface of the panels and embedding steel tubes within the panel core. The experimental program was supplemented by a finite element study to evaluate the location, magnitude, and extent of stress concentrations in the panels. The experimental program demonstrated that the failure modes of the stiffened panels shifted from local punching to delamination of the loaded GFRP skin which initiated at the discontinuities of the panel stiffness. The finite element analysis indicated that the delamination failure was due to stress concentrations which formed at these critical locations. The local stiffening of the panel approximately tripled the concentrated load carrying capacity of the panels. The research findings suggest that, through careful design and detailing, composite sandwich panels can be used to resist large-magnitude concentrated loads such as those found in civil infrastructure and heavy freight transportation applications.     

Thermomechanical postbuckling of multilayered composite panels with cutouts

The results of a study of the detailed thermomechanical postbuckling response characteristics of flat unstiffened composite panels with central circular cutouts are presented. The panels are subjected to combined temperature changes and applied edge loading (or edge displacements). The analysis is based on a first-order shear deformation plate theory. A mixed formulation is used with the fundamental unknowns consisting of the generalized displacements and the stress resultants of the plate. The postbuckling displacements, transverse shear stresses, transverse shear strain energy density, and their sensitivity coefficients are evaluated. The sensitivity coefficients measure the sensitivity of the post-buckling response to variations in the different lamination and material parameters of the panel. Numerical results are presented showing the effects of the variations in the hole diameter, laminate stacking sequence, fiber orientation, and aspect ratio of the panel on the thermomechanical postbuckling response and its sensitivity to changes in panel parameters.