碳纤维复合材料金字塔点阵结构制备工艺及力学性能研究

本文针对碳纤维复合材料点阵结构,从结构设计、制备工艺、平压性能、剪切性能等方面对其进行试验表征及理论模型研究.设计四种成型碳纤维复合材料金字塔点阵结构的思想,并采用一种新的制备工艺即预浸料二次成型工艺制备试样,试验结果表明,该工艺能最大程度发挥纤维增强潜力.通过实验揭示在平压载荷下杆件屈曲、杆件断裂、杆件分层脱胶失效机理,在剪切载荷下杆件屈曲、杆件分层、杆件脱胶失效机理,基于结构力学基础原理,建立相应理论模型,经过修正之后的理论模型均能较好预报典型载荷下力学性能.本文研究发现碳纤维复合材料金字塔点阵结构具有密度低、比强度大、比刚度高等优点,且芯子中具有大量空间,可以制备轻质多功能结构.     

缝合复合材料泡沫夹层结构层间剪切性能研究

复合材料泡沫夹层结构在飞机结构上的应用日益广泛,面板与芯子的全厚度缝合是提高泡沫夹层结构层间剪切性能的重要途径。本文通过层间剪切试验,研究不同缝合密度下单向带面板和织物面板复合材料泡沫夹层结构的层间剪切强度及其变化规律。研究结果表明:面板为单向带的缝合泡沫夹层结构最大剪切载荷和层间剪切强度均优于未缝合泡沫夹层结构的,且层间剪切性能随着缝合密度的增加而增加;面板为织物的缝合泡沫夹层结构缝合密度超过4000针/m2左右后,最大剪切载荷和层间剪切强度均优于未缝合泡沫夹层结构,且层间剪切性能随着缝合密度的增加而增加。     

复合材料四面体点阵夹芯梁的自由振动分析

点阵夹芯结构是一种由上下面板和中间点阵芯子组成的新型轻质多功能结构.由于该结构具有独特的结构形式,其力学特性分析比较复杂.论文将离散的点阵芯子等效为连续均匀材料,研究了复合材料四面体点阵夹芯梁的自由振动特性.考虑面板的弯曲变形和芯子的剪切变形,根据Hamilton变分原理,推导出复合材料点阵夹芯梁的自由振动控制方程.以...     

X状Z向碳pin增强泡沫夹层结构剪切刚度预报

综合考虑了面板对横向增强Z-pin的不同约束情况,结合空间网架结构和等效夹杂方法,提出了X状Z-pins增强泡沫夹层结构剪切刚度的预报模型,经实际计算后与已有的实验值和有限元模拟值比较,证明该方法具有足够的工程精度.计算表明,X状Z-pins能大幅度地提高泡沫夹层结构的剪切刚度,并具有良好的可设计性,可以通过改变Z-pin材料,Z-pin的体积分数、角度、直径等参数改变其力学性能.其中,Z-pin体积分数越大、拉伸模量越高、直径越大,Z-pins增强泡沫夹层结构的剪切刚度越高.     

轻质金属点阵夹层板热屈曲临界温度分析

本文针对均匀温度场下四边简支和四边固支金属点阵夹层板的临界热屈曲温度进行了求解和参数影响分析。将点阵夹芯等效为均匀连续体,并且将夹层板的剪切刚度近似为点阵夹芯的抗剪切刚度,忽略夹芯的抗弯刚度且认为夹层板主要由面板来提供抗弯刚度。对于无法获得解析解的四边固支条件,通过对未知变量进行双傅里叶展开的方法求解了Ressiner夹层板模型的临界屈曲温度,理论分析结果与有限元计算结果吻合良好。进一步分析了不同边界条件、点阵胞元构型、点阵材料相对密度、面板厚度等对临界屈曲温度的影响规律。     

基于Layerwise离散层理论的复合材料夹层板屈曲分析

复合材料夹层结构由于面板和芯层力学特性差异较大,屈曲分析时要分层考虑各层的剪切变形。基于Reddy的Layerwise离散层理论,假设每一层变形服从一阶剪切变形理论,在统一的位移场描述下,推导建立了一种用于复合材料夹层结构屈曲分析的四节点四边形板单元,并采用混合插值方法对单元的剪切锁定进行了修正。分别对三种典型的夹层板结构进行线性屈曲有限元分析,并将计算结果与文献中已有结果进行了对比。结果表明：本文的分析方法能离散考虑各层的力学特性,将结构离散为多层时,计算结果与三维弹性理论或高阶板理论吻合;将结构等效为单层时,计算结果与基于一阶剪切变形理论的文献结构吻合,验证了单元的有效性。     

缝合复合材料泡沫夹层结构稳定性研究

随着复合材料结构在航空航天领域的应用日渐广泛,非主承力结构壁板趋向于采用高比刚度的泡沫夹层结构。采用缝合工艺虽能提高泡沫夹层结构的面外性能和层间性能,但对泡沫夹层结构其它性能的影响并不明晰。通过压缩稳定性试验对泡沫夹层结构的稳定性进行研究,夹层结构分别采用单向带面板和织物面板。研究对象包括未缝合泡沫夹层结构和不同缝合密度的缝合泡沫夹层结构。试验结果表明:缝合会降低泡沫夹层结构的稳定性,缝合密度增加时,泡沫夹层结构稳定性性能降低。     

泡沫夹层结构力学性能的非线性有限元分析

泡沫夹层结构因其较高的比刚度及比强度,在各领域得到广泛应用.但由于泡沫在受力过程中呈现较强的非线性,且相对其它常用材料强度较小,需对泡沫进行材料的非线性分析,才能更准确地判断泡沫夹层结构在应用中所体现的力学性能.本文根据泡沫材料呈现的相关性能,定义了该材料的非线性本构关系,并利用MSC.Marc二次开发用户子程序接口将该本构关系写入,而且引入了针对泡沫材料的三参数广义强度准则,建立了泡沫材料的非线性有限元计算模型.通过铝面板泡沫夹层结构的平拉、平压、剪切实例分析并结合其它分析方法与实验结果进行比较,论证了该泡沫材料非线性有限元模型的准确性,同时证实了广义强度准则在泡沫材料上的适用性,为泡沫夹层结构研究与应用提供了依据.     

双层夹芯复合材料结构横向冲击响应实验

采用玻璃纤维增强环氧树脂复合材料层合板作为内、外面板,以PVC泡沫作为芯材,构造了双层夹芯复合材料结构。采用落锤冲击实验,得到了冲击过程的撞击力历史;研究了在不同的冲击能量下,双层夹芯结构的冲击响应及内面板位置对双层夹芯结构冲击响应的影响。实验结果表明,内面板的引入及内面板的位置显著影响双层夹芯结构的撞击力历史,根据该撞击力历史可以优化设计出抗冲击性能优异的新型双层夹芯复合材料结构。     

基于实验模态分析的点阵夹层结构动态性能预测

引入均一化等效理论,对金字塔型结构芯体夹层材料的芯体弹性常数进行均一化等效处理,并将其用于研究该夹层材料结构的动态性能．同时采用三维（3D）离散有限元模型计算了结构的动态性能．为验证了理论预测的正确性,设计并制备了金字塔点阵悬臂梁,进行了实验模态分析,将实验结果与理论计算的各阶自振频率进行了比较．结果表明：该模型对低阶自振频率的计算结果与实验结果、3D离散有限元模型计算结果吻合得都比较好,一阶自振频率误差不到5％,其它误差在10％左右．     

环氧树脂/泡沫铝一体型复合夹层板压缩及弯曲试验研究

提出了一种环氧树脂/泡沫铝一体型复合夹层板,通过准静态试验以及与纯泡沫铝、传统蒙皮夹层板的对比研究了其破坏过程、破坏形貌、破坏机理及压缩和弯曲力学性能。分别通过压缩应力-应变曲线和弯曲荷载-挠度曲线分析了复合层厚度对压缩及弯曲力学性能的影响,并与传统夹层板的力学性能进行了比较。结果表明,随着夹层板中环氧树脂/泡沫铝复合层厚度增加,其压缩弹性模量和抗压强度增加,弯曲承载力提高。相比传统蒙皮夹层板,由于表层和芯层之间没有明显界面,大大提高了夹芯板的整体性,在受力过程中不会出现表层剥离等现象。     

Three-dimensional Composite Lattice Structures Fabricated by Electrical Discharge Machining

We present a novel method for fabricating carbon fiber composite sandwich panels with lattice core construction by means of electrical discharge machining (EDM). First, flat-top corrugated carbon fiber composite cores were fabricated by a hot press molding method. Then, two composite face sheets were bonded to each corrugated core to create precursor sandwich panels. These panels were transformed into sandwich panels with near-pyramidal truss cores by EDM plunge-cutting the corrugated core between the face sheets with a shaped cuprite electrode. The flat top corrugation permits adhesive to be applied consistently, and the selected dimensions leave a substantial bond area after cutting, resulting in a strong core-to-sheet bond. The crushing behavior of this novel construction was investigated in flatwise compression, and the results were compared to analytical expressions for strength and stiffness.     

Combined shear/compression structural testing of asymmetric sandwich structures

Asymmetric sandwich technology can be applied in the design of lightweight, non-pressurized aeronautical structures such as those of helicopters. A test rig of asymmetric sandwich structures subjected to compression/shear loads was designed, validated, and set up. It conforms to the standard certification procedure for composite aeronautical structures set out in the “test pyramid”, a multiscale approach. The static tests until failure showed asymmetric sandwich structures to be extremely resistant, which, in the case of the tested specimen shape, were characterized by the absence of buckling and failure compressive strains up to 10,000 μ strains. Specimens impacted with perforation damage were also tested, enabling the original phenomenon of crack propagation to be observed step-by-step. The results of the completed tests thus enable the concept to be validated, and justify the possibility of creating a much larger machine to overcome the drawbacks linked to the use of small specimens.     

Critical velocity of sandwich cylindrical shell under moving internal pressure

Critical velocity of an infinite long sandwich shell under moving internal pressure is studied using the sandwich shell theory and elastodynamics theory. Propagation of axisymmetric free harmonic waves in the sandwich shell is studied using the sandwich shell theory by considering compressibility and transverse shear deformation of the core, and transverse shear deformation of face sheets. Based on the elastodynamics theory, displacement components expanded by Legendre polynomials, and position-dependent elastic constants and densities are introduced into the equations of motion. Critical velocity is the minimum phase velocity on the desperation relation curve obtained by using the two methods. Numerical examples and the finite element （FE） simulations are presented. The results show that the two critical velocities agree well with each other, and two desperation relation curves agree well with each other when the wave number k is relatively small. However, two limit phase velocities approach to the shear wave velocities of the face sheet and the core respectively when k limits to infinite. The two methods are efficient in the investigation of wave propagation in a sandwich cylindrical shell when k is relatively small. The critical velocity predicted in the FE simulations agrees with theoretical prediction.     

基于Zig-Zag变形假定的复合材料夹层板的自由振动

针对复合材料夹层板的实际变形特征，基于Zig-Zag变形假定和Mindlin一阶剪切理论，建立了复合材料夹层板自由振动的有限元模型，在该模型中分别对上、下面板和芯体建立了三个独立坐标系，使三部分的转角独立，为具有厚夹芯和软夹芯的复合材料夹层板的动力分析提供了一种更为准确的有限元模型；在此基础上推导了相应的刚度阵和质量阵，并采用子空间迭代法求解。夹层板的固有频率。通过典型考题证明了本模型的有效性。文中最后还通过参数讨论，研究了具有不同长厚比的复合材料夹层板基频的变化规律。     

BENDING RESPONSES OF AN EXPONENTIALLY GRADED SIMPLY-SUPPORTED ELASTIC/VISCOELASTIC/ELASTIC SANDWICH PLATE

The bending response for exponentially graded composite (EGC) sandwich plates is investigated.The three-layer elastic/viscoelastic/elastic sandwich plate is studied by using the sinusoidal shear deformation plate theory as well as other familiar theories.Four types of sandwich plates are considered taking into account the symmetry of the plate and the thickness of each layer.The effective moduli and Illyushin’s approximation methods are used to solve the equations governing the bending of simply-supported EGC fiber-reinforced viscoelastic sandwich plates.Then numerical results for deflections and stresses are presented and the effects due to time parameter,aspect ratio,side-to-thickness ratio and constitutive parameter are investigated.     

NONLINEAR BUCKLING BEHAVIOR OF DAMAGED COMPOSITE SANDWICH PLATES CONSIDERING THE EFFECT OF TEMPERATURE-DEPENDENT THERMAL AND MECHANICAL PROPERTIES

On the basis of the first-order shear deformation plate theory and the zig-zag deformation assumption, an incremental finite element formulation for nonlinear buckling analysis of the composite sandwich plate is deduced and the temperature-dependent thermal and mechanical properties of composite is considered. A finite element method for thermal or thermo-mechanical coupling nonlinear buckling analysis of the composite sandwich plate with an interfacial crack damage between face and core is also developed. Numerical results and discussions concerning some typical examples show that the effects of the variation of the thermal and mechanical properties with temperature, external compressive loading, size of the damage zone and ply angle of the faces on the thermal buckling behavior are significant. Project supported by the National Natural Science Foundation of China (No. 59975013).     

Free vibration of functionally graded sandwich plates using four-variable refined plate theory

This paper uses the four-variable refined plate theory (RPT) for the free vibration analysis of functionally graded material (FGM) sandwich rectangular plates.Unlike other theories, there are only four unknown functions involved, as compared to five in other shear deformation theories. The theory presented is variationally consistent and strongly similar to the classical plate theory in many aspects. It does not require the shear correction factor, and gives rise to the transverse shear stress variation so that the transverse shear stresses vary parabolically across the thickness to satisfy free surface conditions for the shear stress. Two common types of FGM sandwich plates are considered, namely, the sandwich with the FGM facesheet and the homogeneous core and the sandwich with the homogeneous facesheet and the FGM core. The equation of motion for the FGM sandwich plates is obtained based on Hamilton's principle. The closed form solutions are obtained by using the Navier technique. The fundamental frequencies are found by solving the eigenvalue problems. The validity of the theory is shown by comparing the present results with those of the classical, the first-order, and the other higher-ordex theories. The proposed theory is accurate and simple in solving the free vibration behavior of the FGM sandwich plates.     

Stress and buckling analysis of a thick-walled micro sandwich panel with a flexible foam core and carbon nanotube reinforced composite(CNTRC) face sheets

In this paper, the stresses and buckling behaviors of a thick-walled micro sandwich panel with a flexible foam core and carbon nanotube reinforced composite(CNTRC) face sheets are considered based on the high-order shear deformation theory(HSDT) and the modified couple stress theory(MCST). The governing equations of equilibrium are obtained based on the total potential energy principle. The effects of various parameters such as the aspect ratio, elastic foundation, temperature changes, and volume fraction of the canbon nanotubes(CNTs) on the critical buckling loads, normal stress,shear stress, and deflection of the thick-walled micro cylindrical sandwich panel considering different distributions of CNTs are examined. The results are compared and validated with other studies, and showing an excellent compatibility. CNTs have become very useful and common candidates in sandwich structures, and they have been extensively used in many applications including nanotechnology, aerospace, and micro-structures. This paper also extends further applications of reinforced sandwich panels by providing the modified equations and formulae.     

Study on wave dispersion characteristics of piezoelectric sandwich nanoplates considering surface effects

In this study, the wave propagation properties of piezoelectric sandwich nanoplates deposited on an orthotropic viscoelastic foundation are analyzed by considering the surface effects (SEs). The nanoplates are composed of a composite layer reinforced by graphene and two piezoelectric surface layers. Utilizing the modified Halpin-Tsai model, the material parameters of composite layers are obtained. The displacement field is determined by the sinusoidal shear deformation theory (SSDT). The Euler-Lagrange equation is derived by employing Hamilton’s principle and the constitutive equations of piezoelectric layers considering the SEs. Subsequently, the nonlocal strain gradient theory (NSGT) is used to obtain the equations of motion. Next, the effects of scale parameters, graphene distribution, orthotropic viscoelastic foundation, and SEs on the propagation behavior are numerically examined. The results reveal that the wave frequency is a periodic function of the orthotropic angle. Furthermore, the wave frequency increases with the increase in the SEs.