复合材料层板冲击后剩余压缩性能声发射分析

利用声发射技术对复合材料层合板的低速冲击和压缩破坏进行了分析.测试过程中用声发射技术进行实时监测,结合载荷—位移曲线,分析了声发射能量,幅值和波形经过快速傅里叶变换后的峰值频率,并对典型信号的波形进行了频谱分析.结果表明:AE参数能很好的描述复合材料层合板低速冲击及其剩余压缩行为.     

冲击载荷下脆性岩板损伤断裂演化的实验模拟研究

在矿山运输系统中,井壁围岩冲击损伤破坏对经济和安全效益的影响是至关重要的,因为动态冲击载荷对井壁围岩和支护结构会产生严重的削弱破坏作用,室内研究表明,岩石样品如岩板在动态载荷的冲击作用下会失效。为研究在低速冲击载荷作用下,脆性岩石损伤断裂的演化过程,利用分离式霍普金森压杆(SHPB)装置中压缩气体发射球体子弹对脆性岩板进行变角度冲击损伤实验,岩板受到冲击后,边缘出现凹坑,表面裂纹从撞击凹坑直达岩板边缘,实验中样品的表面裂纹能有效代表试样内部的开裂状况,能有效反映冲击能量的耗散、破裂区面积与裂纹表面积随入射能量呈非线性增长趋势,同时与入射角度相关,但当破裂区面积急剧下降时,裂纹表面积反而急剧上升,表明裂纹的发生发展有明显的孕育期,在入射能量达到临界值前,主要表现为裂纹孕育增长,在达到临界值后,发生宏观断裂破坏,裂纹面积呈负增长,破裂区面积增大。实验结果分析表明在实际工程中,围岩和支护结构的抗冲击的最优化设计角度范围在15°～30°。     

Experiments and simulation of low-velocity impact characteristics on carbon fiber composite lattice core sandwich structures

Since composite sandwich structures are susceptible to low-velocity impact damage,a thorough characterization of the loading and damage process during impact is important.In the present paper,the low-velocity impact response of carbon fiber composites lattice structures is investigated by experimental and numerical methods.Impact tests on composite plates are performed using an instrumented drop-weight machine(Instron 9250HV)and a new damage mode is observed.A three-dimensional finite element model is built by ABAQUS/Explicit and user subroutine(VUMAT)to predict the peak loading and simulate the complicated damage problem.The numerical predictions are in good agreement with the experimental results.     

复合材料迭层板铺层可靠性优化设计

飞机复合材料结构的壁板主要承受轴力和剪力。这两种外载之间存在一定的比例关系,因而是一个广义外载。文中以某一小展弦比复合材料多墙式翼面结构为例,据轴力和剪力的不同比值,对根部蒙皮的迭层板进行铺层可靠性优化设计。采用加速收敛梯度法得到广义外载作用下满足结构系统可靠度指标 R_s~*的主要约束条件和次要约束条件(最小层数比约束条件、±45°层均衡对称约束条件等)迭层板总重最小时的最优分层比例。通过算例证明本文提出的复合材料迭层板可靠性基础上的铺层优化设计方法是十分有效的。     

ZrB2基层状复合材料力学性能与应力影响分析

通过层压复合技术制备出Mo/ZrB2层状复合材料,该复合材料的抗弯强度达到471 MPa,同时具有高的断裂韧性7.64 MPa·m1/2.研究发现材料内部的残余应力引起裂纹扩展阻力增大,裂纹发生偏转,材料因此得到强韧化.采用非均匀应变模型分析层状复合材料的内部残余应力,结果表明:基体层受拉应力,最大为64 MPa,界面层受压应力,最大为320 MPa,同时在层间存在剪切应力,最大为1.149MPa.基体层和界面层的厚度比对材料内部应力分布影响较大.     

复合材料层合板低速冲击及其剩余压缩强度

为了研究冲击能量对层合结构冲击性能及吸能特性的影响规律,本文主要采用不同冲击能量作用下的复合材料层合板低速冲击性能及其剩余压缩强度的研究方法.通过低速冲击实验,研究了冲击能量对复合材料层合板的损伤影响.通过准静态压缩试验,较好地分析冲击能量对试件的压缩剩余强度的影响.     

Fatigue life prediction and experiment research for composite laminates with circular hole

Based on the fatigue prediction model of exponential function and Whitney-Nuismer(WN) criterion of static strength for the composite material laminate with a circular hole, the stress correct factor (β) was put forward and a new fatigue prediction model for composite material laminate was set up. T300/KH304, which is recently studied and is a high capability composite material, was used as the raw material. In order to gain the factor β, the fatigue experiments of the laminates with holes in different diameters and the same ratio of width to diameter were conducted. The fatigue analysis and tests of the laminates with a hole 5 mm in diameter are carried out at different stress levels, and the results meet the engineering requirement. The simple, prompt and practical method is provided for the prediction of S-N curve of composite laminate with a circular hole.     

层间加胶膜层压板的层间应力与孔边应力分析

采用建立在边界层理论基础上的复合材料层压板孔边层间应力分析方法，计算了层间加胶膜层压板的孔边应力，还采用三维有限元方法分析层间加胶膜层压板的层间应力边缘效应，结果表明，层间胶膜的加入以使 层压板边缘和孔边的层间应力明显下降。     

Analysis of transient temperature field of the laminate composite membrane in space environment

The on-orbit transient temperature of reflector laminate film was analyzed by using finite element method (FEM). Numerical simulation was used by FEM software ANSYS. Results reveal that the temperature levels of the laminate composite membrane alternate greatly in the orbital period, which is about ±80℃. This range exceeds the material’s operating temperature level. So it is necessary to put effective thermal control into effect to the laminate composite membrane. There is temperature gradient in the thickness direction of the laminate composite membrane; there is a light change in Kevlar/Epoxy layer. The temperature of the laminate composite membrane is obviously lower than the seam’s temperature. Results provide reference to the thermal control of the inflatable reflector with high precision requirement.     

复合材料层压结构系统的可靠性分析方法

本文针对复合材料层压结构的特点提出层压结构系统可靠性分析的变刚度全量载荷法。根据元件利用率的大小找出临界元件,然后采用分类组合临界元件的方法枚举结构系统的破坏模式,从而得到结构系统的破坏树。由各单一破坏模式的破坏概率和计及两个破坏模式间相关系数的二阶共概率求得结构系统的可靠度。利用破坏模式删除和合并的原则使结构系统破坏概率的计算大为简化。通过算例表明本文提出的确认复合材料结构系统主要破坏模式的方法是有效的,尤其对大型复杂结构更显出它的优点。     

层合板在低速冲击载荷作用下本构方程的研究

纤维增强复合材料层合板的冲击响应是一个兼有几何非线性、材料非线性、接触非线性的复杂过程。本文采用连续介质力学,对层合板的运动、变形进行描述,给出了冲击系统的有限元列式。在此基础上,通过建立壳局部坐标系与参考坐标系之间的转换矩阵,导出有限应变低阶壳单元在显式分析中的应力更新方法,为进一步研究复合材料的动态力学行为提供一个新思路。     

液压膨胀夹具夹紧性能影响因素分析及优化设计

为优化液压膨胀夹具夹持性能,利用有限元软件分析了某液压膨胀夹具系统的不同结构及配合参数对工件夹紧变形、夹紧力矩、锁紧刚度的影响规律,并采用多目标优化方法对参数进行了优化分析。结果表明:通过调整液压膨胀套夹具的结构和配合参数,能使液压膨胀夹具的夹持性能显著提高,工件中部的夹紧变形量由 12 μm 减小到 3.2 μm,两端的夹紧变形量由 28 μm 减小到 4.8 μm,工件的最大应力由 435.9 MPa 减小到85.7 MPa。     

Optimization of geometric parameters of reinforced sheets based on a cell-based smoothed discrete shear gap (CS-FEM-DSG3) method

Optimization of design features of reinforced sheet is investigated. Initially, equations governing composite structures are extracted based on Kirchhoff sheet model under bending using Hamilton's principal. Then, design parameters for the composite structure are extracted with simple supportive boundary conditions from proposed solution. Next, optimization is achieved by determining dimensions of a reinforced sheet specimen. Weight optimization of reinforced sheet structure has been obtained based on variations in thickness and number of longitudinal and transverse reinforcements. Buckling static characteristic is utilized in optimization process. To solve the extracted equations, semi-analytical method of CS-DSG3 has been applied. Results are presented in graphs that show variation of design parameters by changing the geometric parameters. ABAQUS software has been used for design verification. The results show that an increase in thickness of 3 mm skip value tends to be zero. Also, there is a change in the amount of deflection for sheets with a minimum thickness of 3 mm by increasing the number of longitudinal and transverse reinforcement. There is a good agreement between the numerical method of finite elements and the method X-FEM-DSG3.     

Experimental Study on Penetration and Perforation of Laminated Kevlar

The penetration behavior and perforation characteristics of Kevlar/Epoxy laminates with various thickness in quasi-static and ballistic perforation penetrated by steel projectiles with different noses are investigated. Quasi-static tests are conducted on MTS810 testing system. The results indicate that global deformation is the major mechanism of energy absorption and woven laminates exhibit larger energy dissipation than that of angleplied laminates. Therefore, the woven laminates have better quasi-static penetration resistance. Ballistic tests with velocity of 200 - 700 m/s are executed by using a powder gun with 7.62 mm barrel. Comparing ballistic experimental results with those under quasi-static condition, both the perforation performance and the failure modes are related closely to the speed of penetrator. Quite different from quasi-static tests, ballistic tests indicate that thick angle-plied laminate targets are even better than woven laminates in resisting ballistic impact. It is observed that the damage zone of the laminate is localized highly with the increasing of the impact velocity and correspondingly, the failure modes are more manifold. The shape of projectile noses affects the impact resistance of laminated Kevlar significantly in the range of velocity around the ballistic limit.     

超高韧性水泥基复合材料的波传播试验研究

为了研究超高韧性水泥基复合材料（UHTCC）中应力波的传播特性,采用Hopkinson杆加载UHTCC试件,测得UHTCC在0.2、0.3、0.4、0.5 MPa冲击气压下的应力波信号. 通过对比入射杆波形,验证相同加载条件下加载波形的一致性. 分别采用两点法和峰值法计算每种冲击气压下UHTCC中应力波的波速,结果显示,两点法适用性较广,计算结果较稳定,利用峰值法测波速则需要入射杆和试件波阻抗相近. 计算结果显示,UHTCC中应力波波速、衰减系数随冲击气压均无明显变化,平均波速为3.060 km/s,平均衰减系数为2.777 m^?1. 可以利用朱-王-唐本构模型参数表达材料中应力波的波速和衰减,也可以利用实测的波速和衰减系数将UHTCC的朱-王-唐冲击本构模型表示为只含单个准静态参数的方程,从而提供通过试验直接确定UHTCC动态本构的方法.     

密肋复合墙体多目标优化设计方法研究

密肋复合墙体是密肋壁板结构体系的主要受力构件,墙体的优化设计方法研究是结构体系设计理论的重要组成部分.本文研究了密肋复合墙体多目标优化设计方法;提出了综合考虑墙体的安全性(墙体斜截面抗剪承载力)与经济性(墙体造价)的多目标优化设计数学模型,并利用序列二次规划法(SQP)在Matlab软件系统上进行优化计算,同时给出了优化设计计算算例.理论分析与计算结果表明:将多目标优化设计方法用于密肋复合墙体的优化设计中,可使各个分目标都较为满意,兼顾了墙体安全性与经济性两方面的要求;方法合理、可行,具有一定的工程实用意义.     

Low velocity impact response and energy absorption behavior on glass fibre reinforced epoxy composites

A study was undertaken to determine the effects of several key geometry influencing factors on the impact response and energy absorption behavior of the glass fibre reinforced epoxy composites at low and intermediate energies.The energy-balance model was employed for characterising the energy absorption behavior and it depends strongly on the plate diameter and thickness.In addition,the damage vs.energy and force maps is effective in monitoring damage growth within the composite panel.The response of the composite laminate configurations characterized by different stacking sequences subjected to low velocity impacts with different impact energies have also been studied to estimate the damage initiation of composites.     

斯特林机帽式密封性能分析及回归参数优化设计

为改善斯特林机活塞杆帽式密封性能,首先采用数值仿真分析了5 MPa工质压力下其静、动态力学特性,从而获取了O型圈内径尺寸LN、C型环径向壁厚T和装配过盈量S三个关键结构参数对密封性能的影响规律,在此基础上,再利用回归设计法以配伍面最大接触压力平稳且密封可靠为优化目标,对密封结构的上述三个关键参数进行优化设计以确定其最佳匹配方案,最后通过密封试验台验证了本文优化设计方法的准确性和普适性。结果表明：活塞杆与C型环密封面中间区域上最大接触压力随LN和S的增大而增大,但随T的增大而减小;通过估计回归系数和方差分析（ANOVA）发现,LN对密封性能影响最为显著、S次之、T影响最小;LN和T、LN和S交互项对响应显著,而T和S交互项对响应不显著;当LN为13.745 mm、T为0.40 mm和S为0.020 mm时,优化密封件对应的正行程最大接触压力为9.01 MPa、回程为9.75 MPa,较工程在用密封件（LN=13.78 mm、T=0.5 mm、S=0 mm）最大接触压力分别降低了14.7%和25.5%;实验进一步验证了优化密封件的密封性能和使用寿命均优于工程在用密封件,并且在不同工质压力下优化密封件的接触压力均匀性更好,减摩延寿效果明显,充分证明本文性能分析与优化设计方法准确有效。     

铺层次序对于碳／玻璃混杂复合材料破坏过程的影响

本文使用有限元方法模拟了三种碳/玻璃编织状混杂复合材料层合板的破坏过程，三种层合板有相同的碳纤维和玻璃纤维的体积比和重量比。层数比相同铺层次序不同，假设碳纤维层首先破坏，计算了破坏处周围的最大拉伸应力、拉伸应变和层间剪切应力，从应力、应变分析和能量分析的观点探讨了铺层次序对于混杂复合材料破坏过程的影响，结果表明：铺层次序影响着脱层破坏的出现，三种分析方法可以得到一致的结论，并与试样断口分析的结果相吻合。     

Prestress design of stainless steel fibers/zirconia composite by tape casting

Prestressed SUS316 fibers/ZrO₂ composite was fabricated using tape casting. Causes of cracks were analyzed by classical thermo-elastic theory and finite element method in preparation process. An optimization design was carried out on SUS316 fibers’ arrangement modes by reducing residual thermal stress. Interface topography and element distribution of composite were observed, and bending strengths were tested. Results show that cracks are generated along the direction vertical to SUS316 fibers by axial thermal stress due to different thermal expansion coefficients between SUS316 fibers and zirconia, and the average cracking space is 2 mm. No macroscopic defect is found in composite with SUS316 fibers of sine distribution, and it has better interfacial binding force since interdiffusion between SUS316 and zirconia. Bending strengths of composite with 0°/0° lamination are anisotropic and that are 385.74 MPa and 500.7 MPa respectively, but that with 0°/90° lamination is isotropic and it is 433.92 MPa. Bending strength of composite is increased obviously compared with that of zirconia because the prestress of surface is compressive stress.