泡沫夹层复合材料的低速冲击损伤及剩余强度的数值模拟

基于渐进累积损伤理论和数据传递分析方法,对泡沫夹层复合材料的低速冲击以及冲击后的压缩破坏过程提出了一种全程数值分析方法,即对泡沫夹层复合材料的冲击以及冲击后损伤的泡沫夹层复合材料在压缩载荷下损伤扩展的全过程进行数值模拟分析。结果表明:由于该方法避免了以往学者对冲击后夹层板损伤状态所做的人为假设,把冲击后的预测损伤直接传递用于剩余强度的研究,从而提高了最终破坏载荷和剩余强度的预测精度,数值模拟结果与已有试验结果吻合较好。     

铝蜂窝夹芯板低速动态冲击响应研究

为研究不同结构参数对质量相同、强度不同的两种铝蜂窝夹芯板低速动态冲击响应的影响，建立了铝蜂窝夹芯板受半球型落锤低速冲击的数值模型，并将有限元计算结果与试验结果进行对比，检验了模型的可靠性。在此基础上，对比研究了不同上下铝板厚度和不同蜂窝芯壁厚对两种铝蜂窝夹芯板在低速冲击下吸能效果的影响。结果表明：在质量相同的情况下，强度小、高度大的夹芯板在低速冲击下力-位移曲线更易出现双峰模式，增加蜂窝芯壁厚或是上下铝板厚度都会使第一次的峰值力增加，第二次峰值力降低；强度小、高度大的夹芯板蜂窝芯在低速冲击中吸能占比更多，强度大、高度小的则是上层铝板吸收的能量更多，前者的质量、体积比吸能更高；铝蜂窝夹芯板质量比吸能和体积比吸能与壁厚边长比、板厚芯高比均呈幂次关系。     

基于应变损伤模型的复合材料层合板低速冲击数值模拟

提出了一种基于应变的复合材料损伤模型,考虑了复合材料冲击过程中出现的面内纤维断裂与压缩,基体开裂与挤裂。在使用Abaqus软件进行数值模拟计算时,自编的用户子程序VUMAT和Cohe-sive模型分别实现了复合材料面板的损伤和层间分层。通过对层合板在不同能量下的低速冲击的有限元模拟发现,模拟得到的分层损伤形状和面积、冲头最大挠度、接触力和凹坑深度都与试验结果吻合较好。     

过载条件下铝蜂窝天线结构静动态响应研究

采用正交各向异性蜂窝夹层板的一种高精度等效分析方法,在MSC-PATRAN平台下建立某铝蜂窝夹层板天线结构有限元模型。重点分析了蜂窝夹层板尺寸对天线板极限承载能力的影响,并用大质量法分析其受冲击载荷的响应结果,得出了适合实际发射要求的结构设计参数,为天线结构优化设计提供工程依据。     

Nomex蜂窝复合材料冲击损伤及剩余剪切强度试验

Nomex蜂窝复合材料在航空航天中的应用越来越广泛,但其对低速冲击损坏较为敏感,针对Nomex蜂窝复合材料冲击损伤问题,研究了蜂窝材料在冲击作用下的损伤行为,并进行了剩余剪切强度试验,观察试验件应变值变化,得出试验结构件破坏载荷和最大破坏应变,并与未进行冲击试验的试验件进行对比。结果表明:冲击损伤后,破坏载荷的保持率为69.0%左右,破坏最大应变的保持率为78.8%,即冲击损伤使蜂窝复合材料的力学性能恶化,且影响较大。     

二维C/SiC复合材料低速冲击损伤特性的表征研究

为研究二维C/SiC复合材料的低速冲击损伤性能,采用落锤式冲击试验机进行低速冲击试验,并利用声发射技术对试验进行动态监测以及冲击后试样的检测。结果表明:冲击能量的大小是造成C/SiC复合材料损伤模式不同的主要因素,同时,声发射参数可以很好地表征C/SiC复合材料的损伤模式和损伤演化过程。在较低冲击能量下(3 J以下),材料的低速损伤主要是基体开裂;介于3 J到9 J之间的冲击作用下,基体开裂和分层是材料损伤的主要模式;冲击能量一旦超过9 J,材料中出现大量纤维断裂。     

展宽机织复合材料破片高速冲击仿真模拟研究

本文基于数值仿真方法研究了展宽平纹机织复合材料平板在金属破片高速冲击载荷作用下的失效行为。在显示动力学求解软件LS-DYNA~?中建立了平纹机织复合材料的宏观精细化有限元模型,通过多尺度分析计算得到单层机织复合材料的等效力学性能,采用经典的Chang-Chang失效准则评估复合材料靶板的冲击损伤和失效行为。通过平板高速冲击试验确定了材料在特定冲击条件下的临界穿透速度范围和典型破坏模式,并与数值仿真结果对比,验证了数值模型的准确性。在此基础上,采用所构建的冲击仿真模型研究了平纹机织复合材料在不同冲击速度(0.1～0.8 km/s)载荷下的侵彻失效特性。研究结果表明:展宽机织复合材料平板在承受高速冲击载荷过程中,中间层受压缩损伤区域较小,靠近边界层损伤区域较大;随着冲击速度的增加,机织复合材料平板受压缩损伤区域减小;在冲击速度为0.2～0.8 km/s下,平板吸收能量与破片冲击速度呈近线性关系。     

编织型复合材料低速冲击损伤及剩余压缩强度研究

通过应用三维逐渐累积损伤理论和分析技术,建立了适用于编织型复合材料板的低速冲击(LVI)及冲击后压缩破坏(CVI)过程的一种全程分析方法.该方法对复合材料板的冲击以及冲击后含损伤板在压缩载荷下损伤扩展的全过程进行分析,分析中把冲击后复合材料板的预测损伤直接用于剩余压缩强度研究,从而提高了最终失效载荷的预测精度,而且避免了为获得冲击后损伤状态参数所进行的大量试验,同时开发了与由MSC.NASTRAN求解器调用执行的模拟程序.     

复合材料夹芯结构低速冲击性能研究

复合材料夹芯结构为电子设备与外层蒙皮提供了一体化设计的思路,可以大幅降低飞行器的结构重量。通过低速冲击试验和ABAQUS仿真研究了5 J和10 J冲击能量下某飞行器复合材料机翼蒙皮典型夹芯区域在低速冲击下的性能。随着冲击能量的增加,复合材料泡沫夹芯结构的能量吸收率由5 J的72.0%提升至10 J的76.0%。由仿真结果可知,当冲击能量达到10 J时,出现了纤维损伤,且损伤沿表层铺层角度扩展,基体压缩损伤主要出现在冲击正面,基体拉伸损伤主要出现在冲击背面,损伤随冲击能量的增加而变大。当冲击能量达到10 J时,上面板与泡沫芯体粘接处也产生了较大的损伤。     

光纤复合材料结构低速冲击判位研究

复合材料智能结构容易产生从表面无法探测到的低速冲击损伤。试验利用光纤复合材料结构中布拉格光纤光栅传感器受到低速冲击后中心波长随应力变化这一特性,在恒温下用布拉格光栅对复合材料智能结构受到的低速冲击位置给出判别。通过计算冲击待测数字采样信号与所有冲击模板数字采样信号的Hausdorff距离,给出两者的相似度,利用相似度判别复合材料结构低速冲击位置。试验表明布拉格光纤光栅传感器可以监测复合材料冲击信号,能够对复合材料结构低速冲击进行判位研究。     

Investigation of low velocity impact behaviors of honeycomb sandwich composites

Honeycomb sandwich composites are used as significant structural members in advanced engineering applications. Thus, it is critical to determine how they behave under impact loading, in addition to other loads. In this study, low velocity impact loading behaviors of honeycomb sandwich composites were experimentally investigated. Almost all of the design parameters of honeycomb sandwich composites were investigated. The results indicated that the core thickness of honeycomb had no effect on the strength of the composite, and the parameter influencing the impact behavior of the specimen the most was the face sheet thickness. When the face sheet thickness of the specimen was increased, the most apparent strength increase was observed in the models using carbon fiber-reinforced composite face sheets. For all face sheet types subject to impact energy of 10 Joules, the upper face sheets of 0.5 mm-thick specimens were perforated.     

某型直升机蜂窝夹层结构有限元分析

对某型直升机蜂窝夹层结构抗弯刚度进行了深入探讨,给出理论上分析计算蜂窝夹层结构抗弯刚度的一般方法,得出了影响弯曲刚度的主要因素。并通过有限元分析软件Nastran对一典型蜂窝夹层结构抗弯刚度进行有限元分析,得出了正确的蜂窝夹层结构应力云图和变形,具有一定的工程指导意义。     

The response of honeycomb sandwich panels under low-velocity impact loading

This paper describes the results of an experimental investigation and a numerical simulation on the impact damage on a range of sandwich panels. The test panels are representative of the composite sandwich structure of the engine nacelle Fan Cowl Doors of a large commercial aircraft. The low-velocity impact response of the composites sandwich panels is studied at five energy levels, ranging from 5 to 20 J, with the intention of investigating damage initiation, damage propagation, and failure mechanisms. These impact energy levels are typically causing barely visible impact damage (BVID) in the impacted composite facesheet.A numerical simulation was performed using LS-DYNA3D transient dynamic finite element analysis code for calculating contact forces during impact along with a failure analysis for predicting the threshold of impact damage and initiation of delaminations. Good agreement was obtained between numerical and experimental results. In particular, the numerical simulation was able to predict the extent of impact damage and impact energy absorbed by the structure. The results of this study is proving that a correct numerical model can yield significant information for the designer to understand the mechanism involved in the low-velocity impact event, prior to conducting tests, and therefore to design a more efficient impact-resistant aircraft structure.     

A study on the crashworthiness and rollover characteristics of low-floor bus made of sandwich composites

This paper describes the results of the numerical evaluation on crashworthiness and rollover characteristics of a lowfloor bus vehicle made of sandwich composites. The sandwich composite used for the vehicle structures was composed of aluminum honeycomb core and WR580/NF4000 glass-fabric/epoxy laminate facesheets. Material tests were conducted to determine the input parameters of the composite laminate facesheet model and the effective equivalent damage model for the orthotropic honeycomb core material. Crashworthiness and rollover analysis of the low-floor bus was conducted using the explicit finite element method (FEM) analysis code LS-DYNA3D with the lapse of time. The crash condition of the low-floor bus was a frontal accident with a speed of 60 km/h. Rollover analysis was done according to the safety rules of the European standards (ECE-R66). The angular and translation velocity and its angle with the ground just before impact for rollover were calculated using the dynamic analysis program. The results showed that the survival spaces for the driver and passengers were secured against frontal crashworthiness and rollover of the low-floor bus. In addition, the modified Chang-Chang failure criterion is recommended to predict the failure modes of the composite structures for crashworthiness and rollover analysis.     

Impact behaviour of GFRP and Kevlar/epoxy sandwich composite plate: Experimental and FE analyses

In this paper, dynamic response of GFRP composite plate under ballistic impact has been studied by experimental tests and also by an efficient FE model. Material characterization of GFRP composite is performed as required for progressive damage analysis of laminate due to impact. Shock effect of impact is considered in the material modeling of composite plate. The influence of the target thickness on the ballistic performance of the composite plate is also studied by considering 3.12, 6.24 and 9.36 mm thick targets. Moreover, sandwich composite plate consisting of GFRP and Kevlar/epoxy in three different combinations of laminate layers is considered to obtain suitable combination for structural application that offer better penetration resistance. Damage pattern, contact force histories and stresses in composite plate are studied in addition to residual velocity and acceleration of projectile. Numerical results from present FE model in terms of residual velocities and damage patterns in composite plate show good agreement with the experimental results.

     

结构型吸波材料电磁特性的设计计算

结构型吸波材料兼具吸波与承载的双重功能,且具有可设计性,是一个重要的吸波材料的研究方向。夹芯结构吸波复合材料因其质轻、强度高,又能较好地吸收电磁波而广泛应用于飞机的机翼、尾翼和机身等部位。应用时域有限差分法(FDTD)建立正六边形蜂窝夹芯结构和波纹板型夹芯结构的电磁散射模型,通过数值仿真手段,计算了两种夹芯吸波结构和全金属结构的RCS值,对不同结构形状的夹芯结构的吸波性能进行了分析。     

基于匹配追踪的蜂窝夹层复合材料损伤检测

基于Lamb波和匹配追踪时频分析方法,提出一种损伤成像方法,对蜂窝夹层复合材料结构进行损伤监测.首先针对Lamb波传播的特点,提出了匹配追踪方法的快速实现方案,该方法能准确地匹配失真变形的窄带脉冲信号,并识别Lamb波的模态;然后对由压电传感器采集到的Lamb波信号,采用匹配追踪方法提取特征信息,得到Lamb波的能量分布;在此基础上,考虑Lamb波在各向异性结构中传播速度的影响,将损伤处的散射波能量分布和各像素点对比度联系起来,得到损伤图像,将损伤的情况可视化.通过蜂窝夹层复合材料结构实验验证了该方法的可行性和有效性.     

连续梯变拉胀蜂窝面内冲击动力学性能研究

研究了一种连续梯变拉胀蜂窝结构,对该结构的相对密度公式进行了推导,采用Abaqus/Explicit建立了蜂窝结构的数值模型,研究了蜂窝结构在不同冲击速度下的变形模式并获得了变形模式分类图,对不同厚度的蜂窝结构在不同速度下的动力学响应和能量吸收情况进行了研究。研究结果表明,蜂窝结构变形模式主要分为准静态模式、转换模式和动态模式,正梯度变化(Positive gradient vary,PGV)蜂窝结构相比负梯度变化(Negative gradient vary,NGV)蜂窝结构的转换模式区域覆盖范围更大,在冲击的初始阶段,PGV蜂窝结构的初始峰值应力相比NGV蜂窝结构更高,蜂窝结构的比能量吸收则随着壁厚的增加和冲击速度的提高而增加,NGV蜂窝结构相比PGV蜂窝结构具有更好的能量吸收能力,并且随着冲击速度的增加,优势更为明显。