穿孔损伤位置对复合材料桨叶振动特性的影响

以某直升机复合材料旋翼桨叶为参考, 在几乎没有对结构进行简化的情况下, 利用有限元软件ANSYS建立完整的有限元模型。在桨叶展向和弦向的不同位置模拟穿孔损伤, 与无损伤桨叶进行比较, 分析不同损伤位置对振动特性的影响, 得到振动特性与穿孔损伤位置的关系。结果表明, 穿孔损伤一般不会引起各阶振动模态的改变, 但会使各阶振动频率发生变化, 对各阶振动频率的影响程度既与损伤发生的位置有关, 也与主承力结构的损伤程度有关。桨叶根部损伤对各阶振动频率都有较大影响, 前缘和后缘损伤对摆振频率影响最大, 翼盒损伤对扭转频率影响最大; 大梁和后缘条的损伤面积越大对摆振频率的影响越大, 抗扭盒形件、 加强梁和大梁内抗扭层等承扭结构的损伤面积越大对扭转频率影响越大。      

穿孔损伤大小和方向对复合材料桨叶振动特性的影响

通过建立的全桨叶有限元模型, 研究了穿孔损伤的大小和方向对桨叶振动特性的影响。以桨叶根部z=50mm处矩形剖面和中部z=835mm处翼型剖面为研究对象, 分别在前缘、 翼盒和后缘模拟不同口径的穿孔损伤, 得到振动特性与穿孔损伤大小的关系, 并通过改变前缘的穿孔损伤方向, 得到振动特性与穿孔损伤方向的关系。结果表明, 穿孔损伤一般不会引起各阶振动模态的改变, 但会使各阶振动频率发生变化。随着损伤口径的增大, 各阶振动频率都降低。损伤发生在前缘和后缘, 摆振频率降低最多, 发生在翼盒, 扭转频率降低最多。穿孔方向对各阶振动频率的影响不仅与损伤的位置和结构有关, 还与损伤剖面的几何形状有关。对于根部矩形剖面, 穿孔方向与剖面弦向夹角为75°和105°对摆振频率影响最大, 对于中部翼型剖面, 夹角接近0°(180°)对摆振频率影响最大。      

多分层对复合材料层合板自振特性的影响

基于Mindlin一阶剪切理论分项等参插值的有限元法, 建立了含多个分层损伤复合材料层合板自由振动分析的有限元模型和分析方法, 并采用线性接触模型模拟分层区域上、 下子板的相互作用。通过典型数值算例, 讨论了分层位置、 数目及板的边界条件诸参数对其振动特性的影响。结果表明: 分层位置沿板长方向变化时, 中间分层的频率变化范围较大, 表面分层变化较小, 但变化趋势基本相同; 沿层合板厚度方向, 多分层中最长分层的位置越靠近层合板中面, 则其对振动特性的影响越大; 多个分层位置较靠近层合板表面, 且板边界条件约束较弱时, 多分层与单分层对振动特性影响的差别不大, 此时, 可将多分层损伤层合板简化为单分层损伤层合板来进行振动分析。      

含穿孔损伤复合材料桨叶结构的振动特性

现代直升机旋翼桨叶通常需要进行损伤容限分析与设计, 损伤对桨叶结构振动特性的影响是其中的重要内容之一。利用有限元法对选定的直升机复合材料桨叶翼段进行了穿孔损伤后的振动特性分析, 并与无损伤的翼段进行了比较, 得到了振动特性与穿孔大小及其位置的关系。结果表明: 旋转翼段的振动模态与静态翼段相同, 但各阶频率有所提高; 穿孔越大对翼段造成的损伤越大, 但穿孔损伤没有改变翼段的振动模态, 对翼段的振动频率影响也比较小; 不同阶次的振动频率随穿孔的位置变化趋势各不相同, 根部与前缘的穿孔损伤对翼段频率的影响较大。      

基体损伤对分层复合材料加筋板动力特性的影响研究

基于Mindlin假定的复合材料层合板单元和层合梁单元,推导了复合材料加筋板的刚度阵和质量阵;采用Adams应变能法与Rayleigh阻尼模型相结合的方法,构造了相应的阻尼阵列式;建立了分层损伤特征的三板模型和表征基体微裂纹损伤的基体损伤模型;并推导了一种基于Hertz型非线性接触法则的虚拟联接单元模型,以避免在振动分析过程中在低阶模态中分层处出现的上、下子板间不合理的嵌入现象;在上述模型和理论基础上,采用精细积分法求解含损伤结构的动力响应。对典型数例进行参数讨论,表明在动载荷作用下,嵌入分层损伤以及在振动过程中诱发的基体微裂纹损伤的演化将明显地影响加筋层合板的动力特性。     

含损伤复合材料AGS 板的屈曲特性

采用有限元数值模拟方法, 研究了蒙皮内含分层损伤复合材料格栅加筋板结构(AGS) 的稳定性问题。对蒙皮和肋骨分别采用基于Mindlin 一阶剪切理论的复合材料层合板单元和层合梁单元来模拟, 推导了相应的有限元列式, 并通过坐标变换, 利用蒙皮与肋骨的几何连续条件, 形成了AGS 的单元刚度阵和几何刚度阵, 建立了含损伤AGS 稳定性分析的有限元控制方程。通过典型算例, 研究了压缩载荷作用下, 分层形状、分层大小、分层深度、肋骨的高度和宽度、布置方式等因素对AGS 的稳定性特征的影响。数值结果表明, 含分层损伤的AGS 具有十分复杂的屈曲性态。屈曲临界力和屈曲模式与分层面积、分层形状、分层深度、肋骨的高度和宽度、布置方式和位置均密切相关。      

某型四座电动飞机复合材料机翼剪切性能试验与分析

为了验证某型四座电动飞机复合材料机翼结构强度是否满足适航规定(CCAR 23-R3《正常类、实用类、特技类和通勤类飞机适航规定》)要求,本工作对该复合材料机翼的翼梁、翼肋、蒙皮、前缘、后缘的布局和铺层等结构形式,以及机翼与机翼、机翼与机身的连接形式进行了研究分析,建立了四座电动飞机全机有限元数值分析模型,并计算了在适航规定要求的限制剪切载荷下,复合材料机翼的变形和应力分布情况,最后通过全机静力试验验证了有限元模拟结果的准确性。结果表明:有限元分析和试验结果有较好的一致性;该电动飞机复合材料机翼的结构设计形式,满足适航所规定的结构强度要求。     

基于频率识别纤维增强树脂复合材料加筋板的分层损伤

以纤维增强树脂（FRP）复合材料加筋板为研究对象,通过对比分层损伤发生前后FRP复合材料加筋板的振动频率变化,来识别FRP复合材料加筋板中的分层损伤。构建了人工神经网络（ANN）和基于有代理模型的优化算法（SAO）两种逆向检测算法,利用FRP复合材料加筋板在损伤前后发生的一系列频率变化值来逆推出FRP复合材料加筋板中的分层位置和大小。分别采用数值验证和实验验证来双重检验ANN和SAO两种算法的识别精度和效率。数值验证结果表明:ANN和SAO两种逆向检测算法对分层损伤位置和大小的识别最大误差分别是5.04%（ANN）和5.24%（SAO）,证明方法在理论上可行。实验验证结果表明:ANN在使用实测频率数据进行识别时预测精度很差,无法得到有效的分层损伤信息;而采用SAO可以较好地预测试件中的分层损伤,且对分层大小的预测比对分层位置的预测精度更高,其中,对贯穿损伤和底板损伤的大小预测误差分别不超过2.05%和9%,而四个试件中有两个试件预测的分层与实际的损伤部位存在重合（重合率分别为34%和32.65%）。因此,当前提出的ANN和SAO在理论上可行,但实际应用时都会受到不同程度实测数据误差的影响,相比ANN而言,SAO算法有更好的鲁棒性,在采用实测频率时也可以较为准确地预测出试件中的分层损伤。      

简谐激励下复合材料加筋板的基体微裂纹损伤演化

研究了在简谐激励作用下复合材料加筋板基体微裂纹损伤的演化行为及其对加筋板动力特性的影响。基于平均微裂纹密度和断裂力学方法, 建立了复合材料加筋板基体微裂纹演化的刚度退化准则。由于该准则考虑了载荷作用周期数的影响, 从而能够更合理地分析周期性动载荷作用下基体微裂纹损伤演化规律。采用Mindlin一阶剪切理论和复合材料模态阻尼模型, 建立了复合材料加筋板动力分析的有限元方法, 研究了在简谐激励作用下, 含分层损伤复合材料加筋板振动过程中诱发的基体微裂纹损伤的演化、 刚度退化, 频率折减和动力响应。      

冲击位置对复合材料加筋板冲击后压缩行为影响试验

对低速冲击(LVI)载荷下不同冲击位置对T型复合材料加筋板损伤容限的影响进行了试验研究.选取了2个典型冲击位置,即:两筋间蒙皮和筋条长桁边缘,引入目视可检冲击损伤(VID).借助目视及无损检测手段观察到不同冲击位置处的损伤存在显著差异.相比于蒙皮冲击,长桁边缘冲击处的损伤形式更复杂,表现为:纤维断裂、基体开裂、分层、层...     

Effect of impact failure on the damping characteristics of beam-like composite structures

This study deals with the free vibration response and damping characteristic of a cantilever composite beam having a single impact failure on it. The fundamental vibration frequency of the beam is measured experimentally using a non-contact technique for different failure locations and the damping ratio is calculated from the envelope of the free vibration response. A failure model based on the delamination formation is used in the finite element model of the damaged composite beam to determine the fundamental vibration frequencies. In the finite element modeling, ANSYS APDL language is used to create the composite beam model with different failure sizes and locations automatically. Experimental results show that damping ratio is more sensitive to a failure on the beam than the natural frequency and severity and location of the failure have considerable effects on the damping ratio.     

Effect of impact failure on the damping characteristics of beam-like composite structures

This study deals with the free vibration response and damping characteristic of a cantilever composite beam having a single impact failure on it. The fundamental vibration frequency of the beam is measured experimentally using a non-contact technique for different failure locations and the damping ratio is calculated from the envelope of the free vibration response. A failure model based on the delamination formation is used in the finite element model of the damaged composite beam to determine the fundamental vibration frequencies. In the finite element modeling, ANSYS APDL language is used to create the composite beam model with different failure sizes and locations automatically. Experimental results show that damping ratio is more sensitive to a failure on the beam than the natural frequency and severity and location of the failure have considerable effects on the damping ratio.     

含多裂纹损伤圆弧曲梁自由振动扰动的有限元网格自适应分析

该文建立圆弧形曲梁裂纹的截面损伤缺陷比拟方案,实施微裂纹损伤诱发截面弱化,实现多裂纹深度、位置、数目的模拟。引入变截面Timoshenko梁的h型有限元网格自适应分析方法,求解含裂纹损伤圆弧曲梁自由振动问题,得到优化的网格和满足预设误差限的高精度自振频率和振型解答,研究多裂纹损伤对圆弧曲梁振型的扰动行为。数值算例表明,该算法中网格非均匀加密可适应裂纹损伤引起的振型变化,应用于各类曲梁夹角和裂纹损伤分布工况下的自由振动研究,定量分析了多裂纹损伤深度、数目、分布对圆弧曲梁自振频率和振型的扰动影响,检验了该文算法的精确性和实用性。     

Detection of multiple cracks using frequency measurements

A method for detection of multiple open cracks in a slender Euler-Bernoulli beams is presented based on frequency measurements. The method is based on the approach given by Hu and Liang [J. Franklin Inst. 330 (5) (1993) 841], transverse vibration modelling through transfer matrix method and representation of a crack by rotational spring. The beam is virtually divided into a number of segments, which can be decided by the analyst, and each of them is considered to be associated with a damage parameter. The procedure gives a linear relationship explicitly between the changes in natural frequencies of the beam and the damage parameters. These parameters are determined from the knowledge of changes in the natural frequencies. After obtaining them, each is treated in turn to exactly pinpoint the crack location in the segment and determine its size. The forward, or natural frequency determination, problems are examined in the passing. The method is approximate, but it can handle segmented beams, any boundary conditions, intermediate spring or rigid supports, etc. It eliminates the need for any symbolic computation which is envisaged by Hu and Liang [J. Franklin Inst. 330 (5) (1993) 841] to obtain mode shapes of the corresponding uncracked beams. The proposed method gives a clear insight into the whole analysis. Case studies (numerical) are presented to demonstrate the method effectiveness for two simultaneous cracks of size 10% and more of section depth. The differences between the actual and predicted crack locations and sizes are less than 10% and 15% respectively. The numbers of segments into which the beam is virtually divided limits the maximum number of cracks that can be handled. The difference in the forward problem is less than 5%.     

Modal parameter identification and vibration based damage detection of a multiple cracked cantilever beam

This paper presents a detailed investigation on the modal parameter identification and vibration based damage detection of a multiple cracked cantilever beam with hollow circular cross-section. To consider multiple crack effects, a cantilever beam including cracks is considered for six damage scenarios. Finite element models are constituted in ANSYS software for numerical solutions. The results are validated by experimental measurements. Ambient vibration tests are performed to extract the dynamic characteristics using Enhanced Frequency Domain Decomposition (EFDD) and Stochastic Subspace Identification (SSI) methods. Calculated and measured natural frequencies and mode shapes for undamaged and damaged beams are compared with each other. Automated model updating is carried out using the modal sensitivity method based on Bayesian parameter estimation to minimize the differences for damage detection. In addition, modal assurance criterion (MAC) and coordinated modal assurance criterion (COMAC) factors are obtained from the mode shapes and two set of measurements to establish the correlation between the measured and calculated values for damage location identification.     

Modal power flow with application to damage detection

Features of power flow of an undamped beam at resonance are studied in the present paper. It is found that when an undamped beam undergoes free vibration at one of its natural frequencies, the active component of the power flow becomes zero while the reactive component is of modal pattern, whose characteristic frequency is twice of the natural frequency. The power flow in this case can thus be termed as modal power flow. The instantaneous energy density associated with the vibration mode consists of a static component and a dynamic component, related to the mean total and Lagrangian energy densities, respectively. The modal power flow is relevant to the latter but independent of the former. Potential application of modal power flow to structural damage detection is investigated. Two typical damages, transverse cracks and delaminations, are considered. A damage index based on the modal power flow is proposed, and compared with the damage indices based on the slope, the bending strain, and the strain energy through numerical examples. The imperfection of boundary conditions is also considered. It is shown that the proposed damage index is sensitive to both types of damage, thus can be used as an universal damage indicator.     

Experimental dynamic analysis on naturally curved honeycomb sandwich beams with different damage patterns

In this study, dynamic analysis of naturally curved honeycomb sandwich beam including two surface cracks and an impact region at the facing skin is presented. Laminates of facing skin and backing skin are known as carbon fiber‐plain weave composite laminates with 1.6 mm in thickness. In the first part, in order to determine mechanical properties of both the skin with no‐crack/crack(s) and the honeycomb core of the composite beam, static tensile tests are conducted with respect to straingage measurement technique. In the second part, drop weight impact tests and vibration tests are performed to present the free vibration characteristics of the clamped‐clamped honeycomb sandwich beam including cracks and an impact‐damaged region. Corresponding to damage patterns of the sandwich beam, experimental dynamic analyses consist of six steps: (1) Vibration analysis with no‐crack and no‐impact region, (2) Vibration analysis with no‐crack and an impact region, (3) Vibration analysis with a surface crack and no‐impact region, (4) Vibration analysis with a surface crack and an impact region, (5) Vibration analysis with two surface cracks and no‐impact region, (6) Vibration analysis with two surface cracks and an impact region. For these purposes, an impact hammer with a force transducer is used to excite the undamaged or damaged naturally curved honeycomb sandwich beam through the selected points. After the excitation, the responses are obtained by an accelerometer. Resonant frequencies for the modal responses of the naturally curved honeycomb sandwich beam with different damage patterns are discussed.     

基于模态频率的缺口梁疲劳裂纹扩展寿命预测

从试验出发,研究了含V型缺口悬臂梁在循环载荷作用下的疲劳裂纹扩展特性及其模态频率变化规律,分析了模态频率与裂纹扩展增量间的关联性。将裂纹扩展增量作为损伤参量,建立了基于模态频率下降率与损伤参量的关系。基于损伤力学,建立了裂纹损伤与循环加载次数的演化模型。结合模态频率下降率与裂纹损伤参量的关系,提出了一种基于模态频率下降率的缺口梁疲劳裂纹扩展寿命预测方法,实现了基于当前裂纹损伤和对应循环次数的疲劳裂纹扩展剩余寿命预测。结果表明,模态频率下降率对缺口梁的疲劳裂纹扩展寿命敏感,该方法预测的疲劳裂纹扩展寿命与实测的疲劳裂纹扩展寿命基本吻合。     

基于小波有限元的悬臂梁裂纹识别

研究了悬臂梁裂纹识别中的正反问题．即通过裂纹位置和尺寸求解梁的固有频率以及利用梁的固有频率．识别裂纹位置和尺寸。以矩形截面裂纹悬臂梁为例，利用小波有限元方法建立了梁自由振动的有限元模型．其中裂纹被看作为一刚度已知的扭转线弹簧，求解出了系统的固有频率；通过行列式变换，将反问题求解简化为只含线弹簧刚度一个未知数的一元二次方程求根问题，分别做出了以不同固有频率作为输入值时裂纹位置与弹簧刚度之间的解曲线，曲线交点预测出裂纹的位置与尺寸。数值算例证实了算法的有效性，为工程结构裂纹故障预示与诊断提供了新的方法。