Low-velocity impact damage response of fiberglass/magnesium fiber-metal laminates under different size and shape impactors

Low-velocity impact tests are performed on fiberglass/AZ31B-H24 magnesium fiber-metal laminates (FMLs) with various configurations in order to gain a better understanding of the effect of an impactor's features on the response of this type of FML. For that, impactors with two different shapes (hemispherical and sharp-edged) and sizes are used to impact the specimens. The impact response data, such as the deformation of the contact location and energy absorption, is obtained directly during the impact tests through the impact equipment, while mechanical sectioning was carried out to establish the extent of delaminated area and post-impact residual deformation. While the sharp-edged impactor caused the development of cracks on the metal constituent, and delamination within the specimens, the hemispherical ones imposed more influence over the residual deformation. Noticeable differences are observed in response of FML specimens made with two and three layers of magnesium, especially with respect to the energy absorption capacity. Moreover, finite-element analysis, as a major part of this study, has been employed to simulate the low-velocity impact response of FML specimens. The behavior of specimens has been simulated using the commercial finite-element code ABAQUS. The results imply that there is a good agreement between the experimental and numerical results.     

Impact response of fiber metal laminate sandwich composite structure with polypropylene honeycomb core

Fiber metal laminates (FMLs) were used as skin on polypropylene honeycomb core to form a sandwich structure. Impact response was measured by conducting a series of low-velocity impact test. Impact force and the force time history were recorded and analyzed. It was found that the maximum impact load increased up to a threshold value at which it plateaus while the energy absorption in the structure increased with increasing impact energy. Post-impact optical image showed a change in damage area with increasing impact energy. The impact damage threshold energy for the sandwich structure was clearly shown in the range of impact energy between 7.84 J and 11.76 J where damages including delamination of the skins and global bending of the structure were observed.     

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.     

Structural intensity study of plates under low-velocity impact

The transmissions of transient energy flow and dynamic transient response of plate structures under low-velocity impact are presented. The structural intensity approach is used to study the transient dynamic characteristics of plate structures under low-velocity impact. In the dynamic impact response analysis, nine-node degenerated shell elements with assumed shear and membrane strain fields are adopted to model the target and impactor. The dynamic contact-impact algorithm and the governing equations for both the target and impactor are derived based on the updated Lagrangian approach. Explicit integration algorithm has been adopted in the time integration process. The novel structural intensity streamline representation is introduced to interpret energy flow paths for transient dynamic response of plates under low-velocity impact. The effects of plates with and without structural damping on the energy flow and energy path are discussed. Numerical results, including contact force, deflection histories and transient energy flow vectors as well as structural intensity streamlines, show that the present method and representation are an efficient approach for exploring dynamic response for plate structures subjected to low-velocity impact.     

薄面板复合材料蜂窝夹层结构冲击试验

为研究薄面板复合材料蜂窝夹层结构在冲击载荷下的接触力响应和损伤情况,用两种不同质量的冲头对不同面板厚度的复合材料夹层结构进行了多种能量的落锤式冲击试验,并对冲击后的试验件进行了损伤测量。结果表明：冲击能量相对较低时,最大接触力较小,随着冲击能量的增加,最大接触力在增大过程中会出现门槛值,即达到某一值后不再上升。低能量下,冲击损伤表现为面板凹坑和冲击点周围的少量分层,随着冲击能量变大,面板逐渐出现纤维断裂进而被穿透。面板未穿透时,冲头会反弹,接触力-时间曲线的下降段没有台阶,分层区域直径约为冲头直径的1.2倍;面板穿透时,冲头不反弹,接触力-时间曲线下降段出现台阶,分层区域直径约为冲头直径的1.8倍。当最大接触力达到门槛值后,相同冲击能量下,冲头质量越大,冲击持续时间越长,凹坑越深。     

Composite materials response under low-velocity impact

A simple model, based on energy considerations, has been tested to predict the maximum contact force during a low-velocity impact between an impactor and a composite plate. Three different composites, i.e. glass cloth-polyester, carbon cloth-polyester and nylon cloth-polyester, were examined.The results reported here, obtained using an instrumented apparatus, show that the total energy applied during the impact is the governing parameter of the phenomenon, rather than the impactor speed or mass. All the composites under evaluation did not show any variation of elastic modulus with impact velocity. Moreover, the dynamic behaviour of carbon-polyester and nylon-polyester composites can be predicted by simple static tests, because of their insensitivity to rate-dependent phenomena; for these materials a simulation of impact tests by static tests is therefore suggested.Glass-polyester composites did show a rate-dependent behaviour, by an increase in strength of about 70% with respect to the static case; a small number of dynamic tests is, however, sufficient to characterise their behaviour under impact conditions.     

Effect of woven yarn angle on the low-velocity impact damage response of fibre woven thermoplastic composites

Fibre woven thermoplastic composites (FWTC) are widely used in aerospace and other fields because of their excellent performance. During service, FWTC structures are inevitably subjected to low-velocity impact (LVI), which can cause invisible damage and eventual failure of the material. At the moment, studies on FWTC mostly focused on the orthogonal woven yarns while there's few reports about the effect of the yarn angle changing on the woven material's LVI damage response. This study aims at the effect of yarn angle changing on the damage behaviour of FWTC. A method for preparation of nonorthogonal prepregs was proposed, by which FWTC laminates with different yarn angles (60°, 75°, and 90°) were prepared for LVI tests. The results show that the maximum impact displacement and the impact duration of the impactor decrease with the decrease of the yarn angle when the FWTC laminate is subjected to LVI, while the maximum impact force shows an increasing trend. This indicates that the smaller yarn angle causes the better load-bearing capacity of the FWTC laminate under LVI conditions, while the orthogonal FWTC laminate is more ductile. The damage morphology indicated by the impact of the FWTC laminate are matrix cracks and yarn breaks, and the damage area increases with the decrease of yarn angle, where the damage of orthogonal laminate is more serious more concentrated. The results found in this paper can provide useful guidance for engineering applications and failure analysis of FWTC.     

Experimental and numerical investigations of low velocity impact on functionally graded circular plates

This paper addresses low-velocity impact behaviour of functionally graded clamped circular plates. An experimental work was carried out to investigate the impact behaviour of FG circular plates which is composed of ceramic (SiC) and metal (Al) phases varying through the plate thickness by using a drop-weight impact test system. The influence of the compositional gradient exponent and impactor velocity on the contact forces and absorbed energies was concentrated on the tests. The explicit finite element method, in which a volume fraction based elastic–plastic model (the TTO model) was implemented for the functionally graded materials, was used to simulate their drop-weight impact tests. Effective material properties at any point inside FGM plates were determined using Mori–Tanaka scheme. The experimental and numerical results indicated that the compositional gradient exponent and impactor velocity more effective on the elasto-plastic response of the FG circular plates to a low-velocity impact loading. The comparison at the theoretical and experimental results showed that the use of the TTO model in modelling the elasto-plastic behaviour of FG circular plates results in increasing deviations between the numerical and experimental contact forces for ceramic-rich compositions whereas it becomes more successful for metal-rich compositions.     

Behaviour of multiple composite plates subjected to ballistic impact

An experimental and numerical investigation has been carried out to study the behavior of single and multiple laminated panels subjected to ballistic impact. A pressurized air gun is used to shoot the impactor, which can attain sufficient velocity to penetrate all the laminates in a multiple laminated panel. The incidental and residual velocity of the impactor is measured to estimate the energy absorption in the impact process. The commercially available code ABAQUS has been used for the numerical simulation where the impactor has been modeled as a rigid body and the laminates have been modeled with a simple shell element. A user material model based on a continuum damage mechanics concept for failure mechanism of laminated composites has been implemented. Experimental tests showed that the numerical model could satisfactorily predict the energy absorption. Most interestingly, it has clearly demonstrated a feasible phenomenon behind counterintuitive experimental results for the multiple laminated panels.     

Impact characterization of glass/epoxy composite plates: An experimental and numerical study

This study presents the effects of impact energy, impactor mass and impact velocity on the maximum contact force, maximum deflection, contact time, absorbed energy, and overall damage area of glass/epoxy laminated composites, experimentally and numerically. The stacking sequence of the composite plates was chosen as [0°/30°/60°/90°]_S. The impact event was simulated and analyzed by using 3DIMPACT finite element code. The overall delamination area obtained from experimental study and numerical analyses were also examined. It is seen that the numerical results are in good agreement with experimental results.     

Indentation of functionally graded beams and its application to low-velocity impact response

The problem of contact between a rigid cylindrical indenter and a functionally graded (FG) beam is studied. The elastic modulus of the material varies in an exponential fashion across the thickness of the beam. For the sake of comparison indentation of a homogeneous beam is also considered. In the case of FG beams indentation of both soft and hard sides of the beam are studied. Results are presented for contact force–contact length relations and contact stresses in the three types of beams. Maximum normal strains and stresses and maximum transverse shear stresses are plotted as a function of strain energy (work done by the indenter) in the beam. The results are extended to low-velocity impact problems. It is seen that for a given impact energy in low-velocity impacts, the maximum stresses and strains are significantly lower in FG beams when the impact occurs on the softer side of the beam.     

半球形头弹不同角度冲击下编织复合材料板的侵彻特性

利用一级气炮发射半球形头弹冲击2 mm厚的编织复合材料层合板,冲击角度为0°、30°和45°,通过高速相机记录弹靶撞击过程并得到弹体速度数据。利用拟合公式处理试验数据,得到不同冲击角度时的弹道极限值,并和理论模型结果进行对比。分析了冲击角度对靶板弹道极限、能量吸收率和失效模式的影响。结果表明：45°斜冲击时的靶板弹道极限最高,正冲击次之,30°斜冲击最低。相同冲击能量时,45°斜冲击的能量吸收率最高,低能量（<80 J）冲击时,30°斜冲击比正冲击能量吸收率高,高能量（>80 J）时,正冲击更高。正冲击时,靶板正面因剪切失效而形成圆形凹坑,背面因纤维拉伸失效形成菱形鼓包,斜冲击形成椭圆形扩孔,且其面积随冲击角度增加而增加。     

球体斜碰撞下包装材料能量传递及转换的试验研究

目的 针对在球体斜碰撞过程中,包装材料界面能量变化及其量化表征的问题,基于碰撞接触面的几何特征,提出外加能量吸收率、传递率和转换率的计算模型。方法 首先,分析球体斜碰撞接触面的几何特征,利用基圆和滑移面面积建立能量吸收率、传递率,以及不同方向能量比率的数学表达式。然后,通过搭建球体自由跌落斜碰撞测试平台,分析冲击角、衬垫厚度、跌落高度、球体直径和材料密度对能量参量的影响。结果 通过碰撞接触面积计算能量吸收率和转换率,遵循了能量守恒定律,具有可行性;能量吸收率在75%以上,并随着跌落高度、球体直径和密度增加而变大,而冲击角对能量吸收率的影响较小;法向能量比率随着冲击角增加、球体直径减小而下降,切向能量比率与此相反,跌落高度和密度对能量比率无明显影响;在给定工况下,衬垫的最佳吸能厚度为4 mm。结论 文中的分析有助于包装材料碰撞界面处能量变化以及接触特性的研究。     

内含气体对蜂窝纸板异面动态冲击性能的影响

目的以六边形蜂窝纸板为对象,研究内含气体对其异面冲击性能的影响。方法通过动态冲击实验分析内含气体对接触力、最大接触力、最大位移、最大应变和吸收能的影响,得出不同孔隙率时,蜂窝纸板的接触力-时间曲线,最大接触力、最大位移、最大应变、吸收能与冲击能曲线和吸收能-孔隙率曲线。结果在给定冲击能的情况下,最大接触力与吸收能随着孔隙率的增大而减小,最大位移及最大应变随着孔隙率的增大而增大。在孔隙率一定时,最大接触力、最大位移、最大应变和吸收能随冲击能线性增大。此外,冲击能越大,接触力达到峰值的时间越短,接触持续时间越长。结论在动态冲击实验中,内含气体使蜂窝纸板吸收冲击能的能力明显增强,并且当冲击能一定时,孔隙率越大,蜂窝纸板越容易被压变形,吸收能越少。     

Response of composite sandwich panels with transversely flexible core to low-velocity transverse impact: A new dynamic model

A new computational procedure based on improved higher order sandwich plate theory (IHSAPT) and two models representing contact behavior between the impactor and the panel are adopted to study the low velocity impact phenomenon of sandwich panels comprising of a transversely flexible core and laminated composite face-sheets. The interaction between the impactor and the panel is modeled with the help of a new system having three-degrees-of-freedom, consisting of spring–mass–damper–dashpot (SMDD) or spring–mass–damper (SMD). The effects of transverse flexibility of the core, and structural damping are considered. The present analysis yields analytic functions describing the history of contact force as well as the deflections of the impactor and the panel in the transverse direction. In order to determine all components of the displacements, stresses and strains in the face-sheets and the core, a numerical procedure based on improved higher order sandwich plate theory (IHSAPT) and Galerkin's method is employed for modeling the layered sandwich panel (without the impactor), while the analytic force function developed on the basis of SMDD or SMD model, can be used for the contact force between the impactor and the panel. The contact force is considered to be distributed uniformly over a contact patch whose size depends on the magnitude of the impact load as well as the elastic properties and geometry of the impactor. Various boundary conditions for the sandwich panel have also been considered. Finally, the numerical results of the analysis have been compared either with the available experimental results or with some theoretical results.     

Impact response of woven composites with small weaving angles

This paper presents experimental investigations on impact response of woven composites with various weaving angles between interlacing yarns. A method for preparing novel woven composites with small weaving angles is presented. The effects of the weaving angle on the impact characteristics such as peak force, contact duration, maximum deflection and absorbed energy are also examined. An energy profiling method seems to be useful for identifying the penetration and perforation thresholds of the woven composites. The damage process of individual woven composites can be reconstructed from comparing the corresponding load–deflection curves, energy profile and images of damaged specimens. The study concludes that the energy absorption capability and perforation threshold of woven composites can be significantly improved by using a small weaving angle between interlacing yarns. For example, the perforation threshold of [0/20]₄ woven composite, which has a weaving angle of 20° between interlacing yarns, is about 40% higher than that of [0/90]₄ woven composite, which has a weaving angle of 90° between interlacing yarns. The higher energy absorption capability of [0/20]₄ over [0/90]₄ is attributed to a lower stiffness caused by a more polarized fiber orientation and a smaller fiber crimp, resulting in a larger maximum deflection, a more extended damage zone and a larger amount of fiber pullout.     

Impact damage and residual strengths of woven fabric glass/polyester laminates

Thick glass/polyester laminates of four different dimensions subject to low-velocity impact have been investigated using a guided drop-weight test rig with a flat-ended impactor in ascending energy order up to 3100 J. The characteristics of impact response and energy absorption have been determined by impact force and absorbed energy histories, and impact damage incurred was examined by cross-sectioning and ultrasonic C-scanning. Residual compressive strengths were measured, and the damage tolerance of the laminates was assessed by the retaining ability of these strengths. It is found that the salient features in force-time history curves can be related to fracture processes occurring in the laminates, and that the established relationships between impact force and incident kinetic energy (IKE) can be used to identify damage initiation without examining impacted specimens, which is later confirmed by the damage force maps. The constructed damage force and energy maps have shown not only damage initiation in an unstable fashion but also increase of damage size with IKE and force until reaching their load-bearing capabilities. Residual compressive strengths are reduced very rapidly with the increase of impact damage due to extensive delamination.     

蜂窝纸板异面动态冲击性能的实验分析

目的以六边形蜂窝纸板为研究对象,研究厚度对其异面冲击性能的影响。方法通过动态冲击实验来分析接触力、最大接触力、最大位移、最大应变、吸收能与单位厚度冲击能之间的关系,研究厚度为30,40,50和60 mm等4种蜂窝纸板的异面冲击力学性能。结果当冲击能一定时,随着蜂窝纸板厚度的增加,接触力逐渐减小,接触时间逐渐变长;当单位厚度冲击能一定时,厚度与最大位移和吸收能成正比例关系,厚度与接触力、最大接触力、最大应变成反比例关系;对于任一厚度的蜂窝纸板,最大接触力、最大位移、最大应变、吸收能随单位厚度冲击能的增加而增加,且与其呈线性关系。结论当冲击能相同时,不同厚度蜂窝纸板的吸收能几乎相同,可知蜂窝纸板吸收能量的能力与蜂窝纸板的厚度无关,取决于冲击能量的大小。     

The effect of polyacrylate microstructure on the impact response of PMMA/PC multi-laminates

Polymer armor is widely implemented in many military and commercial applications, particularly where optical clarity is required. The impact mechanics and energy absorption mechanisms of these multi-layered structures are not well understood. This experimental study focuses on the impact response of three-layered structures consisting of poly(methyl methacrylate) (PMMA) and polycarbonate (PC) outlerlayers with various polyacrylate adhesives. Specifically, the effect of varying the microstructure of a soft interlayer incorporated into all-polymer multi-laminates is investigated. Four polyacrylates (VHB 4905, VHB 5925, VHB 4930 and VHB 4936) having a common acrylic base matrix with microstructural variations including combinations of compressible air gaps and rigid microsphere inclusions. To examine how interlayer microstructure affects impact resistance, an instrumented, compressed air driven, experimental setup is utilized to conduct intermediate velocity (9-30 m/s) normal impact testing. The setup is unique in that both force and displacement during impact are recorded independently using a shock accelerometer embedded impactor and optical displacement sensors measuring contact force and out-of-plane deflection, respectively. Quantitative metrics from the data are used to characterize and assess impact response between various configurations. Two impact velocities are tested: 12 and 22 m/s. Several correlations between adhesive microstructure and impact response are observed, including a secondary contact force decrease in multi-laminates having interlayers with microspheres and delamination in multi-laminates having interlayers without air gaps. The multi-laminates with VHB 5925 adhesives (air gaps only) showed the longest cracks and largest fracture area, which directly relates to the greatest displacements and pulsewidths, and smallest second force peaks. Increased fracture compromises structural integrity resulting in more deflection, prolonged impactor contact with the multi-laminate, and decreased elastically stored energy lessening impactor reload. It is demonstrated that this experimental methodology is capable of consistently probing and assessing the local impact response and modulation of an impact load when a multi-layered polymer includes a soft middle layer. Quantitative and qualitative effects of the interlayers’ microstructure on overall impact performance are presented.     

Contact force history analysis of composite sandwich plates subjected to low-velocity impact

Usually the modified Hertzian contact law or experimental static indentation law has been used to analyze low-velocity impact response of composite laminates. In composite laminated plates subjected to low-velocity impact, usually indentation by impact is very small and also energy absorption by indentation is negligible, so ‘spring element method’, which proposed by author recently, can be well applied to investigate impact response. In the present study ‘lumped mass method’ also had been proposed by author to approximately calculate contact force history of composite laminates will be conceptually described as well as the spring element method. And it will be discussed that how the spring element method can be applied to composite sandwich plates. Finally numerical results easily obtained from finite element analysis based on the spring element method using general-purpose commercial FEM software is compared with experimental results. The comparison shows overall agreement.