基于灰色关联分析的轧制差厚板盒形件充液拉深成形工艺参数多目标优化

目的 将充液拉深工艺引入轧制差厚板零件的成形,为了进一步掌握差厚板的充液拉深成形性能,对差厚板盒形件充液拉深成形过程进行研究。方法 通过理论推导获取临界液池压力公式,在此基础上运用数值模拟方法分析液池压力比对差厚板厚度减薄率和厚度过渡区移动量的影响,采用正交试验和灰色关联分析获取成形参数对差厚板盒形件成形性能的影响规律和最优参数组合,实现对差厚板盒形件充液拉深成形工艺参数的多目标优化。结果 随着薄-厚侧液池压力比的增大,差厚板最大厚度减薄率先减小后增大,过渡区移动量先增大后趋于平稳,薄-厚侧液池压力比为2较为合理。厚侧压边力、摩擦因数、薄-厚侧液池压力之比、薄-厚侧压边力之比、厚侧液池压力对差厚板盒形件充液拉深性能的影响程度依次减小。结论 采用灰色关联分析得到的最优工艺参数组合来完成差厚板盒形件的充液拉深成形,能够有效地抑制差厚板零件厚度的过分减薄及厚度过渡区的过度移动,进而提高差厚板的成形性能。     

纸瓦楞夹层板的压缩变形与塑性吸能特性研究

目的研究在不同压缩速率下纸瓦楞夹层板的压缩变形与塑性吸能特性。方法利用Hoff夹层板、正交各向异性弹性薄板理论和工程梁理论,研究瓦楞夹层板的横向压缩位移,分析瓦楞芯层的压缩变形模式及塑性吸能特性,提出芯层结构的压溃强度模型,并通过静态压缩实验进行对比分析。结果B型、C型纸瓦楞夹层板的压溃强度理论预测值分别为0.1195,0.0612 MPa,在1,12,18,48 mm/min的压缩速率下,B型纸瓦楞夹层板的压溃强度分别为0.1011,0.1071,0.1048,0.1075 MPa,C型纸瓦楞夹层板的压溃强度分别为0.0462,0.0640,0.0475,0.0451 MPa。结论低应变率(低压缩率)条件下,纸瓦楞夹层板的横向压缩性能影响基本不变,弹性强度、屈服强度、压溃强度等基本相同。对于相同的材质,几何参数对纸瓦楞夹层板的压缩性能和塑性吸能影响较大。     

汽车双帽型前纵梁设计

试验数据表明,在正面碰撞中前纵梁是主要的吸能部件,因此在耐撞安全性的优化中,对前纵梁的优化十分重要。该文通过使用双帽型新型截面的前纵梁结构提升整车耐撞性能,应用有限元系列软件HyperWorks进行结构性能验证与优化设计。首先,建立双帽梁的轴向压溃简化模型,分析了双帽梁的轴向吸能特性;然后分析了简化模型与整车模型的相关性,提升了计算效率;最后,基于双帽梁的轴向吸能规律,对焊接边宽度参数进行了优化,优化后提高了双帽梁结构的耐撞性能,峰值压溃力减小了4.5%,比吸能增大了5.7%。     

双相钢DP600帽型梁碰撞实验与数值模拟

目的分析双相钢DP600的烘烤特性对碰撞实验的影响,以及验证修正的Johnson-Cook模型对双相钢DP600动态力学性能描述的准确性。方法对DP600帽型薄壁梁结构试件在轴向冲击下的压溃变形模式与吸能特性进行实验研究,采用前处理软件Hyper Works和LS-Dyna求解器对DP600帽型梁轴向压溃实验进行有限元分析。结果通过对比烘烤前后的碰撞实验结果,发现烘烤前后压溃力、位移与时间曲线吻合较好,变形结果基本一致。将实验与仿真结果进行对比分析发现,有限元模拟结果与实验结果吻合较好。结论烘烤温度为180℃,时间为20 min的烘烤工艺对材料特性影响不显著。验证了修正的Johnson-Cook模型能够较好地描述DP600的动态力学性能,可以应用于整车碰撞仿真中。     

轧制渐变厚度的汽车吸能盒结构参数优化

研究基于差厚技术的汽车吸能盒结构设计方案,提出了解决差厚板的厚度渐变特性和材料力学性能渐变特性的仿真建模方法,推导了综合考虑厚度分布、吸能盒重量、吸能量的多目标优化问题数学模型,基于多目标优化算法获得了差厚吸能盒结构最优设计参数,并实现了样件试制。试制的差厚吸能盒样件在准静态压溃过程中出现充分且对称的褶皱,且褶皱次序与厚度分布特征一致,变形模式稳定,在保持吸能水平提升的同时,与原冲压等厚吸能盒相比降重约7%。     

直升机抗坠毁元件构形设计分析研究

为探究差异化的构形参数对复合材料波纹梁吸能性能影响,针对多种构形波纹梁,进行动态压溃试验,对试验现象分析及试验数据处理,给出了多种构形波纹梁的载荷-时间曲线和破坏模式。采用有限元软件ABAQUS模拟波纹梁的瞬态冲击过程,得到吸能特性参数比吸能(SEA)和平均载荷值等,并与试验结果对比,对比结果验证了数值模型的有效性。通过试验及数值分析结果讨论了波纹构形对波纹梁峰值载荷和吸能能力的影响,对不同构形波纹梁以及增加薄弱环节设计的吸能差异作出评估,为实际工程设计提供参考依据。结果表明,利用等截面剖面杆轴向压缩载荷作用下的临界应力方程将波纹梁梁高/波幅比、波长/波幅比设定在相应关系式时波纹梁结构表现出较为稳定的压溃过程,具有一定的应用价值;波纹腹板圆角R值除了对峰值载荷及平均载荷有影响,对波纹梁破坏模式改变也有一定关系,薄弱圆角r值能比较好的改善峰值载荷大小。     

复合材料/铝复合管轴向准静态及冲击压溃的吸能特性

用数值模拟方法,研究了方形和圆形截面的复合材料/铝复合管在轴向准静态及冲击压溃下的吸能特性,计算得到压溃力-位移曲线。通过将一组方形截面复合管在准静态压溃条件下的计算结果与文献的实验数据进行对比,以验证有限元模型和参数设置的正确性。在铝管的管厚、管长以及截面外周长相同,缠绕不同厚度的复合材料情况下,对比分析了方形和圆形截面复合管在准静态及冲击压溃条件下的轴向压溃吸能特性。结果表明,复合管的截面构型对其吸能效果影响很大,在轴向准静态压溃条件下,圆形截面复合管吸能能力要强于方形截面复合管;冲击压溃吸能量不但与结构自身吸能力有关,还受到外界冲击大小的影响。在设计复合材料层厚度时,需要控制复合管的刚度,避免回弹造成吸能量的降低。     

含随机不确定参数复合材料薄壁结构吸能特性评估方法研究

针对复合材料力学性能分散度大、加工精度低,导致复合材料薄壁吸能因素不确定等,提出含随机不确定参数复合材料薄壁结构吸能特性评估方法。考虑材料力学性能及结构特征尺寸的不确定性,评估准静态压溃条件下薄壁圆管峰值载荷及比吸能指标。据试样级材料性能实验确定各参数分布特征;用Plackett-Burman方法选实验点,采用显式求解有限元方法分析选出对比吸能、峰值载荷影响显著的参数;建立影响显著参数及结构吸能特性指标间二阶响应面函数;据参数分布抽样计算获得吸能特性指标分布情况。结果显示,对复合材料薄壁圆管而言,纤维方向拉伸、压缩强度及圆管壁厚、基体压缩强度对其轴向压溃的比吸能及峰值载荷影响显著。     

基于内翻复合材料管的冲击吸能器特性研究

提出了一种利用复合材料管向内翻转、压溃来吸收冲击能量的吸能器。吸能器由复合材料管和两端的连接帽组成,其中一个连接帽内端面为平面;另外一个连接帽内端面为曲面,在复合材料管受到轴向冲击时,使管壁内翻,产生分层和断裂,并逐渐填满复合材料管内腔。在复合材料管的压溃过程中,没有任何的碎屑溢出,在管材内腔的碎屑逐渐被压实,进一步提高吸能器的性能。吸能器主要通过复合材料分层、断裂以及复合材料管与套筒间的摩擦来吸收冲击能量。分别使用静态试验和冲击试验研究了连接帽内表面曲率对吸能效果的影响,结果表明,该新型吸能器在减小初始峰值载荷的同时能够增加材料的比吸能,非常适合应用于轻量化的抗冲击结构中。     

圆形薄壁构件准静态径向压缩下的吸能特性分析

为探讨薄壁吸能构件径向压缩下的吸能防冲特性,以圆形薄壁构件为例,采用理论分析、数值模拟和实验研究方法,对构件径向压缩下的吸能防冲特性进行研究,得出以下主要结论:构件压缩过程中具有稳定的变形破坏模式和较为恒定的承载力。内径对载荷波动系数、冲程效率和总吸能影响较小,压溃峰值载荷、平均压溃载荷随内径增加而降低。构件压溃峰值载荷、平均压溃载荷和总吸能均随壁厚增加而增大,载荷波动系数和冲程效率随壁厚增加而降低。长度对载荷波动系数和冲程效率影响较小,构件压溃峰值载荷、平均压溃载荷和总吸能均随长度增加而增大。研究结果为圆形构件尺寸选取提供理论依据,为其它类型薄壁构件径向压缩吸能特性分析提供参考。     

V型折叠式夹层板横向压皱吸能特性研究

金属夹层板具有优越的力学性能,良好的吸能特性可用于船舶耐撞、抗爆防护结构设计。以V型折叠式夹芯结构为研究对象,通过试验分析夹芯层结构变形模式、压皱力历程曲线等,得到了夹芯层结构横向压皱力学性能,采用有限元软件Abaqus对其在横向受压时的力学行为进行数值仿真分析,分析结构压皱动态渐进屈曲过程、变形模式、吸能效率、平均压皱强度等。对比分析表明,V型夹芯层结构在横向压皱载荷下发生屈曲、褶皱变形模式,变形模式决定了压皱力学行为及其性能,其中单元变形模式I的吸能效率较高。采用合理的模型化技术得到的有限元计算结果与试验结果两者吻合较好,验证了有限元数值仿真的计算精度。     

楞型对瓦楞结构材料瓦楞方向准静态力学性能的影响

目的研究不同楞型瓦楞结构材料在准静态条件下对瓦楞方向相关力学性能的影响。方法通过有限元模拟的方法,在准静态压缩条件下,得到不同楞型的瓦楞结构材料在瓦楞方向上的变形模式、应力-应变曲线等,通过能量效率法对其峰应力、密实化应变、平均抗压强度和单位体积吸收能量等进行对比分析。结果在同一壁厚条件下,A,C,B,E这4种楞型的峰应力、平均抗压强度、单位体积吸收能量依次增大;对于任一楞型来说,峰应力、平均抗压强度、单位体积吸收能量随壁厚的增大而增大,且与其呈线性关系;随着壁厚的增大,A,C,B,E这4种楞型的峰应力、平均抗压强度、单位体积吸收能量的增长幅度依次增大。结论楞型对瓦楞结构材料瓦楞方向的力学性能有显著影响,在其他条件相同的情况下,A,C,B,E这4种楞型的力学性能依次增强。     

Effect of natural stitched composites on the crashworthiness of box structures

In the present paper the effects of stitching on the energy absorption and crashworthy behaviour of composite box structures will be studied. The combination of unidirectional carbon fibre-reinforced polymer (CFRP) and glass fibre-reinforced polymer (GFRP) composite materials are used to laminate the composite boxes. Delamination study in Mode-I with the same lay-up was carried out to investigate the effect of stitching on delamination crack growth on energy absorption of stitched and non-stitched composite box structures. The double cantilever beam (DCB) standard test method was chosen for delamination studies. For non-stitched and stitched composite boxes the lamina bending and brittle fracture crushing modes were observed. It was found that the stitched composite boxes which show higher fracture toughness in Mode-I delamination tests, are not necessarily able to absorb more crushing energy in comparison with non-stitched composite boxes. It was also observed that the position of stitched area can affect the crushing mode and consequently energy absorption capability of composite box structures. The main reason can be related to other mechanisms such as bending, friction and bundle fracture which significantly contribute to energy absorption. The analytical model based on energy balance approach is proposed to estimate the mean crushing force, F_m, in axial crushing of square composite box.     

薄壁开孔圆管在轴向荷载作用下的理论研究

研究薄壁开孔圆管的轴向耐撞性有助于其在缓冲、吸能领域的广泛应用。通过分别考虑开孔区域和未开孔区域的能量吸收特征并引入材料的应变强化效应,根据塑性铰理论建立了轴向荷载下开孔圆管轴对称压溃模式的理论模型,得到了弯曲应变能、拉伸应变能、平均压溃力、比吸能的解析表达式。分析结果表明:该理论模型的预测结果与数值和实验结果相吻合;正则化平均压溃力会随半皱褶长细比的降低而显著增加;单层孔数对正则化平均压溃力的影响会随管壁厚度的增加或孔半径的减小而降低;比吸能可通过减少单层孔数或减小孔半径提高。     

Some theoretical considerations on the dynamic response of sandwich structures under impulsive loading

A theoretical solution is obtained to predict the dynamic response of peripherally clamped square metallic sandwich panels with either honeycomb core or aluminium foam core under blast loading. In the theoretical analysis, the deformation of sandwich structures is separated into three phases, corresponding to the transfer of impulse to the front face velocity, core crushing and overall structural bending/stretching, respectively. The cellular core is assumed to have a progressive crushing deformation mode in the out-of-plane direction, with a dynamically enhanced plateau stress (for honeycombs). The in-plane strength of the cellular core is assumed unaffected by the out-of-plane compression. By adopting an energy dissipation rate balance approach developed by earlier researchers for monolithic square plates, but incorporating a newly developed yield condition for the sandwich panels in terms of bending moment and membrane force, “upper” and “lower” bounds are obtained for the maximum permanent deflections and response time. Finally, comparative studies are carried out to investigate: (1) influence of the change in the in-plane strength of the core after the out-of-plane compression; (2) performances of a square monolith panel and a square sandwich panel with the same mass per unit area; and (3) analytical models of sandwich beams and circular and square sandwich plates.     

A new composite energy absorbing system for aircraft and helicopter

In this paper, an innovative lightweight composite energy-absorbing keel beam system has been developed to be retrofitted in aircraft and helicopter in order to improve their crashworthiness performance. The developed system consists of everting stringer and keel beam. The sub-floor stringers were designed as everting stringer to guide and control the failure mechanisms at pre-crush and post-crush failure stages of composite keel beam webs and core. Polyurethane foam was employed to fill the core of the beam to eliminate any hypothesis of global buckling. Quasi-static axial crushing behaviour of the composite keel beam is investigated experimentally. The results showed that the crushing behaviour of the developed system is found to be sensitive to the change in keel beam web thickness. Laminate sequence has a significant influence on the failure mode types, average crush loads and energy absorption capability of composite keel beam. The desired energy absorbing mechanism revealed that the innovated system can be used for aircraft and helicopter and meet the requirements, together with substantial weight saving.     

Failure initiation and propagation characteristics of honeycomb sandwich composites

The energy absorbed during the failure of a variety of structural shapes is influenced by material, geometry and the failure mode. Failure initiation and propagation of the honeycomb sandwich under loading involves not only non-linear behavior of the constituent materials, but also complex interactions between various failure mechanisms. Therefore, there is a need for an improved understanding of the material characteristics and energy absorption modes to facilitate the design of sandwich performance. In the present study, failure initiation and propagation characteristics of sandwich beams and panels subjected to quasi-static and impact loadings were investigated. Experimental studies involved a series of penetration and perforation tests on 2D beam and 3D panel configurations using a truncated cone impactor with impact velocities up to 10 m/s. Preliminary tests were also performed on the sandwich beams subjected to the three-point bending. Load-carrying, energy-absorbing characteristics and failure mechanisms under quasi-static and impact loading were determined. Dominant deformation modes involved upper skin compression failure in the vicinity of the indenter, core crushing and lower skin tensile failure.     

明胶鸟弹撞击复合材料蜂窝夹芯板试验

开展明胶鸟弹撞击复合材料蜂窝夹芯板试验,研究夹芯结构在软体高速冲击下的损伤形式,分析相关因素对结构动态响应结果的影响。通过CT扫描对复合材料蜂窝夹芯板内部进行检测可知,面板出现分层、基体开裂、纤维断裂、凹陷、向胞内屈曲等损伤形式,蜂窝芯出现芯材压溃、与面板脱粘的损伤形式;分析复合材料蜂窝夹芯板后面板的动态变形过程及撞击中心处位移-时间数据可知,复合材料蜂窝夹芯板在撞击过程中出现由全局弯曲变形主导和局部变形主导的两种变形模式;通过对比不同工况下的复合材料蜂窝夹芯板损伤程度可知,复合材料蜂窝夹芯板损伤程度随鸟弹撞击速度的增加而增大;蜂窝芯高度为10 mm的复合材料蜂窝夹芯板较蜂窝芯高度为5 mm的复合材料蜂窝夹芯板的损伤程度大;初始动能较大的球形鸟弹较圆柱形鸟弹对复合材料蜂窝夹芯板造成的冲击损伤程度更大。      

蜂窝金属夹芯板重复冲击动态响应研究

蜂窝金属及其夹芯结构是一种物理功能与结构一体化的新型轻质高强结构,广泛应用于结构轻量化与碰撞冲击防护领域。采用ABAQUS非线性有限元软件建立了蜂窝金属夹芯板(honeycomb sandwich panel,HSP)结构动态冲击数值仿真模型,数值仿真计算结果与文献实验结果吻合较好,验证了数值仿真模型的正确性。在此基础上,开展了重复冲击载荷作用下蜂窝金属夹芯板结构动态响应研究,得到了重复冲击力时程曲线、动态变形时程曲线、冲击力位移曲线以及最终挠度,分析了冲击能量、蜂窝壁厚以及上、下面板厚度分配对蜂窝金属夹芯板结构重复冲击动态响应的影响规律。研究结果表明,重复冲击载荷作用下蜂窝金属夹芯板结构上、下面板弯曲变形以及蜂窝芯层压缩变形逐渐积累,蜂窝芯层薄壁结构逐渐达到密实化,结构抗弯刚度逐渐上升,变形增量逐渐减小,结构整体能量吸收率下降。通过调节蜂窝壁厚和上、下面板厚度分配可以显著调节蜂窝金属夹芯板结构重复冲击动态响应与能量吸收性能。     

Approximate elastic-plastic analysis of the static and impact behaviour of polymer composite sandwich beams

An elastic-plastic beam bending model has been developed to simulate the post-upper skin failure energy absorption behaviour of polymer composite sandwich beams under three-point bending. The beam skins consist of woven and chopped strand glass, while the core is a resin impregnated non-woven polyester material known as Coremat. A polyester resin was used for the construction. The theoretical model consists of a central hinge dominated by a crushing core and tensile elastic strains in the lower skin. Experimental measurements of the non-linear force-deflection characteristics for the beam are compared to the theoretical predictions from the model, and it is shown that the shear crushing of the core has an important effect on the behaviour of the beam. The model shows that the most important material properties are the lower skin tensile failure strain and the core crushing strength. Dynamic effects are included in the model in the form of a strain rate dependence of the core crushing stress and the strain rate dependence of the failure strain in the lower skin. The increase in material strength with strain rate gives rise to an improved energy absorption capacity for the beam under impact loading.