民用飞机平尾前缘鸟撞数值分析及试验验证

用电子液压拉伸试验机与分离式霍普金森拉杆(SHTB)装置进行2024-T3、7075-T6铝合金材料不同应变率的拉伸试验,拟合出反映两种材料应变率强化效应的Johnson-Cook本构方程。通过SHTB动态拉伸试验获得7种铆钉的极限拉伸、剪切载荷。基于瞬态动力学软件PAM-CRASH,利用元件级材料试验获得铝合金本构方程及连接件动态失效参数,耦合光滑粒子流体动力学(SPH)方法与有限元方法建立民机平尾前缘鸟撞数值模型进行试验并验证数值计算结果。计算、试验结果的一致性表明,所建鸟撞数值计算模型合理、可靠。整个积木式试验、分析流程可为民机结构抗鸟撞设计提供有力参考。     

7075-T6铝合金动态力学试验及本构模型研究

分别采用电子万能试验机、高速液压伺服试验机和分离式霍普金森拉杆(SHTB)装置进行了7075-T6铝合金材料在室温下的准静态、中应变率和高应变率动态力学性能试验。获得了该材料不同应变率下的应力-应变曲线,结果显示:7075-T6铝合金具有明显的应变率强化效应;随着应变率的提高,试件断口处颈缩现象越发明显。拟合出了能够反映材料应变硬化效应、应变率强化效应的Johnson-Cook本构方程,对方程中的应变率强化项进行了修正,使拟合结果与试验结果吻合得更好。     

2024-T42铝合金低中应变率力学性能及本构关系

为研究2024-T42铝合金的低中应变率力学性能和本构关系,采用电子万能实验机和高速液压伺服材料实验机,进行常温下2024-T42铝合金准静态、低中应变率拉伸实验,得到材料在不同应变率下的应力-应变曲线。考虑颈缩对真实应力-真实应变的影响,采用仿真反演方法对颈缩后的真实应力-真实应变曲线进行修正,并基于Johnson-Cook本构模型进行拟合。结果表明:2024-T42铝合金在低中应变率范围的率敏感性较弱;但具有较强的应变硬化效应;基于仿真分析的反演修正方法能较好重构材料颈缩点后的真实应力-真实应变曲线;并通过铝管压溃实验和仿真分析,验证了反演修正方法的合理性和所获本构模型参数的准确性。     

2A16铝合金中应变率力学性能研究

为研究2A16铝合金的中应变率力学性能及热处理状态对其应变率敏感性的影响,利用电子万能试验机和高速液压伺服试验机对其(O状态和T4状态)进行常温下准静态和中应变率力学性能试验,得到不同应变率下的应力应变曲线,并基于修正的Johnson-Cook本构模型对其进行拟合。结果表明:在应变率10~(-4)~10~2s~(-1)内,热处理状态对2A16铝合金的应变率敏感性有较大影响,其中2A16-O状态铝合金的应变率敏感性较强,而2A16-T4状态铝合金的应变率敏感性较弱,但两种材料均具有较强的应变硬化效应;此外,修正Johnson-Cook本构模型的拟合结果与试验结果吻合很好,能够很好表征材料的动态力学行为。     

基于损伤模型的2024-O-T42搭接件动态拉伸失效分析

针对高锁螺栓单搭接件所采用的2024-O-T42铝合金,设计狗骨试验件进行准静态与动态拉伸试验,设计六种不同的缺口试验件进行准静态拉伸试验。通过开展拉伸失效仿真,对比Hartley-Srinivasan与Johnson-Cook两种本构模型,以及最大塑性应变失效准则、Johnson-Cook失效模型与GISSMO损伤模型三种失效模型。结果表明,在试验的100 s^-1应变率范围内,2024-O-T42铝合金材料流动应力应变率效应不明显,其最大相差约为5%;在不考虑应变率及温度的情况下,Hartley-Srinivasan本构模型比Johnson-Cook本构模型更能准确表征材料塑性段的力学行为;采用Hartley-Srinivasan本构模型和GISSMO损伤模型,高锁螺栓单搭接件在1 m/s、3 m/s、5 m/s拉伸速度下的仿真结果与试验结果吻合更好,且仿真获得的失效位移相对试验失效位移平均值分别偏大4.7%、偏大4.3%和偏小7.4%。     

7050-T7351铝合金力学性能测试及本构模型研究

为分析7050-T7351铝合金的应力流动行为和塑性变形情况，对该铝合金进行了不同应变率和温度下的力学性能测试，通过测试结果标定了Johnson-Cook(JC)、Hartley-Srinivasan(HS)和Swift本构模型。利用ABAQUS有限元软件建立有限元模型进行仿真分析，根据计算结果对JC本构模型给予修正，最终得到Modified Johnson-Cook(MJC)本构模型。将JC的应变率和温度项乘子与HS和Swift模型耦合，然后进行Taylor杆撞击测试以及相应的有限元计算，验证三种本构模型的有效性。结果表明：JC模型高估了7050-T7351铝合金的应力流动行为，而MJC本构模型预测的结果与试验有很好的一致性，HS和Swift模型均能较好地反映该材料在准静态下的应力流动行为。此外，MJC模型可以很好地预测Taylor杆的塑性变形，而将JC的应变率和温度项乘子与HS和Swift模型耦合后的修正模型对Taylor杆变形情况的预测精度相对较差。     

TC4钛合金动态力学性能及本构模型研究

为研究TC4钛合金的动态力学性能及本构模型,利用电子万能试验机、高速液压伺服试验机和分离式Hopkinson压杆(SHPB)装置,对其进行常温下准静态、中应变率和高应变率动态力学性能试验,得到不同应变率下的应力应变曲线,拟合得到Johnson-Cook本构模型,并分析材料中应变率力学特性对本构模型参量的影响。结果表明:TC4钛合金在应变率10~(-4)~10~3s~(-1)范围内具有明显的应变率强化效应和一定的应变硬化效应,且应变率强化效应随应变的增大而减小,应变硬化效应随应变率的增大而减小;考虑材料中应变率力学特性可提高本构模型参量的准确性;通过数值方法和试验方法研究TC4钛合金平板撞击和高速拉伸过程的动态响应,两者结果具有很好的一致性,证明所得本构模型的准确性。     

TC4钛合金力学性能测试及其本构关系研究

为合理描述TC4钛合金材料的应力流动行为,分别利用万能材料试验机、霍普金森压杆设备,进行常温和高温准静态拉伸试验、动态压缩试验。通过试验得到了材料在不同应变率、温度下的工程应力-应变曲线,发现TC4钛合金材料应变硬化效应较弱,但应变率敏感性和温度软化效应较强。其次,基于试验结果,修正Johnson-Cook (J-C)本构模型和断裂准则获得MJC模型,并结合数值模拟标定J-C与MJC模型参数。最后,为校验模型和参数的有效性,采用ABAQUS/Explicit有限元软件建立卵形头弹体撞击靶体的模型,分别将J-C和MJC模型及参数嵌入到有限元程序中,进行数值仿真计算,对比撞击试验与数值模拟计算结果。研究表明,MJC模型预测的弹体弹道极限与靶体失效模式更接近于试验。     

Q235B钢Johnson-Cook模型参数的确定

使用万能材料试验机、扭转试验机和霍普金森拉杆装置研究了Q235B钢在常温~950℃的准静态、动态力学性能,获得了Q235B强度与等效塑性应变,应变率和温度的关系以及延性与应力三轴度,应变率和温度的关系。基于实验结果,修改了Johnson-Cook(J-C)强度模型中的应变强化项以及Johnson-Cook失效模型中的温度软化项,并结合数值仿真标定了相关模型参数。最后通过Taylor撞击试验验证了模型参数的有效性。     

三种建筑钢筋材料高应变率下拉伸力学性能研究

钢筋混凝土结构除承受静载荷外,在恐怖袭击、燃气管道爆炸等特殊情况下还会承受动态载荷的作用,因此,研究其组成材料之一的钢筋材料在动态载荷作用下的力学性能,对于研究钢筋混凝土结构整体在动态载荷作用下的力学响应有重要意义。该文首先利用旋转盘冲击拉伸试验系统对3种常用建筑钢筋材料(HPB235、HRB335和HRB400)在400 s-1~2000 s-1应变率范围内的动态拉伸力学性能进行试验研究,然后根据试验数据,分析应变率对屈服强度的影响规律,并对常用的Johnson-Cook本构模型进行修正,以获得可以更好描述这3种钢筋材料动态拉伸应力-应变关系的本构模型及相关的材料参数。研究结果表明:3种钢筋材料的屈服应力均随应变率的增大而增大,而静载屈服应力越低的钢筋对应变率越敏感;修正后的Johnson-Cook本构模型能较好地描述3种钢筋材料的动态拉伸应力-应变关系。     

6013-T4铝合金不同温度下的动态流变应力及组织演变

采用分离式霍普金森(SHPB)压杆装置进行6013-T4铝合金动态压缩试验,获得温度为25℃、100℃、200℃、300℃、400℃,应变速率为1 000s~(-1)、2 000s~(-1)、3 000s~(-1)、4 000s~(-1)、5 000s~(-1)条件下材料的真应力-真应变曲线,并通过透射电子显微镜(TEM)观测了6013-T4铝合金在不同变形条件下的组织演变。结果表明:6013铝合金有明显的温度敏感性,但是对应变速率的敏感性较弱。应变速率和温度对6013铝合金微观组织的影响显著,位错密度随应变速率的升高而增大,随温度的升高而减小。基于实验数据,求得了6013铝合金Johnson-Cook模型的本构参数并建立其本构模型。与实验结果进行对比,结果表明,所建立的本构模型能够很好地预测6013铝合金的流变应力。     

Constitutive descriptions for hot compressed 2124-T851 aluminum alloy over a wide range of temperature and strain rate

The compressive deformation behaviors of 2124-T851 aluminum alloy were investigated over a wide range of temperature and strain rate on Gleeble-1500 thermo-simulation machine. The results show that the true stress–true strain curves exhibit a peak stress at a very small strain, after which the flow stresses decrease until high strains, showing a dynamic flow softening. The measured flow stress was modified by friction correction, and the corrected flow stresses are lower than the measured ones, which nicely reflect negative effects of the interfacial friction on the flow stress. A revised model is proposed to describe the relationships of the flow stress, strain rate and temperature of 2124-T851 aluminum alloy at elevated temperatures. The stress–strain values of 2124-T851 aluminum alloy predicted by the proposed model well agree with experimental results, which confirmed that the revised deformation constitutive equation gives an accurate and precise estimate for the flow stress of 2124-T851 aluminum alloy.     

Fracture of laminates combining 2024-T3 and 7075-T6 aluminum alloys

Crack growth resistance curves have been determined for crack-divider laminates in which layers of 2024-T3 aluminum alloy are adhesively bonded to layers of 7075-T6 alloy. Results are compared with the fracture resistance of laminates consisting wholly of each material, the layer thickness being the same (1.54 mm) in all cases. The initial portions of the resistance curves are similar for both alloys; however those for 2024-T3 have steeper slopes at longer effective crack lengths. As a result, laminates consisting entirely of 2024-T3 alloy exhibit greater amounts of stable crack extension and higher toughnesses at instability. This is attributed in part to the greater strain hardening rate in 2024-T3 material. Laminates combining 2024-T3 and 7075-T6 layers are intermediate between those consisting entirely of one or the other alloy.     

Dynamic Tensile Fracture Behaviours of Selected Aluminum Alloys under Various Loading Conditions

Experiments investigating dynamic tensile fracture were performed on the extruded rods of 2024‐T4 and 7075‐T6 aluminum alloys under varying loading conditions. The initial yield stress and fracture strain of 7075‐T6 alloy obtained in spilt Hopkinson tension bar tests are higher than that of 2024‐T4 alloy. But the initiation fracture toughness and spall strength of 2024‐T4 alloy are higher than those of 7075‐T6 alloy in three‐point bending and plate impact experiments, which indicates that 2024‐T4 alloy has better crack initiation tolerance and stronger spall failure resistance. Based on metallurgical investigations by using optical and scanning electron microscopes, it is revealed that the microstructure has a profound effect on the dynamic tensile fracture mechanism of each aluminum alloy. The 2024‐T4 alloy is relatively brittle due to voids or cracks nucleated at many coherent CuMgAl₂ precipitate phases in the grain interiors, and the fracture mode is predominantly transgranular. The 7075‐T6 alloy exhibits relatively ductile fracture because voids or cracks growth is partly intergranular along the grain boundaries and partly transgranular by void formation around coarse intermetallic particles. The obvious differences of damage distribution and void coalescence mechanisms for 2024‐T4 and 7075‐T6 alloys under plate impact are also discussed.     

2219铝合金动态力学性能及其本构关系

针对2219铝合金在高温、高应变率加工条件下的变形特征以及流动应力变化规律,利用分离式Hopkinson压杆设备对该合金进行了室温以及高温动态压缩力学性能研究,并利用电子万能试验机对其进行准静态压缩力学性能测试,得到了2219铝合金在不同应变率和温度下的真实应力-应变曲线。结果表明:2219铝合金对温度有较高的敏感性,其流动应力随着温度的升高而降低;当应变率在1000~3000s-1范围内时,材料的流动应力变化并不明显;基于Johnson-Cook模型拟合出的模型参数,能较好地预测实验中材料的流动应力。     

Approximate determination of a strain-controlled fatigue life curve for aluminum alloy sheets for aircraft structures

This paper deals with selected methods of approximate determination of a strain-controlled fatigue life curve for aluminum alloy sheets used in aircraft structures. Authors based their analysis of those methods on the results of own research of 2024-T3 alloy and its Russian equivalent D16CzATW. The approximate strain-fatigue life curves were compared with the experimental curves. The influence of inconsistencies between those curves on the calculation results was analyzed on computational examples by means of the Palmgren–Miner’s rule.     

Strain rate effects for aluminum and magnesium alloys in finite element simulations of steering wheel armature impact tests

This paper addresses the strain rate effects for aluminum and magnesium steering wheel armatures when they are subjected to dynamic impact tests. Two geometrically different steering wheel armatures, a three spoke proprietary aluminum alloy armature and a four spoke magnesium alloy (AM50A) armature, underwent experimental impact testing. The testing conditions for each armature were different; testing with the aluminum alloy armature involved impacts with a deformable chestform and the magnesium armature experienced impact tests with a rigid plate. Finite element models of all testing apparatuses were developed for both testing conditions and numerical simulations were conducted based on the experimental method employed. Strain rate effects for the aluminum alloy were considered using the Cowper–Symonds constitutive relation and a Johnson–Cook material law was utilized for the magnesium alloy. Simulations were conducted with and without strain rate effects considered. The comparison between the experimental and numerical methods illustrate that there is only a minor change in the numerical testing results with the inclusion of strain rate effects, however, a better correlation between experimental and numerical methods occurs.     

光学玻璃材料动态冲击试验与鸟撞研究

针对多光谱硫化锌(zinc sulfide,ZnS)光学玻璃材料用于飞行器时的鸟撞问题进行了研究。对多光谱硫化锌玻璃进行了中高应变率下的压缩试验获得其材料属性。鸟体采用光滑粒子流体动力学(smoothed particle hydrodynamics,SPH)方法建模,引入Gruneisen状态方程定义鸟体本构模型。对建立的鸟体模型进行撞击铝板的仿真并进行试验验证,验证结果表明建立的鸟体模型具有较高的精度,可以用于其它碰撞情景下的仿真。建立鸟撞玻璃平板的模型对多光谱硫化锌玻璃的耐鸟撞性能进行预测分析,仿真结果表明ZnS玻璃撞击部位和边缘约束的地方容易达到极限应变并发生失效;另外,随着鸟体撞击角度的减小玻璃表面的接触力峰值也逐渐减小。该研究所得结果可以为鸟体SPH方法的数值模拟以及多光谱硫化锌玻璃在飞行器上的应用提供参考。     

激光冲击2024 铝合金诱导动态应力应变实验研究

为了研究激光冲击波动态加载过程中金属材料的动态应力应变特性,采用高功率激光器单次冲击2024 铝合金薄板,利