三维机织芳纶／环氧复合材料应变率压缩响应研究

研究三维机织芳纶/环氧复合材料在高应变率下的压缩力学性能.运用分离式霍普金森杆(SHPB)测试不同应变率在复合材料厚度方向的压缩性能,同时对材料在准静态情况的力学性能进行测试,与高应变率下的力学性能比较表明,三维机织芳纶/环氧机织复合材料是应变率敏感材料,随着应变率的增加,压缩刚度和最大应力增加,而相应最大应力的应变则减小.     

Relationship Between Compression Strength and Its Microstructure of 5 Axial-Braided Composite

Compression performance of 5-axial braided composites is observed through compression tests.A mixed model of micro-buckling shear with braided tows web is set up to predict compression stress of braided composite through analyzing three broken modes.Using this mixed model,data from tests indicated that the main parameters effecting the compression properties of braided composite are fiber volume fraction,directional angle,axial-tow volume fraction and diameter of tow.Contributing rate of tows is proposed to describe the compression properties of fibre composites.Optimization geometrical structure of braids can optimize composite properties.     

15%SiC_P/8009铝基复合材料热压缩流变应力行为

采用Gleeble-3500热模拟试验机对15%Si CP/8009铝基复合材料在温度为400~550℃和应变速率为0.001~1 s~(-1)条件下的热变形流变行为进行研究。结果表明:流变应力在开始阶段随应变的增加而增大,出现峰值后逐渐趋于平稳;流变应力随温度的升高而降低,随应变速率的增大而升高,呈现出正应变速率敏感性;流变应力行为可以用双曲正弦模型来描述,其热变形激活能为488.3853 k J/mol,应力指数为7.19022。     

高应变率条件下38CrMoAl钢的动态力学行为及失效模型

38CrMoAl钢是飞机某频繁经受冲击载荷结构的主要材料，为了获得该钢在冲击载荷下的力学行为和失效参数，本文对38CrMoAl钢开展了准静态试验、应变率从650 s^-1至5 500 s^-1的动态力学试验以及应力三轴度试验，对材料的金相组织和断口形貌进行了微观观察分析，最后基于试验结果确定了材料的修正强度模型和失效模型参数。试验结果表明，38CrMoAl钢具有较强的应变率敏感性，材料屈服强度随着应变率的增加具有正应变率强化效应，应变率在10^-3~5 500 s^-1的范围变化时，屈服应力从450 MPa上升到了1 085 MPa，应变率为5 500 s^-1时材料的屈服应力达到了准静态条件下的2.41倍。对材料组织的微观观察分析发现材料主要由呈现颗粒状的回火索氏体组成，材料在高应变速率加载下其塑性发生了下降，断口由韧窝型塑性断口向局部解理断面发生转变，韧窝尺寸也随着应变率的升高而变小。对Johnson-Cook（J-C）强度模型中的应变率强化项进行了修正，使修正后的本构模型可以更有效地描述38CrMoAl钢的动态力学行为，最后结合数值模拟方法确定了材料的J-C失效准则参数。     

三维五向编织复合材料的冲击压缩特性及破坏机制

利用分离式霍普金森压杆(split Hopkinson pressure bar,SHPB)实验系统和高速摄像技术对三维五向碳/环氧编织复合材料的动态压缩特性进行研究。通过对编织角为22.3°的试样分别进行沿纵向和横向方向的冲击压缩实验,得到材料在200~1200 s^-1应变率范围内的应力应变曲线,并结合高速摄像记录的动态压缩过程,对不同应变率下材料在高速变形下的渐进破坏规律进行分析。同时,综合试样的宏观破坏特征和微观断口形貌特征,进一步分析材料的破坏模式及破坏机理。结果表明:随着应变率的增加,材料在纵向和横向均具有一定的应变率强化效应,在横向方向的应变率强化效应更为显著;不同加载方向下材料的渐进破坏过程、应力应变曲线特征以及破坏方式均具有明显差异,且随着应变率的增加而发生改变。     

一种高硅镍铜合金高温热压缩变形的研究

利用Gleeble-1500热模拟材料实验机,对高硅镍铜合金铸态试样分别在温度为T1,T2,T3,T4,应变速率为S1,S2,S3,S4,S5时进行压缩变形.对该合金的高温塑性变形行为和热压缩后的组织演变规律进行了研究.分析了流变应力与应变速率和温度的关系,计算出了应力指数和变形激活能.结果表明,流变应力随应变速率的增加而增加,随温度的升高而减小,并且该合金在高温变形条件下发生动态再结晶.     

循环加载下复合推进剂的能量耗散

在空空导弹的挂载飞行阶段,弹体高频振动导致的固体推进剂温升极大地损害了固体火箭发动机的性能。为深入探究固体推进剂的能量耗散及其影响因素,针对某复合推进剂进行了不同应变幅值下的多频率疲劳测试,并利用非接触式红外辐射装置同步采集了循环加载下推进剂试件的表面温度,讨论了频率、应变幅值两个因素对复合推进剂能量耗散的影响。结果发现,复合推进剂由于自身的黏滞性,在外部激励下产生了剧烈的疲劳生热行为,其能量耗散密度随着加载幅值和频率的增大而提高,能量耗散带来的试件表面温度呈现出先增大后稳定的规律。根据能量耗散和温度场方程,建立了复合推进剂疲劳过程中的温升计算模型,利用有限元仿真对不同加载条件下推进剂的滞后温升进行了较好的预测。     

系列嵌套圆环系统的能量吸收特性

能量吸收结构的性能对航空、航天等领域的人员和结构防护非常重要。针对一种系列嵌套圆环系统的能量吸收特性进行了理论、数值和实验研究。首先建立了考虑应变强化效应的系列嵌套圆环系统受刚性平板横向准静态压缩时的刚塑性理论模型;然后对双环和三环嵌套圆环系统进行了准静态压缩实验及有限元数值模拟,理论预测、数值模拟和实验测得的系列嵌套圆环系统的载荷-挠度曲线吻合很好;最后对将系列嵌套圆环系统应用到航空领域进行了探讨,以应用至航空座椅为例,建立了人体、座椅、能量吸收结构的数学模型,参照美国航空联邦局航空座椅动态实验标准,基于该模型计算得到了人体所受的腰椎负荷,并与不装备能量吸收结构时的腰椎负荷进行了比较,结果表明应用系列嵌套圆环系统可以有效地对人体进行防护。     

Constitutive behavior and microstructural evolution in hot deformed 2297 Al-Li alloy

The microstructural evolution mechanism and constitutive behavior of 2297 Al-Li alloy were studied via thermal compression test with the constant strain rates of 0.001–1 s⁻¹ and the deformation temperatures ranging from 623 to 773 K. To verify the predictable ability of diverse constitutive models under different stress states, the hot compression experiments with stress triaxiality varying from −0.33 to 0.46 were conducted. The microstructures of the deformed specimens under diverse deformation conditions are probed to reveal the mechanism of hot deformation behavior. The experimental results indicate that the work-hardening and dynamic softening are competitive during the hot compression process, and the dynamic softening is more obvious under low deformation temperature and high strain rate. The microstructural analysis manifests that the dynamic recovery gets predominant at high deformation temperature to produce fine grains. Meanwhile, the dynamic recrystallization becomes more dominant as the strain rate decreases, which is sensitive to the stress triaxiality. In addition, both the modified Johnson-Cook model and strain-compensated Arrhenius-type function are suitable for describing the flow behavior of 2297 alloy, while the latter reveals a more accurate prediction. However, the predictability of the two kinds of models is worsened with the transformation of stress triaxiality, and the validity of the Arrhenius-type model is restricted by high stress triaxiality.     

Damage characteristics and constitutive modeling of the 2D C/Si C composite: Part I – Experiment and analysis

This paper reports an experimental investigation on the macroscopic mechanical behaviors and damage mechanisms of the plain-woven(2D) C/Si C composite under in-plane on- and offaxis loading conditions. Specimens with 15, 30, and 45 off-axis angles were prepared and tested under monotonic and incremental cyclic tension and compression loads. The obtained results were compared with those of uniaxial tension, compression, and shear specimens. The relationships between the damage modes and the stress state were analyzed based on scanning electronic microscopy(SEM) observations and acoustic emission(AE) data. The test results reveal the remarkable axial anisotropy and unilateral behavior of the material. The off-axis tension test results show that the material is fiber-dominant and the evolution rate of damage and inelastic strain is accelerated under the corresponding combined biaxial tension and shear loads. Due to the damage impediment effect of compression stress, compression specimens show higher mechanical properties and lower damage evolution rates than tension specimens with the same off-axis angle. Under cyclic tension–compression loadings, both on-axis and off-axis specimens exhibit progressive damage deactivation behaviors in the compression range, but with different deactivation rates.     

复合材料波纹梁吸能能力的数值模拟

运用MSC/DYTRAN有限元软件,对3组不同尺寸的碳纤维—环氧树脂圆弧形波纹梁的破坏过程、峰值载荷和能量吸收能力进行了数值模拟研究。由于MSC/DYTRAN有限元软件不能直接用于复合材料的吸能分析,分析时采用了等效的方法。比较波纹梁的计算结果与准静态轴向压溃试验的结果可见,两者较为一致。在此基础上分析了波纹梁的耐撞性,得到波纹梁在碰撞过程中的吸能数据,进一步研究了不同薄弱环节设置对波纹梁峰值载荷的影响。说明采用了等效的方法并运用该有限元软件来模拟复合材料结构的吸能能力是可行的。     

Analysis of composite laminates with intra- and interlaminar damage

Failure process of composite laminate under quasi-static or fatigue loading involves sequential accumulation of intra- and interlaminar damage. Matrix cracking parallel to the fibres in the off-axis plies is the first intralaminar damage mode observed. These cracks are either arrested at the interface or cause interlaminar damage (delamination) due to high interlaminar stresses at the ply interface. This paper summarises recent theoretical modelling developed by the authors on stiffness property degradation and mechanical behaviour of general symmetric laminates with off-axis ply cracks and crack-induced delaminations. Closed-form analytical expressions are derived for Mode I, Mode II and the total strain energy release rates associated with these damage modes. Dependence of strain energy release rates on crack density, delamination area and ply orientation angle in balanced and unbalanced symmetric laminates is examined and discussed. Also, stiffness degradation due to various types of damage is predicted and analysed.     

纤维缠绕角度对CFRP-Al混合圆管横向受载性能影响

基于准静态横向弯曲试验对缠绕工艺下制备的CFRP/Al混合圆管进行抗弯性能和吸能特性研究,分析了混合圆管的破坏模式,基于不同纤维缠绕角度的碳纤维复合材料-铝合金混合圆管三点弯曲试验结果,通过有限元仿真方法研究了内层纤维缠绕角度对其横向抗弯与吸能特性的影响。试验结果表明,CFRP-Al混合圆管横向载荷下的失效形式、损伤模式与纯铝管基本保持一致,但受纤维缠绕角度的影响失效形貌略有差异。纤维缠绕角度越小,CFRP-Al混合圆管的抗弯性能和吸能性越好,同时压溃效率(CFE)明显降低。基于验证的有限元模型,研究不同角度纤维缠绕内层对于表层纤维层的应力传递影响,小角度缠绕内层对于管件的轴向拉伸变形抑制增加了管件整体峰值载荷与吸能作用,大角度缠绕内层对于管件环向刚度的提升增加了整体压溃效率。依此分析可为合理设计CFRP-Al混合管提供有效依据。     

Assessment of two quasi-static approaches to mimic repeated impact response and damage behaviour of CFRP laminates

Full impact damage tolerance assessment requires the ability to properly mimic the repeated impact response and damage behaviour of composite materials using quasi-static approximations. To this aim, this paper reports an experimental investigation evaluating two quasi-static methods for mimicking repeated impact response and damage behaviour of Carbon Fibre Reinforced Polymer (CFRP) composite laminates. In this study, an 8.45-J single impact was repeated 225 times and mimicked with 225 times 6.51-J quasi-static (energy equivalent) indentations and with 225 quasi-static (force equivalent) indentations following the recorded impact peak force variation. Results show that the loading rate and the inertial effect are the two major factors affecting the responses of the composite laminates under out-of-plane concentrated loading. Both the energy- and force-equivalent quasi-static indentations failed to reproduce the impact responses greatly associated with high loading rate and inertial effect. The force-equivalent quasi-static indentations were performed in a semi-automatic way and induced damage states more similar to those of the repeated impacts than those of the energy-equivalent quasi-static indentations, whereas the latter can be better automated and has better reproducibility compared to that of the repeated impact responses, as it is less dependent on high loading rate and inertial effect.     

3种铝合金材料动态性能及其温度相关性对比研究

 对3种铝合金2024-T351、7050-T7451和LY12-CZ进行了温度在77～573 K的静、动态压缩（应变率10^-3～6 000/s）和拉伸（应变率10^-3～3 000/s）试验,分别得到了3种铝合金材料的应力 应变关系和失效应变。对比研究结果表明,随温度升高3种材料的塑性流动应力降低,应变率敏感性增加。最后基于Johnson-Cook模型,拟合了用以预测铝合金材料塑性流动应力的模型参数,其预测结果与试验结果吻合较好。     

原位合成TiB_2/6351复合材料热压缩变形特性

采用Gleeble-1500D热模拟试验机对原位合成TiB2(质量分数,8%)/6351复合材料在不同变形温度和不同应变速率条件下的热变形特性进行了研究,利用透射电镜(TEM)和光学显微镜分析了压缩后试样的微观组织.结果表明, 材料的流变应力随变形温度的升高而降低,随应变速率的提高而增大;材料的流变行为主要表现为加工硬化、动态回复和动态再结晶;相应的显微组织特征为:位错网络、混乱的位错团和胞状结构,亚晶及等轴晶.在应变速率和变形温度均较低时,增强体颗粒周围的基体中形成高密度位错区,但随变形温度的升高而减少;在应变速率较高时,增强体颗粒和基体的界面处开裂甚至增强体颗粒本身发生破碎.     

SiC_P/Al-Cu复合材料动态再结晶行为及临界条件

利用Gleeble-1500D热模拟试验机对40%SiC_P/Al-Cu复合材料进行压缩实验,研究其在温度为350~500℃、应变速率为0.01~10 s~(-1)条件下的高温塑性变形行为。由实验得出变形过程中的应力-应变曲线,采用加工硬化率处理方法对应力-应变数据进行处理,结合lnθ-ε曲线的拐点和(-α(lnθ)/αε)-ε曲线最小值的判据,研究该复合材料动态再结晶临界条件。结果表明:40%SiC_P/Al-Cu复合材料的应力-应变曲线主要以动态再结晶软化机制为特征,峰值应力(σ_p)随变形温度的降低或应变速率的升高而增加;该材料的lnθ-ε曲线出现拐点,(-α(lnθ)/αε)-ε曲线出现最小值;临界应变(ε_c)随变形温度的升高与应变速率的降低而减小,且临界应变与峰值应变(εp)之间具有相关性,即ε_c=0.528εp;临界应变与Zener-Hollomon参数(Z)之间的函数关系为ε_c=4.58×10~(-3)Z~(0.09)。透射电镜观察显示应变为0.06时(变形温度为400℃,应变速率为10 s~(-1))已经发生动态再结晶,应变为0.2时,动态再结晶晶粒充分长大。     

编织结构复合材料力学性能分析

以分析编织结构复合材料的力学性能和修正的经典层合板理论为基础,首先对三维编织织物结构进行分析,考虑厚度方向的效应,采用三维应力-应变分析,预报编织结构复合材料的有效弹性模量;同时,进行了编织结构复合材料的力学性能实验,理论预报和试验结果符合得较好。     

三维五向圆型编织复合材料细观分析及弹性性能预测

 基于三维圆型编织的主要工艺，系统研究了三维五向圆型编织的纱线交织结构，建立了内部单胞和表面单胞模型。推导了单胞的几何特性、编织工艺参数之间的数学关系。基于此模型，采用改进的刚度平均化方法，计算了三维圆型编织复合材料的弹性性能参数，并与实验的结果进行了对比，吻合较好。分析了编织角和纤维体积含量对弹性性能的影响，结果表明，五向圆型编织复合材料保持了四向圆型编织复合材料良好的力学性能，同时由于轴纱的加入，使得轴向的力学性能得以提高。     

定应力幅值往复拉伸过程中推进剂的损伤扩展

对复合固体推进剂进行不同应力幅值条件下的纯复拉仲试验,找出加载过程中往复拉伸曲线、特征应变以及耗散能的变化规律,以分析定应力幅值往复拉伸过程中推进剂的损伤特性.结果表明:往复拉伸过程中耗散能的变化反映了推进剂在不同拉伸应变下损伤形式不同,往复过程中的耗散能主要由基体的粘性耗散与破坏提供,应力幅值与往复拉伸寿命的对数之间...