碳纤维复合材料板热弯曲试验研究

为解决传统复合材料件成形效率低、制造成本高等问题,提出一种采用加热模具对复合材料板直接进行热冲压的复合材料成形新方法。该方法使用局部加热模具将复合材料板中需发生变形的区域进行局部加热,并借助复合材料加热到一定温度下软化的特点,使其随模具的运动逐步成形,并在模具作用下固化。对复合材料板V形件的热弯曲成形进行了试验研究,分析了成形温度、加载速度和开模温度对成形后工件精度的影响规律。试验结果表明：碳纤维复合材料板热弯曲性能良好,成形力小;通过测量试件室温回复角度发现,复合材料的热弯曲成形回复角度随着成形温度的降低而增大,随着开模温度的降低而减小。     

航天用超大规格GH4169高温合金螺栓热镦工艺

为研究一种航天用超大规格GH4169高温合金螺栓热镦工艺，利用热模拟试验机对材料进行了高温压缩实验，分析了不同变形温度和应变速率对材料变形抗力的影响，并对GH4169高温合金螺栓的热镦成形过程进行了数值模拟，分析了成形过程中等效应力场分布、损伤值分布、金属流线分布、摩擦因数对成形载荷的影响，最后进行了工艺实验。研究结果表明：应变速率一定时，随着变形温度的升高，材料的变形抗力逐渐降低；变形温度一定时，随应变速率的增大，材料的变形抗力逐渐增大；摩擦因数μ=0.3时成形过程中的最大载荷为3.56×10⁶ N,摩擦因数μ=0.5时成形过程中的最大载荷为4.11×10⁶ N。工艺实验得到的GH4169高温合金螺栓锻件充填饱满，尺寸符合要求，未发现锻造缺陷，符合航天领域使用需求。     

树脂板多点热成形数值模拟与实验研究

介绍了树脂板多点热成形的原理,选择具有良好综合性能的聚甲基丙烯酸甲酯(PMMA)和聚碳酸酯(PC)为研究对象,测试了其玻璃态转变温度。建立了树脂板多点热成形有限元模型,得到了球形面和鞍面件多点热成形的数值模拟结果,结果表明多点热成形技术可以实现PMMA、PC等树脂板三维曲面件的高精度成形。进行了PMMA板球面件和PC板鞍面件多点热成形实验,结果表明实验件的轮廓形状较好、壁厚分布较均匀,验证了树脂板多点热成形技术的可行性和实用性。对树脂板多点热成形实验结果和数值模拟结果进行对比分析,结果表明,在合理的偏差及测量误差范围内,实验结果与数值模拟结果吻合较好,验证了树脂板多点热成形数值模拟的正确性。     

带肋板齿轮坯热精锻成形工艺方案设计

提出带肋板齿轮坯开式模锻和闭式模锻两种热精锻成形工艺方案,借助有限元分析软件模拟了两种工艺方案下齿轮坯的成形过程,分析比较了两种方案中的金属流动规律。仿真结果显示:采用开式模锻,肋板充填不饱满,成形载荷大;采用闭式模锻,零件成形质量较高,成形载荷较小。导致开式模锻成形载荷大并且肋板充填不饱满的原因为:成形中后期充填肋板的金属流动阻力增加,金属径向流动加剧并形成较大飞边,随着上模下压,飞边变形消耗滑块能量,并增加了与模具的接触面积,导致成形力急剧增加而模具型腔充填不饱满。工艺实验表明,其结果与数值模拟相吻合。     

GH2674合金大型涡轮盘锻造成形技术

通过热模拟压缩试验研究了变形温度和变形速率对GH2674合金组织和性能影响,试验温度范围为950～1200℃,应变速率为0.01、0.05、0.1和1.0s-1,变形量为65%;同时采用有限元法模拟分析了GH2674合金大型涡轮盘的成形过程,创造性的提出局部成形的方法,并对局部成形过程中应变场及载荷分布情况进行分析,从而确定了GH2674合金大型盘件合适的热成形工艺,并生产出了符合标准要求的直径达φ2200mm的GH2674合金大型涡轮盘锻件。     

高固相率SiCP/AZ61复合材料触变成形的数值模拟

采用等温热处理法制备SiCP/AZ61复合材料半固态坯料,在自制实验装置上进行触变成形实验.采用所建立的高固相率SiCP/AZ61复合材料本构模型,对触变成形过程进行了数值模拟,得到了不同成形温度下的应力、应变和温度场分布.结果表明,与成形温度为530℃相比,560℃时复合材料触变成形具有变形抗力小、应变与温度场分布均匀的特点.通过实验和模拟结果对比可知(成形温度为560℃),两者吻合较好,所获结果可指导高固相率镁基复合材料触变成形工艺实践.     

温度和压边力对高强度硼钢热冲压成形板厚的影响

针对高强度硼钢板热冲压成形过程中厚度分布不均匀的问题,对它的成形过程进行了数值模拟,结合实验研究了初始成形温度和压边力对热冲压件板料厚度的影响规律。结果表明:初始成形温度850℃、压边力70MPa时,材料成形性能较好。在该工艺条件下获得了合格制件,验证了模拟结果的可靠性。     

2A12硬铝合金板热拉深成形极限图研究

通过自主设计的热拉深成形专用模具,进行了在350~450℃范围内的2A12硬铝合金极限应变实验,并获得了其在该温度范围内的成形极限图,进而分析了在热拉深成形过程中温度对2A12硬铝合金成形极限的影响规律。基于MSC.MARC软件,分别应用最大载荷判断法、应变路径法以及二者相结合的3种失稳准则,对板材热拉深成形极限进行数值模拟分析。通过将数值模拟结果和实验结果进行对比,发现基于二者相结合的方法与实验结果吻合较好。并且基于不同的温度建立了2A12硬铝合金的热拉深成形极限的预测模型,为2A12硬铝合金在不同温度下进行构件实验奠定了理论基础。     

网孔板渐进成形的性能研究

基于实验和数值模拟,对网孔板的成形极限角和变形机理进行了初步研究。通过改变锥台形件模型的成形角,应用逼近法测得了孔距为5,8和11 mm网孔板的成形极限角。采用相同的模型对各网孔板进行成形,发现网孔由圆形变为近似椭圆形,且椭圆的尺寸随着孔距增加而增加。为分析网孔距离对板料厚度和应变分布的影响,采用ABAQUS/explicit对网孔板渐进成形过程进行了数值模拟。模拟结果表明椭圆孔短轴两侧的板料变形剧烈、厚度最薄,其变形方式为拉伸变形。而远离网孔的板料变形较小、厚度较大,其变形方式为近似剪切变形。通过对比实验验证了数值模拟结果的准确性,二者板厚的相对误差低于5%。     

高强度硼钢22MnB5的热变形方程及其模拟应用

利用Gleeble-3500热模拟试验机,在温度为700℃～950℃、应变速率为0.01/s～0.4/s的条件下,对高强度硼钢22MnB5的热变形行为进行研究。结果表明,随着变形温度的升高,硼钢的延伸率升高,变形抗力降低;随着应变速率的提高,硼钢22MnB5的变形抗力和延伸率增大。根据高温拉伸实验得出的数据,构建硼钢22MnB5的稳态流变应力模型和热变形方程,并将试验结果和构建的本构方程输入ABAQUS软件进行U型件热弯曲成形的回弹模拟,数值模拟结果与实验结果吻合较好,验证了模型的可靠性和正确性,为成形所需的最大载荷及设备选择提供依据。     

Simulation and experimental study on thermal deep drawing of carbon fiber woven composites

Carbon fiber woven composites are composed of carbon fiber woven and resin matrix. To reduce the manufacture cost, thermal stamping, a new forming technology, was proposed and investigated to fabricate composite part. The mechanical properties of carbon fiber have great influence on the deformation of carbon fiber composites. In this study, shear angle–displacement curves and shear load–shear angle curves were obtained from picture frame test. Thermal deep drawing experiments and simulation were conducted, and the shear load–displacement curves under different forming temperatures and shear angle–displacement curves were obtained. The results show the compression and shear between fiber bundles are the main deformation mechanism of carbon fiber woven composite. The maximum shear angle for the composites in this study is 33°. In the drawing process, the forming temperature affects the drawing force, which drops rapidly with the increasing temperature. The suitable forming temperature in deep drawing of the carbon fiber woven composite is approximately 170 °C.     

Bending mechanical property and failure mechanisms of woven carbon fiber-reinforced aluminum alloy composite

Copper-coated woven carbon fiber-reinforced aluminum alloy composite was prepared by spark plasma sintering (SPS). Microstructure, three-point bending mechanical property, and the failure mechanisms of the composite were investigated. Microstructure observation shows that the carbon fibers bond compactly with matrix alloy. Compared with the matrix aluminum alloy, the bending strength, ductility, fracture energy, and cracking resistance of the composite are evidently improved. Microstructure analyses reveal that the high specific strength of carbon fibers and transfer of stress from matrix alloy to carbon fibers are responsible for the increase of the composite bending strength. The expanding of cracks is restrained, and cracking resistance of the composite is improved by adding woven carbon fiber. Attributed to the carbon fibers’ debonding, cracks deflection, and multipath propagation mechanisms, the fracture energy of the composite increases.     

基于响应曲面法的波形弹簧片冲压工艺参数优化

以汽车离合器波形弹簧片作为分析对象,利用响应曲面法对冲压成形工艺参数进行优化。通过中心设计组合法及弯曲成形模具得出板料成形高度的响应值,建立了工艺参数与成形高度之间的二阶响应面模型,研究得知工艺参数对板料成形高度交互式影响的顺序依次为:弯曲半径与冲压速度、模具间隙与冲压速度、弯曲半径与模具间隙。将模具间隙、弯曲半径以及冲压速度作为设计变量,以板料成形高度作为优化目标,结合Design Expert软件对响应曲面模型进行优化,通过分析得出优化的冲压工艺参数:弯曲半径为22.13 mm,模具间隙为1.01t mm,冲压速度为2699.47 mm·s-1,成形高度的响应值为1.782 mm,经过工艺参数的修正,成形高度的试验值为1.72 mm。然而相比于正交试验得出的成形高度优化值1.65 mm,响应曲面法在波形弹簧片冲压成形工艺参数的优化中更具优越性。     

Rapid fabrication of C/C/SiC composite by PIP of HMDS

The C/C/SiC composite was fabricated within several days by the method of precursor impregnation and pyrolysis (PIP) using hexamethyldisilazane (HMDS) as the precursor. The carbon fiber plates, woven and punctured with two-dimensional orthogonal continuous carbon bundle and short carbon fiber, were used as the reinforced preforms. The characters of the C/C/SiC composite were analyzed using XRD, EDS and SEM, and three-point-bending test. The results indicated that pyrolyzed substance of the precursor contained excessive carbon, followed by silicon, and a small amount of nitrogen. There were micro-cracks on the massive matrix. The phase composition was difficult to distinguish, primarily considered as the Si–C–N composite. The structure of C/C/SiC was dense and homogeneous with some pores whose sizes were less than 5 μm between fibers and less than 100 μm between the carbon fiber bundles, respectively.

Fiber pull-out was observed on the bending fracture surface. The stress–strain curve of both at room temperature and 1300 °C appeared ascending zigzag. Flexural strength was 150 MPa at 1300 °C, higher than 121 MPa at room temperature.     

Processing and properties of C/Si–B–C–N fiber–reinforced ceramic matrix composites prepared by precursor impregnation and pyrolysis

The fabrication of C/Si–B–C–N fiber–reinforced ceramic matrix composites (FRCs) is reported. The processing basically involves three individual steps: (i) vacuum-assisted infiltration of a liquid two-component Si–B–C–N precursor into stacked woven carbon fiber fabrics, (ii) stepwise thermal cross-linking and (iii) thermal transformation of the polymer matrix composite into a ceramic matrix composite. Repeated polymer infiltration/pyrolysis cycles resulted in FRCs with 89% relative density. The average bending strength of the FRCs was 255 MPa and considerable fiber pull-out was observed throughout the fractured surfaces. The composite retained its strengths upon bending even at 1500 °C in argon and there was no evidence for brittle fracture. The flexural creep strain of the composite at 1400 °C was 0.55%.     

Drilling delamination and thermal damage of carbon nanotube/carbon fiber reinforced epoxy composites processed by microwave curing

The drilling-induced delamination and thermal damage of carbon fiber reinforced epoxy composite materials are serious problems especially for high value components of the aviation industry. To suppress the delamination and drilling ablation, an innovative approach was employed in this study. The multiwalled carbon nanotubes (MWCNTs) were introduced to the matrix resin to improve the interlaminar strength and thermal conductivity. The as-prepared composite was processed by microwave curing to enhance the interface strength between carbon fiber and the carbon nanotubes modified matrix. During the drilling processes, optical fiber Bragg grating sensors were utilized to precisely measure the drilling temperature. Experimental results indicated that the interlaminar fracture toughness was increased by more than 66% compared to that of the traditional thermal cured samples without MWCNTs. And the delamination factor was decreased by 16% according to the computerized tomography scanning results. The maximum drilling temperature of the MWCNTs reinforced composite was below the glass transition temperature of the matrix resin and declined by 23 °C compared to traditional composites. With this novel method of carbon nanotube modification and microwave curing, we provide the capability of reducing the drilling delamination and thermal damage of carbon fiber composites simultaneously, and explored the possibility of manufacturing and machining integration.     

层压法制备SiC_f/Al_2O_3复合材料的抗弯性能研究

以氧化铝为填料,硅溶胶为粘结剂,碳化硅纤维布为增强纤维,使用层压法制备SiCf/Al2O3复合材料,并对该复合材料做了抗弯性能试验。结果显示,随处理温度的升高,基体缓慢释放出的结合水会对纤维造成氧化损伤,使试样的抗弯性能下降,但是材料始终表现出非脆性断裂行为,这与基体与纤维之间未形成强结合有关;包裹氧化硼玻璃后在空气中对SiCf/Al2O3进行处理后,氧化硼玻璃能有效阻止空气与纤维的接触,防止了纤维在高温下被氧化,分析表明在600、700、800℃保温0.5、1、1.5、2 h后,抗弯强度变化不大。     

Mechanisms for controlling springback and strength in heat-assisted sheet forming

The recently developed multi-step sheet forming technology with inductive in-situ heating serves to increase the productivity and to reduce costs compared to hot stamping with furnace heating. The paper reveals the mechanisms for the flexible setting of geometric and mechanical properties such as the bending angle and strength in terms of a closed loop control. The air and die bending as representative forming processes are analyzed with respect to the mechanisms overbending, springback and thermal distortion by experimental, numerical, and analytical investigations. The mechanisms for controlling strength in carbon steels by grain refinement, grain growth and cooling rate are described.     

精冲—板料成形复合工艺要点

以具有精密轮廓和三维形状的零件为例,介绍了精冲与拉伸、弯曲、翻边、半冲孔等板料成形复合工艺以及复合工艺设计要点,分析模具设计中的技术问题,得出了工艺制定过程中的一些具体要求。