SiC纤维增强钛基复合材料强度分析方法研究

发布时间：2018-05-18 07:40

本文选题：金属基复合材料 + 多尺度　；参考：《南京航空航天大学》2015年硕士论文

【摘要】：随着航空航天工业的不断发展,复合材料在航空航天领域应用前景十分广阔。金属基复合材料由于其良好的材料性能将成为高温结构材料研究的重点。然而,对于单向金属基复合材料的各方面研究还处于初始阶段,需要一个逐步认识、逐步完善的过程。因此,开展对金属基复合材料强度分析方法的研究显得非常有必要。采用细观有限元法模拟了Si C/Ti-6Al-4V复合材料的单轴拉伸行为。首先,建立Si C/Ti-6Al-4V复合材料的有限元模型,其中加入了内聚力界面模型来了模拟复合材料的界面;其次,利用有限元软件模拟得到了Si C/Ti-6Al-4V复合材料的轴向热残余应力以及单轴拉伸时的应力应变曲线,并与相关文献结果进行对比;最后模拟分析了不同界面强度以及纤维体积含量对复合材料单轴拉伸性能的影响。基于有限容积直接平均细观力学法(FVDAM)来预测复合材料的宏观性能,结合复合材料细观失效准则以及弹性性能折减模型等,发展了一套宏细观统一的渐进失效分析方法。利用此方法编写了一套程序并对Si C/Ti-6Al-4V复合材料含中心孔的平板构件进行了失效分析模拟,预测了其失效强度以及失效模式。以某型航空发动机压气机叶片为原型,利用宏细观统一渐进失效分析方法对叶片结构进行了失效过程模拟分析,初步验证了复合材料多尺度渐进失效分析方法在工程实际应用中的可行性。此外,本文对未来金属基复合材料的研究提出了几点建议和展望。
[Abstract]:With the continuous development of aerospace industry, composite materials are widely used in aerospace field. Metal-matrix composites will become the focus of high-temperature structural materials because of their good material properties. However, the study on all aspects of unidirectional metal matrix composites is still in the initial stage, which needs a gradual understanding and improvement process. Therefore, it is necessary to study the strength analysis method of metal matrix composites. The uniaxial tensile behavior of Si C/Ti-6Al-4V composites was simulated by mesoscopic finite element method. Firstly, the finite element model of Si C/Ti-6Al-4V composite is established, in which the cohesive interface model is added to simulate the interface of the composite. The axial thermal residual stresses of Si C/Ti-6Al-4V composites and the stress-strain curves under uniaxial tension were obtained by using finite element software, and the results were compared with those obtained in related literatures. Finally, the effects of interfacial strength and fiber volume content on uniaxial tensile properties of composites were simulated and analyzed. Based on the finite volume direct mean mesomechanics (FVDAM) method to predict the macroscopical properties of the composites, a set of macro- and meso-unified progressive failure analysis method was developed, combining with the meso-failure criterion and the elastic properties reduction model. By using this method, a set of program is compiled and the failure analysis simulation of the plate member with center hole in Si C/Ti-6Al-4V composite is carried out, and the failure strength and failure mode are predicted. Taking a certain aeroengine compressor blade as the prototype, the failure process of the blade structure is simulated and analyzed by using the macroscopical unified progressive failure analysis method. The feasibility of multi-scale incremental failure analysis method for composite materials in engineering practice is preliminarily verified. In addition, some suggestions and prospects for the research of metal matrix composites in the future are put forward in this paper.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：TB33

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