| Related citation: | Chao Lv,Feng Li,Shuyuan Zhao,Qian Sun,Mingrui Li,Xinyang Sun.Influence of Assembly Parameters on Tensile Behavior of Hybrid CMC and Superalloy Bolted Joints by Progressive Damage Analysis[J].Journal of Harbin Institute Of Technology(New Series),2021,28(3):53-60.DOI:10.11916/j.issn.1005-9113.2021097. |
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| Author Name | Affiliation | | Chao Lv | China Academy of Aerospace Aerodynamics, Beijing 100074, China | | Feng Li | China Academy of Aerospace Aerodynamics, Beijing 100074, China | | Shuyuan Zhao | National Key Laboratory of Science and Technology on Advanced Composites inSpecial Environments, Harbin Institute of Technology, Harbin 150080, China | | Qian Sun | Shenyang Aircraft Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110000, China | | Mingrui Li | National Key Laboratory of Science and Technology on Advanced Composites inSpecial Environments, Harbin Institute of Technology, Harbin 150080, China | | Xinyang Sun | School of Aeronautics and Astronautics, Harbin Institute of Technology, Harbin 150001, China |
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| Abstract: |
| With the considerable applications of ceramic matrix composites (CMC) in aircraft engineering, the design of CMC bolted joint gains paramount attention because of its capacity to to improve load-bearing efficiency of aircraft key structure. In this work, a 3D finite element model was established to predict tensile performance and failure modes of single-lap, single-bolt 2D C/SiC composite, and superalloy joint, which considers the progressive damage behavior of 2D woven C/SiC composites. On the basis of the developed progressive damage model, a parametric study was carried out to illustrate the effects of bolt preload and bolt-hole clearance on mechanical behaviors of the hybrid bolted joint. It was found that the increase in the value of bolt preload made the failure load grow first and then drop, and the optimum value of bolt preload 5.00 kN generated 56.47% rise in the initial failure load and 22.83% rise in the final failure load for the bolted joint in comparison with zero preload case. As the clearance increased from 0 to 2.00%, the initial and final failure loads respectively declined by 45.88% and 24.02% for 2.00% bolt-hole clearance relative to the neat-fit case. The loss in failure loads can be reduced to compressive stress concentration around the fastening hole-edge area, leading to the appearance of earlier damages by the introduction of increasing bolt hole clearance. |
| Key words: ceramic matrix composite progressive damage analysis tensile performance bolt preload bolt-hole clearance |
| DOI：10.11916/j.issn.1005-9113.2021097 |
| Clc Number:V19 |
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| Descriptions in Chinese: |
| 基于渐进损伤分析的装配参数对陶瓷基复合材料与高温合金 混合螺栓连接结构拉伸行为的影响 吕超1，李锋1，赵淑媛2，孙茜3，李明瑞2，孙新杨4 （1.中国航天空气动力技术研究院，北京 100074；2.哈尔滨工业大学 特种环境复合材料技术国家级重点实验室，哈尔滨 150080；3.中航工业集团公司沈阳飞机设计研究所，沈阳 110000；4.哈尔滨工业大学 航天学院，哈尔滨 150001） 创新点说明：采用ABAQUS有限元软件对陶瓷基复合材料和高温合金螺栓连接结构进行了渐进损伤分析，研究了连接结构装配参数对混合连接结构拉伸性能的影响规律，并讨论了连接结构的损伤失效模式，为提高陶瓷基复合材料连接结构的结构效率及服役安全性提供理论基础。 研究目的： 在飞行器结构应用中，陶瓷基复合材料与金属螺栓连接件的强度分析与结构设计对提高结构承载效率及维护结构完整性起着至关重要的作用，研究连接结构装配参数对陶瓷基复合材料-高温合金螺栓连接结构拉伸性能的影响，对其在航空航天领域的运用具有重要意义。 研究方法： 采用有限元软件ABAQUS建立了2D编织C/SiC陶瓷基复合材料与高温合金GH4169组成的单钉单搭接螺栓连接结构的有限元分析模型，结合Fortran语言将非线性本构模型、失效准则及材料退化模型编写成用户子程序UMAT文件，并嵌入到ABAQUS有限元软件中实现高温拉伸条件下陶瓷基复合材料与高温合金沉头螺栓紧固件的渐进损伤分析。基于此模型研究了连接结构装配参数对混合连接结构拉伸性能的影响规律，并讨论了连接结构的损伤失效模式。 结果： 2D编织C/SiC复合材料与高温合金组成的螺栓连接结构施加适当的预紧力可以提高连接结构的刚度和强度，但过大的预紧力会使复合材料板厚度方向发生破坏，从而导致接头强度下降。钉孔间隙的增加将加剧孔内挤压区域的应力集中现象，导致结构强度降低。 结论： 本研究针对陶瓷基复合材料和高温合金螺栓连接结构，研究了连接结构装配参数对混合连接结构拉伸性能的影响规律及相关失效模式，为陶瓷基复合材料连接件的结构设计和工程化应用提供了技术支撑。 关键词：陶瓷基复合材料；渐进损伤分析；拉伸性能；预紧力；钉孔间隙 |
