| Related citation: | Chao Lv,Shuyuan Zhao,Zhengyu Li,Zeliang Pu,Jianglong Dong,Xinyang Sun,Wenjiao Zhang.Bolt Design of Ceramic Matrix Composite and Superalloy Bolted Joint Based on Damage Failure Load[J].Journal of Harbin Institute Of Technology(New Series),2021,28(2):55-61.DOI:10.11916/j.issn.1005-9113.2019061. |
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| Author Name | Affiliation | | Chao Lv | China Academy of Aerospace Aerodynamics, Beijing 100074, China | | Shuyuan Zhao | National Key Laboratory of Science and Technology for National Defense on Advanced Composites in Special Environments, Harbin Institute of Technology, Harbin 150080, China | | Zhengyu Li | National Key Laboratory of Science and Technology for National Defense on Advanced Composites in Special Environments, Harbin Institute of Technology, Harbin 150080, China | | Zeliang Pu | National Key Laboratory of Science and Technology for National Defense on Advanced Composites in Special Environments, Harbin Institute of Technology, Harbin 150080, China | | Jianglong Dong | National Key Laboratory of Science and Technology for National Defense on Advanced Composites in Special Environments, Harbin Institute of Technology, Harbin 150080, China | | Xinyang Sun | School of Aeronautics and Astronautics, Harbin Institute of Technology, Harbin 150001, China | | Wenjiao Zhang | Engineering College, Northeast Agricultural University, Harbin 150030, China |
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| Abstract: |
| Ceramic matrix composite (CMC) and superalloy bolted joints are commonly used high temperature connection structures in aerospace and aeronautical fields. In this paper, a finite element model coupled with progressive damage analysis of 2D C/SiC composites and superalloy bolted joint was implemented to simulate the uniaxial tensile loading process by using the ABAQUS finite element software. The parametric effects of raised head bolt on stress distribution, tensile performance, and damage process were studied for the CMC-superalloy bolted joint structures. The results showed that the final failure load increased first to the maximum value, and then decreased with the rise of bolt diameter, bolt head diameter, and bolt head thickness, respectively. When the three parameters were 5.0 mm, 9.5 mm, and 2.8 mm for the current studied bolt configuration, the joint structure gave the maximum load bearing capacity for the considered parameter ranges. It was also found that around 42% potential improvement in load bearing capacity could be achieved by very small adjustments in bolt parameters of the joints. |
| Key words: 2D C/SiC composite progressive damage analysis tensile properties bolted joint bolt parameters |
| DOI：10.11916/j.issn.1005-9113.2019061 |
| Clc Number:V19 |
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| Descriptions in Chinese: |
| 瞬态热载荷下陶瓷基复合材料螺栓连接结构热应力及装配参数演化 吕超1，赵淑媛2，李正禹2，蒲泽良2，董江龙2，孙新杨3，张文娇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．哈尔滨工业大学 航天学院，哈尔滨 150001；4．东北农业大学 工程学院，哈尔滨 150030） 创新点说明：基于有限元软件ABAQUS对陶瓷基复合材料和高温合金螺栓连接结构的单轴拉伸性能进行渐进损伤分析，研究了螺钉几何参数对陶瓷基复合材料-高温合金螺栓连接结构拉伸性能及失效行为的影响规律，并给出了连接结构失效载荷最大时的螺钉尺寸参数。 研究目的： 陶瓷基复合材料由于其耐高温、耐磨、抗高温蠕变、导热系数和热膨胀系数较低等特点，逐渐在飞行器热结构上得到广泛的应用。在飞行器结构中，陶瓷基复合材料常常不可避免的与金属件组成连接结构。螺钉的尺寸参数显著影响陶瓷基复合材料螺栓连接结构承载能力，对螺钉的几何尺寸进行设计对提高陶瓷基复合材料-金属螺栓连接结构的承载能力具有重要意义。 研究方法： 针对2D编织C/SiC陶瓷基复合材料与高温合金GH4169组成的螺栓连接结构，利用UMAT子程序将材料模型嵌入到ABAQUS有限元模型中建立了单钉单搭接螺栓连接结构的渐进损伤分析方法。基于已建立的C/SiC陶瓷基复合材料-高温合金螺栓连接结构的有限元模型，研究六角凸头螺钉的螺钉直径、钉头直径及钉头高度对于连接结构孔周应力分布、拉伸强度以及破坏方式的影响情况，讨论给出承载能力最大的螺钉最优几何参数。 研究结果： C/SiC陶瓷基复合材料-高温合金螺栓连接结构的刚度随螺钉直径的增加小幅下降，受钉头直径与厚度的影响较小。在给定的螺钉直径、钉头直径及钉头厚度参数范围内，连接结构的拉伸强度均先随各参数的增加而增大而后降低，当螺钉直径为5mm，钉头直径为9.5mm，钉头厚度为2.8mm时室温最终失效载荷达到最大。 结论： 本研究基于ABAQUS有限元软件对2D编织C/SiC陶瓷基复合材料-高温合金进行有限元渐进损伤模拟分析,讨论螺钉尺寸参数对于连接结构拉伸性能的影响规律，为陶瓷基复合材料机械连接结构的工程应用提供设计分析基础及指导。 关键词：2D C/SiC陶瓷基复合材料；渐进损伤分析；拉伸性能；螺钉连接；螺钉参数 |
