M5 3DN C/SiC螺栓的微结构与高温拉伸退化机理

康根发; 王守财; 孙晓军; 金宏; 何东方; 吴优; 周心悦; 张毅

doi:10.16080/j.issn1671-833x.25020295

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M5 3DN C/SiC螺栓的微结构与高温拉伸退化机理

研究论文 | 更新时间：2026-06-16

- M5 3DN C/SiC螺栓的微结构与高温拉伸退化机理
- 航空制造技术 2026年69卷第10期页码：127-136
- 作者机构：
  
  河南省紧固连接技术重点实验室，信阳 464000
  河南航天精工制造有限公司，信阳 464000
  中国航空工业集团有限公司沈阳飞机设计研究所，沈阳 110035
  沈阳飞机工业（集团）有限公司，沈阳 110034
  西北工业大学超高温结构复合材料重点实验室，西安 710072
- 作者简介：
  
  张毅，副研究员，博士，研究方向为陶瓷基复合材料连接技术。
- 基金信息：
  
  河南省紧固连接技术重点实验室开放课题(JGLJ2403);河南航天精工制造有限公司课题(XM（H）2024-FD1)
- DOI：10.16080/j.issn1671-833x.25020295
  中图分类号： V252;TB332
- 收稿：2025-09-17，
  
  修回：2025-10-29，
  
  录用：2025-11-26，
  
  纸质出版：2026-05-15
- 稿件说明：
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引文格式：康根发，王守财，孙晓军，等.M5 3DN C/SiC螺栓的微结构与高温拉伸退化机理[J].航空制造技术，2026, 69（10）：25020295.

KANG Genfa, WANG Shoucai, SUN Xiaojun, et al. Microstructural features and tensile degradation mechanisms of M5 3DN C/SiC bolts at high-temperatures[J]. Aeronautical Manufacturing Technology, 2026, 69(10): 25020295.
引文格式：康根发，王守财，孙晓军，等.M5 3DN C/SiC螺栓的微结构与高温拉伸退化机理[J].航空制造技术，2026, 69（10）：25020295. DOI： 10.16080/j.issn1671-833x.25020295.

KANG Genfa, WANG Shoucai, SUN Xiaojun, et al. Microstructural features and tensile degradation mechanisms of M5 3DN C/SiC bolts at high-temperatures[J]. Aeronautical Manufacturing Technology, 2026, 69(10): 25020295. DOI： 10.16080/j.issn1671-833x.25020295.

摘要

连续碳纤维增韧碳化硅陶瓷基复合材料的机械连接技术是推动该复合材料应用于航空航天复杂热结构件的关键。本文采用化学气相渗透工艺制备了M5 3DN C/SiC螺栓和螺母，系统研究了其在室温、300 ℃、600 ℃、1000℃的拉伸性能，并基于微结构演变分析了其高温拉伸退化机理。结果表明，3DN C/SiC 复合材料的孔隙主要出现在三维针刺层周边和无纬布层中，加工过程中切削力变化造成了螺纹缺齿。M5 3DN C/SiC螺栓的高温拉伸失效模式主要有螺柱拉断和螺牙拉脱两种。1000 ℃拉伸位移为1/2螺距时，由于发生基体开裂并随着载荷增加出现裂纹扩展，裂纹处裸露的碳纤维受到1000 ℃高温氧化环境影响，其后续的承载能力快速丢失。

Abstract

Mechanical joining technology for continuous carbon fiber reinforced silicon carbide ceramic matrix composites is key to promoting the application of this composite material in complex thermal structural components in the aerospace field. This study employed the chemical vapor infiltration process to fabricate M5 3DN C/SiC bolts and nuts

systematically investigating their tensile properties at room temperature

300 ℃

600 ℃

and 1000 ℃. The high-temperature tensile degradation mechanism was analyzed based on microstructural evolution. The results indicate that pores in the 3DN C/SiC composite primarily occur around the three-dimensional needled layers and within the unidirectional cloth layers.Variations in cutting forces during the machining process led to thread tooth defects. The high-temperature tensile failure modes of the M5 3DN C/SiC bolts mainly included bolt shank fracture and thread stripping. At 1000 ℃

when the tensile displacement reached half of the pitch

matrix cracking occurred and propagated with increasing load. The exposed carbon fibers at the crack sites

subjected to the high-temperature oxidative environment at 1000 ℃

rapidly lost their subsequent load-bearing capacity.

关键词

Keywords

references

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