Ti/CFRP叠层结构钻削叠层界面损伤形成及抑制策略研究
Study on Stack Interface Damage Formation and Suppression Strategy for Ti/CFRP Stacks
- 兵工学报 2026年
- 作者机构：
1. 郑州航空工业管理学院 机械工程学院,河南,郑州,450046
2. 河南理工大学 机械与动力工程学院,河南,焦作,454000
- 作者简介：
- 基金信息：国家自然科学基金项目(51675164);河南省科技攻关项目(252102220069);河南省高校重点项目(26B460028);郑州航空工业管理学院青年科研基金支持计划项目（25ZHQN01010）
DOI：10.12382/bgxb.2025.0878
中图分类号： V262;TG52;TB559收稿：2025-09-25，
网络出版：2025-12-29，
- 稿件说明：
移动端阅览
李远霄, 焦锋, 申俊杰, 等.Ti/CFRP叠层结构钻削叠层界面损伤形成及抑制策略研究[J/OL]. 兵工学报, 2026(2026-01-04). https://doi.org/10.12382/bgxb.2025.0878.
LI Y X, JIAO F, SHEN J J, et al.Study on stack interface damage formation and suppression strategy for Ti/CFRP stacks[J/OL]. Acta Armamentarii, 2025(2025-12-29). https://doi.org/10.12382/bgxb.2025.0878. (in Chinese)
李远霄, 焦锋, 申俊杰, 等.Ti/CFRP叠层结构钻削叠层界面损伤形成及抑制策略研究[J/OL]. 兵工学报, 2026(2026-01-04). https://doi.org/10.12382/bgxb.2025.0878. DOI：
LI Y X, JIAO F, SHEN J J, et al.Study on stack interface damage formation and suppression strategy for Ti/CFRP stacks[J/OL]. Acta Armamentarii, 2025(2025-12-29). https://doi.org/10.12382/bgxb.2025.0878. (in Chinese) DOI：
摘要
钛合金/碳纤维增强复合材料（Carbon Fibre Reinforced Plastics，CFRP）叠层结构在航空航天领域应用日益广泛，为抑制Ti/CFRP叠层结构装配孔钻削中叠层界面损伤，提高构件结构完整性，分析Ti/CFRP叠层结构制孔过程中叠层界面损伤的形成和互相影响机制，基于超声振动辅助钻削和低频振动辅助钻削的优势，提出高低频复合振动钻削的叠层界面损伤抑制策略，并开展Ti/CFRP叠层结构制孔试验。研究结果表明：Ti/CFRP叠层结构制孔过程中，过大钻削力和钻削温度引起的钛合金叠层界面出口毛刺会侵入近叠层界面CFRP材料，引起严重的分层、撕裂和烧伤；高低频复合振动钻削基于其更低的钻削力、钻削温度，钛合金叠层界面出口毛刺高度最大降低50.55%，CFRP界面分层因子最大降低55.13%，此外有效降低了CFRP界面烧伤，显著抑制了Ti/CFRP叠层结构钻削叠层界面损伤，同时降低了刀具磨损。为航空航天异质叠层结构一体化制孔提供了工艺参考。
Abstract
Ti/ carbon fibre reinforced plastics(CFRP) stacks are increasingly widely used in the aerospace field. In order to suppress the stack interface damage in the drilling of Ti/CFRP stacks and improve the structural integrity of components
the formation and interaction mechanism of stack interface damage of Ti/CFRP stacks were analyzed firstly. Then
based on the advantages of ultrasonic vibration-assisted drilling (UVAD) and low-frequency vibration-assisted drilling (LFVAD)
the damage suppression strategy for stack interface
namely high and low-frequency combined vibration-assisted drilling (H-LCVAD)
is proposed. Finally
the drilling experiments of Ti/CFRP stacks were carried out. The results show that during the drilling process of Ti/CFRP stacks
the Ti exit burrs at stack interface caused by excessive drilling force and drilling temperature will invade the CFRP material near the stack interface
causing serious delamination
tearing and burns. H-LCVAD
based on its lower drilling force and drilling temperature
can reduce the Ti exit burr height by 50.55% and the CFRP interface delamination factor by 55.13% at most. In addition
it can effectively reduce the CFRP interface burn
significantly inhibit the Ti/CFRP stacks interface damage
and reduce the tool wear. It provides a process reference for the integrated drilling of aerospace heterogeneous laminated structure.
关键词
Keywords
references
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