Braided thermoplastic composite rivets for composite structures

用于复合结构的编织热塑性复合铆钉

• 批准号: 488387-2015
• 负责人: LabergeLebel, Louis
• 金额: $ 0.9万
• 依托单位: École Polytechnique de Montréal
• 依托单位国家: 加拿大
• 项目类别: Collaborative Research and Development Grants
• 财政年份: 2017
• 资助国家: 加拿大
• 起止时间: 2017-01-01 至 2018-12-31
• 项目状态: 已结题
• 来源: https://www.nserc-crsng.gc.ca/ase-oro/Details-Detailles_eng.asp?id=618523
• 关键词: Braided; thermoplastic; composite; rivets; structures

A significant part of modern aircraft structures are fabricated using composites materials. These materials are stiff and strong while being lighter than metallic materials such as aluminum, titanium or steel commonly used in traditional aerospace manufacturing. Composite material components must be assembled using heavy titanium fasteners since structural bounding is not certifiable by governmental authorities. Moreover, the drilling precision requirements are much greater than for metallic structure fastening. This research project will develop a composite rivet for composite structures. Rivet blanks will be produced using the pultrusion manufacturing technique. Pultrusion must be adapted to advanced materials such as PEEK polymers and braided carbon fibres. The rivet setting operation, taking advantage of the deformability of bi-axial braids, willrelax the drilling precision requirements. The composite rivet will be of similar material to the surrounding composite structure, eliminating the galvanic corrosion issues. Also, the composite rivet's low electric conductivity will mitigate the risks associated with electrostatic discharge when using metallic fasteners. A robotized riveting machine will be designed in order to study and determine the optimal riveting parameters. Mechanical performance of simple joint configurations will be characterized. Meeting these objectives will allow us to develop a new technology that has the potential to reduce cost associated with drilling and assembly, improve the safety, lower the weight of the aircraft.

现代飞机结构的很大一部分是用复合材料制造的。这些材料坚硬而坚固，同时比传统航空航天制造中常用的铝、钛或钢等金属材料更轻。复合材料部件必须使用重型钛紧固件组装，因为结构边界没有得到政府部门的认证。而且，钻孔精度要求远高于金属结构的紧固。本研究项目将开发一种用于复合结构的复合铆钉。铆钉坯料将采用拉挤制造技术生产。拉挤必须适应于先进的材料，如PEEK聚合物和编织碳纤维。铆钉设置操作，利用双轴编织的可变形性，将放松钻孔精度要求。复合铆钉将采用与周围复合结构相似的材料，从而消除了电偶腐蚀问题。此外，复合铆钉的低导电性将降低使用金属紧固件时与静电放电相关的风险。为了研究和确定最佳铆接参数，设计了一种自动化铆接机。简单关节结构的力学性能将被表征。实现这些目标将使我们能够开发出一种新技术，该技术有可能降低钻井和组装的相关成本，提高安全性，降低飞机的重量。