Smart-Patch Repair Engineering of Aging Aircraft and Spacecraft Structures

老化飞机航天结构智能补片修复工程

• 批准号: 14205138
• 负责人: SEKINE Hideki
• 金额: $ 24.54万
• 依托单位: Tohoku University
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (A)
• 财政年份: 2002
• 资助国家: 日本
• 起止时间: 2002 至 2005
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-14205138/
• 关键词: Aging Aircraft and Spacecraft Structures; Safety; Repair Engineering; Composite Patch Repair; Smart Patch; Prediction of Damage Evolution; Identification of Damage; Retardation of Damage Evolution; 構造安定性; 複合材パッチ接触補修

The repair engineering of cracked aircraft and spacecraft structures is needed to extend the service life of aging aircraft and spacecraft. In this research project, the repair engineering of the structural panels using smart patches, i.e. composite patches with sensors and actuators, was investigated to accomplish a high level of safety of repaired aircraft and spacecraft. The main results are summarized as follows :1. Based on a three-dimensional combined BEM/FEM, the numerical simulation method of damage evolution behavior in repaired structural panels was presented.2. The strain measuring sensor system using fiber Bragg grating (FBG) sensors installed on the patch surface was developed, and the method for identifying the locations and shapes of damage fronts in repaired structural panels was presented.3. The enhancement of patching efficiency due to the activation of piezoelectric actuators in smart patches was examined, and the retardation of damage evolution in repaired structural panels was realized.4. The issues in practical use of the smart-patch repair engineering were considered, and the feasibility study was made.

为延长老化飞机和航天器的使用寿命，需要对飞机和航天器结构裂纹进行修复工程。在本研究项目中，研究了使用智能补片（即具有传感器和致动器的复合材料补片）的结构板的修复工程，以实现修复的飞机和航天器的高水平安全性。主要研究结果如下：1.基于三维边界元/有限元相结合的方法，提出了修复结构板损伤演化行为的数值模拟方法.研制了安装在补片表面的光纤布拉格光栅（FBG）应变测量传感系统，提出了修复结构板损伤前沿位置和形状的识别方法.研究了智能补片中压电致动器的激活对补片修补效率的提高，实现了对结构板损伤演化的延缓.考虑了智能补片修复工程在实际应用中存在的问题，并进行了可行性研究。

项目成果

パッチで接着補修された航空機機体構造パネル内の疲労き裂および接着はく離の先端位置および先端形状の同定に関する研究

补片修复飞机机身结构板疲劳裂纹尖端位置和尖端形状及胶粘剂分层识别研究

• 发表时间: 2006
• 期刊: 日本航空宇宙学会論文集 54・624
• 作者: Naoe Nishihara;Shin-ichi Tanabe;藤元伸悦
• 通讯作者: 藤元伸悦

接着補修された航空機機体構造パネル内の疲労き裂および接着はく離の同定

胶粘修复飞机机身结构面板中疲劳裂纹和胶粘剂分层的识别

• 发表时间: 2004
• 期刊: 日本機械学会第17回計算力学講演会講演論文集 04・40
• 作者: 藤元伸悦

Identification of Location and Shape of Fatigue Crack Fronts in Aircraft Structural Panels Repaired with a Bonded FRP Composite Patch Containing a Strain Measurement Plane

识别用含有应变测量平面的粘合 FRP 复合材料补片修复的飞机结构面板中疲劳裂纹前沿的位置和形状

• 发表时间: 2004
• 期刊: Journal of the Japan Society for Aeronautical and Space Sciences Vol.52, No.607
• 作者: S.Fujimoto

A Framework for Understanding Damage Development in Structural Composites : Modelling the Failure Processes

理解结构复合材料损伤发展的框架：失效过程建模

• 发表时间: 2004
• 期刊: The 11th US-Japan Conference on Composite Materials
• 作者: P.W.R.Beaumont

Propagation Rate of a Fatigue Crack in Rectangular Aircraft Structural Panels Repaired with a Bonded FRP Composite Patch Containing a Piezoelectric Fiber Composite Actuator Layer

用含有压电纤维复合执行器层的粘合 FRP 复合材料补片修复矩形飞机结构面板中疲劳裂纹的扩展率

• 发表时间: 2003
• 期刊: Transactions of the Materials Research Society of Japan 28・3
• 作者: K.Iida;H.Akimoto;S.Kubo;S.Fujimoto
• 通讯作者: S.Fujimoto