CAJ | 학술논문

胶接增强修复补片的可设计性是胶接技术的优点之一，科学设计飞机结构损伤部位的增强补片是保证修补效果的重要因素。本文利用 ANSYS 软件对飞机2024蒙皮裂纹复合材料增强补片进行三维有限元建模与仿真计算，计算了复合材料单级补片和多级补片边缘胶层最大剪应力，给出了飞机2024蒙皮裂纹单侧修补时的补片优化设计参数。计算表明，用复合材料增强修补铝合金蒙皮裂纹时，补片应设计成多级形式；当补片级数超过5级时，补片边缘的胶层剪应力显著减小，与单级补片相比，其最大剪应力下降了85%。
효접증강수복보편적가설계성시효접기술적우점지일，과학설계비궤결구손상부위적증강보편시보증수보효과적중요인소。본문이용 ANSYS 연건대비궤2024몽피렬문복합재료증강보편진행삼유유한원건모여방진계산，계산료복합재료단급보편화다급보편변연효층최대전응력，급출료비궤2024몽피렬문단측수보시적보편우화설계삼수。계산표명，용복합재료증강수보려합금몽피렬문시，보편응설계성다급형식；당보편급수초과5급시，보편변연적효층전응력현저감소，여단급보편상비，기최대전응력하강료85%。
Flexible design pattern is an advantage for bonded repair,it is an important factor to optimize the enhanced patch pattern to ensure the durability of the repaired structure.In the paper,a 3D finite element analysis model of 2024-skin crack with composite patch was created and simulated ,the max shearing stress of single and multiple patch at edge was cal-culated,the optimized factor of one side repair of 2024-skin crack were listed.Through calculating,the enhanced patch should be designed to multiple shapes when the crack of aluminum alloy skin was repaired by composite material.The shear-ing stress at the patch edge was reduced obviously when patch series was more then grade 5,and its max shearing stress was reduced 85% compare with single patch.