大型民机复合材料翼梁R区褶皱力学性能研究
Study on Mechanical Properties of Radius of Aircraft Composite Spar
樊维超 1仇翯辰 1方亚宁 1穆晓光2
作者信息
- 1. 中国商飞上海飞机制造有限公司,复合材料中心,上海 200123;中国商飞北京民用飞机技术研究中心,民用飞机结构与复合材料北京市重点实验室,北京 102211
- 2. 中国商飞上海飞机制造有限公司,复合材料中心,上海 200123
- 折叠
摘要
翼梁是飞机主盒段结构的重要组成部件,在国际主流的大型民机中,翼梁采用T800 级碳纤维复合材料制造;R区结构是翼梁的重要结构特征,其力学性能通常直接决定着翼梁产品的优劣.本文针对复合材料翼梁制造过程中存在的R区褶皱缺陷,制定R区褶皱缺陷定量化标定方法,通过曲梁四点弯试验测试方法,对含R区缺陷和不含R区缺陷的试验件进行测试,研究其R区力学性能差异,为翼梁R区结构设计和产品接收标准的制定提供数据支持.
Abstract
Spar is an important component of the main box of the aircraft.In the international mainstream large civil aircraft,the spar is made of T800 carbon fiber composite materials.Radius structure is an important structural feature of spar,its mechanical properties usually directly determine the quality of spar.Aiming at the wrinkle exist-ing in the manufacturing process of composite spar,a quantitative calibration method for radius was developed in this paper.Test pieces with and without wrinkle were tested by the four-point bending test method of the curved beam.The difference of mechanical properties in radius was studied,which provided data support for the de-sign of radius structure and the product reception standards of spar.
关键词
复合材料/翼梁/R区/褶皱Key words
composite material/spar/radius/wrinkle引用本文复制引用
出版年
2024
NETL
NSTL
万方数据