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

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。

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 existing 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 design of radius structure and the product reception standards of spar.