考察机身收缩段的复合材料Ω型加筋壁板前段和后段连接结构在拉伸载荷下的承载能力,开展了拉伸破坏试验研究。试验件为壁板与框呈75°夹角的倾斜结构,试验考核了加筋壁板、连接框、连接角盒和紧固件的应变水平、试验件的载荷-位移曲线和破坏载荷。试验结果表明,Ω型加筋壁板前后段连接结构在拉伸载荷下,角盒和框的连接处的紧固件以及框的转角处最先发生破坏。试验结果可作为飞行机身复合材料结构连接的设计和评定依据。 The bearing capacity under the tensile load of the composite section Ω-shaped stiffened panel of the fuselage shrinkage section was investigated and the tensile failure test was carried out. The test piece is a tilting structure with an angle of 75 ° between the wall plate and the frame. The test verifies the strain level of the stiffened wall plate, the connection frame, the connecting corner box and the fastener, the load-displacement curve and the breaking load of the test piece. The experimental results show that under the tensile load, the joints of corner box and frame and the corners of the box are the first to be damaged. The test results can be used as the basis for the design and evaluation of the structural connection of flying fuselage composite materials.