In order to gain the load capability of connection structure of composite Ω type stiffened panels in after fuselage

failure experiments for connection structure of Ω stiffened panels subjected to tension load were conducted. The specimen was a sloping structure with the angle of 75° between stiffened panel and the frame. The experiment tested strain of stiffened panel

frame

fitting and fasteners and gained the load-displacement curve and cracking load. The experiment results show that the corner of the frame and the fasteners which connect the fittings and the frames are the prior damage points in tension load. The experiment result is meaningful to connection design for composites structure on fuselage.