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| Failure Damage Experiment Research for Connection Structure of Ω Type Stiffened Panels Subjected to Tension Load |
| LU Binghe |
| (Shanghai Aircraft Design and Research Institute, Shanghai 201210, China) |
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Abstract 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.
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2017, 
