In composite integral panels,it is often necessary to terminate some of the stiffeners at wing rib, at the forward or rear spar,or at wing oil box to satisfy detailed design requirements. An abrupt Stiffener termination can cause highly stress concentration conduce to flange/skin interface delamination. Experiment tests are carried out relating to four different stiffener runout specimens and the load capability were discussed in detail. The result indicate that the stiffener runout of B group is the best,their stress concentration is the lowest,dimension of delami-nation is the smallest,and the method of using A-ultrasound to detect delamination is feasible, which could intui-tively present the whole course of delamination.%复合材料结构整体化设计时,由于设计要求或设计限制条件,机翼壁板的长桁常常在翼肋、机翼的前后梁附近、机翼的油箱附近等部位终止.在长桁截止端处应力集中水平较高,极易引起缘条/蒙皮界面脱胶分层.设计4种不同构型的截止端试件,并开展相应的拉伸试验研究.结果表明,B组试件的截止端斜削构型最优,应力集中水平最低且损伤扩展最小的截止端构型;试验中采用A超检测损伤的发法是可行的,能够直观地呈现出损伤扩展的历程.
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