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由于设计要求或设计限制条件,壁板的长桁常常在翼肋或机身框附近、机翼的前后梁附近、机翼与机身的开口附近、机翼的油箱附近等部位终止。在面内载荷作用下,截面形状突变和传载路径偏移在端头处会产生应力集中,极易引起缘条/蒙皮界面脱胶分层。对三种构型的长桁终止端典型件在单向拉、压载荷下的破坏机制进行了试验研究与数值模拟,结果表明,拉伸时的失效是由面外剥离应力与层间剪应力的共同作用所致,而压缩时的失效主要是由层间剪应力所致。
Due to design or design constraints, the sills of the sills are often near the ribs or fuselage frame, near the front and rear wings of the wing, near the openings of the fuselage and the fuselage, and near the fuel tank of the wing. Under the action of in-plane load, sudden change of cross-section shape and migration of path will produce stress concentration at the tip, which can easily cause degumming and delamination of the edge / skin interface. Experimental and numerical simulations of the failure mechanism of three types of trusses at the end of typical trusses under uniaxial tension and ballast load show that the failure in tension is caused by the difference between the in-plane peel stress and the interlaminar shear stress The failure of compression is mainly caused by the interlaminar shear stress.