机身壁板剪切试验方法研究

RESEARCH ON TEST METHOD OF FUSELAGE PANEL SUBJECTED TO SHEAR LOAD

机身壁板剪切试验方法研究是飞机结构强度研究的重要内容,基于机身壁板剪切载荷的承力特性,给出了一种新的剪切试验方法。该方法采用"D"夹具和弓形角盒模拟机身圆筒结构,用合页连接"D"夹具和机身壁板组成单闭室盒段,以扭转单闭室盒段的方式施加剪切载荷。设计加工了机身壁板试验件和试验装置,并完成验证试验。验证试验实测应力分布较为合理,且与理论解基本相符,证明该试验方法是正确的和工程可行的。该方法避免设置与机身壁板尺寸相近的过渡段和加载段,减少装配工作量,节约研究成本,并已应用于民用飞机机身壁板剪切稳定性试验。

The test method of fuselage panel subjected to shear load is an important technique for aircraft structure strength research. A new shear test method is proposed based on the property of aircraft fuselage panel subjected to shear load. ＂D＂jig and arch angle connectors is designed to simulate the circular structure of fuselage,and the shear stress is applied through the torsional form of single closed box structure,consisting of ＂D＂jig and fuselage panel through hinge. A test panel and a set of fixtures were designed and manufactured,and validation test were conducted. Validation test verifies the validity and engineering feasibility of this method,and the stress distribution of panel in test is uniform as well as in a good agreement with theoretical analysis. In addition,this test method avoids to design a transition section and a loading section with the similar length of aircraft fuselage panel,and saves assembly work and test expenses. The stability test of the fuselage panel on civil aircraft adopts this new method at present.