飞机静力试验中机翼的载荷分配研究

Research on Load Distribution of Wing in Aircraft Static Test

针对飞机静力试验加载的问题,为使得试验加载力反映飞机受力特性,由载荷分配前输入的典型剖面上剪力、弯矩、扭矩推导出相邻剖面之间的剪力、弯矩、扭矩,通过构造带内力约束的拉格朗日极值函数求出试验加载力,将载荷分配前输入的内力与试验载荷分配后产生的内力进行对比分析,可以得出:通过构造带内力约束的拉格拉日极值函数法分配得到的试验载荷符合载荷的传递,能够满足飞机静力试验加载的要求,可以用于飞机静力试验的加载。

Referring to the problem of impropriety loading in the aircraft static test, the section internal forces were deduced from the shearing force and bending moment and torsional moment of its neighboring sections, and the Lagrange function with internal forces restriction was imported to calculate the loading force in the static test, in order to reflect the aircraft forcing characteristic more reality in the test loading process. Comparing the original internal force before load distribution to the calculating internal force after load distribution, it was known that the internal force calculated from the method of constructing the Lagrange function with internal forces restriction was consistent to the real transferring loading, which satisfies the in the aircraft static test. requirement of the static test, the method can be applied