全机结构疲劳试验载荷优化技术模拟研究

Simulation Study on Full-scale Aircraft Structure Fatigue Test Load Optimization Technology

在全机疲劳试验中,需要将模拟飞机数倍寿命内不同起落不同飞行状态的试验设计载荷转化为用一套加载设备连续施加的试验载荷。就此问题建立了试验载荷优化处理的数学模型,模型为多任务目标的非线性规划优化模型,优化模型的目标函数综合考虑了弯矩、剪力和扭矩误差,并引入加权系数,以期针对不同部件调节弯、剪、扭误差所占比重。模型用MAT-LAB的Fmincon函数求解。该方法简化了全机疲劳试验载荷优化处理,并已成功应用于某型飞机全机疲劳试验中。

In full-scale aircraft structure fatigue test,it is required changing design load to test load. A load optimized mathematical model is built in this essay,using MATLAB fmincon function to solve this model. Objective function of optimization model includes all of the bending moment,shear force and the torque error,and introduces the weighted coefficient,in order for the different parts of aircraft to adjust bending,shear and torsion error percentage. The method simplifies the full-scale aircraft fatigue test load optimization,and the method has been successfully ap-plied to a type of full-scale aircraft fatigue test.