基于带主动矩控制的全机疲劳试验载荷处理技术

飞机结构疲劳试验是型号取证、立项乃至运营的一种试验手段。全尺寸飞机结构疲劳试验更是一项庞大的试验体系和工程,如何准确地施加飞机各部段载荷,是模拟飞机真实受载的关键。全尺寸飞机存在考核部位多、载荷种类多且复杂多变、机体部分部段空间有限、试验加载设备难以安装等因素,往往需要将试验载荷简化处理,在有限的加载作动筒下,尽可能真实地施加飞机的真实受载。因此,在疲劳试验载荷处理中,需要选取某些特定的控制剖面,经过特定的运算,保证加载点载荷对这些剖面的弯矩、剪力、扭矩与原始载荷对控制剖面的弯矩、剪力、扭矩误差控制在一定范围内,通过一套加载装置完成所有工况下的载荷施加,进而准确地模拟飞机的真实受载。因此,推导出一种带主动矩控制的全机疲劳试验载荷处理方法,结合某型飞机全机疲劳试验进行验证和实施,达到理想的效果,满足试验加载要求。

The fatigue test of aircraft structure is a kind of test means for obtaining evidence of model,establishing project and even operating.The fatigue test of full-scale aircraft structure is a huge test system and engineering.How to apply the load of every part of the aircraft accurately is the key to simulate the real load of the aircraft.Due to the factors such as the large number of testing parts,the variety and complexity of loads,the limited space of parts of the airframe and the difficulty of installing test loading equipment,it is often necessary to simplify and deal with the test loads,in the case of a limited number of loading actuators,the actual loading of the aircraft is applied as realistically as possible.Therefore,in the fatigue test load processing,we need to select some specific control section,through the specific calculation,to ensure that the bending moment,shearing force,torsion of the loading point and the original load on the control section are controlled within a certain range,through a set of loading device to complete the load under all operating conditions,and then accurately simulate the real load of the aircraft.Therefore,a load treatment method of fatigue test with active moment control for the whole aircraft is derived,which is verified and carried out in combination with the whole aircraft fatigue test of a certain type of aircraft.