基于虚拟载荷校准试验的襟翼曲柄测载方法

飞行载荷测量是验证飞机结构完整性，完成飞机定型必需的试验项目。基于应变法的飞行载荷测量方法通过地面校准试验构建应变与加载载荷之间的对应关系，然后将飞行实测应变代入载荷模型求得飞行载荷。某型飞机襟翼驱动曲柄几何外形不规则，具有轴向弯折、截面非对称等特点，载荷测量存在困难。基于该襟翼驱动曲柄的运动机理及襟翼操纵机构的传力路径研究，对曲柄进行受力分析，提出曲柄载荷测量方法，并利用虚拟载荷校准试验的手段对本方法进行验证。结果表明，本文方法是正确、有效的。

A flap crank load measurement method based on virtual load calibration test

The flight load measurement is a test item that is necessary to verify the structural integrity of the aircraft and complete the aircraft's finalization. In the flight load measurement based on the strain method, load equation of strain and load is constructed by a load calibration test, and then the measured flight strain is substituted into the load equation to obtain the flight load. Since the geometry of a certain type of aircraft's flap drive crank is irregular and has axial bending and asymmetrical cross section, it is difficult to measure the load of the flap drive crank. Based on the motion mechanism of the flap drive crank and the force transmission path of the flap control mechanism, the crank force is analyzed and a crank load measurement method is proposed. The method is verified by the virtual load calibration test. The results show that the method is correct and effective.