Fatigue load optimization and test verification of the full-scale aileron
LIU Lu
LI Wang
ZHANG Wei
LI Miao
WANG Pengfei
Abstract：In the fatigue test of aircraft wing structural components,the fatigue design loads need to be optimized so as to reduce the bending,shear and torsion load errors applied during the test.Firstly,taking the full-scale aileron as the research object,the fatigue test load optimization model was established;then the objective function was solved by using the weighted summation method,and the optimized load at each loading point were obtained.The results show that the load is more suitable for loading design than the load assigned by the minimum energy method,and the load distribution is closer to the design load.Finally,the full-scale aileron fatigue test was designed and carried out,and the test strains were basically the same as the calculated results.It proves that the model can be used for fatigue test load optimization of large-scale components.
Keywords：Fatigue testFull-scale aileronLoad optimizationObjective function
Publication Date：2025-11-15
Online Publishing Date：2026-09-12(First online date of this platform, not the publication date of the document)
Pages：7( 107-113 )