THE NUMERICAL ANALYSIS OF THE PEAK STRESS ON FUSELAGE SKIN STEP

In the design of the civil aircraft fuselage panel, the step is widely used to optimize skin. The step which could reduce the structural weight to improve the economy of the civil aircraft is a typical structural design detail for the civil aircraft fatigue analysis. The bad step structure sizing would increase the local stress level, thus the service life of the aircraft could be reduced. For preferably evaluating the fatigue life in the absence of reference data and test data, the numerical equations are given to calculate the peak stress on fuselage skin step. By comparison with analyzing data of 3D finite element model, the precision of numerical equations can be validated. In the early phase of structural design, the numerical simulation method is much simpler and less time consuming than other methods.