This invention belongs to the field of aircraft structural performance evaluation technology, specifically involving a method for determining the allowable stress for durability design of aircraft
metal structures. First, the baseline local allowable stress is calculated under a given material and
load spectrum using fatigue analysis. Considering actual structural factors, an
equivalent stress concentration factor is introduced to correct the baseline local allowable stress. Furthermore, a stress correction factor is introduced based on the correction of theoretical analysis results using fatigue tests. Considering reliability requirements, a fatigue
uncertainty factor is also introduced, thereby establishing a set of analogous calculation formulas to determine the allowable stress for durability design. The calculation formula is: where, [σ max,0 [K] is the reference local allowable stress. te C is the
equivalent stress concentration factor, SCF is the stress correction factor, FSF is the fatigue
uncertainty factor, and C is the
stress concentration factor. load This is the load
conversion factor. This invention simplifies the fatigue
test matrix while ensuring the accuracy of theoretical analysis; it can quickly determine whether the
structural fatigue margin meets the requirements, thus enabling durability analysis to cover the entire load-bearing structure of the aircraft.