The invention discloses a fatigue life calibration method based on a
nominal stress method and belongs to the technical field of aircraft
strength design. The method comprises the steps that first, for test pieces of the same material with different surface quality, values of parameters alpha and A of an S-N curve are basically identical, and a theoretical
fatigue limit C is determined as a uniquesensitive parameter needing optimization; second, according to a load stress spectrum designated in advance, mid-value life t<50> corresponding to the load stress spectrum is determined as an objective for optimization, an initial value is set, the value of the theoretical
fatigue limit C is continuously adjusted, the
nominal stress method is repeatedly utilized to calculate the mid-value life till the calculated life is equal to a set target mid-value t<50>, and the corresponding
C value at the moment is a corrected
C value in a three-parameter expression of the S-N curve; and third, the determined
nominal stress method and the corresponding theoretical
fatigue limit C are verified, the parameters obtained through optimization and the nominal stress method are adopted through
verification to perform life prediction under other load spectra, and therefore life calculation results under other load spectra have high precision.