Hundreds or thousands of load conditions are typically simulated using a single set of loading devices in air-craft structural fatigue tests, making it critical to accurately convert design loads into test loads. This paper introduces existing fatigue test load equivalent algorithms and proposes a novel method for calculating loading point positions based on test load spectra. Additionally, a fatigue test load optimization function incorporating Miner’s linear cumulative damage theory is established. Taking a fighter aircraft wing as an example, the equivalent results of different objective functions are compared, and their advantages and disadvantages are analyzed. The results demonstrate that the proposed algorithm achieves optimal performance under limited loading points by balancing load equivalence and cumulative damage effects. Finally, future research directions are discussed to enhance load application accuracy and improve the reliability of test data through integrated finite element modeling and field-measured spectrum conversion.