A method and device for creating a strength model of an aircraft structure. The method comprises: obtaining a stress unit in a stress model of an aircraft structure (S102); determining a strength unit in a strength model of the aircraft structure on the basis of the stress unit (S104); obtaining an association between the stress unit in the stress model and a stress characteristic, and determining a strength characteristic having an association with the strength unit (S106); obtaining, on the basis of a mapping relationship between the strength unit and the stress unit as well as the stress load in the stress model, the strength load of the strength unit, the strength load being used for indicating the maximum working load of the strength unit (S108); obtaining an allowable load according to the strength characteristic corresponding to the strength unit, the allowable load being used for indicating the maximum load capacity of the strength unit (S110); and comparing the strength load and the allowable load to obtain the safety margin of the aircraft structure (S112). The solution resolves the technical problems in the prior art of complexity and low accuracy in obtaining initial parameters for strength calculation of an aircraft structure.