Split parallel simulation method for modeling of aircraft electromechanical system

The invention discloses a split parallel simulation method for modeling of an aircraft electromechanical system, which comprises the following steps of: analyzing a modal complex characteristic value and frequency response of an aircraft electromechanical system model through a frequency domain analysis principle, calculating and finding a detachable position of the system model, and splitting the system model into a plurality of models with independent input quantities and output quantities; stripping and extracting the input quantity and the output quantity of each split model to become a single data variable, defining one end of each split model as an output end, defining the other end of each split model as an input end, arranging an input module and an output module at the input end and the output end respectively, and writing variable data; adding a capacitive link or an inertial weight link, adding an adaptive module, integrating and unifying models of different software modeling, and achieving parallel simulation. The models do not need to be simplified, simulation precision is not sacrificed, and the architecture of the system becomes clear.