Abstract: To achieve the yaw control of a distributed propulsion aircraft through the thrust difference between multiple propellers, the research has been conducted. Firstly, based on the differential method, the Computational Fluid Dynamics (CFD) method is used to calculate the dynamic stability derivative of the distributed propulsion aircraft, which is used to construct the aerodynamic force and moment models in the dynamic equations. Then the 6-DOF nonlinear flight dynamic model of the distributed propulsion aircraft is established. Based on the principle of time scale separation, The flight control system of the distributed propulsion aircraft is divided into inner and outer loop subsystems, and the dynamic inverse control method based on the Extended state observer (ESO) is used to design the control algorithm for the subsystems. Finally, the control simulation is carried out with yaw control as the goal. The results show that the thrust/control coupling method designed by the dynamic inverse control method based on ESO achieves the expected control performance and realizes 90 degree yaw control. The introduction of ESO enhances the robustness of the dynamic inverse controller, enabling the distributed propulsion aircraft to effectively resist external disturbances during the control process.