| Citation: | TIAN Yu, KOU Peng, YAO Xuanyu, et al. Modeling and analysis of slipstream effect during powered yaw control in distributed electric propulsion aircraft[J]. Journal of Aerospace Power, 2025, 40（8）：20230535 doi: 10.13224/j.cnki.jasp.20230535
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During the process of differential thrust, the slipstream effect of the electric propulsors has varying impacts on lift and drag distribution, resulting in additional lateral moments. This is a critical consideration in yaw control. To address this issue, a vortex-tube vortex-ring coupling model was established to evaluate the aerodynamic interference between the electric propulsors and wing. Utilizing the established model, the effects of propeller slipstream on the lateral moment were computed. This refinement enabled consideration of the slipstream effect in the lateral-directional flight dynamics equations for distributed electric propulsion aircraft, and facilitated the design of a powered yaw control system. Yaw control simulations were conducted. The computed results were compared with the CFD results by capturing a moment in-flight during yaw. The simulation results demonstrated that the established vortex tube-vortex ring coupled model effectively captured the slipstream effect on the wing of the distributed electric propulsion system. Specifically, the calculation error for the roll moment generated by slipstream effects was 3.22%, and the computation time was less than 5 min.
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