Static aeroelastic effects on rudder efficiency of flying wing aircraft
Document Type
Conference Proceeding
Date of Original Version
11-27-2020
Abstract
Effects of aeroelastic deformation on control surface efficiency of a flying wing aircraft are investigated using CFD/CSD coupling method. Results indicate that the equivalent deflection angles of inboard elevon, outboard elevon and split rudder decrease due to aeroelastic deformation. As a result, the control surface efficiency is reduced to different degrees. Therefore, in the design of flying wing aircraft, it is necessary to consider the influence of aeroelastic deformation on control surface efficency. Otherwise the control surface efficiency may be insufficient.
Publication Title, e.g., Journal
Proceedings of 2020 3rd International Conference on Unmanned Systems Icus 2020
Citation/Publisher Attribution
Meng, Cheng, Yuan Kaihua, and He Haibo. "Static aeroelastic effects on rudder efficiency of flying wing aircraft." Proceedings of 2020 3rd International Conference on Unmanned Systems Icus 2020 (2020). doi: 10.1109/ICUS50048.2020.9274846.