基于变弯度后缘的机翼阵风响应减缓数值研究

A mathematical model for gust response analysis is established for a wing with camber morphing trailing edges, and a simulation study of gust response alleviation is carried out. The computational fluid dynamics method is used to calculate the generalized unsteady aerodynamic force under the given dynamic morphing of the trailing edge, and the generalized aerodynamic force model under the dynamic deflection of the trailing edge is established based on the state observer method,. The panel method is used to calculate the generalized aerodynamic force caused by mode motion and gust, while the generalized predictive control (GPC) method is used in the design of gust alleviation control law. On this basis, the aerodynamic characteristics of the camber morphing trailing edge and the traditional hinged flap are compared. The simulation results show that the GPC method based on the camber morphing trailing edge can effectively alleviate the wing-tip acceleration response caused by gust, and the wing-tip acceleration reduction efficiency is 44.25%. The wing with morphing trailing edge has a more continuous pressure distribution on the upper and lower surfaces, a greater impact on the aerodynamics, and higher acceleration reduction efficiency. The use of camber morphing trailing edges for gust alleviation has a broader application prospect.