| In this paper, solving the unsteady N-S equation and structure dynamics equations is used tonumerical calculating and analysis about two-degree-of-freedom airfoil’s flutter suppression and gustalleviation unsteady response process.cell-centered scheme is applied to solve the two-dimensional N-S equations, and the dual-timestepping for multistage schemes is used for time marching. Spalat-Allmaras One-Equation turbulencemodel is employed to simulate turbulent flows. An approximate simplified method called elasticdeformation is taken to form dynamic grid of the airfoil or wing. Raileigh-Ritz method is used tosolve the structure dynamics equations. Eroelastic problems is solved by loosely coupling the flowfield and the structural field. Grid velocity method is used to simulate the influence of the gust. Then alot of open-loop and closed-loop control methods is used to realize gust alleviation and fluttersuppression.the results of “1-cos” gust response process simulate show: little changes in the value of themaximum lift coefficient of fixed-wing and airfoil gust, the airfoil’s maximum acceleration of the upsand downs in simulated occurs in the second cycle after the gust, and the maximum pitch accelerationreachs105magnitude. The open loop control method can achieve a50%off the gust responds, whilethe closed-loop control method can only reach20%off the gust responds.Established an airfoil flutter analysis calculation method, and the calculation results go well withreference results. The open-loop control of the flutter suppression is not ideal. Subsonic, theclosed-loop control method can quickly suppressed flutter, but this control method does not apply tothe transonic flutter suppression. |
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