滑动蒙皮变后掠气动力非定常滞回与线性建模

UNSTEADY DYNAMIC AERODYNAMIC HYSTERESIS EFFECTS AND LINEAR MODELING ABOUT THE SLIDE-SKIN SWEPT-ANGLE MORPHING WING

针对低速不可压条件下滑动蒙皮方式变后掠过程中非定常动态气动特性开展了3方面的研究工作:(1)飞行器变形过程中非定常动态气动特性风洞试验技术研究;(2)变形过程中滞回效应研究和机理分析;(3)基于风洞试验结果开展变形过程中非定常动态气动力线性建模.初步研究表明:(1)采用强迫振荡法可以有效地获取变形过程中非定常动态气动力滞回效应;(2)造成变形过程中气动滞回效应的机理有两个,即"动边界效应"和"流场结构滞回效应",造成滞回效应的机理可能主要在于后者;(3)引入升力系数和俯仰力矩系数随后掠角变化率的动导数概念,可以建立变形过程中非定常动态气动力线性模型.

In this paper, three jobs were carried out about the unsteady dynamic aerodynamic effects during the sliding skin swept-angle wing morphing under the incompressible condition. （1） The wind tunnel experimental measure technologies about the unsteady dynamic aerodynamic characteristic during aircraft morphing were studied; （2） The aerodynamic hysteresis effects during the swept-angle morphing were investigated and the mechanisms were analyzed initially; （3） The unsteady dynamic aerodynamic linear models were made during morphing based on the experimental results. The primary research indicated that： （1） the method of the forced periodic morphing could obtain the unsteady dynamic aerodynamic hysteresis effects effectively; （2） there were two mechanisms which bring the effects： ＂The moving boundary effect＂ and ＂The flow structure hysteresis effect＂. And the hysteresis effects in this paper might be caused by the latter mainly; （3） the dynamic derivatives of the lift and pitching moment coefficients to the morphing rate of swept-angle were defined in this paper, which can make the linear model about the unsteady dynamic aerodynamics during morphing.