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旋转的螺旋桨滑流掠过机翼将使机翼的气动特性发生改变,在高空超长航时无人机的设计中有必要对大柔性机翼气动弹性问题的螺旋桨滑流影响进行分析.运用Prandtl修正的动量叶素理论分析螺旋桨滑流及面内载荷;采用兰金涡核模拟滑流对机翼的诱导速度;采用三维升力线方法计算机翼定常气动力,利用曲面样条插值方法解决结构/气动耦合问题,并结合非线性有限元静力学计算方法,建立了螺旋桨滑流及面内载荷作用下大柔性机翼静气动弹性问题的快速迭代求解方法.以某大展弦比螺旋桨机翼为例,采用文中所建立方法对其静气动弹性特性进行计算研究.结果表明,旋转的滑流改变了机翼绕流当地攻角,从而影响了机翼气动力和变形分布,且在小前进比时影响更大.所建立的分析方法简便高效,在初步设计阶段有较好的应用前景翼绕流当地攻角,从而影响了机翼气动力和变形分布,且在小前进比时影响更大.所建立的分析方法简便高效,在初步设计阶段有较好的应用前景.
It is necessary to analyze the influence of the propeller slip caused by the aerodynamic flexibility of a large flexible wing in the design of high-altitude long-flight UAS due to the rotating propeller slipstream passing the wing will change the aerodynamic characteristics of the wing. The propeller slipstream and in-plane loads were analyzed by Prandtl’s modified momentum vane theory. The induced velocity of wing was simulated by Rankine core, and the steady aerodynamic force was calculated by three-dimensional lift line method. The surface spline interpolation method was used to solve the structure / Aerodynamic coupling problem and a nonlinear iterative finite element static method, a fast iterative method for solving the problem of static aerodynamic elasticity of a large flexible wing under propeller slip surface and in-plane load is established. With a large aspect ratio propeller wing As an example, the static and dynamic elastic properties of the wing are calculated by the method established in this paper.The results show that the rotating slipstream changes the local angle of attack around the wing, which affects the aerodynamic and deformation distribution of the wing, The influence is greater than the time.The established analysis method is simple and efficient, and has better application prospects in the preliminary design stage. The wing winds around the local angle of attack, thus affecting the aerodynamic force of the wing Strain distribution, and a greater impact than at small forward analysis method established is simple and efficient, there is a good prospect in the preliminary design stage.