前行桨叶概念旋翼气动弹性响应分析

基于CFD/CSD松耦合策略,建立了前行桨叶概念（ABC）旋翼气动弹性分析方法.CFD计算中以非定常Euler/N-S方程为控制方程,通过动态重叠网格及动网格方法实现桨叶的运动及变形;桨叶结构模型通过中等变形梁理论得到;CFD和CSD数据每隔一个旋转周期交换一次.以XH-59A直升机为例,对不同前飞速度下的旋翼效率进行了分析,计算结果与试验值吻合良好.然后对旋翼振动载荷、桨尖间距、升力偏移量及桨叶载荷进行了分析,研究了前飞速度、旋翼交叉角、提前操纵角等参数对上述动力学性能的影响.该文方法具有很好的分析精度和工程适用性,分析结果可为前行桨叶概念旋翼设计提供重要参考.

Aeroelastic Response Analysis for Advancing Blade Concept Rotors

Based on the loose coupled CFD/CSD simulation, an aeroelastic response analysis methfor advancing blade concept rotors was developed. The unsteady Euler/N - S equations were used in CFD analysis, and the overset grid and dynamic grid techniques were implemented to simulate the blade motion and deformation. The structure model of blades was established by moderate deflection beam theory. The CFD and CSD results exchanged after each rotation cycles. The XH -59A heli- copter was taken as example, the aerodynamic performance on different airspeed has been studied, and the results fitting well with the flight test data. Then the influences of parameters such as the forward speed, crossover angle, and control phase angle on the rotor vibration loads, tip clearance, lift offset and blade root loads were investigated. This method was accurate and practical, the results could provide important basis for advancing blade concept rotor designing.