带后缘小翼的旋翼振动载荷计算

建立了考虑弹性桨叶、刚性小翼的旋翼气动弹性分析模型和旋翼载荷计算方法.以广义质量和广义力的形式描述小翼惯性力和气动力对系统的影响,以非定常/动态失速模型计算剖面气动力,结合基于实验数据修正的组合气动模型计算带小翼部分的剖面气动力,集成大变形桨叶模型考虑弹性变形的非线性,以力积分法计算桨叶剖面振动载荷.通过计算分析与实验结果相比较,验证了建立的气动弹性模型和载荷计算方法.结果表明:建立的桨叶结构模型精度很高,气弹模型能够准确预测旋翼的振动载荷,挥舞弯矩平均误差控制在9.1%,使用修正的小翼气动模型能有效提高小翼运动时桨叶振动载荷的计算精度. 

Vibratory loads prediction of rotor with trailing edge flaps

A rotor aeroelastic model with elastic blade and rigid trailing edge flap and its load calculation method were developed. The inertial forces and aerodynamic forces of flap were described as generalized mass and generalized forces. The aerodynamic forces of the common airfoil were calculated with the unsteady/dynamic stall model, and those of the flapped airfoil were got from a coupled aerodynamic model corrected with experimental data. The nonlinear elastic deformation was considered by a large deformation blade model. The force integration method was used to predict the vibratory structural loads. The predicted results and the test results were compared to verify the aeroelastic model and the load calculation method. The results show the accuracy of the blade structure model is quite high. Vibratory loads of rotor can be calculated well with the aeroelastic model, the average error of flapwise moment is 9.1%. Prediction in the vibratory loads of blade with flap motion is implemented with corrected flapped airfoil aerodynamic model.