旋翼异形桨叶大变形气弹动力学分析与试验研究

摘要

Aeroelastic model is developed using large deflection theory. Based on the two-dimensional cross-section analysis and one-dimensional nonlinear beam analysis, the strain energy in the composite rotor blade is deduced. The generalized strains are expressed by the variables describing the elastic motion of a reference line along the axis of the rotor blade, and all the nonlinear terms are included in the formulation. The kinetic energy and aerodynamic force are also incorporated. To verify the correctness of the analysis result, a special-shaped blade mode test is conducted. Correlations between the analysis results and the experimental data from Princeton beam test and Minguet＇ s composite beam experiments also show that this method is valid for large deflection analysis of composite rotor blades. Aeroelastic analysis of helicopter rotor and influence study of blade sweep are implemented.%采用大变形梁理论建立一种旋翼桨叶气弹动力学分析方法,桨叶应变能分析分解为一维非线性分析和二维剖面特性分析,将应变能方程中的广义应变用桨叶参考轴线处弹性运动表示,保留所有非线性项,推导出的桨叶大变形应变能公式在气弹分析中使用更为方便.集成惯性力与气动力计算模型形成气弹分析方法.异形桨叶模态试验的计算结果与试验测试结果以及国外大变形梁试验结果的比较,验证了本文结构模型的正确性.计算了旋翼的气弹稳定性,研究了异形桨叶几何参数对旋翼桨叶气弹稳定性的影响,计算结果表明了分析方法的有效性,分析精度得以明显提高.