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首页> 外文期刊>Chinese journal of aeronautics >Composite Rotor Blade Design Optimization for Vibration Reduction with Aeroelastic Constraints
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Composite Rotor Blade Design Optimization for Vibration Reduction with Aeroelastic Constraints

机译：具有气动弹性约束的减振复合转子叶片设计优化

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摘要

The paper presents an analytical study of the helicopter rotor vibratory load reduction design optimization with aeroelastic stability constraints. The composite rotor blade is modeled by beam type finite elements, and warping deformation is taken into consideration for 2-dimension analysis, while the one-dimension nonlinear differential equations of blade motion are formulated via Hamilton's principle. The rotor hub vibratory loads is chosen as the objective function, while rotor blade section construction parameter, composite material ply structure and blade tip swept angle as the design variables, and au-torotation inertia, natural frequency and aeroelastic stability as the constraints. A 3-bladed rotor is designed, as an example, based on the vibratory hub load reduction optimization process with swept tip angle and composite material. The calculating results show a 24.9%-33% reduction of 3/rev hub loads in comparison with the base-line rotor.
机译：本文对具有气动弹性稳定性约束的直升机旋翼减振设计优化进行了分析研究。利用梁式有限元对复合材料转子叶片进行建模，并考虑了翘曲变形进行二维分析，并利用汉密尔顿原理建立了叶片运动的一维非线性微分方程。以转子轮毂的振动载荷为目标函数，以转子叶片截面构造参数，复合材料帘布层结构和叶片尖端后掠角为设计变量，以自转惯性，固有频率和气动弹性为约束条件。例如，基于带有扫掠尖角和复合材料的减振优化过程，设计了三叶转子。计算结果表明，与基线转子相比，3 / rev轮毂负载降低了24.9％-33％。

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