CAJ | 학술논문

研究以降低直升机旋翼激振力为目标的复合材料桨叶结构动力学减振优化设计,分析了桨叶结构特性及桨尖后掠角等参数对N次/转旋翼桨毂振动载荷的影响.在建立的桨叶二维结构特性有限元分析方程中,计入了桨叶剖面翘曲变形的影响,并利用哈密尔顿原理推导了旋翼桨叶的一维非线性运动微分方程.以桨毂交变载荷为目标函数,直接以复合材料桨叶典型剖面构造节点数据、铺层设计参数和桨尖后掠角等为设计变量,引入桨叶挥舞惯量、固有频率和气弹稳定性约束,进行旋翼的动力学优化设计,并结合3片桨叶旋翼的设计进行了算例分析,优化结果使3次/转的桨毂载荷降低了24.9%～33%.
연구이강저직승궤선익격진력위목표적복합재료장협결구동역학감진우화설계,분석료장협결구특성급장첨후략각등삼수대N차/전선익장곡진동재하적영향.재건립적장협이유결구특성유한원분석방정중,계입료장협부면교곡변형적영향,병이용합밀이돈원리추도료선익장협적일유비선성운동미분방정.이장곡교변재하위목표함수,직접이복합재료장협전형부면구조절점수거、포층설계삼수화장첨후략각등위설계변량,인입장협휘무관량、고유빈솔화기탄은정성약속,진행선익적동역학우화설계,병결합3편장협선익적설계진행료산례분석,우화결과사3차/전적장곡재하강저료24.9%～33%.
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 autorotation 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.