低振动旋翼桨尖代理优化设计  

Rotor blade tip shape optimization for vibration reduction based on surrogate model

作　　者：邓旭东[1] 高乐[1] 邓景辉[1] DENG Xu-dong;GAO Le;DENG Jing-hui(Science and Technology on Rotorcraft Aeromechanics Laboratory,China Helicopter Research and Development Institute,Jingdezhen 333001,China)

机构地区：[1]中国直升机设计研究所旋翼动力学重点实验室,江西景德镇333001

出　　处：《振动工程学报》2021年第1期108-115,共8页Journal of Vibration Engineering

基　　金：航空科学基金资助项目(2018ZA02001)。

摘　　要：为探索直升机低振动旋翼的工程设计方法,将代理优化与旋翼气弹耦合分析相结合,开展了旋翼桨尖几何外形设计,推导了非平直桨叶气弹动力学方程,训练了旋翼功率、模态阻尼以及振动载荷预测的Kriging代理模型。以气动性能与气弹稳定性为约束,以桨毂振动载荷最小化为目标,采用自适应加点准则设计了优化流程。以某旋翼为例,计算了其气动性能与振动载荷,通过与试验结果对比,验证了气弹模型的有效性。对该基准旋翼0.9R-1.0R(R为旋翼半径)桨叶段的后掠、下反以及扭转分布进行了优化设计,结果表明,基于样本点最小间距的自适应加点准则能够实现目标函数与约束函数代理精度的同步提升。通过优化结果可行性分析,得到了一种"双后掠+上、下反"桨尖构型,旋翼桨毂振动载荷降低了25%。To establish efficient design methods of a helicopter rotor with low vibration,blade tip shape design is conducted through the combination of surrogated-based optimization and aeroelastic analysis.The aeroelastic equations of rotor blades with unstraight tips are derived.The Kriging surrogate-based models for predicting rotor power,modal damping and vibratory loads are trained.By using the aerodynamic performance and aeroelastic stability as constrains and minimizing the hub vibratory loads as objective,optimization strategy is developed based on an adaptive infill sampling criteria.Taking a scaled model rotor as an example,its performance and vibratory loads are calculated.The aeroelastic model validity is obtained through the comparison with experimental results.Design optimization of the blade sweep,droop and twist distribution from 0.9 R to 1.0 R is performed.The result indicates that the accuracy of the surrogates of objective function and constraint functions can be improved simultaneously with this adaptive infill sampling criteria based on minimum distance between two training samples.Through the feasibility analysis for optimization results,an optimized blade with double swept and negative/positive anhedral tip is obtained,which results in a 25%reduction of the vibratory hub loads.

关 键 词：旋翼 桨尖 气弹分析 减振 代理优化 

分 类 号：V275.1[航空宇航科学与技术—飞行器设计]