Aerodynamic/aeroacoustic variable-fidelity optimization of helicopter rotor based on hierarchical Kriging model
Aerodynamic/aeroacoustic variable-fidelity optimization of helicopter rotor based on hierarchical Kriging model
复制标题
基于分层克里格模型的直升机旋翼气动/气动声学变保真优化
DOI：
10.1016/j.cja.2019.09.019
复制
发表时间：
2020-02-01
影响因子：
5.7
通讯作者：
Zhang, Liang
中科院分区：
文献类型：
--
作者：
Bu, Yuepeng;Song, Wenping;Zhang, Liang
旋翼噪声是制约直升机发展的最重要原因之一，因此，同时考虑气动声学和气动性能的旋翼桨叶优化设计一直是研究关注的焦点。对于设计变量较多的复杂转子设计问题，传统Kriging模型的计算效率有待提高。因此，分层克里格（HK）模型在本研究中用于转子优化设计。采用基于FW-H-pds方程的RANS求解器和声学方法，建立了一种基于HK模型的悬停旋翼高维气动/气动声学优化方法。采用现有的HK模型和新的渗透抽样准则，设计变量由原来的20个增加到53个。两个解析函数测试案例的结果表明，HK模型计算效率高、精度高。在此基础上，基于HK模型和高维设计变量，对悬停状态下的旋翼桨叶进行了气动/气动声学性能优化设计。该目标函数通过降低声压的绝对峰值来改善旋转噪声特性。此外，推力，悬停效率，实度和翼型厚度的约束严格满足。优化结果表明，Kriging模型经过248次迭代后达到降噪2.87 dB的目标，而HK模型经过164次迭代后才达到降噪2.87 dB的目标。HK模型的优化效率明显高于传统的Kriging模型。在分析的情况下，HK模型节省了克里格模型所用时间的35%。(C)2019中国航空航天学会。制作和主办：Elsevier Ltd.
Rotor noise is one of the most important reasons for restricting helicopter development; hence, the optimization design of rotor blade considering aeroacoustic and aerodynamic performance at the same time has always been the focus of research attention. For complex rotor design problems with a large number of design variables, the efficiency of the traditional Kriging model needs to be improved. Thus, Hierarchical Kriging (HK) model is employed in this study for rotor optimization design. By using the validated RANS solver and acoustic method based on the FW-H-pds equation, an efficient aerodynamic/aeroacoustic optimization method for high-dimensional problem of rotors in hover based on HK model is developed. By using present HK model and new infill-sampling criteria, the number of design variables is increased from less than 20-53. Results of two analytical function test cases show that the HK model is efficient and accurate in calculation. Subsequently, the helicopter rotor blade is optimally designed for aerodynamic/aeroacoustic performance in hover based on the HK model with high dimensional design variables. The objective function is adopted to improve the rotational noise characteristics by reducing the absolute peak of the acoustic pressure. In addition, the constraints of thrust, hover efficiency, solidity, and airfoils thickness are strictly satisfied. Optimization results show that the Kriging model finds the objective of reducing the noise by 2.87 dB after 248 iterations while the HK model does it only after 164 iterations. The optimization efficiency of the HK model is significantly higher than that of the traditional Kriging model. In the case analyzed, the HK model saves 35% of the time used by the Kriging model. (C) 2019 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd.