孙俊峰, 卢风顺, 黄勇, 等. 旋翼翼型气动设计与评估软件HRADesign[J]. 空气动力学学报, 2021, 39(4): 59−68. doi: 10.7638/kqdlxxb-2019.0106
引用本文: 孙俊峰, 卢风顺, 黄勇, 等. 旋翼翼型气动设计与评估软件HRADesign[J]. 空气动力学学报, 2021, 39(4): 59−68. doi: 10.7638/kqdlxxb-2019.0106
SUN J F, LU F S, HUANG Y, et al. Rotor airfoil aerodynamic design and evaluation software HRADesign[J]. Acta Aerodynamica Sinica, 2021, 39(4): 59−68. doi: 10.7638/kqdlxxb-2019.0106
Citation: SUN J F, LU F S, HUANG Y, et al. Rotor airfoil aerodynamic design and evaluation software HRADesign[J]. Acta Aerodynamica Sinica, 2021, 39(4): 59−68. doi: 10.7638/kqdlxxb-2019.0106

旋翼翼型气动设计与评估软件HRADesign

Rotor airfoil aerodynamic design and evaluation software HRADesign

  • 摘要: HRADesign系统作为通用旋翼翼型气动设计和评估系统,研制目的主要是为工业设计环境提供通用、高效、鲁棒的优化设计架构,应用于各类旋翼翼型族的设计,提高旋翼翼型设计的效率和精度,以满足先进直升机对高性能旋翼翼型的迫切需求。旋翼翼型设计技术是直升机旋翼设计的核心技术,旋翼翼型的优化设计具有多点、多目标、强约束的特点。HRADesign系统针对旋翼翼型设计的特点,发展了多目标进化算法、PCA多目标降维技术、Kriging代理模型、基于CST方法的翼型参数化技术以及高精度CFD等优化设计技术,构建了基于进化算法的多目标优化流程。通过详细介绍平台的系统架构、主要的功能模块以及多目标优化流程,展现了系统架构设计的灵活性和功能模块的完备性。通过ADODG基准测试算例、某厚度旋翼翼型常规多目标优化算例和考虑多目标降维的优化算例进行了系统功能验证,优化结果表明,在满足约束的条件下,优化后的旋翼翼型和基准翼型相比,综合性能都有明显改善,验证了优化设计系统的有效性、可靠性。

     

    Abstract: The HRADesign is a general-purpose rotor airfoil aerodynamic design and evaluation software platform. The main purpose of developing this platform is to provide an universal, efficient, high-fidelity, and robust design optimization framework for designing high-performance rotor airfoils of advanced helicopters. Rotor airfoil design, which is a multi-point, multi-objective, and strong-constrained process, is one of the core techniques of helicopter rotor aerodynamic design. According to the characteristics of rotor airfoil design, the HRADesign has developed multi-objective evolutionary algorithms, a PCA multi-objective dimensionality reduction technique, an airfoil parameterization based CST method, Kriging surrogate models, high-fidelity CFD analysis tools and so on, and has also constructed a multi-objectives optimization process based on evolutionary algorithms. By introducing the platform architecture, the main functional modules, and the multi-objective optimization process in detail, the flexibility of the system architecture design and the completeness of the functional modules are demonstrated. At last, system functions had been verified through three examples including a ADODG benchmark case, a conventional multi-objective rotor-airfoil optimization, and an optimization test considering multi-objective dimensionality reduction. The results show that the overall performance of the optimized rotor airfoil is significantly improved under the constraints, which verifies the effectiveness and reliability of the optimization system.

     

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