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超声速民机高效高可信度声爆/气动多学科优化方法

单程军1,贡天宇1,易理哲1,杨浩辉1,龙垚松2   

  1. 1. 华中科技大学
    2. 华中科技大学航空航天学院
  • 收稿日期:2024-04-22 修回日期:2024-09-21 出版日期:2024-09-23 发布日期:2024-09-23
  • 通讯作者: 龙垚松

High-efficiency and High-reliability Sonic Boom/Aerodynamic Multidisciplinary Optimization Mehtod for Supersonic Civil Aircraft

  • Received:2024-04-22 Revised:2024-09-21 Online:2024-09-23 Published:2024-09-23

摘要: 如何降低声爆强度和提高巡航气动效率是超声速民机的关键研究问题之一。针对目前声爆/气动多学科优化研究中存在的高可信度优化效率低和忽略大尺度布局参数等问题,提出了一种超声速民机高效高可信度声爆/气动多学科优化方法。自研了一套基于非线性Burgers方程的远场声爆传播程序“BoomProp”,结合基于CFD的近场流动预测方法,建立了高可信度地面声爆强度预测流程。采用基于CEHVIM(Constrained Expected Hypervolume Improvement Matrix,CEHVIM)准则的高效全局约束多目标优化算法,耦合高维不规则设计空间的最优拉丁超体试验设计方法、布局参数化自动成型、网格自动生成与高可信度声爆/气动性能预测方法,搭建了超声速民机高效高可信度声爆/气动多学科优化平台。基于该平台针对机翼布局开展了声爆/气动多学科优化,优化结果在声爆与阻力性能方面有较为明显提升,同时与基于Kriging代理模型的NSGA-Ⅱ多目标遗传算法对比,综合验证了所提出方法的有效性与高效性。

关键词: 超声速民机, 非线性Burgers方程, 计算流体力学, 声爆, 多学科优化方法, 高效全局约束多目标优化方法

Abstract: One of the key research challenges for supersonic civil aircraft is reducing sonic boom intensity and improving cruise aerody-namic efficiency. Addressing issues such as low optimization efficiency in high-fidelity optimization and the neglect of large-scale configuration parameters in current sonic boom/aerodynamic multidisciplinary optimization studies, a highly efficient and high-fidelity multidisciplinary optimization method for supersonic civil aircraft is proposed. A self-developed far-field sonic boom propagation program, "BoomProp," based on the nonlinear Burgers equation, was integrated with a near-field flow predic-tion method using CFD to establish a high-fidelity ground-level sonic boom intensity prediction process. An efficient global constrained multi-objective optimization algorithm based on the CEHVIM (Constrained Expected Hypervolume Improvement Matrix) criterion was adopted, coupled with the optimal Latin hypercube design method for high-dimensional irregular design spaces, automated layout parameterization, mesh generation, and high-fidelity sonic boom/aerodynamic performance prediction methods, to build a highly efficient and high-fidelity multidisciplinary optimization platform for supersonic civil aircraft. Using this platform, multidisciplinary optimization for sonic boom and aerodynamics was conducted on wing configurations, yielding significant improvements in both sonic boom and drag performance. Additionally, a comparison with the NSGA-II multi-objective genetic algorithm based on the Kriging surrogate model comprehensively validated the proposed method’s effective-ness and efficiency.

Key words: Supersonic civil aircraft, Nonlinear Burgers equation, Computational Fluid Dynamics, Sonic boom, Multi-disciplinary optimization method, Efficient global-constraint multi-objective optimization method

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