航空学报 > 2023, Vol. 44 Issue (4): 126664-126664   doi: 10.7527/S1000-6893.2022.26664

基于离散伴随的高超声速密切锥乘波体气动优化设计

刘超宇1, 屈峰1(), 孙迪1, 刘传振2, 钱战森3, 白俊强1   

  1. 1.西北工业大学 航空学院,西安  710072
    2.中国航天空气动力技术研究院,北京  100074
    3.中国航空工业空气动力研究院,沈阳  110034
  • 收稿日期:2021-11-16 修回日期:2021-11-30 接受日期:2022-01-04 出版日期:2023-02-25 发布日期:2022-01-11
  • 通讯作者: 屈峰 E-mail:qufeng@nwpu.edu.cn
  • 基金资助:
    国家自然科学基金(11972308);陕西省自然科学基金(11802245)

Discretized adjoint based aerodynamic optimization design for hypersonic osculating-cone waverider

Chaoyu LIU1, Feng QU1(), Di SUN1, Chuanzhen LIU2, Zhansen QIAN3, Junqiang BAI1   

  1. 1.School of Aeronautics,Northwestern Polytechnical University,Xi’an  710072,China
    2.China Academy of Aerospace Aerodynamics,Beijing  100074,China
    3.AVIC Aerodynamics Research Institute,Shenyang  110034,China
  • Received:2021-11-16 Revised:2021-11-30 Accepted:2022-01-04 Online:2023-02-25 Published:2022-01-11
  • Contact: Feng QU E-mail:qufeng@nwpu.edu.cn
  • Supported by:
    National Natural Science Foundation of China(11972308);Natural Science Foundation of Shaanxi Province(11802245)

摘要:

基于定平面形状的密切锥乘波体设计方法能够显著提高传统乘波体的设计灵活性和整体升阻特性。但是该类乘波体在设计时忽略了三维效应、黏性效应以及头部/前缘的钝化效应,在设计工况下仍会出现溢流,升阻比难以达到最优;另外,这类乘波体仍具有传统乘波体在偏离设计条件下气动特性会出现恶化的不足。因此,有必要在考虑黏性的情况下,针对定平面形状的密切锥乘波体开展全机气动优化设计。结合基于全速域通量求解方法和RANS湍流模型的高精度CFD求解器、鲁棒的结构网格变形方法、自由变形参数化方法、离散伴随方法以及序列二次规划算法,实现了基于离散伴随的高超声速飞行器气动优化设计方法。基于上述方法,针对定平面形状的密切锥乘波体开展了单点和多点的三维整机气动优化设计。在400万多块结构网格、600个设计变量以及303个设计约束条件下,所采用的离散伴随优化方法仅花费2 240CPU小时和3 360CPU小时即完成了三维整机单点和多点的优化设计。结果表明,相较于初始构型,单点优化得到的构型在设计状态下的升阻比提升了近5%;多点优化得到的构型可保证在设计点状态升阻特性没有损失的同时,将非设计点的升阻比提升10%以上,进而在一定程度上改善了定平面密切锥乘波体的理论局限性。

关键词: 高超声速, 气动优化设计, 离散伴随, 密切锥乘波体, 定平面

Abstract:

The design method of osculating-cone waverider based on planform-controllable shape can significantly improve the design flexibility and overall lift-drag characteristics for traditional waveriders. However, because the three-dimensional effect, the viscous effect and the passivation effect of the head/leading edge are ignored in the design of the waverider, overflow still occurs under the design conditions leading to the difficulty in achieving the optimal lift-to-drag ratio. In addition, the lift-drag characteristics will still be poor when the waverider is not in design conditions. In this paper, an aerodynamic shape optimization design method for the hypersonic vehicle based on discretized adjoint is constructed by combining the CFD solvers based on the full-velocity flux solution method and the RANS turbulence model, the robust automatic structured mesh wrapping method, the free form deformation geometry parameterization method, the discretized adjoint method and the sequential quadratic programming algorithm. Through this method, the single point and multi-point three-dimensional aerodynamic optimization designs of the whole aircraft are carried out for the planform-controllable osculating-cone waverider. Under more than 4 million structural grids, 600 design variables and 303 design constraints, the proposed method only takes 2 240 CPU hours and 3 360 CPU hours to achieve the single point and multi-point optimization designs of the waverider. The results show that compared with the initial configuration, the lift-drag ratio of the single point optimization configuration in the design state increased by nearly 5%. The configuration obtained by multipoint optimization can ensure that the lift-drag ratio at off-design states is increased by more than 10% without loss of lift-drag characteristics at design state, which improves the theoretical limitations of the planform-controllable osculating-cone waverider to a certain extent.

Key words: hypersonic, aerodynamic optimization design, discretized adjoint, osculating-cone waverider, planform-controllable

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