基于连续伴随方法的高超声速飞行器高精度气动优化

doi:10.7527/S1000-6893.2020.24490

流体力学与飞行力学

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基于连续伴随方法的高超声速飞行器高精度气动优化

高昌¹, 李正洲¹, 黄江涛², 贺元元¹, 吴颖川¹, 乐嘉陵¹, 桂丰³

1. 中国空气动力研究与发展中心高超声速冲压发动机技术重点实验室, 绵阳 621000;
2. 中国空气动力研究与发展中心, 绵阳 621000;
3. 中国航发四川燃气涡轮研究院, 成都 610500

收稿日期:2020-07-03 修回日期:2020-07-16 发布日期:2020-08-17
通讯作者: 黄江涛 E-mail:hjtcyf@163.com
基金资助:
高超声速超燃冲压发动机技术重点实验室基金（STS/MY-ZY-2018-007）

High-accuracy aerodynamic optimization of hypersonic vehicles based on continuous adjoint

GAO Chang¹, LI Zhengzhou¹, HUANG Jiangtao², HE Yuanyuan¹, WU Yingchuan¹, LE Jialing¹, GUI Feng³

1. Science and Technology on Scramjet Laboratory, China Aerodynamics Research and Development Center, Mianyang 621000, China;
2. China Aerodynamics Research and Development Center, Mianyang 621000, China;
3. AECC Sichuan Gas Turbine Establishment, Chengdu 610500, China

Received:2020-07-03 Revised:2020-07-16 Published:2020-08-17
Supported by:
Foundation of Science and Technology on Scramjet Laboratory (STS/MY-ZY-2018-007)

摘要/Abstract

摘要： 高精度气动优化是改善高超声速飞行器气动性能的必要途径。基于Navier-Stokes方程推导了连续伴随方程以及与气动力目标函数对应的边界条件和壁面灵敏度公式，考虑了层流输运系数变分对伴随方程的贡献，采用基于二阶熵修正Roe格式的伴随对流项离散形式，构造了适用于高超声速流动的连续伴随求解器；结合FFD （Free Form Deformation）参数化方法和SQP （Sequential Quadratic Programming）优化算法构建了高精度梯度优化框架；在高超声速来流条件下对二维翼型和Sanger飞行器机翼优化开展了验证和应用。结果显示，在高超声速流动条件下所采用的伴随对流项离散形式具有较好的鲁棒性和低耗散性；连续伴随求解器能够较好地给出气动力目标函数梯度；优化后Sanger机翼构型通过二次激波压缩实现了减阻增升，升阻比提高5.0%；验证了连续伴随优化作为高超声速飞行器高精度气动优化方法的可行性。

关键词: 高超声速飞行器, 高精度气动优化, 连续伴随方法, FFD方法, SQP算法

Abstract: High-accuracy aerodynamic optimization is an essential approach to the improvement of the aerodynamic performance of hypersonic vehicles. The continuous adjoint equations considering the variations of laminar viscous transport coefficients, boundary conditions and surface sensitivity of aerodynamic force objective functions are derived based on the Navier-Stokes equations. The continuous adjoint solver applicable to hypersonic flows is built and the adjoint convective flux discretized based on a 2-order Roe scheme with entropy corrections. Based on the Free Form Deformation (FFD) methods and the Sequential Quadratic Programming (SQP) algorithm, a high-accuracy adjoint gradient optimization sketch is established, verified and applied to a 2D airfoil and Sanger wing under hypersonic free streams. Results indicate that the adjoint convective scheme possesses strong robustness and low dissipation. The aerodynamic force objective function gradients obtained by the continuous adjoint solver are valid. The lift-drag ratio of the optimized Sanger vehicle increases by 5.0% due to the second shock wave. Verification and optimization confirm the feasibility of the high-accuracy aerodynamic optimization of hypersonic vehicles based the continuous adjoint methods.

Key words: hypersonic vehicles, high-accuracy aerodynamic optimization, continuous adjoint method, FFD methods, SQP algorithm

中图分类号:

V211

高昌, 李正洲, 黄江涛, 贺元元, 吴颖川, 乐嘉陵, 桂丰. 基于连续伴随方法的高超声速飞行器高精度气动优化[J]. 航空学报, 2021, 42(7): 124490-124490.

GAO Chang, LI Zhengzhou, HUANG Jiangtao, HE Yuanyuan, WU Yingchuan, LE Jialing, GUI Feng. High-accuracy aerodynamic optimization of hypersonic vehicles based on continuous adjoint[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(7): 124490-124490.

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基于连续伴随方法的高超声速飞行器高精度气动优化

High-accuracy aerodynamic optimization of hypersonic vehicles based on continuous adjoint

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