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

作　　者：高昌[1] 李正洲 黄江涛[2] 贺元元[1] 吴颖川[1] 乐嘉陵[1] 桂丰 GAO Chang;LI Zhengzhou;HUANG Jiangtao;HE Yuanyuan;WU Yingchuan;LE Jialing;GUI Feng(Science and Technology on Scramjet Laboratory,China Aerodynamics Research and Development Center,Mianyang 621000,China;China Aerodynamics Research and Development Center,Mianyang 621000,China;AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China)

机构地区：[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

出　　处：《航空学报》2021年第7期164-175,共12页Acta Aeronautica et Astronautica Sinica

基　　金：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)。

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。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 2 Dairfoil 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.

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 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]