高超声速进气道宽范围工作多场耦合效应及快速预测研究  

Multi-Field Coupling Effects and Rapid Prediction of Hypersonic Inlet Operating in a Wide Range

作　　者：王谋远 苏纬仪[1] 孙斐 崔晟 张文强 关开港 WANG Mou-yuan;SU Wei-yi;SUN Fei;CUI Sheng;ZHANG Wen-qiang;GUAN Kai-gang(College of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《推进技术》2023年第2期170-184,共15页Journal of Propulsion Technology

基　　金：国家自然科学基金(11572155);航天科技创新基金(CHA16007)。

摘　　要：为准确预测高超声速进气道气动热力环境及结构响应,开展了三个方面的研究。基于分区求解方法实现了气动力/热/结构三维多场耦合计算,并验证了该方法的正确性。研究了宽范围内来流马赫数和攻角对进气道多场耦合效应的影响。基于本征正交分解技术和径向基函数构建了进气道结构温度场、应力场及应变场的瞬态降阶模型。结果表明,进气道结构变形主要发生在模型的俯仰方向,当来流马赫数由4增加至7时,进气道压缩面气动热载荷增加,结构最大位移增加了4.78倍;当攻角由-2°增加至4°时,结构最大位移增幅为59.69%;设计工况下,降阶模型预测结果与多场耦合计算结果吻合较好,预测误差<0.80%。In order to accurately predict the aerodynamic and thermodynamic environment and structural response of hypersonic inlet, research was carried out in three aspects. Firstly, the three-dimensional aerodynamic/thermal/structural multi-field coupling method was established using the partition algorithm, and then its validity was proved. Secondly, the multi-field coupling effects of a hypersonic inlet operating in a wide range were studied under different incoming Mach numbers and attack angles. Finally, based on the proper orthogonal decomposition technique and radial basis function, a transient reduced order model for predicting the temperature field, stress field and strain field of inlet structure was established. The results show that the deformation of inlet structure mainly occurs in the pitching direction. When incoming Mach number increases from 4 to 7, the aerodynamic thermal load on the compression surface of inlet increases, and the maximum displacement of inlet increases by 4.78 times. With the attack angle increasing from-2° to 4°, the maximum displacement of the structure increases by 59.69%. Under the design condition, the prediction fields based on the reduced order model agree well with fluid-thermal-structural interaction calculation results, and the prediction error is less than 0.80%.

关 键 词：高超声速进气道 多场耦合分析 气动热 本征正交分解 快速预测 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]