摘要
提出了基于分区协调耦合推进的翼面热颤振时域研究方法,其中气动力和气动热采用有限体积法求解,且流场空间离散采用AUSM+格式,而结构温度场采用有限元法求解。采用模态叠加法进行结构瞬态响应的求解,在耦合面上采用基于虚拟空间的插值方法进行耦合变量的传递。研究了高超声速翼面的热颤振问题,获得了不同马赫数下的翼面温度场分布。根据"频率重合理论"获得了热环境下翼面一阶弯曲和一阶扭转频率的相互靠近导致了翼面临界颤振速度下降的结论。
A division coordinating coupled marching time domain method for thermal flutter of hypersonic wing is presented. The aerodynamic force and heating are calculated by finite volume method,the advection upstream splitting method(AUSM+)scheme is adopted for spatial discretization. The structural temperature field is calculated by finite element method. The structural transient responses are calculated by modal superposition method. In addition,the transfers of coupling variables are conducted by the interpolation method based on virtual space. The thermal flutter of hypersonic wing is studied. The temperature fields of the wing under different Mach numbers are obtained. According to the frequency coincidence theory,the first order bending frequency and first order torsion frequency are closer to each other in thermal environment,and it is the reason for that critical flutter velocity of wing in thermal environment is lower than that in normal temperature.
作者
范冰
黄杰
姚卫星
FAN Bing;HUANG Jie;YAO Weixing(State Key Laboratory of Mechanics and Control of Mechanical Structures,Nanjing University of Aeronautics and Astronautics Nanjing,210016,China;Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle,Nanjing University of Aeronautics and Astronautics Nanjing,210016,China)
出处
《振动．测试与诊断》
EI
CSCD
北大核心
2021年第5期951-955,1036,共6页
Journal of Vibration,Measurement & Diagnosis
基金
国家自然科学基金资助项目(52002181)
江苏高校优势学科建设工程资助项目。
关键词
有限体积法
有限元法
高超声速翼面
热颤振
耦合分析
finite volume method
finite element method
hypersonic wing
thermal flutter
coupling analysis
