摘要
采用CFD/CSD/CTD耦合方法研究了高超声速机翼的热气动弹性问题。首先采用多场耦合方法进行了静热气动弹性配平,获得了结构热平衡状态下的温度分布和位移分布;在此基础上对结构进行了热模态分析,得到了其各阶模态频率随来流马赫数的变化规律;最后,研究了材料属性变化和热应力对热配平结果的影响。结果表明,气动热使结构特性发生改变,模型结构刚度下降主要由材料属性变化引起,而结构变形则与热膨胀有关。
The aerothermoelasticity of hypersonic wing is studied based on the CFD / CSD / CTD coupling method.First,static aerothermoelastic trim is conducted using multi-field coupling method and the temperature and displacement distribution of the trim results are obtained.Then,thermal modal analysis of the wing is done based on the trim results and get the change law of modal frequencies with freestream Mach number.Finally,study the influence of material property and thermal stress on the results of static aerothermoelastic trim is studied.The results show that aerodynamic heating can change the structure characteristics,and for the model used,the reduction of structure stiffness is mainly caused by the change of material property and the deformation is mainly caused by thermal expansion.
出处
《盐城工学院学报（自然科学版）》
CAS
2015年第1期34-38,共5页
Journal of Yancheng Institute of Technology:Natural Science Edition
关键词
多场耦合
高超声速
热气动弹性
热模态分析
热应力
Multi-field Coupling
Hypersonic
Aerothermoelasticity
Thermal modal analysis
Thermal stress
