Numerical studies on the thermal-fluid-structure coupling analysis method of hypersonic flight vehicle

• Published in: Thermal science and engineering progress Vol. 40; p. 101792
• Main Authors: Wang, Weiji, Qian, Wei, Bai, Yuguang, Wang, Kunming
• Format: Journal Article
• Language: English
• Published: Elsevier Ltd 01.05.2023
• Subjects: Aerodynamic heating; CFD; Hypersonic aircraft; Thermal-fluid-structure coupling analysis; CFD; Thermal-fluid-structure coupling analysis; Hypersonic aircraft; Aerodynamic heating
• ISSN: 2451-9049; 2451-9049
• DOI: 10.1016/j.tsep.2023.101792

•An elastic hypersonic configuration via delta wings with large sweep angle was designed.•A thermal-fluid-structure coupling method is proposed to analyze the thermal conditions of hypersonic vehicle.•Thermal dynamics and thermal flutter stability were presented for the present hypersonic aircraft. Aero-heating effects on hypersonic aircraft bring dangerous environment for the design of the structures. Different FEM modelling methods are always employed for structural dynamic analysis and transient heat conduction, respectively. An effective thermal-fluid-structure coupling analysis method of hypersonic flight vehicle is thus necessary to solve the bifurcation between the two different subjects. Aeroelastic models based on a popular structure of a hypersonic aircraft was chosen to find the proposed analysis method. CFD based simulation was used to compute hypersonic aero-heating. Effective interpolation algorithms were developed in this paper to combine temperature distribution with the structural model. With thermal dynamic computation of the present structure, thermal-fluid-structure coupling effects were discussed. Thermal effects on flutter characteristics of the present wing via thermal or normal dynamics could be found, too. It can be seen that the present thermal-fluid-structure coupling analysis method can provide useful application for dynamic engineering design of novel hypersonic aircraft. Therma-fluid-structure effects can influence the flutter boundary for the present configuration of hypersonic vehicle.