Aeroelasticity & Structural Dynamics in a Fast Changing World
17 – 21 June 2024, The Hague, The Netherlands
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An integrated static/dynamic aerothermoelastic analysis framework for functionally graded structures in hypersonic vehicles


Go-down ifasd2024 Tracking Number 87

Presentation:
Session: High speed aeroelasticity 1
Room: Room 1.3
Session start: 09:40 Wed 19 Jun 2024

Chang Li   changli@buaa.edu.cn
Affifliation: BUAA

Zhiqiang Wan   wzq@buaa.edu.cn
Affifliation:

Xiaozhe Wang   wangxiaozhemvp@buaa.edu.cn
Affifliation:

Chao Yang   yangchao@buaa.edu.cn
Affifliation:

Zhiying Chen   chen_zhiying@buaa.edu.cn
Affifliation:


Topics: - Computational Aeroelasticity (High and low fidelity (un)coupled analysis methods:), - High Speed Structural Dynamics Phenomena (High and low fidelity (un)coupled analysis methods:)

Abstract:

Hypersonic vehicles are susceptible to considerable aerodynamic heating and noticeable aerothermoelastic effects during flight due to their high speeds. Functionally graded materials (FGMs), which enable continuous changes in material properties by varying the ratio of two or more materials, provide both thermal protection and load-bearing capabilities. Therefore, they have great advantages in thermal protection structures for hypersonic vehicles. There have been numerous studies of basic elements made of FGMs, such as functionally graded (FG) plates, beams and shells. However, few studies focus on the FG structures applied in the hypersonic vehicles such as the wing. In addition, FGMs are sensitive to the temperature, which are changeable in the flight. Therefore, the characteristics of FG structures are important to investigate. This paper will establish an integrated static/dynamic aerothermoelastic analysis framework for FG structures in hypersonic vehicles. First, the static aerothermoelastic responses are analysed during the flight based on the aerodynamic analysis method of the piston theory, and structure analysis method of the finite element method. Second, at a given moment, the temperature field, deformations and aerodynamic forces acquired in the static analysis are inputted for the panel flutter analysis for plates in the FG structures, based on a semianalytical method. Meanwhile, the flutter characteristics of the wing are analysed based on the heated structures obtained in the static analysis. Finally, the static responses, panel flutter and flutter characteristics of the wing during the whole flight will be obtained through this framework, which will analyse the global and local responses and stability characteristics simultaneously. The framework will provide the characteristics of FG structures in hypersonic vehicles over time, identify the critical design point, and provide a foundation for the following design.