Analysis of modal characteristics of aircraft wing structure in the aerodynamic heating environment

L. Lei1, G. Xiangren2, G. Yewei2, H. Lixin2 and W. Anling2

1State Key Laboratory of Aerodynamics, Mianyang Sichuan, P.R. China
2China Aerodynamics Research and Development Center, Mianyang, Sichuan, P.R. China

Keywords: aerodynamic heat
property: modal characteristic
material: heat affecting

With the accelerating pace of space exploration, a variety of concept hypersonic vehicle appeared. The aerodynamic heating with the supersonic flight increased many challenges to the hypersonic vehicle design. The aerothermoelasticity is one of the key issues. The traditional aeroelasticity is an interdisciplinary, the main work of which is to study the coupling characteristics between the elastic force, aerodynamic force and inertia force. Based on the traditional aeroelasticity, the aerothermoelasticity coupled the impact of heat. The aerodynamic heating will result in the rising of structural temperature, the changing of material properties and thermal stress. All of these will change the modal characteristics of the original structure, and may make the stability of the aeroelastic system become lower. In this paper, based on the characteristics of aerothermoelasticity, the impact of aerodynamic heating on the modal properties of supersonic aircraft wing structure was studied. The actual aerodynamic heat environment was obtained using approximate aerodynamic heating method. And on this basis, the temperature and stress of this wing structure calculated. In the calculation of the wing structural modes, the finite element method (FEM) was used, and the material properties changing with temperature and the additional stiffness caused by thermal stress have been considered. The computation results show that when the effect of aerodynamic heating on the surface of this structure has been considered the structure modals changed notably. All of the structural natural frequencies reduced, and the space between the natural frequencies are smaller, which will lead to reduction in flutter speed. Compared to the common research, that the wing structure is uniform temperature rising or function distribution, the impact of structural modal characteristics is greater.

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