An Aero-Thermo-Elasticity Method Applied on the Supersonic Aircraft Model

Hong Tang; Guo Guang Chen; Hui Zhu He

doi:10.4028/www.scientific.net/AMM.215-216.438

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vols. 215-216An Aero-Thermo-Elasticity Method Applied on the...

An Aero-Thermo-Elasticity Method Applied on the Supersonic Aircraft Model

Abstract:

Coupling between the vibration frequencies and the unsteady aerodynamic will reduce the flutter speed and ride quality through the aerodynamic heat transfer. As the flight speed improved, the aeroelastic analysis has become an essential means of aircraft design. The method of aero-thermo-elastic (ATE) analysis is coupled with aircraft aeroelastic analysis and thermal deformation, and is more realistic reflection of the actual flight of the aircraft. In this paper, an ATE analysis of aircraft adopted by computational fluid dynamics/computational structural dynamics (CFD/CSD) methods, and compared with the traditional analysis, to provide analytical tools for the supersonic aircraft design.

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Periodical:

Applied Mechanics and Materials (Volumes 215-216)

Pages:

438-442

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.215-216.438

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Online since:

November 2012

Authors:

Hong Tang, Guo Guang Chen, Hui Zhu He

Keywords:

Aerothermoelasticity, Aircraft, Computational Fluid Dynamics (CFD), Coupling, CSD, Flutter, Heat Transfer, Supersonic

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