Impact of Fluid-Thermal-Structural Coupling on Response Prediction of Hypersonic Skin Panels

Culler, Adam J.; McNamara, Jack J.

doi:10.2514/1.j050617

Cited by 127 publications

(81 citation statements)

References 38 publications

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“…[3][4][5][6][7][8][9][10][11][12][13][14][15][16] The effectiveness of these techniques is closely tied to topics such as design of experiments (DOE), both from general statistics as well as the specific circumstances of computational experiments, as can be seen in various example applications. 15,[17][18][19][20][21][22][23][24][25][26][27][28][29][30][31][32][33] Multidisciplinary analysis and optimization (MDA/MDO), including formal optimization, coupled system theory, and sensitivity analysis, is also relevant to this research work. Traditional optimization has a long history, rooted in mathematical programming, and has well developed tools.…”

Section: Background and Related Workmentioning

confidence: 99%

Reduced-Order Techniques for Sensitivity Analysis and Design Optimization of Aerospace Systems

Parrish

2015

AIAA Journal

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This work proposes a new method for using reduced order models in lieu of high fidelity analysis during the sensitivity analysis step of gradient based design optimization.The method offers a reduction in the computational cost of finite difference based sensitivity analysis in that context. The method relies on interpolating reduced order models which are based on proper orthogonal decomposition. The interpolation process is performed using radial basis functions and Grassmann manifold projection. It does not require additional high fidelity analyses to interpolate a reduced order model for new points in the design space.The interpolated models are used specifically for points in the finite difference stencil during sensitivity analysis.The proposed method is applied to an airfoil shape optimization (ASO) problem and a transport wing optimization (TWO) problem. The errors associated with the reduced order models themselves as well as the gradients calculated from them are evaluated. The effects of the method on the overall optimization path, computation times, and function counts are also examined.

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Section: Background and Related Workmentioning

confidence: 99%

Reduced-Order Techniques for Sensitivity Analysis and Design Optimization of Aerospace Systems

Parrish

2015

AIAA Journal

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“…Panel flutter due to aerothermoelasticity is an important issue in modern aerospace, a lot of researches have been carried out in the past decades [1][2][3][4][5][6][7][8][9][10][11]. On the other hand, Functionally Graded Materials (FGMs) have great potentials and been increasingly used in the modern aerospace engineering, so it is significant to investigate the aerothermoelastic behaviors of Functionally Graded Panels (FGPs) AEROTHERMOELASTIC BEHAVIORS OF GRADED PANELS 883 in supersonic flows.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Aerothermoelastic Behaviors of Functionally Graded Panels in Supersonic Flows

Zhang

Ren

et al. 2015

Journal of Thermal Stresses

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Considering the potentials of Functionally Graded Panels (FGPs) in aerospace field, it is necessary to study the aerothermoelastic behaviors of FGPs in supersonic flows. In this study, Piston Theory Aerodynamics (PTA) and Eckert reference enthalpy method are used to model aerodynamic force and heating, respectively. The 2-D heat conduction equation is solved and the impact of elevated temperature on the mechanical properties of FGPs is considered to build an aerothermoelastic two-way coupling model of FGPs, and Finite Element Method (FEM) is used to approach the solution. As the results, it is found that there exist three different regions in the bifurcation diagram, namely, thermal buckling region, critical region and flutter region. Due to the inhomogeneous distribution of thermal expansion coefficient, the panel buckles up first and then buckles down via vibration, as thermal buckling happens. Also, irregular vibrations are observed in the critical region of bifurcation diagram. In the flutter region, the dynamic behavior of FGPs is discontinuous and very sensitive to initial conditions. With the impact of aerothermoelastic two-way coupling, different FGPs behaviors lead to the differences in temperature distribution. In particular, the final buckling position and vibration center move to lower positions, and lower temperature region near leading edge is left in the FGPs, because of thermal moment. Also, regular vibrations, rather than irregular vibrations, are easy to extract more principal and regular POD (Proper Orthogonal Decomposition) modes. The results presented could be applied to the analysis and design of Functionally Graded Panels in supersonic flows.

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“…[1][2][3] Recently, several studies [4][5][6] have demonstrated the aerothermoelastically driven structural state evolution associated with extended exposure to a high speed flow. However, a potential area of concern is the added effect of plasticity and other damage drivers, and how they might couple with a long duration fluid-thermal-structural response.…”

Section: Introductionmentioning

confidence: 99%

Characterizing the Role of Plasticity in Structural Response to High Speed Flows

Gogulapati

LaFontaine

McNamara

2014

55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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This paper discusses the development of a framework for characterizing the role of plasticity in the structural response of panels in high speed flows. The framework is developed around a commercial nonlinear finite element solver by incorporating CFD surrogates, for the coupled aerothermodynamic loads, in the form of user defined functions. This approach conveniently enables the study of complex built-up structural models, and the incorporation of advanced constitutive modules. The general features of the framework are provided. Also, a preliminary demonstration is carried out on the potential effect of plasticity on the fluid-thermal-structural response of a simple panel subject to both shock-impingements and severe acoustic loading over multiple loading cycles.

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Impact of Fluid-Thermal-Structural Coupling on Response Prediction of Hypersonic Skin Panels

Cited by 127 publications

References 38 publications

Reduced-Order Techniques for Sensitivity Analysis and Design Optimization of Aerospace Systems

Reduced-Order Techniques for Sensitivity Analysis and Design Optimization of Aerospace Systems

Investigation of Aerothermoelastic Behaviors of Functionally Graded Panels in Supersonic Flows

Characterizing the Role of Plasticity in Structural Response to High Speed Flows

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