Metallic thermal protection system technology development - Concepts, requirements and assessment overview

Dorsey, John T.; Poteet, Carl C.; Chen, Roger R.; Wurster, Kathryn E.

doi:10.2514/6.2002-502

Cited by 29 publications

(19 citation statements)

References 4 publications

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“…Both the Saffil and the cryogenic foam insulation layers were sized using an iterative thermal analysis, 3 American Institute of Aeronautics and Astronautics increasing or decreasing layer thicknesses until an optimum solution was reached.…”

Section: Insulation Sizing Criteriamentioning

confidence: 99%

Advanced metallic thermal protection system development

Blosser

Chen

Schmidt

et al. 2002

40th AIAA Aerospace Sciences Meeting &Amp; Exhibit

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Section: Insulation Sizing Criteriamentioning

confidence: 99%

Advanced metallic thermal protection system development

Blosser

Chen

Schmidt

et al. 2002

40th AIAA Aerospace Sciences Meeting &Amp; Exhibit

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“…In case of thermal effects, aerothermoelastic considerations are important in the design of space re-entry vehicles and high speed aircraft [35] and these effects may produce deformations, thermomechanical stresses, and changes in material properties that can dramatically affect their aeroelastic behavior. In this sense, the structural panels of supersonic/hypersonic flight vehicles can experience, among others, the thermal flutter instability generated by the combined influence of the thermal field, unsteady aerodynamic loads, elasticity of structures, and the dynamic effects [36].…”

Section: Introductionmentioning

confidence: 99%

Static/Dynamic Edge Movability Effect on Non-Linear Aerothermoelastic Behavior of Geometrically Imperfect Curved Skin Panel: Flutter and Post-Flutter Analysis

Abbas

Rui

Marzocca

et al. 2012

Journal of Applied Mechanics

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This paper addresses the problem of the aerothermoelastic modeling behavior and analyses of skin curved panels with static and dynamic edge movability effect in high supersonic fiow. Flutter and post-fiutter behavior will be analyzed toward determining under which conditions such panels will exhibit a benign instability, that is a stable limit cycle oscillation, or a catastrophic instability, that is an unstable LCO. The aerothermoelastic governing equations are developed from the geometrically non-linear theory of infinitely long two dimensional curved panels. Von Kármán non-linear strain-displacement relation in conjunction with the Kirchhoff plate-hypothesis is adopted. A geometrically imperfect curved panel forced by a supersonic/hypersonic unsteady flow is numerically investigated using Galerkin approach. These equations are based on the third-order piston theory aerodynamic for modeling the fiow-induced forces. Furthermore, the effects of thermal degradation and Kelvin's model of structural damping independent of time and temperature are also considered in this model. Computational analysis and discussion of the finding along with pertinent conclusions are presented.

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“…It is therefore desired to develop a model that accounts for mechanical properties, thermal shock, and thermomechanical coupling under extreme complex environment [20].…”

Section: Introductionmentioning

confidence: 99%

Thermomechanical Coupling of non-Fourier Heat Conduction with the C-V Model: Thermal Propagation in Coating Systems

Zhang

Chu

2015

Journal of Thermal Stresses

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A coupled thermomechanical model is established for multilayered structure subjecting to heat deposition, and specified for a thermal barrier system. The thermomechanical interaction including the C-V (Cattaneo-Vernotte) model of heat conduction law for the homogeneous linear thermoelastic material is developed, in which the Non-Fourier heat conduction law and the influence of stress and strain to heat transfer are taken into account. The variation of thermal stress with the heat wave due to the coupled relationship is quite significant. Under a pulse heat deposition on the surface, a model thermal barrier system's (trilayer structure) transient thermal and stress fields are investigated. The result indicates that a high tensile stress is developed, especially near the interface between ceramic coating and oxide layer, which is the most likely damage region, and the failure mechanism is related to the propagation of the coupled thermalmechanical wave. The maximum stress in the oxide layer is affected by the size of material system.

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Metallic thermal protection system technology development - Concepts, requirements and assessment overview

Cited by 29 publications

References 4 publications

Advanced metallic thermal protection system development

Advanced metallic thermal protection system development

Static/Dynamic Edge Movability Effect on Non-Linear Aerothermoelastic Behavior of Geometrically Imperfect Curved Skin Panel: Flutter and Post-Flutter Analysis

Thermomechanical Coupling of non-Fourier Heat Conduction with the C-V Model: Thermal Propagation in Coating Systems

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