Bibliographies thématiques / Charring ablator

Littérature scientifique sur le sujet « Charring ablator »

Auteur : Grafiati

Publié le 14 mars 2023

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Articles de revues sur le sujet "Charring ablator"

Hakkaki-Fard, A., et F. Kowsary. « Heat Flux Estimation in a Charring Ablator ». Numerical Heat Transfer, Part A : Applications 53, n^o 5 (6 novembre 2007) : 543–60. http://dx.doi.org/10.1080/10407780701678240.

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Guo, Jin, et Haiming Huang. « A novel method for analysing the thermal behaviour of charring ablator ». Thermal Science and Engineering Progress 7 (septembre 2018) : 107–14. http://dx.doi.org/10.1016/j.tsep.2018.05.006.

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Weng, Haoyue, Ümran Düzel, Rui Fu et Alexandre Martin. « Geometric Effects on Charring Ablator : Modeling the Full-Scale Stardust Heat Shield ». Journal of Spacecraft and Rockets 58, n^o 2 (mars 2021) : 302–15. http://dx.doi.org/10.2514/1.a34828.

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Chen, Yih-Kanq, et Frank S. Milos. « Effects of Nonequilibrium Chemistry and Darcy—Forchheimer Pyrolysis Flow for Charring Ablator ». Journal of Spacecraft and Rockets 50, n^o 2 (mars 2013) : 256–69. http://dx.doi.org/10.2514/1.a32289.

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Li, Weijie, Haiming Huang, Ye Tian et Zhe Zhao. « A nonlinear pyrolysis layer model for analyzing thermal behavior of charring ablator ». International Journal of Thermal Sciences 98 (décembre 2015) : 104–12. http://dx.doi.org/10.1016/j.ijthermalsci.2015.07.002.

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Wang, Yeqing, Timothy K. Risch et Joseph H. Koo. « Assessment of a one-dimensional finite element charring ablation material response model for phenolic-impregnated carbon ablator ». Aerospace Science and Technology 91 (août 2019) : 301–9. http://dx.doi.org/10.1016/j.ast.2019.05.039.

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SZASZ, Bianca, Kei-ichi OKUYAMA, Sumio KATO, Takayuki SHIMODA et Sean Lee TUTTLE. « S1910102 Study of the Heat Shield Characteristics of a Lightweight Charring CFRP-based Ablator ». Proceedings of Mechanical Engineering Congress, Japan 2015 (2015) : _S1910102a. http://dx.doi.org/10.1299/jsmemecj.2015._s1910102a.

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Xu, Yi Hua, Chun Bo Hu, Zhuo Xiong Zeng et Yu Xin Yang. « Research on Mechanical Model of EPDM Insulation Charring Layer ». Applied Mechanics and Materials 152-154 (janvier 2012) : 57–63. http://dx.doi.org/10.4028/www.scientific.net/amm.152-154.57.

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The coupling effect of physics, chemistry and mechanics is through charring layer in the process of ablation of the insulation material. Description of the structure and mechanical properties of charring layer is the critical factor to numerical computation for foretelling the ablation of insulation material. The characteristic of charring layer structure of EPDM insulation at sorts of ablating condition were analyzed, and based on characteristic of porous medium of charring layer, the mechanical model with porosity as parameter was modeled by using theory of solid porous medium. According to the intensity determination of charring layer, the coefficient of intensity model was determined, then, the failure criterion of charring layer was set up, which can provide the mechanical parameters of charring layer for numerical computation to foretell the ablation of insulation material.

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Xiao, Jie, Lin Jiang et Qiang Xu. « Insight into chemical reaction kinetics effects on thermal ablation of charring material ». Thermal Science, n^o 00 (2021) : 85. http://dx.doi.org/10.2298/tsci201010085x.

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Thermal ablation plays an important role in the aerospace field. In this paper, to study the chemical kinetics effects on heat transfer and surface ablation of the charring ablative material during aerodynamic heating, a charring ablation model was established using the finite element method. AVCOAT5026-39H/CG material, one typical thermal protection material used in thermal protection system, was employed as the ablative material and heated by aerodynamic heating condition experienced by Apollo 4. The finite element model considers the decomposition of the resin within the charring material and the removal of the surface material, and uses Darcy?s law to simulate the fluid flow in the porous char. Results showed that the model can be used for the ablation analysis of charring materials. Then effects of chemical kinetics on ablation were discussed in terms of four aspects, including temperature, surface recession, density distribution, and mass flux of pyrolysis gas. The pre-exponential factor and activation energy have different effects on ablation, while the effect of the reaction order is little. This paper is helpful to understand the heating and ablation process of charring ablative materials and to provide technical references for the selection and design of thermal protection materials.

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Fu, Rui, Haoyue Weng, Jonathan F. Wenk et Alexandre Martin. « Thermomechanical Coupling for Charring Ablators ». Journal of Thermophysics and Heat Transfer 32, n^o 2 (avril 2018) : 369–79. http://dx.doi.org/10.2514/1.t5194.

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Thèses sur le sujet "Charring ablator"

Omidy, Ali D. « Multiphase Interaction in Low Density Volumetric Charring Ablators ». UKnowledge, 2018. https://uknowledge.uky.edu/me_etds/128.

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The present thesis provides a description of historical and current modeling methods with recent discoveries within the ablation community. Several historical assumptions are challenged, namely the presence of water in Thermal Protection System (TPS) materials, presence of coking in TPS materials, non-uniform elemental production during pyrolysis reactions, and boundary layer gases, more specifically oxygen, interactions with the charred carbon interface. The first topic assess the potential effect that water has when present within the ablator by examining the temperature prole histories of the recent flight case Mars Science Laboratory. The next topic uses experimental data to consider the instantaneous gas species produced as the ablator pyrolyzes. In this study, key gas species are identified and assumed to be unstable within the gas phase; thus, equilibrating to the solid phase. This topic investigates the potential effects due to the these process. The finial topic uses a simplified configuration to study the role of carbon oxidation, from diatomic oxygen, on the ablation modes of a TPS, surface versus volumetric ablation. Although each of these topics differ in their own right, a common theme is found by understanding the role that common pyrolysis and boundary layer gases species have as they interacts with the porous TPS structure. The main objective of the present thesis is to investigate these questions.

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Weng, Haoyue. « Multidimensional Modeling of Pyrolysis Gas Transport Inside Orthotropic Charring Ablators ». UKnowledge, 2014. https://uknowledge.uky.edu/me_etds/50.

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During hypersonic atmospheric entry, spacecraft are exposed to enormous aerodynamic heat. To prevent the payload from overheating, charring ablative materials are favored to be applied as the heat shield at the exposing surface of the vehicle. Accurate modeling not only prevents mission failures, but also helps reduce cost. Existing models were mostly limited to one-dimensional and discrepancies were shown against measured experiments and flight-data. To help improve the models and analyze the charring ablation problems, a multidimensional material response module is developed, based on a finite volume method framework. The developed computer program is verified through a series of test-cases, and through code-to-code comparisons with a validated code. Several novel models are proposed, including a three-dimensional pyrolysis gas transport model and an orthotropic material model. The effects of these models are numerically studied and demonstrated to be significant.

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Fadigati, Luca. « Numerical investigation of charring thermal protection pyrolysis and ablation in solid rocket motors ». Master's thesis, Alma Mater Studiorum - Università di Bologna, 2020.

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The solid rocket propulsion is a simple and reliable system, it is less complex than liquid propulsion because it does not require tanks, pumps and the propellant is already stored into the combustion chamber. The main issues are the lower propulsive performance and the lack of controllability. The solid rocket motor thrust can be controlled only moving the nozzle direction of few degrees while its magnitude can not be controlled, therefore it is very important to well know the thrust profile because there is no possibility to control its magnitude during the flight. The thrust shape can be obtained experimentally or performing simulations. The first way is quite expensive therefore the second one is preferable. The tool ROBOOST (ROcket BOOst Simulation Tool), developed by the university of Bologna propulsion laboratory in collaboration with Avio S.p.A., already achieves the goal to predict the thrust profile during the ignition phase and the combustion one. But it fails to follow the experimental curve in the tail-off, underestimating the residual thrust. This discrepancy can be due to different phenomena that are not considered in the this simulation: heat coming from the nozzle, heat coming from slugs and the mass flow rate due to the thermal protection pyrolysis and ablation. This thesis focuses on simulate thermal protection pyrolysis and ablation obtaining their behavior when they are exposed to the hot gases of the combustion chamber.

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Actes de conférences sur le sujet "Charring ablator"

Weng, Haoyue, Huai-Bao Zhang, Ovais Khan et Alexandre Martin. « Multi-Dimensional Modeling of Charring Ablator ». Dans 43rd AIAA Thermophysics Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-2748.

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Mansour, Nagi, Jean Lachaud, Thierry Magin, Julien de Mûelenaere et Yih-Kanq Chen. « High-Fidelity Charring Ablator Thermal Response Model ». Dans 42nd AIAA Thermophysics Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-3124.

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Amar, Adam J., Brandon Oliver, Benjamin Kirk, Giovanni Salazar et Justin Droba. « Overview of the CHarring Ablator Response (CHAR) Code ». Dans 46th AIAA Thermophysics Conference. Reston, Virginia : American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-3385.

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Martin, Alexandre. « Modeling of chemical nonequilibrium effects in a charring ablator ». Dans 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-301.

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Titov, Evgeny, Rakesh Kumar, Deborah Levin et Brian Anderson. « Development and Application of a Charring Ablator Thermal Response Model ». Dans 42nd AIAA Thermophysics Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-3785.

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Salazar, Giovanni, et Adam J. Amar. « Contact Boundary Conditions in the CHarring Ablator Response (CHAR) Code ». Dans AIAA AVIATION 2021 FORUM. Reston, Virginia : American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-3134.

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Rostkowski, Przemyslaw, et Marco Panesi. « Quantification of Uncertainty in Extrapolation of Charring Ablator Material Performance to Flight ». Dans AIAA SCITECH 2022 Forum. Reston, Virginia : American Institute of Aeronautics and Astronautics, 2022. http://dx.doi.org/10.2514/6.2022-2360.

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Salazar, Giovanni, Justin Droba, Brandon Oliver et Adam J. Amar. « Development and Verification of Enclosure Radiation Capabilities in the CHarring Ablator Response (CHAR) code ». Dans 46th AIAA Thermophysics Conference. Reston, Virginia : American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-3388.

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Congdon, William, Donald Curry et Douglas Rarick. « Validation Arc-Jet Testing and Thermal-Response Modeling of Advanced Lightweight Charring-Ablator Families ». Dans 8th AIAA/ASME Joint Thermophysics and Heat Transfer Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-2999.

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Congdon, William, et Donald Curry. « Thermal performance of advanced charring ablator systems for future robotic and manned missions to Mars ». Dans 35th AIAA Thermophysics Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-2829.

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