Modeling of Mechanical Ablation in Thermal Protection Systems

Palaninathan, R.; Bindu, S.

doi:10.2514/1.10710

Cited by 34 publications

(14 citation statements)

References 14 publications

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“…[8,9] Severe oxidation and mechanical denudation of C/C composites during ablation process always result in high ablation rates. [10,11] The intrinsic properties of C/C composites, including the fiber architecture, matrix microstructure, and bulk density, are closely concerned with the ablation property of the composites. [12][13][14] Carbon fibers and various kinds of carbon matrices (pitch carbon, resin carbon, and pyrolytic carbon [PyC]) exhibit different ablation properties considering their different microstructures.…”

Section: Introductionmentioning

confidence: 99%

Improved Thermal Conductivity and Ablation Resistance of Microdiamond‐Modified C/C Composites after Diamond Graphitization

et al. 2019

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C/C composites with diamond addition are prepared, and a 1600 °C heat treatment is conducted to investigate the effects of diamond graphitization on the ablation resistance and thermal conductivity of the composites. With diamond content increasing, a higher degree of stress graphitization occurs to the surrounding pyrolytic carbon (PyC) due to the enhanced stress accumulation in the diamond stacking region during graphitization process. After heat treatment at 1600 °C, the single diamond/PyC interface is substituted by complex diamond/graphite and graphite/PyC interfaces which results in a more compact structure and enhanced interface strength. Benefiting from the optimized interface microstructure and reduced closed pores after diamond graphitization, higher thermal conductivities are achieved for C/C–diamond composites. The ablation performance of the composites is improved due to the better oxidation resistance of diamond particles, increased compactness of diamond stacking region, and optimized thermal properties of the composites.

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Section: Introductionmentioning

confidence: 99%

Improved Thermal Conductivity and Ablation Resistance of Microdiamond‐Modified C/C Composites after Diamond Graphitization

et al. 2019

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“…Ferraiuolo and Manca [5] developed analytical and semi-analytical procedures to solve thermal problems. Palaninathan and Bindu [8] gave a model for mechanical ablation in thermal protection systems. Kunihiko [7] gave a thermal analysis for re-entry vehicle structure using the CFD/FEM coupling method.…”

Section: Introductionmentioning

confidence: 99%

The inverse problem in zero linear ablation of aluminizing carbon composites under high heat flux

Huang

et al. 2013

THERM SCI

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The concept of zero linear ablation is introduced to describe the mass ablation without shape change, and it is employed to design thermal protection materials under an extreme thermal environment. Aluminizing carbon composites are used as a sample to study numerically the heat response. As indicated in the numerical results, the shape of the composites did not change under a high heat flux because the phase transition (melt or evaporation) of aluminum can absorb a lot of energy before the ablation of carbon, and the zero linear ablation depends on not only the volume fraction of aluminum, but also the heating period and the heat flux.

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“…5 Thermal protection system (TPS) materials impart heat shield to protect the structure, aerodynamic surface and the payload of missiles, and those vehicles interacting with the hypersonic environment. 6,7 Polymeric ablative materials serve to effect as TPS that defends space vehicles and probes during the atmospheric entry; they are effective to produce passively cooled rocket combustion chambers 8 and to render insulation to the solid rocket motors (SRMs) at high temperature. [9][10][11] Although some nonpolymeric materials such as inorganic polymers/ceramics or metals have been used as ablative TPS, polymeric ablatives represent the most flexible category of ablatives.…”

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confidence: 99%

Recent developments in elastomeric heat shielding materials for solid rocket motor casing application for future perspective

George

Panda

Mohanty

et al. 2017

Polymers for Advanced Techs

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Catastrophic breakdown that occurs during the flight of supersonic vehicles demands more focused research in the insulation of rocket engines. At present, optimization of polymeric ablatives as viable insulation for solid rocket motor casing has a prominent role in the successful mission of rockets. Among polymers, elastomer serves an imperative part. Comprehensive investigations were disclosed, especially in the elastomeric heat shielding materials with various reinforcing agents. In this paper, research progress of mostly used elastomers is reviewed, and a circumstantial understanding about the features of ablation and insulation has been validated. 2-4 Therefore, to protect the vehicle from miserable failure of spacecraft, some design features are added to cope with the aerodynamic heating. 5Thermal protection system (TPS) materials impart heat shield to protect the structure, aerodynamic surface and the payload of missiles, and those vehicles interacting with the hypersonic environment. 6,7 Polymeric ablative materials serve to effect as TPS that defends space vehicles and probes during the atmospheric entry; they are effective to produce passively cooled rocket combustion chambers 8 and to render insulation to the solid rocket motors (SRMs) at high temperature. [9][10][11] Although some nonpolymeric materials such as inorganic polymers/ceramics or metals have been used as ablative TPS, polymeric ablatives represent the most flexible category of ablatives. In contrast to the inorganic polymers, polymer ablatives have more inborn benefits: high-heat shock resistance, lower density, good mechanical strength, and thermal insulation capabilities. 12The broad range of heat shielding materials (HSMs) for rocket motor casing is produced from reinforced thermosets or elastomers. [13][14][15][16][17][18][19] The most assuring material for the HSM for rocket motors is the elastomers, which can be produced as rubbers, foamed rubbers, or fiber-reinforced composite materials. On the grounds of lightweight, low thermal conductivity, stability in the mechanical and thermal stresses during the operation, elastomeric HSMs (EHSMs) can find relevance in the insulation of SRM casing where thermal insulation is a prime necessity. They do not possess the ability to form cokes without the introduction of special additives due to the linear chain structure of elastomers, thus no solid carbonic residue on thermal decomposition.Also, elastomers have high elongation at break and the capacity to withstand the mechanical and the thermal stresses during the manufacturing and in use. 20This review puts the elastomeric materials as ablative insulators for SRM into frame and would confer the readers the progress that has been attained in developing relatively low surface eroding and ablative insulating systems for SRM. These systems can be used to manufacture variety of ablative TPS systems for rocket motor casing application and would provide an idea regarding the composite system that would behave elastomeric as well as ablative. Scrutini...

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Modeling of Mechanical Ablation in Thermal Protection Systems

Cited by 34 publications

References 14 publications

Improved Thermal Conductivity and Ablation Resistance of Microdiamond‐Modified C/C Composites after Diamond Graphitization

Improved Thermal Conductivity and Ablation Resistance of Microdiamond‐Modified C/C Composites after Diamond Graphitization

The inverse problem in zero linear ablation of aluminizing carbon composites under high heat flux

Recent developments in elastomeric heat shielding materials for solid rocket motor casing application for future perspective

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