Arc-jet measurements of low-density ablator spallation

Price, Kristen; Panerai, Francesco; Borchetta, Colby; M., Hardy, James; Martin, Alexandre; Bailey, Sean

doi:10.1016/j.expthermflusci.2021.110544

Cited by 20 publications

(2 citation statements)

References 18 publications

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“…At temperatures above 1,200 K, pyrolysis is complete and the remaining carbonaceous char layer interacts with both the pyrolysis gases and the reactants transported to the surface. This ablation zone is dominated by finite-rate heterogeneous reactions, such as oxidation and nitridation, phase changes (e.g., sublimation of solid carbon into gas carbon species), and mechanical material removal by friction and shear stresses (spallation) (Bailey et al 2018, Price et al 2022. The extent of the ablation zone is the result of competing diffusion-reaction processes.…”

Section: Ablation Phenomenamentioning

confidence: 99%

Flow Mechanics in Ablative Thermal Protection Systems

Mansour,

Panerai,

Lachaud

et al. 2024

Annu. Rev. Fluid Mech.

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Ablative thermal protection systems have experienced renewed interest in the past decade owing to the retirement of NASA's Space Shuttle fleet and the US presidential mandate to develop technologies that enable humans to explore space beyond low Earth orbit. Blunt body architecture for spacecraft and the use of ablators for thermal protection systems returned as the primary choice in mission planning. This review addresses current progress in modernizing predictive tools for ablative material response. Current theory development leverages progress made in the theory of flows in porous media. This development, combined with progress in experimental techniques and high-end computing, is enabling the development of 3D macroscale models with realistic closure coefficients derived from direct numerical simulations of 3D microscale geometries of actual materials. While flight data quantifying ablative material response remain sparse, the next decade will be one of exploration in which heatshield instrumented spacecraft will provide crucial flight data for refining and validating closure models.

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Section: Ablation Phenomenamentioning

confidence: 99%

Flow Mechanics in Ablative Thermal Protection Systems

Mansour,

Panerai,

Lachaud

et al. 2024

Annu. Rev. Fluid Mech.

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“…[12][13][14] The ablation property of ATPCs under aerodynamic heating environment is important for the safety and reliability design of supersonic vehicles. [15,16] Until now, several methods, such as quartz lamp, [17,18] oxyacetylene, [19] flame plasma wind tunnel, [20,21] and arc-jet, [22,23] have been used to assess the ablation property of the ATPCs. The first two methods are widely used because of the advantages of easy apparatus getting, simple operation, and low cost.…”

Section: Introductionmentioning

confidence: 99%

Investigation on the Reliability of an Ablation Thermal Protection Coating with Adjustable Thickness under Aerothermal–Vibration Coupling Environment

Jiao

et al. 2022

Adv Eng Mater

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Advanced thermal protection system is the core component of supersonic vehicles. A novel hydroxyl‐terminated silicone oligomer‐bridged epoxy resins (PSG)‐based ablation thermal protection coatings (ATPCs) with different thickness are fabricated. The thermal insulation and structural reliability of the coatings are investigated by an aerothermal–vibration coupling test system. During the test, the heat flux of the surface of ATPCs ranges from 400 to 700 kW m−2. Meanwhile, the vibration load is a random vibration with frequency range of 20–2000 Hz and root mean square of total acceleration (Grms) of 15 g. The maximum surface and back‐face temperatures of the coating with the thickness of 2 mm reach 771.8 and 113.6 °C, respectively. Compared with epoxy resin‐based ATPCs, the PSG‐based ATPCs show excellent structural reliability during the test. Finally, the comprehensive properties of ATPCs with different thickness are also carefully studied. Results show that the reduction of thickness obviously suppresses the surface temperature (≈743.4 °C) and increase in back‐face temperature (≈241.5 °C) yet maintaining much higher structural reliability. This study provides a solution for obtaining excellent thermal insulation performance ATPCs with high structural reliability, which is highly desired in supersonic vehicles.

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Pyrolysis front detection in carbon phenolic composites using x-ray computed tomography

Brewer,

Poovathingal

2024

Composites Part A: Applied Science and Manufacturing

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Arc-jet measurements of low-density ablator spallation

Cited by 20 publications

References 18 publications

Flow Mechanics in Ablative Thermal Protection Systems

Flow Mechanics in Ablative Thermal Protection Systems

Investigation on the Reliability of an Ablation Thermal Protection Coating with Adjustable Thickness under Aerothermal–Vibration Coupling Environment

Pyrolysis front detection in carbon phenolic composites using x-ray computed tomography

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