Thermodynamic state investigation of the hypersonic air plasma flow produced by the arc-jet facility SCIROCCO

Cipullo, A.; Savino, L.; Marenna, Elisa; Filippis, F. De

doi:10.1016/j.ast.2011.09.002

Cited by 10 publications

(2 citation statements)

References 7 publications

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“…The estimation of the measurement error on the rotational temperature was carried out applying the procedure described in details in work 13 . Fixing the T vib = 1073 K and varying T rot , the resulting RMSE is showed in Figure 6.…”

Section: Figure 5comparison Between Experimental Spectrum and Fittedmentioning

confidence: 99%

Non-Intrusive Characterization and Numerical Investigation on a Mach 10 Ionized Air Flow

Cristofolini

Neretti

Borghi

et al. 2012

43rd AIAA Plasmadynamics and Lasers Conference

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This paper deals with the measurements performed to characterize the jet produced by the plasma wind tunnel SCIROCCO. The measurements are aimed to determine the vibrational temperature and the electron density of the plasma flow. A numerical rebuilding of the expansion trough the nozzle has then been performed. The work is part of an experimental activity funded by the European Space Agency and by the Italian Space Agency in the framework of a conjunct research project on the MHD interaction in an unseeded hypersonic air flow.

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Section: Figure 5comparison Between Experimental Spectrum and Fittedmentioning

confidence: 99%

Non-Intrusive Characterization and Numerical Investigation on a Mach 10 Ionized Air Flow

Cristofolini

Neretti

Borghi

et al. 2012

43rd AIAA Plasmadynamics and Lasers Conference

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“…Centre)was the biggest scale of arc-jet facility that aims test a full scale component of spacecrafts [8]. Although long duration experiment can study the in-depth material response for ablation, the plasma flow was not the exactly same aero-thermodynamics condition to the real re-entry.…”

Section: Ablation Testing In Long Duration Facilitymentioning

confidence: 99%

Development of a hot-wall hemispherical model for ablation studies

Tseung¹

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During atmospheric re-entry, a space vehicle must withstand an extreme aerodynamic heating environment, which may lead to surface temperatures above 3000K. Thermal Protection Systems (TPS) were designed to protect the underlying metallic structure. To investigate ablation of the TPS, groundbased experiments in impulse duration facilities can be conducted to understand the aerothermodynamic surface ablation. Impulse duration facilities can reproduce a realistic re-entry flow but representative surface temperatures were only possible by pre-heating the test model (D'Souza, 2010). In previous implementations, prototypes with rectangular cross sections were successfully pre-heated to above 3000K using electrical heating (Zander, 2013). However, this does not match the geometry of real re-entry vehicles (e.g. Apollo, Stardust) which were generally blunt bodies with hemispherical nose segments. This discrepancy was addressed by this thesis which aims to design a hemispherical model which can be electrically preheated to realistic surface temperatures of approximately 3000K. The heated model was to be fabricated from graphite, as this was representative of the char layer which formed on the TPS surface after the original material undergoes pyrolysis. This thesis provided an overview on typical past methods for studying ablation in ground-testing facilities, including both longduration facilities such as arc jets and impulse facilities such as expansion tubes. The potential ablation mechanisms for carbon include oxidation, nitridation, sublimation, and mechanical spallation. Further measurements and characterisation of these processes were required to reduce TPS design uncertainties.Past re-entry spacecraft designs and studies typically used a blunt body design concept (Walter G. Vincenti, 2007), and the role of the blunted nose was discussed. In the terms of geometry design, for this work the electrical preheating calculations were validated against past experiments with rectangular cross sections. Secondly, the electrical heating and radiative cooling of hemispherical geometries were theoretically investigated to determine a cross-sectional profile which provides a uniform temperature distribution, for various grades of graphite. These predictions were then validated using the finite element method, allowing the most suitable material to be selected. Eventually, a hemispherical geometry was designed and simulated which able to preheat evenly on its out most surface.

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A novel physics methodology based on compact emission spectroscopy in the VNIR (0.4–0.9 μm) ranges for plasma shock layer/material temperature determinations and surface emissivity evaluations in the VNIR – LWIR (7–14 μm) ranges during atmospheric re-entry by PWT facility

Savino

Martucci

Vecchio

et al. 2020

Infrared Physics & Technology

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Thermodynamic state investigation of the hypersonic air plasma flow produced by the arc-jet facility SCIROCCO

Cited by 10 publications

References 7 publications

Non-Intrusive Characterization and Numerical Investigation on a Mach 10 Ionized Air Flow

Non-Intrusive Characterization and Numerical Investigation on a Mach 10 Ionized Air Flow

Development of a hot-wall hemispherical model for ablation studies

A novel physics methodology based on compact emission spectroscopy in the VNIR (0.4–0.9 μm) ranges for plasma shock layer/material temperature determinations and surface emissivity evaluations in the VNIR – LWIR (7–14 μm) ranges during atmospheric re-entry by PWT facility

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