Evaluation of SCIROCCO plasma wind-tunnel capabilities for entry simulations in CO2 atmospheres

Marieu, Vincent; Reynier, Ph.; Marraffa, L.; Vennemann, D.; Filippis, F. De; Caristia, S.

doi:10.1016/j.actaastro.2006.12.006

Cited by 32 publications

(22 citation statements)

References 4 publications

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“…A segmented arc plasma torch [6,7] was adopted as the plasma source since it is simple to scale-up the input power to the MW level and because contamination and erosion of the electrode is controllable. This plasma source can produce high enthalpy plasma flows sufficient for transferring steady-state heat fluxes greater than 10 MW/m 2 .…”

Section: Introductionmentioning

confidence: 99%

Commissioning of a high enthalpy plasma facility for testing plasma facing materials in a fusion reactor

Choi

Moon

et al. 2016

Fusion Engineering and Design

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Section: Introductionmentioning

confidence: 99%

Commissioning of a high enthalpy plasma facility for testing plasma facing materials in a fusion reactor

Choi

Moon

et al. 2016

Fusion Engineering and Design

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“…These materials must survive extreme environments with a combined (convective and radiative) heat flux of more than several MW/m 2 and a peak pressure of a few atm. To develop the thermal protection material, plasma wind tunnels that can simulate the conditions during the supersonic flight and re-entry of space vehicles have been used (6)(7)(8)(9) . High enthalpy and a high Mach number at the exit of the arc torch (with stable operation) are required, and (depending on the plasma-forming gases and the maximum heat flux) they can be utilised to test the thermal protection materials for a variety of missions.…”

Section: Introductionmentioning

confidence: 99%

Characteristics of a plasma wind tunnel for the development of thermal protection materials

et al. 2017

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Thermal plasma wind tunnels with power of 0.4 MW and 2.4 MW have been constructed at Chonbuk National University (CBNU) in Korea. This facility is capable of producing a heat flux greater than 10 MW/m2, a level that is relevant for testing thermal protection materials that are used for re-entry vehicles in space transportation. A segmented arc plasma torch was adopted as a plasma source; this was designed to have high thermal efficiency and long life, and to produce a supersonic plasma flow with enthalpy greater than 10 MJ/kg. We investigated the characteristics of the supersonic plasma flow using intrusive and non-intrusive diagnostic systems. Ablation characteristics of potential thermal protection materials such as carbon/carbon composites and graphite were investigated with the plasma wind tunnel. Cracks and pores in the materials accelerated the erosion. For carbon/carbon composites, the pores grew and the cracks which occurred at the interfaces between the carbon fibres and the matrix propagated, while for the graphite, the erosion started at the pores and peeled off the surface.

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“…In fact, the usual performance envelope is different, and the presence of large fraction of CO for medium range enthalpy has to be considered [11]. As a consequence, test facilities have to be capable of operating with carbon dioxide and of reproducing flight conditions typical of Martian entry and ascent.…”

Section: Mars Entrymentioning

confidence: 99%

Survey of European and Major ISC Facilities for Supporting Mars and Sample Return Mission Aerothermodynamics and Tests Required for Thermal Protection System and Dynamic Stability

Bugel¹,

Reynier²,

Smith

2011

International Journal of Aerospace Engineering

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In the frame of future sample return missions to Mars, asteroids, and comets, investigated by the European Space Agency, a review of the actual aerodynamics and aerothermodynamics capabilities in Europe for Mars entry of large vehicles and high-speed Earth reentry of sample return capsule has been undertaken. Additionally, capabilities in Canada and Australia for the assessment of dynamic stability, as well as major facilities for hypersonic flows available in ISC, have been included. This paper provides an overview of European current capabilities for aerothermodynamics and testing of thermal protection systems. This assessment has allowed the identification of the needs in new facilities or upgrade of existing ground tests for covering experimentally Mars entries and Earth high-speed reentries as far as aerodynamics, aerothermodynamics, and thermal protection system testing are concerned.

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Evaluation of SCIROCCO plasma wind-tunnel capabilities for entry simulations in CO2 atmospheres

Cited by 32 publications

References 4 publications

Commissioning of a high enthalpy plasma facility for testing plasma facing materials in a fusion reactor

Commissioning of a high enthalpy plasma facility for testing plasma facing materials in a fusion reactor

Characteristics of a plasma wind tunnel for the development of thermal protection materials

Survey of European and Major ISC Facilities for Supporting Mars and Sample Return Mission Aerothermodynamics and Tests Required for Thermal Protection System and Dynamic Stability

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