Numerical Simulation of control of plasma flow with magnetic field for thermal protection in Earth reentry flight

Fujino, Takayasu; Ishikawa, Masatoshi

doi:10.1109/tps.2006.872458

Cited by 47 publications

(19 citation statements)

References 13 publications

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“…Free stream conditions used are density ρ∞ = 1.48 gm -3 , pressure p∞ = 132Pa and temperature T∞ = 300K, corresponding to air properties of atmosphere at an altitude of 40 km [88]. A blunt-body diameter D = 1.6 m has been taken into consideration and in all the cases the imposed initial magnetic field is uniform and perpendicular to the flow direction.…”

Section: Numerical Analysismentioning

confidence: 99%

See 1 more Smart Citation

Radiative Aerothermodynamics of Entering Space Vehicles: Toward the Use of State-to-State Approach

Суржиков¹,

Reynier²,

Seller³

et al. 2014

TOPPJ

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Modern problems of radiative aerothermodynamics of entering space vehicles are demonstrated and analyzed in the paper. New radiative gas dynamic problems concerned to coupling processes of non-equilibrium dissociation with radiation heat transfer in shock layers generated above large scale re-entry space vehicles returning from orbital and super orbital space mission are considered in the first part.Three-dimensional numerical simulation data on radiative aerothermodynamics of Martian entry probes Pathfinder, Exomars and Mars Science Laboratory (MSL) are presented and analyzed in the second part. It is shown that integral radiative heating of leeward surface of the entry probes exceeds corresponding convective heating.The third part is dedicated to consideration preliminary numerical simulation results on radiative gas dynamics of Galileo probes. At first, a review of the available results obtained during the mission preparation and post-flight analyses has been undertaken to select a computational matrix. This matrix has been selected by accounting for previous numerical efforts from the literature to crosscheck the results. Then, a model based on previous efforts has been set up for computing the flow-field around the probe at high altitude. Finally the test case matrix has been computed and crosschecked with existing numerical predictions performed.Some possibilities of innovative magneto-hydrodynamic (MHD) technologies being applied to solve problems of re-entry vehicles heat protection are discussed in the fourth part.All presented data demonstrate necessity of further development of the radiative aerothermodynamics based on state-tostate approaches.

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Section: Numerical Analysismentioning

confidence: 99%

“…Up to now, only few works using upwind methods with a self-consistent, finite and non-homogeneous electrical conductivity have been afforded [88][89][90][91][92]. For this reason, in this work we have developed a two-dimensional MHD model describing a chemically reacting nitrogen hypersonic flow past a bluntbody.…”

Section: Introductionmentioning

confidence: 99%

Radiative Aerothermodynamics of Entering Space Vehicles: Toward the Use of State-to-State Approach

Суржиков¹,

Reynier²,

Seller³

et al. 2014

TOPPJ

View full text Add to dashboard Cite

show abstract

“…However, it can be simplified for a hypersonic re-entry flow by neglecting the Hall and ion-slip effects [10]. In the plasma region produced behind the shock, the ion-slip effect does not have a considerable influence on the electric current [21]. The Hall effect is also not important in this case because it does not have a negative influence on the usefulness of a MHD flow control system [22].…”

Section: B Mhdmentioning

confidence: 99%

Plasma manipulation using a MHD-based device for a communication blackout in hypersonic flights

Kim

Gülhan

2011

Proceedings of 5th International Conference on Recent Advances in Space Technologies - RAST2011

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When a vehicle flies with hypersonic velocity, a weakly ionized plasma layer is generated around the vehicle due to the shock heated air. Since the created plasma layer has a high electron number density, the vehicle has a communication difficulty known as radio blackout. In this study, we propose an innovative concept of a mitigation scheme based on MHD. The proposed mitigation scheme uses an ExB layer to manipulate the plasma density in a specific region during hypersonic flights. Due to the reduced electron number density in the plasma layer, it provides the possibility for communication during radio blackout.

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“…As can be seen, the re-entry flow requires a multi-species chemistry model. 8 In this study, the following eleven species air chemistry model is considered: N, O, N 2 , O 2 , NO, N + , O + , N + 2 , O + 2 , NO + , and e − . The governing equations for the ExB layer with the eleven chemical species are composed mainly of two parts, which are the flow field and the electric field.…”

Section: Numerical Modelingmentioning

confidence: 99%

Numerical Modeling of Plasma Manipulation Using an ExB Layer in the Hypersonic Boundary Layer

Kim

Boyd²,

Keidar

2009

40th AIAA Plasmadynamics and Lasers Conference

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When a vehicle flies with hypersonic velocity or re-enters the atmosphere, a weakly ionized plasma layer is generated around the vehicle due to the shock heated air. Since the created plasma layer has a high plasma number density, the vehicle has a communication problem known as radio blackout. In this study, we illustrate that an applied ExB layer can manipulate the plasma density in a specific region. The manipulated plasma reduces radio wave attenuation in the plasma layer and provides the possibility for communication during radio blackout. The possibility of the ExB layer mitigation scheme is evaluated in a realistic operating condition for a hypersonic flow in terms of signal attenuation.

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Numerical Simulation of control of plasma flow with magnetic field for thermal protection in Earth reentry flight

Cited by 47 publications

References 13 publications

Radiative Aerothermodynamics of Entering Space Vehicles: Toward the Use of State-to-State Approach

Radiative Aerothermodynamics of Entering Space Vehicles: Toward the Use of State-to-State Approach

Plasma manipulation using a MHD-based device for a communication blackout in hypersonic flights

Numerical Modeling of Plasma Manipulation Using an ExB Layer in the Hypersonic Boundary Layer

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