Recent advances in computational analysis of hypersonic vehicles

Walter, Robert F.

doi:10.1007/bf00797649

Cited by 3 publications

(2 citation statements)

References 12 publications

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“…As it was mentioned above the non-equilibrium radiation heat transfer processes can be significant for large-scale spacecraft of the new generation (with blunt radiuses ~ 5 m) even at orbital entry (V ∞ ~ 7 km/s), at least at high altitudes (H ~ 80 km) where intensities of radiative and convective heating are not so much as at region of maximal heating load (at altitudes H ~ 60-70 km). It was predicted [12,13] and found [2,3] that for high altitudes of such space vehicles the radiative gas dynamic interaction becomes also significant. It means that taking into account radiation heat processes in energy conservation equation results in significant rebuilding of the gas dynamic fields.…”

Section: Somementioning

confidence: 99%

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.

show abstract

Section: Somementioning

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

“…It was predicted [12,13] and found [2,3] that for high altitudes of such space vehicles the radiative gas dynamic interaction becomes also significant. It means that taking into account radiation heat processes in energy conservation equation results in significant rebuilding of the gas dynamic fields.…”

mentioning

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

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.

show abstract

Coupled radiative gasdynamic interaction and non-equilibrium dissociation for large-scale returned space vehicles

Суржиков

2012

Chemical Physics

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Recent advances in computational analysis of hypersonic vehicles

Cited by 3 publications

References 12 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

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

Coupled radiative gasdynamic interaction and non-equilibrium dissociation for large-scale returned space vehicles

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