Radiative Gas Dynamics of Martian Space Vehicles

Суржиков, С. Т.; Omaly, Pierre

doi:10.2514/6.2011-452

Cited by 16 publications

(20 citation statements)

References 9 publications

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“…Detailed description of the base aero-physical model is presented in [43,49]. Numerical simulation results obtained [43].…”

Section: Initial Conditions For Numerical Simulationmentioning

confidence: 99%

“…Numerical simulation results on radiative aerothermodynamics of Martian entry probes were presented in [43][44][45][46][47][48][49][50]. These papers contain calculated data obtained with two-and three-dimensional codes.…”

Section: Martian Entrymentioning

confidence: 99%

“…Preliminary results of systematic computational fluid dynamics (CFD) investigations of radiation aerothermodynamics of Martian entry probes were presented in [43][44][45][46][47][48][49]. Different kinds of entry probes and different freestream conditions were analyzed with the purpose of determination of intensity of convective and radiative heating along entry trajectories.…”

Section: Initial Conditions For Numerical Simulationmentioning

confidence: 99%

See 2 more Smart Citations

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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“…Detailed description of the base aero-physical model is presented in [43,49]. Numerical simulation results obtained [43].…”

Section: Initial Conditions For Numerical Simulationmentioning

confidence: 99%

Section: Martian Entrymentioning

confidence: 99%

Section: Initial Conditions For Numerical Simulationmentioning

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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“…In some conditions, the radiative heat flux is effective when the convective and conductive contributions are negligible [1][2][3].…”

Section: Introductionmentioning

confidence: 99%

Advanced Models in Shock Waves

Colonna¹,

Ammando²,

Dikalyuk³

et al. 2014

TOPPJ

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Abstract:The paper presents three collisional-radiative models developed to investigate non-equilibrium chemistry and radiation in hypersonic shock tubes operating with different planetary atmospheres. An hybrid collisional-radiative model, employing the state-to-state kinetics of electronically excited states of molecules and the multi-temperature approximation for the vibrational degree of freedom is presented first, and applied to the numerical rebuilding of experimental shock tube emission spectra. Next, an hybrid collisional-radiative model for ionized air is presented. This model consider the state-tostate approach for electronic states of atoms and the multi-temperature model for the vibrational populations of diatomic molecules in their ground electronic state. A radiative transport equation is also solved to determine radiative source terms in the kinetic scheme and the enthalpy production due to radiation. The third model considers the state-to-state collisionalradiative model of Jupiter's atmosphere, self-consistently coupled with the Boltzmann equation for free electrons and the radiative transfer equation for the radiation transport in one-dimensional slab geometry.

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“…Models of the ExoMars spacecraft [1][2][3] and variants of the X-43 air intake [4][5][6][7][8][9] were first tested in the hypersonic aerodynamic shock tube (HAST) [10-13] facility. The shock-wave structures of the gas flow under Mach numbers M=7…4.5 around the model surfaces were filmed by high-speed video camera.…”

mentioning

confidence: 99%

Preliminary experimental assessment of supersonic airflow behavior over ExoMars and X–43 inlet models using multiple flow regime shock tube

Kotov

Ruleva

Solodovnikov

et al. 2018

J. Phys.: Conf. Ser.

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Abstract. Models of the ExoMars spacecraft [1][2][3] and variants of the X-43 air intake [4][5][6][7][8][9] were first tested in the hypersonic aerodynamic shock tube (HAST) [10-13] facility. The shock-wave structures of the gas flow under Mach numbers M=7…4.5 around the model surfaces were filmed by high-speed video camera. The obtained data were analyzed using image recognition software systems. Preliminary estimates of the flow behavior over the investigated models in the test section of the installation during the whole test are given.

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Radiative Gas Dynamics of Martian Space Vehicles

Cited by 16 publications

References 9 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

Advanced Models in Shock Waves

Preliminary experimental assessment of supersonic airflow behavior over ExoMars and X–43 inlet models using multiple flow regime shock tube

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