Development of a steady-state shape change ablation code for the design of outer planet probes

Brewer, R. A.; Brant, D.; Fogaroli, R.

doi:10.2514/6.1977-95

“…COLTS, 30 a viscous shock-layer code developed at NASA Langley Research Center, provided computational uid dynamics (CFD) predictions of heat shield recession. 2 The thermodynamic outer planets insulation code (TOPIC) 31 was the primary design tool used by the General Electric Re-Entry Systems Division to predict heat shield recession. 3 TOPIC was an engineering code that combined computations and correlations of CFD and experimental data for shock shape, pressure distribution, carbon ablation thermochemistry, convective and radiative heat transfer and blockage, spallation, and other factors.…”

Section: Comparison With Predictionsmentioning

confidence: 99%

Galileo Probe Heat Shield Ablation Experiment

Milos

¹

1997

Journal of Spacecraft and Rockets

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The Galileo Probe deceleration module contained an experiment that measured the surface recession of the forebody heat shield during the hypersonic entry into the Jovian atmosphere. A detailed description of the experiment, reduction of the recession data, reconstruction of the heat-shield shape history, and comparisons with pre ight predictions are presented. Sensor performance was compromised by an extraneous signal during the rst half of the hypersonic entry, but data quality was reasonably good for the second half of the entry. To within measurement accuracy the ablation was axisymmetric, and the nal shape was well de ned. Stagnation point recession was signi cantly less than predicted. Frustum recession exceeded predictions and was comparable to stagnation point recession. Nomenclature

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“…COLTS, 30 a viscous shock-layer code developed at NASA Langley Research Center, provided computational uid dynamics (CFD) predictions of heat shield recession. 2 The thermodynamic outer planets insulation code (TOPIC) 31 was the primary design tool used by the General Electric Re-Entry Systems Division to predict heat shield recession. 3 TOPIC was an engineering code that combined computations and correlations of CFD and experimental data for shock shape, pressure distribution, carbon ablation thermochemistry, convective and radiative heat transfer and blockage, spallation, and other factors.…”

Section: Comparison With Predictionsmentioning

confidence: 99%

Galileo probe heat shield ablation experiment

Milos

¹

1996

31st Thermophysics Conference

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The Galileo Probe deceleration module contained an experiment that measured the surface recession of the forebody heat shield during the hypersonic entry into the Jovian atmosphere. A detailed description of the experiment, reduction of the recession data, reconstruction of the heat-shield shape history, and comparisons with pre ight predictions are presented. Sensor performance was compromised by an extraneous signal during the rst half of the hypersonic entry, but data quality was reasonably good for the second half of the entry. To within measurement accuracy the ablation was axisymmetric, and the nal shape was well de ned. Stagnation point recession was signi cantly less than predicted. Frustum recession exceeded predictions and was comparable to stagnation point recession.

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“…entry [57,66,67]. Another issue was the turbulence that has been extensively investigated [57,59,66,67]. Rarefied effects were also investigated for the mission preparation [68].…”

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

2

0

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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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Development of a steady-state shape change ablation code for the design of outer planet probes

Cited by 34 publications

References 6 publications

Galileo Probe Heat Shield Ablation Experiment

Galileo Probe Heat Shield Ablation Experiment

Galileo probe heat shield ablation experiment

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

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