Experimental and Numerical Investigation of Martian Atmosphere Entry

Paterna, D.; Monti, R.; Savino, Raffaele; Espósito, Antonio

doi:10.2514/2.3804

Cited by 36 publications

(17 citation statements)

References 11 publications

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“…Unlike Earth, however, the Martian atmosphere is made up of about 95.7% carbon dioxide along with other trace chemicals 2 . While catalytic heating for Earth return missions can exist, the magnitude of such heating augmentation is generally small when compared to the potential catalytic effects of a carbon dioxide environment 3 . The large negative heats of formation of carbon dioxide and carbon monoxide along with the particular kinetics of carbon dioxide dissociation behavior in the shock layer create the potential for large levels of energy release on a catalytic surface.…”

Section: Introductionmentioning

confidence: 99%

Catalytic Effects on Heat Transfer Measurements for Aerothermal Studies with CO2

MacLean

Holden

2006

44th AIAA Aerospace Sciences Meeting and Exhibit

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An investigation has been performed at CUBRC using the LENS facilities to study the behavior of surface heating augmentation due to catalytic surface recombination for carbon dioxide and air test gases. Three types of heat transfer instrumentation have been employed on a model that shows definitive heating enhancement which can only be caused by the effect of surface catalysis. The measured heat transfer data from all types of instrumentation correlate well with CFD predictions in baseline non-catalytic flows, but show consistently higher heating levels than can be predicted with a non-catalytic wall in a catalytic environment. A similar effect has been documented in air with atomic oxygen and nitric oxide recombination. The successful demonstration and understanding of this behavior is critical to optimum heat shield/TPS systems design for future Martian entry applications.

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Section: Introductionmentioning

confidence: 99%

Catalytic Effects on Heat Transfer Measurements for Aerothermal Studies with CO2

MacLean

Holden

2006

44th AIAA Aerospace Sciences Meeting and Exhibit

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“…Steady-state simulations are performed by a pseudo-time integration algorithm based on an explicit fivestage Runge-Kutta scheme. A more detailed description of the numerical technique may be found in [12,18]. A sketch of the computational grid is shown in Fig.…”

Section: Boundary Layer Thermal Protection Of the Vehicle Structurementioning

confidence: 99%

A low risk reentry: looking backward to step forward

Monti

Paterna

2006

Aerospace Science and Technology

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“…Attempts to predict radiative heating along the whole surface of space vehicle pose a number of additional problems of radiation heat transfer in shock layer and wake regions. General ways for verification and validation all of such models and codes are the comparison with available experimental and flight data such as [36,[39][40][41][42]. Unfortunately, the list of the data, is utterly small.…”

Section: Martian Entrymentioning

confidence: 99%

“…A lot of obtained calculation and experimental data [36][37][38][39][40][41][42] allow form general representation about aerothermodynamics of Martian entry aerothermodynamics. All these data were undoubtedly used at successfully realized Martian missions.…”

Section: Martian Entrymentioning

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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Experimental and Numerical Investigation of Martian Atmosphere Entry

Cited by 36 publications

References 11 publications

Catalytic Effects on Heat Transfer Measurements for Aerothermal Studies with CO2

Catalytic Effects on Heat Transfer Measurements for Aerothermal Studies with CO2

A low risk reentry: looking backward to step forward

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

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