Heatshield erosion in a dusty Martian atmosphere

Papadopoulos, Periklis; Tauber, Michael E.; Chang, I-Dee

doi:10.2514/3.11522

Cited by 43 publications

(18 citation statements)

References 23 publications

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“…However, the work of Palmer et al [9] opposed the findings of Papadopoulos et al [8] by stating that the heat flux due to impingement of the particles onto the entry vehicle surface was overestimated previously. The reason the work by Palmer et al [9] saw less surface erosion due to dust than Papadopoulos et al [8] was that the dust model used in the two analyses was different. The model used by Papadopoulos et al assumed larger average dust particle sizes and more of them.…”

Section: State Of the Artmentioning

confidence: 93%

“…A mass loss and an increase in heat flux caused by the particles were observed. Besides experimental work, Papadopoulos et al [8] numerically analyzed the influence of dust particles onto the vehicle during Martian entry and found a significant increase of heat flux due to impingement of the particles. However, the work of Palmer et al [9] opposed the findings of Papadopoulos et al [8] by stating that the heat flux due to impingement of the particles onto the entry vehicle surface was overestimated previously.…”

Section: State Of the Artmentioning

confidence: 99%

“…Besides experimental work, Papadopoulos et al [8] numerically analyzed the influence of dust particles onto the vehicle during Martian entry and found a significant increase of heat flux due to impingement of the particles. However, the work of Palmer et al [9] opposed the findings of Papadopoulos et al [8] by stating that the heat flux due to impingement of the particles onto the entry vehicle surface was overestimated previously. The reason the work by Palmer et al [9] saw less surface erosion due to dust than Papadopoulos et al [8] was that the dust model used in the two analyses was different.…”

Section: State Of the Artmentioning

confidence: 99%

See 2 more Smart Citations

Two-Phase Flow Solver for Hypersonic Entry Flows in a Dusty Martian Atmosphere

Majid

Bauder

Herdrich

et al. 2016

Journal of Thermophysics and Heat Transfer

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The occurrence of global dust storms on Mars is one of the most spectacular meteorological events in the solar system. The following question arises: What influence might dust particles have on the heat flux onto a heat shield of a planetary probe entering the Martian atmosphere? For the numerical simulation of such an entry, the sequential iterative nonequilibrium algorithm program previously developed at the Institut für Raumfahrtsysteme is used. A five-species model (CO 2 , O 2 , CO, O, and C) is implemented in the code. The Euler-Lagrangian approach is used for the modeling and simulation of the solid dust particles in the hypersonic entry flow. An adequate model for the drag force computation is implemented. The heat transfer model of the particles consists of convective heating and radiation cooling. With these models, heat fluxes onto the heat shield of the Mars sample return orbiter spacecraft due to impingement of particles are computed and compared with the convective heat fluxes from the continuum flowfield for the exemplary conditions of test case 3. From these simulations, it is found that the ratio of heat flux due to impingement of the particles compared to convective heat flux of the flowfield gas is very low. However, particles with larger radii may generate significant heat fluxes and erosion on the wall of the particle.

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Section: State Of the Artmentioning

confidence: 93%

Section: State Of the Artmentioning

confidence: 99%

Section: State Of the Artmentioning

confidence: 99%

See 1 more Smart Citation

Two-Phase Flow Solver for Hypersonic Entry Flows in a Dusty Martian Atmosphere

Majid

Bauder

Herdrich

et al. 2016

Journal of Thermophysics and Heat Transfer

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show abstract

“…Even during the quiet season (with much less storms), the probability of a storm is never null and a local one can evolve in a global storm within few days. The presence of the particles would increase TPS recession and overheating [16,17] of the substructure material.…”

Section: Mars Entrymentioning

confidence: 99%

Survey of European and Major ISC Facilities for Supporting Mars and Sample Return Mission Aerothermodynamics and Tests Required for Thermal Protection System and Dynamic Stability

Bugel¹,

Reynier²,

Smith

2011

International Journal of Aerospace Engineering

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In the frame of future sample return missions to Mars, asteroids, and comets, investigated by the European Space Agency, a review of the actual aerodynamics and aerothermodynamics capabilities in Europe for Mars entry of large vehicles and high-speed Earth reentry of sample return capsule has been undertaken. Additionally, capabilities in Canada and Australia for the assessment of dynamic stability, as well as major facilities for hypersonic flows available in ISC, have been included. This paper provides an overview of European current capabilities for aerothermodynamics and testing of thermal protection systems. This assessment has allowed the identification of the needs in new facilities or upgrade of existing ground tests for covering experimentally Mars entries and Earth high-speed reentries as far as aerodynamics, aerothermodynamics, and thermal protection system testing are concerned.

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“…Particles impacting the window may pit the window, causing the window and the optics to deteriorate. 29 In this case an impact sensor can be used to count particles. These situations have not been investigated at present.…”

Section: Signal-to-noise Ratiomentioning

confidence: 99%

Feasibility of determining haze properties during high-speed Titan entry

Nelson

1994

Journal of Thermophysics and Heat Transfer

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An international cooperative project between the National Aeronautics and Space Administration and the European Space Agency is planning to send a probe into the atmosphere of Titan (a moon of Saturn) as part of the Cassini Mission to Saturn. This article analyzes the feasibility of measuring the intensity of atomic carbon and hydrogen line emission in the shock layer during the high-velocity portion of the entry to determine the number density and composition of the organic haze particles in the Titan atmosphere. Analysis indicates that the line radiation signal-to-noise ratios are high enough so that determination of the haze particle number density and composition appears to be feasible. The analysis may be applicable to other future planetary Nomenclature A ul = Einstein coefficient for spontaneous emission, 1/s C p = particle specific heat, 1.80 kJ/(kg-K) c = speed of light D = particle diameter, m/x d {} = gas-molecule diameter, 6.0 x 10~1 () rn E u = energy of upper state, J Fi_ 2 = view-factor for radiometer g fl = degeneracy of upper state of transition H = enthalpy, kJ/kg h = Planck's constant, J/K / A = radiation emission, w/(cm 3 -stradian) K np = Knudsen number of haze particle k = Boltzmann's constant, J-s L -particle vaporization energy, J/kg L () = particle heat of evaporation, 360 kJ/kg N •= number density, I/cm 3 P = gas pressure, Pa P -particle flow rate, particles/(cm' 2 -s) Q = total heat transfer, J Q c = convective heat transfer rate, W Q r = radiative heat transfer rate, W q c = convective flux to haze particle, W/cm 2 4, = radiative flux to haze particle, W/cm 2 R = radius of view-cylinder, cm S = photons emitted S = photon emission rate, photons/s T = temperature, K 7 1 ,.= vibrational temperature, K va P = particle evaporation temperature, 300 K t = time, s /,. = particle evaporation time, s V = velocity, m/s V v fl = view-volume times solid angle, stradian-cm 3 V (} = initial entry velocity, 6220 m/s x = distance in front of window, cm Z = electronic partition function

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Heatshield erosion in a dusty Martian atmosphere

Cited by 43 publications

References 23 publications

Two-Phase Flow Solver for Hypersonic Entry Flows in a Dusty Martian Atmosphere

Two-Phase Flow Solver for Hypersonic Entry Flows in a Dusty Martian Atmosphere

Survey of European and Major ISC Facilities for Supporting Mars and Sample Return Mission Aerothermodynamics and Tests Required for Thermal Protection System and Dynamic Stability

Feasibility of determining haze properties during high-speed Titan entry

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