Simulation of radiating CO2-N2 shock layer experiments at hyperbolic entry conditions

Potter, Daniel; Eichmann, Troy N.; Brandis, Aaron M.; Morgan, Richard G.; Jacobs, Peter A.; McIntyre, Timothy J.

doi:10.2514/6.2008-3933

Cited by 12 publications

(7 citation statements)

References 23 publications

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“…Chemical kinetic calculations are performed following the works of Park et al [4] and Lee et al [31]. Park et al's model [4] has been widely validated by various shock-tube experiments since 1994 [3,6,31]. This model has also been extensively used to study nonequilibrium radiation for Mars entry [8,14,32] and has served as a foundation in developing more precise models, such as threetemperature models and collisional-radiative models [16,17].…”

Section: Chemical Kinetic Calculationsmentioning

confidence: 99%

“…However, future Mars exploration systems, especially those in support of crewed missions, will be larger landers and have higher-speed entries. Radiative heating, which can be comparable to or even greater than convective heating, will make an important contribution to the entry heating environment [2] (e.g., radiation is predicted to contribute at least 80% of the total heat flux at velocities over 8.5 km∕s [3]). As we know, the radiation intensity strongly depends on physical and chemical phenomena occurring in the shock layer in front of the heat shield of a space probe.…”

Section: Introductionmentioning

confidence: 99%

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Experimental and Numerical Study of Carbon-Dioxide Dissociation for Mars Atmospheric Entry

Lin

Chen

et al. 2018

Journal of Thermophysics and Heat Transfer

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The mechanism of CO 2 dissociation during entry in the Mars atmosphere is experimentally investigated. A hydrogen-oxygen combustion-driven shock tube is used to simulate physical and chemical conditions in a CO 2-N 2 mixture. Two shock velocity/initial pressure conditions are studied: 7.09 0.05 km∕s at 100 Pa (called the low-pressure condition) and 5.68 0.07 km∕s at 300 Pa (called the high-pressure condition). The temperature behind the shock wave is obtained by analyzing the high-temporal-resolution and high-spatial-resolution experimental spectra of the CN violet (B 2 Σ → X 2 Σ , Δv 0) system. The CO number density is derived using a tunable diode laser absorption spectroscopy system based on CO absorption near 2.33 μm. Moreover, a numerical code is developed to reproduce the experimental results (temperatures and species densities). The kinetic code in this work is based on Park's two-temperature model. Comparisons between experiments and calculations are presented. Such a relatively simple two-temperature model fails to accurately describe the nonequilibrium temperature and CO number density but is suitable for equilibrium temperature predictions.

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Section: Chemical Kinetic Calculationsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Study of Carbon-Dioxide Dissociation for Mars Atmospheric Entry

Lin

Chen

et al. 2018

Journal of Thermophysics and Heat Transfer

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“…The expansion tubes of the University of Queensland [19,20] have already been run for Mars like atmosphere in the frame of an ESA TRP study; as a consequence, some of the elements available on these facilities, particularly the measurement techniques developed, have been accounted for the paper.…”

Section: Facilities Surveymentioning

confidence: 99%

“…These three facilities can reach velocities in the range of superorbital Earth re-entry; they have been successfully used in the frame of an ESA TRP [19,33] focusing on Earth highspeed reentry (and Titan entry). Moreover, since there is no equivalent in Europe for the time being, they could be used alternatively or conjunctly to ISC facilities.…”

Section: Mars Ascentmentioning

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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“…Different groups from USA, Europe, Australia, Japan, and Russia performed a number of experiments on the physical and chemical processes behind a reentry shock wave in Martian-like mixtures, especially about non-equilibrium radiation and chemical reactions [8][9][10][11][12][13] . Up to now studies, the radiation measurements have been widely studied through optical emission spectroscopy (OES), and several chemical kinetic models have been established.…”

Section: Introductionmentioning

confidence: 99%

A new flux splitting scheme for Euler equations of gas dynamics

Li¹,

Hu²,

Jiang³

2015

AIP Conference Proceedings

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Shock tube experiments are carried out to study the physical and chemical processes during a vehicle entry into the Mars atmosphere using optical emission spectroscopy (OES) and tunable diode laser absorption spectroscopy (TDLAS). Gas temperature and CO concentration distribution are diagnosed behind a shock wave in a CO 2 -N 2 mixture with two different conditions of initial pressure and velocity. The strong shock wave is established in a shock tube driven by combustion of hydrogen and oxygen. Time-resolved spectra of the Δv = 0 sequence of the B 2 Σ + →X 2 Σ + electronic transition of CN have been observed through OES. A precise analysis of the CN violet spectra is performed and used to determine rotational and vibrational temperatures. Two absorption lines in the first overtone band of CO near 2.33 μm, are selected from a HITRAN simulation to calibrate laser wavelength and detect the CO concentration. Combined with these temperature results using OES, CO concentrations in the thermal equilibrium region are derived, which are 2.91 × 10 12 cm -3 and 1.01 × 10 13 cm -3 , corresponding to equilibrium temperatures equal to 7000 ± 400 K and 6000 ± 300 K in low and high pressure conditions, respectively.

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Simulation of radiating CO2-N2 shock layer experiments at hyperbolic entry conditions

Cited by 12 publications

References 23 publications

Experimental and Numerical Study of Carbon-Dioxide Dissociation for Mars Atmospheric Entry

Experimental and Numerical Study of Carbon-Dioxide Dissociation for Mars Atmospheric Entry

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

A new flux splitting scheme for Euler equations of gas dynamics

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