Experimental Investigation on Transpiration Cooling Effectiveness for Spacecraft Entering Martian Atmosphere

Ibrahim, S. Mohammed; Vivek, Padmanabha; Reddy, K. P. J.

doi:10.2514/1.j054757

Cited by 8 publications

(3 citation statements)

References 14 publications

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“…Actively cooled porous thermal protection systems have potential applications in future hypersonic vehicles that are exposed to heat fluxes which cannot be managed by passive cooling [1][2][3][4][5][6][7]. Thermal management of wall temperatures and absorbed heat load of re-entry vehicles or hypersonic cruise vehicles is one of the major challenges of such systems [8].…”

Section: Introductionmentioning

confidence: 99%

Thermal Impulse Response in Porous Media for Transpiration-Cooling Systems

Hermann¹,

McGilvray²,

Ifti³

et al. 2020

Journal of Thermophysics and Heat Transfer

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A solution of the coupled differential equations for fluid and solid phase in a one-dimensional porous medium in thermal non-equilibrium is presented using the concept of analyzing the impulse response. The impulse response is shown to be sensitive to the volumetric heat transfer coefficient and the coolant mass flux. Experimental data obtained from surface heating of transpiration cooled porous ZrB 2 samples is compared to a newly developed theoretical model. The surface and backside temperature of the solid are measured using thermographic imaging and thermocouple instrumentation. The non-integer system identification approach is used to experimentally obtain the thermal impulse response which is then compared to the model prediction. Good agreement is found between the simulated and experimental data with average deviations below 10 %. The developed model provides the basis for inverse heat transfer measurements and further analysis of transpiration cooled materials. Nomenclature a Heat loss constant, W m −3 K −1 A Coefficient in Laplace-space B Coefficient in Laplace-space c p Specific heat capacity, J kg −1 K −1 C Coefficient for analytical temperature solution, K d Length of square illuminated by the laser radiation H Impulse response, K h v Volumetric heat transfer coefficient, W m −3 K −1 J Iteration parameter

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Section: Introductionmentioning

confidence: 99%

Thermal Impulse Response in Porous Media for Transpiration-Cooling Systems

Hermann¹,

McGilvray²,

Ifti³

et al. 2020

Journal of Thermophysics and Heat Transfer

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show abstract

“…Wall temperatures need to be kept below critical values, e. g. oxidation, sublimation or melting temperatures. For shape stable heat shields transpiration cooling is an approach that enables active thermal control [2][3][4][5][6][7][8]. It relies on a gaseous or liquid fluid which is fed through a porous solid material [9][10][11][12][13][14].…”

Section: Introductionmentioning

confidence: 99%

“…with density ρ and velocity u. Studies are excluded where the Reynolds number or blowing ratio could not be inferred from the published data [8,[29][30][31][32][33], or where other geometries were used [4,7,14,[34][35][36][37][38][39].…”

Section: Introductionmentioning

confidence: 99%

Performance of Transpiration-Cooled Heat Shields for Reentry Vehicles

2020

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This paper presents results of a system study of transpiration cooled thermal protection systems for Earth re-entry. The cooling performance for sustained hypersonic flight and transient re-entry of a blunt cone geometry is assessed. A simplified numerical model is used to calculate the transient temperature of a transpiration cooled heat shield. The performance of transpiration cooling is assessed by calculating the overall required coolant mass for different steady state and transient flight scenarios. Spatially and temporally optimised mass injection is presented for various flight conditions. The majority of the injection is required on the spherical nose segment of the blunted cone. Carbon/Carbon composite ceramic and the ultra high temperature ceramic Zirconium diboride are considered as wall materials. Both materials require similar amounts of coolant injection. In continuous hypersonic cruise, transpiration cooling is highly effective for flight conditions with velocities below 8 km s −1 and altitudes above 40 km. For transient re-entry, transpiration cooling is most viable for trajectories of entry velocities below 8.5 km s −1 and ballistic coefficients below 2.1 kg m −2. Nomenclature A Area, m 2 C D Drag coefficient c p Specific heat capacity, J kg −1 K −1

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Fundamental of Shock Waves and Shock Tube

Vivek

Sitharam

2019

Granular Materials Under Shock and Blast Loading

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Experimental Investigation on Transpiration Cooling Effectiveness for Spacecraft Entering Martian Atmosphere

Cited by 8 publications

References 14 publications

Thermal Impulse Response in Porous Media for Transpiration-Cooling Systems

Thermal Impulse Response in Porous Media for Transpiration-Cooling Systems

Performance of Transpiration-Cooled Heat Shields for Reentry Vehicles

Fundamental of Shock Waves and Shock Tube

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