Isotherm Sensor Calibration Program for Mars Science Laboratory Heat Shield Flight Data Analysis

Santos, José Maria Campos dos; Oishi, Tomo; Martinez, Ed

doi:10.2514/6.2011-3955

Cited by 22 publications

(12 citation statements)

References 3 publications

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“…with the entry of MSL into Mars' atmosphere show that such sensors are readily available in terms of in-depth thermocouples and heat flux sensors. 19,46 This already allows for spatial information on heat shield temperature distributions which provides valuable information for the thermal radiation emitted by the heat shield and also for boundary conditions for the flow near the surface.…”

Section: Future Perspectivesmentioning

confidence: 99%

Airborne Observation of Re-entries - Lessons Learned and Future Perspectives (Invited)

Winter

2014

19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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A review of airborne observation data with particular respect to the observation of the Stardust, ATV-1, and Hayabusa is given. These re-entries were observed from the NASA Airborne Observatory (in case of ATV-1 in addition from a second airplane) and, if possible, through ground based observation. A variety of experiments were used to gather data over a spectral range from 300nm to 1.6 m with different spectral resolutions to create a spectral data base to support the validation of aerothermodynamic simulation codes. A motivation for such re-entry observation is given and the basic principles and constraints of airborne observations are explained. The theoretical simulation of observation data and the re-entry missions of concern are discussed and selected results are presented. Finally, future perspectives for even more effective observation campaigns are given.

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Section: Future Perspectivesmentioning

confidence: 99%

Airborne Observation of Re-entries - Lessons Learned and Future Perspectives (Invited)

Winter

2014

19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…Currently, the isotherm sensor is going under an extensive testing and calibration program. 13 The purpose of this calibration campaign is to determine the nominal value of the isotherm and the associated uncertainties. The isotherm that this sensor tracks could depend on the temperature change rate as well as the local temperature.…”

Section: Simulated Datamentioning

confidence: 99%

Time-dependent Estimation of Mars Science Laboratory Surface Heating from Simulated MEDLI data

Mahzari

Braun

2012

43rd AIAA Thermophysics Conference

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There are substantial uncertainties in the computational models currently used to predict the heating environment and the Thermal Protection System (TPS) material response during Mars entry. Flight data is required to quantify and possibly reduce such uncertainties as well as improve current computational tools. The Mars Science Laboratory (MSL) Entry, Descent and Landing Instrumentation (MEDLI) suite will provide a comprehensive set of flight data which will include subsurface temperature measurements of its PICA heatshield at different locations. Accurate reconstruction of MSL surface heat flux from the flight data is a critical step in reducing these uncertainties. The purpose of this paper is to investigate the time-dependent estimation of MSL surface heating from simulated MEDLI subsurface temperature data using inverse methods in the presence of random and bias measurement and model errors. The surface heat flux is indirectly reconstructed by estimating the discretized surface heat transfer coefficient profile as a function of time. Whole-time domain least-squares methods in conjunction with the Tikhonov regularization technique are applied to this problem. The analysis is performed for the instrument plugs at the lowest and highest heating locations. The performance of the estimation methods and the accuracy of the reconstructed surface conditions are investigated under different types of errors in the measurements such as random noise and thermocouple lag. Furthermore, the effect of material property bias on the estimation of surface conditions is also studied. Nomenclature A = Surface area B' = Dimensionless surface blowing rate C H = FIAT heat transfer coefficient = ρ e u e c h Cp = Specific heat h = Enthalpy, contact conductance H1 = First-order Tikhonov regularization matrix H R = Total recovery enthalpy J = Sensitivity matrix ṁ = Surface blowing rate M = Number of measurements N = Number of discretized C H points p = Pressure P = Vector of estimation parameters q = Heat flux S = Sum of square of errors (objective function) t = Time T = Temperature T = Vector of direct problem outputs (FIAT predictions) V = Volume Y = Vector of measurements α = Surface absorptivity 2 ε = Surface emissivity µ = Regularization parameter ρ = Density σ = Stefan-Boltzmann constant Subscripts c = Char cond = Conduction g = Pyrolysis gas host = Host material rad = Radiative w = Material surface wire = TC wire properties ∞ = Freestream Superscripts BE = Best-estimate k = Iteration number Nom = Nominal T = Transpose of a matrix

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“…In this paper, we limit the analysis to the plugs that experience the highest and lowest surface heating, T2 and T4, respectively, to bound the range of surface heating expected by MISP plugs in flight. Currently, the isotherm sensor is going under an extensive testing and calibration program [13]. The purpose of this calibration campaign is to determine the nominal value of the isotherm and the associated uncertainties.…”

Section: Simulated Datamentioning

confidence: 99%

Time-Dependent Mars Entry Aeroheating Estimation from Simulated In-Depth Heat Shield Temperature Measurements

Mahzari

Braun

2013

Journal of Thermophysics and Heat Transfer

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There are substantial uncertainties in the computational models currently used to predict the heating environment and the Thermal Protection System material response during Mars entry. Flight data are required to quantify and possibly reduce such uncertainties as well as improve current computational tools. The Mars Science Laboratory Entry, Descent, and Landing Instrumentation suite will provide a comprehensive set of flight data that will include subsurface temperature measurements of its Phenolic Impregnated Carbon Ablator heatshield at different locations. The purpose of this paper is to investigate the time-dependent estimation of Mars Science Laboratory surface heating from simulated Mars Science Laboratory Entry, Descent, and Landing Instrumentation temperature data using inverse methods in the presence of random and bias measurement and model errors. The surface heat flux is indirectly reconstructed by estimating the discretized heat transfer coefficient profile as a function of time. Whole-time domain least-squares methods in conjunction with the Tikhonov regularization technique are applied to this problem. The performance of the estimation methods and the accuracy of the reconstructed surface conditions are investigated under different types of errors in the measurements, such as random noise and thermocouple lag. Furthermore, the effect of material property bias on the estimation of surface conditions is also studied.

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Isotherm Sensor Calibration Program for Mars Science Laboratory Heat Shield Flight Data Analysis

Cited by 22 publications

References 3 publications

Airborne Observation of Re-entries - Lessons Learned and Future Perspectives (Invited)

Airborne Observation of Re-entries - Lessons Learned and Future Perspectives (Invited)

Time-dependent Estimation of Mars Science Laboratory Surface Heating from Simulated MEDLI data

Time-Dependent Mars Entry Aeroheating Estimation from Simulated In-Depth Heat Shield Temperature Measurements

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