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  • 1
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    Full-Scale MSL Heatshield Material Response Using DSMC and CFD to Compute the Aerothermal Environments (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: During Mars atmospheric entry, the Mars Science Laboratory (MSL) was protected by a 4.5 meters diameter ablative heatshield assembled in 113 tiles [1]. The heatshield was made of NASA's flagship ablative material, the Phenolic Impregnated Carbon Ablator (PICA) [2]. Prior work [3] compared the traditional one-dimensional and three-dimensional material response models at different locations in the heatshield. It was observed that the flow was basically one-dimensional in the nose and flank regions, but three-dimensional flow effects were observed in the outer flank. Additionally, the effects of tiled versus monolithic heatshield models were also investigated. It was observed that the 3D tiled and 3D monolithic configurations yielded relative differences for in-depth material temperature up to 18% and 28%, respectively, when compared to the a 1D model.
    Keywords: Aeronautics (General)
    Type: ARC-E-DAA-TN57503 , Annual International Planetary Probe Workshop; Jun 11, 2018 - Jun 15, 2018; Boulder, CO; United States
    Format: application/pdf
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  • 2
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    Inverse Determination of Aeroheating and Charring Ablator Response (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Mars Science Laboratory (MSL) was protected during its Mars atmospheric entry by an instrumented heatshield that used NASA's Phenolic Impregnated Carbon Ablator (PICA). PICA is a lightweight carbon fiber/polymeric resin material that offers excellent performances for protecting probes during planetary entry. The Mars Entry Descent and Landing Instrument (MEDLI) suite on MSL offers unique in-flight validation data for models of atmospheric entry and material response. MEDLI recorded, among others, time-resolved in-depth temperature data of PICA using thermocouple sensors assembled in the MEDLI Integrated Sensor Plugs (MISP). These measurements have been widely used in the literature as a validation benchmark for state-of-the-art ablation codes. The objective of this work is to perform an inverse estimate of the MSL heatshield material properties and aerothermal environment during Mars entry from the MISP flight data.
    Keywords: Aeronautics (General)
    Type: ARC-E-DAA-TN57496 , Annual International Planetary Probe Workshop (IPPW-2018); Jun 11, 2018 - Jun 15, 2018; Boulder, CO; United States
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  • 3
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    DSMC Simulations of Mars Science Laboratory Entry from Rarefied to Continuum Conditions (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Lunar and Planetary Science and Exploration; Spacecraft Design, Testing and Performance
    Type: ARC-E-DAA-TN56603 , 31st International Symposium on Rarefied Gas Dynamics; Jul 23, 2018 - Jul 27, 2018; Glasgow; United Kingdom
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  • 4
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    DSMC Simulations of Mars Science Laboratory Entry from Rarefied to Continuum Conditions (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Lunar and Planetary Science and Exploration; Spacecraft Design, Testing and Performance
    Type: ARC-E-DAA-TN59250 , International Symposium on Rarefied Gas Dynamics; Jul 23, 2018 - Jul 27, 2018; Glasgow; United Kingdom
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  • 5
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    Significance of DSMC Computed Aerothermal Environments in the Rarefied Regime for Atmospheric Entry Material Response (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: During Mars atmospheric entry, the Mars Science Laboratory (MSL) was protected by a 4.5 meters diameter ablative heatshield assembled in 113 tiles. The heatshield was made of NASA's flagship ablative material, the Phenolic Impregnated Carbon Ablator (PICA). Prior work compared the traditional one-dimensional and three-dimensional material response models at different locations in the heatshield. It was observed that the flow was basically one-dimensional in the nose and flank regions, but three-dimensional flow effects were observed in the outer flank. The objective of this work is to study the effects of the aerothermal environment on the material response. We extend prior work by computing aerothermal environments using the direct simulation Monte Carlo (DSMC) code SPARTA and the CFD code Data Parallel Line Relaxation (DPLR). SPARTA is used to compute environment in the rarefied regime prior to 48.4s of entry where the Knudsen number is such that the Navier-Stokes equations can be inaccurate. Similarly to previous work, the DPLR software is used to compute the hypersonic environment for laminar then turbulent boundary layer assumptions from 48.4 s up to 100 s after Entry Interface (EI) along the MSL 08-TPS-02/01a trajectory. We observe that extending the aerothermal environments to times prior to 48.4 s modifies the thermal response of the heat shield at the surface and in-depth; however the effects on the recession are minimal. Additionally, using the assumption of a turbulent boundary layer versus a laminar one leads to higher surface and in-depth temperatures, larger recession, and a displacement of the peak heating and peak recession location.
    Keywords: Composite Materials
    Type: ARC-E-DAA-TN61347 , Ablation Workshop; Sep 17, 2018 - Sep 18, 2018; Burlington, VT; United States
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  • 6
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    Heatshield Entry Modeling Using a Design, Analysis, and Optimization Toolbox (2019)
    In:  CASI
    Details
    Publication Date: 2019-08-07
    Description: The Mars Science Laboratory (MSL) was protected during its Mars atmospheric entry by an instrumented heatshield that used NASA's Phenolic Impregnated Carbon Ablator (PICA). PICA is a lightweight carbon fiber/polymeric resin material that offers excellent performances for protecting probes during planetary entry. The Mars Entry Descent and Landing Instrument (MEDLI) suite on MSL offers unique in-flight validation data for models of atmospheric entry and material response. MEDLI recorded, among others, time-resolved in-depth temperature data of PICA using thermocouple sensors assembled in the MEDLI Integrated Sensor Plugs (MISP). The objective of this work is to showcase the capability of the Design, Analysis, and Optimization of Thermal Protection Materials (DAOTPM) software. DAO-TPM is a Python based framework that works as a link between mission design, aerothermal and radiative environment computation, Thermal Protection Systems (TPS) microstructure analysis, material response and optimization tools. The toolbox has a Graphical User Interface (GUI) that allows the user to build as well as run the various software and utilities used to design, analyze and optimize a heatshield during atmospheric entry.
    Keywords: Fluid Mechanics and Thermodynamics; Spacecraft Design, Testing and Performance
    Type: ARC-E-DAA-TN70612 , IPPW - International Planetary Probe Workshop; Jul 08, 2019 - Jul 12, 2019; Oxford; United Kingdom
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  • 7
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    Preliminary Measurements of the Motion of Arcjet Current Channel Using Inductive Magnetic Probes (2020)
    In:  CASI
    Details
    Publication Date: 2020-01-23
    Description: This paper covers the design and first measurements of non-perturbative, external inductive magnetic diagnostics for arcjet constrictors which can measure the motion of the arc current channel. These measurements of arc motion are motivated by previous simulations using the ARC Heater Simulator (ARCHeS), which predicted unsteady arc motion due to the magnetic kink instability. Measurements of the kink instability are relevant to characterizing motion of the enthalpy profile of the arcjet, the arcjet operational stability, and electrode damage due to associated arc detachment events. These first measurements indicate 4 mm oscillations at 0.5-2 kHz of the current profile.
    Keywords: Plasma Physics
    Type: AIAA 2020-0919 , ARC-E-DAA-TN76208 , AIAA Scitech 2020 Forum; Jan 06, 2020 - Jan 10, 2020; Orlando, FL; United States
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  • 8
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    3D Unsteady Model of Arc Heater Plasma Flow Using the ARC Heater Simulator (ARCHeS) (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Aeronautics (General)
    Type: ARC-E-DAA-TN62603 , Annual Meeting of the APS Division of Plasma Physics; Nov 05, 2018 - Nov 09, 2018; Portland, OR; United States
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  • 9
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    Towards the Prediction of the Mars 2020 Heatshield Material Response (2018)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Introduction: NASAs next mission to Mars, the Mars 2020, will use the same heatshield of the Mars Science Laboratory (MSL) for thermal protection during entry, descent and landing. The heatshield is a tiled system made of Phenolic Impregnated Carbon Ablators (PICA) blocks [1]. PICA is a lightweight carbon fiber/polymeric resin material that offers excellent performances for protecting probes during planetary entry. The Mars Entry Descent and Landing Instrument (MEDLI) suite on MSL offers unique in-flight validation data for models of atmospheric entry and material response. MEDLI recorded, among others, time-resolved in-depth temperature data of PICA using thermocouple sensors assembled in the MEDLI Integrated Sensor Plugs (MISP). The objective of this work is to compare the thermal response of the MSL heatshield to the MISP flight data. In preparation to Mars 2020 post-flight analysis, the predictive material response capability is benchmarked against MEDLI flight data.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: ARC-E-DAA-TN61346 , Ablation Workshop; Sep 17, 2018 - Sep 18, 2018; Burlington, VT; United States
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  • 10
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    Full-Scale Mars Science Laboratory Tiled Heatshield Material Response (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Composite Materials; Fluid Mechanics and Thermodynamics
    Type: ARC-E-DAA-TN45965 , Ablation Workshop; Aug 30, 2017 - Aug 31, 2017; Bozeman, MT; United States
    Format: application/pdf
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