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  • 1
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    Assessment of Fencing on the Orion Heatshield (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper presents recent experimental results from arc-jet tests of the Orion heatshield that were conducted at NASA Ames Research Center. Test conditions that simulated a set of heating profiles in time representative of the Orion flight environments were used to observe their effect on Orion's block architecture in terms of differential recession or fencing. Surface recession of arc-jet models was characterized during and after testing to derive fencing profiles used for the baseline sizing of the heatshield. Arc-jet test data show that the block architecture produces varying degrees of fencing.
    Keywords: Fluid Mechanics and Thermodynamics; Spacecraft Design, Testing and Performance
    Type: ARC-E-DAA-TN27895 , AIAA Thermophysics Conference; Jun 13, 2016 - Jun 17, 2016; Washington, DC; United States
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  • 2
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    On Laminar to Turbulent Transition of Arc-Jet Flow in the NASA Ames Panel Test Facility (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper provides experimental evidence and supporting computational analysis to characterize the laminar to turbulent flow transition in a high enthalpy arc-jet facility at NASA Ames Research Center. The arc-jet test data obtained in the 20 MW Panel Test Facility include measurements of surface pressure and heat flux on a water-cooled calibration plate, and measurements of surface temperature on a reaction-cured glass coated tile plate. Computational fluid dynamics simulations are performed to characterize the arc-jet test environment and estimate its parameters consistent with the facility and calibration measurements. The present analysis comprises simulations of the nonequilibrium flowfield in the facility nozzle, test box, and flowfield over test articles. Both laminar and turbulent simulations are performed, and the computed results are compared with the experimental measurements, including Stanton number dependence on Reynolds number. Comparisons of computed and measured surface heat fluxes (and temperatures), along with the accompanying analysis, confirm that that the boundary layer in the Panel Test Facility flow is transitional at certain archeater conditions.
    Keywords: Aerodynamics
    Type: ARC-E-DAA-TN5382 , 43rd AIAA Thermophysics Conference; Jun 25, 2012 - Jun 28, 2012; New Orleans, LA; United States
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  • 3
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    Laser-Enhanced Arc-Jet Facility Wedge Tests: Avcoat Material Performance Under Convective and Radiative Heating Environments (2019)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper presents the first set of experimental results from Laser Enhanced Arc-Jet Facility (LEAF-Lite) tests that were conducted shortly after the radiative LEAF-Lite system was added to the 60-MW Interaction Heating Facility at NASA Ames Research Center. Results were gathered to characterize the new radiative and combined heating capabilities as well as the convective heating resulting from the new IHF nozzle that was required for combined heating operations. Tests were ultimately conducted at several combinations of radiative and convective heating prompted by the need to understand the effect of combined heating on the Orion heatshield material prior to pursuing combined heating tests of the more complex block architecture.
    Keywords: Spacecraft Design, Testing and Performance
    Type: ARC-E-DAA-TN62912 , Joint Thermophysics and Heat Transfer Conference; Jun 17, 2019 - Jun 21, 2019; Dallas, TX; United States
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  • 4
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    Flow Characterization Studies of the 10-MW TP3 Arc-Jet Facility: Probe Sweeps (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper reports computational simulations and analysis in support of calibration and flow characterization tests in a high enthalpy arc-jet facility at NASA Ames Research Center. These tests were conducted in the NASA Ames 10-MW TP3 facility using flat-faced stagnation calorimeters at six conditions corresponding to the steps of a simulated flight heating profile. Data were obtained using a conical nozzle test configuration in which the models were placed in a free jet downstream of the nozzle. Experimental surveys of arc-jet test flow with pitot pressure and heat flux probes were also performed at these arc-heater conditions, providing assessment of the flow uniformity and valuable data for the flow characterization. Two different sets of pitot pressure and heat probes were used: 9.1-mm sphere-cone probes (nose radius of 4.57 mm or 0.18 in) with null-point heat flux gages, and 15.9-mm (0.625 in) diameter hemisphere probes with Gardon gages. The probe survey data clearly show that the test flow in the TP3 facility is not uniform at most conditions (not even axisymmetric at some conditions), and the extent of non-uniformity is highly dependent on various arc-jet parameters such as arc current, mass flow rate, and the amount of cold-gas injection at the arc-heater plenum. The present analysis comprises computational fluid dynamics simulations of the nonequilibrium flowfield in the facility nozzle and test box, including the models tested. Comparisons of computations with the experimental measurements show reasonably good agreement except at the extreme low pressure conditions of the facility envelope.
    Keywords: Aeronautics (General); Fluid Mechanics and Thermodynamics
    Type: ARC-E-DAA-TN32374 , AIAA Thermophysics Conference; Jun 13, 2016 - Jun 17, 2016; Washington, DC; United States
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  • 5
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    CFD Simulations of the IHF Arc-Jet Flow: 9-Inch Nozzle, Flow Surveys, LEAF Wedge Calibration Data (2019)
    In:  CASI
    Details
    Publication Date: 2019-08-03
    Description: This paper reports computational analyses and flow characterization studies in a high enthalpy arc-jet facility at NASA Ames Research Center. These tests were conducted using a wedge model placed in a free jet downstream of new 9-inch diameter conical nozzle in the Ames 60-MW Interaction Heating Facility. Both the nozzle and wedge model were specifically designed for testing in the new Laser-Enhanced Arc-jet Facility. Data were obtained using stagnation calorimeters and wedge models placed downstream of the nozzle exit. Two instrumented wedge calibration plates were used: one water-cooled and the other RCG-coated tile plate. Experimental surveys of arc-jet test flow with pitot and heat flux probes were also performed at three arc-heater conditions, providing assessment of the flow uniformity and valuable data for the flow characterization. The present analysis comprises computational fluid dynamics simulations of the nonequilibrium flowfield in the facility nozzle and test box, including the models tested, and comparisons with the experimental measurements. By taking into account nonuniform total enthalpy and mass flux profiles at the nozzle inlet as well as the expansion waves emanating from the nozzle exit and their effects on the model flowfields, these simulations approximately reproduce the probe survey data and predict the wedge model surface pressure and heat flux measurements.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: ARC-E-DAA-TN68962 , AIAA & ASME Joint Thermophysics and Heat Transfer Conference; Jun 17, 2019 - Jun 21, 2019; Dallas, TX; United States
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  • 6
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    Computational Simulations of the 10-MW TP3 Arc-Jet Facility Flow (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: This paper reports computational simulations and analysis in support of calibration tests in a high enthalpy arc-jet facility at NASA Ames Research Center. These tests were conducted using stagnation calorimeters and two different blunted wedge models with calibration plates at a wide range of conditions in the NASA Ames 10-megawatt TP3 (Test Position 3) facility. Data were obtained using four different conical nozzles with the same test configuration in which the models were placed in a free jet downstream of the nozzle. Experimental surveys of arc-jet test flow with pitot and null-point heat flux probes were also performed at several arc-heater conditions, providing assessment of the flow uniformity and valuable data for the flow characterization. The present analysis comprises computational fluid dynamics simulations of the nonequilibrium flowfield in the facility nozzle and test box, including the models tested, and comparisons with the experimental measurements. These computational simulations provide estimates of the arc-jet test environment parameters that are not measured but are needed to evaluate the performance of thermal protection system materials, along with further valuable insights into the arc-jet testing environment. Simulation results are used to estimate centerline total enthalpy, surface shear, boundary layer thickness, and boundary layer edge Mach number and to verify that specific test requirements from the Orion program are met.
    Keywords: Fluid Mechanics and Thermodynamics; Spacecraft Design, Testing and Performance
    Type: ARC-E-DAA-TN23980 , AIAA Thermophysics Conference; Jun 22, 2015 - Jun 26, 2015; Dallas, TX; United States|AIAA Aviation and Aeronautics Forum (Aviation 2015); Jun 22, 2015 - Jun 26, 2015; Dallas, TX; United States
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  • 7
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    Assessment of Fencing on the Orion Heatshield (2016)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper presents recession measurements of arc-jet test articles that simulate an ablator with gap filler and were exposed to various heating profiles. Results were used to derive empirically-based differential recession models used for the baseline sizing of the Orion block heatshield architecture. The profile test conditions represent different local flight environments associated with different regions of the heatshield. Recession measurements were collected during and after arc-jet tests, and the results were used to observe the heating profiles effect on differential recession. Arc-jet tests were conducted at the Aerodynamic Heating Facility at NASA Ames Research Center.
    Keywords: Fluid Mechanics and Thermodynamics; Spacecraft Design, Testing and Performance
    Type: ARC-E-DAA-TN32134 , AIAA Thermophysics Conference; Jun 13, 2016 - Jun 17, 2016; Washington, D.C.; United States
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  • 8
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    Thermal Protection System Aerothermal Screening Tests in the HYMETS Facility (2011)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Fluid Mechanics and Thermodynamics
    Type: AIAA Thermophysics Conference; Jun 27, 2011 - Jun 30, 2011; Honolulu, HI; United States
    Format: text
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  • 9
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    Pterodactyl: Trade Study for an Integrated Control System Design of a Mechanically Deployed Entry Vehicle (2020)
    In:  CASI
    Details
    Publication Date: 2020-01-22
    Description: This paper presents a trade study method used to evaluate and down-select from a set of guidance and control (G&C) system designs for a mechanically deployable entry vehicle (DEV). The Pterodactyl project, funded by NASA's Space Technology Mission Directorate (STMD), was prompted by the challenge to develop an effective G&C system for a vehicle without a backshell, which is the case for DEVs. For the DEV, the project assumed a specific aeroshell geometry pertaining to an Adaptable, Deployable, Entry Placement Technology (ADEPT) vehicle, which was successfully developed by STMD prior to this study. The Pterodactyl project designed three different G&C systems for the vehicle's precise entry, which this paper briefly discusses. This paper details the Figures of Merit (FOMs) and metrics used during the course of the project's G&C system assessment. Each G&C configuration was traded against the three FOMs categories: G&C system performance, affordability and life cycle costs, and safety and mission success. The relative importance of the FOMs was determined from the Analytical Hierarchy Process (AHP), which was used to develop weights that were combined with quantitative design metrics and engineering judgement to rank the G&C systems against one another. This systematic method takes into consideration the project's input while simultaneously reducing unintentional judgement bias and ultimately was used to select a single G&C design for the project to continue pursuing in the next prototyping and testing phase.
    Keywords: Spacecraft Design, Testing and Performance
    Type: ARC-E-DAA-TN69534 , AIAA SciTech Forum; Jan 06, 2020 - Jan 10, 2020; Orlando, Fl; United States
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  • 10
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    Pterodactyl: Trade Study for an Integrated Control System Design of a Mechanically Deployable Entry Vehicle (2020)
    In:  CASI
    Details
    Publication Date: 2020-01-16
    Description: This paper presents the trade study method used to evaluate and downselect from a set of guidance and control (G&C) system designs for a mechanically Deployable Entry Vehicle (DEV). The Pterodactyl project was prompted by the challenge to develop an effective G&C system for a vehicle without a backshell, which is the case for DEVs. For the DEV, the project assumed a specific aeroshell geometry pertaining to an Adaptable, Deployable Entry and Placement Technology (ADEPT) vehicle, which was successfully developed by NASAs Space Technology Mission Directorate (STMD) prior to this study. The Pterodactyl project designed three different entry G&C systems for precision targeting. This paper details the Figures of Merit (FOMs) and metrics used during the course of the projects G&C system assessment. The relative importance of the FOMs was determined from the Analytic Hierarchy Process (AHP), which was used to develop weights that were combined with quantitative design metrics and engineering judgement to rank the G&C systems against one another. This systematic method takes into consideration the projects input while simultaneously reducing unintentional judgement bias and ultimately was used to select a single G&C design for the project to pursue in the next design phase.
    Keywords: Spacecraft Design, Testing and Performance
    Type: ARC-E-DAA-TN75944 , AIAA SciTech Forum; Jan 06, 2020 - Jan 10, 2020; Orlando, Fl; United States
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