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  • Other Sources  (3,296)
  • Fluid Mechanics and Thermodynamics  (1,665)
  • Spacecraft Propulsion and Power  (1,603)
  • AERODYNAMICS
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  • 2015-2019  (1,035)
  • 2000-2004  (2,212)
  • 1940-1944  (49)
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  • Other Sources  (3,296)
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  • 1
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    Investigation of a Liquefaction Methodology to Enable the Utilization of In-Situ Produced Propellant on the Lunar and Martian Surfaces (2019)
    In:  CASI
    Details
    Publication Date: 2020-01-23
    Description: To enable NASAs plans to return astronauts to the lunar surface and eventually to Mars, the agency is putting emphasis on reusable cryogenic systems. Such systems will require replenishing of cryogens on-orbit via a cryogenic tanker or refueling depot, and potentially on the lunar or Martian surfaces with the utilization of in-situ resources. Surface replenishing requires the in-situ production of gaseous oxygen (and hydrogen if on the lunar surface), followed by liquefaction and storage. The liquefaction system can be integrated into the propulsion system propellant tanks, or in a separate storage facility and transferred to the propulsion system when needed. In interest of developing a liquefaction and storage system that is efficient, reliable and scalable, a multicenter team of NASA engineers was formed. The team conducted trade studies on various system level concepts including multiple heat exchanger configurations to be integrated with active cooling (cryocoolers). When the trade studies concluded, the team settled on a system level configuration which included a propellant tank outfitted with a tube-on-tank heat exchanger integrated with a cryocooler. The team executed a development plan to include: 1) a brassboard level test series to demonstrate proof of concept, 2) model development to predict system performance, 3) model validation utilizing brassboard test results, 4) the design, development and demonstration of a Mars surface liquefaction and storage system prototype, and 5) eventually conduct an end-to-end demonstration to include in-situ production, liquefaction, and long duration storage of cryogens with zero boil-off. The effort is currently in the brassboard level testing phase which will be discussed here.
    Keywords: Spacecraft Propulsion and Power
    Type: M19-7405 , Cold Facts
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Comparison of Energy Conversion Technologies for Space Nuclear Power Systems (2019)
    In:  CASI
    Details
    Publication Date: 2020-01-18
    Description: A key element of space nuclear power systems is the energy conversion subsystem that converts the nuclear heat into electrical power. Nuclear systems provide a favorable option for missions that require long-duration power in hostile space environments where sunlight for solar power is absent or limited. There are two primary nuclear power technology options: (1) radioisotope power systems (RPSs) utilize the natural decay heat from 238Pu to generate electric power levels up to about 1 kW and (2) fission power systems (FPSs) rely on a sustained fission reaction of 235U and offer the potential to supply electric power from kilowatts to megawatts. Example missions utilizing nuclear power include Mars science rovers (e.g., Curiosity, Mars 2020), lunar and Mars surface landers, crewed surface outposts, deep space planetary orbiters, Ocean World science landers, and robotic space probes that utilize nuclear electric propulsion. This report examines the energy conversion technology options that can be used with RPSs and FPSs, and provides an assessment of their relative performance.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA/TM—2019-219935 , AIAA–2018–4977 , GRC-E-DAA-TN58370 , 2018 AIAA Propulsion and Energy Forum; Jul 09, 2018 - Jul 11, 2018; Cincinnati, OH; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Determination of Aerothermal Environment and Ablator Material Response Using Inverse Methods (2019)
    In:  CASI
    Details
    Publication Date: 2020-01-18
    Description: The Mars Science Laboratory (MSL) was protected during entry into the Martian atmosphere by a thermal protection system that used NASAs Phenolic Impregnated Carbon Ablator (PICA). The heat shield of the probe was instrumented with the Mars Entry Descent and Landing Instrument (MEDLI) suite of sensors. MEDLI Integrated Sensor Plugs (MISP) included thermocouples that measured in-depth temperatures at various locations on the heatshield. The flight data has been used as a benchmark for validating ablation codes within NASA. This work seeks to refine the estimate of the material properties for the MSL heat shield and the aerothermal environment during Mars entry using estimation methods in DAKOTA on the temperature data obtained from MEDLI.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: ARC-E-DAA-TN73346 , Ablation Workshop; Sep 16, 2019 - Sep 17, 2019; Minneapolis, MN; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    A Comparison of Energy Conversion Technologies for Space Nuclear Power Systems (2018)
    In:  CASI
    Details
    Publication Date: 2020-01-18
    Description: A key element of space nuclear power systems is the energy conversion subsystem that converts the nuclear heat into electrical power. Nuclear systems provide a favorable option for missions that require long-duration power in hostile space environments where sunlight for solar power is absent or limited. There are two primary nuclear power technology options. Radioisotope Power System (RPS) utilize the natural decay heat from Pu238 to generate electric power levels up to about one kilowatt. Fission Power System (FPS) rely on a sustained fission reaction of U235 and offer the potential to supply electric power from kilowatts to megawatts. Example missions for nuclear power include Mars science rovers (e.g. Curiosity, Mars 2020), lunar and Mars surface landers ? including crewed missions, deep space planetary orbiters, Ocean World science landers, and robotic space probes that utilize nuclear electric propulsion. This paper examines the energy conversion technology options that can be used with RPS and FPS, and provides an assessment of their relative performance and technology readiness.
    Keywords: Spacecraft Propulsion and Power
    Type: AIAA–2018–4977 , GRC-E-DAA-TN57836 , 2018 AIAA Propulsion and Energy Forum; Jul 09, 2018 - Jul 11, 2018; Cincinnati, OH; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Heat Exchanger Performance Impacts on Optimum Cost Conditions in Thermoelectric Energy Recovery Designs (2016)
    In:  Other Sources
    Details
    Publication Date: 2020-01-14
    Description: No abstract available
    Keywords: Fluid Mechanics and Thermodynamics
    Type: JPL-CL-16-3997 , (e-ISSN 2214-7853)|European Conference on Thermoelectrics; Sep 20, 2016 - Sep 23, 2016; Lisbon; Portugal
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Power Subsystem Approach for The Europa Mission (2016)
    In:  Other Sources
    Details
    Publication Date: 2020-01-13
    Description: NASA is planning to launch a spacecraft on a mission to the Jovian moon Europa, in order to conduct a detailed reconnaissance and investigation of its habitability. The spacecraft would orbit Jupiter and perform a detailed science investigation of Europa, utilizing a number of science instruments including an ice-penetrating radar to determine the icy shell thickness and presence of subsurface oceans. The spacecraft would be exposed to harsh radiation and extreme temperature environments. To meet mission objectives, the spacecraft power subsystem is being architected and designed to operate efficiently, and with a high degree of reliability.
    Keywords: Spacecraft Propulsion and Power
    Type: JPL-CL-16-4385 , European Space and Power Conference; Oct 03, 2016 - Oct 07, 2016; Thessaloniki; Greece
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    E-Glider: Active Electrostatic Flight Concept for Airless Body Exploration (2016)
    In:  Other Sources
    Details
    Publication Date: 2020-01-13
    Description: No abstract available
    Keywords: Spacecraft Propulsion and Power
    Type: JPL-CL-16-3747 , NIAC Summer Symposium; Aug 23, 2016 - Aug 25, 2016; Raleigh, NC; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Power Subsystem Approach for the Europa Mission (2016)
    In:  Other Sources
    Details
    Publication Date: 2020-01-13
    Description: NASA is planning to launch a spacecraft on a mission to the Jovian moon Europa, in order to conduct a detailed reconnaissance and investigation of its habitability. The spacecraft would orbit Jupiter and perform a detailed science investigation of Europa, utilizing a number of science instruments including an ice-penetrating radar to determine the icy shell thickness and presence of subsurface oceans. The spacecraft would be exposed to harsh radiation and extreme temperature environments. To meet mission objectives, the spacecraft power subsystem is being architected and designed to operate efficiently, and with a high degree of reliability.
    Keywords: Spacecraft Propulsion and Power
    Type: JPL-CL-16-3998 , European Space and Power Conference; Oct 03, 2016 - Oct 07, 2016; Thessaloniki; Greece
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Thermal Cycling for Development of Hybrid Fuel for a Notional Mars Ascent Vehicle (2016)
    In:  Other Sources
    Details
    Publication Date: 2020-01-08
    Description: No abstract available
    Keywords: Spacecraft Propulsion and Power
    Type: JPL-CL-16-3160 , AIAA Joint Propulsion Conference; Jul 25, 2016 - Jul 27, 2016; Salt Lake City, UT; United States
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    NASA TECHNICAL REPORTS
  • 10
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    Hybrid Propulsion In-Situ Resource Utilization Test Facility Results for Performance Characterization (2016)
    In:  Other Sources
    Details
    Publication Date: 2020-01-07
    Description: No abstract available
    Keywords: Spacecraft Propulsion and Power
    Type: JPL-CL-16-3195 , AIAA Joint Propulsion Conference; Jul 25, 2016 - Jul 27, 2016; Salt Lake City, UT; United States
    Format: text
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    NASA TECHNICAL REPORTS
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