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  • Spacecraft Propulsion and Power  (3)
  • 14C in-situ incubation; 14C uptake; Archive of Ocean Data; ARCOD; Bacteria, abundance; Calculated; Carbon, organic, dissolved; Carbon, organic, particulate; Carbon, organic, total; Chukchi Sea; Counting; Dark assimilation rate, carbon dioxide; DEPTH, water; Elevation of event; Event label; Filtration; Latitude of event; LI-ChS-106; LI-ChS-11; LI-ChS-14; LI-ChS-20; LI-ChS-22; LI-ChS-25; LI-ChS-7; LI-ChS-85; Longitude of event; Mass spectrometry; MULT; Multiple investigations; Primary production of carbon per area, daily; Suspended particulate matter; Water bodies; Wet combustion; δ13C, organic carbon  (1)
  • 2005-2009  (4)
  • 1965-1969
  • 1955-1959
  • 1930-1934
  • 2007  (3)
  • 2006  (1)
Collection
Keywords
Publisher
Years
  • 2005-2009  (4)
  • 1965-1969
  • 1955-1959
  • 1930-1934
Year
  • 2007  (3)
  • 2006  (1)
  • 1
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    (Table 1) Primary productivity, concentration of suspended matter, particulate and dissolved organic carbon concentrations, δ¹³C-Corg in suspended matter, and rate of dark CO2 assimilation in the water column of the Chukchi Sea (2007)
    PANGAEA
    Details
    Publication Date: 2024-04-20
    Keywords: 14C in-situ incubation; 14C uptake; Archive of Ocean Data; ARCOD; Bacteria, abundance; Calculated; Carbon, organic, dissolved; Carbon, organic, particulate; Carbon, organic, total; Chukchi Sea; Counting; Dark assimilation rate, carbon dioxide; DEPTH, water; Elevation of event; Event label; Filtration; Latitude of event; LI-ChS-106; LI-ChS-11; LI-ChS-14; LI-ChS-20; LI-ChS-22; LI-ChS-25; LI-ChS-7; LI-ChS-85; Longitude of event; Mass spectrometry; MULT; Multiple investigations; Primary production of carbon per area, daily; Suspended particulate matter; Water bodies; Wet combustion; δ13C, organic carbon
    Type: Dataset
    Format: text/tab-separated-values, 130 data points
    Location Call Number Expected Availability
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    DATA PANGAEA
  • 2
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    Nuclear Thermal Propulsion Mars Mission Systems Analysis and Requirements Definition (2007)
    In:  CASI
    Details
    Publication Date: 2018-06-12
    Description: This paper describes the Mars transportation vehicle design concepts developed by the Marshall Space Flight Center (MSFC) Advanced Concepts Office. These vehicle design concepts provide an indication of the most demanding and least demanding potential requirements for nuclear thermal propulsion systems for human Mars exploration missions from years 2025 to 2035. Vehicle concept options vary from large "all-up" vehicle configurations that would transport all of the elements for a Mars mission on one vehicle. to "split" mission vehicle configurations that would consist of separate smaller vehicles that would transport cargo elements and human crew elements to Mars separately. Parametric trades and sensitivity studies show NTP stage and engine design options that provide the best balanced set of metrics based on safety, reliability, performance, cost and mission objectives. Trade studies include the sensitivity of vehicle performance to nuclear engine characteristics such as thrust, specific impulse and nuclear reactor type. Tbe associated system requirements are aligned with the NASA Exploration Systems Mission Directorate (ESMD) Reference Mars mission as described in the Explorations Systems Architecture Study (ESAS) report. The focused trade studies include a detailed analysis of nuclear engine radiation shield requirements for human missions and analysis of nuclear thermal engine design options for the ESAS reference mission.
    Keywords: Spacecraft Propulsion and Power
    Type: 2007 Space Nuclear Conference
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Finite Element Simulation of Solid Rocket Booster Separation Motors During Motor Firing (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: One of the toughest challenges facing Solid Rocket Booster (SRB) engineers is to ensure that any design changes made to the Shuttle-Derived Booster Separation Motors (BSM) for future space exploration vehicles is able to withstand the increasingly hostile motor firing environment without cracking its critical component - the graphite throat. This paper presents a critical analysis methodology and techniques for assessing effects of BSM design changes with great accuracy and precision. For current Space Shuttle operation, the motor firing occurs at SRB separation - approximately 125 seconds after Shuttle launch at an altitude of about 28 miles. The motor operation event lasts about two seconds, however, the surface temperature of the graphite throat increases approximately 3400 F in less than one second with a corresponding increase in surface pressure of approximately 2200 pounds per square inch (psi) in less than one-tenth of a second. To capture this process fully and accurately, a two-phase sequentially coupled thermal-mechanical finite element approach was developed. This method allows the time- and location-dependent pressure fields to interact with the spatial-temporal thermal fields throughout the operation. The material properties of graphite throat are orthotropic and temperature-dependent. The analysis involves preload and multiple body contacts.
    Keywords: Spacecraft Propulsion and Power
    Type: KSC-2007-142 , American Institute of Aeronautics and Astronautics (AIAA) Conference; Sep 18, 2007 - Sep 20, 2007; Long Beach, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Comparison of Performance Predictions for New Low-Thrust Trajectory Tools (2006)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Several low thrust trajectory optimization tools have been developed over the last 3% years by the Low Thrust Trajectory Tools development team. This toolset includes both low-medium fidelity and high fidelity tools which allow the analyst to quickly research a wide mission trade space and perform advanced mission design. These tools were tested using a set of reference trajectories that exercised each tool s unique capabilities. This paper compares the performance predictions of the various tools against several of the reference trajectories. The intent is to verify agreement between the high fidelity tools and to quantify the performance prediction differences between tools of different fidelity levels.
    Keywords: Spacecraft Propulsion and Power
    Type: AIAA Paper 2006-6742 , AIAA/AAS Astrodynamics Specialist Conference; Aug 21, 2006 - Aug 24, 2006; Keystone, CO; United States
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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