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  • 1
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    Simulated real-time lunar volatiles prospecting with a rover-borne neutron spectrometer (2015)
    Elsevier
    Details
    Publication Date: 2015-05-01
    Print ISSN: 0273-1177
    Electronic ISSN: 1879-1948
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
    Published by Elsevier
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    PAPER CURRENT
  • 2
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    Assessment of robotic recon for human exploration of the Moon (2010)
    Elsevier
    Details
    Publication Date: 2010-11-01
    Print ISSN: 0094-5765
    Electronic ISSN: 1879-2030
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Elsevier
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    PAPER CURRENT
  • 3
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    The Green Propellant Infusion Mission Thruster Performance Testing for Plume Diagnostics (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Green Propellant Infusion Mission (GPIM) is sponsored by NASA's Space Technology Mission Directorate (STMD) Technology Demonstration Mission (TDM) office. The goal of GPIM is to advance the technology readiness level of a green propulsion system, specifically, one using the monopropellant, AF-M315E, by demonstrating ground handling, spacecraft processing, and on-orbit operations. One of the risks identified for GPIM is potential contamination of sensitive spacecraft surfaces from the effluents in the plumes of AF-M315E thrusters. NASA Glenn Research Center (GRC) is conducting activities to characterize the effects of AF-M315E plume impingement and deposition. GRC has established individual plume models of the 22-N and 1-N thrusters that will be used on the GPIM spacecraft. The model simulations will be correlated with plume measurement data from Laboratory and Engineering Model 22-N, AF-M315E thrusters. The thrusters are currently being tested in a small rocket, altitude facility at NASA GRC. A suite of diagnostics, including Raman spectroscopy, Rayleigh spectroscopy, and Schlieren imaging are being used to acquire plume measurements of AF-M315E thrusters. Plume data will include temperature, velocity, relative density, and species concentration. The plume measurement data will be compared to the corresponding simulations of the plume model. The GRC effort will establish a data set of AF-M315E plume measurements and a plume model that can be used for future AF-M315E applications.
    Keywords: Propellants and Fuels; Spacecraft Propulsion and Power
    Type: GRC-E-DAA-TN16234 , AIAA/ASME/SAE/ASEE Joint Propulsion Conference; Jul 28, 2014 - Jul 30, 2014; Cleveland, Ohio; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Recommended Figures of Merit for Green Monopropellants (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Hydrazine propellant has historically been used as a rocket thruster monopropellant since the mid-1960s. Mission managers are well aware of its characteristics and performance. However, it is a known toxic chemical and a wide effort is underway to reduce and/or eliminate its use worldwide. Several new propellant combinations have been developed in the last few years which tout or promise to provide same or better performance as hydrazine while being "non-toxic" or "green". Yet, there is no consistent definition for what constitutes "non-toxic" or "green", and thus no good figure of merit for which to compare. This paper seeks to review the three major categories of figures of merit, and discusses how they might be used to assess the viability of a propellant.
    Keywords: Astronautics (General); Propellants and Fuels
    Type: NASA/TM-2013-216560 , AIAA Paper 2013-3722 , E-18733 , GRC-E-DAA-TN9862 , AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit; Jul 14, 2013 - Jul 17, 2013; San Jose, CA; United States
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    NASA TECHNICAL REPORTS
  • 5
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    Recommended Figures of Merit for Green Monopropellants (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Hydrazine propellant has historically been used as a rocket thruster monopropellant since the mid-1960s. Mission managers are well aware of its characteristics and performance. However, it is a known toxic chemical and a wide effort is underway to reduce and/or eliminate its use worldwide. Several new propellant combinations have been developed in the last few years which tout or promise to provide same or better performance as hydrazine while being "non-toxic" or "green". Yet, there is no consistent definition for what constitutes "non-toxic" or "green", and thus no good figure of merit for which to compare. This paper seeks to review the three major categories of figures of merit, and discusses how they might be used to assess the viability of a propellant.
    Keywords: Propellants and Fuels
    Type: NASA/TM-2013-216560 , E-18733 , GRC-E-DAA-TN9862 , International Energy Conversion Engineering Conference; Jul 15, 2013 - Jul 17, 2013; San Jose, CA; United States|AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit; Jul 15, 2013 - Jul 17, 2013; San Jose, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Plume Characterization of a Laboratory Model 22 N GPIM Thruster via High-Frequency Raman Spectroscopy (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Green Propellant Infusion Mission (GPIM) will demonstrate the capability of a green propulsion system, specifically, one using the monopropellant, AF-M315E. One of the risks identified for GPIM is potential contamination of sensitive areas of the spacecraft from the effluents in the plumes of AF-M315E thrusters. Plume characterization of a laboratory-model 22 N thruster via optical diagnostics was conducted at NASA GRC in a space-simulated environment. A high-frequency pulsed laser was coupled with an electron-multiplied ICCD camera to perform Raman spectroscopy in the near-field, low-pressure plume. The Raman data yielded plume constituents and temperatures over a range of thruster chamber pressures and as a function of thruster (catalyst) operating time. Schlieren images of the near-field plume enabled calculation of plume velocities and revealed general plume structure of the otherwise invisible plume. The measured velocities are compared to those predicted by a two-dimensional, kinetic model. Trends in data and numerical results are presented from catalyst mid-life to end-of-life. The results of this investigation were coupled with the Raman and Schlieren data to provide an anchor for plume impingement analysis presented in a companion paper. The results of both analyses will be used to improve understanding of the nature of AF-M315E plumes and their impacts to GPIM and other future missions.
    Keywords: Spacecraft Propulsion and Power; Lasers and Masers
    Type: GRC-E-DAA-TN24679 , Propulsion and Energy Forum 2015; Jul 27, 2015 - Jul 29, 2015; Orlando, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Development and Testing of a Methane/Oxygen Catalytic Microtube Ignition System for Rocket Propulsion (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This study sought to develop a catalytic ignition advanced torch system with a unique catalyst microtube design that could serve as a low energy alternative or redundant system for the ignition of methane and oxygen rockets. Development and testing of iterations of hardware was carried out to create a system that could operate at altitude and produce a torch. A unique design was created that initiated ignition via the catalyst and then propagated into external staged ignition. This system was able to meet the goals of operating across a range of atmospheric and altitude conditions with power inputs on the order of 20 to 30 watts with chamber pressures and mass flow rates typical of comparable ignition systems for a 100 Ibf engine.
    Keywords: Spacecraft Propulsion and Power
    Type: E-18451 , AIAA Joint Propulsion Conference; Jul 30, 2012 - Aug 01, 2012; Atlanta, GA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Tele-Operated Lunar Rover Navigation Using Lidar (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Near real-time tele-operated driving on the lunar surface remains constrained by bandwidth and signal latency despite the Moon s relative proximity. As part of our work within NASA s Human-Robotic Systems Project (HRS), we have developed a stand-alone modular LIDAR based safeguarded tele-operation system of hardware, middleware, navigation software and user interface. The system has been installed and tested on two distinct NASA rovers-JSC s Centaur2 lunar rover prototype and ARC s KRex research rover- and tested over several kilometers of tele-operated driving at average sustained speeds of 0.15 - 0.25 m/s around rocks, slopes and simulated lunar craters using a deliberately constrained telemetry link. The navigation system builds onboard terrain and hazard maps, returning highest priority sections to the off-board operator as permitted by bandwidth availability. It also analyzes hazard maps onboard and can stop the vehicle prior to contacting hazards. It is robust to severe pose errors and uses a novel scan alignment algorithm to compensate for attitude and elevation errors.
    Keywords: Communications and Radar
    Type: ARC-E-DAA-TN5509 , International Symposium on Artificial Intelligence, Robotics and Automation in Space (I-SAIRAS); Sep 04, 2012 - Sep 06, 2012; Turin; Italy
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Prospecting for Polar Volatiles: Results from the Resolve Field (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Both the Moon and Mercury evidently host ice and other volatile compounds in cold traps at the planets poles. Determining the form, spatial distribution, and abundance of these volatiles at the lunar poles can help us understand how and when they were delivered and emplaced. This bears directly on the delivery of water and prebiotic compounds to the inner planets over the solar system s history, and also informs plans for utilizing the volatiles as resources for sustained human exploration as well as the commercial development of space. Temperature models and orbital data suggest near-surface volatile concentrations may exist at polar locations not strictly in permanent shadow. Remote operation of a robotic lunar rover mission for the 7-10 days of available sunlight would permit key questions to be answered. But such a short, quick-tempo mission has unique challenges and requires a new concept of operations. Both science and rover operations decisionmaking must be done in real time, requiring immediate situational awareness, data analysis, and decision support tools.
    Keywords: Space Sciences (General)
    Type: ARC-E-DAA-TN7567 , Lunar and Planetary Science Conference (LPSC) 2013; Mar 18, 2013 - Mar 22, 2013; The Woodlands, TX; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    First Results from the Mojave Volatiles Prospector (MVP) Field Campaign, a Lunar Polar Rover Mission Analog (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-26
    Description: The Mojave Volatiles Prospector (MVP) project is a science-driven field program with the goal to produce critical knowledge for conducting robotic exploration of the Moon. MVP will feed science, payload, and operational lessons learned to the development of a real-time, short-duration lunar polar volatiles prospecting mission. MVP achieves these goals through a simulated lunar rover mission to investigate the composition and distribution of surface and subsurface volatiles in a natural and a priori unknown environment within the Mojave Desert, improving our understanding of how to find, characterize, and access volatiles on the Moon. The MVP field site is the Mojave Desert, selected for its low, naturally occurring water abundance. The Mojave typically has on the order of 2-6% water, making it a suitable lunar analog for this field test. MVP uses the Near Infrared and Visible Spectrometer Subsystem (NIRVSS), Neutron Spectrometer Subsystem (NSS), and a downward facing GroundCam camera on the KREX-2 rover to investigate the relationship between the distribution of volatiles and soil crust variation. Through this investigation, we mature robotic in situ instruments and concepts of instrument operations, improve ground software tools for real time science, and carry out publishable research on the water cycle and its connection to geomorphology and mineralogy in desert environments. A lunar polar rover mission is unlike prior space missions and requires a new concept of operations. The rover must navigate 3-5 km of terrain and examine multiple sites in in just ~6 days. Operational decisions must be made in real time, requiring constant situational awareness, data analysis and rapid turnaround decision support tools. This presentation will focus on the first science results and operational architecture findings from the MVP field deployment relevant to a lunar polar rover mission.
    Keywords: Astronomy
    Type: ARC-E-DAA-TN18863 , American Geophysical Union Fall 2014 Meeting; Dec 15, 2014 - Dec 19, 2014; San Francisco, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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