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  • Spacecraft Propulsion and Power  (19)
  • 2015-2019  (19)
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  • 2019  (19)
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  • 1
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    Electric Propulsion and the Gateway: Sustainable Exploration of Cis-Lunar Space (2019)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: NASA is committed to a sustainable return of humans to the Moon for long-term exploration and utilization. Gateway will enable this sustained cis-lunar presence and provide the capabilities necessary to develop and deploy critical infrastructure.
    Keywords: Spacecraft Propulsion and Power
    Type: GRC-E-DAA-TN67049
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Flight Servicing of Robotic Refueling Mission 3 (2019)
    In:  CASI
    Details
    Publication Date: 2019-07-26
    Description: The Robotic Refueling Mission 3 (RRM3) payload launched aboard a SpaceX rocket en route to the International Space Station on December 5th, 2018. The Goddard Space Flight Center designed payload carried approximately 50 liters of liquid methane onboard, with a mission to demonstrate long term storage and transfer of the cryogenic fluid in microgravity. Kennedy Space Center (KSC) was tasked to design, fabricate, test, and operate a system equipped to fill an RRM3 dewar with liquid methane prior to launch. Though KSC has a rich history of fueling rockets and payloads, no such operations had previously been accomplished using liquid methane. As such, all of the hardware and processes had to be developed from scratch. The completed ground system design, along with the verification and validation testing will be outlined in this paper. Several challenges that were met and overcome during procurement of the high purity methane are described. In addition, budget restrictions prohibited fueling operations from occurring in traditional processing facilities. The unique and creative solutions which were required to maintain payload cleanliness during cryogenic servicing are also detailed.
    Keywords: Spacecraft Propulsion and Power
    Type: KSC-E-DAA-TN70858 , Space Cryogenics Workshop; Jul 17, 2019 - Jul 19, 2019; Southbury, CT; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Flight Servicing of Robotic Refueling Mission 3 (2019)
    In:  CASI
    Details
    Publication Date: 2019-07-26
    Description: The Robotic Refueling Mission 3 (RRM3) payload launched aboard a SpaceX rocket en route to the International Space Station on December 5th, 2018. The Goddard Space Flight Center designed payload carried approximately 50 liters of liquid methane onboard, with a mission to demonstrate long term storage and transfer of the cryogenic fluid in microgravity. Kennedy Space Center (KSC) was tasked to design, fabricate, test, and operate a system equipped to fill an RRM3 dewar with liquid methane prior to launch. Though KSC has a rich history of fueling rockets and payloads, no such operations had previously been accomplished using liquid methane. As such, all of the hardware and processes had to be developed from scratch. The completed ground system design, along with the verification and validation testing will be outlined in this paper. Several challenges that were met and overcome during procurement of the high purity methane are described. In addition, budget restrictions prohibited fueling operations from occurring in traditional processing facilities. The unique and creative solutions which were required to maintain payload cleanliness during cryogenic servicing are also detailed.
    Keywords: Spacecraft Propulsion and Power
    Type: KSC-E-DAA-TN65286 , Space Cryogenics Workshop; Jul 17, 2019 - Jul 19, 2019; Southbury, CT; United States
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 4
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    Flight Servicing of Robotic Refueling Mission 3 (2019)
    In:  CASI
    Details
    Publication Date: 2019-07-26
    Description: The Robotic Refueling Mission 3 (RRM3) payload launched aboard a SpaceX rocket en route to the International Space Station on December 5th, 2018. The Goddard Space Flight Center designed payload carried approximately 50 liters of liquid methane onboard, with a mission to demonstrate long term storage and transfer of the cryogenic fluid in microgravity. Kennedy Space Center (KSC) was tasked to design, fabricate, test, and operate a system equipped to fill an RRM3 dewar with liquid methane prior to launch. Though KSC has a rich history of fueling rockets and payloads, no such operations had previously been accomplished using liquid methane. As such, all of the hardware and processes had to be developed from scratch. The completed ground system design, along with the verification and validation testing will be outlined in this paper. Several challenges that were met and overcome during procurement of the high purity methane are described. In addition, budget restrictions prohibited fueling operations from occurring in traditional processing facilities. The unique and creative solutions which were required to maintain payload cleanliness during cryogenic servicing are also detailed.
    Keywords: Spacecraft Propulsion and Power
    Type: KSC-E-DAA-TN70282 , Space Cryogenics Workshop; Jul 17, 2019 - Jul 19, 2019; Southbury, CT; United States
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 5
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    Characterization of Propellant Flow and Bias Required to Initiate an Arc Discharge in a Heaterless Hollow Cathode (2019)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: Heaterless hollow cathodes provide an opportunity to reduce complexity and improve reliability in electric propulsion systems. While removal of the heater has little effect on steady-state operation of a hollow cathode, it has a considerable effect on the ignition process. To successfully integrate a heaterless hollow cathode into a spaceflight electric propulsion system, it will be necessary to establish definitive requirements for the propellant feed and electrical subsystems so that ignition of a plasma discharge can be achieved reliably. The aim of this research was to form a better understanding of these requirements by performing an investigation of the propellant flow and voltage conditions required for the ignition of a plasma arc discharge. This aim was achieved by performing discharge initiation experiments using both a specially designed experimental apparatus and a functional heaterless hollow cathode assembly. It was demonstrated that there is a distinct difference in the voltage required to initiate a plasma discharge between two common electric propulsion propellants, xenon and krypton, which suggests that the developmental testing of heaterless hollow cathodes needs to be performed with the appropriate propellant gas species. Heaterless hollow cathode ignition experiments showed that the keeper orifice diameter has a strong effect on the voltage required to ignite a plasma discharge at a given propellant mass flow rate, while the effect of keeper-cathode separation distance was only strong at flow rates below 25 sccm (Xe).
    Keywords: Spacecraft Propulsion and Power
    Type: GRC-E-DAA-TN70748 , AIAA Joint Propulsion Conference 2019; Aug 19, 2019 - Aug 22, 2019; Indianapolis, IN; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Overview of Electric Propulsion Projects at NASA Glenn Research Center (2019)
    In:  CASI
    Details
    Publication Date: 2019-09-25
    Description: NASA Glenn Research Center (GRC) is currently leading the development of multiple electric propulsion systems to flight readiness. The Advanced Electric Propulsion System is a 12.5 kW Hall thruster system that is being developed by the Solar Electric Propulsion Technology Demonstration Mission (SEP TDM) project, under the sponsorship of the Space Technology Mission Directorate. NASA's Evolutionary Xenon Thruster-Commercial (NEXT-C) is 7 kW class gridded ion thruster system that being developed under the sponsorship of the Science Mission Directorate. NASA GRC is also providing electric propulsion discipline support to the Power and Propulsion Element and the Double Asteroid Redirection Test (DART) missions, which will be the first applications for these technologies, respectively. Lower technology readiness level (TRL) projects are underway for applications including CubeSats, small spacecraft and Mars exploration vehicles. Under the sponsorship of the Small Spacecraft Technology Program, NASA GRC has performed numerous independent verification and validation tests of CubeSat class electric propulsion systems in support of a growing number of small US businesses that are developing these systems. Lastly, three technology development efforts focused on 100 kW EP strings led by Aerojet Rocketdyne, Ad Astra and MSNW were recently completed.
    Keywords: Spacecraft Propulsion and Power
    Type: GRC-E-DAA-TN72263 , International Electric Propulsion Conference; Sep 15, 2019 - Sep 20, 2019; Vienna; Austria
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Uncertainty in Electric Propulsion Erosion Measurements (2019)
    In:  CASI
    Details
    Publication Date: 2019-09-10
    Description: Uncertainty in erosion rates as measured by different methods is discussed and quantified. The work focuses on case studies from components on the Hall Effect Rocket with Magnetic Shielding (HERMeS) Hall thruster, but the methods can be extended for many electric propulsion applications. The primary method used for evaluating erosion is non-contact profilometry of masked and exposed components. Accurate quantification of the erosion rates of components is critical to determining lifetime and is therefore critical to mission planning purposes.
    Keywords: Spacecraft Propulsion and Power
    Type: GRC-E-DAA-TN72106 , AIAA Propulsion and Energy Forum 2019; Aug 19, 2019 - Aug 22, 2019; Indianapolis, IN; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Non-Intrusive Characterization of the Wear of the HERMeS Thruster Using Optical Emission Spectroscopy (2019)
    In:  CASI
    Details
    Publication Date: 2019-10-12
    Description: The Hall Effect Rocket with Magnetic Shielding (HERMeS) is a 12.5 kW Hall thruster electric propulsion string that has been in development by NASA Glenn Research Center(GRC) and NASA JPL since 2012. Due to the magnetically shielded design, service life-limiting erosion of the boron nitride discharge has been virtually eliminated. The inner front pole cover (IFPC) has now been identified as the component defining erosion-based service life. Optical emission spectroscopy (OES) is used as an in-situ diagnostic to measure relative erosion trends during operation of the HERMeS thruster during a series of short duration wear tests. Erosion trends obtained from the OES data will be compared to traditional erosion data measured with a non-contact profilometer.
    Keywords: Spacecraft Propulsion and Power
    Type: GRC-E-DAA-TN72554 , International Electric Propulsion Conference; Sep 15, 2019 - Sep 20, 2019; Vienna; Austria
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    ACO: Liquid Oxygen/Methane Lander Propulsion (LOX-CH4 Prop) Task (2019)
    In:  CASI
    Details
    Publication Date: 2019-10-02
    Description: High-level overview of JSC work during Blue Moon ACO.
    Keywords: Spacecraft Propulsion and Power
    Type: JSC-E-DAA-TN72982 , STMD Game Changing Development Program Annual Project Review; Sep 24, 2019 - Sep 27, 2019; Rlington, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Completion of the Long Duration Wear Test of the NASA HERMeS Hall Thruster (2019)
    In:  CASI
    Details
    Publication Date: 2019-10-08
    Description: The NASA Hall Effect Rocket with Magnetic Shielding (HERMeS) 12.5-kW Hall thruster has been the subject of extensive technology maturation by NASA GRC and JPL in preparation for development into a flight propulsion system. As part of this effort, a series of wear tests have been conducted to identify erosion phenomena and the accompanying failure modes as well as to validate service-life models for magnetically-shielded thrusters. This work presents a summary of the results obtained during the Long Duration Wear Test (LDWT), which was the third in this wear test series. The LDWT accumulated approximately 3,570 hours of operation and had the overall goal to identify and correct design or facility issues prior to the flight qualification campaign. Thruster performance, stability, and plume properties were invariant throughout the duration of the LDWT and consistent with measurements acquired during previous HERMeS performance and wear characterizations. Average erosion rates of a carbon-carbon composite pole cover were found to match those measured with graphite to within the empirical uncertainty while the previously observed time-dependence of pole cover erosion rates was linked to changes in pole cover roughness. Azimuthal variations in keeper wear rate were observed including deposition on one of the azimuthal-facing sides of the keeper mask. This strongly suggests the presence of an azimuthal component in the process driving keeper erosion.
    Keywords: Spacecraft Propulsion and Power
    Type: GRC-E-DAA-TN71915 , AIAA Propulsion and Energy Forum and Exposition; Aug 19, 2019 - Aug 22, 2019; Indianapolis, IN; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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