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  • 1
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    Robotic Refueling Mission-3—an overview (2020)
    Institute of Physics
    Details
    Publication Date: 2020-06-30
    Print ISSN: 1757-8981
    Electronic ISSN: 1757-899X
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Institute of Physics
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    PAPER CURRENT
  • 2
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    Return to Service of a Liquid Hydrogen Storage Sphere (2019)
    In:  CASI
    Details
    Publication Date: 2019-08-03
    Description: One, of two, 850,000 gallon liquid hydrogen storage spheres, at NASA's Kennedy Space Center, was decommissioned in 2010. This tank had an abnormally high heat leak that was investigated and determined to be the result of a large void in the perlite insulation. The insulation void was subsequently filled, and the tank was refurbished for its planned use in the Space Launch Systems (SLS) program. Return to service of this tank began in December of 2017 with a partial liquid hydrogen fill. Since that time, routine measurement of the liquid level have been recorded in order to establish a new boiloff rate and associated heat leak. This data shows the perlite top off activities have resulted in a much reduced, and within design specification, heat leak.
    Keywords: Ground Support Systems and Facilities (Space); Propellants and Fuels
    Type: KSC-E-DAA-TN69387 , Cryogenic Engineering Conference and International Cryogenic Materials Conference (CEC/ICMC); Jul 21, 2019 - Jul 25, 2019; Hartford, CT; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Return to Service of a Liquid Hydrogen Storage Sphere (2019)
    In:  CASI
    Details
    Publication Date: 2019-08-02
    Description: One, of two, 850,000 gallon liquid hydrogen storage spheres, at NASA's Kennedy Space Center, was decommissioned in 2010. This tank had an abnormally high heat leak that was investigated and determined to be the result of a large void in the perlite insulation. The insulation void was subsequently filled, and the tank was refurbished for its planned use in the Space Launch Systems (SLS) program. Return to service of this tank began in December of 2017 with a partial liquid hydrogen fill. Since that time, routine measurement of the liquid level have been recorded in order to establish a new boiloff rate and associated heat leak. This data shows the perlite top off activities have resulted in a much reduced, and within design specification, heat leak.
    Keywords: Propellants and Fuels; Ground Support Systems and Facilities (Space)
    Type: KSC-E-DAA-TN65442 , Cryogenic Engineering Conference and International Cryogenic Materials Conference (CEC/ICMC); Jul 21, 2019 - Jul 25, 2019; Hartford, CT; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Robotic Refueling Mission-3 An Overview (2019)
    In:  CASI
    Details
    Publication Date: 2019-07-26
    Description: Robotic Refueling Mission-3 (RRM3) is an external payload on the International Space Station (ISS) to demonstrate the techniques for storing and transferring a cryogenic fuel on orbit. RRM3 was designed and built at the National Aeronautics and Space Administration/Goddard Space Flight Center (NASA/GSFC). Initial testing was performed at GSFC using liquid nitrogen and liquid argon. Final testing and flight fill of methane was performed at the NASA Kennedy Space Center (KSC) to take advantage of KSC's facilities and expertise for handling a combustible cryogen.
    Keywords: Propellants and Fuels
    Type: GSFC-E-DAA-TN70912 , Cryogenic Engineering Conference and International Cryogenic Materials Conference 2019; Jul 21, 2019 - Jul 25, 2019; Hartford, CT; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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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
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    NASA TECHNICAL REPORTS
  • 6
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    Annular Air Leaks in a Liquid Hydrogen Storage Tank (2016)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Large liquid hydrogen (LH2) storage tanks are vital infrastructure for NASA, the DOD, and industrial users. Over time, air may leak into the evacuated, perlite filled annular region of these tanks. Once inside, the extremely low temperatures will cause most of the air to freeze. If a significant mass of air is allowed to accumulate, severe damage can result from nominal draining operations. Collection of liquid air on the outer shell may chill it below its ductility range, resulting in fracture. Testing and analysis to quantify the thermal conductivity of perlite that has nitrogen frozen into its interstitial spaces and to determine the void fraction of frozen nitrogen within a perlite-frozen nitrogen mixture is presented. General equations to evaluate methods for removing frozen air, while avoiding fracture, are developed. A hypothetical leak is imposed on an existing tank and a full analysis of that leak is detailed. This analysis includes a thermal model of the tank and a time-to-failure calculation. Approaches to safely remove the frozen air are analyzed, leading to the conclusion that the optimal approach is to allow the frozen air to melt and use a water stream to prevent the outer shell from chilling.
    Keywords: Physics (General); Propellants and Fuels
    Type: KSC-E-DAA-TN36861 , Programmatic Industrial Base (PIB) Subcommittee; Dec 05, 2016 - Dec 08, 2016; Phoenix, AZ; United States|Spacecraft Propulsion Subcommittee (SPS); Dec 05, 2016 - Dec 08, 2016; Phoenix, AZ; United States|Modeling and Simulation Subcommittee (MSS); Dec 05, 2016 - Dec 08, 2016; Phoenix, AZ; United States|Liquid Propulsion Subcommittee (LPS); Dec 05, 2016 - Dec 08, 2016; Phoenix, AZ; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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