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  • 1
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    Neon dewar for the X-ray spectrometer onboard Suzaku (2006)
    Elsevier
    Details
    Publication Date: 2006-04-01
    Print ISSN: 0168-9002
    Electronic ISSN: 1872-9576
    Topics: Physics
    Published by Elsevier
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    PAPER CURRENT
  • 2
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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
  • 3
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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
  • 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-TN70858 , Space Cryogenics Workshop; Jul 17, 2019 - Jul 19, 2019; Southbury, 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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    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
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    NASA TECHNICAL REPORTS
  • 7
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    Liquid helium servicing from the Space Station (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: The current concept of liquid helium resupply from the Space Station is discussed with regard to user and Space Station requirements, as well as requirements of the liquid helium servicing facility itself. A number of trade-offs which will affect both the hardware and the operation of the facility are presented. A total of 12 potential users have been identified. The users are divided into two groups: large volume users which are serviced every one to two years and small volume users which are serviced every few months. Both groups have a very strong impact on the definition of the liquid helium servicing facility. The facility components will be based on results of the Superfluid Helium On Orbit Transfer flight demonstration being conducted by NASA. Currently, the Space Station design includes a customer servicing bay which provides electrical power, thermal and contamination control, and connections for control and data handling systems. Restrictions on venting and vibrational disturbances on the Space Station may preclude servicing during quiescent periods when accelerations are minimal.
    Keywords: ASTRONAUTICS (GENERAL)
    Type: Cryogenics (ISSN 0011-2275); 28; 68-76
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Mechanical cooler-to-Dewar interfacing in a long-lifetime, hybrid stored cryogen system (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: The means for making efficient use of mechanical coolers to limit the parasitic heating into the Dewar are addressed. Thermal efficiency is achieved by minimizing the parasitic heating and thermal impedance of the cooler-to-Dewar interface within the mechanical constraints. The important issues related to compatibility with the instrument system are also briefly discussed. Parasitic heating from the nonoperating (reserved or failed) cooler pair can be reduced with an active thermal switch that isolates the cooler cold tips from the cold finger. An analysis was performed to determine the optimal switch-operating characteristics for this application. Requirements associated with the use of the coolers, analyses performed, and the interface design concept are discussed.
    Keywords: ENGINEERING (GENERAL)
    Type: Cryogenics (ISSN 0011-2275); 32; 2 19
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Operation of A Sunpower M87 Cryocooler In A Magnetic Field (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Alpha Magnetic Spectrometer-02 (AMS-02) is an experiment that will be flown as an attached payload on the International Space Station to detect dark matter and antimatter. It uses large superconducting magnets cooled with superfluid helium to bend the path of cosmic particles through a series of detectors, which then measure the mass, speed, charge, and direction of the particles. Four Sunpower M87N Stirling-cycle cryocoolers are used to extend the mission life by cooling the outer vapor-cooled shield of the dewar. The main magnet coils are separated by a distance of approximately 1 m and the coolers are located approximately 1.5 m from the center line of the magnet, where the field is as high as 925 gauss perpendicular to the cryocooler axis and 400 gauss along the cryocooler axis. Interactions between the applied magnetic field and the linear motor may result in additional forces and torques on the compressor piston. Motion of the compressor arid displacer pistons through the magnetic field spatial gradients will generate eddy currents. Additional eddy currents are created during magnet charge, discharge, and quench by the time-varying magnetic field. The results of tests to determine the magnitude of the forces, torques, and heating effects, as well as the need for additional magnetic shielding, are presented.
    Keywords: Engineering (General)
    Type: 12th International Cryocooler Conference; Jun 17, 2002 - Jun 20, 2002; Cambridge, MA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Space Flight Qualification Program for the AMS-2 Commercial Cryocoolers (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Alpha Magnetic Spectrometer-02 (AMS-02) experiment is a state-of-the-art particle physics detector containing a large superfluid helium-cooled superconducting magnet. Highly sensitive detector plates inside the magnet measure a particle's speed, momentum, charge, and path. The AMS-02 experiment will study the properties and origin of cosmic particles and nuclei including antimatter and dark matter. AMS-02 will be installed on the International Space Station on Utilization Flight-4. The experiment will be run for at least three years. To extend the life of the stored cryogen and minimize temperature gradients around the magnet, four Stirling-cycle Sunpower M87N cryocoolers will be integrated with AMS-02. The cryocooler cold tip will be connected via a flexible strap to the outer vapor cooled shield of the dewar. Initial thermal analysis shows the lifetime of the experiment is increased by a factor of 2.8 with the use of the cryocooler. The AMS-02 project selected the Sunpower M87 cryocoolers and has asked NASA Goddard to qualify the cryocoolers for space flight use. This paper describes the interfaces with the cryocoolers and presents data collected during testing of the two engineering model cryocoolers. Tests include thermal performance characterization and launch vibration testing. Magnetic field compatibility testing will be presented in a separate paper at the conference.
    Keywords: Engineering (General)
    Type: 12th International Cryocooler Conference (ICC-12); Jun 18, 2002 - Jun 20, 2002; Cambridge, MA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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