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  • Other Sources  (3)
  • Spacecraft Instrumentation and Astrionics  (2)
  • Structural Mechanics
  • 2000-2004  (3)
  • 2003  (3)
  • 1
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    In-Flight Thermal Performance of the Geoscience Laser Altimeter System (GLAS) Instrument (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Geoscience Laser Altimeter System (GLAS) instrument is NASA Goddard Space Flight Center's first application of Loop Heat Pipe technology that provides selectable/stable temperature levels for the lasers and other electronics over a widely varying mission environment. GLAS was successfully launched as the sole science instrument aboard the Ice, Clouds, and Land Elevation Satellite (ICESat) from Vandenberg AFB at 4:45pm PST on January 12, 2003. After SC commissioning, the LHPs started easily and have provided selectable and stable temperatures for the lasers and other electronics. This paper discusses the thermal development background and testing, along with details of early flight thermal performance data.
    Keywords: Spacecraft Instrumentation and Astrionics
    Type: Rept-2003-01-2421 , Rept-03ICES-274 , 33rd International Conference on Environmental Systems; Jan 01, 2003; Vancouver, British Columbia; Canada
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Geoscience Laser Altimetry System (GLAS) On-Orbit Flight Report on the Propylene Loop Heat Pipes (LHPs) (2003)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Geoscience Laser Altimetry System (GLAS) instrument which is the sole instrument on ICESat was launched on January 12, 2003. GLAS utilizes two actively controlled propylene Loop Heat Pipes (LHPs) as the core of its thermal system. The LHPs started quickly when the Dale Ohm starter heaters were powered and have as designed. The low control heater power and on-orbit tight temperature control appear independent of gravity effects when comparing ground testing to flight data. The use of coupling blocks was also unique to these LHPs. Their application reduced control heater power by reducing the subcooling from the radiator. The effectiveness in reducing subcooling of the coupler blocks decreased during flight from ground testing, but internal thermal isolation in the compensation chamber between the subcooled returning liquid increased in flight resulting in no net increase in control heater power versus ground measurements. Overall the application of LHPs in the thermal system for GLAS met instrument requirements and provided flexibility for the overall system as last minute requirements became known.
    Keywords: Spacecraft Instrumentation and Astrionics
    Type: International Two-Phase Workshop; Sep 15, 2003 - Sep 17, 2003; Noordwijk; Netherlands
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Preliminary Thermal Stress Analysis of a High-Pressure Cryogenic Storage Tank (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: The thermal stresses on a cryogenic storage tank strongly affect the condition of the tank and its ability to withstand operational stresses. These thermal stresses also affect the growth of any surface damage that might occur in the tank walls. These stresses are particularly of concern during the initial cooldown period for a new tank placed into service, and during any subsequent thermal cycles. A preliminary thermal stress analysis of a high-pressure cryogenic storage tank was performed. Stresses during normal operation were determined, as well as the transient temperature distribution. An elastic analysis was used to determine the thermal stresses in the inner wall based on the temperature data. The results of this elastic analysis indicate that the inner wall of the storage tank will experience thermal stresses of approximately 145,000 psi (1000 MPa). This stress level is well above the room-temperature yield strength of 304L stainless steel, which is about 25,000 psi (170 MPa). For this preliminary analysis, several important factors have not yet been considered. These factors include increased strength of 304L stainless steel at cryogenic temperatures, plastic material behavior, and increased strength due to strain hardening. In order to more accurately determine the thermal stresses and their affect on the tank material, further investigation is required, particularly in the area of material properties and their relationship to stress.
    Keywords: Structural Mechanics
    Type: SE-2003-06-0043-SSC
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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