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  • Structural Mechanics  (5)
  • Spacecraft Instrumentation and Astrionics  (4)
  • 2000-2004  (9)
  • 1
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    Geoscience Laser Altimeter System (GLAS) Loop Heat Pipes: An Eventual First Year On-Orbit (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Goddard Space Flight Center's Geoscience Laser Altimeter System (GLAS) is the sole scientific instrument on the Ice, Cloud and land Elevation Satellite (ICESat) that was launched on January 12, 2003 from Vandenberg AFB. A thermal control architecture based on propylene Loop Heat Pipe technology was developed to provide selectable/stable temperature control for the lasers and other electronics over the widely varying mission environment. Following a nominal LHP and instrument start-up, the mission was interrupted with the failure of the first laser after only 36 days of operation. During the 5-month failure investigation, the two GLAS LHPs and the electronics operated nominally, using heaters as a substitute for the laser heat load. Just prior to resuming the mission, following a seasonal spacecraft yaw maneuver, one of the LHPs deprimed and created a thermal runaway condition that resulted in an emergency shutdown of the GLAS instrument. This paper presents details of the LHP anomaly, the resulting investigation and recovery, along with on-orbit flight data during these critical events.
    Keywords: Spacecraft Instrumentation and Astrionics
    Type: Rept-2004-01-2558 , 34th International Conferrence on Environmental Systems; Jul 18, 2004 - Jul 22, 2004; Colorado Springs, CO; United States
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  • 2
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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
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  • 3
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    AMSD Reaction Structure Cryo Deformation Test Plan (2002)
    In:  Other Sources
    Details
    Publication Date: 2019-07-18
    Description: The method developed for measuring both in-plane & out-of-plane cryo deformations of AMSD reaction structures at the XRCF will be presented. For in-plane measurements, a theodolite is used to track the positions of several (up to ten) targets on the reaction structure. For out-of-plane measurements, the Leica ADM is used to measure the change in distance to several (up to ten) corner cubes attached to the reaction structure.
    Keywords: Structural Mechanics
    Type: 2nd Annual Technology Days; May 22, 2002 - May 24, 2002; Huntsville, AL; United States
    Format: text
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  • 4
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    Experimental Results From Stitched Composite Multi-Bay Fuselage Panels Tested Under Uni-Axial Compression (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: The experimental results from two stitched VARTM composite panels tested under uni-axial compression loading are presented. The curved panels are divided by frames and stringers into five or six bays with a column of three bays along the compressive loading direction. The frames are supported at the ends to resist out-of-plane translation. Back-to-back strain gages are used to record the strain and displacement transducers were used to record the out-of-plane displacements. In addition a full-field measurement technique that utilizes a camera-based-stero-vision system was used to record displacements. The panels were loaded in increments to determine the first bay to buckle. Loading was discontinued at limit load and the panels were removed from the test machine for impact testing. After impacting at 20 ft-lbs to 25 ft-lbs of energy with a spherical indenter, the panels were loaded in compression until failure. Impact testing reduced the axial stiffness 4 percent and less than 1 percent. Postbuckled axial panel stiffness was 52 percent and 70 percent of the pre-buckled stiffness.
    Keywords: Structural Mechanics
    Type: NASA/TM-2004-213262 , ARL-TR-3233 , L-19031
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  • 5
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    Test and Analyses of a Composite Multi-Bay Fuselage Panel Under Uni-Axial Compression (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A composite panel containing three stringers and two frames cut from a vacuum-assisted resin transfer molded (VaRTM) stitched fuselage article was tested under uni-axial compression loading. The stringers and frames divided the panel into six bays with two columns of three bays each along the compressive loading direction. The two frames were supported at the ends with pins to restrict the out-of-plane translation. The free edges of the panel were constrained by knife-edges. The panel was modeled with shell finite elements and analyzed with ABAQUS nonlinear solver. The nonlinear predictions were compared with the test results in out-of-plane displacements, back-to-back surface strains on stringer flanges and back-to-back surface strains at the centers of the skin-bays. The analysis predictions were in good agreement with the test data up to post-buckling.
    Keywords: Structural Mechanics
    Type: AIAA Paper 2004-2056 , 45th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference; Apr 19, 2004 - Apr 22, 2004; Palm Springs, CA; United States
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  • 6
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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
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  • 7
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    Onboard Autonomy on the Earth Observing One Mission (2004)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The Earth Observing One Spacecraft is currently flying The Autonomous Sciencecraft Experiment (ASE) - onboard autonomy software to improve science return. The ASE software enables the spacecraft to autonomously detect and respond to science events occurring on the Earth. ASE includes software systems that perform science data analysis, mission planning, and run-time robust execution. In this article we describe the autonomy flight software and how it enables a new paradigm of autonomous science and mission operations.
    Keywords: Spacecraft Instrumentation and Astrionics
    Type: AIAA First Intelligence Systems Technical Conference; Sep 20, 2004 - Sep 22, 2004; Chicago, IL; United States
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  • 8
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    Analysis and Test of Repair Concepts for a Carbon-Rod Reinforced Laminate (2000)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: The use of pultruded carbon-epoxy rods for the reinforcement of composite laminates in some structures results in an efficient structural concept. The results of an analytical and experimental investigation of repair concepts of completely severed carbon-epoxy rods is presented. Three repair concepts are considered: (a) bonded repair with outside moldline and inside moldline doublers; (b) bonded repair with fasteners, and (c) bonded repair with outside moldline doubler only. The stiffness of the repairs was matched with the stiffness of the baseline specimen. The failure strains for the bonded repair with fasteners and the bonded repair with an outside moldline doubler exceeded a target design strain set for the repair concepts.
    Keywords: Structural Mechanics
    Type: AIAA Paper 2000-1596
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  • 9
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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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