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  • 1
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    Design and Flight Performance of NOAA-K Spacecraft Batteries (1999)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The US National Oceanic and Atmospheric Administration (NOAA) operates the Polar Operational Environmental Satellite (POES) spacecraft (among others) to support weather forecasting, severe storm tracking, and meteorological research by the National Weather Service (NWS). The latest in the POES series of spacecraft, named as NOAA-KLMNN, is in orbit and four more are in various phases of development. The NOAA-K spacecraft was launched on May 13, 1998. Each of these spacecraft carry three Nickel-Cadmium batteries designed and manufactured by Lockheed Martin. The battery, which consists of seventeen 40 Ah cells manufactured by SAFT, provides the spacecraft power during the ascent phase, orbital eclipse and when the power demand is in excess of the solar array capability. The NOAA-K satellite is in a 98 degree inclination, 7:30AM ascending node orbit. In this orbit the satellite experiences earth occultation only 25% of the year. This paper provides a brief overview of the power subsystem, followed by the battery design and qualification, the cell life cycle test data, and the performance during launch and in orbit.
    Keywords: Energy Production and Conversion
    Type: The 1998 NASA Aerospace Battery Workshop; 113-138; NASA/CP-1999-209144
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    FAST Spacecraft Battery Design and Performance (1997)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Fast Auroral Snapshot (FAST) Explorer spacecraft is to study the physical processes that produce the aurora borealis and aurora australis. It is a unique plasma physics experiment that will take fundamental measurements of the magnetic and electrical fields. This investigation will add significantly to our understanding of the near-earth space environments and its effect. The FAST has a 1 year requirement and 3-year goal for its mission life in low earth orbit. The FAST power power system topology is a Direct Energy Transfer (DET) system based on the SAMPEX design. The FAST flight battery supplies power to the satellite during pre-launch operations, the launch phase, the eclipse periods for all mission phases, and when the load is about 50 watts.
    Keywords: Energy Production and Conversion
    Type: The 1996 NASA Aerospace Battery Workshop; 469-492; NASA-CP-3347
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    On-Orbit Health Check of Hubble Space Telescope Nickel-Hydrogen Batteries (1997)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The Hubble Space Telescope is a one-of-a-kind spacecraft that pushes technology to its limits. Housing an 8-foot (2.4 meter) mirror and several sophisticated cameras and detectors the telescope is the largest orbital astronomy observatory ever placed in space. It has two modules each containing three 88 Ah NiH2 batteries (six total). Reconditioning has traditionally been used as a means of maintaining the performance of normal cells and batteries. This paper describes the objective, procedure, and results of a reconditioning processes that used to improve the performance of an HST nickel-hydrogen batteries.
    Keywords: Energy Production and Conversion
    Type: The 1996 NASA Aerospace Battery Workshop; 231-261; NASA-CP-3347
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  • 4
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    In-Orbit Earth Radiation Budget Satellite (ERBS) Battery Switch (2000)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A viewgraph presentation outlines the Earth Radiation Budget Satellite (ERBS) power system and battery history. ERBS spacecraft and battery cell failures are listed with the reasons for failure. The battery management decision and stabilization of the batteries is discussed. Present battery operations are shown to be successful.
    Keywords: Energy Production and Conversion
    Type: The 1999 NASA Aerospace Battery Workshop; 65-85; NASA/CP-2000-209959
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  • 5
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    Performance of Nickel-Cadmium Batteries on the GOES-1 Series of Weather Satellites (1999)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: This is an errata from an original paper published in the 1997 NASA Aerospace Battery workshop proceedings. A minor change was made to the second equation on page 98 and table 4 was revised during the final preparation of the paper. These changes were inadvertently left out of the final proceedings. These pages are reproduced in their entirety.
    Keywords: Energy Production and Conversion
    Type: The 1998 NASA Aerospace Battery Workshop; 703-705; NASA/CP-1999-209144
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  • 6
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    Thermal Control Using Electrochromism (1999)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The applicability of a charge balanced electrochromic device to modulate the frequencies in the thermal infrared region is examined in this study. The device consisted of a transparent conductor, WO3, anode, PMMA/LiClO4 electrolyte, V2O5 cathode and transparent conductor. The supporting structure in the device is SnO2 coated glass and the edges are sealed with epoxy to reduce moisture absorption. The performance evaluation comprised of cyclic voltammetric measurements and determination of transmittance at various wavelengths. The device was subjected to anodic and cathodic polarization by sweeping the potential at a rate of 10 mV/sec from -0.8V to 1.8V. The current versus voltage profile indicated no reaction between -0.5 and +0.5 V. The device is colored green at 1.8 V with a transmittance of 5% at a wavelength, lambda = 900 nm and colorless at -0.8 V with a transmittance of 74% at lambda = 500 nm. The optical modulation is limited to 400-1500 nm and there is no activity in the thermal infrared. The switching time is a function of temperature and time for coloring reaction was slower than the bleaching reaction. The device yielded reproducible values for transmittance when cycled between colored and bleached states by application of 1.8V and -0.8V, respectively.
    Keywords: Energy Production and Conversion
    Type: The 1998 NASA Aerospace Battery Workshop; 39-59; NASA/CP-1999-209144
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  • 7
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    Behavior of 2-Cell CPV Ni-H2 Battery During Pulse Discharge (1998)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A study was carried out to determine the transient voltage behavior of the 2-cell CPV nickel-hydrogen battery with the objective of using the results as a basis for mathematical modeling. The 2-cell CPV battery which is manufactured by Eagle Picher, Inc. for the GOES program yields 18.5 Ah at C/2 rate of discharge at 10 C with a mid-discharge voltage of 2.514 V. The capacity increased with decrease of temperature and a maximum capacity of 22 Ah was obtained at -5 C. The pulse tests consisted of obtaining the voltage profile in the first 20 milliseconds of the one minute pulse discharge at 37 A and pulse discharge was repeated as a function of state-of-charge. The pulse test at 10 C and 20 C provided voltage profiles with the expected decrease in voltage as the pulse was applied. The end of pulse voltage decreased with the state-of-charge. The battery voltage was above 2V at the end of the one-minute pulse at 8 % state-of-charge at 10 C. The voltage profile during the 37 A pulse discharge consists of an initial drop in voltage which was independent of the state of charge. The invariability in the value for the initial drop in voltage with state of charge is a very important observation. The results show that towards the end of discharge the dominant resistance is not ohmic in nature. It could be hypothesized from the nature of the voltage transients that the dominant mechanism towards the end of discharge is proton diffusion. The study also shows that the dominant resistance in the voltage plateau during discharge is activation polarization.
    Keywords: Energy Production and Conversion
    Type: The 1997 NASA Aerospace Battery Workshop; 713-727; NASA/CP-1998-208536
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  • 8
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    Crane Cell Testing Support of Goddard Space Flight Center (1998)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The objective of this section is to verify the quality and reliability of aerospace battery cells and batteries for NASA flight programs and to design the battery/cell for upcoming NASA spacecraft.
    Keywords: Energy Production and Conversion
    Type: The 1997 NASA Aerospace Battery Workshop; 149-160; NASA/CP-1998-208536
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  • 9
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    Crane Cell Testing Support of NASA/Goddard Space Flight Center: An Update (2001)
    In:  CASI
    Details
    Publication Date: 2017-09-27
    Description: The objectives presented in this viewgraph presentation include: 1) Verify the quality and reliability of aerospace battery cells and batteries for NASA flight programs; 2) Disseminate the data to develop a plan for in-orbit battery management and to design a cell/battery for future NASA spacecraft; and 3) Establish a cell test data base for rechargeable cell/batteries. In summary: quality EPT Ni-H2, EPT Super NiCd and SAFT NiCd cells have been demonstrated for aerospace applications; the data has been provided to NASA Centers and other agencies for their use and application; developed plan and used in NASA in-orbit battery management. Database on rechargeable cell/batteries is now available for customer use.
    Keywords: Energy Production and Conversion
    Type: The 2000 NASA Aerospace Battery Workshop; NASA/CP-2001-210883
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  • 10
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    Effects of AEA Cell-Bypass-Switch Closure on Charged EOS-Aqua NiH2 Cell (2001)
    In:  CASI
    Details
    Publication Date: 2017-09-27
    Description: The nominal performance of AEA CBPD under simulated EOS-Aqua/Aura flight hardware configuration has been demonstrated. There is no evidence of cell rupture or excessive heat production during or after CBPD switch activation under simulated high cell impedance (open-circuit cell failure mode). Inadvertent CBPD switch activation with a charged cell (low impedance path) intermittently closes and opens up the switch, therefore the device may or may not provide protection against future open-circuit cell failure. Further testing with switches F01 and F02 may provide clarification. The formation of a continuous low impedance path (a homogeneous low melting point alloy), has been confirmed - which is the expected mode of operation.
    Keywords: Energy Production and Conversion
    Type: The 2000 NASA Aerospace Battery Workshop; NASA/CP-2001-210883
    Format: application/pdf
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