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  • 1
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    Design of a nickel-hydrogen battery simulator for the NASA EOS testbed (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The hardware and software design of a nickel-hydrogen (Ni-H2) battery simulator (BS) with application to the NASA Earth Observation System (EOS) satellite is presented. The battery simulator is developed as a part of a complete testbed for the EOS satellite power system. The battery simulator involves both hardware and software components. The hardware component includes the capability of sourcing and sinking current at a constant programmable voltage. The software component includes the capability of monitoring the battery's ampere-hours (Ah) and programming the battery voltage according to an empirical model of the nickel-hydrogen battery stored in a computer.
    Keywords: GROUND SUPPORT SYSTEMS AND FACILITIES (SPACE)
    Type: In: IECEC '92; Proceedings of the 27th Intersociety Energy Conversion Engineering Conference, San Diego, CA, Aug. 3-7, 1992. Vol. 2 (A93-25851 09-44); p. 2.399-2.404.
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    NASA TECHNICAL REPORTS
  • 2
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    Design of a solar array simulator for the NASA EOS testbed (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The present spacecraft solar array simulator addresses both dc and ac characteristics as well as changes in illumination and temperature and performance degradation over the course of array service life. The computerized control system used allows simulation of a complete orbit cycle, in addition to automated diagnostics. The simulator is currently interfaced with the NASA EOS testbed.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: In: IECEC '92; Proceedings of the 27th Intersociety Energy Conversion Engineering Conference, San Diego, CA, Aug. 3-7, 1992. Vol. 1 (A93-25851 09-44); p. 1.63-1.66.
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Spacecraft power system compatibility and stability for the NASA EOS satellite (1992)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: This paper addresses the problem of system stability of the NASA EOS satellite power system. A potential stability problem exists without a clear specification of the payload input impedance characteristic. Design guidelines are established for the control of the power system and the individual subcomponents to help insure stability with an unknown complex load. A testbed of the EOS power system is employed to verify the analysis.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: In: IECEC '92; Proceedings of the 27th Intersociety Energy Conversion Engineering Conference, San Diego, CA, Aug. 3-7, 1992. Vol. 1 (A93-25851 09-44); p. 1.57-1.62.
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Experimental verification of Space Platform battery discharger design optimization (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The detailed design of two candidate topologies for the Space Platform battery discharger, a four module boost converter (FMBC) and a voltage-fed push-pull autotransformer (VFPPAT), is presented. Each has unique problems. The FMBC requires careful design and analysis in order to obtain good dynamic performance. This is due to the presence of a right-half-plane (RHP) zero in the control-to-output transfer function. The VFPPAT presents a challenging power stage design in order to yield high efficiency and light component weight. The authors describe the design of each of these converters and compare their efficiency, weight, and dynamic characteristics.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: IECEC ''91: Intersociety Energy Conversion Engineering Conference; Aug 04, 1991 - Aug 09, 1991; Boston, MA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Use of nonlinear design optimization techniques in the comparison of battery discharger topologies for the space platform (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A detailed comparison of a boost converter, a voltage-fed, autotransformer converter, and a multimodule boost converter, designed specifically for the space platform battery discharger, is performed. Computer-based nonlinear optimization techniques are used to facilitate an objective comparison. The multimodule boost converter is shown to be the optimum topology at all efficiencies. The margin is greatest at 97 percent efficiency. The multimodule, multiphase boost converter combines the advantages of high efficiency, light weight, and ample margin on the component stresses, thus ensuring high reliability.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Intersociety Energy Conversion Engineering Conference; Aug 12, 1990 - Aug 17, 1990; Reno, NV; United States
    Format: text
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    NASA TECHNICAL REPORTS
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