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  • 1
    Publication Date: 2014-09-12
    Description: An overview of space power management and distribution (PMAD) is provided which encompasses historical and current technology trends. The PMAD components discussed include power source control, energy storage control, and load power processing electronic equipment. The status of distribution equipment comprised of rotary joints and power switchgear is evaluated based on power level trends in the public, military, and commercial sectors. Component level technology thrusts, as driven by perceived system level trends, are compared to technology status of piece-parts such as power semiconductors, capacitors, and magnetics to determine critical barriers.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Space Power; p 205-218
    Format: text
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  • 2
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    In:  CASI
    Publication Date: 2019-07-13
    Description: This is the second in a series of semi-annual reports that describe the technology areas being advanced under this contract and the progress achieved to date. The last technology report concentrated on the spacecraft. This report places greater emphasis on the payloads. White papers by several of the payload providers are attached. These are HSI, UCB, PRKE, and CAFE. This report covers the period from January 1995 through June 1995.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NIPS-95-05614 , NASA-CR-199619 , NAS 1.26:199619
    Format: application/pdf
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  • 3
    Publication Date: 2019-07-13
    Description: Observatory power is generated by a partially deployable solar array which is modularized to facilitate adaptation to three missions having different power requirements. Three nickel-cadmium batteries are controlled independently from dedicated modular chargers to increase subsystem adaptability and decrease sensitivity to temperature differences between batteries. Battery level redundancy is employed, enabling mission completion with two of three battery/charger combinations operational. Bus voltage limiting is accomplished by a modularized shunt regulator which can survive any single part failure and meet all mission requirements. Relatively low shunt electronics power dissipation internal to the observatory is achieved by sequenced operation of linear shunt segments which are coupled to a large area resistive shunt radiator. Summaries of solar array, battery and subsystem breadboard test results are provided.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Conference on Intersociety Energy Conversion Engineering; Sep 12, 1976 - Sep 17, 1976; State Line, NV
    Format: text
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  • 4
    Publication Date: 2019-07-13
    Description: The Pioneer F/G spacecraft is the first to use radioisotope thermoelectric generators (RTG's) for a long duration interplanetary mission. This paper describes the design of the spacecraft power subsystem which meets the unique requirements of such a mission. The primary power source consists of four SNAP 19 RTG's. The 4.2 volt dc outputs of the RTG's are inverted to higher voltage ac by four inverters which are connected in parallel at their outputs. A power control unit (PCU) regulates the ac output of the inverters such that the RTG's are operated at near maximum power voltage throughout the mission. The PCU also contains charge and discharge controls for a silver cadmium battery which supplements the RTG's if load requirements temporarily exceed RTG power output. Battery reliability is enhanced by overcharge and cell reversal protection electronics which are provided for each cell. Multiple, low voltage, regulated dc outputs which supply power to the spacecraft subsystems are provided by a central transformer-rectifier-filter unit (CTRF). The CTRF operates directly from the regulated ac bus.
    Keywords: AUXILIARY SYSTEMS
    Type: PCSC ''71; Power Conditioning Specialists Conference, California Institute of Technology; Apr 19, 1971 - Apr 20, 1971; Pasadena, CA
    Format: text
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  • 5
    Publication Date: 2019-07-13
    Description: The design and flight performance of the HEAO-1 power subsystem is described. Solar array power analysis and test data are compared to orbital performance. The batteries are described along with parametric cell tests which led to the temperature-compensated voltage limits used in the charge controls. Battery life test results, used for verification of battery charger temperature-compensated voltage limits, are compared with orbital performance. The control electronics are
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: Intersociety Energy Conversion Engineering Conference; Aug 20, 1978 - Aug 25, 1978; San Diego, CA
    Format: text
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