A spacecraft, configured to be operated in a geosynchronous orbit includes a power subsystem, including a battery, and a battery charge controller. The spacecraft is configured to have a power demand, during an eclipse season of the geosynchronous orbit, of ‘P’ kilowatts and the battery is sized to have a nominal capacity, measured in kilowatt-hours, smaller than 1.2*P/0.85. In some implementations, the battery has a rated charge voltage corresponding to the nominal capacity and the battery charge controller is configured to execute a battery charge management strategy that charges the battery to an above-rated charge voltage during selected portions of the eclipse season.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Battery charge management for geosynchronous spacecraft


    Beteiligte:

    Erscheinungsdatum :

    2019-03-26


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    H02J CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER , Schaltungsanordnungen oder Systeme für die Abgabe oder Verteilung elektrischer Leistung / B60R Fahrzeuge, Fahrzeugausstattung oder Fahrzeugteile, soweit nicht anderweitig vorgesehen , VEHICLES, VEHICLE FITTINGS, OR VEHICLE PARTS, NOT OTHERWISE PROVIDED FOR



    Charge Control of Geosynchronous Spacecraft Using Field Effect Emitters

    Mandell, Myron / Davis, Victoria / Gardner, Barbara et al. | AIAA | 2007


    Design of geosynchronous spacecraft

    Agrawal, Brij N. | TIBKAT | 1986


    A New Battery Life Prediction Method for Geosynchronous Spacecraft*

    Lyons, J. W. / Earl, H. W. / Dunlop, J. D. | AIAA | 1987



    INCLINED GEOSYNCHRONOUS ORBIT SPACECRAFT CONSTELLATIONS

    TURNER ANDREW E | Europäisches Patentamt | 2017

    Freier Zugriff