A spacecraft (100) includes a structural interface adapter for mating to a launch vehicle, an aft surface disposed proximate thereto, and a forward surface disposed opposite thereto, a main body structure, including a plurality of sidewalls (116,117), disposed between the aft surface and the forward surface and a plurality of unfurlable antenna reflectors (130). At least one unfurlable antenna reflector is configured to be illuminated, in an on-orbit configuration, by a respective feed array.(160). The spacecraft is reconfigurable from a launch configuration to the on-orbit configuration. In the launch configuration, the at least one unfurlable antenna reflector (130) is disposed, undeployed, forward of the respective feed array (160), proximate to and outboard of one of the plurality of sidewalls (116, 117). In the on-orbit configuration, the forward surface is substantially earth-facing and the at least one unfurlable antenna reflector is disposed, deployed, so as to be earth-facing from a position aft of the respective feed array.


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    Title :

    HIGH CAPACITY COMMUNICATION SATELLITE


    Additional title:

    HOCHLEISTUNGSKOMMUNIKATIONSSATELLIT
    SATELLITE DE COMMUNICATION À GRANDE CAPACITÉ


    Contributors:
    WU GORDON (author) / ALLEY PHILIP (author) / MARLOW DAVID (author)

    Publication date :

    2020-02-26


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS / H01Q Antennen , ANTENNAS, i.e. RADIO AERIALS



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