Telecommunications satellite architecture
AssigneesAirbus Defence and Space GmbH, Thales, Centre National D'Etudes Spatiales (Cnes)
InventorsRaphaël Hache, Bruno Trancart, Andrew Walker
Life of this patent
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Abstract
A telecommunications satellite stabilized on three axes includes a set of dissipative equipment constituting a payload of the satellite. The satellite includes support data transmission antennas and is substantially parallelepipedal in shape with the panels forming two opposite faces, east and west faces. The panels form two additional opposite faces, north and south faces, and include radiator surfaces on their external faces. The radiator surfaces are configured to cool the electronic equipment of the satellite. The equipment installed on the north and south panels dissipate thermal power corresponding to less than 25% of the total dissipated power.
Claims16
A telecommunications satellite stabilized on three axes, comprising:
- a set of dissipative equipment constituting a satellite payload, the satellite is substantially parallelepipedal in form with east and west panels forming two opposing faces, the satellite comprises supporting data transmission antennas, and north and south panels forming two other opposing faces, the north and south panels comprising, on their outer faces, radiator surfaces configured to cool an electronic equipment of the satellite;
- and
- wherein the dissipative equipment installed on the north and south panels is configured to dissipate a thermal power corresponding to less than 25% of a total dissipated power of the electronic equipment of the payload.
An integration method for a telecommunications satellite stabilized on three axes, the satellite comprises a set of dissipative equipment constituting a satellite payload, the satellite is substantially parallelepipedal in form with east and west panels forming two opposing faces, the satellite comprises supporting data transmission antennas, and north and south panels forming two other opposing faces, the north and south panels comprising, on their outer faces, radiator surfaces configured to cool an electronic equipment of the satellite, the method comprises the steps of using the dissipative equipment installed on the north and south panels to dissipate a thermal power corresponding to less than 25% of a total dissipated power of the electronic equipment of the payload;
- and opening one of the north or south panels to access the satellite payload.
Dependencies are inferred from the claim text.