ELECTRICAL POWER DISTRIBUTION INTEGRATED INTO A SATELLITE STRUCTURAL PANEL

Abstract

A structural panel for a satellite includes an external skin, an internal skin and a core layer arranged between the two, internal and external, skins and provided with a blind void comprising at least one electrically insulated inserted busbar.

Claims

1. A structural panel for a satellite comprising an external skin, an internal skin and a core layer arranged between the two, internal and external, skins and provided with a blind void comprising at least one electrically insulated inserted busbar, the busbar comprising a set of electrically insulating layers and of electrically conductive layers such that each conductive layer is doubly electrically insulated by an envelope formed of two electrically insulating layers, and the panel comprising a joining material filling the blind void in order to keep the inserted busbar fixed in place.

2. The structural panel for a satellite according to claim 1, wherein the joining material is rigid foam, resin or glue.

3. The structural panel for a satellite according to claim 1, wherein a bar of the busbar comprises at least two electrical contacts that are intended to connect an element arranged outside the panel on the side of the internal skin.

4. The structural panel for a satellite according to claim 3, wherein an electrical contact comprises two contact pads.

5. The structural panel for a satellite according to claim 1, wherein the core layer comprises a material with a cellular structure.

6. The structural panel for a satellite according to claim 5, wherein the core layer comprising a material with a cellular structure has a honeycomb structure.

7. The structural panel for a satellite according to claim 1, wherein the inserted busbar comprises three bars corresponding to two different voltage sources and a common ground.

8. A satellite comprising at least one structural panel according to claim 1.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The invention will be better understood from studying a few embodiments described by way of completely non-limiting example and illustrated by the appended drawings, in which:

[0024] FIG. 1 schematically illustrates a structural panel for a satellite, according to one aspect of the invention;

[0025] FIG. 2 schematically illustrates a busbar, according to one aspect of the invention;

[0026] FIG. 3 schematically illustrates a busbar and a connection, according to one aspect of the invention; and

[0027] FIG. 4 schematically illustrates a satellite, according to one aspect of the invention.

[0028] Throughout the1ures, elements having identical references are similar.

DETAILED DESCRIPTION

[0029] FIG. 1 shows, in cross section, a structural panel according to one aspect of the invention, comprising an external skin 1, which is for example electromagnetically shielded, intended to be on the outside of a satellite, an internal skin 2, which is for example electromagnetically shielded, intended to be on the inside of the satellite, and a core layer 3 arranged between the two, internal 2 and external 1, skins and provided with a blind void 4 comprising at least one inserted busbar 5. A joining material 6 fills the blind void 4 in order to keep the inserted busbar 5 fixed in place.

[0030] FIG. 2 shows, in cross section, the detail of a busbar 5 comprising a set of electrically conductive layers 7 and of electrically insulating layers 8 such that each conductive layer 7 is electrically insulated by an envelope formed of two electrically insulating layers 6. For example, the busbar 5 comprises three bars or conductive layers 7 that are electrically insulated by a respective envelope formed of two electrically insulating layers 6. Two contiguous layers are attached to one another by an adhesive layer 9, for example a prepreg.

[0031] The joining material 6 may be rigid foam, resin or glue.

[0032] The core layer 3 is, for example, a material with a cellular structure, or a material of rigid foam type.

[0033] Advantageously, the core layer 3 is a material with a cellular structure of honeycomb type. The honeycomb commonly called NIDA consists of a hexagonal cellular structure enclosed between two thin sheets of aluminium. The conductors placed inside this composite structure are therefore ideally shielded from an electromagnetic point of view, by construction. Consequently, larger high-frequency currents may flow without interfering with their surroundings. Measurements have shown that it is possible to increase the high-frequency currents in conductors trapped within a NIDA tenfold. This has a direct effect on the sizing of the electrical filters, which may be decreased in size and therefore in weight.

[0034] FIG. 3 shows an electrical contact 10 connected to a bar of a busbar 5, in cross section, according to one aspect of the invention. The connection between the electrical contact 10 and the bar of the busbar 5 may be made by soldering or crimping.

[0035] FIG. 4 schematically shows a satellite, the faces of which comprise structural panels as described above. The satellite therefore comprises, in its panels, a busbar comprising, for example, three bars: a high-voltage current bar 6a, a low-voltage current bar 6c and a common ground bar 6b.