Avionics chassis

1. An avionics chassis assembly comprising:

a housing having an outer surface, defining an exterior of the housing, an inner surface, defining an interior of the housing, at least one wall having inner and outer surfaces corresponding to the housing inner and outer surfaces, and made with carbon fiber reinforcement;

at least one card rail for holding an electronic circuit board mounted to the inner surface of the housing;

at least one heat-dissipating fin composed of carbon fiber and extending from the outer surface of the at least one wall and having a tab extending through the at least one wall and in abutting contact with the card rail; and

a plurality of isotropic carbon fibers extending from an interior of the fin through the at least one wall of the housing and in abutting contact with the card rail;

wherein the plurality of isotropic fibers extend through the tab and form a direct conductive path from the card rail to the heat-dissipating fin.

2. The avionics chassis assembly of claim 1 , wherein the at least one heat-dissipating fin is co-cured to the housing.

3. The avionics chassis assembly of claim 1 , further comprising a thermally conductive mount connecting the card rail to the inner surface of the wall and thermally conductively coupling the card rail to the isotropic carbon fibers to form part of the conductive path.

4. The avionics chassis assembly of claim 3 , wherein the thermally conductive mount is located between the card rail and the inner surface of the at least one wall and defines a plurality of interstitial spaces in which a thermally conductive adhesive is located to form part of the conductive path.

5. The avionics chassis assembly of claim 1 , wherein the at least one wall is metal plated.

6. The avionics chassis assembly of claim 1 , further comprising a frame to which the at least one wall is mounted.

7. The avionics chassis assembly of claim 1 , further comprising at least one other heat-dissipating fin projecting from the exterior of the at least one wall and wherein no plurality of isotropic carbon fibers extend through the at least one wall from the at least one other heat-dissipating fin.

8. The avionics chassis assembly of claim 7 , wherein the at least one wall is formed from a carbon composite that conducts heat from the at least one card rail to the at least one other heat-dissipating fin.

9. The avionics chassis assembly of claim 1 , wherein the isotropic carbon fibers have a thermal conductivity of about 1100 W/m-K.

10. The avionics chassis assembly of claim 1 , wherein the at least one heat-dissipating fin parallels the card rail.

11. The avionics chassis assembly of claim 10 , wherein the at least one heat-dissipating fin is of the same length as the card rail.

12. The avionics chassis assembly of claim 11 , wherein the plurality of isotropic fibers are arranged in groups spaced along the length of the heat-dissipating fin.

13. The avionics chassis assembly of claim 1 , further comprising a plurality of heat-dissipating fins, each having a plurality of isotropic fibers conductively coupled to the at least one card rail.

14. An avionics chassis assembly comprising:

a housing having an outer surface, defining an exterior of the housing, an inner surface, defining an interior of the housing, and made with carbon fiber reinforcement;

at least one card rail for holding an electronic circuit board mounted to the inner surface of the housing;

at least one heat-dissipating fin composed of carbon fiber, extending from the outer surface, paralleling the card rail and having the same length as the card rail; and

a plurality of isotropic carbon fibers extending from an interior of the fin through the housing and in abutting contact with the card rail;

wherein the plurality of isotropic fibers are arranged in groups spaced along the length of the heat-dissipating fin and the plurality of isotropic fibers form a direct conductive path from the card rail to the heat-dissipating fin.

15. The avionics chassis assembly of claim 14 , further comprising at least one other heat-dissipating fin projecting from the exterior of the housing and wherein no plurality of isotropic carbon fibers extend through the housing from the at least one other heat-dissipating fin.

16. The avionics chassis assembly of claim 14 , wherein the at least one heat-dissipating fin is co-cured to the housing.

17. The avionics chassis assembly of claim 14 , wherein the isotropic carbon fibers have a thermal conductivity of about 1100 W/m-K.

18. The avionics chassis assembly of claim 14 , further comprising a plurality of heat-dissipating fins, each having a plurality of isotropic fibers conductively coupled to the at least one card rail.