Aircraft heat sink and electronics enclosure

1. An aircraft component comprising:

a first section adapted to be attached at an exterior surface of an aircraft to close an access opening through the exterior surface;

a second section extending outward from the first section and forming at least one heat transfer surface to transfer heat from the first section to air passing by the exterior surface and second section, wherein the first and second sections are integrally formed as a one-piece member; and

a heat sink comprising the first and second sections, and wherein a third section is provided at an inward facing side with a connection section adapted to have housing walls attached to the connection section to form a housing for an electronic device.

2. An aircraft component as in claim 1 wherein the aircraft component is comprised of ferromagnetic material to form an electromagnetic interference (EMI) shielding member.

3. An aircraft electronic device comprising:

electronic circuitry comprising at least one printed circuit board; and

a housing having the electronic circuitry located in the housing, the housing comprising an aircraft component forming a first housing member and at least one second housing member attached to the aircraft component to form an enclosure housing the electronic circuitry, wherein the aircraft component comprises:

a first section adapted to be attached at an exterior surface of an aircraft to close an access opening through the exterior surface; and

a second section extending outward from the first section and forming at least one heat transfer surface to transfer heat from the first section to air passing by the exterior surface and second section,

wherein the first and second sections are integrally formed as a one-piece member.

4. An aircraft electronic device as in claim 3 wherein the electronic circuitry comprises an airborne microwave modem assembly.

5. An aircraft electronic device as in claim 3 wherein the electronic circuitry comprises digital signal encrypting and compression electronics.

6. An aircraft comprising:

a drive unit;

an air frame comprising at least one airfoil, the drive unit being attached to the air frame; and

an aircraft electronic device as in claim 3 connected to the airfoil.

7. An aircraft as in claim 6 wherein the airfoil is a wing of the aircraft, and wherein the at least one heat transfer surface extends from a bottom side of the wing.

8. An aircraft electronic device comprising:

electronic circuitry which generates heat; and

a housing having the electronic circuitry located in the housing, the housing comprising a first wall member with a heat sink section that extends in an outward direction at an outer side of the first wall member, and a connection section located at an inner side of the first wall member, wherein other walls of the housing are attached to the connection section to form an enclosure housing the electronic circuitry, and wherein the first wall member further comprises a flange extending from the connection section which is sized and shaped to be attached to an exterior side of an aircraft,

wherein the electronic circuitry comprises at least one printed circuit board, and the housing comprises heat rail and card slot members on opposite sides of the printed circuit board, wherein sides of the printed circuit board are attached to the heat rail and card slot members, and wherein the heat rail and card slot members are attached to the inner side of the first wall member.

9. An aircraft electronic device as in claim 8 wherein the heat sink section comprises heat transfer fins extending in the outward direction.

10. An aircraft electronic device as in claim 8 wherein the flange comprises a perimeter flange which surrounds the connection section, and wherein the flange comprises holes adapted to receive fasteners to attach the flange to the exterior side of the aircraft.

11. An aircraft electronic device as in claim 8 wherein the housing, including the first wall member, forms an electromagnetic interference (EMI) shield surrounding the electronic circuitry.

12. An aircraft electronic device as in claim 8 further comprising an electromagnetic interference (EMI) shield surrounding the electronic circuitry, the EMI shield comprising the first wall member.

13. An aircraft electronic device comprising:

electronic circuitry which generates heat; and

a housing having the electronic circuitry located in the housing, the housing comprising a first wall member with a heat sink section that extends in an outward direction at an outer side of the first wall member, and a connection section located at an inner side of the first wall member, wherein other walls of the housing are attached to the connection section to form an enclosure housing the electronic circuitry, and wherein the first wall member further comprises a flange extending from the connection section which is sized and shaped to be attached to an exterior side of an aircraft,

wherein the electronic circuitry comprises an airborne microwave modem assembly.

14. An aircraft electronic device comprising:

electronic circuitry which generates heat; and

a housing having the electronic circuitry located in the housing, the housing comprising a first wall member with a heat sink section that extends in an outward direction at an outer side of the first wall member, and a connection section located at an inner side of the first wall member, wherein other walls of the housing are attached to the connection section to form an enclosure housing the electronic circuitry, and wherein the first wall member further comprises a flange extending from the connection section which is sized and shaped to be attached to an exterior side of an aircraft,

wherein the electronic circuitry comprises an airborne link interface assembly comprising digital signal encryption and compression electronics.

15. An aircraft electronic device comprising:

electronic circuitry which generates heat; and

a housing having the electronic circuitry located in the housing, the housing comprising a first wall member with a heat sink section that extends in an outward direction at an outer side of the first wall member, and a connection section located at an inner side of the first wall member, wherein other walls of the housing are attached to the connection section to form an enclosure housing the electronic circuitry, and wherein the first wall member further comprises a flange extending from the connection section and adapted to be attached to an exterior side of an aircraft,

wherein the connection section of the first wall member comprises a wedge shaped section adapted to have the other walls of the housing located thereon.

16. An aircraft comprising:

a drive unit;

an air frame comprising at least one airfoil, the drive unit being attached to the air frame; and

an electronic communications device connected to the air frame, wherein the electronic communications device comprises a printed circuit board and a housing, wherein the housing has a first side section connected at an exterior side of the airfoil to close an access opening through the airfoil, and wherein the first side section of the housing forms a wall of an enclosure for the printed circuit board,

wherein the first side section comprises a heat sink located in the access opening of the airfoil, and wherein the heat sink comprises heat transfer fins extending outward from the airfoil.

17. An aircraft as in claim 16 wherein the housing forms an electromagnetic interference (EMI) shield around the printed circuit board.

18. An aircraft as in claim 16 wherein the first side section comprises a perimeter flange with holes therethrough for attaching the first side section to the exterior side of the airfoil.

19. An aircraft as in claim 16 wherein the first side section forms a structural and contour component for the airfoil.

20. A method of assembling an electronic device with an aircraft comprising steps of:

providing the electronic device with a housing having a side with a heat sink;

inserting the electronic device into an access aperture in the aircraft; and

attaching the side of the housing of the electronic device to the aircraft to close the access aperture, wherein the heat sink is located in the access aperture and at an exterior of the aircraft.

21. An aircraft electronic device comprising:

electronic circuitry which generates heat; and

a housing comprising a first wall member and a second wall member, wherein the first wall member comprises a heat sink section and a connection section, wherein the second wall member is attached to the first wall member to at least partially enclose the electronic circuitry in the housing, and wherein the connection section is sized and shaped to be attached to an aircraft with the heat sink section located at an exterior of the aircraft to transfer heat directly from the heat sink section to air passing along the exterior of the aircraft, wherein the heat sink section comprises heat transfer fins extending in an outward direction relative to the exterior of the aircraft.