Systems and methods for routing electrical wiring through an aircraft structure

1. An aircraft wing, comprising:

a front spar;

a rear spar;

a plurality of ribs extending from the front spar to the rear spar, each rib including a plurality of wire openings,

a plurality of high voltage wires disposed in the wire openings in the plurality of ribs such that each wire opening receives one high voltage wire, and the each wire opening has an opening size larger than a size of the one high voltage wire, the opening size being smaller than a size of a connector attached to an end of the one high voltage wire;

a lower skin; and

an upper skin,

wherein the wire openings accommodate the high voltage wires being installed in the wire openings before curing the upper skin onto the plurality of ribs.

2. The aircraft wing of claim 1 , wherein the plurality of wire openings on the each rib are positioned along a length of the each rib proximate the upper skin.

3. The aircraft wing of claim 1 , wherein the plurality of wire openings on the each rib are spaced apart to maintain a predetermined separation between each of the high voltage wires.

4. The aircraft wing of claim 1 , wherein the high voltage wires are configured to pass through a fuselage of an aircraft, through the plurality of openings on the plurality of ribs of the aircraft wing, and into a wing box of the aircraft wing.

5. The aircraft wing of claim 1 , further comprising a plurality of interface connectors positioned between the aircraft wing and a fuselage of an aircraft, wherein the plurality of interface connectors are configured to be coupled to the high voltage wires.

6. The aircraft wing of claim 1 , wherein curing the upper skin onto the plurality of ribs is performed at a temperature in a range between about 115° C. and about 200° C.

7. The aircraft wing of claim 1 , wherein the opening size ranges between about 1.5 inches and about 2.5 inches.

8. The aircraft wing of claim 1 , wherein a weight of one of the each rib ranges between about 5 lbs and about 10 lbs.

9. The aircraft wing of claim 1 , wherein a distance between any two of the high voltage wires ranges between about 4 inches and about 30 inches.

10. A method of manufacturing an aircraft wing, the method comprising:

assembling a front spar, a rear spar, and a plurality of ribs onto a lower skin, wherein the plurality of ribs extend from the front spar to the rear spar, each rib in the plurality of ribs including a plurality of wire openings configured to receive high voltage wires,

wherein each wire opening has an opening size larger than a size of one high voltage wire, the opening size being smaller than a size of a connector attached to an end of the one high voltage wire;

installing high voltage wires in the wire openings in the plurality of ribs, such that the each wire opening receives the one high voltage wire;

assembling an upper skin onto the plurality of ribs after installing the high voltage wires in the wire openings; and

curing bonds between the front spar, the rear spar, the plurality of ribs, the lower skin, and the upper skin to form a final wing assembly.

11. The method of claim 10 , further comprising forming the plurality of wire openings in the each rib along a length of the each rib proximate the upper skin.

12. The method of claim 10 , further comprising forming the plurality of wire openings such that the wire openings are spaced apart from each other at a predetermined distance.

13. The method of claim 10 , wherein installing the high voltage wires in the wire openings further comprises:

passing the high voltage wires through a fuselage of an aircraft, through the wire openings on the plurality of ribs of an aircraft wing, and into a wing box of the aircraft wing.

14. The method of claim 10 , wherein installing the high voltage wires in the wire openings further comprises:

installing the high voltage wires in an uncured composite aircraft wing; and

curing the bonds between the front spar, the rear spar, the plurality of ribs, the lower skin, and the upper skin to form the final wing assembly with the high voltage wires inside the aircraft wing.

15. The method of claim 10 , further comprising positioning a plurality of interface connectors between the aircraft wing and a fuselage of an aircraft, wherein the plurality of interface connectors are configured to be coupled to the high voltage wires.

16. The method of claim 10 , wherein curing the bonds is performed at a temperature in a range between about 115° C. and about 200° C.

17. The method of claim 10 , wherein the opening size ranges between about 1.5 inches and about 2.5 inches.

18. The method of claim 10 , wherein a weight of the each rib ranges between about 5 lbs and about 10 lbs.

19. The method of claim 10 , wherein a distance between any two of the high voltage wires ranges between about 4 inches and about 30 inches.

20. An aircraft assembly, comprising:

an aircraft structure comprising a component;

a plurality of wire openings in the component; and

a plurality of high voltage wires disposed in the wire openings in the component such that each wire opening receives one high voltage wire, and the each wire opening has an opening size larger than a size of the one high voltage wire, the opening size being smaller than a size of a connector attached to an end of the one high voltage wire;

wherein the wire openings accommodate the high voltage wires being installed in the wire openings before curing the aircraft structure.

21. The aircraft structure of claim 20 , wherein the aircraft structure is a wing and the component comprising the wire openings is a rib of the wing.

22. The aircraft structure of claim 20 , wherein the aircraft structure is a fuselage and the component comprising the wire openings is a frame of the fuselage.

23. The aircraft structure of claim 20 , wherein the aircraft structure is a fuselage and the component comprising the wire openings is a skin of the fuselage.

24. The aircraft structure of claim 20 , wherein the aircraft structure is a boom and the component comprising the wire openings is a skin of the boom.

25. The aircraft structure of claim 20 , wherein the aircraft structure is a stabilizer and the component comprising the wire openings is a rib of the stabilizer.