Aircraft cable routing system and method of installation thereof
A cable routing system is disclosed having dielectric, or insulating, liner which is installed within a cable routing channel, or raceway, to subdivide the channel into at least two secondary channels. This can achieve more efficient use of space and enable more flexible placement of cables within the channels while meeting safety requirements. Installation of cables into the channel can include inserting the cables into the dielectric liner before the installation of the dielectric liner into the cable routing channel. The cable routing system can be used in an aircraft, including within space-constrained areas of the aircraft such as inside a wing.
1. An aircraft cable routing system comprising:
a cable raceway having a channel-shaped and configuration; and
a dielectric liner configured to be inserted into the cable raceway, wherein the dielectric liner comprises at least one subdividing element such that, when inserted into the cable raceway, the dielectric liner divides the cable raceway into at least two secondary channels positioned within the cable raceway, and wherein the dielectric liner defines a closed secondary channel.
2. An aircraft cable routing system according to claim 1 , further comprising a second dielectric liner which defines at least two open secondary channels which are at least partially open along their length.
3. An aircraft cable routing system according to claim 1 , wherein the dielectric liner is an assembly comprising a first liner part and a second liner part, and the closed secondary channel is defined by both the first liner part and the second liner part.
4. An aircraft cable routing system according to claim 1 , wherein the dielectric liner comprises a retention feature for retaining the dielectric liner in the cable raceway.
5. An aircraft cable routing system according to claim 1 , wherein the routing fixture comprises a retention feature for retaining the dielectric liner in the cable raceway.
6. An aircraft cable routing system, comprising:
a routing fixture defining a primary channel;
a dielectric liner for insertion into the primary channel, wherein the dielectric liner commits at least one subdividing element such that, when inserted into the primary channel, the dielectric liner divides the primary channel into at least two secondary channels positioned within the primary channel; and,
wherein a length of the at least two secondary channels is greater than a length of the primary channel.
7. An aircraft cable routing system according to claim 6 , comprising:
a second routing fixture defining a second primary channel; and
wherein, in use, the second routing fixture is spaced apart from the routing fixture and the dielectric liner is engaged with both the primary channel and the second primary channel such that the dielectric liner extends between the routing fixture and the second routing fixture.
8. An aircraft cable routing system according to claim 1 , wherein the dielectric liner comprises thermoplastic composite material, thermoset material, thermoset composite material or a combination thereof.
9. An aircraft cable routing system according to claim 1 , wherein a dielectric liner is at least 0.5 mm thick between secondary channels.
10. An aircraft cable routing system according to claim 1 , wherein the cable raceway is conductive.
11. An aircraft cable routing system according to claim 1 , wherein the cable raceway is not conductive.
12. An aircraft wing comprising an aircraft cable routing system according to claim 1 and at least one cable contained in a secondary channel of the aircraft cable routing system.
13. An aircraft comprising an aircraft cable routing system according to claim 1 and at least one cable contained in a secondary channel of the aircraft cable routing system.
14. A method of installing cables into an aircraft, the method comprising:
providing a routing fixture on a structural component of an aircraft, wherein the routing fixture defines a primary channel;
providing a dielectric liner separately from the routing fixture, wherein the dielectric liner is for insertion into the primary channel and defines at least two secondary channels;
routing a first cable in a first secondary channel of the dielectric liner;
routing a second cable in a second secondary channel of the dielectric liner;
inserting the dielectric liner into the primary channel after the routing a first cable and the routing a second cable, such that the at least two secondary channels are contained within the primary channel.
15. A method according to claim 14 , wherein:
the dielectric liner comprises:
a first liner part which at least partially defines the first secondary channel; and
a second liner part which at least partially defines the second secondary channel;
the method comprising:
inserting the first liner part into the primary channel; and
inserting the second liner part into the primary channel after the inserting the first liner part.
16. A method according to claim 14 , wherein a length of the at least two secondary channels is greater than a length of the primary channel, the method comprising:
providing a second routing fixture on a structural component of the aircraft spaced apart from the routing fixture, wherein the second routing fixture defines a second primary channel; and
inserting the dielectric liner into both the primary channel and the second primary channel after the routing a first cable and the routing a second cable such that the dielectric liner extends between the routing fixture and the second routing fixture.
17. A cable routing system for an aircraft comprising:
a raceway; and
an insulating liner configured to be inserted into the raceway, wherein the insulating liner comprises at least one subdividing wall such that, when inserted into the raceway, the insulating liner divides the raceway into at least two separate closed secondary channels positioned within the raceway.