| 摘要 |
A particular method includes exposing a plurality of fibers of a composite skin of an aircraft component by providing an opening in a layer of a first resin overlaying the plurality of fibers at an interior surface of the composite skin. The method also includes bonding a conductive patch in electrical contact with the plurality of fibers of the composite skin at the opening using a second resin. The method further includes preparing the aircraft component to receive a connector in electrical contact with the conductive patch. |
