The present invention relates generally to an aircraft composite structure and more particularly to wiring integratable with an aircraft composite structure.
Composite structures include a complex material, such as graphite, in which two or more distinct, structurally complementary substances combine to produce structural or functional properties not present in any individual component. In other words, composite structures have increased strength over the individual components thereof. Generally, the component parts include a composite structure having a core material, a reinforcing material, and a resin binder. Each of these substances alone provides limited strength, but combined properly they become a strong composite structure.
In aircraft construction, composite structures often include various fiber forms and resin combinations in which the fiber form is embedded in the resin while still retaining its identity. Advanced composite airplane materials include high strength fibers embedded in an epoxy matrix. These composites provide for major weight savings in airplane structures due to high strength to weight ratios.
Currently, wiring systems are generally not “buried” within composite structures, as this could possibly lead to difficulties analyzing structural strength of the composite structure and inspection of the wiring systems.
It would therefore be highly desirable to have an aircraft composite structure system with wiring integrated into the composite material.
In accordance with one embodiment of the present invention, a wire for integration with an airplane composite structure material includes a conductive core surrounded by an isolation layer for substantially isolating the conductive core from the composite structure material. The isolation layer includes braided fibers, and the braided fibers include a material having at least substantially similar properties as the composite structure material.
In general terms, integration of two or more separate parts such as composite structures and wires, as in the present invention, may save weight and cost. The present invention may also contribute to the structural capabilities (e.g. carry load) for composite structures and thereby provide weight savings over prior wiring systems. In addition, eliminating wiring support features, such as clips and brackets, through implementation of the present invention, may add further weight savings.
Other objects and advantages of the present invention will become apparent when viewed in light of the detailed description and preferred embodiment when taken in conjunction with the attached drawings and claims.
For a complete understanding of the invention, there will now be described some embodiments thereof, given by way of example, reference being made to the accompanying drawings, in which:
The present invention is illustrated with respect to a wire 10 for integrating with a composite structure material, particularly suited to the aerospace field. The present invention is, however, applicable to various other uses that may require wiring systems, as will be understood by one skilled in the art. In each of the following figures, the same reference numerals are used to refer to the same components.
Referring to
In
In accordance with an alternate embodiment of the present invention,
The first isolation layer 16 includes braided non-conductive fibers 18, as illustrated in
The shielding layer 22 includes a shielding material, which may be the same as or similar to the material used for the conductive core 14. Through alternating the different braided layers in order to shield the inner conductive core, the wire 10 a coaxial conductor may be fabricated.
The first conductive core 14, the isolation layers 16, 24, and the shielding layers 22 may share a structural load with the composite structure material. All components of the wire 10 are also integratable with the composite structure, such that structural integrity of the composite structure is substantially constant following integration of the wire 10.
The conductors or conductive core 14 may be multi-strand wire filaments or an inter-woven combination of wire and glass. The core 14 may then be encased in an additional tube or sock (e.g. isolation layer 16) of woven glass, which acts as an insulator. Another embodiment includes surrounding the insulated core 14 in a braided metal sleeve conductor as shielding 22, which is then surrounded with a sleeve of woven glass (outer isolation layer 24 or second isolation layer). One or more of these alternating layers of conductor and insulator is treated with resin such that when the entire wire 10 is cured, it is saturated with resin and becomes an integral part of the composite structure. Further, the wire 10 can be cured such that the glass is almost transparent, such that the conductor remains visible for inspection or failure analysis.
Referring to
The housing 42 may include a filler material, such that the plurality of wires 44 is arranged similarly to those in
Referring to
Referring to
Referring to
Referring to
For installation on a cured part, resin or adhesive may be applied to the wire locally, thereby impregnating the wire. As mentioned, the assembled integrated wiring may also be infused with a resin, which may be similar to the prepreg process that is used in common composite materials, which would then be stored and handled like common prepreg material. In wet lay-up type systems, the conductor or wire may absorb resin, as may the composite structure.
As previously discussed, the materials of the present invention are compatible with airplane composite structures, and durability of the wire is tailored to aircraft weight demands.
While the invention has been described in connection with one or more embodiments, it is to be understood that the specific mechanisms and techniques which have been described are merely illustrative of the principles of the invention, numerous modifications may be made to the methods and apparatus described without departing from the spirit and scope of the invention as defined by the appended claims.
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Number | Date | Country | |
---|---|---|---|
20080115954 A1 | May 2008 | US |