Patent Description:
In the aircraft industry, antennas and other components are often attached to the lower outer surfaces of aircraft wings. A cable, e.g., coaxial cable, is typically routed from each antenna or other component to inside the fuselage to a controller for communication between the corresponding antenna or other component and the controller.

Many aircraft have wings that include at least a portion of a fuel tank for fuel storage. Such aircraft wings are commonly referred to as "wet wings. " When an antenna or other component is mounted on a wet wing, for example to the mid-core section on the lower outer surface of the wing directly below the fuel tank, routing of a cable from the antenna or other component to inside the fuselage to the controller becomes more challenging.

One way to route a cable from an antenna or other component mounted on a wet wing is through the interior structure portion of the wing adj acent to the fuel tank. However, FAA regulations, specifically CFR <NUM> entitled "Fuel Tank Ignition Prevention," require testing to confirm that any new designs to the aircraft structure or system do not induce a source of ignition that could ignite a fuel component (e.g., fuel vapor and/or liquid) in and/or around the fuel tank. As such, other approaches for routing a cable from an antenna or other component mounted on a wet wing that do not require additional testing per FAA regulations would be advantageous. <CIT> relates to trunking intended to receive and conceal one or more elongated cables, pipes, conduits or the like on exposed surfaces of walls, architraves, panels or other building or architectual fittings. <CIT> is concerned with an aircraft wire fairing having an electrical wire embedded therein. <CIT> relates to a vehicle fairing including an electrical routing. <CIT> relates to harness assemblies for electrically joining various sections of high performance missile systems. <CIT> relates to raceway harness assemblies suitable for use in multi-stage rockets and missiles. <CIT> relates to a drainmast assembly for ejecting potable waste water (i.e., gray water) from an onboard potable water system of an aircraft. <CIT> relates to an apparatus for reducing aero/hydrodynamic drag on cylindrical objects.

Accordingly, it is desirable to provide apparatuses for retaining a cable, for example away from a fuel tank on a wing, of an aircraft, and aircraft and methods including such apparatuses. Furthermore, other desirable features and characteristics of the various embodiments described herein will become apparent from the subsequent detailed description and the appended claims, taken in conjunction with the accompanying drawings and this background.

Various non-limiting embodiments of a cable retainer apparatus for retaining a cable proximate a surface of an aircraft, an aircraft including such a cable retainer apparatus, and a method for retaining a cable from an antenna or other component that is disposed on a wing of an aircraft, are provided herein.

In a first non-limiting embodiment, the cable retainer apparatus includes, but is not limited to, a cable retainer having a cable channel that extends longitudinally through the cable retainer that is configured to receive and retain the cable. The cable retainer apparatus further includes, but is not limited to, a fairing that is disposed about the cable retainer. The fairing is configured to couple to the aircraft to support the cable retainer adjacent to the surface of the aircraft, and the cable retainer and fairing are cooperatively configured such that when the fairing is coupled to the aircraft, a first interference fit is defined between the cable retainer and the fairing, and a second interference fit is defined between the cable and the cable retainer.

In another non-limiting embodiment, the aircraft includes, but is not limited to, a fuselage. The aircraft further includes, but is not limited to, a wing extending outward from the fuselage and having an outer surface. The aircraft further includes, but is not limited to, an antenna or other component disposed on the wing. The aircraft further includes, but is not limited to, a cable having a proximal section extending to a distal section. The proximal section is disposed adjacent to the antenna or other component and the distal section extends towards the fuselage. The aircraft further includes, but is not limited to, a cable retainer apparatus as above that is coupled to the outer surface of the wing adjacent to the antenna or other component. The cable retainer apparatus includes, but is not limited to, a cable retainer as above that retains the proximal section of the cable. The cable retainer apparatus further includes, but is not limited to, a fairing that is coupled to the aircraft and that is disposed about the cable retainer to support the cable retainer adjacent to the outer surface of the wing.

In another non-limiting embodiment, the method includes, but is not limited to, disposing a cable retainer as above adjacent to the antenna or other component. The method further includes, but is not limited to, advancing the cable into the cable channel disposed in the cable retainer. The method further includes, but is not limited to, coupling a fairing to the wing about the cable retainer.

The following Detailed Description is merely exemplary in nature and is not intended to limit the various embodiments or the application and uses thereof. Furthermore, there is no intention to be bound by any theory presented in the preceding background or the following detailed description.

<FIG> illustrates a perspective top view of a portion of an aircraft <NUM> in accordance with an exemplary embodiment. The aircraft <NUM> includes a fuselage <NUM> as the main body of the aircraft <NUM> that supports the wings <NUM> (only one wing shown) and tail (not shown). The wings <NUM> extend outwardly (outboard direction indicated by single headed arrow <NUM> shown in <FIG>) from the fuselage <NUM>. Depending on the design of the aircraft <NUM>, the engines <NUM> (only one shown) may be attached to the wings <NUM>, or alternatively, to the fuselage <NUM>.

<FIG> illustrates a perspective bottom view of a portion of the wing <NUM> including a cable retainer apparatus <NUM> in accordance with an exemplary embodiment. Referring to <FIG>, the wing <NUM> has an upper outer surface <NUM> and a lower outer surface <NUM> opposite the upper outer surface <NUM>. The upper and lower outer surfaces <NUM> and <NUM> extend between a leading edge portion <NUM> and a trailing edge portion <NUM> of the wing <NUM>. In an exemplary embodiment, the wing <NUM> is a wet wing <NUM> that includes a wet wing portion <NUM>, which includes at least a portion of a fuel tank <NUM> disposed therein between the lower and upper outer surfaces <NUM> and <NUM> with a forward and aft perimeter of the fuel tank <NUM> defining a fuel boundary <NUM>. An antenna <NUM> is disposed on the wet wing portion <NUM> of the lower outer surface <NUM> of the wing <NUM> directly below the fuel tank <NUM>. A cable <NUM> , e.g., coaxial cable, that is coupled to the antenna <NUM> and extends therefrom. As illustrated, the cable has a proximal end section <NUM> disposed adjacent to the antenna <NUM> and extends to a distal end section <NUM> towards the fuselage <NUM>.

In an exemplary embodiment, the cable retainer apparatus <NUM> is coupled to the lower outer surface <NUM> of the wing <NUM> adjacent to the antenna <NUM> and retains the proximal end section <NUM> of the cable <NUM>. As illustrated, the cable retainer apparatus <NUM> extends between the antenna <NUM> and the leading edge portion <NUM>, which extends forward (forward direction indicated by single headed arrow <NUM>) of the wet wing portion <NUM> past the fuel boundary <NUM>, to retain and guide the cable <NUM> from the antenna <NUM> past the fuel boundary <NUM>. In an exemplary embodiment, the cable retainer apparatus <NUM> functions as a fuel barrier (e.g., additional fuel boundary) and provides retention of the proximal end section <NUM> of the cable <NUM> and further separation between the cable <NUM>, which is disposed on the exterior portion of the wing <NUM>, and the fuel tank <NUM>, which is disposed on the inside of the wing <NUM>. The distal end section <NUM> of the cable <NUM> which is disposed past both the cable retainer apparatus <NUM> and the fuel boundary <NUM> and therefore is not near the fuel tank <NUM>, may be routed through the interior structure <NUM> of the leading edge portion <NUM> of the wing <NUM> towards the fuselage <NUM>. Note, it is to be understood that although the cable retainer apparatus <NUM> is being described as retaining a cable <NUM> from an antenna <NUM> or other component to the leading edge portion <NUM> of the wing <NUM>, other embodiments may use the cable retainer apparatus <NUM> as described herein for retaining a cable <NUM> from an antenna <NUM> or other component to the trailing edge portion <NUM>.

Referring to <FIG>, in an exemplary embodiment, the cable retainer apparatus <NUM> includes a cable retainer <NUM> that retains the proximal section <NUM> of the cable <NUM>, and a fairing <NUM> (e.g., relatively rigid material, for example plastic, composite, metal or aluminum or other rigid material sheet curved or otherwise formed to fit over the cable retainer <NUM>) that is coupled to the aircraft <NUM> and disposed about the cable retainer <NUM> to support the cable retainer <NUM> adjacent to the lower outer surface <NUM> of the wing <NUM>. In an exemplary embodiment, the cable retainer <NUM> is formed of a relatively compliant or flexible material that is fuel resistant. For example, the cable retainer <NUM> may be formed of an elastomeric material for example rubber, a polymeric material, and/or a composite material. Nitrile rubber is an example of an elastomeric material that has excellent fuel resistant. In an exemplary embodiment, the cable retainer material has a hardness durometer of about or less than about <NUM> Shore A, such as from about <NUM> Shore A to about <NUM> Shore A, such as from about <NUM> Shore A to about <NUM> Shore A, for example from about <NUM> Shore A to about <NUM> Shore A.

In an exemplary embodiment, the cable retainer <NUM> has a relatively low profile aerodynamic shape so as to have minimal effect on airflow across the lower outer surface <NUM> of the wing <NUM>. In one example, the cable retainer <NUM> is an extruded or elongated body <NUM> having a cross-section with a substantially "D"-shaped outer profile <NUM> including a substantially linear section <NUM> coupled to opposing ends <NUM> and <NUM> of a substantially curved section <NUM>. As illustrated, the substantially linear section <NUM> interfaces with the lower outer surface <NUM>, e.g., outer skin surface, of the wing <NUM> of the aircraft <NUM> while the substantially curved section <NUM> interfaces with an inner surface <NUM> of the fairing <NUM>. Other relatively low profile aerodynamic cross-sectional shapes for the cable retainer <NUM> may also be used.

In an exemplary embodiment, the cable retainer <NUM> has a length of from about <NUM> to <NUM>, for example, <NUM> to <NUM>, and may be continuous monolithic piece or may be formed in sections that are abutted end to end to form the elongated body <NUM>. In an exemplary embodiment, the cable retainer <NUM> encases the proximal end section <NUM> of the cable <NUM> to shield the cable <NUM> from exposure to a fuel component, e.g., fuel leakage component, or the like.

In an exemplary embodiment, the cable retainer <NUM> has a cable channel <NUM> that retains the proximal end section <NUM> of the cable <NUM> and that extends longitudinally through the cable retainer <NUM> to route the cable <NUM> from the antenna <NUM> past the fuel boundary <NUM> to the leading edge portion <NUM> of the wing <NUM>. Opposing positive features <NUM> and <NUM> (e.g., ribs, lips, nibs or the like) are disposed adjacent to the cable channel <NUM> and are substantially elastic or flexible such that the opposing positive features <NUM> and <NUM> can be moved from a nominal position away from each other for arranging the cable <NUM> in the cable channel <NUM> and spring back or return to the nominal position to retain the cable <NUM> in the cable channel <NUM>.

As illustrated in <FIG>, to facilitate positioning the cable <NUM> into the cable channel <NUM> of the cable retainer <NUM>, a gap F is present between the opposing positive features <NUM> and <NUM> when in the nominal position. In an exemplary embodiment, the gap F is from about <NUM>,<NUM> to about <NUM>,<NUM>, for example about <NUM>.

Further and as illustrated, in an exemplary embodiment, the cable retainer <NUM> has the following dimensions A of from about <NUM> to about <NUM>, for example about <NUM>,<NUM> dimension B of greater than <NUM>,<NUM>, for example about <NUM>,<NUM> or greater, such as about <NUM>,<NUM> to about <NUM>,<NUM> to provide continuous positive separation between the cable <NUM> and the lower outer surface <NUM> of the wing <NUM> under the fuel tank <NUM>, dimension C of about <NUM>,<NUM> to <NUM>, for example from about <NUM> to about <NUM>,<NUM>, such as about <NUM>,<NUM> to provide a relatively low profile shape, and diameter E of about <NUM>,<NUM> to about <NUM>,<NUM>.

It is to be understood that the dimensions provided above are non-limiting, and other suitable dimensions (A-F) for the cable retainer <NUM> may be used without departing from various embodiments described herein.

As illustrated in <FIG>, the cable retainer <NUM> may have one or more holes <NUM> formed therein spaced apart from the cable channel <NUM>, for example to facilitate manufacturing, and/or reducing weight of the cable retainer <NUM>. The hole(s) <NUM> may be elongated in the longitudinal direction of the cable retainer <NUM>, for example as formed during an extrusion process, and may have any variety of cross-sectional shapes including a triangular or substantially triangular shape, other polygonal or substantially polygonal shape, curved or substantially curved shape, or the like. Alternatively, the cable retainer <NUM> may not have any holes formed therein spaced apart from the cable channel <NUM>.

Referring to <FIG> and <FIG>, the cable retainer <NUM> and fairing <NUM> are cooperatively configured such that when the fairing <NUM> is coupled to the aircraft <NUM>, there is an interference fit between the cable retainer <NUM> and the fairing <NUM>, for example by having the volume formed between the inner surface <NUM> of the fairing <NUM> and the corresponding portion of the lower outer surface <NUM> of the wing <NUM> being slightly less than the volume defined by the outer profile <NUM> of the cable retainer <NUM>. As such, the cable retainer <NUM> is slightly oversized relative to the volume provided by the fairing <NUM>, thereby applying a compressive force to the cable retainer <NUM> when the fairing <NUM> is coupled to the lower outer surface <NUM> of the wing <NUM> to close off the gap F between the opposing positive features <NUM> and <NUM> and forming a sealingly tight fit to prevent the cable <NUM> from being exposed to a fuel component, fuel leakage component, or the like.

Additionally, there is an interference fit between the cable <NUM> and the cable retainer <NUM>, for example by having the diameter of the cable channel <NUM> slightly less than the diameter of the cable <NUM>. In an exemplary embodiment, advantageously the interference fit between the cable <NUM> and the cable retainer <NUM> prevents the cable <NUM> from vibrating within the cable retainer <NUM>.

As illustrated, the fairing <NUM> has a curved section <NUM> that interfaces with the cable retainer <NUM> and flange sections <NUM> and <NUM> that extend outwardly in opposite directions from the curved section <NUM> and that interface with the lower outer surface <NUM> of the wing <NUM>. In an exemplary embodiment, the wing <NUM> includes a skin <NUM> having the lower outer surface <NUM> and an inner surface <NUM> that is opposite the lower outer surface <NUM>. A plurality of fasteners <NUM> extends through the flange sections <NUM> and <NUM> of the fairing <NUM> and the skin <NUM> into corresponding nut plates <NUM> to couple the fairing <NUM> to the wing <NUM>. As illustrated, the nut plates <NUM> are disposed on the inner surface <NUM> of the skin <NUM> and a fuel tank sealant <NUM> is disposed over each of the nut plates <NUM> to seal the cable retainer apparatus <NUM> from any fuel leakage from the attachment areas. Note, <FIG> illustrates an alternative design for a nut plate <NUM>.

Referring to <FIG>, a method <NUM> for retaining a cable from an antenna that is disposed on a wing of an aircraft is provided. The method includes disposing (STEP <NUM>) a cable retainer adjacent to the antenna. The cable from the antenna is advanced (STEP <NUM>) into a cable channel that is disposed in the cable retainer. In one example, the cable is advanced into the cable channel by manually pressing the cable against opposing positive features that are disposed adjacent to the cable channel to move the opposing positive features from a nominal position away from each other for arranging the cable in the cable channel. A fairing is coupled (STEP <NUM>) to the wing about the cable retainer.

Claim 1:
A cable retainer apparatus (<NUM>) configured to be coupled to an outer surface of an aircraft wing (<NUM>)
and configured to retain a cable proximate said outer surface in an aerodynamic manner, the cable retainer apparatus (<NUM>) comprising:
a cable retainer (<NUM>) having a cable channel (<NUM>) that extends longitudinally through the cable retainer (<NUM>) that is configured to receive and retain the cable (<NUM>); and
a fairing (<NUM>) disposed about the cable retainer (<NUM>) and configured to couple to the outer surface of the aircraft wing (<NUM>) to support the cable retainer (<NUM>) adjacent to the surface of the aircraft (<NUM>),
characterized in that
the cable retainer (<NUM>) and fairing (<NUM>) are cooperatively configured such that, in use, when the fairing (<NUM>) is coupled to the outer surface of the aircraft wing (<NUM>), a first interference fit is defined between the cable retainer (<NUM>) and the fairing (<NUM>), and a second interference fit is defined between the cable (<NUM>) and the cable retainer (<NUM>).