Patent Description:
An aircraft cabin is provided as defined by claim <NUM>.

In some embodiments, the first threaded section and the second threaded section may be separated by at least one non-threaded section.

In some embodiments, a transition point between the head and the body may be of a non-uniform height with respect to the second end of the body.

In some embodiments, the at least one threaded section may include a single threaded section along the length of the body. The single threaded section may be configured to couple to the fitting and to the threaded nut.

In some embodiments, the at least one shaped portion with the at least one sloped wall may include a first shaped portion with a first sloped surface proximate to the tool section and a second shaped portion with a second sloped surface proximate to the body.

In some embodiments, the at least one intermediate diameter may be at a transition point between the first sloped surface and the second sloped surface.

In some embodiments, the first sloped surface may be set at a first angle relative to a central axis through a length of the body that is shallower than a second angle relative to the central axis through the length of the body at which the second sloped surface is set.

The appearances of the phrase "in some embodiments" in various places in the specification are not necessarily all referring to the same embodiment, and embodiments may include one or more of the features expressly described or inherently present herein.

<FIG> generally illustrate an aircraft monument floor attachment stud, in accordance with one or more embodiments of the disclosure.

An aircraft cabin may include one or more aircraft monuments. The aircraft monument may include floor attachment components requiring the use of hand tools during installation of the aircraft monument within the aircraft cabin.

Being installed within an aircraft cabin, the aircraft monument may be required to meet load-bearing/weight-bearing requirements set forth in aviation guidelines and/or standards without losing the intended functionality of the aircraft monument. For example, the aircraft monument may need to be configured in accordance with aviation guidelines and/or standards put forth by, but not limited to, the Federal Aviation Administration (FAA), the European Aviation Safety Agency (EASA) or any other flight certification agency or organization; the American National Standards Institute (ANSI), Aeronautical Radio, Incorporated (ARINC), or any other standards setting organization or company; the Radio Technical Commission for Aeronautics (RTCA) or any other guidelines agency or organization; or the like.

One type of floor attachment component includes a floor attachment stud requiring the use of a hex key (e.g., Allen key or Allen wrench) inserted within a hex socket set within the body of the floor attachment stud. Due to the size of the floor attachment stud, a predetermined amount of torque necessary to secure the aircraft monument and allow the aircraft monument meet aviation guidelines and/or standards, when applied with the hex key, may damage the floor attachment stud and/or the hex key.

For example, the hex socket may be stripped, with the internally-set corners being rounded until the hex key no longer engages the hex socket. By way of another example, the floor attachment stud may fail (e.g., crack, shear, or the like) proximate to a section of the wall of the floor attachment stud including the hex socket. By way of another example, the hex key may be stripped, with the externally-set corners being rounded until the hex key no longer engages the hex socket.

As such, it would be beneficial to provide an aircraft monument floor attachment stud that is less prone to failure during installation of the aircraft monument while continuing to allow the aircraft monument to continue to meet aviation guidelines and/or standards. For example, the aircraft monument floor attachment stud may include an improved mechanism in place of the hex socket requiring the use of a hex key, where the improved mechanism is still capable of accepting the amount of torque necessary to secure the aircraft monument and allow the aircraft monument to meet aviation guidelines and/or standards.

<FIG> in general illustrate an aircraft cabin <NUM> including an aircraft monument floor attachment stud <NUM>, in accordance with one or more embodiments of the disclosure. It is noted herein that the terms "aircraft monument floor attachment stud <NUM>" and variants of the term including, but not limited to, "floor attachment stud <NUM>", "attachment stud <NUM>", "floor stud <NUM>", "stud <NUM>", or the like may be considered equivalent, for purposes of the present disclosure.

Referring now to <FIG>, the aircraft cabin <NUM> may include one or more aircraft monuments <NUM>. It is noted herein the one or more attachments studs <NUM> may be considered components of the one or more aircraft monuments <NUM>, or instead components separate from the one or more aircraft monuments <NUM> (e.g., standalone components configured to interact with the one or more aircraft monuments <NUM>).

The one or more attachment studs <NUM> may pass through or be inserted into one or more corresponding openings <NUM> that are defined within an aircraft monument <NUM> of the one or more aircraft monuments <NUM>. For example, the one or more corresponding openings <NUM> may be of a limited width and/or height, such that tool access to the one or more attachment studs <NUM> may be limited to select hand tools.

The one or more attachment studs <NUM> may be inserted into one or more corresponding openings <NUM> within the aircraft monument <NUM>. The one or more openings <NUM>, <NUM> may be within one or more support structures of the aircraft monument <NUM>. For example, the one or more support structures may include, but are not limited to, one or more frames, one or more sub-frames, one or more interior or exterior décor panels, or the like.

The one or more attachment studs <NUM> may be configured to engage the aircraft monument <NUM> via one or more fasteners <NUM>. For example, the one or more fasteners <NUM> may include, but are not limited to, washers, threaded nuts, bushings, spacers, or the like.

The one or more attachment studs <NUM> may be inserted into the aircraft monument <NUM> proximate to a floor <NUM> of the aircraft cabin <NUM>. In one non-limiting example, the one or more fasteners <NUM> may include, but are not limited to, one or more washers or spacers on a floor <NUM> side of the one or more openings <NUM>, one or more bushings at least partially positioned within the one or more openings <NUM>, one or more washers or spacers on an opposite side of the one or more openings <NUM> (e.g., an opening <NUM> side), and/or one or more threaded nuts on the opposite side of the one or more openings <NUM>.

The floor <NUM> may include one or more mount points <NUM>. The one or more mount points <NUM> include one or more tracks, and may include one or more cargo tie-down components (e.g., rings, brackets, or the like) or other installed mount points configured to allow the one or more aircraft monuments <NUM> to be installed within the aircraft cabin <NUM>.

The one or more tracks <NUM> may be configured to receive one or more fittings <NUM>. A fitting <NUM> of the one or more fittings <NUM> may be configured to insert into a mount point <NUM> of the one or more mount points <NUM> at (or in) a first position <NUM> of the mount point <NUM> and be configured to lock to the mount point <NUM> at (or in) a second position <NUM> of the mount point <NUM>. For example, the fitting <NUM> may be configured to insert into the mount point <NUM> at the first position <NUM> and translate within the mount point <NUM> until it locks to the mount point <NUM> at the second position <NUM>. By way of another example, the fitting <NUM> may be configured to insert into the mount point <NUM> at the first position <NUM> and rotate within the mount point <NUM> until it locks to the mount point <NUM> in the second position <NUM>. By way of another example, the fitting <NUM> may be configured to insert into the mount point <NUM> at the first position <NUM> and both translate and rotate within the mount point <NUM> until it locks to the mount point <NUM> at and in the second position <NUM>. The one or more attachment studs <NUM> may be configured to couple to the one or more fittings <NUM>.

In one non-limiting example, the aircraft cabin <NUM> may include one or more tracks <NUM> and one or more track fittings <NUM>, where the one or more track fittings <NUM> are configured to insert to the one or more tracks <NUM> at (or in) the first position <NUM> and configured to lock to the one or more tracks <NUM> at (or in) the second position <NUM>.

While embodiments of the present disclosure illustrate the aircraft cabin <NUM> may include and/or components installed within the aircraft cabin <NUM> (e.g., the aircraft monument <NUM>, the one or more fasteners <NUM>, the floor <NUM>, the one or more mount points <NUM>, the one or more fittings <NUM>, or other components installed within the aircraft cabin <NUM>) may receive the one or more attachment studs <NUM>, it should be understood that the aircraft cabin <NUM> and/or the components installed within the aircraft cabin <NUM> may not form part of the claimed invention or design but rather is only a portion of an environment in which the claimed invention or design operates. Therefore, the above description should not be interpreted as a limitation on the scope of the present disclosure but merely an illustration.

Referring now to <FIG> and <FIG>, the attachment stud <NUM> may include a body <NUM>. For example, the body <NUM> may include an external circular or polygon cross-section with <NUM>, <NUM>, or up to an N number of sides. For instance, the body <NUM> may include, but is not limited to, a circular cross-section, a star-shaped cross section, a hexagonal cross-section, or the like.

The body <NUM> may include one or more interlocking assemblies along a length of the body <NUM>. The one or more interlocking assemblies may include threaded sections at one or more points along a length of the body <NUM>. For example, the body <NUM> may include a first threaded section <NUM> along a first portion of the length of the body and proximate to a first end <NUM> of the body <NUM>. By way of another example, the body <NUM> may include a second threaded section <NUM> along a second portion of the length of the body and proximate to a second end <NUM> of the body <NUM>. For instance, the first threaded section <NUM> may be configured to couple to a corresponding threaded section within a fitting <NUM> of the one or more fittings <NUM>, and the second threaded section <NUM> may be configured to couple to a fastener <NUM>, where the opening <NUM> of the aircraft monument <NUM> is contained between the fastener <NUM> and the fitting <NUM>. By way of another example, the body <NUM> may include a single threaded section <NUM>. For instance, the threaded section <NUM> may be configured to couple to a corresponding threaded section within a fitting <NUM> of the one or more fittings <NUM> and may be configured to couple to a fastener <NUM>, where the opening <NUM> of the aircraft monument <NUM> is contained between the fastener <NUM> and the fitting <NUM>.

For example, as illustrated in <FIG>, the body <NUM> may include one or more non-threaded sections <NUM> (e.g., smooth sections, or the like) at one or more points along the length of the body <NUM>. For instance, the body <NUM> may include one or more non-threaded sections <NUM> positioned between the first threaded section <NUM> and the second threaded section <NUM>. By way of another example, as illustrated in <FIG>, the body <NUM> may not include a non-threaded section <NUM>, and the entire body <NUM> may instead include a single threaded section <NUM>.

Although embodiments of the disclosure illustrate the body <NUM> including threaded sections <NUM>, it is noted that in examples not claimed the body <NUM> is not limited to threading but instead may include alternative interlocking assemblies (e.g., taband-groove assemblies, or the like). For example, the body <NUM> and a fitting <NUM> may include components of a shared interlocking assembly. By way of another example, the body <NUM> and a fastener <NUM> may include components of a shared interlocking assembly. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

The attachment stud <NUM> may include a head <NUM>. The head <NUM> may be integrated with or coupled to the body <NUM> at the second end <NUM> of the body <NUM>. Where the body <NUM> include the second threaded section <NUM> along the second portion of the length of the body, the second threaded section <NUM> may be proximate to the head <NUM>.

The head <NUM> may include a tool section <NUM>. The tool section <NUM> may include a hexagonal cross-section.

The tool section <NUM> may be configured to receive a tool, the tool capable of being inserted into an opening <NUM> including the attachment stud <NUM>. The tool may be capable of providing a predetermined amount of torque necessary to secure the aircraft monument <NUM> including the attachment stud <NUM> and allow the aircraft monument <NUM> to meet aviation guidelines and/or standards. For example, the tool section <NUM> may be configured to engage with a wrench (or spanner) including, but not limited to, an open-end wrench, a combination open-end and box-end wrench, a box-end wrench, an adjustable or crescent wrench, or other wrench configured to provide a predetermined amount of torque necessary to secure the aircraft monument <NUM> including the attachment stud <NUM> and allow the aircraft monument <NUM> to meet aviation guidelines and/or standards. By way of another example, the tool section <NUM> may be configured to engage with a socket (e.g., a component of a ratchet or socket wrench) configured to provide a predetermined amount of torque necessary to secure the aircraft monument <NUM> including the attachment stud <NUM> and allow the aircraft monument <NUM> to meet aviation guidelines and/or standards.

In this regard, the tool section <NUM> being raised above the body <NUM> may allow for an increased possible number of usable tools to provide torque to the attachment stud <NUM> (e.g., as opposed to an attachment stud with a hex socket set within the body).

The tool section <NUM> may include one or more tool section diameters <NUM> (e.g., a single tool section diameter <NUM> where the tool section <NUM> cross-section is circular, or multiple tool section diameters <NUM> where the tool section <NUM> cross-section is non-circular). The body <NUM> may include one or more body diameters <NUM> (e.g., a major or minor diameter of the threaded section <NUM>, a diameter of the non-threaded section <NUM>, or the like).

At least one tool section diameter <NUM> of the one or more tool section diameters <NUM> may be less than at least one body diameter <NUM> of the one or more body diameters <NUM> of the body <NUM>. To account for the difference in the tool section diameter <NUM> versus the body diameter <NUM>, the head <NUM> may include a shaped section <NUM>. In general, the shaped section <NUM> may include one or more shaped portions. The one or more shaped portions may include one or more sloped surfaces configured to provide a transition between the tool section diameter <NUM> of the tool section <NUM> and the body diameter <NUM> of the body <NUM>.

For example, the shaped section <NUM> may include a first shaped portion <NUM> with a first sloped surface <NUM> proximate to the tool section <NUM> and a second shaped portion <NUM> with a second sloped surface <NUM> proximate to the body <NUM>. For instance, the first sloped surface <NUM> may transition the head <NUM> from the tool section diameter <NUM> of the tool section <NUM> to an intermediate diameter <NUM>. In addition, the second sloped surface <NUM> may transition the head <NUM> from the intermediate diameter <NUM> to the body diameter <NUM> of the body <NUM>. In this regard, one intermediate diameter <NUM> may be considered at an intersection or a transition point between the first sloped surface <NUM> and the second sloped surface <NUM>.

Where the shaped section <NUM> includes multiple shaped portions, the multiple shaped portions may include surfaces with different slopes. For example, the first sloped surface <NUM> may be set at a shallower angle relative to a central axis through a length of the body <NUM> as compared to an angle relative to the central axis through the length of the body <NUM> at which the second sloped surface <NUM> may be set. It is noted herein, however, the multiple shaped portions may include surfaces with the same slope.

A transition point between the head <NUM> and the body <NUM> (e.g., at the end <NUM> of the body <NUM>) may include be of a non-uniform height with respect to the end <NUM> (e.g., may trace a wavy line, scalloped line, undulating line, or the like). The uneven interface may reduce or prevent the possibility of the attachment stud <NUM> failing at the head <NUM>. It is noted herein, however, that the interface between the head <NUM> and the body <NUM> may be of a uniform height with respect to the end <NUM>. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

In this regard, the shaped section <NUM> may be configured to improve torque transfer via the tool section <NUM> of the head <NUM> to the body <NUM> from the tool. The improved torque transfer may reduce or prevent the possibility of the attachment stud <NUM> failing at the head <NUM> (e.g., as opposed to an attachment stud with a hex socket set within the body).

Although embodiments of the present disclosure illustrate the shaped section <NUM> including straight-line portions, it is noted herein the shaped section <NUM> may include one or more convex or concave-line portions to further reduce or prevent the possibility of a corner within the head <NUM> that may result in an increased chance of failure of the attachment stud <NUM> when torque is transferred via the tool section <NUM> of the head <NUM> to the body <NUM> from the tool.

The end <NUM> of the body <NUM> may include an edge-forming surface <NUM>. For example, the edge-forming surface <NUM> may include a chamfer, fillet, bevel, or other edge-forming surface. The edge-forming surface <NUM> may reduce or prevent the possibility of failure (e.g., when the attachment stud <NUM> is inserted into a particular opening <NUM> and/or a particular opening <NUM>, when the attachment stud <NUM> engages a fitting <NUM>, or the like). In this regard, the body <NUM> may include multiple body diameters <NUM> (e.g., one or more main body diameters <NUM> and a reduced body diameter <NUM> at the end <NUM> of the body <NUM>).

The attachment stud <NUM> may be fabricated through any manufacturing process known in the art. The body <NUM> and/or the head <NUM> may be machined in a fully heat-treated condition. Sharp edges may be deburred. The threaded section <NUM> may be formed through one or more rolling processes. For example, the threaded section <NUM> may be formed through a single continuous process. For instance, the threaded section <NUM> may be a right-hand threading. By way of another example, the threaded section <NUM> may be formed after the heat treatment and machining of the body <NUM> and/or the head <NUM>. By way of another example, a threaded section <NUM> runout may include a progressive and regular junction avoiding sharp changes. For instance, a threaded section <NUM> lead and/or the threaded section <NUM> runout may be configured to meet guidelines and/or standards as set forth in Clause <NUM> of International Organization for Standardization (ISO) <NUM><NUM>:<NUM>.

The attachment stud <NUM> may be fabricated to one or more specifications. In one or more non-limiting examples, the specifications may include, but are not limited to, a <NUM> depth x <NUM>/<NUM>-inch (") <NUM> UNJF-3A thread, a <NUM> depth x <NUM>/<NUM>" - <NUM> UNJF-3A thread, or a <NUM> x <NUM>° chamfer.

The attachment stud <NUM> may be fabricated to meet one or more tolerances. In one or more non-limiting examples, the tolerances may include, but are not limited to, at least one of linear dimensions ranging between +/- <NUM> millimeter (mm), angular dimensions ranging between +/- <NUM> degrees (°), drilled holes ranging from +/- <NUM>, a corner radius ranging between +/- <NUM>, a surface finish ranging from +/- <NUM> micrometer (µm), a flatness of <NUM> per <NUM>, or an internal bend radius ranging between +/- <NUM>.

It is noted herein the one or more fabrication processes, the one or more specifications, and/or the one or more tolerances as provided in the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

In this regard, the aircraft monument floor attachment stud <NUM> is less prone to failure during installation of the aircraft monument <NUM> while continuing to allow the aircraft monument <NUM> to continue to meet aviation guidelines and/or standards. For example, the aircraft monument floor attachment stud <NUM> may include the tool section <NUM> of the head <NUM>, where the tool section <NUM> of the head <NUM> is capable of accepting the amount of torque necessary to secure the aircraft monument <NUM> and allow the aircraft monument <NUM> to meet aviation guidelines and/or standards.

Although embodiments of the disclosure are directed to an aviation environment such as an aircraft cabin <NUM>, it is noted herein the aircraft monument floor attachment stud <NUM> is not limited to the aviation environment and/or the aircraft components within the aviation environment. For example, the aircraft monument floor attachment stud <NUM> may be configured for any type of vehicle known in the art. For example, the vehicle may be any air, space, land, or water-based personal equipment or vehicle; any air, space, land, or water-based commercial equipment or vehicle; any air, space, land, or water-based military equipment or vehicle known in the art. By way of another example, the aircraft monument floor attachment stud <NUM> may be configured for commercial or industrial use in either a home or a business. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

Claim 1:
An aircraft cabin (<NUM>) comprising:
a floor (<NUM>) including a track (<NUM>),
an aircraft monument (<NUM>) including an opening (<NUM>) defined within a support structure of the aircraft monument;
a fitting (<NUM>) inserted within and locked to the track;
one or more fasteners (<NUM>) including a threaded nut;
a floor attachment stud (<NUM>) engaged to the aircraft monument by the one or more fasteners and coupled to the fitting, comprising:
a body (<NUM>) disposed within the opening of the aircraft monument and including a first threaded section (<NUM>) and a second threaded section (<NUM>) each including at least one body diameter, the first threaded section disposed at a first end of the body by which the body is coupled to the fitting (<NUM>), the second threaded section disposed at a second end of the body by which the body is coupled to the threaded nut; and
a head (<NUM>) integrated with the body at the second end, the head comprising:
a tool section (<NUM>) including an external hexagonal cross-section and at least one tool section diameter (<NUM>), the at least one section diameter being less than the at least one body diameter, the tool section being configured to receive a predetermined amount of torque from a tool by the external hexagonal cross-section to secure the aircraft monument to the fitting; and
a shaped section (<NUM>) including at least one intermediate diameter (<NUM>), the shaped section including at least one shaped portion with at least one sloped wall, the shaped section being configured to provide a transition between the at least one tool section diameter of the tool section and the at least one body diameter of the body, the at least one intermediate diameter being greater than the at least one tool section diameter, the at least one intermediate diameter being less than the at least one body diameter;
wherein the fitting is positioned on a floor side of the opening and the threaded nut is positioned on an opposite side of the opening.