Aircraft seatback cover attachment system

A seatback cover attachment system is disclosed. The attachment system may include a substrate configured to reversibly couple to a portion of a seatback frame. The substrate may include one or more surfaces that define a channel. The channel may be configured to receive a portion of the seatback frame. The attachment system may include a seatback cover sub-system. The seatback cover sub-system may include a dress cover. The seatback cover sub-system may include a side panel configured to couple to a portion of the substrate. The side panel may be configured to couple to one or more portions of the dress cover to form the seatback cover sub-system.

BACKGROUND

Seats may include components such as a seatback cover, a seatback cushion, and seatback support system. Additionally, in some designs, the seats may include additional components such as a seat pan cover, a seat pan cushion, and a seat pan support system. The components may be coupled together with one or more attachment assemblies. In addition, in select industries the build of the seat (and any included components within the build) may be required to meet guidelines and/or standards.

SUMMARY

A seatback cover attachment system is disclosed, in accordance with one or more embodiments of the present disclosure. In one embodiment, the attachment system includes a substrate, the substrate configured to reversibly couple to a portion of a seatback frame, the substrate including one or more surfaces that define a channel, the channel configured to receive a portion of the seatback frame. In another embodiment, the attachment system includes a seatback cover sub-system, the seatback cover sub-system. In another embodiment, the seatback cover sub-system includes a dress cover. In another embodiment, the seatback cover sub-system includes a side panel, the side panel configured to couple to a portion of the substrate, the side panel configured to couple to one or more portions of the dress cover to form the seatback cover sub-system.

In some embodiments, the attachment system may include one or more seams to join the side panel directly to a portion of the substrate.

In some embodiments, the substrate may include a lowered portion and a raised portion on a surface of the substrate.

In some embodiments, the raised portion may be dimensioned to obscure the one or more seams.

In some embodiments, the attachment system may include one or more seams to join the side panel to a portion of the dress cover.

In some embodiments, the dress cover may include a seatback cover layer and a seatback cushion layer, the seatback cushion layer being integrated with the seatback cover layer.

In some embodiments, the substrate may include one or more seatback frame mount cut outs configured to conform to one or more seatback frame mounts of the seatback frame.

In some embodiments, the attachment system may further include one or more flaps including one or more fastening assemblies configured to visually hide the one or more seatback frame mounts.

In some embodiments, the substrate may be formed of a thermoformed plastic or laminated fiberglass.

An aircraft seat is disclosed, in accordance with one or more embodiments of the present disclosure. In one embodiment, the aircraft seat includes a support system including a seatback frame and a seat pan frame. In another embodiment, the aircraft seat includes a seat pan cover including at least one surface configured to conform to a corresponding surface of the support system. In another embodiment, the aircraft seat includes a seatback cover attachment system. In another embodiment, the attachment system includes a substrate, the substrate configured to reversibly couple to a portion of the seatback frame, the substrate including one or more surfaces that define a channel, the channel configured to receive a portion of the seatback frame. In another embodiment, the attachment system includes a seatback cover sub-system, the seatback cover sub-system. In another embodiment, the seatback cover sub-system includes a dress cover. In another embodiment, the seatback cover sub-system includes a side panel, the side panel configured to couple to a portion of the substrate, the side panel configured to couple to one or more portions of the dress cover to form the seatback cover sub-system. In another embodiment, the seatback cover attachment system is configured to secure the seatback cover sub-system to the seatback frame via the substrate.

In some embodiments, the seatback frame may be configured to fit within the channel of the seatback cover attachment system.

In some embodiments, the seatback frame may be configured be inserted in the channel of the seatback cover attachment system.

In some embodiments, the seatback frame may be configured to engage with the substrate via a force applied in a direction downward from the channel of the seatback cover attachment system.

In some embodiments, the seatback frame may be configured to disengage from the substrate via a force applied in a direction upward from the channel of the seatback cover attachment system.

In some embodiments, the substrate and the side panel may at least partially overlap to prevent a seatback diaphragm of the seatback frame from cutting into a portion of the side panel.

DETAILED DESCRIPTION OF THE INVENTION

FIGS. 1-8in general illustrate an aircraft seatback cover attachment system, in accordance with one or more embodiments of the disclosure.

Seats may include some combination of components such as, but not limited to, a seat pan cover, a seatback cover, a seat pan cushion, a seatback cushion, a seat pan support system, and a seatback support system. In select seat designs, the seatback cover alone may be composed of numerous pieces, where each piece is then coupled together to form the seatback cover. After the individual components are assembled, the seat components may be coupled together with one or more attachment assemblies to form the aircraft seat.

These methods of manufacture and attachment may require extensive assembly and installation time. For example, these methods may require thirty minutes of assembly time and approximately twenty minutes of installation time. In addition, these methods may cause difficulties during alignment and/or an indeterminateness in the alignment of the seatback cover, cushion, and/or support system during manufacturing and/or installation of the aircraft seat. Further, the methods may result in increased cost in manufacturing and/or installation.

The seatback cover may be subjected to stress, strain, dirt or other mess such as airsickness, contraband, or the like resulting in damage of the seatback cover. After a period of time and/or a particular type of wear factor occurring, the seatback cover may be removed for cleaning and/or replacement. Removing and re-installing the seatback cover may require a method that is quick, inexpensive, and not labor intensive. For example, the seatback cover attachment system should be quickly dismantled and put together without incurring considerable labor costs.

In addition, in select industries the build of the seat (and any included components within the build) may be required to meet guidelines and/or standards. For example, aircraft seats may be required to meet aviation guidelines and/or standards. For instance, the select aircraft seats 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. Seatback cover attachment systems may present difficulties such as, but not limited to, failing to meet load requirements (e.g., 9 g static load requirements or 16 g dynamic load requirements), burn requirements, or the like as set forth by the FAA in 14 C.F.R. Part 25, AIRWORTHINESS STANDARDS: TRANSPORT CATEGORY AIRPLANES).

As such, it would be desirable to provide a seatback cover attachment system. The seatback cover attachment system should reduce the number of parts, allowing for more efficient removal and installation of the seatback cover. For example, the seatback cover attachment system may include an integrated seatback cover and cushion sub-system to eliminate the need for an additional seatback cushion component. The seatback cover attachment system should be inexpensive to implement, whether on a retrofitted aircraft seat or in a new aircraft seat design. The seatback cover attachment system should reduce the amount of seatback frame finishing steps. The seatback cover attachment system should be configured in accordance with aviation guidelines and/or standards.

Referring in general toFIGS. 1-6D, one or more seatback cover attachment systems may be integrated within an aircraft seat100installed within an aircraft cabin. For example, the aircraft seat100may include, but is not limited to, a business class or first-class passenger seat, an economy-class passenger seat, a crew member seat, or the like. It is noted herein the terms “aircraft seats” and “passenger seats” may be considered equivalent, for purposes of the disclosure.

The aircraft seat100may be rotatable about an axis (e.g., swivelable). The aircraft seat100may be fully positionable between the outer limits of motion as defined by the moveable components of the aircraft seat100. Where the aircraft seat100is installed within a passenger compartment, the aircraft seat100may be fully positionable between the outer limits of motion as defined by one or more passenger compartment monuments of the passenger compartment. It is noted herein an upright or raised position may be considered a taxi, takeoff, or landing (TTL) position during select stages of flight (though the upright or raised position is not limited to use during the select stages of flight as the TTL position, but also may be used at any point during the flight), for purposes of the present disclosure. In addition, it is noted herein that any position that does not meet the above-defined requirements of the TTL position may be considered a non-TTL position, for purposes of the present disclosure. Further, it is noted herein the aircraft seat100may be actuatable (e.g., translatable and/or rotatable) from the TTL position to a non-TTL position, and/or vice versa. Further, it is noted herein the aircraft seat100may be capable of a fully upright or raised position, and that the TTL position may have a more reclined seatback cushion and a more angled upward seat pan cushion as compared to the fully upright or raised position. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

In general, an aircraft seat100may be translatable (e.g., trackable or slidable). The aircraft seat100may be rotatable about an axis cross-wise through the aircraft seat100into a position including, but not limited to, the upright or raised position, one or more lounge or reclined positions, and a lie-flat or bed position. For example, the aircraft seat100may transition directly between the upright or raised position and the lie-flat or bed position. By way of another example, it is noted herein the aircraft seat100may transition through one or more lounge or reclined positions between the upright or raised position and the lie-flat or bed position. By way of another example, the aircraft seat100may transition into one or more lounge or reclined positions in a motion separate from the transition between the upright or raised position and the lie-flat or bed position. Therefore, the above description should not be interpreted as a limitation on the scope of the disclosure but merely an illustration.

The aircraft seat100may include a support system102. The support system102may be a rigid structure within the aircraft seat100, such that the support system102does not move. The support system102may include one or more movable components such that the support system102may articulate. For example, the support system102may articulate when the aircraft seat100actuates between the upright or raised position, the one or more lounge or reclined positions, and/or the lie-flat or bed position.

The support system102may include a seat pan103. The aircraft seat100may include a seat pan cushion104. The aircraft seat100may include a seat pan frame106including one or more seat pan frame elements108. For example, one or more seat pan frame elements108may include, but are not limited to, seat pan structural hoops. The seat pan frame106including the one or more seat pan frame elements108may form a portion of an exterior boundary of the seat pan of the aircraft seat100. AlthoughFIG. 1depicts the support system102including a seat pan cushion, seat pan frame, seat pan elements, seat pan diaphragm, seat pan cover, and the like, it is noted herein the support system102may not include one or more of the following: a seat pan cushion, seat pan frame, seat pan elements, seat pan diaphragm, seat pan cover, and the like. Therefore,FIG. 1and the related discussion should not be construed as limiting the scope of the present disclosure.

The support system102may include a seat pan diaphragm110. The seat pan diaphragm110may include any type of diaphragm including, but not limited to, a plastic diaphragm, a metal diaphragm, a fabric diaphragm, a wire or wireframe diaphragm, or the like.

The seat pan cushion104may conform or substantially conform to the support system102. For example, at least one surface of the seat pan cushion104may conform to a corresponding surface of the support system102. By way of another example, components of the support system102(e.g., components including, but not limited to, straps configured to couple the diaphragm110to the seat pan frame106with the one or more seat pan frame elements108, where the support system102is or includes the diaphragm110) may extend beyond the boundaries of the cushion104, such that the at least one surface of the cushion104does not fully conform to the corresponding surface of the support system102. By way of another example, a portion of the cushion104may wrap around or otherwise enclose a portion of the support system102(e.g., including, but not limited to, a front edge or leading portion of the cushion104). In general, the support system102may conform to a portion of a user (e.g., a passenger, a crew member, or the like), and the cushion104may similarly conform to the portion of the user due to the cushion104conforming to the support system102.

The aircraft seat100may include a seat pan cover112. The seat pan cover112may be configured to fit over at least a portion of the seat pan cushion104. For example, the seat pan cover112may be configured to wrap around or otherwise enclose exterior surfaces of the seat pan cushion104not proximate to the support system102. The seat pan cover112may be configured to attach to the support system102and/or the cushion104. It is noted herein “seat cover” and “dress cover” may be considered equivalent, for purposes of the disclosure.

The support system102may include a seatback113. The aircraft seat100may include a seatback frame114including one or more seatback frame elements116. For example, one or more seatback frame elements116may include, but are not limited to, seatback structural hoops. The seatback frame114including the one or more seatback frame elements116may form a portion of an exterior boundary of the seatback of the aircraft seat100.

The support system102may include a seatback diaphragm118. The diaphragm118may include any type of diaphragm including, but not limited to, a plastic diaphragm, a metal diaphragm, a fabric diaphragm, a wire or wireframe diaphragm, or the like.

The aircraft seat100may include a seatback attachment cover system120. The seatback attachment system120may be configured to fit over at least a portion of the seatback frame114.

FIGS. 2A-6Dillustrate components of a seatback cover attachment system120, in accordance with one or more embodiments of the disclosure.FIG. 7is a method or process700for installing the seatback cover attachment system120on the aircraft seat100, in accordance with one or more embodiments of the disclosure.FIG. 8is a method or process800for uninstalling the seatback cover attachment system120from the aircraft seat100, in accordance with one or more embodiments of the disclosure. It is noted herein “seatback cover attachment system” and variants including, but not limited to, “attachment system” or “system” may be considered equivalent, for purposes of the disclosure.

The attachment system120may include a substrate202. For example, the attachment system120may include a substrate202configured to attach to a portion of the one or more seatback frame elements116. The substrate202may include one or more surfaces204that define a channel206. For example, the channel206may be configured to receive a portion of the one or more seatback frame elements116of the seatback frame114. For instance, the channel206may include a cross-section shaped to receive and/or conform to a portion of the seatback frame114. As shown inFIG. 3A, the channel206may be a “J-channel”. Further, the channel206may be a “C-channel”. Further, the channel206may be a “L-channel”. In general, the channel may include a cross-section having any shape configured to receive and/or conform to a portion of the seatback frame114.

When attached to the seatback frame114, the substrate202may substantially enclose the seatback frame114, such that only a portion of the seatback frame114may be visible when fully assembled. In this regard, the one or more surfaces204of the substrate202may be configured to hide various manufacturing imperfections in the seatback frame114. Further, the substrate202may be configured to reduce seatback frame finishing steps.

The substrate202may be formed of any material. For example, the substrate202may be formed of a thermoformed plastic including, but not limited to, acrylic-polyvinyl chloride, polyethylene terephthalate (PET), polystyrene (HIPS), high-density polyethylene (HDPE), polyvinyl chloride (PVC), polyethylene terephthalate glycol-modified (PETG), or the like. By way of another example, the substrate202may be formed of laminated fiberglass. In general, the substrate202may be configured to be formed from any material (e.g., plastic, metal, or the like) configured to meet aviation guidelines and/or standards (e.g., for load-bearing requirements, burn requirements, or the like).

The seatback cover attachment system120may include an integrated seatback cover and cushion sub-system208. It is noted herein “integrated seatback cover and cushion sub-system” and variants including, but not limited to, “integrated cover and cushion sub-system” or “sub-system” may be considered equivalent, for purposes of the disclosure.

The integrated cover and cushion sub-system208may include a dress cover210. It is noted herein the dress cover210may conform to a portion of a user (e.g., a passenger, a crew member, or the like), or may be independently-shaped.

The dress cover210may include a seatback cover layer212. The seatback cover layer212may be formed of any material known in the art including, but not limited to, leather, synthetic leather, fabric, or the like.

The dress cover210may include a seatback cushion layer214. The seatback cushion layer214may be formed of any material known in the art including, but not limited to, foam, or the like.

The seatback cushion layer214may be integrated with the seatback cover layer212of the dress cover210. For example, the dress cover210may be formed of a laminated piece of material integrated with a cushion backing (e.g., a foam backed fabric). It is noted that the seatback cushion layer214may be integrated with the seatback cover layer212via any fabrication process (e.g., sewing, or the like) or fastening mechanism (e.g., an adhesive, or the like). In this regard, the seatback cover attachment system120may include an integrated seatback cover and cushion assembly to eliminate the need for an additional seatback cushion component, thereby reducing the assembly time by reducing the number of seatback component parts.

Although embodiments of the disclosure illustrate the dress cover210including a seatback cushion layer214, it is noted herein the seatback cushion layer214may be separate from the dress cover210(e.g., where a cushion layer is separately installed on the aircraft seat100) and/or the seatback cushion layer214may not be installed on the aircraft seat100). Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

The integrated cover and cushion sub-system208may include a side panel216. The side panel216may be formed of a piece of wrapped fabric218.

The side panel216may be coupled to one or more portions of the dress cover210via one or more attachment mechanisms formed via one or more fabrication processes to form the integrated cover and cushion sub-system208. For example, the side panel216may be coupled to one or more portions of the dress cover210via one or more seams219generated via one or more sewing processes.

The side panel216may be coupled to one or more portions of the substrate202. For example, the side panel216may be coupled to a portion of the substrate202via one or more seams219. In this regard, a first end of the side panel216may be sewn directly onto a surface204of the substrate202via a first seam219a. It is noted that this single seam coupling mechanism may be configured to allow for efficient assembly to reduce assembly time.

AlthoughFIGS. 3A-3Bdepict the side panel216coupled to the top surface of the substrate202, it is noted that the side panel216may be coupled to any surface of the substrate202. For example, the side panel216may be coupled to a side surface of the substrate202. By way of another example, the side panel216may be coupled to a bottom surface of the substrate202.

In one non-limiting example, the attachment system120may be formed of three parts (e.g., substrate202, dress cover210, and side panel216), where the three parts may be coupled together to form the attachment system120. The attachment system120may include one or more seams joining the three parts. For example, the attachment system120may include a first seam219ajoining the dress cover210and the side panel216. By way of another example, the attachment system120may include a second seam219bjoining the side panel216and the substrate202. It is noted herein, however, the attachment system120may include any number of seams219. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

The substrate202may include a contoured surface including a lowered portion300and a raised portion302on a surface204of the substrate202. The fabric218of the dress cover210may be configured to attached to the lowered portion300via one or more attachment mechanisms (e.g., one or more seams219, or the like) generated by one or more fabrication processes (e.g., one or more sewing processes, or the like). The raised portion302may be dimensioned to obscure the one or more seams219from a rear view of the aircraft seat100. For example, the height of the raised portion302may be greater than or equal to the thickness of the fabric218of the side panel216to obscure the seam219.

Although embodiments of the disclosure illustrate the one or more fabrication processes including one or more sewing processes to join together dress cover210, the side panel216, and the substrate202at one or more seams219, it is noted herein the one or more fabrication processes are not limited to one or more sewing processes. For example, the dress cover210, the side panel216, and the substrate202may be joined together by mechanical fasteners including, but not limited to, zippers, hook-and-loop fasteners, rivets, and the like. By way of another example, the dress cover210, the side panel216, and the substrate202may be joined together by bonding agents including, but not limited to, adhesives, or the like. Therefore, the above description should not be interpreted as a limitation on the present disclosure but merely an illustration.

Referring toFIG. 4, the attachment system120may be configured to receive one or more seatback frame mounts. For example, the substrate202may include one or more seatback frame cut outs400configured to conform to one or more seatback frame mounts. In this regard, the one or more seatback frame cuts outs400may be configured to slide past the one or more seatback frame mounts, without interfering with the substrate202, when the seatback frame114is inserted in the channel206of the substrate202.

The attachment system120may include one or more side panel flaps402configured to visually hide the one or more seatback frame mounts and the one or more seatback frame cut outs400. The one or more side panel flaps402may be coupled to the substrate202via one or more fastening assemblies404. For example, the one or more side panel flaps402may include a snap406and the substrate202may include a receiving snap408. In this regard, the one or more side panel flaps402may be coupled to the substrate202by fastening the snap406to the receiving snap408. By way of another example, the one or more side panel flaps402may include a hook and loop fastening assembly including a loop portion coupled to the flap402and a hook portion coupled to the substrate202. In this regard, the one or more side panel flaps402may be coupled to the substrate202by fastening the hook portion of the substrate202to the loop portion of the flap402.

Installing an aircraft seatback using the seatback cover attachment system120may include one or more of the following steps of the method or process700:

In a step702, the seatback frame114may be inserted into a portion of the attachment system120. For example, a portion of the one or more seatback frame elements116may be inserted at an angle502into the channel206of the substrate202.

In a step704, a force may be applied to engage the seatback frame114with the channel206until the attachment system120interlocks with the seatback frame114. For example, the force may be applied through an application of force on the attachment system120in a specific direction until the attachment system120interlocks with the seatback frame114. For instance, the force may be applied in a downward direction from the channel206of the substrate202. In this regard, the force may be applied to engage the seatback frame114with the channel206until the substrate202snaps into place.

Referring toFIGS. 3C-3D, when the attachment system120engages with the seatback frame114, the attachment system120may be configured to prevent the diaphragm118from cutting into the side panel216. For example, the substrate202may be coupled to the side panel216such that a portion of the substrate202overlaps with a portion of the side panel216. In this regard, the substrate202of the overlap is configured to prevent the diaphragm118from cutting into the side panel. In this regard, the attachment system120may be easily installed without removing the diaphragm118and/or damaging the diaphragm118.

The attachment system120may interlock with the seatback frame114when a specific amount of force is applied. For example, the force may cause the substrate202to flex into place to cause the attachment system120to interlock with the seatback frame114. In this regard, the attachment system120does not require an additional interlocking assembly to secure the attachment system120with seatback frame114.

In an optional step706, one or more side panel flaps may be coupled to a portion of the substrate202via one or more fastening assemblies. For example, as shown inFIGS. 4, 6A-6D, the attachment system120may include one or more side panel flaps402configured to visually hide the one or more seatback frame mounts and the one or more seatback frame cut outs400. The one or more side panel flaps402may be coupled to the substrate202via one or more fastening assemblies404. For example, the one or more side panel flaps402may include a snap406and the substrate202may include a receiving snap408. In this regard, the one or more side panel flaps402may be coupled to the substrate202by fastening the snap406to the receiving snap408. By way of another example, the one or more side panel flaps402may include a hook and loop fastening assembly including a loop portion coupled to the flap402and a hook portion coupled to the substrate202. In this regard, the one or more side panel flaps402may be coupled to the substrate202by fastening the hook portion of the substrate202to the loop portion of the flap402.

Removing the attachment system120may include one or more of the following steps of the method or process800:

In an optional step802, one or more side panel flaps may be un-coupled from a portion of the substrate202via one or more fastening assemblies. For example, as shown inFIGS. 4, 6A-6E, the attachment system120may include one or more side panel flaps402configured to visually hide the one or more seatback frame mounts and the one or more seatback frame cut outs400. The one or more side panel flaps402may be coupled to the substrate202via one or more fastening assemblies404when assembling the seat100. The one or more side panel flaps402may then be un-coupled from the substrate202via the one or more fastening assemblies404when disassembling the seat100. For example, the one or more side panel flaps402may include a snap406and the substrate202may include a receiving snap408. In this regard, the one or more side panel flaps402may be coupled to the substrate202by fastening the snap406to the receiving snap408and later un-coupled via the snap406and receiving snap408. By way of another example, the one or more side panel flaps402may include a hook and loop fastening assembly including a loop portion coupled to the flap402and a hook portion coupled to the substrate202and then later un-coupled via the hook and loop fastening assembly.

In a step804, a force may be applied to disengage the seatback frame114and the channel206. For example, the force may be applied through an application of force on the attachment system120in a specific direction to cause the attachment system120to disengage from the seatback frame114. For instance, the force may be applied through an application of force in an upward direction from the channel206of the substrate202. In this regard, the force may be applied to disengage the seatback frame114from the channel206until the substrate202un-snaps from the seatback frame114.

Referring toFIGS. 3C-3D, when the attachment system120disengages with the seatback frame114, the attachment system120may be configured to prevent the diaphragm118from cutting into the side panel216. For example, the substrate202may be coupled to the side panel216such that a portion of the substrate202overlaps with a portion of the side panel216. In this regard, the substrate202of the overlap is configured to prevent the diaphragm118from cutting into the side panel. In this regard, the attachment system120may be easily removed without removing the diaphragm118and/or damaging the diaphragm118.

In a step806, the seatback frame114may be removed from the channel of the substrate. For example, the seatback frame elements116of the seatback frame114may be removed from the channel206of the substrate202when the attachment system is fully disengaged with the frame114.

It is noted herein the methods or processes700,800is not limited to the steps and/or sub-steps provided. The methods or processes700,800may include more or fewer steps and/or sub-steps. In addition, the methods or processes700,800may perform the steps and/or sub-steps simultaneously. Further, the methods or processes700,800may perform the steps and/or sub-steps sequentially, including in the order provided or an order other than provided. Therefore, the above description should not be interpreted as a limitation on the scope of the disclosure but merely an illustration.

Although embodiments of the disclosure illustrate coupling or uncoupling various components of the attachment system120from above as illustrated in at leastFIGS. 5A-6D, it is noted herein various component of the attachment system120may be coupled or uncoupled from a front or rear direction with enough applied force. Therefore, the above description should not be interpreted as a limitation on the scope of the disclosure but merely an illustration.

It is noted herein the seatback cover attachment system120may be configured to work with any aircraft seat100and/or any set of components in the aircraft seat100. For example, the seatback cover attachment system120may be configured to take into account any changes in shape of the components of the aircraft seat100(e.g., within an x-y plane forming a seating surface for an occupant), where the changes in shape may be caused by or otherwise dependent on the location of the aircraft seat100within the aircraft cabin.

Although embodiments of the disclosure illustrate the seatback cover attachment system120being integrated within the aircraft seat100, it is noted herein, however, that the seatback cover attachment system120and/or components of the seatback cover attachment system120are not limited to the aviation environment and/or the aircraft components within the aviation environment. For example, the seatback cover attachment system120and/or components of the seatback cover attachment system120may be configured for any type of vehicle known in the art. For instance, 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 seatback cover attachment system120and/or components of the seatback cover attachment system120may 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.