Decorative cover pull-tab retention system

Abstract

The present invention relates to a retention system for an aircraft seat cover that defines a sewn cable channel around the perimeter of a back portion. A cable is tightened in the cable channel to tighten the aircraft seat cover around the back of the aircraft seat. Adjustable buckles at the ends of the cable interlock and allow the cable to be tightened. Midpoint straps are provided on opposite sides of the perimeter to allow the aircraft seat cover to fit more completely to the structure of the aircraft seat.

Description

[0001] Priority

[0002] This application claims the benefit of U.S. Provisional Application No. 62 / 992,572 (filed March 20, 2020), which is incorporated herein by reference. TECHNICAL FIELD

[0003] The present invention relates to aircraft seats and aircraft seat covers, and more particularly to a retention system for an aircraft seat cover. BACKGROUND

[0004] Existing aircraft seat covers are difficult to install and require specialized tools. Aircraft seats often have a unique profile that requires a seat cover to be specially manufactured. Loosely fitted or poorly attached seat covers can pull out or detach from the aircraft seat.

[0005] It would be advantageous to have an aircraft seat cover that is easy to install, can be secured to the seat back frame to prevent pulling out, and can be used on different types of aircraft seats. SUMMARY

[0006] In one aspect, embodiments of the inventive concept disclosed herein relate to a retention system for an aircraft seat cover. The aircraft seat cover defines a cable channel sewn around a perimeter of a back portion. A cable in the cable channel is tightened to tighten the aircraft seat cover around the aircraft seat back. Adjustable buckles at the ends of the cable interlock and allow the cable to be tightened.

[0007] In another aspect, a midpoint strap is disposed on opposite sides of the perimeter. The midpoint strap enables the aircraft seat cover to more completely conform to the structure of the aircraft seat.

[0008] It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the scope of the claims. The accompanying drawings, which are incorporated in and constitute a part of the specification, illustrate exemplary embodiments of the inventive concept disclosed herein and, together with the general description, serve to explain principles. BRIEF DESCRIPTION OF DRAWINGS

[0009] The numerous advantages of embodiments of the inventive concept disclosed herein can be better understood by reference to the drawings, in which:

[0010] Figure 1 An environmental view of an aircraft seat for implementing exemplary embodiments is shown;

[0011] Figure 2 A perspective environmental view of an aircraft seat cover according to exemplary embodiments is shown;

[0012] Figure 3A perspective view and detail view of an aircraft seat trim cover is shown in accordance with an example embodiment;

[0013] Figure 4 A perspective view of an aircraft seat trim cover is shown in accordance with an example embodiment;

[0014] Figure 5 A detailed cross-sectional view of a cable channel in an aircraft seat trim cover is shown in accordance with an example embodiment. DETAILED DESCRIPTION

[0015] Before one or more embodiments of the inventive concepts disclosed herein are explained in detail, it is to be understood that the inventive concepts disclosed herein are not limited in their application to the details of construction and the arrangement of components or steps or methods set forth in the following detailed description or illustrated in the accompanying drawings. In the following detailed description of embodiments of the inventive concepts, numerous specific details are set forth in order to provide a more thorough understanding of the inventive concepts. However, it will be apparent to one of ordinary skill in the art in view of this disclosure that the inventive concepts disclosed herein can be practiced without these specific details. In other instances, well-known features can not be described in detail to avoid unnecessarily complicating the disclosure. The inventive concepts disclosed herein are capable of other embodiments or of being practiced or carried out in various ways. Also, it is to be understood that the phraseology and terminology employed herein are for the purpose of description and should not be regarded as limiting.

[0016] As used herein, letters following reference numerals are intended to denote embodiments of a feature or element that can be similar to but not necessarily identical to elements or features previously described with the same reference numeral (e.g., 1, 1a, 1b). Such shorthand notations are used for convenience purposes only and should not be interpreted to limit the inventive concepts disclosed herein in any way, unless expressly so indicated.

[0017] Further, unless expressly stated to the contrary, “or” means an inclusive “or” and not an exclusive “or”. For example, any of the following conditions satisfy the condition A or B: A is true (or exists) and B is false (or does not exist), A is false (or does not exist) and B is true (or exists), and both A and B are true (or exist).

[0018] Additionally, elements and components of the embodiments of the inventive concepts are described herein using general terms and symbols wherein the terms and symbols are generally used in a manner to convey their ordinary meanings in the art. The use of certain terms and symbols is not intended to limit the scope of the inventive concepts disclosed herein unless explicitly so stated.

[0019] Finally, as used herein, any reference to "one embodiment" or "some embodiments" means that a particular element, feature, structure or characteristic described in connection with the embodiment is included in at least one embodiment of the inventive concepts disclosed herein. The appearances of the phrase "in some embodiments" in various places in the specification are not necessarily all referring to the same embodiment, and the inventive concepts disclosed herein can include embodiments having none, some or all of the attributes described in conjunction with any other such embodiment.

[0020] Broadly, embodiments of the inventive concepts disclosed herein relate to a retention system for an aircraft seat cover. The aircraft seat cover defines a sewn cable channel around a perimeter of a back portion. A cable in the cable channel is tightened to tighten the aircraft seat cover around the aircraft seat. Adjustable buckles at ends of the cable interlock and allow the cable to be tightened.

[0021] Reference is made to Figure 1 , showing an environmental view of an aircraft seat 100 for which example embodiments are implemented. The aircraft seat 100 includes a frame 102 and a seat back portion 104, which typically includes a seat back frame and a cushion. The seat back portion 104 typically has a particular contour such that differently modelled aircraft seats 100 require specially made covers to fit properly.

[0022] Reference is made to Figure 2 , showing a perspective environmental view of an aircraft seat cover 200 according to example embodiments. The aircraft seat cover 200 includes a cover body that generally wraps around a corresponding aircraft seat back portion. A peripheral or perimeter portion of the cover body partially overlaps a back surface of the seat back portion (a back surface of the seat back frame).

[0023] The aircraft seat cover 200 defines a cable channel 204 at the perimeter portion. The cable channel 204 can include a sewn overlap of material (fabric, leather, polyester, etc.) or a dedicated element secured to the material of the aircraft seat cover 200. A cable 202 within the cable channel 204 can be tightened via one or more tightening elements 206 connected to the cable 202. Tightening the cable 202 generally uniformly tightens the aircraft seat cover 200 around the seat back portion. Further, tightening via the cable 202 in the cable channel 204 at the perimeter of the cover body tends to generally conform the aircraft seat cover 200 to the aircraft seat back portion, including the model-specific contour. Moreover, the generally uniform fitting, tightening and securing via the cable and the one or more tightening elements 206 can resist pull-out of the aircraft seat cover 200 until the pull force along the perimeter edge is minimized at 30 pounds.

[0024] In at least one embodiment, the seatback portion includes a frame 208 having a plurality of cable engagement elements 210. The cable engagement elements 210 can be disposed on the frame 208 such that the cable 202 can be wrapped around the cable engagement elements 210 to reorient the cable 202 from a downward or vertical direction to a lateral or horizontal direction. This reorientation allows the tightening element 206 to complete a loop including the cable 202. Moreover, the portion of the cable 202 in the cable channel 204 is held in an orientation that facilitates a generally uniform tightening (substantially conforming to the contour of the seatback portion). Also, the cable engagement elements 210 prevent lateral forces on the cable channel 204 that can cause excessive wear, tearing, deformation, or fatigue, which can shorten the useful life of the aircraft seat trim cover 200.

[0025] In at least one embodiment, the aircraft seat trim cover 200 includes a midpoint strap 212 disposed at opposing edges of the perimeter portion; for example, the midpoint strap 212 can connect the perimeter portion along each vertical edge of the aircraft seat trim cover 200 at a location below the top of the seatback portion and above the tightening element 206. Moreover, the midpoint strap 212 can be disposed at a location that generally conforms to a contour change of the aircraft seat. Although not specific to any particular aircraft seat, it can be appreciated that a model of an aircraft seat can include a contour change that generally corresponds to a location on the seatback portion (e.g., a lower half of the seatback portion). In at least one embodiment, the midpoint strap 212 can include an elastic strap configured to exert a lateral force when installed on the seatback portion.

[0026] It can be appreciated that, in at least one embodiment, components of the aircraft seat trim cover 200 can be concealed by the seatback accessory.

[0027] Reference Figure 3 is shown a perspective view and detail view of an aircraft seat trim cover 300 according to an example embodiment. In instances where the seatback trim cover 300 defines a cable channel 304 at a perimeter portion and a cable 302 passing through the cable channel 304 tightens the aircraft seat trim cover 300 around a seatback portion via one or more tightening elements 306, the tightening elements 306 can include adjustable draw straps 314, 320. A first adjustable draw strap 314 is connected to a first end of the cable 302 via a cable connection element 316 (e.g., a clip configured to engage a loop defined in an end of the cable). Likewise, a second adjustable draw strap 320 is connected to a second end of the cable 302 via a cable connection element 322.

[0028] In at least one embodiment, each of the pull straps 314, 320 includes an interlocking element 318, 324. The interlocking elements 318, 324 can include corresponding portions of a buckle that engage one another to form a closed loop including the cable 302. In such embodiments, the seatback frame 308 can include a cable engagement element 310 to re-orient the cable 302 to allow the interlocking elements 318, 324 to engage while allowing the cable 302 to generally conform to the shape of the seatback portion. Alternatively or additionally, the seatback frame 308 can include a frame interlocking element configured to engage corresponding interlocking elements 318, 324 connected with the cable 302 without forming a closed loop.

[0029] In at least one embodiment, the cable engagement element 310 can directly engage corresponding loops in the cable ends. In such embodiments, the cable 302 can have elastic properties.

[0030] The aircraft seat cover 300 can include a midpoint strap 312. In at least one embodiment, the midpoint strap 312 includes a first strap element 330 and a second strap element 334. The first strap element 330 is connected to one vertical component of the aircraft seat cover perimeter, while the second strap element 334 is connected to an opposite vertical component of the aircraft seat cover perimeter. Each strap element 330, 334 can include a corresponding element of hook-and-loop fabric 332, 336. The hook-and-loop fabric 332, 336 allows the midpoint strap 312 to be adjusted as needed to conform to the seatback portion.

[0031] Referring to Figure 4 and Figure 5 , perspective and detail cross-sectional views of a cable channel 404 in an aircraft seat cover 400 according to an example embodiment are shown. Where the aircraft seat cover 400 includes the cable channel 404 and corresponding cable 402 to tighten the aircraft seat cover 400 around a seatback portion, a cable bushing 506 can be provided in the cable channel 404. The cable 402 is disposed within the cable bushing 506. The cable 402 can move more freely within the cable bushing 506 during tightening, for example via one or more tightening elements 414, 420, as compared to abutting an interior portion of the cable channel 404. The cable bushing 506 also protects the material from wear caused by the cable 402.

[0032] It can be appreciated that one or more midpoint straps 430, 434 can change the shape of the perimeter of the aircraft seat cover 400. The cable bushing 506 can also mitigate friction and wear that can be caused by such shape changes.

[0033] The aircraft seat trim cover retention system according to the present disclosure provides reliable retention during flight use and prevents premature failure and pull out of the trim cover from the seat back and seat back trim features. Installation of the trim cover, or removal of the cover and cover, can be performed without any tools in most applications.

[0034] It is believed that the present invention concept disclosed herein and many of its attendant advantages will be understood by the foregoing description, and it will be apparent that various changes can be made in the form, construction and arrangement of the components thereof without departing from the scope and spirit of the invention concept disclosed herein or without sacrificing all of its material advantages; and, that individual features from various embodiments can be combined to produce other embodiments; and it is the intent of the following claims to encompass and include such changes. It is therefore intended that the form described above be considered merely as illustrative of the present invention concept and that the full scope of the invention concept be determined by the appended claims and their equivalents.

Claims

1. An aircraft seat cover, comprising: A seat cover body, wherein the seat cover body defines a cable channel in its peripheral portion; A cable, the cable being disposed in a peripheral passage, the cable defining a first end and a second end; A tightening element is disposed on each of the first end and the second end; as well as Two cable coupling elements are disposed on corresponding seat frames, wherein the cable is wound around each of the two cable coupling elements to redirect the cable from a downward or vertical direction to a lateral or horizontal direction. This redirection allows the tightening element to complete a loop including the cable. in: The seat cover body is configured to wrap around the seat back frame, wherein the peripheral portion is located on the rear surface of the seat back frame; and The tightening element interlocks with the corresponding end disposed on the seat back frame to tighten the cable and tighten the peripheral portion around the rear surface.

2. The aircraft seat cover of claim 1, further comprising a cable bushing disposed in the cable channel, the cable bushing being configured to reduce friction in the cable channel when the cable is tightened.

3. The aircraft seat cover according to claim 1, further comprising a midpoint strip disposed at opposite ends of the peripheral portion.

4. The aircraft seat trim cover according to claim 3, wherein the center strip comprises: A first belt element is disposed on a first side of the peripheral portion, and the first belt element includes a hook portion of a hook-and-loop connector; and The second belt element is disposed on the second side of the peripheral portion, and the second belt element includes the loop portion of the hook-and-loop connector.

5. The aircraft seat trim cover according to claim 3, wherein the midpoint strip comprises an elastic strip.

6. The aircraft seat cover of claim 1, wherein the tightening elements on each of the first end and the second end are configured to interlock with each other.

7. An aircraft seat comprising: Seat back frame ； Aircraft seat cover, the aircraft seat cover comprising: A seat cover body, wherein the seat cover body defines a cable channel in its peripheral portion; A cable, the cable being disposed in a peripheral passage, the cable defining a first end and a second end; and A tightening element, wherein the tightening element is disposed on each of the first end and the second end; and Two cable coupling elements are disposed on the seat frame, wherein the cable is wound around each of the two cable coupling elements to redirect the cable from a downward or vertical direction to a lateral or horizontal direction, such redirection allowing the tightening element to complete a loop including the cable. in: The seat cover body is configured to wrap around the seat back frame, wherein the peripheral portion is located on the rear surface of the seat back frame; and The tightening element interlocks with the corresponding end disposed on the seat back frame to tighten the cable and tighten the peripheral portion around the rear surface.

8. The aircraft seat of claim 7, wherein the aircraft seat cover further comprises a cable bushing disposed in the cable channel, the cable bushing being configured to reduce friction in the cable channel when the cable is tightened.

9. The aircraft seat of claim 7, wherein the aircraft seat cover further comprises a midpoint strip disposed at opposite ends of the peripheral portion.

10. The aircraft seat of claim 9, wherein the midpoint band comprises: A first belt element is disposed on a first side of the peripheral portion, and the first belt element includes a hook portion of a hook-and-loop connector; and The second belt element is disposed on the second side of the peripheral portion, and the second belt element includes the loop portion of the hook-and-loop connector.

11. The aircraft seat of claim 9, wherein the midpoint strap comprises an elastic strap.

12. The aircraft seat of claim 7, wherein the tightening elements on each of the first end and the second end are configured to interlock with each other.

13. The aircraft seat of claim 7, further comprising two frame ends disposed on the seat back frame, wherein the tightening element on each of the first end and the second end is configured to engage with one of the two frame ends.

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