Seat structure

Abstract

A seat structure, comprising a first seat and a second seat; a first spreader attached to a portion of the first seat and a second spreader attached to a portion of the second seat; a beam; and a leg configured to receive a portion of the beam; wherein the beam extends between the first spreader and the second spreader and through a portion of the leg, connecting the first seat and the second seat.

Description

SEAT STRUCTURECROSS REFERENCE TO RELATED APPLICATIONS

[0001] This application claims priority to U.S. Provisional Application No. 63 / 586,616 filed September 29, 2023, which is incorporated by reference herein in its entirety.TECHNICAL FIELD

[0002] Embodiments of this disclosure are directed to seat structures, specifically, a bench seat for an aircraft and uses thereof.INTRODUCTION

[0003] Aircraft seat structures have different configurations and features based on what type of aircraft they are used in. In commercial airplanes, for example, there are numerous seats that can be placed in a variety of configurations, e.g. , two seats in a row, three seats in a row, etc. However, in smaller aircrafts, e.g., helicopters, the amount of space, and as a result, the number of seats, is limited. Helicopter seats are also configured to individually stroke, i.e. , deflect, in an effort to absorb seat motion and reduce the motion or energy that transfers to the passenger during a crash landing. Such helicopter seats are designed as individual and independent chairs, which takes up more space when compared to commercial airplane seats. There is a desire for seat structures, e.g., seat structures for helicopters and vertical take-off and landing aircrafts, that are safe and comfortable for passengers, but that also allow for additional passengers to sit in smaller aircrafts.SUMMARY OF THE DISCLOSURE

[0004] The present disclosure describes a seat structure, the seat structure comprising a first seat and a second seat; a first spreader attached to a portion of the iSUBSTITUTE SHEET (RULE 26)first seat and a second spreader attached to a portion of the second seat; a beam; and a leg configured to receive a portion of the beam; wherein the beam extends between the first spreader and the second spreader and through a portion of the leg, connecting the first seat and the second seat.

[0005] Various embodiments of the seat may include one or more of the following features. The beam may be a first beam and the seat structure may further include a second beam. The leg may be configured to receive a portion of the first beam and a portion of the second beam. The second beam may extend between the first spreader and the second spreader, and through a portion of the leg. The first spreader may be attached to a seat portion and the second spreader may be attached to a seat portion of the second seat. The leg may include a foot. The foot may include an attachment mechanism for attaching the foot to a planar surface. At least one of the first spreader, the second spreader, and the leg, may include an energy absorbing member. The seat structure may be for a helicopter or vertical take-off and landing aircrafts. A console may be attached to at least one of a portion of the beam, a portion of the first seat, a portion of the second seat, or combinations thereof. The console may include at least one component chosen from an electronic screen for displaying videos, a universal serial bus, headphone inlets, a speaker, a speaker inlet, a mirror, or combinations thereof. The seat structure may include plastic materials, metals, metallic materials, polymers, composite materials, or combinations thereof.

[0006] The present disclosure also describes a seat structure, the seat structure comprising a first seat and a second seat, each seat including a back portion having a first sidewall and a second sidewall, and a seat portion; a first spreader attached to a portion of the first seat and a second spreader attached to a2SUBSTITUTE SHEET (RULE 26)portion of the second seat; a first beam and a second beam; and a first leg attached to a portion of the first seat and a second leg attached to a portion of the second seat, each leg including at least one opening; wherein the first beam and the second beam each extends between the first spreader and the second spreader and through the opening of the first leg and the second leg, connecting the first seat and the second seat.

[0007] Various embodiments of the seat may include one or more of the following features. The first spreader may extend from the seat portion of the first seat and is vertically aligned with the first sidewall of the back portion of the first seat, and the second spreader may extend from the seat portion of the second seat and is vertically aligned with the first sidewall of the back portion of the second seat. The first leg may include a first foot and the second leg may include a second foot. The first foot and the second foot may each include an attachment mechanism for attaching each foot to a planar surface. At least one of the first spreader, the second spreader, the first leg, and the second leg, includes an energy absorbing member. The seat structure may be for a helicopter or vertical take-off and landing aircrafts. The seat structure may comprise a console attached to at least one of a portion of the first beam, a portion of the first seat, a portion of the second seat, or combinations thereof. The console may include at least one component chosen from an electronic screen for displaying videos, a universal serial bus, headphone inlets, a speaker, a speaker inlet, a mirror, or combinations thereof.BRIEF DESCRIPTION OF THE FIGURES

[0008] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate various examples and, together with the3SUBSTITUTE SHEET (RULE 26)description, serve to explain the principles of the disclosed examples and embodiments.

[0009] Aspects of the present disclosure may be implemented in connection with embodiments illustrated in the attached drawings. These drawings show different aspects of the present disclosure and, where appropriate, reference numerals illustrating like structures, components, materials, and / or elements in different figures are labeled similarly. It is understood that various combinations of the structures, components, and / or elements, other than those specifically shown, are contemplated and are within the scope of the present disclosure.

[0010] Moreover, there are many embodiments described and illustrated herein. The present disclosure is neither limited to any single aspect or embodiment thereof, nor is it limited to any combinations and / or permutations of such aspects and / or embodiments. Moreover, each of the aspects of the present disclosure, and / or embodiments thereof, may be employed alone or in combination with one or more of the other aspects of the present disclosure and / or embodiments thereof. For the sake of brevity, certain permutations and combinations are not discussed and / or illustrated separately herein. Notably, an embodiment or implementation described herein as “exemplary” is not to be construed as preferred or advantageous, for example, over other embodiments or implementations; rather, it is intended to reflect or indicate the embodiment(s) is / are “example” embodiment(s).

[0011] FIG. 1A is a perspective front view of a seat structure and FIG. 1 B is a perspective rear view of the seat structure, according to embodiments of the present disclosure.4SUBSTITUTE SHEET (RULE 26)

[0012] FIG. 2A is a perspective front view of a seat structure and FIG. 2B is a perspective rear view of the seat structure, according to embodiments of the present disclosure.

[0013] FIG. 3 is a perspective front view of a seat structure according to embodiments of the present disclosure.

[0014] FIG. 4 is a rear view of a seat structure within an exemplary aircraft, according to embodiments of the present disclosure.

[0015] As used herein, the terms “comprises,” “comprising,” “includes,” “including,” or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements, but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. The term “exemplary” is used in the sense of “example,” rather than “ideal.” In addition, the terms “first,” “second,” and the like, herein do not denote any order, quantity, or importance, but rather are used to distinguish an element or a structure from another. Moreover, the terms “a” and “an” herein do not denote a limitation of quantity, but rather denote the presence of one or more of the referenced items.

[0016] Notably, for simplicity and clarity of illustration, certain aspects of the figures depict the general structure and / or manner of construction of the various embodiments. Descriptions and details of well-known features and techniques may be omitted to avoid unnecessarily obscuring other features. Elements in the figures are not necessarily drawn to scale; the dimensions of some features may be exaggerated relative to other elements to improve understanding of the example embodiments. For example, one of ordinary skill in the art appreciates that the side views are not drawn to scale and should not be viewed as representing proportional5SUBSTITUTE SHEET (RULE 26)relationships between different components. The side views are provided to help illustrate the various components of the depicted assembly, and to show their relative positioning to one another.DETAILED DESCRIPTION

[0017] Reference will now be made in detail to examples of the present disclosure, which are illustrated in the accompanying drawings. Wherever possible, the same reference numbers will be used throughout the drawings to refer to the same or like parts. In the discussion that follows, relative terms such as “about,” “substantially,” “approximately,” etc. are used to indicate a possible variation of a numerical range in a stated numeric value, as will be designated below.

[0018] Aircraft seat structures have different configurations and features based on what type of aircraft they are used in. In commercial airplanes, there are numerous seats that can be placed in a variety of configurations, e.g., two seats in a row, three seats in a row, etc. For example, in economy class of Boeing® 737 airplanes, three seats are tied together utilizing two legs. Specifically, a first leg may be between a first seat and a second seat, and a second leg may be between the second seat and a third seat. However, seats in commercial airplanes are not designed to withstand the same crash loads as seats in smaller aircrafts, e.g., helicopters and electric vertical takeoff or landing (eVTOL) aircrafts.

[0019] In smaller aircrafts, e.g., helicopters and eVTOL aircraft, the amount of space, and as a result, the number of seats, is limited. Such seats traditionally used in smaller aircrafts are designed to withstand more impact than seats on larger, commercial airplanes. For example, helicopter seats must be designed to only move in a vertical direction, to absorb motion and / or shock caused by turbulence during takeoff, and / or landing, and to withstand extreme impact from a crash or hard6SUBSTITUTE SHEET (RULE 26)landing. Typical helicopter seats are also designed and installed as individual and independent chairs, where each seat includes its own pair of legs. This allows each seat to individually stroke, i.e. , deflect, in an effort to absorb seat motion and reduce the motion that may be transferred to a passenger during a crash landing. However, this configuration also takes up more space as compared to commercial airplane seats. To reconfigure traditional helicopter seats and include multiple seats and / or rows of seats in a helicopter, any design must satisfy all safety requirements and ensure any safety and shock mechanisms may properly function.

[0020] Although the present disclosure references a seat for an aircraft, those of ordinary skill in the art will readily recognize that the concepts of the present disclosure may be utilized in configurations and designs where a bench seat that provides both safety and comfort for a passenger or passengers is needed. Moreover, although the present disclosure makes reference to a small plane or a helicopter, those of ordinary skill in the art will readily recognize that reference to a small plane or a helicopter is exemplary, and that the concepts of the present disclosure may be used in conjunction with any suitable or comparable aircraft, e.g., commercial airplanes or electrical vertical takeoff and landing aircrafts (eVTOL aircrafts).

[0021] Embodiments of the present disclosure relate to a seat, and, in particular, a bench seat for an aircraft (e.g., a helicopter, small aircrafts, and / or eVTOL aircrafts). In the present disclosure, seat, seat structure, and bench seat, may be used interchangeably. FIG. 1 A depicts a perspective front view of a seat structure 100 and FIG. 1 B depicts a perspective rear view of seat structure 100. Seat structure 100 may include a first seat 102a and a second seat 102b. As shown in the figures, seat structure 100 may include at least two seats. In some embodiments,7SUBSTITUTE SHEET (RULE 26)seat structure 100 may include more than two seats, e.g., at least three seats or at least four seats.

[0022] First seat 102a and second seat 102b may each include a back portion 104a, 104b, and a seat portion 110a, 110b. Back portion 104a, 104b may each include a plurality of sidewalls. Referring to FIG. 1A, back portion 104a, 104b may each include a first sidewall 106a, 106b and a second sidewall 108a, 108b. Seat portion 110a, 110b may each include a first surface 112a, 112b and a second surface 114a, 114b. First surface 112a, 112b may be referred to as the top surface and second surface 114a, 114b may be referred to as the bottom surface. The top surface is where the passenger may sit and the bottom surface faces the floor of the aircraft.

[0023] Seats according to the present disclosure may be of any size or configuration conforming to Federal Aviation Administration (FAA) standards and safety standards. The seats may have a width ranging from about 14 inches to about 20 inches. For example, a width of seat 102a, 102b may range from about 14 inches to about 18 inches, about 14 inches to about 16 inches, about 16 inches to about 20 inches, or about 16 inches to about 18 inches. In some examples, a width of seat 102a, 102b may be about 14 inches, about 15 inches, about 16 inches, about 17 inches, about 18 inches, about 19 inches, or about 20 inches. A portion of the seat, e.g., a bullnose 115a, 115b of corresponding seat portion 110a, 110b may have a distance, i.e., a height, relative to a surface, e.g., a floor 330 of an aircraft as shown in FIG. 4, ranging from about 10 inches to about 18 inches from the floor. For example, the height of bullnose 115a, 115b relative to floor 330 may range from about 10 inches to about 16 inches, about 12 inches to about 18 inches, or about 12 inches to about 16 inches. In some examples, the distance of height of bullnose8SUBSTITUTE SHEET (RULE 26)115a, 115b relative to floor 330 may be about 10 inches, about 11 inches, about 12 inches, about 13 inches, about 14 inches, about 15 inches, or about 16 inches.

[0024] With continuing reference to FIGS. 1A-1 B, seat structure 100 may include a leg 116, a foot 118, a plurality of spreaders 130a, 130b, a first beam 140, and a second beam 150. As shown in FIGS. 1A-1B, leg 116 may be located at any position between first seat 102a and second seat 102b. In some examples, leg 116 may be positioned between first seat 102a and second seat 102b, such that leg 116 is equidistant from each of first seat 102a and second seat 102b. In some embodiments, however, leg 116 may be positioned closer to either of first seat 102a or second seat 102b. Leg 116 may have any appropriate shape or configuration such that leg 116 may securely couple and / or support first seat 102a and second seat 102b to form a bench seat, and such that the resulting bench seat may be secured to the aircraft, e.g., to floor 330 of the aircraft. For example, leg 116 may have a Y-shape, a cone shape, or a pyramid shape.

[0025] In some embodiments, first seat 102a and second seat 102b may be positioned with a gap, e.g., width, between first seat 102a and second seat 102b ranging from about 2 inches to about 30 inches apart. For example, the width between first seat 102a and second seat 102b may range from about 2 inches to about 25 inches, about 2 inches to about 20 inches, about 2 inches to about 15 inches, about 2 inches to about 10 inches, about 4 inches to about 30 inches, about 4 inches to about 25 inches, about 4 inches to about 20 inches, about 4 inches to about 15 inches, about 4 inches to about 10 inches, about 6 inches to about 30 inches, about 6 inches to about 25 inches, about 6 inches to about 20 inches, about 6 inches to about 15 inches, or about 6 inches to about 10 inches. In some examples, the width between first seat 102a and second seat 102b may be about 29SUBSTITUTE SHEET (RULE 26)inches, about 4 inches, about 6 inches, about 8 inches, about 10 inches, about 12 inches, about 14 inches, about 16 inches, about 18 inches, about 20 inches, about 22 inches, about 24 inches, about 26 inches, about 28 inches, or about 30 inches.

[0026] Each spreader 130a, 130b may be secured to a portion of first seat 102a and second seat 102b. For example, a first spreader 130a may be secured to a portion of first seat 102a and a second spreader 130b may be secured to a portion of second seat 102b. Referring to FIGS. 1A-1 B, first spreader 130a may be secured to an inner surface portion of first sidewall 106a of first seat 102a, and second spreader 130b may be secured to an inner surface portion of second sidewall 108b of second seat 102b. In some embodiments, and as shown in FIGS. 1A-1 B, first spreader 130a may be placed in a vertical configuration and generally aligned with first sidewall 106a of first seat 102a. Second spreader 130b may also be placed in a vertical configuration and generally aligned with second sidewall 108b of second seat 102b. In some embodiments, first spreader 130a may be secured to a portion of seat portion 110a of first seat 102a and second spreader 130b may be secured to a portion of seat portion 110b of second seat 102b. For example, first spreader 130a may be secured to and / or extends from second surface 114a of first seat 102a, in a direction away from first surface 112a, and second spreader 130b may be secured to and / or extends from second surface 114b of second seat 102b, in a direction away from first surface 112b. Spreader 130a and / or spreader 130b may be secured to a portion of first seat 102a and / or second seat 102b, respectively, via any appropriate mechanism, e.g., screws, clamps, bolts, nails, or any other appropriate type of fastener or combinations thereof. In other embodiments, spreader 130a may be manufactured integrally from a one-piece construction with a portion of first seat 102a, such that spreader 130a and first seat 102a may form a single structure, ioSUBSTITUTE SHEET (RULE 26)and / or spreader 130b may be manufactured integrally from a one-piece construction with a portion of second seat 102b, such that spreader 130b and second seat 102b may form a single structure. Seat structure 100 may include any appropriate number of spreaders 130a, 130b. For example, seat structure 100 may include at least two spreaders, at least three spreaders, at least four spreaders, at least five spreaders, or at least six spreaders. Referring to FIG. 1 A, a spreader may be placed between first seat 102a and leg 116. In other examples, a spreader may be placed between leg 116 and second seat 102b. In some embodiments, a spreader may be placed between first seat 102a and leg 116 and an additional spreader may be placed between leg 116 and second seat 102b.

[0027] In other embodiments, first spreader 130a may be angled inwards, i.e., towards leg 116, and relative to first sidewall 106a, and second spreader 130b may be angled inwards, i.e., towards leg 116, and relative to first sidewall 106b. Angling the spreaders 130a, 130b inwards and away from the frame of the aircraft (e.g., as shown in FIG 4), may allow for further nesting within the frame. In other words, seat structure 100 may more easily fit into a narrow, rounded cabin of a relatively smaller aircraft, such as, e.g., a helicopter or an eVTOL aircraft. This may also provide additional space for the passengers. Spreader 130a, 130b may have any appropriate shape and / or configuration. For example, spreader 130a, 130b may have a generally rectangular shape. In some examples, spreader 130a, 130b may have a generally rectangular body with at least one end portion having a generally circular or rounded shape. As shown in FIGS. 1A-1 B, spreader 130a, 130b may have a generally rounded portion configured to receive a portion of first beam 140 and / or second beam 150, as will be further discussed below. nSUBSTITUTE SHEET (RULE 26)

[0028] Spreader 130a, 130b may each include an opening or recess for receiving a portion of first beam 140 and / or second beam 150. For example, as shown in FIGS. 1A-2B, each spreader 130a, 130b may include a first generally circular feature 132a, 132b corresponding to first beam 140 and a second generally circular feature 134a, 134b corresponding to second beam 150. Each of first generally circular features 132a, 132b and second generally circular features 134a, 134b may define openings configured to receive terminal ends of first beam 140 and second beam 150, respectively. First beam 140 and / or second beam 150 may be secured within first generally circular features 132a, 132b and second generally circular features 134a, 134b by any suitable manner known in the art. For example, first beam 140 and / or second beam 150 may be secured within first generally circular features 132a, 132b and second generally circular features 134a, 134b by an adhesive, ultrasonic welding, friction stir welding, and / or spin welding. First beam 140 and / or second beam 150 may be secured to spreader 130a, 130b, such that spreader 130a, spreader 130b, or any additional spreaders, may slide along a length of first beam 140 and / or second beam 150. In further embodiments, first beam 140 and second beam 150 may be manufactured integrally from a one-piece construction with spreaders 130a, 130b. In other embodiments, spreader 130a, 130b may be removably coupled or permanently secured to a portion of first beam 140 and / or second beam 150 via a fastener, including, e.g. , screws, clamps, bolts, nails, or any other appropriate type of fastener or combinations thereof.

[0029] As shown in FIGS. 1A-2B, each spreader 130a, 130b may define an outer periphery 160a, 160b. Each spreader 130a, 130b may include at least one energy absorbing member 136, which will be discussed in further detail below.12SUBSTITUTE SHEET (RULE 26)In other embodiments, referring to FIG. 3, the outer periphery 160a, 160b of each spreader 130a, 130b may surround an interior cavity 162a, 162b (not shown). Interior cavity 162a, 162b of each spreader 130a, 130b may include at least one diagonal wall 164a, 164b. Each diagonal wall 164a, 164b may extend between first generally circular features 132a, 132b and second generally circular features 134a, 134b. In some embodiments, diagonal wall 164a, 164b may be horizontal or vertical. In some embodiments, each interior cavity 162a, 162b may include at least one energy absorbing member 136.

[0030] As shown in FIGS. 1 A-1 B, seat structure 100 may include a first beam 140 and a second beam 150. First beam 140 may extend in a horizontal direction through a portion of first seat 102a and a portion of second seat 102b, forming a bench seat. In some embodiments, first beam 140 may extend in a horizontal direction from first spreader 130a through a portion of first seat 102a, through a portion of leg 116, through a portion of second seat 102b, and to second spreader 130b. Second beam 150 may extend in a horizontal direction from first spreader 130a through a portion of leg 116, and to second spreader 130b. First beam 140 may be disposed relatively closer to seat portions 110a, 110b as compared to second beam 150. First beam 140 and second beam 150 may have any appropriate shape and / or configuration such that first beam 140 and second beam 150 may be utilized as described herein. In some embodiments, first beam 140 and / or second beam 150 may have a cylindrical shape with a solid interior or a hollow space inside. In some embodiments, seat structure 100 may include more than two seats, e.g., at least three seats or at least four seats where the additional seats may include one o more additional spreaders such that first beam 140 and second beam 150 may extend through the one or more additional spreaders.13SUBSTITUTE SHEET (RULE 26)

[0031] First beam 140 and / or second beam 150 may have any appropriate size to be utilized with the seat structures described herein. For example, first beam 140 and / or second beam 150 may have a length ranging from about 30 inches to about 70 inches. For example, first beam 140 and / or second beam 150 may have a length ranging from about 30 inches to about 65 inches, about 30 inches to about 60 inches, about 30 inches to about 55 inches, about 30 inches to about 50 inches, about 35 inches to about 70 inches, about 35 inches to about 65 inches, about 35 inches to about 60 inches, about 35 inches to about 55 inches, about 35 inches to about 50 inches, about 40 inches to about 70 inches, about 40 inches to about 65 inches, about 40 inches to about 60 inches, about 40 inches to about 55 inches, about 40 inches to about 50 inches, about 45 inches to about 70 inches, about 45 inches to about 65 inches, about 45 inches to about 60 inches, about 45 inches to about 55 inches, about 45 inches to about 50 inches, about 50 inches to about 70 inches, about 50 inches to about 65 inches, about 50 inches to about 60 inches, or about 50 inches to about 55 inches. In some examples, first beam 140 and / or second beam 150 may have a length of about 30 inches, about 35 inches, about 40 inches, about 45 inches, about 50 inches, about 55 inches, about 60 inches, about 65 inches, or about 70 inches.

[0032] First beam 140 and / or second beam 150 may have an exterior diameter ranging from about 0.5 inch to about 3 inches. For example, first beam 140 and / or second beam 150 may have an exterior diameter ranging from about 0.5 inch to about 2.5 inches, about 0.5 inch to about 2 inches, about 1 inch to about 3 inches, about 1 inch to about 2.5 inches, about 1 inch to about 2 inches, about 1.5 inches to about 3 inches, about 1 .5 inches to about 2.5 inches, or about 1.5 inches to about 2 inches. In some examples, first beam 140 and / or second beam 150 may have an14SUBSTITUTE SHEET (RULE 26)exterior diameter of about 0.5 inch, about 1 inch, about 1 .5 inches, about 2 inches, about 2.5 inches, or about 3 inches.

[0033] First beam 140 and / or second beam 150 may have an interior diameter ranging from about 0.5 inch to about 3 inches. For example, first beam 140 and / or second beam 150 may have an interior diameter ranging from about 0.5 inch to about 2.5 inches, about 0.5 inch to about 2 inches, about 1 inch to about 3 inches, about 1 inch to about 2.5 inches, about 1 inch to about 2 inches, about 1 .5 inches to about 3 inches, about 1 .5 inches to about 2.5 inches, or about 1 .5 inches to about 2 inches. In some examples, first beam 140 and / or second beam 150 may have an interior diameter of about 0.5 inch, about 1 inch, about 1 .5 inches, about 2 inches, about 2.5 inches, or about 3 inches. In other examples, first beam 140 and / or second beam 150 may have different portions with varying interior diameters. For example a first portion of first beam 140 and / or second beam 150 may have a first interior diameter and a second portion of first beam 140 and / or second beam 150 may have a second interior diameter.

[0034] As described above, traditional seats for small aircrafts, e.g., helicopters or eVTOL aircraft, are designed as individual seats, allowing each of the seats to stroke, i.e. , deflect separately and individually. The individual seats are able to absorb seat motion and reduce the motion or energy that may be transferred to the passenger during a crash landing. The present disclosure describes a bench seat comprising more than one seat, e.g., two seats.

[0035] Referring back to FIGS. 1A-1 B and as described in detail above, first seat 102a and second seat 102b may form bench seat structure 100 via the use of spreaders 130a, 130b, leg 116, first beam 140, and second beam 150. Traditional helicopter seats typically include at least two legs per individual seat. Each leg may15SUBSTITUTE SHEET (RULE 26)serve as an attachment point to the frame of the aircraft, e.g., the floor surface of the aircraft. Seat structures 100 of the present disclosure have a limited number of legs. For example, as shown in FIGS. 1A-3, seat structures 100 may include no more than two legs. In some embodiments, seat structures 100 may include a single leg. In other embodiments, seat structures 100 may include no more than three legs or no more than four legs. The legs may serve as attachment points to the frame of the aircraft, e.g., the floor surface of the aircraft. The seat structures 100 described herein limit the number of attachment points, i.e., legs, and simplify the design of typical seats in small aircrafts, allowing for quicker cabin installation and / or reconfiguration, and increasing floor space and / or living space within the cabin.

[0036] Referring to FIGS. 1A-1 B, leg 116 may include foot 118. Leg 116 may have any appropriate shape or configuration for receiving first beam 140 and / or second beam 150, as described above. For example, leg 116 may include at least one opening to receive first beam 140 and / or second beam 150. In some embodiments, leg 116 may include a first opening for receiving first beam 140 and a second opening for receiving second beam 150. Foot 118 may have any appropriate shape or configuration such that foot 118 may be placed on floor 330 of an aircraft. A portion of foot 118 may define an outer periphery 119 surrounding an interior aperture 121. As shown in FIG. 1A, interior aperture 121 may include an energy absorbing member 138, which will be discussed in further detail below. A portion of foot 118 may be removably attached or permanently secured to the floor surface of the aircraft via a fastener, including, e.g., screws, clamps, bolts, nails, or any other appropriate type of fastener or combinations thereof. In other embodiments, a portion of foot 118 may be removably attached or permanently secured to the floor surface of the aircraft via an attachment mechanism. The attachment mechanism16SUBSTITUTE SHEET (RULE 26)may be, e.g., a nuts and bolts system or a track system. In embodiments where foot118 may be attached to the floor surface via a track system, foot 118 may include a first track and the floor surface may include a second track. The second track may be configured to receive a portion of the first track. For example, the second track may include a plurality of holes or recesses for receiving corresponding portions of the first track.

[0037] Regarding energy absorption, the configuration of seat structure 100 allows for each seat, e.g., first seat 102a and second seat 102b, to individually stroke and absorb seat motion during a crash landing. Energy absorbing members 136, 138 may be located in at least one of the legs and / or spreaders. For example, energy absorbing members 136, 138 may be located in at least one of leg 116, first spreader 130a, and second spreader 130b. As shown in FIGS. 1 A-B, each spreader 130a, 130b may include at least one energy absorbing member 136 and leg 116 may include at least one energy absorbing member 138. With continuing reference to FIGS. 1A-B, leg 116 may include a plurality of energy absorbing members 138. For example, the plurality of energy absorbing members 138 may be in any appropriate configuration, e.g., energy absorbing members 138 may be configured horizontally, vertically, and / or diagonally. As shown in FIG. 1A, energy absorbing members 138 may be configured diagonally in alternating directions forming a zigzag design. In one or more embodiments, seat portion 110a, 110b may include energy absorbing members. In one or more embodiments, back portion 104a, 104b may include energy absorbing members. In one or more embodiments, seat 102a and 102b may include energy-absorbing members.

[0038] Such energy absorbing members 136, 138 may comprise of a metallic material, e.g., steel, aluminum, copper, or combinations thereof, as well as17SUBSTITUTE SHEET (RULE 26)composite materials, e.g., metal matrix composites. Energy absorbing members 136,138 may be any material or composite of materials that may take an initial shape and as a result of the energy produced by movement of first seat 102a, second 102b, components thereof, or combinations thereof, may deform into another shape.Examples of an energy absorbing member may include a coil that may have an initial spiraled or coiled shape and a final shape where the coil is stretched out straight or a rod that may be sent through a mandrel or a die to change the cross section of the rod. Referring to FIGS. 1A-2B, first spreader 130a and second spreader 130b are not directly connected to the floor surface of the aircraft. First spreader 130a and second spreader 130b may each be attached to leg 116 via first beam 140 and second beam 150, and leg 116 serves as the attachment point to the floor surface of the aircraft. Energy absorbing members 136, 138 in first spreader 130a, second spreader 130b, leg 116, or combinations thereof, absorb motion from each of first seat 102a and second seat 102b. Energy absorbing members 136, 138 may be a one-time use mechanism to absorb energy during a hard landing. In other examples, energy absorbing members 136, 138 may be replaceable. For example, once energy absorbing members 136, 138 are activate to absorb energy, energy absorbing members 136, 138 may deform, i.e. , depress, and can no longer be used. The configuration and combination of spreaders 130a, 130b, leg 116, and energy absorbing members 136, 138 allows each seat, e.g., first seat 102a and second seat 102b, to individually stroke during a crash landing, while also saving floor space and / or living space within the cabin of the aircraft.

[0039] FIGS. 2A-2B depict an alternative configuration of seat structure 200, according to the present disclosure. In FIGS. 2A-2B, seat structure 200 may include a first leg 120a and a second leg 120b, wherein first leg 120a includes a first foot18SUBSTITUTE SHEET (RULE 26)122a and second leg 120b includes a second foot 122b. First leg 120a may be secured to a portion of first seat 102a. For example, first leg 120a may be secured to a portion of second sidewall 108a of first seat 102a and second leg 120b may be secured to a portion of first sidewall 106b of second seat 102b. In some embodiments, first leg 120a may be placed in a vertical configuration and generally aligned with second sidewall 108a of first seat 102a and second leg 120b may be placed in a vertical configuration and generally aligned with first sidewall 106b of second seat 102b. Descriptions of the components for seat structure 100 above in reference to FIGS. 1 A-1 B may also apply to the corresponding components of seat structure 200 as depicted in FIGS. 2A-2B. Seat structure 200 includes at least two legs, e.g., first leg 120a and second leg 120b. As described above in regards to FIGS. 1 A-1 B, energy absorbing members may be included in one or both of first leg 120a and second leg 120b. The use of two legs may increase the energy absorption ability of seat structure 200, while still increasing floor space and / or living space within the cabin.

[0040] FIG. 4 depicts another embodiment of a seat structure 400. Seat structure 400 is shown in an aircraft cabin 310. As shown in FIG. 4, first spreader 130a may be attached to second surface 114a of seat portion 110a, where first spreader 130a is angled inwards, i.e. , towards first leg 120a, and relative to first sidewall 106a, and second spreader 130b may be attached to second surface 114b of seat portion 110b, where second spreader 130b is angled inwards, i.e., towards second leg 120b, and relative to second sidewall 108b. Angling the spreaders 130a, 130b inwards and away from the frame of the helicopter, as shown in FIG. 4, may allow for further nesting within the frame. In other words, seat structure 400 would more easily fit into a narrow, rounded cabin of a helicopter. This may also provide19SUBSTITUTE SHEET (RULE 26)additional space for the passengers, e.g., in the head space 320 of aircraft cabin310. Descriptions of the components for seat structure 100 above in reference to FIGS. 1A-1 B, seat structure 200 above in reference to FIGS. 2A-2B, and seat structure 300 in reference to FIG. 3, may also apply to the corresponding components of seat structure 400 as depicted in FIG. 4.

[0041] In some embodiments, the space between first seat 102a and second seat 102b may include additional components. For example, a console (not shown) may be attached to a portion of first seat 102a, a portion of second seat 102b, a portion of first beam 140, or combinations thereof. In some embodiments, the console may include a compartment for storage. In other examples, the console may include additional components for use by the passenger. The components may include, e.g., an electronic screen for displaying videos (e.g., via WI-FI, cellphones, tablets, etc.), a universal serial bus (USB), headphone inlets, a speaker, a speaker inlet, a mirror, or combinations thereof. In other examples, a cushion and / or an arm rest may be attached to a portion of first seat 102a, a portion of second seat 102b, a portion of first beam 140, or combinations thereof. Using this additional space between first seat 102a and second seat 102b may free up space around the seats, on the floor, and in the aircraft, providing a more comfortable environment for the passengers.

[0042] Components of the seats may be formed of any suitable material with sufficient weight and components to withstand energy and impact from air flight and / or with any characteristics suitable for use in an aircraft. The back portion, seat portion, legs, spreaders, and / or beams, may include plastic materials, metals, metallic materials, polymers, composite materials, or combinations thereof. For example, the back portion, seat portion, legs, spreaders, and / or beams, may include20SUBSTITUTE SHEET (RULE 26)steel, titanium, magnesium, aluminum, carbon fiber, plastic, or combinations thereof.In some examples, the beams may include a high strength aerospace grade aluminum material. Components of the track and / or attachment mechanisms may be made from plastic materials, metals, chemical composites, alloys, or combinations thereof. For example, components of the track and / or attachment mechanisms may include steel, titanium, magnesium, aluminum, carbon fiber, plastic, or combinations thereof. In some embodiments, components of the seats may be made of metal machined to a desired configuration.

[0043] The description above and examples are illustrative and are not intended to be restrictive. One of ordinary skill in the art may make numerous modifications and / or changes without departing from the general scope of the invention. For example, and as has been referenced, aspects of above-described embodiments may be used in any suitable combination with each other. Additionally, portions of the above-described embodiments may be removed without departing from the scope of the invention. In addition, modifications may be made to adapt a particular situation or aspect to the teachings of the various embodiments without departing from their scope. Many other embodiments will also be apparent to those of skill in the art upon reviewing the above description.21SUBSTITUTE SHEET (RULE 26)

Claims

CLAIMSWhat is claimed is:1 . A seat structure, comprising: a first seat and a second seat; a first spreader attached to a portion of the first seat and a second spreader attached to a portion of the second seat; a beam; and a leg configured to receive a portion of the beam; wherein the beam extends between the first spreader and the second spreader and through a portion of the leg, connecting the first seat and the second seat.

2. The seat structure of claim 1 , further comprising: a third seat; and a third spreader attached to a portion of the third seat, wherein the beam extends between the first spreader, second spreader, and third spreader, connecting the first seat and the second seat.

3. The seat structure of claim 1 , wherein the beam is a first beam, and the seat structure further includes a second beam, and wherein the leg is configured to receive a portion of the first beam and a portion of the second beam.

4. The seat structure of claim 1 , wherein the beam is a first beam, and the seat structure further includes a second beam, wherein the leg is configured to receive a portion of the first beam and a portion of the second beam, and wherein the second22SUBSTITUTE SHEET (RULE 26)beam extends between the first spreader and the second spreader, and through a portion of the leg.

5. The seat structure of claim 1 , wherein the first spreader is attached to a seat portion of the first seat and the second spreader is attached to a seat portion of the second seat.

6. The seat structure of claim 1 , wherein the leg includes a foot configured to enclose an energy absorbing member.

7. The seat structure of claim 1 , wherein the leg includes a foot, wherein the foot includes an attachment mechanism for attaching the foot to a planar surface, and wherein the attachment mechanism is a track system on the planar surface.

8. The seat structure of claim 1 , wherein at least one of the first spreader, the second spreader, the leg, the first seat, the second seat includes an energy absorbing member.

9. The seat structure of claim 1 , wherein the seat structure is for a helicopter or vertical take-off and landing aircrafts.

10. The seat structure of claim 1 , further comprising a console attached to at least one of a portion of the beam, a portion of the first seat, a portion of the second seat, or combinations thereof.23SUBSTITUTE SHEET (RULE 26)11 . The seat structure of claim 1 , further comprising a console attached to at least one of a portion of the beam, a portion of the first seat, a portion of the second seat, or combinations thereof, and wherein the console includes at least one component chosen from an electronic screen for displaying videos, a universal serial bus, headphone inlets, a speaker, a speaker inlet, a mirror, or combinations thereof.

12. The seat structure of claim 1 , including plastic materials, metals, metallic materials, polymers, composite materials, or combinations thereof.

13. A seat structure, comprising: a first seat and a second seat, each seat including a back portion having a first sidewall and a second sidewall, and a seat portion; a first spreader attached to a portion of the first seat, and a second spreader attached to a portion of the second seat; a first beam and a second beam; and a first leg attached to a portion of the first seat, and a second leg attached to a portion of the second seat, each leg including at least one opening; wherein the first beam and the second beam each extend between the first spreader and the second spreader and through the opening of the first leg and the second leg, connecting the first seat and the second seat.

14. The seat structure of claim 13, wherein the first spreader extends from the seat portion of the first seat and is vertically aligned with the first sidewall of the back portion of the first seat, and the second spreader extends from the seat portion of the24SUBSTITUTE SHEET (RULE 26)second seat and is vertically aligned with the first sidewall of the back portion of the second seat.

15. The seat structure of claim 13, further comprising: a third seat; a third spreader attached to a portion of the third seat; and a third spreader attached to a portion of the third seat, wherein the first beam and second beam extend between the first spreader, second spreader, and third spreader, connecting the first seat and the second seat.

16. The seat structure of claim 13, wherein the first leg includes a first foot and the second leg includes a second foot, wherein the first foot and the second foot each include an attachment mechanism for attaching each foot to a planar surface, and wherein the attachment mechanism is a track system.

17. The seat structure of claim 13, wherein at least one of the first spreader, the second spreader, the first leg, the second leg, the first seat, and the second seat includes an energy absorbing member.

18. The seat structure of claim 13, wherein the seat structure is for a helicopter or vertical take-off and landing aircrafts.

19. The seat structure of claim 13, further comprising a console attached to at least one of a portion of the first beam, a portion of the first seat, a portion of the second seat, or combinations thereof.25SUBSTITUTE SHEET (RULE 26)20. The seat structure of claim 13, further comprising a console attached to at least one of a portion of the first beam, a portion of the first seat, a portion of the second seat, or combinations thereof, wherein the console includes at least one component chosen from an electronic screen for displaying videos, a universal serial bus, headphone inlets, a speaker, a speaker inlet, a mirror, or combinations thereof.26SUBSTITUTE SHEET (RULE 26)

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