Aircraft seating equipment

Abstract

The invention is based on an aircraft seating arrangement comprising a mounting unit adapted to be attached to the cabin floor and having at least one cross beam, two seat structural elements arranged in each case on one side of the seat area and each having one bearing point, a seat back attached via the bearing points of the seat structural elements, and a bearing device adapted to pivotally support the seat back between an upright seating position and a comfort position, the seat back comprising a pivotable back element.It is proposed that the aircraft seating arrangement comprises at least one restoring module adapted to provide at least a restoring force for restoring the seat back from the comfort position to the upright seating position, and for this purpose arranged at least substantially in the area above the bearing points of the seat structural elements.

Description

[Technical Field]

[0001] The present invention relates to an aircraft seating arrangement according to the preamble of claim 1 . [Background technology]

[0002] An aircraft seating arrangement has already been proposed, which comprises a mounting unit configured to be attached to the cabin floor and having at least one cross beam, two seat structural elements each arranged on one side of the seat area and each having a bearing point, a seat back attached via the bearing points of the seat structural elements, and a bearing device configured to pivotally support the seat back between an upright seating position and a comfort position, the seat back comprising a pivotable seat back element. Summary of the Invention [Problem to be solved by the invention]

[0003] The object of the invention is to provide a universal device with improved properties, in particular being compact and advantageously offering a large degree of freedom for the passenger's legs. This object is achieved according to the invention by the features of claim 1, advantageous implementations and further developments of the invention being readable from the subclaims. [Means for solving the problem]

[0004] The present invention is based on an aircraft seating arrangement comprising: a mounting unit configured to be mounted on a passenger cabin floor and having at least one cross beam; two seat structural elements each arranged on one side of the seat area and each having a bearing point; a seat back attached via the bearing points of the seat structural elements; and a bearing device configured to pivotally support the seat back between an upright seating position and a comfort position, wherein the seat back comprises a pivotable seat back element.

[0005] It is proposed that the aircraft seating arrangement has at least one restoring module, which is configured to provide a restoring force for restoring at least the seat back from the comfort position to the upright seating position and, for this purpose, is at least substantially arranged in an area above the bearing point of the seat structural element. The term "aircraft seating arrangement" should preferably be understood to mean at least one component, e.g., a subassembly, of an aircraft seat, in particular an aircraft passenger seat. In principle, it is also conceivable that the aircraft seating arrangement substantially or completely forms the aircraft seat. The term "aircraft seat" should be understood to mean a passenger seat configured to be attached to the aircraft cabin floor. The aircraft seat is preferably formed as part of an aircraft seat row of a plurality of aircraft seats arranged adjacent to one another. The aircraft seat preferably comprises at least one seat bottom forming a seating area for the passenger and a backrest providing a seat back contact surface against which the passenger seated in the aircraft seat can rest their back. Furthermore, the aircraft seat has a mounting unit via which the aircraft seat is attached to the cabin floor and further components, such as the seat bottom and the backrest, are attached to the mounting unit. "Mounting unit" should preferably be understood to mean the basic structure of an aircraft seat, which preferably forms the load-bearing structure of the aircraft seat. The aircraft seat is mounted on a mounting surface, i.e. in particular on a cabin floor, via the mounting unit. The mounting unit preferably has at least two seat legs and at least one transverse element connected to the seat legs. The transverse element forms a support tube. The mounting unit preferably has two transverse elements, i.e. a front transverse element and a rear transverse element. The mounting unit is preferably coupled to the cabin floor, preferably via a plurality of fixtures, preferably to corresponding fixed rails on the cabin floor. The mounting unit forms a load-bearing frame of the aircraft seat, preferably of an aircraft seat row.

[0006] The term "seat structural element" is preferably understood to mean a part of the load-bearing structure of an aircraft seat, to which further components of the aircraft seat, such as a seat back, a seat back element, or armrests, may be fixed. The seat structural element is preferably configured as a seat divider. The seat structural element embodied as a seat divider is preferably rigidly connected to at least one, preferably two, transverse elements of the mounting unit. The seat structural element embodied as a seat divider preferably extends substantially horizontally from the front transverse element to the area rearward of the rear transverse element. In the area rearward of the rear transverse element, the seat structural element embodied as a seat divider extends substantially vertically away from the mounting surface, preferably up to the armrest height. In principle, it is also conceivable for the seat structural element to be integrally formed with part of the seat shell, for example the lower seat back element. In this case, the integrally formed seat structural element may be formed, for example, by a side area of ​​the seat shell.

[0007] A "bearing point" is preferably understood to mean a mounting point to which a component, such as a back element, can be fixedly mounted. The component can preferably be fixedly and movably mounted via the bearing point. The bearing point is preferably configured to movably, preferably pivotally, mount a further component, in particular a back element, to the component forming the bearing point. A "bearing device" is understood to mean a module on which a backrest, in particular a pivotable backrest element, is pivotally supported on a unit, in particular a mounting unit. The bearing device can preferably be formed by a bearing bolt. In principle, it is also conceivable that the bearing device is formed by a hinge or another bearing mechanism on which the backrest, in particular a pivotable backrest element, is pivotally supported. The bearing device forms a rotation axis about which the backrest, in particular a pivotable backrest element, can pivot. A pivotable backrest is understood to mean that at least one pivotable backrest element of the backrest is pivotable relative to the mounting structure, i.e., the mounting unit. The term "pivotable back element" is to be understood as meaning a back element that preferably forms at least a part, preferably most, of the back surface of the backrest. The pivotable back element is pivotally supported relative to the mounting unit, in particular relative to a bearing point of the seat structure element, in order to form a comfort position and an upright sitting position. The pivotable back element has a load-bearing basic structure, the inner area of ​​which forms the back surface. The pivotable back element preferably has a back frame and a fabric or shell element that forms the back surface and is connected to the back frame. In principle, it is also conceivable for the pivotable back element to be formed by a sandwich-like component. In this case, it is conceivable for the pivotable back element to have no back frame.

[0008] "Upright seating position" should be understood to mean the maximum upright seating position of an aircraft seat that must be assumed for safety reasons, in particular during the takeoff phase, the landing phase, and during turbulence. The upright seating position is embodied in this case as the so-called TTL position (taxi, takeoff, landing). In this case, in the upright seating position, the backrest, in particular the pivotable backrest element, and the seat base of the aircraft seat are substantially perpendicular to each other, preferably at an angle of 95 to 115 degrees. "Comfort position" should be understood to mean, in particular, a backward-inclined seating position of an aircraft seat, in which at least the backrest, in particular the pivotable backrest element, is inclined backward, opposite to the seating direction of the aircraft seat, so that a passenger sitting in the aircraft seat can have a comfortable backward-inclined seating position. In principle, it is also conceivable that in the comfort position, in addition to the pivotable backrest element, the seat base is also inclined in contrast to the upright seating position of the aircraft seat. In the comfort position, the backrest, in particular the pivotable backrest element and the seat bottom, can in particular have an angle relative to one another that is different, particularly advantageously larger, than in the upright seating position (TTL position). In the comfort position, the backrest, in particular the pivotable backrest element, is pivoted backwards by at least 3 degrees, preferably at least 5 degrees, particularly preferably more than 8 degrees from the maximum upright seating position.

[0009] A "restoring module" is to be understood as meaning a module that is preferably configured to apply a restoring force to the backrest, in particular a movably supported backrest element, in order to move the backrest element from a position, in particular a comfort position, to an upright sitting position. For this purpose, the restoring module preferably comprises an element that provides a force for adjusting the backrest, in particular a pivotable backrest element. The element for providing the restoring force is preferably embodied as a spring element.

[0010] The restoring module has a locking unit configured to lock or unlock the restoring module itself and / or the pivotable back element. The locking unit has a locked state and an unlocked state. In the locked state, the locking unit locks the restoring module and / or the pivotable back element, and the restoring module cannot exert a restoring force on the pivotable back element. In the unlocked state, the restoring module is unlocked by the locking unit and can exert a restoring force on the back, in particular the pivotable back element, to adjust the back to an upright seat position. Preferably, the locking unit has at least one locking element that mechanically locks the restoring module itself and / or the pivotable back element. The locking element is preferably embodied as a form-fit and / or pressure-fit element. The locking element is adjustable between a locked position and an unlocked position. Preferably, the locking element is adjustable between the locked position and the unlocked position by a mechanical adjustment element, for example, a Bowden cable. In principle, it is also conceivable that the locking element can be adjusted between a locked position and an unlocked position by an electric actuator, for example, an electromagnetic actuator. For example, it is also conceivable that the locking element is embodied as part of an electronic actuator, in particular an electromechanical actuator. Therefore, it is conceivable that the restoring module and / or the pivotable backrest element can be electrically or electronically locked or unlocked by the locking unit. The phrase "area substantially above the bearing point" should preferably be understood to mean an area that is at least partially, preferably mostly, located above the bearing point. However, in this case, the area can also extend at least partially below the bearing point. At least the locking unit of the restoring module and part of the elements for providing the restoring force are preferably located above the bearing point of the backrest. Particularly preferably, at least one-third, preferably at least one-half, and particularly preferably at least two-thirds of the elements for generating the restoring force, i.e., the spring elements, are also arranged above the bearing point of the seat structure element."Above the bearing point" should be understood to mean the mounting surface, i.e. the side opposite the passenger compartment floor. "Configured" should be understood to mean, in particular, specially designed and / or equipped. That an object is configured for a particular function should be understood to mean, in particular, that the object performs and / or fulfils this particular function in at least one state of use and / or operating condition.

[0011] The aircraft seat is configured as a seat with purely mechanical adjustment. In particular, the adjustment of the backrest, in particular the pivotable backrest element, is effected solely by an adjustment force applied by the passenger and / or the force of a spring element. Preferably, the aircraft seat does not have electromechanical actuators that allow electrical adjustment of the aircraft seat between an upright seating position and a comfort position, in particular electrical adjustment of the aircraft seat, in particular the backrest and / or seat bottom. Preferably, the aircraft seat is not embodied as a business class seat or a first class seat with electronic aircraft seat adjustment.

[0012] The inventive implementation advantageously provides a particularly compact aircraft seating arrangement in which the restoring module is arranged in a particularly advantageous manner. The inventive implementation particularly advantageously provides an aircraft seat that provides a particularly advantageous degree of leg freedom for passengers, particularly passengers sitting at the back of the aircraft seat. The inventive implementation allows the seat back to be embodied particularly narrowly in the area below the bearing points. As a result, the aircraft seat can be embodied particularly narrowly, especially in the knee area, and can have a particularly advantageously large degree of leg freedom.

[0013] Furthermore, it is proposed that the seat structural elements extend upward in their rear regions away from the mounting unit at least substantially to armrest height, and each seat structural element has a bearing point at its rear upper end for supporting a pivotable backrest element. The "rear region of the seat structural element" should be understood to mean the rear region opposite the front end when viewed with respect to the seating direction of the aircraft seat. The "armrest height" should preferably be understood to mean the height at which the aircraft seating arrangement, in particular the armrest of the aircraft seat, is positioned to provide an armrest surface for the passenger. The armrest height is preferably between 550 mm and 700 mm relative to the cabin floor. The armrest height should preferably be understood to mean the height at which the armrest is attached to the mounting unit of the aircraft seat. As a result, a particularly advantageously high pivot point for the backrest, in particular the pivotable backrest element, can be provided, which in turn provides a particularly advantageously large degree of leg freedom, in particular for passengers seated at the rear.

[0014] It is further proposed that the restoring module has at least one spring element configured to provide a restoring force. "Spring element" should preferably be understood to mean an element that provides a spring force in at least one direction. The spring element is preferably embodied as a compression spring. The spring element is configured to exert a compressive force in one direction. In principle, it is conceivable for the spring element to be embodied as a mechanical spring, for example, a spiral spring. In principle, it is also conceivable for the spring element to be embodied as a gas compression spring. Likewise, it is conceivable for the spring element to be embodied as an element other than a gas compression spring or a spiral spring. Preferably, it is conceivable for the spring element to be embodied as a leaf spring element. The spring element preferably has an activated state and an inactivated state. In the activated state, the spring element is configured to provide its spring force as a restoring force. The activated state is preferably embodied as an unlocked state of the locking unit. The inactivated state of the spring element is embodied as a locked state of the spring element. In the deactivated state, the spring element is configured so as not to provide any spring force as a restoring force, which is preferably embodied as a locked state of the locking unit, as a result of which a restoring module for generating the restoring force can be embodied particularly simply.

[0015] It is further proposed that the backrest has a lower backrest element that forms the lower region of the backrest and is fixed to the seat structural element. "Lower backrest element" should preferably be understood to mean an element that rigidly forms the lower part of the backrest facing the seat bottom. The lower backrest element is preferably formed by a shell element. The lower backrest element is preferably formed by a shell element made of fiber-reinforced plastic. In principle, it is also conceivable to form the lower shell element from an aluminum shell or a metal shell made of another metal, in particular a light metal. The lower backrest element is preferably embodied as a separate element. The lower backrest element is preferably rigidly, i.e., immovably, fixed to the seat structural element. In principle, it is also conceivable that the lower backrest element is formed integrally with the seat shell of the seat bottom. As a result, the backrest can be embodied particularly advantageously and lightly.

[0016] It is further proposed that the lower back element extends from the height of the at least one cross beam to a height of 450 mm to 700 mm, measured from the mounting surface. The height of the lower back element is measured here on a vertical axis perpendicular to the mounting surface. Preferably, the back element extends to a height of 500 mm to 650 mm. This allows for a particularly advantageous implementation of the back element.

[0017] It is further proposed that the spring element be embodied as a leaf spring element and be configured to be attached to the lower backrest element or the mounting unit. The spring element embodied as a leaf spring element is preferably arranged in the upper region of the lower backrest element. The spring element embodied as a leaf spring element is preferably attached to the upper half, preferably the upper third, of the lower backrest element. "Attached" should preferably be understood to mean fixedly connected or abutting. The spring element embodied as a leaf spring element is attached to the lower backrest element by a first end. The spring element embodied as a leaf spring element is preferably attached to the pivotable backrest element by a second end. The spring element embodied as a leaf spring element can preferably be directly or indirectly connected to the pivotable backrest element or the lower backrest element. Preferably, the restoring module has a first fastening unit for attaching the spring element embodied as a leaf spring element to the pivotable backrest element. Preferably, the restoring module has a second fastening unit for attaching the leaf spring element to the lower backrest element. Preferably, the first fastening unit or the second fastening unit is optionally embodied as a floating bearing, via which the leaf spring element can move relative to the pivotable backrest element or the lower backrest element in at least one direction. In principle, it is also conceivable for both fastening units to be embodied as floating bearings. In principle, it is also conceivable for the spring element embodied as a leaf spring element to be attached to a mounting unit, for example a transverse element or a seat structure element. "Leaf spring element" should preferably be understood to mean an elongated spring element configured to provide a spring force in a tensioned state that is configured substantially perpendicular to the main extension direction of the leaf spring element. As a result, the spring elements of the restoring module can be embodied in a particularly simple and space-saving manner.

[0018] Furthermore, it is proposed that the backrest has a cross beam in the region above the bearing point, and that a spring element embodied as a leaf spring element is attached to the cross beam to transmit the restoring force to the pivotable backrest element. The spring element embodied as a leaf spring element may be rigidly connected to the cross beam or may be embodied integrally with the cross beam. In principle, it is also conceivable that the spring element embodied as a leaf spring element is movably, for example slidably, attached to the cross beam. Preferably, the connection between the spring element embodied as a leaf spring element and the cross beam has at least one degree of freedom. As a result, the introduction of the restoring force into the backrest, especially the pivotable backrest element, can be particularly advantageous.

[0019] It is further proposed that the lower back element has, at its upper end, an upper lip extending in a region above the bearing point for supporting the back. "Lip" should be understood to mean a region extending, preferably at least partially, from a region, in particular away from the upper edge of the back element. The lip preferably extends over at least a partial region of the upper edge of the back element. The lip is preferably located in the center of the upper edge of the back element. In principle, it is also conceivable for the lip to extend over the entire width of the upper edge of the back element. The lip is preferably formed integrally with the remainder of the lower back element. The lip is formed integrally with the back element formed by a shell element. The lip has a higher flexibility than the remainder of the back element. The lip is preferably formed by fewer layers than the remainder of the back element formed as a shell element. As a result, a particularly advantageous transition between the lower back element and the cover or shell element of the upper pivotable back element can be provided.

[0020] It is further proposed that the pivotable back element comprises a back frame and a fabric clamped to the back frame or a shell element connected to the back frame. The "back frame" is understood to mean a rigid frame, preferably extending in at least three directions and centered around a fabric forming the back surface. The "fabric" is understood to mean a fabric tensioned in a central region fixed by the back frame and forming the back surface in the tensioned state. The back frame with its cover forms a pivotally supported upper back element. This allows for a particularly simple and lightweight design of the back.

[0021] It is further proposed that the restoring module has a spring element embodied as a gas pressure spring and arranged in the area above the bearing point, so that the restoring module can be provided with a particularly easy-to-actuate spring element.

[0022] It is further proposed that the restoring module has at least one lever gear configured to transmit a restoring force to the pivotable back element, as a result of which the force transmission of the restoring force can be performed particularly advantageously and advantageously small spring elements can be used.

[0023] It is further proposed that the restoring module has a torsion tube that transmits the restoring force from one side of the backrest to the other. Preferably, the restoring force of the restoring module is transmitted directly to the torsion tube. The torsion tube is configured to be rotated to adjust the backrest, in particular the pivotable backrest element. As a result, the return of the backrest can be particularly advantageously uniform.

[0024] Furthermore, it is proposed that the bearing point for supporting the pivotable backrest element defines a rotation axis located above the knee region of the backrest. The "knee region" is preferably understood to mean the region of the backrest where the knees of a passenger sitting at the back of an aircraft seat are located. The knee region is preferably embodied as a region extending from the lower end of the backrest to at least 650 mm, particularly preferably 700 mm, above the mounting surface. The knee region is preferably embodied as a region of the backrest between 400 mm and 700 mm, particularly preferably between 450 mm and 650 mm, measured from the mounting surface. As a result, a particularly advantageous knee region can be provided for a passenger sitting at the back of an aircraft seat.

[0025] Furthermore, it is proposed that the spring element embodied as a leaf spring element for providing the restoring force is formed integrally with the lower back element, as a result of which the spring element formed as a leaf spring element can be embodied particularly simply.

[0026] It is further proposed that the spring element for generating the restoring force be at least partially integrally formed with the pivotable backrest element. "Integral" should be understood to mean, in particular, at least bondedly connected, for example, by welding, adhesive bonding, injection molding, and / or another process deemed convenient by those skilled in the art, and / or preferably integrally formed, for example, by casting and / or by a single-component or multi-component injection molding method, preferably from a single blank. The fact that the spring element embodied as a leaf spring element is at least partially integrally formed with the pivotable backrest element should be understood to mean that preferably, at least one partial region of the spring element embodied as a leaf spring element is formed by the pivotable backrest element. As a result, the backrest can be embodied particularly narrow in the region of the lower backrest element.

[0027] The aircraft seating arrangement according to the present invention should not be limited herein to the applications and embodiments described above, and in particular, the aircraft seating arrangement according to the present invention may have a different number of individual elements, components and units than those mentioned herein in order to perform the functions described herein.

[0028] Further advantages will be gained from the following description of the drawings. Eleven exemplary embodiments of the present invention are shown in the drawings. These drawings, the description, and the claims include numerous feature combinations. Those skilled in the art will also be able to appropriately consider these features individually and combine them to form further suitable combinations.

[0029] The drawings are as follows: [Brief explanation of the drawings]

[0030] [Figure 1] 1 shows a schematic diagram of an aircraft seat row with an aircraft seat arrangement in a first exemplary embodiment with a backrest with an upper backrest pivot point and a restoring module with spring elements designed as leaf spring elements. [Figure 2] 1 shows a schematic rear view of an aircraft seat row with a restoring module and spring elements designed as leaf spring elements; [Figure 3] 1 shows a schematic side view of two rows of aircraft seats with pivotable seatback elements in an upright seating position and a comfortable position. [Figure 4] 1 shows a detailed view of the mounting of a spring element designed as a leaf spring element by means of a fastening unit. [Figure 5] 1 shows a schematic diagram of an aircraft seat row with an aircraft seat arrangement in a second exemplary embodiment with a backrest with an upper backrest pivot point having fabric and a restoring module with spring elements designed as leaf spring elements. [Figure 6] 1 shows a schematic rear view of an aircraft seat with a covered back element with fabric and a restoring module with spring elements designed as leaf spring elements. [Figure 7] 4 shows a schematic view of a pivotable backrest element forming a spring element designed as a leaf spring element in a third exemplary embodiment of an aircraft seating arrangement; [Figure 8] 10 shows a schematic view of an aircraft seating arrangement in a fourth exemplary embodiment with a restoring module having a spring element designed as a leaf spring element formed by a lower seat back element. [Figure 9] 10 shows a schematic diagram of an aircraft seat arrangement in a fifth exemplary embodiment with a restoring module having a spring element designed as a gas pressure spring and a lever gear. [Figure 10] 1 shows a schematic detail of a pivotable backrest element with a spring element designed as a gas pressure spring and a lever gear. [Figure 11] 1 shows a schematic detail of a restoring module with a spring element designed as a gas pressure spring and a lever gear. [Figure 12] 10 shows a schematic diagram of an aircraft seat arrangement in a sixth exemplary embodiment with a restoring module having a spring element designed as a gas pressure spring and a lever gear with a torsion tube. [Figure 13] 1 shows a schematic detail view of the pivotable back element in an upright seating position. [Figure 14] 1 shows a schematic detail of a pivotable back element in a comfort position. [Figure 15] 10 shows a schematic diagram of an aircraft seating arrangement in a seventh exemplary embodiment with a pivotable backrest with a lower backrest pivot point and a restoring module with spring elements designed as leaf spring elements. [Figure 16] 10 shows a schematic diagram of an aircraft seating arrangement in an eighth exemplary embodiment with a seat shell element forming a seat bottom and a lower backrest element and a restoring module with a spring element designed as a leaf spring element. [Figure 17] 13 shows a schematic diagram of an aircraft seat row with an aircraft seat arrangement in a ninth exemplary embodiment, with a seat back having an upper seat back pivot point and a restoring module. [Figure 18]13 shows a schematic rear view of an aircraft seat in a ninth exemplary embodiment. [Figure 19] FIG. 13 shows a schematic side view of an aircraft seat in a ninth exemplary embodiment. [Figure 20] 1 shows a schematic view of an upper backrest element with a restoring module having two spring elements designed as spiral springs. [Figure 21] 13 shows a schematic view of an upper backrest element of an aircraft seat arrangement in a tenth exemplary embodiment with a restoring module having two spring elements designed as torsion bars. [Figure 22] FIG. 19 shows a highly simplified view of a lower back element of an aircraft seat arrangement in an eleventh exemplary embodiment. DETAILED DESCRIPTION OF THE INVENTION

[0031] 1 to 4 show an aircraft seating arrangement in a first exemplary embodiment. In this case, the aircraft seating arrangement is part of an aircraft seat 10a. In an installed state, the aircraft seat 10a is installed in a cabin of an aircraft. In an installed state, the aircraft seat 10a is configured to be fixedly installed on a cabin floor of the aircraft cabin. The aircraft seating arrangement has a mounting unit 12a. The aircraft seat 10a can be installed on a cabin floor of the aircraft cabin by means of the mounting unit 12a. The cabin floor forms a mounting surface. The aircraft seat 10a is formed as part of an aircraft seat row 14a. Preferably, the aircraft seat 10a is formed as part of an aircraft seat row 14a including a plurality of aircraft seats 10a. As an example, the aircraft seat row 14a is shown in the figures having two aircraft seats 10a, 16a. The illustrated aircraft seat row 14a includes a second aircraft seat 16a. The further aircraft seat 16a is arranged adjacent to the first aircraft seat 10a. The second aircraft seat 16a is preferably configured identically to the first aircraft seat 10a, so only one aircraft seat 10a will be described in more detail below. In principle, it is also conceivable that the aircraft seat row 14a has three or more aircraft seats 10a, 16a. In this case, the mounting unit 12a is configured as a common mounting unit 12a for the aircraft seats 10a, 16a of the aircraft seat row 14a. The mounting unit 12a includes two seat legs 18a, 20a. Each of the seat legs 18a, 20a is connected to a fixed rail fixedly connected to the cabin floor via mounting fixtures (not shown in detail). The mounting fixtures can be fixedly locked into the fixed rails.

[0032] The mounting unit 12a has two cross beams 22a, 24a. The cross beams 22a, 24a are embodied as support tubes. The front cross beam 22a is arranged in the front region of the aircraft seat 10a. The rear cross beam 24a is arranged in the rear region of the aircraft seat 10a. The cross beams 22a, 24a extend in the transverse direction of the aircraft seat 10a. The cross beams 22a, 24a extend over at least substantially the entire transverse range of all aircraft seats 10a in the aircraft seat row 14a. The aircraft seat arrangement has two seat structural elements 26a, 28a. The two seat structural elements 26a, 28a are each arranged on one side of a seating area 30a of the aircraft seat arrangement. The two seat structural elements 26a, 28a are each arranged laterally with respect to the seating area 30a formed by the aircraft seat 10a. The seat structural elements 26a, 28a are embodied as seat dividers. The seat structural elements 26a, 28a are arranged on the cross beams 22a, 24a. The seat structural elements 26a, 28a are fixed to the cross beams 22a, 24a at a lateral distance from each other. The seat structural elements 26a, 28a are connected to the cross beams 22a, 24a so that their positions are fixed. The seat structural elements 26a, 28a are each connected at their front ends to the front cross beam 22a. In this case, the seat structural elements 26a, 28a are preferably connected to the front cross beam 22a in a force-fit and / or form-fit manner. The seat structural elements 26a, 28a are embodied substantially in an L-shape. Each of the seat structural elements 26a, 28a has a first partial region that is oriented substantially horizontally in the installed state. Each of the seat structural elements 26a, 28a has a second partial region that is oriented substantially vertically in the mounted state. The second partial region of the seat structural elements 26a, 28a is disposed in the rear region of the aircraft seat 10a. The second partial region of the seat structural elements 26a, 28a extends to the rear end of the seat structural elements 26a, 28a. The second partial region of the seat structural elements 26a, 28a forms the rear region of the seat structural elements 26a, 28a. Therefore, the rear regions of the seat structural elements 26a, 28a extend upward away from the mounting unit 12a, particularly the mounting surface.The seat structural elements 26a, 28a extend upward in their rear regions substantially up to the armrest height X. The seat structural elements 26a, 28a extend up to the armrest height X of the aircraft seat 10a. The armrest height X is 650 mm. In principle, it is conceivable that the armrest height X is preferably in the range of 500 mm to 700 mm.

[0033] The seat structural elements 26a, 28a embodied as seat dividers are configured, at least in part, for the purpose that different components of the corresponding aircraft seats 10a, 16a are fastened to the seat structural elements 26a, 28a, as will be explained in more detail below. In principle, it is also conceivable that the mounting unit 12a does not have seat structural elements 26a, 28a or has seat structural elements 26a, 28a embodied differently, and that the corresponding components of the aircraft seats 10a, 16a are attached differently to the mounting unit 12a.

[0034] The aircraft seating arrangement comprises a seat bottom 32a. The seat bottom 32a forms the seating area 30a. The seat bottom 32a forms the seating surface of the aircraft seat 10a. The seat bottom 32a has a body and an upholstery element fixedly attached to the body. The upholstery element forms the seating surface of the aircraft seat 10a. The seat bottom 32a is attached to the mounting unit 12a. The seat bottom 32a is attached, inter alia, to the cross beams 22a, 24a. The seat bottom 32a is connected to the seat back 34a. The seat bottom 32a is directly connected to the seat back 34a.

[0035] The aircraft seating arrangement includes a seat back 34a. In this case, the seat back 34a is configured so that a person seated in an aircraft seat 10a, of which the aircraft seating arrangement is a part, can rest their back against the seat back 34a. The seat back 34a preferably has an upholstery element, not shown in detail. The seat back 34a forms a seat back contact surface. The seat back 34a is arranged at the rear end of the seat bottom 32a. The seat back 34a is pivotally arranged with respect to the mounting unit 12a. The seat back 34a is attached to the seat structural elements 26a, 28a. In this case, the aircraft seat 10a forms a seating direction. The seating direction is defined as the direction in which a passenger sits in the aircraft seat 10a. The seating direction extends perpendicular to the back surface of the seat back 34a and parallel to the mounting surface toward the front end of the seat bottom 32a.

[0036] The backrest 34a is pivotally embodied. The backrest 34a is configured to pivot between an upright seating position and a comfortable position. The backrest 34a is configured to pivot relative to the mounting unit 12a. The backrest 34a is pivotable relative to the seat structural elements 26a, 28a. The backrest 34a has a pivotable backrest element 36a. The pivotable backrest element 36a is pivotally supported by the mounting unit 12a. The pivotable backrest element 36a is pivotally attached to the seat structural elements 26a, 28a. The seat structural elements 26a, 28a have bearing points 38a, 40a, respectively, for supporting the backrest 34a. The bearing points 38a, 40a are configured so that the pivotable backrest element 36a is supported by the bearing points 38a, 40a. The pivotable backrest element 36a is pivotally mounted to the seat structural elements 26a, 28a via bearing points 38a, 40a. The bearing points 38a, 40a are embodied as bearing receptacles. The bearing points 38a, 40a define the position, particularly the height, of a rotation axis 44a about which the backrest 34a, particularly the pivotable backrest element 36a, is pivotally supported. In FIG. 3, which shows a side view of the aircraft seat 10a, the backrest 34a is shown schematically in dashed lines in a comfort position. The pivotable backrest element 36a is shown in dashed lines in FIG. 3 as the pivotable backrest element 36a' in a comfort position. The pivotable backrest element 36a' is pivoted to its comfort position approximately 10 degrees rearward, opposite the seating direction, from an upright seating position. In principle, it is also conceivable for the pivotable backrest element 36a' to be pivoted backwards by only 5 degrees or even 8 degrees from the upright seating position in the comfort position.

[0037] The aircraft seating arrangement includes a bearing device 42a. The bearing device 42a is configured to pivotally support the seat back 34a between an upright seating position and a comfortable position. The bearing device 42a is configured to pivotally support the pivotable seat back element 36a between the upright seating position and a comfortable position. The bearing device 42a defines a rotation axis 44a. The pivotable seat back element 36a is pivotable about the rotation axis 44a by means of the bearing device 42a. The bearing device 42a includes two bearing bolts 46a, 48a. The bearing bolts 46a, 48a define the rotation axis 44a. Each of the bearing bolts 46a, 48a is connected to one of the bearing points 38a, 40a of one of the seat structural elements 26a, 28a. Preferably, the bearing bolts 46a, 48a are rotatably fixedly attached to the respective bearing points 38a, 40a. The pivotable backrest element 36a is rotatably supported on the bearing bolts 46a, 48a. The pivotable backrest element 36a is preferably pivotally supported on the bearing bolts 46a, 48a via plain bearings. In principle, it is also conceivable that the pivotable backrest element 36a is rotatably supported on the bearing bolts 46a, 48a by means of roller bearings. In principle, it is also conceivable that the bearing bolts 46a, 48a are rotatably attached to the respective bearing points 38a, 40a of the seat structure elements 26a, 28a via suitable bearing arrangements.

[0038] The pivotable back element 36a has a back frame 60a. The back frame 60a forms the load-bearing structure of the pivotable back element 36a. The back frame 60a is embodied as a perimeter frame. The back frame 60a is preferably substantially U-shaped. The back frame 60a has two side frame elements and an upper frame element connecting the two side frame elements at the upper end of the back frame 60a. The back frame 60a preferably has an open lower end. The lower end of the back frame 60a forms the lower end of the pivotable back element 36a. The bearing bolts 46a, 48a are attached to the back frame 60a of the pivotable back element 36a at the lower ends of the back frame 60a of the opposing side frame elements, respectively.

[0039] The pivotable backrest element 36a has a shell element 62a. The shell element 62a is embodied as a plate-like element. The shell element 62a is made of fiber-reinforced plastic. The shell element 62a is made of, for example, GRP or CFRP. The shell element 62a is configured to form the back contact surface of the pivotable backrest element 36a. The shell element 62a is arranged in an inner region of the pivotable backrest element 36a that is clamped by the backrest frame 60a. The shell element 62a is fixedly connected to the backrest frame 60a of the pivotable backrest element 36a. The shell element 62a is fixedly connected, at least in partial regions, to the lateral frame elements of the backrest frame 60a. The shell element 62a is preferably attached at its upper end to the upper frame element of the backrest frame 60a. Shell element 62a preferably defines the back contour of pivotable back element 36a and is configured to receive the upholstery element of back element 34a.

[0040] The pivotable back element 36a has a cross beam 66a. The cross beam 66a is arranged in the region above the bearing points 38a, 40a. Viewed vertically, the cross beam 66a is arranged approximately in the center of the pivotable back element 36a. The cross beam 66a is attached between the lateral frame elements of the back frame 60a. The cross beam 66a extends between the lateral frame elements of the back frame 60a. The cross beam 66a is in each case fixedly connected to the respective lateral frame element of the back frame 60a. The cross beam 66a is preferably screwed to the lateral frame elements of the back frame 60a. In principle, it is also conceivable that the cross beam 66a is adhesively bonded to the lateral frame elements of the back frame 60a or otherwise connected by form-fit, press-fit, and / or cohesive means. The cross beam 66a is preferably configured to reinforce the back frame 60a, in particular the entire pivotable back element 36a. Preferably, the cross beam 66a can be configured so that further mounting elements of the back 34a are fixed to the cross beam 66a. For example, it is conceivable that a pivotable table element, a cup holder, a tablet holder or a tall document bag is attached to the back 34a, in particular to the cross beam 66a of the pivotable back element 36a.

[0041] The backrest 34a is designed as a backrest with a high backrest pivot point. The backrest pivot point is formed by a rotation axis 44a of the bearing device 42a. The backrest pivot point, i.e., the rotation axis 44a of the bearing device 42a, is located above the knee area 50a of the aircraft seat 10a. The knee area 50a of the aircraft seat 10a starts from the cabin floor and extends to a height of 650 mm. The knee area 50a is located as an area where a passenger sitting at the rear of the aircraft seat 10a can place their knees.

[0042] To form high backrest pivot points, the seat structural elements 26a, 28a are formed with bearing points 38a, 40a for supporting the backrest 34a in a high region. The seat structural elements 26a, 28a are formed with bearing points 38a, 40a in each case at their upper ends. The seat structural elements 26a, 28a are formed with bearing points 38a, 40a in a second rear partial region at their upper ends, away from the mounting surface. The bearing points 38a, 40a of the seat structural elements 26a, 28a are located above the knee region 50a. The bearing points 38a, 40a of the seat structural elements 26a, 28a are located at armrest height X. The bearing points 38a, 40a for supporting the pivotable backrest element 36a define a rotation axis 44a that is located above the knee region 50a of the backrest 34a.

[0043] The pivotable backrest element 36a forms the backrest 34a above the bearing points 38a, 40a of the seat structural elements 26a, 28a. The pivotable backrest element 36a forms only the upper region of the backrest 34a. The pivotable backrest element 36a is embodied as an upper backrest element. The pivotable backrest element 36a forms the back contact surface of the backrest 34a in the region above the armrest height X. Preferably, the pivotable backrest element 36a is arranged substantially only in the region above the armrest height X. Only the region for attaching the backrest element 36a to the seat structural elements 26a, 28a extends below the armrest height X.

[0044] The backrest 34a has a lower backrest element 52a. The lower backrest element 52a is rigidly embodied. Preferably, the lower backrest element 52a is immovably embodied. The lower backrest element 52a forms the lower region of the backrest 34a. The lower backrest element 52a forms a backrest contact surface in the lower region of the backrest 34a. The lower backrest element 52a is fixedly fastened to the seat structural elements 26a, 28a. The lower backrest element 52a extends substantially between the height of the cross beams 22a, 24a of the mounting unit 12a and the lower end of the pivotable backrest element 36a. Preferably, the lower backrest element 52a extends to just below the armrest height X. The lower back element 52a extends from the level of the cross beams 22a, 24a to a height of approximately 450mm to 700mm measured from the mounting surface. Preferably, the lower back element 52a extends to a height of 600mm measured from the mounting surface.

[0045] The lower backrest element 52a is formed by a shell element. It is formed by a shell made of fiber-reinforced plastic. For example, it is conceivable for the lower backrest element 52a to be formed by a GRP or CFP shell. The lower backrest element 52a preferably has a slightly curved shape. The lower backrest element 52a is laterally connected to one of the seat structural elements 26a, 28a via two fastening elements 54a in each case. In principle, it is also conceivable for the lower backrest element 52a to be formed at least partially integrally with the seat bottom 32a, in particular the seat shell. In principle, it is also conceivable for the lower backrest element 52a to be formed at least partially or completely by a cover.

[0046] The aircraft seating apparatus includes a restoring module 56a. The restoring module 56a is configured to restore the seat back 34a from a comfortable position to an upright seating position. The restoring module 56a is configured to restore the seat back 34a from a pivoted seating position to an upright seating position. The restoring module 56a is configured to restore the pivotable seat back element 36a. The restoring module 56a is configured to restore the seat back 34a, particularly the pivotable seat back element 36a, to provide a restoring force. The restoring module 56a is configured to restore the seat back 34a to apply a restoring force to the pivotable seat back element 36a. The restoring module 56a is at least substantially disposed in an area above the bearing points 38a, 40a of the seat structural elements 26a, 28a. The restoring module 56a is disposed at least substantially above the armrest height X, i.e., on the side away from the mounting surface. The restoring module 56a is positioned at least mostly above the knee region 50a of the backrest 34a. As a result of this positioning of the restoring module 56a, the knee region 50a of the backrest 34a can preferably remain substantially free of components of the restoring module 56a. In particular, the relatively large components of the restoring module 56a can be advantageously positioned above the armrest height X and therefore outside the knee region 50a of the backrest 34a.

[0047] The restoring module 56a includes a spring element 58a for providing a restoring force. In principle, it is also conceivable that the restoring module 56a includes a plurality of spring elements 58a for providing the restoring force. The spring element 58a is configured to apply a spring force to the pivotable backrest element 36a to pivot the pivotable backrest element 36a toward its upright seating position. The spring force of the spring element 58a forms the restoring force of the restoring module 56a. The spring element 58a is operatively disposed between the pivotable backrest element 36a and the mounting unit 12a. The spring element 58a is configured to be supported on a first side by the mounting unit 12a. The spring element 58a is configured to be supported on a second side by the backrest 34a, particularly by the pivotable backrest element 36a. As a result, the spring element 58a can transmit a restoring force from the installed mounting unit 12a to the pivotable back element 36a.

[0048] The spring element 58a is embodied as a leaf spring element. The spring element 58a embodied as a leaf spring element is embodied as an elongated component. The spring element 58a embodied as a leaf spring element is operatively arranged between the lower backrest element 52a and the pivotable backrest element 36a. The spring element 58a embodied as a leaf spring element is attached to the lower backrest element 52a by its first lower end. The spring element 58a embodied as a leaf spring element is supported by its lower end on the lower backrest element 52a. The spring element 58a embodied as a leaf spring element is attached to an upper region of the lower backrest element 52a. Thus, the spring element 58a embodied as a leaf spring element partially extends in a region below the rotation axis 44a, i.e., within the armrest height X. The spring element 58a, embodied as a leaf spring element, is attached by its second upper end to the pivotable backrest element 36a. The spring element 58a, embodied as a leaf spring element, is supported by its second upper end on the pivotable backrest element 36a. The spring element 58a, embodied as a leaf spring element, preferably extends within a central region of the pivotable backrest element 52a.

[0049] To attach the spring element 58a embodied as a leaf spring element to the pivotable backrest element 36a, the restoring module 56a has a first fastening unit 64a. The spring element 58a embodied as a leaf spring element is fixedly attached to the pivotable backrest element 36a by the first fastening unit 64a. The spring element 58a embodied as a leaf spring element is rigidly and fixedly connected to the pivotable backrest element 36a by the first fastening unit 64a. In principle, it is also conceivable that the spring element 58a embodied as a leaf spring element is movably connected to the pivotable backrest element 36a with at least one degree of freedom by the first fastening unit 64a. Furthermore, it is equally conceivable that the spring element 58a embodied as a leaf spring element simply abuts with its upper end against the pivotable backrest element 36a. In this case, it is conceivable that the spring element 58a embodied as a leaf spring element slides by its upper end on the pivotable backrest element 36a, in particular on the rear side of the shell element 62a. To transmit the restoring force, the spring element 58a formed as a leaf spring element is attached to a cross beam 66a. The spring element 58a embodied as a leaf spring element is attached directly to the cross beam 66a via a fastening unit 64a. The cross beam 66a allows the restoring force provided by the spring element 58a embodied as a leaf spring element to be transmitted uniformly to both sides of the pivotable backrest element 36a.

[0050] To attach the spring element 58a embodied as a leaf spring element to the lower backrest element 52a, the restoring module 56a includes a second fastening unit 68a. The spring element 58a embodied as a leaf spring element is fixedly attached to the lower backrest element 52a via the second fastening unit 68a. The spring element 58a embodied as a leaf spring element is movably attached to the lower backrest element 52a via the second fastening unit 68a. The second fastening unit 68a includes a fastening body 70a. The fastening body 70a is fixedly attached to the rear side of the lower backrest element 52a. The fastening body 70a of the second fastening unit 68a includes a receptacle configured to receive the spring element 58a embodied as a leaf spring element. The spring element 58a embodied as a leaf spring element is displaceably supported in the receptacle of the fastening body 70a. The receptacle of the fastening body 70a defines a displacement axis along which the spring element 58a, embodied as a leaf spring element, is displaceably supported. The displacement axis is vertical in the mounted state. The fastening unit 68a includes two fastening elements 72a, 74a that attach the spring element 58a, embodied as a leaf spring element, to the fastening body 70a. The fastening elements 72a, 74a are embodied as fastening screws. In principle, it is also conceivable to embody the fastening elements 72a, 74a in different ways. The spring element 58a, embodied as a leaf spring element, has two through-grooves 76a, 78a for attachment to the fastening body 70a. To attach the spring element 58a, embodied as a leaf spring element, the fastening elements 72a, 74a are guided through the through-grooves 76a, 78a.

[0051] The spring element 58a, embodied as a leaf spring element, is at least partially integrated into the pivotable backrest element 36a. The spring element 58a, embodied as a leaf spring element, is partially integrated into the shell element 62a of the pivotable backrest element 36a. The spring element 58a, embodied as a leaf spring element, is configured to be received within the shell element 62a of the pivotable backrest element 36a. The shell element 62a of the pivotable backrest element 36a has a central region 80a. The central region 80a is laterally disposed centrally between the lateral frame elements of the backrest frame 60a. The spring element 58a, embodied as a leaf spring element, is at least partially integrated into the central region 80a of the shell element 62a. The shell element 62a has a receiving region 82a for the spring element 58a, embodied as a leaf spring element, in its rear central region 80a. The receiving area 82a extends from the lower end of the shell element 62a to the area below the cross beam 66a in the central area 80a. In principle, it is also conceivable that the spring element 58a embodied as a leaf spring element abuts only the rear side of the shell element 62a in the central area 80a. It is also conceivable that the spring element 58a embodied as a leaf spring element does not come into contact with the shell element 62a in the central area 80a.

[0052] The pivotable backrest element 36a has elastic ribs 84a, 86a in its lower region, each extending laterally outward from the central region 80a. In the exemplary embodiment, three elastic ribs 84a, 86a are shown per side by way of example. Each elastic rib 84a, 86a extends from the central region 80a to a lateral frame element of the backrest frame 60a. The ribs 84a, 86a located adjacent to one side of the central region 80a are spaced apart vertically. Each elastic rib 84a, 86a is elastically deformable independently of the other. Each elastic rib 84a, 86a has a shape that curves forward in the seating direction. The elastic ribs 84a, 86a are preferably formed integrally with the shell element 62a, particularly with the central region 80a. In principle, it is equally conceivable that the elastic ribs 84a, 86a are formed at least partially separate from the shell element 62a. In this case, it is particularly conceivable that the ribs 84a, 86a are partially formed as separate elements connected to the shell element 62a, in particular to the central region 80a of the shell element 62a. In this case, it is particularly conceivable that the separately formed ribs 84a, 86a can be attached to the shell element 62a in a detachable manner. As a result, the ribs 84a, 86a can advantageously be easily replaced if damaged. Preferably, detachably formed ribs 84a, 86a allow ribs 84a, 86a with different stiffnesses to be attached particularly easily to different points on the pivotable backrest element 36a. As a result, the pivotable backrest element 36a can be embodied particularly easily with different stiffnesses in different partial regions. Preferably, the differently formed ribs 84a, 86a can be easily arranged at different points on the pivotable back element 36a by means of the detachably formed ribs 84a, 86a, which allows the pivotable back element 36a to be embodied with different or adaptable ergonomics in a particularly easy manner.

[0053] The restoring module 56a has a locking unit 88a. The locking unit 88a is configured to lock or unlock the restoring module 56a. The locking unit 88a is configured to lock the backrest 34a, i.e., the pivotable backrest element 36a, at least in the upright sitting position and the comfort position. Preferably, it is also conceivable that the locking unit 88a is configured to lock the pivotable backrest element 36a in a further position. In this case, the further position of the pivotable backrest element 36a is particularly embodied as a pivot position between the upright sitting position and the comfort position. The locking unit 88a has a locked state and an unlocked state. In the locked state, the locking unit 88a locks the restoring module 56a, and the restoring module 56a cannot apply a restoring force to the pivotable backrest element 36a. In the unlocked state, the locking unit 88a unlocks the restoring module 56a, allowing the restoring module 56a to apply a restoring force to the pivotable backrest element 36a. The locking unit 88a is configured to lock the pivotable backrest element 36a in a current position in the locked state. In the locked state of the locking unit 88a, the pivotable backrest element 36a is locked in its current position. In the locked state of the locking unit 88a, the pivotable backrest element 36a is not pivotable. In the locked state of the locking unit 88a, the pivotable backrest element 36a is preferably fixed relative to the mounting unit 12a. Preferably, the pivotable backrest element 36a is fixedly fixed relative to the seat structure elements 26a, 28a in the locked state of the locking unit 88a.

[0054] The locking unit 88a is preferably operatively arranged between the pivotable backrest element 36a, in particular the backrest frame 60a, and one of the seat structural elements 26a, 28a. In principle, it is equally conceivable for the locking unit 88a to be operatively arranged between the backrest frame 60a and the two seat structural elements 26a, 28a. The locking unit 88a preferably has at least one locking element. The locking element of the locking unit 88a is preferably configured to lock the restoring module 56a in the locked state of the locking unit 88a. The locking element of the locking unit 88a is preferably configured to directly lock the pivotable backrest element 36a. The locking element of the locking unit 88a is configured to form-fit lock the pivotable backrest element 36a. The locking element of the locking unit 88a is configured to form-fit engage with a corresponding form-fit element of the locking unit 88a in the locked state of the locking unit 88a. The locking unit 88a has a corresponding form-fitting element for each lockable position, i.e., for the upright seating position and the comfort position of the pivotable backrest element 36a. In principle, it is also conceivable that the locking unit 88a is configured to lock the pivotable backrest element 36a in a force-fit manner and to have at least one force-fitting element for this purpose. In principle, it is equally conceivable that the locking unit 88a is configured to lock the pivotable backrest element 36a in a force-fit and form-fit manner. The locking unit 88a has an actuating element 90a by which the locking unit 88a can be adjusted from a locked state to an unlocked state. The actuating element 90a is configured to be actuated by a passenger sitting in the aircraft seat 10a. The actuating element 90a is preferably embodied as a push button. The actuating element 90a is coupled to the locking element of the locking unit 88a via a suitable connecting element, in particular a Bowden cable, for adjusting the locking element between its locked and unlocked positions.

[0055] The locking unit 88a is arranged above the knee region 50a of the backrest 34a. The locking unit 88a is preferably arranged in the region above the bearing points 38a, 40a of the seat structural elements 26a, 28a. The locking unit 88a is preferably arranged substantially, i.e., mostly, above the armrest height X. The locking unit 88a is arranged in the region of the pivotable backrest element 36a. The locking unit 88a is preferably arranged outside the region of the lower backrest element 52a. In particular, the locking elements of the locking unit 88a for locking the pivotable backrest element 36a and corresponding form-fitting elements are arranged above the bearing points 38a, 40a and the armrest height X. The individual components of the locking unit 88a, in particular the actuating element 90a and the Bowden cable, can also be arranged partially below the armrest height X.

[0056] The aircraft seating device includes two armrests 92a, 94a. The armrests 92a, 94a are part of an aircraft seat 10a in an aircraft seat row 14a. The armrests 92a, 94a are each arranged laterally relative to a seating area 30a of the aircraft seat 10a. The armrests 92a, 94a are attached at armrest height X. The armrests 92a, 94a are attached to a mounting unit 12a so that their rear ends are at armrest height X. The armrests 92a, 94a are attached via seat structural elements 26a, 28a. The armrests 92a, 94a are attached to the aircraft seat 10a via bearing points 38a, 40a of the seat structural elements 26a, 28a, which are embodied as seat dividers. The armrests 92a, 94a are attached to the seat structural elements 26a, 28a via bearing bolts 46a, 48a of a bearing device 42a of a seat back 34a. The armrests 92a, 94a are attached to the seat structural elements 26a, 28a via the same bearing bolts 46a, 48a as the pivotable backrest element 36a. The armrests 92a, 94a are preferably pivotally attached to the seat structural elements 26a, 28a. The armrests 92a, 94a are pivotable about the same axis of rotation 44a as the pivotable backrest element 36a. In principle, it is also conceivable for the armrests 92a, 94a to be rotatably fixedly attached to the seat structural elements 26a, 28a. The actuating element 90a of the locking unit 88a is preferably introduced into one of the armrests 92a, 94a.

[0057] Alternatively, the spring element 58a embodied as a leaf spring element can be attached directly to the mounting unit 12a. In this case, the spring element 58a embodied as a leaf spring element can be attached directly to the rear cross beam 24a of the mounting unit 12a, rather than to the lower backrest element 52a. In this case, the spring element 58a embodied as a leaf spring element can be arranged in a lateral region directly in the region of one of the seat structural elements 26a, 28a arranged on the lateral side. As a result, the central region of the knee region 50a of the backrest 34a can advantageously be embodied without the spring element 58a.

[0058] Ten further exemplary embodiments of the present invention are shown in Figures 5 to 22. The following description and drawings are substantially limited to the differences between the exemplary embodiments, and for components having the same designations, particularly the same reference numerals, reference can essentially be made to the drawings, particularly Figures 1 to 4, and / or descriptions of the other exemplary embodiments. To distinguish the exemplary embodiments, the reference numerals of the exemplary embodiments in Figures 1 to 4 are followed by the letter a. In the exemplary embodiments in Figures 5 to 22, the letter a is replaced by letters b to k.

[0059] 5 and 6 show a second exemplary embodiment of an aircraft seating arrangement according to the present invention. In this case, the aircraft seating arrangement is part of an aircraft seat 10b. In the installed state, the aircraft seat 10b is installed in the cabin of an aircraft. The aircraft seating arrangement has a mounting unit 12b. The aircraft seat 10b can be installed on the cabin floor of the aircraft cabin by means of the mounting unit 12b. The aircraft seat 10b is formed as part of an aircraft seat row 14b. The aircraft seat row 14b shown as an example has a second aircraft seat 16b. In this case, the mounting unit 12b is formed as a common mounting unit for the aircraft seats 10b, 16b of the aircraft seat row 14b. The mounting unit 12b has two seat legs 18b, 20b. The mounting unit 12b has two cross beams 22b, 24b.

[0060] The aircraft seating arrangement includes two seat structural elements 26b, 28b. The two seat structural elements 26b, 28b are each arranged on one side of a seating area 30b of the aircraft seating arrangement. The two seat structural elements 26b, 28b are each arranged laterally with respect to the seating area 30b formed by the aircraft seat 10b. The seat structural elements 26b, 28b are embodied as seat dividers. The seat structural elements 26b, 28b are arranged on the cross beams 22b, 24b. The seat structural elements 26b, 28b are embodied substantially in an L-shape. Thus, the seat structural elements 26b, 28b extend upward in their rear regions away from the mounting unit 12b, in particular the mounting surface. The seat structural elements 26b, 28b extend upward in their rear regions substantially to the armrest height X. The seat structural elements 26b, 28b extend to armrest height X of the aircraft seat 10b.

[0061] The aircraft seating apparatus includes a seat back 34b. The seat back 34b is configured to allow a person seated in an aircraft seat 10b, of which the aircraft seating apparatus is a part, to rest their back against the seat back 34b. The seat back 34b is pivotally disposed relative to the mounting unit 12b. The seat back 34b is attached to the seat structural elements 26b and 28b. The seat back 34b is configured to pivot between an upright seating position and a comfort position. The seat back 34b includes a pivotable backrest element 36b. The pivotable backrest element 36b is pivotally supported by the mounting unit 12b. The pivotable backrest element 36b is pivotally attached to the seat structural elements 26b and 28b. The seat structural elements 26b and 28b have bearing points 38b and 40b, respectively, for supporting the seat back 34b. The bearing points 38b, 40b are configured such that the pivotable back element 36b is supported on the bearing points 38b, 40b.

[0062] The aircraft seating arrangement includes a bearing device 42b. The bearing device 42b is configured to pivotally support the seat back 34b between an upright seating position and a comfortable position. The bearing device 42b is configured to pivotally support the pivotable seat back element 36b between an upright seating position and a comfortable position. The bearing device 42b defines a rotation axis 44b. The pivotable seat back element 36b is pivotable about the rotation axis 44b by the bearing device 42b. The bearing device 42b includes two bearing bolts 46b, 48b. The bearing bolts 46b, 48b define the rotation axis 44b. The bearing bolts 46b, 48b are respectively coupled to one of the bearing points 38b, 40b of one of the seat structural elements 26b, 28b.

[0063] The pivotable back element 36b has a back frame 60b. The back frame 60b forms the load-bearing structure of the pivotable back element 36b. The back frame 60b is embodied as a perimeter frame. The back frame 60b is preferably substantially U-shaped. The back frame 60b has two lateral frame elements and an upper frame element connecting the two lateral frame elements at the upper end of the back frame 60b. The back frame 60b preferably has an open lower end. The lower end of the back frame 60b forms the lower end of the pivotable back element 36b. The bearing bolts 46b, 48b are attached to the back frame 60b of the pivotable back element 36b at the lower end of the back frame 60b of the opposing lateral frame element, respectively.

[0064] The backrest 34b is designed as a backrest with a high backrest pivot point. The backrest pivot point, i.e., the rotation axis 44b of the bearing device 42b, is located above the knee region 50b of the aircraft seat 10b. To form the high backrest pivot point, the seat structural elements 26b, 28b are formed with bearing points 38b, 40b for supporting the backrest 34b in a high region. The bearing points 38b, 40b of the seat structural elements 26b, 28b are located above the knee region 50b. The bearing points 38b, 40b of the seat structural elements 26b, 28b are located at armrest height X.

[0065] In contrast to the first exemplary embodiment, the pivotable back element 36b has a fabric 100b. The fabric 100b is clamped to the back frame 60b. The fabric 100b is formed by a piece of fabric clamped between the lateral frame elements of the back frame 60b. In principle, it is conceivable that the fabric 100b is also attached to the upper frame element of the back frame 60b. The fabric 100b extends from the lower end of the back frame 60b to the upper end region of the back frame 60b.

[0066] The backrest 34b has a lower backrest element 52b. The lower backrest element 52b is rigid. Preferably, the lower backrest element 52b is immovable. The lower backrest element 52b forms the lower region of the backrest 34b. The lower backrest element 52b forms a backrest contact surface in the lower region of the backrest 34b. The lower backrest element 52b is fixedly fastened to the seat structural elements 26b, 28b. The lower backrest element 52b is formed by a shell element. The lower backrest element 52b is formed from fiber-reinforced plastic. Preferably, the lower backrest element 52b is formed from multiple layers of fiber-reinforced plastic. For example, it is conceivable that the lower back element 52b is formed by one or more GRP layers or by one or more CFP layers. The lower back element 52b has a main region 102b. The main region 102b substantially forms the back contact surface of the lower back element 52b and is embodied substantially similarly to the lower back element of the first exemplary embodiment.

[0067] In contrast to the first exemplary embodiment, the lower back element 52b has a lip 104b at its upper end. The lip 104b is directly adjacent to the upper end of the main region 102b of the lower back element 52b. The lip 104b forms the upper end region of the lower back element 52b. The lip 104b is formed integrally with the remainder of the lower back element 52b. The lip 104b is arranged laterally centrally at the upper end of the lower back element 52b. In principle, it is also conceivable for the lower back element 52b to have two or more off-centered lips 104b at its upper end. If the lower back element 52b has multiple lips 104b at its upper end, these lips are preferably arranged symmetrically relative to the central axis of the lower back element 52b. The lip 104b of the lower back element 52b extends into the area above the bearing points 38b, 40b for supporting the pivotable back element 36b. The lip 104b of the lower back element 52b extends into the area behind the pivotable back element 36b, particularly into the area behind the fabric 100b of the pivotable back element 36b. The lip 104b is configured to allow the fabric 100b of the pivotable back element 36b to be attached by its lower edge. The fabric 100b is attached by its lower edge to a front side 106b of the lip 104b of the lower back element 52b. The fabric 100b is preferably removably attached to the front side 106b of the lip 104b by a loop and hook strap. In principle, it is also conceivable that the fabric 100b could be joined to the lip 104b of the lower back element 52b in a different way, for example adhesively bonded.

[0068] The aircraft seating apparatus includes a restoring module 56b. The restoring module 56b is configured to restore the seat back 34b from a comfortable position to an upright seating position. The restoring module 56b is configured to restore the seat back 34b from a pivoted seating position to an upright seating position. The restoring module 56b is at least substantially arranged in an area above the bearing points 38b, 40b of the seat structural elements 26b, 28b. The restoring module 56b is arranged at least substantially above the armrest height X, i.e., on the side facing away from the mounting surface. The restoring module 56b is at least mostly arranged above the knee region 50b of the seat back 34b.

[0069] The restoring module 56b includes a spring element 58b for providing a restoring force. The spring element 58b is configured to apply a spring force to the pivotable backrest element 36b to pivot the pivotable backrest element 36b toward its upright seating position. The spring element 58b is embodied as a leaf spring element. The spring element 58b, embodied as a leaf spring element, is attached by its first lower end to the lower backrest element 52b. The spring element 58b, embodied as a leaf spring element, is attached to an upper region of the lower backrest element 52b. The spring element 58b, embodied as a leaf spring element, is attached below a lip 104b in a main region 102b of the lower backrest element 52b.

[0070] To attach the spring element 58b embodied as a leaf spring element to the pivotable backrest element 36b, the restoring module 56b has a first fastening unit 64b. The spring element 58b embodied as a leaf spring element is fixedly attached to the pivotable backrest element 36b via the first fastening unit 64b. The pivotable backrest element 36b has a cross beam 66b. The cross beam 66b is arranged in an area above the bearing points 38b, 40b. The cross beam 66b is arranged behind the upholstery 100b. The spring element 58b embodied as a leaf spring element is directly attached to the cross beam 66b via the fastening unit 64b. To attach the spring element 58b embodied as a leaf spring element to the lower backrest element 52b, the restoring module 56b has a second fastening unit 68b. The spring element 58b, embodied as a leaf spring element, is fixedly attached to the lower back element 52b via a second fastening unit 68b. The spring element 58b, embodied as a leaf spring element, is movably attached to the lower back element 52b via a second fastening unit 68b.

[0071] The restoring module 56b includes a locking unit 88b. The locking unit 88b is configured to lock or unlock the restoring module 56b. The locking unit 88b is configured to lock the backrest 34b, i.e., the pivotable backrest element 36b, in at least the upright seating position and the comfort position. The locking unit 88b is preferably operatively arranged between the pivotable backrest element 36b, particularly the backrest frame 60b, and one of the seat structural elements 26b, 28b. The locking unit 88b is preferably arranged above the knee region 50b of the backrest 34b. The locking unit 88b is preferably arranged in an area above the bearing points 38b, 40b of the seat structural elements 26b, 28b. The locking unit 88b is preferably arranged substantially, i.e., mostly, above the armrest height X.

[0072] FIG. 7 shows a third exemplary embodiment of an aircraft seating arrangement according to the present invention. The aircraft seating arrangement is a part of an aircraft seat 10c, which is partially illustrated. The aircraft seat 10c is formed substantially identically to the aircraft seat of the first exemplary embodiment from FIGS. 1 to 4 and will therefore not be described in further detail here. The aircraft seating arrangement has a mounting unit, which is not illustrated in more detail. The aircraft seating arrangement has two seat structural elements, which are connected to the mounting unit and are embodied as a seat divider, which is not illustrated in more detail. The seat structural elements extend up to the armrest height X of the aircraft seat 10c.

[0073] The aircraft seating device includes a seat back 34c. The seat back 34c forms a seat back contact surface. The seat back 34c is attached to a seat structural element. The seat back 34c is pivotally embodied. The seat back 34c is configured to pivot between an upright seating position and a comfortable position. The seat back 34c has a pivotable seat back element 36c. The seat back 34c is designed as a seat back with a high seat back pivot point. The seat back pivot point is formed by a rotation axis 44c of a bearing device 42c. The pivotable seat back element 36c is pivotally attached to the seat structural element. The seat structural elements have bearing points 38c, 40c, respectively, for supporting the seat back 34c. The pivotable seat back element 36c has a seat back frame 60c. The back frame 60c forms the load-bearing structure of the pivotable back element 36c. The pivotable back element 36c has a shell element 62c. The shell element 62c is embodied as a plate-like element. The shell element 62c is made of fiber-reinforced plastic. The shell element 62c is made of, for example, GRP or CFRP. The shell element 62c is configured to form the back contact surface of the pivotable back element 36c. The shell element 62c is fixedly connected to the back frame 60c of the pivotable back element 36c. The shell element 62c preferably forms the back contour of the pivotable back element 36c. The back 34c has a lower back element, which is not shown in more detail. The lower back element is likewise formed by a shell element.

[0074] The aircraft seating apparatus includes a restoring module 56c. The restoring module 56c is configured to restore the seat back 34c from a comfort position to an upright seating position. The restoring module 56c is configured to restore the pivotable seat back element 36c. The restoring module 56c is configured to restore the seat back 34c, particularly the pivotable seat back element 36c, to provide a restoring force. The restoring module 56c includes a spring element 58c for providing the restoring force. The spring element 58c is embodied as a leaf spring element. In contrast to the first exemplary embodiment, the spring element 58c embodied as a leaf spring element is at least partially integrally formed with the pivotable seat back element 36c. The spring element 58c embodied as a leaf spring element is integrally formed with a shell element 62c of the pivotable seat back element 36c. The spring element 58c embodied as a leaf spring element is formed by the central region 80c of the shell element 62c. The spring element 58c embodied as a leaf spring element is integrated into the central region 80c of the shell element 62c. The spring element 58c embodied as a leaf spring element is embedded in the fiber-reinforced layer of the shell element 62c. The spring element 58c embodied as a leaf spring element is preferably formed as a leaf spring element that is inserted into the shell element 62c during the manufacturing process. However, in principle, it is also conceivable that the spring element 58c embodied as a leaf spring element is formed in the central region 80c itself by the fiber layer of the shell element 62c.

[0075] The spring element 58c, which is integrally formed with the shell element 62c, can form a lateral reinforcing element 108c at its upper end. The lateral reinforcing element 108c is integrally formed with the spring element 58c and, therefore, with the shell element 62c. Similar to the cross beams of the first exemplary embodiment, the lateral reinforcing element 108c is configured to better introduce a restoring force into the pivotable backrest element 36c. In this exemplary embodiment, the pivotable backrest element 36c preferably does not have a separate cross beam. In principle, it is also conceivable that the spring element 58c embodied as a leaf spring element does not have the lateral reinforcing element 108c. The pivotable backrest element 36c has elastic ribs 84c, 86c in its lower region, each extending laterally outward from the central region 80c. The outwardly extending elastic ribs 84c, 86c may preferably be formed integrally with the spring element 58c, which is likewise embodied as a leaf spring element. To attach the spring element 58c, embodied as a leaf spring element, to the lower backrest element, the restoring module 56c has a fastening unit 68c, embodied similarly to the first exemplary embodiment. The fastening unit 68c is formed at least by through-grooves 76c, 78c, embodied as elongated holes, at the lower end of the spring element 58c.

[0076] The restoring module 56c has a locking unit, not shown in detail here, which is formed in substantially the same manner as in the previously described exemplary embodiment. The locking unit is preferably operatively arranged between the pivotable backrest element 36c, in particular the backrest frame 60c, and one of the seat structural elements. The locking unit is preferably arranged in an area above the bearing point of the seat structural element. The locking unit is preferably arranged substantially, i.e., mostly, above the armrest height X.

[0077] FIG. 8 shows a fourth exemplary embodiment of an aircraft seating arrangement according to the present invention. The aircraft seating arrangement is a part of an aircraft seat 10d, which is partially illustrated. The aircraft seating arrangement has a mounting unit 12d. The aircraft seat 10d can be mounted to the cabin floor of an aircraft cabin by means of the mounting unit 12d. The mounting unit 12d has two cross beams 24d. The aircraft seating arrangement has two seat structural elements 26d, 28d. The two seat structural elements 26d, 28d are each arranged on one side of a seating area 30d of the aircraft seating arrangement. The two seat structural elements 26d, 28d are each arranged laterally with respect to the seating area 30d formed by the aircraft seat 10d. The seat structural elements 26d, 28d are embodied as seat dividers. The seat structural elements 26d, 28d are arranged on the cross beam 24d. The seat structural elements 26d, 28d are embodied in a substantially L-shape. Thus, the seat structural elements 26d, 28d extend upward in their rear regions away from the mounting unit 12d, in particular the mounting surface. The seat structural elements 26d, 28d extend upward in their rear regions substantially to the armrest height X. The seat structural elements 26d, 28d extend up to the armrest height X of the aircraft seat 10d.

[0078] The aircraft seating apparatus includes a seat back 34d. The seat back 34d is pivotally disposed relative to the mounting unit 12d. The seat back 34d is attached to the seat structural elements 26d, 28d. The seat back 34d is configured to pivot between an upright seating position and a comfort position. The seat back 34d includes a pivotable seat back element 36d. The pivotable seat back element 36d is pivotally supported on the mounting unit 12d. The seat structural elements 26d, 28d include bearing points 38d, 40d, respectively, for supporting the pivotable seat back element 36d. The aircraft seating apparatus includes a bearing device 42d. The bearing device 42d is configured to pivotally support the seat back 34d between the upright seating position and the comfort position. The bearing device 42d is configured to pivotally support the pivotable backrest element 36d between an upright seating position and a comfortable position. The bearing device 42d defines a rotation axis 44d. The bearing device 42d includes two bearing bolts 46d, 48d. The bearing bolts 46d, 48d define the rotation axis 44d. The bearing bolts 46d, 48d are each connected to one of the bearing points 38d, 40d of one of the seat structural elements 26d, 28d. The backrest 34d is designed as a backrest with a high back pivot point. The backrest pivot point, i.e., the rotation axis 44d of the bearing device 42d, is located above the knee area 50d of the aircraft seat 10d. To provide a high backrest pivot point, the seat structure elements 26d, 28d are formed with bearing points 38d, 40d for supporting the backrest 34d in a high region. The bearing points 38d, 40d of the seat structure elements 26d, 28d are located above the knee region 50d. The bearing points 38d, 40d of the seat structure elements 26d, 28d are located at armrest height X.

[0079] The pivotable backrest element 36d has a backrest frame 60d. The backrest frame 60d forms the load-bearing structure of the pivotable backrest element 36d. The pivotable backrest element 36d has a shell element 62d. The shell element 62d is made of fiber-reinforced plastic. The shell element 62d is fixedly connected to the backrest frame 60d of the pivotable backrest element 36d. The shell element 62d of the pivotable backrest element 36d has a central region 80d. The pivotable backrest element 36d has elastic ribs 84d, 86d in its lower region, which respectively extend laterally outward from the central region 80d. The elastic ribs 84d, 86d are preferably formed integrally with the shell element 62d, in particular with the central region 80d.

[0080] The backrest 34d has a lower backrest element 52d. The lower backrest element 52d forms the lower region of the backrest 34d. The lower backrest element 52d forms a backrest contact surface in the lower region of the backrest 34d. The lower backrest element 52d is fixedly fastened to the seat structural elements 26d, 28d. The lower backrest element 52d extends substantially between the height of the cross beams 22d, 24d of the mounting unit 12d and the lower end of the pivotable backrest element 36d. The lower backrest element 52d is formed by a shell element. The lower backrest element 52d is formed by a shell made of fiber-reinforced plastic.

[0081] The aircraft seating apparatus includes a restoring module 56d. The restoring module 56d is configured to restore the seat back 34d from the comfort position to an upright seating position. The restoring module 56d is configured to restore the pivotable seat back element 36d. The restoring module 56d is configured to restore the seat back 34d, particularly the pivotable seat back element 36d, to provide a restoring force. The restoring module 56d includes a spring element 58d for providing the restoring force. The spring element 58d is embodied as a leaf spring element. In contrast to the previously described exemplary embodiment, the spring element 58d embodied as a leaf spring element is at least partially integrally formed with the lower seat back element 52d.

[0082] The spring element 58d embodied as a leaf spring element is integrally formed with the lower back element 52d embodied as a shell element. The spring element 58d embodied as a leaf spring element is formed by the central region of the lower back element 52d. The spring element 58d embodied as a leaf spring element is partially integrated with the lower shell element. The spring element 58d embodied as a leaf spring element is embedded in a fiber-reinforced layer of the lower back element 52d embodied as a shell element. The spring element 58d embodied as a leaf spring element is preferably formed as a leaf spring element that is inserted into the lower back element 52d during the manufacturing process. The spring element 58d embodied as a leaf spring element extends from the lower back element 52d to the center of the pivotable back element 36d.

[0083] To attach the spring element 58d embodied as a leaf spring element to the pivotable backrest element 36d, the restoring module 56d has a first fastening unit 64d. The pivotable backrest element 36d has a cross beam 66d. The cross beam 66d is arranged in an area above the bearing points 38d, 40d. The spring element 58d embodied as a leaf spring element is directly attached to the cross beam 66d via the fastening unit 64d. The spring element 58d embodied as a leaf spring element is axially movably connected to the cross beam 66d. The spring element 58d embodied as a leaf spring element has two through-grooves embodied as slots, through which the spring element 58d is displaceably connected to the cross beam 66d via two fastening elements, e.g., screws, of the fastening unit 64d. The first fastening unit 64d for attaching the spring element 58d embodied as a leaf spring element may preferably be embodied equivalently to the second fastening unit of the first exemplary embodiment for attaching the spring element embodied as a leaf spring element to the lower backrest element.

[0084] The restoring module 56d includes a locking unit 88d. The locking unit 88d is configured to lock or unlock the restoring module 56d. The locking unit 88d is configured to lock the backrest 34d, i.e., the pivotable backrest element 36d, in at least the upright seating position and the comfort position. The locking unit 88d is preferably operatively arranged between the pivotable backrest element 36d, particularly the backrest frame 60d, and one of the seat structural elements 26d, 28d. The locking unit 88d is preferably arranged above the knee region 50d of the backrest 34d. The locking unit 88d is preferably arranged in an area above the bearing points 38d, 40d of the seat structural elements 26d, 28d. The locking unit 88d is preferably arranged substantially, i.e., mostly, above the armrest height X.

[0085] 9 to 11 show a fifth exemplary embodiment of an aircraft seating arrangement according to the present invention. The aircraft seating arrangement is a part of an aircraft seat 10e, which is partially illustrated. The aircraft seating arrangement has a mounting unit 12e. The aircraft seat 10e can be mounted to a cabin floor of an aircraft cabin by the mounting unit 12e. The mounting unit 12e has two cross beams 24e. The aircraft seating arrangement has two seat structural elements 26e, 28e. The two seat structural elements 26e, 28e are each arranged on one side of a seating area 30e of the aircraft seating arrangement. The two seat structural elements 26e, 28e are each arranged laterally with respect to the seating area 30e formed by the aircraft seat 10e. The seat structural elements 26e, 28e are embodied as seat dividers. The seat structural elements 26e, 28e are arranged on the cross beam 24e. The seat structural elements 26e, 28e are embodied in a substantially L-shape. Thus, the seat structural elements 26e, 28e extend upward in their rear regions away from the mounting unit 12e, in particular the mounting surface. The seat structural elements 26e, 28e extend upward in their rear regions substantially to the armrest height X. The seat structural elements 26e, 28e extend up to the armrest height X of the aircraft seat 10e.

[0086] The aircraft seating arrangement includes a seat back 34e. The seat back 34e is pivotally disposed relative to the mounting unit 12e. The seat back 34e is attached to the seat structural elements 26e, 28e. The seat back 34e is configured to pivot between an upright seating position and a comfort position. The seat back 34e has a pivotable backrest element 36e. The pivotable backrest element 36e is pivotally supported on the mounting unit 12e. The seat structural elements 26e, 28e have bearing points 38e, 40e, respectively, for supporting the pivotable backrest element 36e.

[0087] The aircraft seating arrangement includes a bearing device 42e. The bearing device 42e is configured to pivotally support a seat back 34e between an upright seating position and a comfortable position. The bearing device 42e is configured to pivotally support a pivotable seat back element 36e between an upright seating position and a comfortable position. The bearing device 42e defines a rotation axis 44e. The bearing device 42e includes two bearing bolts 46e, 48e. The bearing bolts 46e, 48e define the rotation axis 44e. The bearing bolts 46e, 48e are each connected to one of the bearing points 38e, 40e of one of the seat structural elements 26e, 28e. The seat back 34e is designed as a seat back with a high back pivot point. The backrest pivot point, i.e., the rotation axis 44e of the bearing device 42e, is located above the knee region 50e of the aircraft seat 10e. To form a high backrest pivot point, the seat structural elements 26e, 28e are formed with bearing points 38e, 40e for supporting the backrest 34e at a high region. The bearing points 38e, 40e of the seat structural elements 26e, 28e are located above the knee region 50e. The bearing points 38e, 40e of the seat structural elements 26e, 28e are located at armrest height X.

[0088] The pivotable backrest element 36e has a backrest frame 60e. The backrest frame 60e forms the load-bearing structure of the pivotable backrest element 36e. The pivotable backrest element 36e can preferably be designed similarly to those of the first two exemplary embodiments and can comprise a shell element or fabric. The backrest 34e further has a lower backrest element (not shown in detail here) that forms the lower region of the backrest 34e.

[0089] The aircraft seating apparatus includes a restoring module 56e. The restoring module 56e is configured to restore the seat back 34e from a comfort position to an upright seating position. The restoring module 56e is configured to restore the pivotable seat back element 36e. The restoring module 56e is configured to restore the seat back 34e, particularly the pivotable seat back element 36e, to provide a restoring force. The restoring module 56e includes a spring element 58e for providing the restoring force. In contrast to the previously described exemplary embodiment, the spring element 58e is designed as a gas pressure spring. The spring element 58e designed as a gas pressure spring is configured to provide the restoring force of the restoring module 56e. The spring element 58e designed as a gas pressure spring is arranged above the bearing points 38e, 40e of the seat structural elements 26e, 28e.

[0090] The restoring module 56e includes a lever gear 110e. The lever gear 110e is configured to convert the spring force of a spring element 58e, which is designed as a gas pressure spring, into a pivoting movement of the pivotable backrest element 36e. The lever gear 110e includes a basic retaining element 112e. The basic retaining element 112e is rigidly and rotatably fixedly connected to the mounting unit 12e. The basic retaining element 112e is preferably rotatably fixedly connected to the seat structural element 26e. The basic retaining element 112e is rotatably and fixedly attached to the seat structural element 26e, in particular via the bearing bolt 46e of the bearing device 42e. The basic retaining element 112e includes a first fixing receptacle 114e. The spring element 58e, which is designed as a gas pressure spring, is pivotally supported at a first end in the first fixing receptacle 114e. The basic retaining element 112e has a second fixed receptacle 116e. The lever gear 110e has a lever element 118e. The lever element 118e is pivotally attached to the basic retaining element 112e via the second fixed receptacle 116e. The lever element 118e of the lever gear 110e is pivotally connected at its first end to the basic retaining element 112e via the second fixed receptacle 116e. In the attached state, the lever element 118e extends upward, away from the attachment surface, in the upright seating position of the backrest 34e (see Figures 9 and 10). A spring element 58e, designed as a gas pressure spring, is rotatably connected at its second end to the second end of the lever element 118e via a bearing point 120e.

[0091] The lever gear 110e has a connecting element 122e that connects the lever gear 110e to the pivotable backrest element 36e. The connecting element 122e is attached at a first end to a bearing point 120e. The connecting element 122e is rotatably connected at its first end to both a second end of the spring element 58e, which is designed as a gas pressure spring, and a second end of the lever element 118e. The connecting element 122e is rotatably connected at its second end to the pivotable backrest element 36e. The connecting element 122e is preferably rotatably connected at its second end to the backrest frame 60e of the pivotable backrest element 36e via a bearing point, not shown in detail.

[0092] The restoring module 56e includes a locking unit 88e. The locking unit 88e is configured to lock or unlock the restoring module 56e. The locking unit 88e is configured to lock the backrest 34e, i.e., the pivotable backrest element 36e, in at least the upright seating position and the comfort position. The locking unit 88e is configured to directly lock the spring element 58e embodied as a gas spring. In the locked state of the locking unit 88e, the spring element 58e embodied as a gas spring is locked and cannot provide any spring force. In the unlocked state of the locking unit 88e, the spring element 58e embodied as a gas spring is unlocked and can provide its spring force as a restoring force. The locking unit 88e is disposed within the spring element 58e embodied as a gas spring. The locking unit 88e is internally embodied in the spring element 58e embodied as a gas spring. The lock unit 88e is integrally formed with a spring element 58e configured as a gas spring.

[0093] When the pivotable backrest element 36e is pivoted backward in its comfort position, the spring element 58e embodied as a gas spring is compressed. The lever element 118e and the spring element 58e embodied as a gas spring are likewise pivoted backward via the fixing receptacles 114e, 116e of the basic holding element 112e in the comfort position of the pivotable backrest element 36e. Now, when the spring element 58e embodied as a gas spring is activated, i.e., unlocked, the spring element 58e embodied as a gas spring pushes the lever element 118e and thus the pivotable backrest element 36e, which is coupled to the lever gear 110e via the connecting element 122e, upward, thus towards an upright sitting position.

[0094] The entire lever gear 110e, the spring element 58e embodied as a gas spring, and the locking unit 88e embodied integrally with the spring element 58e are arranged above the armrest height X. The entire restoring module 56e is arranged above the bearing points 38e, 40e of the seat structural elements 26e, 28e for the pivotable backrest element 36e. The restoring module 56e is arranged completely above the knee area 50e of the backrest 34e. The entire restoring module 56e is arranged on one side of the pivotable backrest element 36e. The restoring module 56e is arranged only on the side facing the left seat structural element 26e. As a result, the restoring module 56e can be arranged in a particularly space-saving manner.

[0095] 12 to 14 show a sixth exemplary embodiment of an aircraft seating arrangement according to the present invention. The aircraft seating arrangement is a part of an aircraft seat 10f, which is partially illustrated. The aircraft seating arrangement has a mounting unit 12f. The aircraft seat 10f can be mounted to a cabin floor of an aircraft cabin by the mounting unit 12f. The mounting unit 12f has two cross beams 22f, 24f. The aircraft seating arrangement has two seat structural elements 26f, 28f. The two seat structural elements 26f, 28f are each arranged on one side of a seating area 30f of the aircraft seating arrangement. The two seat structural elements 26f, 28f are each arranged laterally with respect to the seating area 30f formed by the aircraft seat 10f. The seat structural elements 26f, 28f are embodied as seat dividers. The seat structural elements 26f, 28f are arranged on the cross beam 24f. The seat structural elements 26f, 28f are embodied in a substantially L-shape. Thus, the seat structural elements 26f, 28f extend upward in their rear regions away from the mounting unit 12f, in particular the mounting surface. The seat structural elements 26f, 28f extend upward in their rear regions substantially to the armrest height X. The seat structural elements 26f, 28f extend up to the armrest height X of the aircraft seat 10f.

[0096] The aircraft seat apparatus includes a seat back 34f. The seat back 34f is pivotally disposed relative to the mounting unit 12f. The seat back 34f is attached to the seat structural elements 26f, 28f. The seat back 34f is configured to pivot between an upright seating position and a comfort position. The seat back 34f includes a pivotable seat back element 36f. The pivotable seat back element 36f is pivotally supported on the mounting unit 12f. The seat structural elements 26f, 28f include bearing points 38f, 40f, respectively, for supporting the pivotable seat back element 36f. The aircraft seat apparatus includes a bearing device 42f. The bearing device 42f is configured to pivotally support the seat back 34f between the upright seating position and the comfort position. The bearing device 42f is configured to pivotally support the pivotable backrest element 36f between an upright seating position and a comfortable position. The bearing device 42f defines a rotation axis 44f. The bearing device 42f includes two bearing bolts 46f, 48f. The bearing bolts 46f, 48f define the rotation axis 44f. The bearing bolts 46f, 48f are each connected to one of the bearing points 38f, 40f of one of the seat structural elements 26f, 28f. The backrest 34f is designed as a backrest with a high back pivot point. The backrest pivot point, i.e., the rotation axis 44f of the bearing device 42f, is located above the knee area 50f of the aircraft seat 10f. To provide a high backrest pivot point, the seat structural elements 26f, 28f are formed with bearing points 38f, 40f for supporting the backrest 34f in a high region. The bearing points 38f, 40f of the seat structural elements 26f, 28f are located above the knee region 50f. The bearing points 38f, 40f of the seat structural elements 26f, 28f are located at armrest height X.

[0097] The pivotable backrest element 36f has a backrest frame 60f. The backrest frame 60f forms the load-bearing structure of the pivotable backrest element 36f. The pivotable backrest element 36f can preferably be designed similarly to those of the first two exemplary embodiments and can comprise a shell element or fabric. The backrest 34f further has a lower backrest element (not shown in detail here) that forms the lower region of the backrest 34f.

[0098] The aircraft seating apparatus includes a restoring module 56f. The restoring module 56f is configured to restore the seat back 34f from a comfort position to an upright seating position. The restoring module 56f is configured to restore the pivotable seat back element 36f. The restoring module 56f is configured to restore the seat back 34f, particularly the pivotable seat back element 36f, to provide a restoring force. The restoring module 56f includes a spring element 58f for providing the restoring force. As in the fifth embodiment of FIGS. 9 to 11, the spring element 58f is embodied as a gas spring. The spring element 58f, which is designed as a gas pressure spring, is configured to provide the restoring force of the restoring module 56f. The spring element 58f, which is designed as a gas pressure spring, is arranged above the bearing points 38f, 40f of the seat structural elements 26f, 28f.

[0099] The restoring module 56f includes a lever gear 110f. The lever gear 110f is configured to convert the spring force of the spring element 58f, which is designed as a gas pressure spring, into a pivoting movement of the pivotable back element 36f. In contrast to the fifth exemplary embodiment, the lever gears 110f are arranged on both sides of the back frame 60f. The lever gears 110f are arranged on both lateral frame elements of the back frame 60f. In this case, the lever gears 110f are arranged inside the two lateral frame elements of the back frame 60f. The lever gear 110f includes two eccentric elements 124f, 126f. The eccentric elements 124f, 126f are pivotally attached to the lateral frame elements of the back frame 60f, respectively. The eccentric elements 124f, 126f are arranged coaxially with respect to each other. The eccentric elements 124f, 126f have first points 128f, 130f, respectively.

[0100] The lever gear 110f has a torsion tube 132f, which connects the two eccentric elements 124f, 126f to each other. The torsion tube 132f is in each case rotatably and fixedly attached to the first mounting points 128f, 130f of the eccentric elements 124f, 126f. The torsion tube 132f connects the eccentric elements 124f, 126f at their first mounting points 128f, 130f. The first eccentric element 124f is arranged on the left side of the pivotable backrest element 36f, this side facing the left seat structural element 26f. The first eccentric element 124f has a second mounting point 134f, via which a spring element 58f configured as a gas pressure spring is attached to the first eccentric element 124f. The spring element 58f, configured as a gas pressure spring, is attached by its second end to the second mounting point 134f of the first eccentric element 124f. The spring element 58f, configured as a gas pressure spring, is rotatably attached at its first end to the mounting unit 12f. The spring element 58f, configured as a gas pressure spring, is preferably rotatably attached at its first end to the bearing bolt 46f of the bearing device 42f. The second eccentric element 126f is disposed on the right side of the pivotable backrest element 36f, and this side faces the right seat structural element 28f. The second eccentric element 126f likewise has a second mounting point 136f. The lever gear 110f has a lever element 138f pivotally attached to the second mounting point 136f of the second eccentric element 126f. The lever element 138f is pivotally mounted at its second end to the mounting point 136f of the second eccentric element 126f. The lever element 138f is rotatably mounted at its first end to the mounting unit 12f. The lever element 138f is preferably rotatably mounted at its first end to the bearing bolt 48f of the bearing arrangement 42f.

[0101] The eccentric elements 124f, 126f rotate as a result of the extension or contraction of the spring element 58f, which is designed as a gas pressure spring. When the pivotable backrest element 36f pivots backward in the comfort position, the spring element 58f, which is designed as a gas spring, is compressed. As a result, the eccentric elements 124f, 126f pivot. When the spring element 58f, which is designed as a gas spring, is activated, i.e., unlocked, it presses against the first eccentric element 124f via the second attachment point 134f, causing it to rotate, and thus causing the pivotable backrest element 36f to rotate to its upright seating position. The restoring force of the spring element 58f, which is designed as a gas pressure spring, is transmitted to the opposite side of the backrest frame 60f by the torsion tube 132f. As a result, the pivotable back element 36f is biased evenly on both sides into an upright seating position.

[0102] Above the armrest height X, the entire lever gear 110f, the spring element 58f configured as a gas pressure spring, and the locking unit 88f embodied integrally with the spring element 58f are arranged. The entire restoring module 56f is arranged above the bearing points 38f, 40f of the seat structural elements 26f, 28f for the pivotable backrest element 36f. The restoring module 56f is arranged completely above the knee area 50f of the backrest 34f.

[0103] FIG. 15 shows a seventh exemplary embodiment of an aircraft seating arrangement according to the present invention. The aircraft seating arrangement is a part of an aircraft seat 10g, which is partially illustrated. The aircraft seating arrangement has a mounting unit 12g. The aircraft seat 10g can be mounted to the cabin floor of an aircraft cabin by means of the mounting unit 12g. The mounting unit 12g has two cross beams 24g. The aircraft seating arrangement has two seat structural elements 26g, 28g. The two seat structural elements 26g, 28g are each arranged on one side of a seating area 30g of the aircraft seating arrangement. The two seat structural elements 26g, 28g are each arranged laterally with respect to the seating area 30g formed by the aircraft seat 10g. The seat structural elements 26g, 28g are embodied as seat dividers. The seat structural elements 26g, 28g are embodied substantially in an L-shape. Each of the seat structural elements 26g, 28g has a first partial area that is oriented substantially horizontally in the mounted state. Each of the seat structural elements 26g, 28g has a second partial region that is oriented substantially vertically in the installed state. The second partial region of the seat structural elements 26g, 28g is arranged in the rear region of the aircraft seat 10g. The seat structural elements 26g, 28g are arranged on the cross beam 24g. Thus, in their rear regions, the seat structural elements 26g, 28g extend upward, away from the mounting unit 12g, in particular the mounting surface. In their rear regions, the seat structural elements 26g, 28g extend upward substantially to the armrest height X. The seat structural elements 26g, 28g extend to the armrest height X of the aircraft seat 10g.

[0104] The aircraft seating apparatus includes a backrest 34g. The backrest 34g is pivotably arranged relative to the mounting unit 12g. The backrest 34g is attached to the seat structural elements 26g, 28g. The backrest 34g is configured to pivot between an upright seating position and a comfort position. The backrest 34g has a pivotable backrest element 36g. In contrast to the previously described exemplary embodiment, the backrest 34g is designed as a backrest with a lower backrest pivot point. Preferably, the backrest 34g does not have a lower backrest element rigidly connected to the seat structural elements 26g, 28g. The pivotable backrest element 36g extends to the area of ​​the seat bottom of the aircraft seat 10g. The pivotable backrest element 36g extends to the area below the seat surface formed by the seat bottom. The pivotable backrest element 36g is pivotally supported in the region below the armrest height X.

[0105] The pivotable backrest element 36g is pivotally attached to the seat structural elements 26g, 28g. The seat structural elements 26g, 28g each have bearing points 38g, 40g for supporting the pivotable backrest element 36g. To form a lower backrest pivot point, the seat structural elements 26g, 28g have bearing points for supporting the pivotable backrest element 36g formed in their lower regions. The bearing points 38g, 40g of the seat structural elements 26g, 28g are preferably located in the lower third of the seat structural elements 26g, 28g, particularly in the lower third of the second partial region of the seat structural elements 26g, 28g. The bearing points 38g, 40g of the seat structural elements 26g, 28g are located in the knee region 50g of the backrest 34g. The bearing points 38g, 40g of the seat structural elements 26g, 28g are arranged below the armrest height X.

[0106] The aircraft seating arrangement includes a bearing device 42g. The bearing device 42g is configured to pivotally support a pivotable backrest element 36g between an upright seating position and a comfort position. The bearing device 42g defines a rotation axis 44g. The rotation axis 44g for supporting the pivotable backrest element 36g is arranged below the armrest height X. The bearing device 42g includes two bearing bolts 46g, 48g. The bearing bolts 46g, 48g define the rotation axis 44g. The bearing bolts 46g, 48g are respectively connected to one of the bearing points 38g, 40g of one of the seat structural elements 26g, 28g.

[0107] The pivotable backrest element 36g has a backrest frame 60g that extends to an area below the bearing points 38g, 40g of the seat structural elements 26g, 28g. The pivotable backrest element 36g has a shell element 62g fixedly connected to the backrest frame 60g of the pivotable backrest element 36g. The shell element 62g of the pivotable backrest element 36g has a central region 80g and elastic ribs 84g, 86g that extend laterally outward from the central region 80g in their lower areas.

[0108] The aircraft seating apparatus includes a restoring module 56g configured to restore the seat back 34g from a comfort position to an upright seating position. The restoring module 56g is configured to restore the pivotable seat back element 36g. The restoring module 56g includes a spring element 58g for providing a restoring force. The spring element 58g is embodied as a leaf spring element. The spring element 58g embodied as a leaf spring element is operatively disposed between the pivotable seat back element 36g and the mounting unit 12g.

[0109] In contrast to other exemplary embodiments, the spring element 58g embodied as a leaf spring element is directly attached by its first lower end to the mounting unit 12g, in particular to the rear cross beam 24g. The spring element 58g embodied as a leaf spring element has its lower end supported by the rear cross beam 24g of the mounting unit. To attach the spring element 58g embodied as a leaf spring element to the rear cross beam 24g, the restoring module 56g includes a fastening unit 68g. The spring element 58g embodied as a leaf spring element is fixedly attached to the mounting unit 12g via the fastening unit 68g. The fastening unit 68g preferably includes a clamp element that surrounds the rear cross beam 24g and is thus fixedly attached to the cross beam 24g. The spring element 58g embodied as a leaf spring element is preferably attached to the rear cross beam 24g via the fastening unit 68g so as to be movable in at least one vertical direction. The spring element 58g embodied as a leaf spring element is attached by a second upper end to the pivotable backrest element 36g. To attach the spring element 58g embodied as a leaf spring element to the pivotable backrest element 36g, the restoring module 56g has a fastening unit 64g.

[0110] The restoring module 56g has a locking unit 88g, which is configured to lock or unlock the restoring module 56g. The locking unit 88g is preferably arranged in an area above the bearing points 38g, 40g of the seat structural elements 26g, 28g. The entire restoring module 56g, except for a partial area of ​​the spring element 58g embodied as a leaf spring that extends to the cross beam 24g of the mounting unit 12g, is arranged above the bearing points 38g, 40g of the seat structural elements 26g, 28g, i.e., above the rotation axis 44g of the pivotable backrest element 36g.

[0111] FIG. 16 shows an eighth exemplary embodiment of an aircraft seating arrangement according to the present invention. The aircraft seating arrangement is a portion of an aircraft seat 10h, which is partially illustrated. The aircraft seating arrangement has a mounting unit 12h. The aircraft seat 10h can be mounted to the cabin floor of an aircraft cabin by the mounting unit 12h. The mounting unit 12h has two cross beams 24h. The aircraft seating arrangement has two seat structural elements 26h, 28h. The two seat structural elements 26h, 28h are each arranged on one side of a seating area 30h of the aircraft seating arrangement. The two seat structural elements 26h, 28h are each arranged laterally with respect to the seating area 30h formed by the aircraft seat 10h. A pivotable seat back element 36h is pivotally attached to the seat structural elements 26h, 28h. The seat structural elements 26h, 28h have bearing points 38h, 40h for supporting the pivotable seat back element 36h, respectively.

[0112] The aircraft seating arrangement comprises a seat bottom 32h. The seat bottom 32h has a load-bearing body. The seat bottom 32h further has an upholstery element attached to the body. The seat bottom 32h is attached to a mounting unit 12h. The aircraft seating arrangement comprises a backrest 34h. The backrest 34h is pivotally arranged relative to the mounting unit 12h. The backrest 34h is attached to the seat structural elements 26h, 28h. The backrest 34h is designed as a backrest with a high back pivot point. The backrest 34h has a lower backrest element 52h. The lower backrest element 52h forms a lower region of the backrest 34h. The lower backrest element 52h forms a backrest contact surface in the lower region of the backrest 34h. The lower backrest element 52h is rigidly coupled to the mounting unit 12h. The backrest 34h is configured to pivot between an upright seating position and a comfort position. The backrest 34h has a pivotable backrest element 36h. The pivotable backrest element 36h has a backrest frame 60h. The pivotable backrest element 36h has a shell element 62h. The pivotable backrest element 36h is formed substantially identically to the first exemplary embodiment and therefore will not be described in detail here.

[0113] In contrast to the previously described exemplary embodiment, the seat structural elements 26h, 28h are not embodied as seat dividers. The aircraft seating arrangement includes a seat shell element 140h. The seat shell element 140h integrally forms the lower backrest element 52h and the main body of the seat bottom 32h. The seat shell element 140h forms the main body of the seat bottom 32h in the lower front region. In the rear region, the seat shell element 140h forms the lower backrest element 52h. The seat shell element 140h is made of fiber-reinforced plastic. The seat shell element 140h is preferably made of CFRP or GRP. In principle, it is also conceivable that the seat shell element 140h is made of another suitable fiber-reinforced plastic. The seat shell element 140h is embodied substantially L-shaped in side view. In contrast to the previously described exemplary embodiment, the seat structural elements 26h, 28h are integrally formed with the seat shell element 140h. The seat structural elements 26h, 28h are formed at least in part from the main bodies of the lower back element 52h and the seat bottom 32h. The seat shell element 140h has side regions 142h, 144h. When viewed laterally, the side regions 142h, 144h each form the lateral ends of the seat shell element 140h. The seat structural elements 26h, 28h are formed in the side regions 142h, 144h of the seat shell element 140h. The side regions 142h, 144h of the seat shell element 140h each form one of the seat structural elements 26h, 28h. The seat shell element 140h preferably has at least one reinforcing element in its side regions 142h, 144h, respectively, to form the seat structural elements 26h, 28h. The reinforcing elements may be embodied, for example, as inserts inserted into the side regions 142h, 144h of the seat shell element 140h. Reinforcing elements embodied as inserts may be embodied, for example, from a metal such as aluminum or magnesium. In principle, it is also conceivable for the reinforcing elements to be formed from local reinforcements made from CFRP or GRP.

[0114] The seat shell element 140h extends, in its side regions 142h, 144h, with which it forms the seat structural elements 26h, 28h, up to the upper edge of the lower backrest element 52h formed thereby. The seat shell element 140h extends, in its side regions 142h, 144h, with which it forms the seat structural elements 26h, 28h, up to the armrest height X. The seat shell element 140h forms, in its side regions 142h, 144h, in each case in its upper end region, bearing points 38h, 40h for the seat structural elements 26h, 28h. The seat shell element 140h forms, in each case in its upper end region of its side regions 142h, 144h, bearing points 38h, 40h for the seat structural elements 26h, 28h, via which the pivotable backrest element 36h is pivotally supported. The pivotable backrest element 36h is pivotally connected directly to the seat shell element 140h via bearing points 38h, 40h.

[0115] The aircraft seating arrangement includes a bearing device 42h. The bearing device 42h is configured to pivotally support a pivotable seatback element 36h between an upright seating position and a comfort position. The bearing device 42h defines a rotation axis 44h. The bearing device 42h includes two bearing bolts 46h, 48h. The bearing bolts 46h, 48h are each connected to one of the bearing points 38h, 40h of the seat structural elements 26h, 28h formed by the seat shell element 140h. The bearing bolts 46h, 48h are fixedly connected to the seat shell element 140h. The pivotable seatback element 36h is directly pivotally attached to the seat shell element 140h via the bearing bolts 46h, 48h.

[0116] The seat shell element 140h is embodied to be wider than the pivotable backrest element 36h. The seat shell element 140h engages at its lower end around the pivotable backrest element 36h, particularly its backrest frame 60h, at its upper end in side regions 142h, 144h, where bearing points 38h, 40h are arranged. Bearing bolts 46h, 48h extend inward from the side regions 142h, 144h of the seat shell element 140h, respectively, toward the backrest frame 60h of the pivotable backrest element 36h. The pivotable backrest element 36h is pivotally attached to the bearing bolts 46h, 48h.

[0117] The aircraft seat apparatus includes a restoring module 56h. The restoring module 56h is configured to restore the seat back 34h from a comfort position to an upright seating position. The restoring module 56h is configured to restore the pivotable seat back element 36h. The restoring module 56h is configured to restore the seat back 34h, particularly the pivotable seat back element 36h, to provide a restoring force. The restoring module 56h includes a spring element 58h for providing the restoring force. The spring element 58h is embodied as a leaf spring element. The restoring module 56h may preferably be embodied as in one of the aforementioned exemplary embodiments. As an example, the restoring module 56h is formed substantially identically to the first exemplary embodiment.

[0118] The spring element 58h, embodied as a leaf spring element, is operatively arranged between the seat shell element 140h and the pivotable backrest element 36h. The spring element 58h, embodied as a leaf spring element, is attached by its first lower end to the seat shell element 140h, in particular to the lower backrest element 52h formed by the seat shell element 140h. To attach the spring element 58h, embodied as a leaf spring element, to the seat shell element 140h, the restoring module 56h has a fastening unit 68h. The spring element 58h, embodied as a leaf spring element, is movably attached to the seat shell element 140h via the fastening unit 68h. To attach the spring element 58h, embodied as a leaf spring element, to the pivotable backrest element 36h, the restoring module 56h has a fastening unit 64h. The pivotable backrest element 36h has a cross beam 66h. The spring element 58h, embodied as a leaf spring element, is attached directly to the cross beam 66h via a fastening unit 64h.

[0119] The restoring module 56h includes a locking unit 88h. The locking unit 88h is configured to lock or unlock the restoring module 56h. The locking unit 88h is preferably operatively arranged between the pivotable backrest element 36h, in particular the backrest frame 60h, and the seat shell element 140h. The locking unit 88h is arranged above the knee region 50h of the backrest 34h. The locking unit 88h is preferably arranged in an area above the bearing points 38h, 40h of the seat structural elements 26h, 28h formed by the seat shell element 140h. The locking unit 88h is preferably arranged substantially, i.e., mostly, above the armrest height X.

[0120] 17 to 20 show a ninth exemplary embodiment of an aircraft seating arrangement according to the present invention. In this case, the aircraft seating arrangement is part of an aircraft seat 10i. In an installed state, the aircraft seat 10i is installed in an aircraft cabin of an aircraft. The aircraft seating arrangement has a mounting unit 12i. The aircraft seat 10i can be installed on a cabin floor of the aircraft cabin by the mounting unit 12i. Preferably, the aircraft seat 10i is formed as part of an aircraft seat row 14i including a plurality of aircraft seats 10i. As an example, an aircraft seat row 14i including three aircraft seats 10i, 16i, and 146i is shown in the figures. The aircraft seat row 14i shown as an example includes a second aircraft seat 16i and a third aircraft seat 146i. The second aircraft seat 16i is formed as a center seat of the aircraft seat row 14i and is arranged between the two other aircraft seats 16i and 146i. The other aircraft seats 16i, 146i of the aircraft seat row 14i are preferably configured substantially identically to the first aircraft seat 10i, so only one aircraft seat 10i will be described in more detail below.

[0121] The mounting unit 12i includes two cross beams 22i, 24i. The cross beams 22i, 24i are embodied as support tubes. The cross beams 22i, 24i extend at least substantially across the entire lateral extent of all of the aircraft seats 10i in the aircraft seat row 14i. The aircraft seating arrangement includes two seat structural elements 26i, 28i. The two seat structural elements 26i, 28i are each disposed on one side of a seating area 30i of the aircraft seating arrangement. The two seat structural elements 26i, 28i are each disposed laterally with respect to the seating area 30i formed by the aircraft seats 10i. The seat structural elements 26i, 28i are embodied as seat dividers. The seat structural elements 26i, 28i embodied as seat dividers are configured to have various components of the corresponding aircraft seats 10i, 16i, 146i fixed thereto. Thus, in their rear regions, the seat structural elements 26i, 28i extend upwards, away from the mounting unit 12i, in particular the mounting surface. In their rear regions, the seat structural elements 26i, 28i extend upwards substantially to the armrest height X. The seat structural elements 26i, 28i extend up to the armrest height X of the aircraft seat 10i.

[0122] The aircraft seating apparatus includes a seat back 34i. The seat back 34i is configured to allow a person sitting in an aircraft seat 10i of which the aircraft seating apparatus is a part to rest their back against the seat back 34i. The seat back 34i is pivotally arranged relative to the mounting unit 12i. The seat back 34i is attached to the seat structural elements 26i, 28i. The seat back 34i is configured to pivot between an upright seating position and a comfort position. The seat back 34i includes a pivotable backrest element 36i. The pivotable backrest element 36i is pivotally supported by the mounting unit 12i. The pivotable backrest element 36i is pivotally attached to the seat structural elements 26i, 28i. The seat structural elements 26i, 28i have bearing points 38i, 40i for supporting the seat back 34i, respectively. The bearing points 38i, 40i are configured such that the pivotable back element 36i is supported on the bearing points 38i, 40i.

[0123] The aircraft seating arrangement includes a bearing device 42i. The bearing device 42i is configured to pivotally support a seat back 34i between an upright seating position and a comfortable position. The bearing device 42i is configured to pivotally support a pivotable seat back element 36i between an upright seating position and a comfortable position. The bearing device 42i defines a rotation axis 44i. The pivotable seat back element 36i is pivotable about the rotation axis 44i by means of the bearing device 42i. The bearing device 42i includes two bearing bolts 46i, 48i. The bearing bolts 46i, 48i define the rotation axis 44i. The bearing bolts 46i, 48i are each coupled to one of the bearing points 38i, 40i of one of the seat structural elements 26i, 28i.

[0124] The pivotable backrest element 36i has a backrest frame 60i. The backrest frame 60i forms the load-bearing structure of the pivotable backrest element 36i. The backrest frame 60i is embodied as a perimeter frame. The backrest frame 60i has two side frame elements and an upper frame element that connects the two side frame elements at the upper end of the backrest frame 60i. The lower end of the backrest frame 60i forms the lower end of the pivotable backrest element 36i. The bearing bolts 46i, 48i are respectively attached to the backrest frame 60i of the pivotable backrest element 36i at the lower end of the backrest frame 60i of the opposing side frame element. The backrest 34i is designed as a backrest with a high back pivot point. The backrest pivot point, i.e., the rotation axis 44i of the bearing device 42i, is located above the knee region 50i of the aircraft seat 10i. To form a high backrest pivot point, the seat structural elements 26i, 28i are formed with bearing points 38i, 40i for supporting the backrest 34i in a high region. The bearing points 38i, 40i of the seat structural elements 26i, 28i are located above the knee region 50i. The bearing points 38i, 40i of the seat structural elements 26i, 28i are located at armrest height X.

[0125] The pivotable backrest element 36i has a shell element 62i. The shell element 62i is embodied as a plate-like element. The shell element 62i is made of fiber-reinforced plastic. The shell element 62i is made of, for example, GRP or CFRP. The shell element 62i is configured to form a back contact surface of the pivotable backrest element 36i. The shell element 62i is arranged in an inner region of the pivotable backrest element 36i that is clamped by the backrest frame 60i. The shell element 62i is fixedly connected to the backrest frame 60i of the pivotable backrest element 36i. The shell element 62i is configured to allow an upholstery element of the backrest 34i to be attached.

[0126] The pivotable backrest element 36i has resilient ribs 84i, 86i in its lower region, each extending laterally outward from the central region 80i. In the exemplary embodiment, three resilient ribs 84i, 86i are shown per side by way of example. Each of the resilient ribs 84i, 86i is resiliently deformable independently of the others. The resilient ribs 84i, 86i are preferably integrally formed with the shell element 62i, particularly with the central region 80i. The shell element 62i forms the resilient ribs 84i, 86i in its lower region. The lower region is preferably formed by approximately the lower third of the shell element 62i. The shell element 62i has a plurality of slots 148i, 150i in its lower region to form the ribs 84i, 86i. The slots 148i, 150i each extend from the outer lateral edge of the shell element 62i to the front of the central region 80i. The slots 148i, 150i separate the upper and lower resilient ribs 84i, 86i from each other.

[0127] The backrest 34i has a lower backrest element 52i. The lower backrest element 52i is rigidly embodied. Preferably, the lower backrest element 52i is immovably embodied. The lower backrest element 52i forms the lower region of the backrest 34i. The lower backrest element 52i forms a backrest contact surface in the lower region of the backrest 34i. The lower backrest element 52i is fixedly fastened to the seat structural elements 26i, 28i. The lower backrest element 52i extends substantially between the height of the cross beams 22i, 24i of the mounting unit 12i and the lower end of the pivotable backrest element 36i. The lower backrest element 52i is formed by a shell element. The lower backrest element 52i is formed by a shell made of fiber-reinforced plastic. For example, it is conceivable that the lower backrest element 52i is formed by a GRP or CFP shell. In principle, it is also conceivable that the lower backrest element 52i is formed from a different material, for example, from a metal sheet, from a film, or from a multi-layer structure with a honeycomb structure. The lower backrest element 52i has an upper region 152i. The upper region 152i forms approximately the upper quarter of the lower backrest element 52i. The uppermost 5 to 10 cm of the lower backrest element 52i forms the upper region 152i. The backrest element 52i has a lip 104i at its upper end. The lip 104i forms the upper end region of the lower backrest element 52i. The lip 104i is formed in the upper region 152i of the lower backrest element 52i. The lip 104i forms the upper end of the upper region 152i of the lower backrest element 52i. The lip 104i is integrally formed with the remainder of the lower backrest element 52i. The lip 104i is laterally centrally located at the upper end of the lower backrest element 52i.

[0128] The lower backrest element 52i is embodied to be flexible in its upper region 152i. The lower backrest element 52i is embodied to be more flexible in its upper region 152i than the main region 102i arranged below it. The lower backrest element 52i is embodied to be elastically flexible in its upper region 152i. To provide flexibility in the upper region 152i, the lower backrest element 52i has a recess pattern 154i in the upper region 152i. The recess pattern 154i is formed by at least one of the recesses 156i introduced into the lower backrest element 52i. The recess pattern 154i is arranged only in the upper region 152i. In principle, it is also conceivable that the recess pattern 154i is arranged only in the region of the lip 104i. In this exemplary embodiment, the recess pattern 154i is formed by a plurality of recesses 156i embodied as slots, spaced apart from one another. The recesses 156i embodied as slots extend from the upper edge of the lower back element 52i to below the lip 104i. In principle, it is also conceivable for the recesses 156i to extend only to the lower edge of the lip 104i. The recesses 156i embodied as slots have a width of 10 mm. In principle, it is also conceivable for the recesses 156i embodied as slots to have a width in the range of 5 mm to 30 mm. In this exemplary embodiment, four recesses 156i embodied as slots are shown by way of example. In principle, it is also conceivable for the recess pattern 154i to have a different number of recesses 156i embodied as slots. In principle, it is also conceivable for the recesses 156i embodied as slots to be narrower.

[0129] However, it is also conceivable in principle for the lower back element 52i to be formed from a combination of different materials. For example, it is conceivable for the upper region 152i or the lip 104i of the lower back element 52i to be formed from a material different from that of the main region 102i. For example, it is conceivable for the main region 102i to be formed from a flexurally stiff fiber composite material or a metal plate, and for the upper region to be formed from a flexible plastic or fiber composite material fixedly connected to the main region 102i. If the lower back element 52i is formed from a fiber composite material, it is preferable for the upper flexible region 152i to be formed from a fewer number of fiber composite layers than the main region 102i. As a result, the upper region 152i can be embodied particularly simply and more flexible than the main region 102i, and the lower back element 52i can advantageously be embodied as a one-piece part.

[0130] The aircraft seating apparatus includes a restoring module 56i. The restoring module 56i is configured to restore the seat back 34i from a comfort position to an upright seating position. The restoring module 56i is configured to restore the seat back 34i from a pivoted seating position to an upright seating position. The restoring module 56i is configured to restore the pivotable seat back element 36i. The restoring module 56i is configured to restore the seat back 34i, particularly the pivotable seat back element 36i, to provide a restoring force. The restoring module 56i is at least substantially disposed in an area above the bearing points 38i, 40i of the seat structural elements 26i, 28i. The restoring module 56i is disposed at least substantially above the armrest height X, i.e., on the side facing away from the mounting surface. The restoring module 56i is disposed at least mostly above the knee region 50i of the seat back 34i.

[0131] The restoring module 56i includes a locking unit 88i. The locking unit 88i is configured to lock or unlock the restoring module 56i. The locking unit 88i is configured to lock the backrest 34i, i.e., the pivotable backrest element 36i, in at least an upright sitting position and a comfort position. The locking unit 88i is configured to lock the backrest 34i in its upright sitting position. The locking unit 88i is configured to lock the pivotable backrest element 36i in the upright sitting position. The locking unit 88i can lock the pivotable backrest element 36i in the comfort position and the upright sitting position. The locking unit 88i has a locked state and an unlocked state. In the locked state of the locking unit 88i, the backrest 34i, in particular the pivotable backrest element 36i, is locked in its current position, i.e., either the upright sitting position or the comfort position. In the locked position of the locking unit 88i, the pivotable backrest element 36i is fixed in a form-fitting manner in a certain position, i.e., in the upright sitting position or the comfort position. In the locked position of the locking unit 88i, the pivotable backrest element 36i is fixed in a positionally fixed state relative to the mounting unit 12i. Preferably, the locking unit 88i is configured only to lock the backrest 34i, i.e., the pivotable backrest element 36i, in the upright sitting position and the comfort position. The locking unit 88i is preferably arranged mostly above the bearing points 38i, 40i. The locking unit 88i is arranged between the seat structure element 26i, 28i and the pivotable backrest element 36i.

[0132] The lock unit 88i includes a first lock module 172i. The first lock module 172i of the lock unit 88i is disposed on the left side of the pivotable backrest element 36i. The first lock module 172i is disposed between the first left seat structural element 26i and the backrest frame 60i. The first lock module 172i is operatively disposed between the left bearing bolt 46i and the left side frame element of the backrest frame 38i. The lock unit 88i includes a second lock module 174i. The second lock module 174i of the lock unit 88i is disposed on the right side of the pivotable backrest element 36i. The second lock module 174i is disposed between the second right seat structural element 28i and the backrest frame 38i. The second lock module 174i is operatively disposed between the right bearing bolt 48i and the right side frame element of the backrest frame 38i. The two locking modules 172i, 174i are configured together to lock the backrest 34i, in particular the pivotable backrest element 36i. The two locking modules 172i, 174i of the locking device 70i are embodied in a substantially identical manner. The locking modules 172i, 174i are embodied in a substantially mirror-image manner relative to one another. Preferably, the locking modules 172i, 174i differ only in the actuating connections or actuating elements for transmitting the actuating force. The locking modules 172i, 174i have a substantially identical structure that is a mirror-image of one another.

[0133] The lock module 172i has a first lock unit 176i. The first lock unit 176i is configured to be fixed to the pivotable back element 36i. The first lock unit 176i forms a part of the lock module 172i facing the pivotable back element 36i. The lock module 172i has a second lock unit 178i. The second lock unit 178i is configured to be fixedly attached to the bearing bolt 46i. The second lock unit 178i forms a part of the lock module 172i facing the mounting unit 12i. The first lock unit 176i and the second lock unit 178i of the lock module 172i are supported movably relative to each other. The first locking unit 176i and the second locking unit 178i are supported for movement relative to each other about the rotation axis 44i by coupling to the pivotable backrest element 36i or by coupling to the bearing bolt 46i via a support of the pivotable backrest element 36i. The first locking unit 176i has a locking element that is spring-loaded and adjustable between a locked position and an unlocked position. The locking element is configured to couple to the second locking unit 178i in a form-fit manner.

[0134] The restoring module 56i has a first spring element 58i for providing a restoring force. The restoring module 56i has a second spring element 158i for providing a restoring force. In contrast to the previously described exemplary embodiment, the restoring module has two spring elements 58i, 158i. The spring elements 58i, 158i are each disposed on one side of the back frame 60i. The spring elements 58i, 158i are each attached to a lateral frame element of the back frame 60i. In the illustrated exemplary embodiment, the spring elements 58i, 158i are each attached to the outer sides of the lateral frame elements of the back frame 60i. The spring elements 58i, 158i are embodied as flexure springs. The spring elements 58i, 158i are preferably embodied as metallic flexure springs. The spring elements 58i, 158i are configured to provide a spring force.

[0135] The spring force of the spring elements 58i, 158i forms the restoring force of the restoring module 56i. The spring elements 58i, 158i are operatively disposed between the pivotable backrest element 36i and the mounting unit 12i. The spring elements 58i, 158i are configured to be supported on a first side by the mounting unit 12i. The spring elements 58i, 158i are configured to be supported on a second side by the pivotable backrest element 36i. The spring elements 58i, 158i are operatively disposed between one of the seat structural elements 26i, 28i and a lateral frame element of the backrest frame 60i. The spring elements 58i, 158i are each identically embodied and are identically attached to the backrest frame 60i. Therefore, only one spring element 58i and its attachment will be described below, and this description can also be used to describe the other spring element 158i. The spring element 58i is embodied as a spiral spring. The spring element 58i has a spiral-shaped central region 160i and two spring legs 162i, 164i protruding from the central region 160i. The restoring module 65i has a bearing element 166i, via which the spring element 58i is attached to the back frame 60i. The bearing element 166i is embodied as a bearing cylinder. The bearing element 166i has a cylindrical circumferential surface on which the spiral-shaped central region 160i of the spring element 58i rests. The spring element 58i surrounds the bearing element 166i with its spiral-shaped central region 160i. The bearing elements 166i are fixedly attached to the outer sides of the lateral frame elements of the back frame 60i, preferably by screwing them in a fixed position to the outer sides of the lateral frame elements of the back frame 60i via threaded connections.

[0136] The first spring leg 162i is configured to support the bearing bolt 46i. The first spring leg 162i is configured to support the first locking unit 176i. The restoring module 56i has a first support element 168i for supporting the first spring leg 162i. The first spring leg 162i is supported on the support element 168i formed by the first locking unit 176i. The support element 168i is preferably formed by the body 180i of the first locking unit 176i. The second spring leg 164i is configured to support the backrest element 36i. The second spring leg 164i is configured to support the lateral frame element of the backrest frame 60i. The restoring module 56i has a second support element 170i for supporting the second spring leg 164i. The second support element 170i is configured so that the second spring leg 164i is supported by the backrest frame 60i. The support element 170i is embodied as a support bolt fixedly attached to the side of a lateral frame element of the backrest frame 60i. Preferably, the support element 170i is attached by a threaded connection. For support, the spring leg 164i of the spring element 58i abuts against the support element 170i.

[0137] Due to the two separate spring elements 58i, 158i, each arranged on one side of the backrest frame 60i, the restoring force provided by the restoring module can advantageously act uniformly on both sides of the pivotable backrest element 36i. As a result, it is advantageously possible to dispense with further stiffening of the backrest frame 60i between the two lateral frame elements, particularly in the intermediate region. As a result, the pivotable backrest element 36i can be advantageously embodied with a low weight.

[0138] In principle, it is also conceivable that the spring elements 58i, 158i and / or the locking modules 172i, 174i of the locking unit 88i are respectively mounted on the inside of each lateral frame element of the backrest frame 60i. As a result of mounting the spring elements 58i, 158i and / or the locking modules 172i, 174i of the locking unit 88i in the backrest frame 60i, a pivotable backrest element 36i can be realized in a particularly advantageous manner.

[0139] The aircraft seat apparatus includes a lower cover module 182i. The lower cover module 182i is configured to at least partially cover a lower region of the seat back 34i toward the rear. The lower cover module 182i is preferably configured to cover at least a partial region of the lower back element 52i. The lower cover module 182i covers a partial region of the lower back element 52i at the rear. The lower cover module 182i includes a cover element 184i. The cover element 184i is arranged in an upper region of the lower back element 52i. The cover element 184i is arranged in the center of the rear side of the lower back element 52i. The cover element 184i covers at least the lip 104i and the upper region 152i of the lower back element 52i. The cover element 184i is configured to cover the flexible upper region 152i of the lower backrest element 52i at the rear. The cover element 184i is connected to the lower backrest element 52i. The cover element is preferably releasably connected to the lower backrest element 52i via a form-fitting element, preferably in particular via a screw connection. The cover element 184i can preferably form a document bag 188i or other additional unit.

[0140] The cover element 184i does not cover the lower region of the lower back element 52i. The lower back element 52i forms a visible surface 186i in its lower region, the rear of which is not covered. The visible surface of the lower back element 52i is not covered by any of the cover elements 184i of the cover module 182i. The visible surface 186i of the lower back element 52i can be coated with a coating or film. In principle, it is also conceivable that the back element 52i does not have a coating on its visible surface 186i. The lower back element 52i, together with its visible surface 186i, forms the kick panel of the backrest 34i.

[0141] The aircraft seat arrangement includes an upper cover module 190i. The upper cover module 190i is configured to cover the upper region of the backrest 34i, in particular the pivotable backrest element 36i, at the rear. The upper cover module 190i includes a cover element 192i, which preferably extends over the entire rear side of the upper pivotable backrest element 36i. The upper cover module 190i preferably covers the lock modules 172i, 174i arranged laterally of the lock unit 88i. Preferably, the upper cover module 190i includes separately removable cover elements in the region of the lock modules 172i, 174i, which can be individually separated from the backrest element 36i for easy access to the lock modules 172i, 174i. The cover element 192i forms a document bag 194i in its upper region. The document bag 194i is arranged in the head region of the seat back 34i. The aircraft seat arrangement further comprises a pivotable table 196i, which can be folded onto the cover element 192i of the upper cover module 190i.

[0142] FIG. 21 illustrates a tenth exemplary embodiment of an aircraft seating apparatus according to the present invention. The aircraft seating apparatus is embodied substantially identically to the aircraft seating apparatus of the ninth exemplary embodiment. The aircraft seating apparatus includes a seat back 34j. The seat back 34j is configured to allow a person sitting in an aircraft seat 10j, of which the aircraft seating apparatus is a part, to rest their back against the seat back 34j. The seat back 34j includes a pivotable seat back element 36j. The pivotable seat back element 36j is pivotally supported by a mounting unit 12j. The aircraft seating apparatus includes a bearing device 42j. The bearing device 42j is configured to pivotally support the seat back 34j between an upright seating position and a comfortable position. The pivotable seat back element 36j includes a seat back frame 60j. The aircraft seating apparatus includes a restoring module 56j. The restoring module 56j is configured to restore the backrest 34j to an upright sitting position from a comfort position. The restoring module 56j has a locking unit 88j. The locking unit 88j is configured to lock or unlock the restoring module 56j. The locking unit 88j is configured to lock the backrest 34j, i.e., the pivotable backrest element 36j, in at least the upright sitting position and the comfort position.

[0143] The restoring module 56j includes a first spring element 58j and a second spring element 158j for providing a restoring force. In contrast to the previously described exemplary embodiment, the spring elements 58j, 158j are embodied as rod spring elements. The rod spring elements 58j, 158j are arranged in each case between a support element 170j attached to the backrest frame 60j and a support element 168j attached to the locking unit 178j. The spring elements 58j embodied as rod spring elements are supported on the respective support elements 168j, 170j by end regions with identical first sides. The restoring module 56j includes a biasing element 198j, on which the spring elements 58j embodied as rod spring elements can be supported by their opposing second sides. The biasing element 198j is arranged between the two support elements 168j, 180j. The biasing element 198j is disposed substantially centrally between the two support elements 168j, 170j. The biasing element 198j is embodied as a support bolt attached to the back frame. The biasing element 198j is screwed to the outside of the lateral frame element of the back frame 60j.

[0144] FIG. 22 shows an alternative implementation of the lower back element 52k in a further exemplary embodiment. The basic implementation of the aircraft seating apparatus is substantially identical to that of the ninth exemplary embodiment. The lower back element 52k is embodied to have flexibility in its upper region 152k. The lower back element 52k is embodied to be more flexible in its upper region 152k than the main region 102k disposed below it. The lower back element 52k is embodied to be elastically flexible in its upper region 152k. To provide flexibility in the upper region 152k, the lower back element 52k has a recess pattern 154k in the upper region 152k. The recess pattern 154k is formed by at least one recess 156k introduced into the lower back element 52k. The recess pattern 154k is arranged only in the upper region 152k. In this exemplary embodiment, the recesses 156k are embodied as wavy recesses 156k. The wavy recesses 156k extend in the transverse direction. Preferably, a plurality of wavy recesses 156k are arranged in a row and spaced apart from one another in the transverse direction. In principle, it is also conceivable that the recesses 156k have or form different shapes. [Explanation of symbols]

[0145] 10 aircraft seats 12 Mounting Unit 14 Aircraft Seat Row 16 aircraft seats 18 Seat legs 20 Seat legs 22 Crossbeam 24 Crossbeam 26 Seat structural elements 28 Seat structural elements 30 seating area 32 Seat bottom 34 Backrest 36 Pivotable backrest element 38 bearing points 40 bearing points 42 Bearing device 44 Rotation axis 46 Bearing bolt 48 Bearing bolt 50 knee area 52 Lower back element 54 Fastening Elements 56 Recovery Module 58 Spring Elements 60 Backrest frame 62 shell elements 64 Fastening Unit 66 Crossbeam 68 Fastening Unit 70 Fastening body 72 Fastening Elements 74 Fastening Elements 76 Through groove 78 Through groove 80 central area 82 Reception Area 84 Ribs 86 Ribs 88 Lock Unit 90 Actuating Elements 92 Armrest 94 Armrest 100 fabrics 102 Main area 104 Lip 106 Front 108 Lateral Stiffening Elements 110 Lever Gear 112 Basic holding elements 114 Fixed Receptacle 116 Fixed Receptacle 118 Lever element 120 bearing points 122 Connected Elements 124 Eccentric element 126 Eccentric element 128 mounting points 130 mounting points 132 Torsion tube 134 mounting points 136 mounting points 138 Lever element 140 Seat Shell Elements 142 Side Area 144 Side Area 146 aircraft seats 148 slots 150 slots 152 Upper area 154 recess pattern 156 Recess 158 Spring Elements 160 Central area 162 Spring leg 164 Spring leg 166 Bearing elements 168 Supporting Elements 170 Supporting Elements 172 Lock Module 174 Lock Module 176 First Lock Unit 178 Second lock unit 180 body 182 Lower Cover Module 184 Cover Elements 186 Visible surface 188 Document Bag 190 Cover Module 192 Cover Elements 194 Document Bag 196 tables 198 Deflection element

Claims

1. 38a, 40a; 38b, 40b; 38c, 40c; 38d, 40d; 38e, 40e; 38f, 40f; 38g, 40a; 38b, 40b; 38c, 40c; 38d, 40d; 38e, 40e; 38f, 40f; 38g, 40a; 38b, 40b; 38c, 40c; 38d, 40d; 38e, 40e; 38f, 40f; 38g, Two seat structural elements (26a, 28a; 26b, 28b; 26c, 28c; 26d, 28d; 26e, 28e; 26f, 28f; 26g, 28g; 26h, 28h) each have 40g; 38h, 40h) respectively, and are attached via the bearing points (38a, 40a; 38b, 40b; 38c, 40c; 38d, 40d; 38e, 40e; 38f, 40f; 38g, 40g; 38h, 40h) of the seat structural elements (26a, 28a; 26b, 28b; 26c, 28c; 26d, 28d; 26e, 28e; 26f, 28f; 26g, 28g; 26h, 28h) An aircraft seat comprising: a backrest (34a, 34b; 34c; 34d; 34e; 34f; 34g; 34h); and a bearing device (42a; 42b; 42c; 42d; 42e; 42f; 42g; 42h) configured to pivotably support the backrest (34a, 34b; 34c; 34d; 34e; 34f; 34g; 34h) and a pivotable backrest element (36a; 36b; 36c; 36d; 36e; 36f; 36g; 36h), wherein the backrest (34a, 34b; 34c; 34d; 34e; 34f; 34g; 34h) comprises a pivotable backrest element (36a; 36b; 36c; 36d; 36e; 36f; 36g; 36h), The seat is positioned such that at least one restoring module (56a; 56b; 56c; 56d; 56e; 56f; 56g; 56h) is configured to provide a restoring force to restore the backrest (34a, 34b; 34c; 34d; 34e; 34f; 34g; 34h) from the comfort position to the upright seating position, for this purpose the bearing points (38a, 40a; 38b, 40b; 26c, 28c; 26d, 28d; 26e, 28e; 26f, 28f; 26g, 28g; 26h, 28h) of the seat structural elements (26a, 28a; 26b, 28b; 26c, 28c; 26d, 28d; 26e, 28e; 26f, 28f; 26g, 28g; 26h, 28h) are configured to provide a restoring force to restore the backrest (34a, 34b; 34c; 34d; 34e; 34f; 34g; 34h; 34h) from the comfort position to the upright seating position, for this purpose the bearing points (38a, 40a; 38b, 40b;An aircraft seating device characterized by being at least substantially located in the region above 38c, 40c; 38d, 40d; 38e, 40e; 38f, 40f; 38g, 40g; 38h, 40h).

2. The aircraft seating device according to claim 1, characterized in that the seat structural elements (26a-26h, 28a-28h) extend upward in their rear region at least substantially to the armrest height (X) away from the mounting unit (12a-12h), and each of the seat structural elements (26a-26h, 28a-28h) has bearing points (38a-38h, 40a-40h) at its rear upper end for supporting the pivotable backrest elements (36a-36h).

3. The aircraft seating device according to claim 1 or 2, characterized in that the restoring module (56a-56h) has at least one spring element (58a-58h) configured to provide a restoring force.

4. The aircraft seating device according to claim 3, characterized in that the backrest (34a-34h) has lower backrest elements (52a-52h) that form a lower region of the backrest (34a-34h) and are fixed to the seat structural elements (26a-26h, 28a-28h).

5. The aircraft seating device according to claim 4, characterized in that the lower backrest elements (52a-52h) extend from the height of at least one crossbeam (22a-22h, 24a-24h) to a height of 450 mm to 700 mm measured from the mounting surface.

6. The aircraft seating device according to claim 4, characterized in that the spring elements (58a-58h) are embodied as leaf spring elements and are configured to be attached to the lower backrest elements (52a-52h) or the mounting unit (12a-12h).

7. The aircraft seating device according to claim 3, characterized in that the backrest (34a-34h) has a crossbeam (66a-66h) in the region above the bearing points (38a-38h, 40a-40h), and the spring elements (58a-58h), which are embodied as leaf spring elements, are attached to the crossbeam (66a-66h) in order to transmit a restoring force to the pivotable backrest elements (36a-36h).

8. The aircraft seating device according to claim 4, characterized in that the lower backrest element (52a-52h) has an upper lip (104b) at its upper end that extends to a region above the bearing points (38a-38h, 40a-40h) for supporting the backrest (34a-34h).

9. The aircraft seating device according to claim 1 or 2, characterized in that the pivotable backrest elements (36a-36h) include a backrest frame (60a-60h) and a fabric clamped to the backrest frame (60a-60h), or a shell element (62a-62h) coupled to the backrest frame (60a-60h).

10. The aircraft seating device according to claim 1, characterized in that the restoration module (56a-56h) is embodied as a gas pressure spring and has spring elements (58e-58f) located in the region above the bearing points (38a-38h, 40a-40h).

11. The aircraft seating device according to claim 10, characterized in that the restoring module (56a-56h) has at least one lever gear (110e-110f) configured to transmit a restoring force to the pivotable backrest elements (36a-36h).

12. The aircraft seating device according to claim 11, characterized in that the restoration module (56a-56h) has a torsion tube (132f) that transmits the restoration force from one side to the opposite side of the pivotable backrest element (36a-36h).

13. The aircraft seating device according to claim 1 or 2, characterized in that the bearing points (38a-38h, 40a-40h) for supporting the pivotable backrest elements (36a-36h) define a rotation axis (44a-44h) located above the knee region (50a-50h) of the backrest (34a-34h).

14. The aircraft seating device according to claim 6, characterized in that the spring elements (58a-58h), which are embodied as leaf spring elements for providing restoring force, are formed integrally with the lower backrest elements (52a-52h).

15. The aircraft seating device according to claim 3, characterized in that the spring elements (58a-58h) for generating a restoring force are formed at least partially integrally with the pivotable backrest elements (36a-36h).

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