Aircraft seat arrangement

Abstract

The invention relates to an aircraft seat arrangement, comprising: a mounting unit (12a; 12b; 12b; 12c, 12c; 12 d; 12e, 12e; 12f, 12f; 12 g; 12h), the mounting unit (12a; 12b; 12b; 12c, 12c; 12 d; 12e, 12e; 12f, 12f; 12 g; 12h) is provided for mounting on the cabin floor and has at least one transverse carrier (22a, 24a; 22b, 24b; 22c, 24c; 22 d, 24 d; 22e, 24e; 22f, 24f; 22 g, 24 g; 22 h, 24 h); the two seat structural elements (26a, 28a; 26b, 28b; 26c, 28c; 26d, 28d; 26d, 28d; 26e, 28e; 26e, 28e; 26f, 28f, 26f, 28f; 26 g, 28 g; 26h, 28h), which seat structure elements (26a, 28a; 26b, 28b; 26c, 28c; 26d, 28d; 26d, 28d; 26e, 28e; 26e, 28e; 26f, 28f, 26f, 28f; 26 g, 28 g; 26h, 28h) are each arranged in a seat region (30a; 30b; 30b; 30c, 30c; 30 d; 30e, 30e; 30f, 30f; 30 g; 30h) and each having a bearing position (38a, 40a; 38b, 40b; 38c, 40c; 38d, 40d; 38d, 40d; 38e, 40e; 38f, 40f, 38f, 40f; 38 g, 40 g; 38 h, 40 h); the backrest (34a; 34a, 34b; 34c, 34c; 34d, 34d; 34e; 34e; 34f, 34f; 34 g; 34h), the backrest (34a, 34b; 34c, 34c; 34d, 34d; 34e; 34e; 34f, 34f; 34 g; 34h) through the seat structural element (26a, 28a; 26b, 28b; 26c, 28c; 26d, 28d; 26d, 28d; 26e, 28e; 26e, 28e; 26f, 28f, 26f, 28f; 26 g, 28 g; 38a, 40a; 38b) of the support position (26h, 26h, 28h); 38b, 40b; 38c, 40c; 38d, 40d; 38d, 40d; 38e, 40e; 38f, 40f, 38f, 40f; 38 g, 40 g; 38h, 40h), and a method for manufacturing the same; and a support device (42a; 42b; 42c; 42c; 42d; 42d; 42e; 42e; 42f; 42f; 42 g; 42h), the support means (42a; 42b; 42c; 42c; 42d; 42d; 42e; 42e; 42f; 42f; 42 g; 42 h) is arranged to define a position of the backrest (34a; 34a, 34b; 34c, 34c; 34d, 34d; 34e; 34e; 34f, 34f; 34 g; 34h) is pivotally supported between an upright seating position and a comfort position, in which the backrest (34a; 34a, 34b; 34c, 34c; 34d, 34d; 34e; 34e; 34f, 34f; 34 g; 34h) comprises a pivotable backrest element (36a; 36b; 36b; 36c, 36c; 36d, 36d; 36e; 36e; 36f, 36f; 36 g; 36h) of the method. It is proposed that the aircraft seat device has at least one reset module (56a; 56b; 56b; 56c; 56c; 56d; 56d; 56e; 56e; 56f; 56f; 56 g; 56h), the reset module (56a; 56b; 56b; 56c; 56c; 56d; 56d; 56e; 56e; 56f; 56f; 56 g; 56h) is provided at least for providing a support for supporting the backrest (34a; 34a, 34b; 34c, 34c; 34d, 34d; 34e; 34e; 34f, 34f; 34 g; 34h) from the comfort position to the upright seat position and for this purpose is at least substantially arranged on the seat structural element (26a, 28a; 26b, 28b; 26c, 28c; 26d, 28d; 26d, 28d; 26e, 28e; 26e, 28e; 26f, 28f, 26f, 28f; 26 g, 28 g; 38a, 40a; 38b) of the support position (26h, 26h, 28h); 38b, 40b; 38c, 40c; 38d, 40d; 38d, 40d; 38e, 40e; 38f, 40f, 38f, 40f; 38 g, 40 g; 38h, 40h) in a region above the first region.

Description

Technical Field

[0001] The invention relates to an aircraft seat arrangement according to the preamble of claim 1 . Background Art

[0002] An aircraft seat arrangement has been proposed, comprising: a mounting unit, which is arranged for mounting on a cabin floor and has at least one transverse carrier, two seat structure elements, which are each arranged on one side of the seat area and each have a bearing position, a backrest, which is attached via the bearing positions of the seat structure elements, and a bearing device, which is arranged to pivotably support the backrest between an upright seat position and a comfort position, wherein the backrest comprises a pivotable backrest element. Summary of the invention

[0003] The object of the invention is in particular to provide a universal device for passengers with improved properties in terms of compactness and advantageously large leg freedom. According to the invention, this object is achieved by the features of claim 1, while advantageous embodiments and improvements of the invention can be obtained from the dependent claims.

[0004] The invention relates to an aircraft seat arrangement, comprising: a mounting unit, which is arranged for mounting on a cabin floor and has at least one transverse carrier; two seat structure elements, which are each arranged on one side of a seat area and each have a bearing position; a backrest, which is attached via the bearing positions of the seat structure elements; and a bearing device, which is arranged to pivotally support the backrest between an upright seat position and a comfort position, wherein the backrest comprises a pivotable backrest element.

[0005] It is proposed that the aircraft seat device has at least one reset module, which is at least provided for providing a reset force for resetting the backrest from the comfort position to the upright seat position and is arranged at least substantially in the area above the support position of the seat structure element. An "aircraft seat device" should preferably be understood as at least one part, such as a subassembly, of an aircraft seat, in particular an aircraft passenger seat. In principle, it is also conceivable that the aircraft seat device substantially or completely constitutes an aircraft seat. An "aircraft seat" should be understood as a seat for passengers, which is arranged to stand upright on the cabin floor of an aircraft. The aircraft seat is preferably formed as part of an aircraft seat row consisting of a plurality of aircraft seats arranged side by side. The aircraft seat preferably comprises: at least one seat bottom, which forms a seat area for passengers; and a backrest, which provides a backrest resting surface, on which a passenger sitting on the aircraft seat can rest his back. In addition, the aircraft seat has a mounting unit, by which the aircraft seat stands upright on the cabin floor, and to which further components, such as a seat bottom and a backrest, are attached. A "mounting unit" is preferably understood to mean a basic structure of an aircraft seat, which basic structure forms the load-bearing structure of the aircraft seat. The aircraft seat is attached to a mounting plane, i.e. in particular the cabin floor, via the mounting unit. The mounting unit preferably has at least two seat feet and at least one transverse element, which is coupled to the seat feet. The transverse element forms a load-bearing tube. Preferably, the mounting unit 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 via a plurality of fittings, preferably to corresponding fastening rails in the cabin floor. The mounting unit forms the load-bearing structure of the aircraft seat, preferably an aircraft seat row.

[0006] A "seat structural element" is preferably to be understood as a part of the load-bearing structure of the aircraft seat, to which other components of the aircraft seat, such as a backrest, a backrest element or an armrest, can be fastened. The seat structural element is preferably designed as a seat separator. The seat structural element designed as a seat separator is preferably rigidly connected to at least one transverse element, preferably two transverse elements, of the mounting unit. The seat structural element designed as a seat separator preferably extends substantially horizontally from the front transverse element into the area behind the rear transverse element. In the area behind the rear transverse element, the seat structural element designed as a seat separator extends away from the mounting plane in a substantially vertical direction, preferably to the height of the armrests. In principle, it is also conceivable that the seat structural element is designed as a single piece with a part of the seat shell, for example with the lower backrest element. Here, the seat structural element designed as a single piece can, for example, be designed by a side area of ​​the seat shell.

[0007] A "supporting position" is preferably understood to mean an attachment point, by means of which a component, such as a backrest element, can be firmly attached. By means of the supporting position, the component can preferably be attached not only rigidly, but also movably. Preferably, the supporting position is arranged to attach another component, such as, in particular, a backrest element, movably, preferably pivotably, to the component forming the supporting position. A "supporting device" is understood to mean a module, by means of which a backrest, in particular a pivotable backrest element, is pivotably supported on a unit, such as, in particular, a mounting unit. The supporting device can preferably be formed by a supporting bolt. In principle, it is also conceivable that the supporting device is formed by a hinge or other supporting mechanism, by means of which a backrest, in particular a pivotable backrest element, is pivotably supported. The supporting device forms an axis of rotation, about which the backrest, in particular the pivotable backrest element, can be pivoted. "The backrest is pivotable" is understood to mean that at least one pivotable backrest element of the backrest can be pivoted relative to the mounting structure, i.e., the mounting unit. A "pivotable backrest element" is preferably understood to mean a backrest element which forms at least a part, preferably a major part, of the backrest surface of the backrest. The pivotable backrest element is pivotably supported relative to a mounting unit, in particular relative to a bearing position of a seat structure element, in order to form a comfort position and an upright seat position. The pivotable backrest element has a load-bearing base structure and forms the backrest surface in its inner region. Preferably, the pivotable backrest element has a backrest frame and a covering or shell element connected to the backrest frame, which forms the backrest surface. In principle, it is also conceivable that the pivotable backrest element is formed by a sandwich component. Here, it is conceivable that the pivotable backrest element does not have a backrest frame.

[0008] An “upright seat position” is to be understood as the maximum upright seat position of the aircraft seat, which must be assumed for safety reasons, in particular during the take-off phase, the landing phase and during turbulence. The upright seat position is designed as a so-called TTL position (Taxi, Takeoff, Landing). In the upright seat position, the backrest, in particular the pivotable backrest element, and the seat bottom of the aircraft seat are essentially perpendicular to one another, preferably at an angle of between 95 and 115 degrees. A “comfort position” is to be understood as a rearward-tilted seat position of the aircraft seat, in which at least the backrest, in particular the pivotable backrest element, is tilted rearward against the seat direction of the aircraft seat, so that a passenger sitting on the aircraft seat can achieve a comfortable rearward-tilted seat position. In principle, it is also conceivable that in the comfort position, in addition to the pivotable backrest element, the seat bottom is also tilted differently from the upright seat position of the aircraft seat. In the comfort position, the backrest, in particular the pivotable backrest element, and the seat bottom can have a different, particularly advantageously greater angle to one another than in the upright seat position (TTL position). In the comfort position, the backrest, in particular the pivotable backrest element, is pivoted backwards from the maximum upright seat position by at least 3 degrees, preferably by at least 5 degrees, particularly preferably by more than 8 degrees.

[0009] A "reset module" is preferably understood to mean a module which is provided to apply a reset force for resetting a backrest, in particular a movably mounted backrest element, in order to move the backrest, in particular the backrest element, from a position, in particular a comfort position, into an upright seating position. For this purpose, the reset module preferably has an element which provides a force for adjusting the backrest, in particular a pivotable backrest element. The element for providing the reset force is preferably designed as a spring element.

[0010] The reset module has a locking unit. The locking unit is arranged to lock or unlock the reset module itself and / or the pivotable backrest element. The locking unit has a locked state and an unlocked state. In its locked state, the locking unit locks the reset module and / or the pivotable backrest element, and the reset module cannot apply a reset force to the pivotable backrest element. In its unlocked state, the reset module is unlocked by the locking unit and can apply a reset force to the backrest, especially the pivotable backrest element, so as to adjust the backrest to its upright seat position. The locking unit preferably has at least one locking element, which mechanically locks the reset module itself and / or the pivotable backrest element. The locking element is preferably configured as a shape-fitting element and / or a force-fitting element. The locking element can be adjusted between a locked position and an unlocked position. Preferably, the locking element can be adjusted between its locked position and its unlocked position by means of a mechanical adjustment element, such as a Bowden cable. In principle, it is also conceivable that the locking element can be adjusted between its locked position and its unlocked position by means of an electric actuator, such as an electromagnetic actuator. For example, it is also conceivable that the locking element is formed as part of an electronic actuator, in particular an electromechanical actuator. Therefore, it is conceivable that the reset module and / or the pivotable backrest element can be electrically or electronically locked or unlocked by means of a locking unit. "Substantially in the region above the support position" should preferably be understood as such a region, which is at least partially, preferably mostly located above the support position. Here, however, the region can also extend at least partially below the support position. Preferably, at least the locking unit of the reset module and a part of the element for providing the reset force are located above the support position of the backrest. Particularly preferably, at least one third, preferably at least half, and particularly preferably at least two thirds of the element for generating the reset force, i.e. the spring element, are also arranged above the support position of the seat structure element. "Above the support position" should be understood as on the side opposite to the mounting plane, i.e. the bottom of the cabin. "Set" should be understood in particular as being specially designed and / or equipped. Setting an object to a specific function should be understood in particular as that the object performs and / or implements the specific function in at least one application state and / or operating state.

[0011] The aircraft seat is designed as a seat with purely mechanical adjustment. In particular, the backrest, in particular the pivotable backrest element, is adjusted only by adjustment forces applied by the passenger and / or by the force of spring elements. The aircraft seat preferably has no electromechanical actuators by which electrical adjustment of the aircraft seat, in particular electrical adjustment of the aircraft seat, in particular the backrest and / or the seat bottom, between an upright seat position and a comfort position can be achieved. The aircraft seat is preferably not designed as a business seat or first-class seat with electronic aircraft seat adjustment.

[0012] The design according to the invention advantageously provides a particularly compact aircraft seat device in which the resetting module is particularly advantageously arranged. Particularly advantageously, the design according to the invention provides an aircraft seat that offers a particularly advantageous degree of leg freedom for passengers, in particular for passengers sitting behind the aircraft seat. The design according to the invention allows the backrest to be particularly narrow in the area below the bearing point. As a result, the aircraft seat is particularly narrow, in particular in the knee area, and has a particularly advantageously large degree of leg freedom.

[0013] In addition, it is proposed that the seat structure element extends upwards away from the mounting unit in its rear region at least substantially to the backrest height, wherein the seat structure element has a support position for supporting the pivotable backrest element at its rear upper end. The "rear region of the seat structure element" should be understood as the rear region opposite to the front end when viewed relative to the seat direction of the aircraft seat. The "armrest height" should preferably be understood as such a height at which an aircraft seat device, especially an armrest of an aircraft seat, is arranged and an arm support surface for a passenger is provided. The armrest height is preferably 550mm to 700mm relative to the cabin bottom. The armrest height should preferably be understood as such a height at which the armrest is placed on the mounting unit of the aircraft seat. Thus, a particularly advantageously high rotation point for the backrest, especially the pivotable backrest element, can be provided, thereby providing a particularly advantageously large leg freedom for passengers sitting at the rear.

[0014] In addition, it is proposed that the reset module has at least one spring element, which is arranged to provide a reset force. "Spring element" should preferably be understood as an element that provides a spring force at least in one direction. Preferably, the spring element is configured as a pressure spring. The spring element is arranged to apply pressure in one direction. In principle, it is conceivable that the spring element is configured as a mechanical spring, such as a spiral spring. In principle, it is also conceivable that the spring element is configured as a gas spring. It is also conceivable that the spring element is configured as an element different from a gas spring or a spiral spring. It is preferably conceivable that the spring element is configured as a leaf spring element. The spring element preferably has an actuated state and an unactuated state. In the actuated state, the spring element is arranged to provide its spring force as a reset force. The actuated state is preferably configured as an unlocked state of the locking unit. The unactuated state of the spring element is configured as a locked state of the spring element. In the unactuated state, the spring element is arranged not to provide a spring force as a reset force. The unactuated state is preferably configured as a locked state of the locking unit. Thus, a reset module for generating a reset force can be particularly simply configured.

[0015] In addition, it is proposed that the backrest has a lower backrest element, which constitutes the lower area of ​​the backrest and is fastened to the seat structure element. "Lower backrest element" should preferably be understood as an element that rigidly constitutes 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 that the lower shell element is composed of an aluminum shell or other metal, especially a metal shell made of light metal. The lower backrest element is preferably constructed as a separate element. The lower backrest element is preferably rigidly, that is, immovably fastened to the seat structure element. In principle, it is also conceivable that the lower backrest element is constructed in one piece with the seat shell of the seat bottom. In this way, the backrest can be constructed particularly advantageously and easily.

[0016] Furthermore, it is proposed that the lower backrest element extends from the height of the at least one transverse carrier to a height of 450 mm-700 mm measured from the mounting plane. Here, the height of the lower backrest element is measured on a vertical axis orthogonal to the mounting plane. Preferably, the backrest element extends to a height of 500 mm to 650 mm. As a result, the backrest element can be designed particularly advantageously.

[0017] Furthermore, it is proposed that the spring element is designed as a leaf spring element and is arranged to be attached to the lower backrest element or to the mounting unit. Preferably, the spring element designed as a leaf spring element is arranged in the upper region of the lower backrest element. The spring element designed as a leaf spring element is preferably attached in the upper half, preferably in the upper third, of the lower backrest element. "Attached" should preferably be understood as firmly connected or abutted. The spring element designed as a leaf spring element is attached to the lower backrest element with a first end. The spring element designed as a leaf spring element is preferably attached to the pivotable backrest element with a second end. The spring element designed as a leaf spring element can preferably be directly or indirectly connected to the pivotable backrest element or the lower backrest element. Preferably, the reset module for attaching the spring element designed as a leaf spring element to the pivotable backrest element has a first fastening unit. Preferably, the reset module for attaching the leaf spring element to the lower backrest element has a second fastening unit. Preferably, optionally, the first fastening unit or the second fastening unit is designed as a floating bearing, by means of which the leaf spring element can be moved relative to the pivotable backrest element or the lower backrest element at least in one direction. In principle, it is also conceivable that both fastening units are designed as floating bearings. In principle, it is also conceivable that the spring element designed as a leaf spring element is attached to a mounting unit, for example to a transverse element or a seat structure element. A "leaf spring element" is preferably understood to be an elongated spring element which is arranged in the covered state to provide a spring force which is arranged substantially orthogonal to the main extension direction of the leaf spring element. As a result, the spring element of the reset module can be designed in a particularly simple and space-saving manner.

[0018] Furthermore, it is proposed that the backrest has a transverse carrier in the region above the bearing point, to which a spring element designed as a leaf spring element is attached in order to transmit the restoring force to the pivotable backrest element. The spring element designed as a leaf spring element can be rigidly connected to the transverse carrier or can be formed integrally with the transverse carrier. In principle, it is also conceivable that the spring element designed as a leaf spring element is attached to the transverse carrier in a movably, for example slidably, manner. Preferably, the connection between the spring element designed as a leaf spring element and the transverse carrier has at least one degree of freedom. As a result, the force transmission of the restoring force into the backrest, in particular into the pivotable backrest element, can be carried out particularly advantageously.

[0019] In addition, it is proposed that the lower backrest element has an upper lip on its upper end, which extends into the area above the supporting position for supporting the backrest. "Lip" should preferably be understood as an area extending away from an area, especially away from the upper edge of the backrest element at least in a sub-area. The lip preferably extends at least through a sub-area of ​​the upper edge of the backrest element. The lip is preferably arranged centrally on the upper edge of the backrest element. In principle, it is also conceivable that the lip extends through the entire width of the upper edge of the backrest element. The lip is preferably formed in one piece with the remainder of the lower backrest element. The lip is formed in one piece with the backrest element formed by the shell element. The lip has a higher flexibility than the remainder of the backrest element. Preferably, the lip is formed by fewer layers than the remainder of the backrest element formed as a shell element. Thus, a particularly advantageous transition can be produced between the lower backrest element and the cover or shell element of the upper pivotable backrest element.

[0020] Furthermore, it is proposed that the pivotable backrest element has a backrest frame and a covering which is tensioned on the backrest frame or a shell element connected to the backrest frame. A "backrest frame" is preferably understood to mean a rigid frame which rotates in at least three directions, in the middle of which a covering which forms the backrest surface is arranged. A "covering" is understood to mean a fabric which covers the middle region which is tensioned by the backrest frame and which forms the backrest surface in the covered state. The backrest frame with the covering forms a pivotably supported upper backrest element. As a result, the backrest can be formed particularly simply and easily.

[0021] Furthermore, it is proposed that the reset module has a spring element designed as a gas pressure spring, which is arranged in the region above the bearing point. Thus, a particularly easily actuatable spring element for the reset module can be provided.

[0022] Furthermore, it is proposed that the restoring module has at least one lever transmission which is provided to transmit the restoring force to the pivotable backrest element. As a result, the force transmission for the restoring force can be designed particularly advantageously and advantageously small spring elements can be used.

[0023] Furthermore, it is proposed that the restoring module has a torsion tube which transmits the restoring force from one side of the backrest to the opposite side. Preferably, the restoring force of the restoring module is transmitted directly to the torsion tube. The torsion tube is arranged to be rotated to adjust the backrest, in particular the pivotable backrest element. As a result, the restoring of the backrest can be carried out particularly advantageously and evenly.

[0024] Furthermore, it is proposed that the bearing position for supporting the pivotable backrest element defines an axis of rotation, which is arranged above the knee area of ​​the backrest. A "knee area" is preferably understood to be a region of the backrest in which the knees of a passenger sitting behind the aircraft seat are arranged. The knee area is preferably designed as a region that extends from the lower end of the backrest into a region that is at least 650 mm, particularly preferably 700 mm, above the mounting plane. The knee area is preferably designed as a region of the backrest between 400 mm and 700 mm measured from the mounting plane, particularly preferably as a region of the backrest between 450 mm and 650 mm measured from the mounting plane. As a result, a particularly advantageous knee area can be provided for a passenger sitting behind the aircraft seat.

[0025] Furthermore, it is proposed that the spring element for providing the restoring force, which is configured as a leaf spring element, is configured in one piece with the lower backrest element. Thus, the spring element, which is configured as a leaf spring element, can be configured particularly easily.

[0026] Furthermore, it is proposed that the spring element for generating the restoring force is at least partially formed in one piece with the pivotable backrest element. "Single piece" is to be understood in particular to mean at least materially connected, for example by welding, gluing, injection molding and / or other processes which appear reasonable to a person skilled in the art, and / or advantageously formed as one component, for example by production using a casting and / or by production using a single-component or multi-component injection molding method and advantageously from a single blank. "The spring element formed as a leaf spring element is at least partially formed in one piece with the pivotable backrest element" is preferably to be understood to mean that at least a subregion of the spring element formed as a leaf spring element is formed by the pivotable backrest element. As a result, the backrest can be designed to be particularly narrow in the region of the lower backrest element.

[0027] In this context, the aircraft seat device according to the invention should not be limited to the applications and embodiments described above. In particular, the aircraft seat device according to the invention may have a number of elements, components and units different from the number mentioned herein to perform the functions described herein. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Further advantages result from the following description of the drawings. Eleven embodiments of the invention are shown in the drawings. The drawings, the description and the claims contain many combined features. It is also appropriate for a person skilled in the art to consider these features individually and to summarize them into other meaningful combinations. In the drawings:

[0029] Figure 1 shows a schematic representation of an aircraft seat row with an aircraft seat arrangement in a first embodiment, the aircraft seat arrangement having a backrest with an upper backrest rotation point and a return module having a spring element designed as a leaf spring element;

[0030] Figure 2 shows a schematic rear view of an aircraft seat bench with a restoring module and a spring element designed as a leaf spring element;

[0031] Figure 3 shows a schematic side view of two aircraft seat rows and a pivotable backrest element in an upright seat position and a comfort position;

[0032] Figure 4 A detailed view of the attachment of a spring element designed as a leaf spring element by means of a fastening unit is shown;

[0033] Figure 5 shows a schematic representation of an aircraft seat row with an aircraft seat arrangement in a second embodiment, the aircraft seat arrangement having a backrest with an upper backrest rotation point, the backrest with a covering, and a return module with a spring element designed as a leaf spring element;

[0034] Figure 6 shows a schematic rear view of an aircraft seat having a covered backrest element with a covering and a restoring module with a spring element designed as a leaf spring element;

[0035] Figure 7 shows a schematic diagram of a pivotable backrest element in a third embodiment of an aircraft seat arrangement, the pivotable backrest element forming a spring element which is formed as a leaf spring element;

[0036] Figure 8 shows a schematic representation of an aircraft seat arrangement in a fourth embodiment, the aircraft seat arrangement having a restoring module with a spring element designed as a leaf spring element, which is formed by a lower backrest element;

[0037] Fig. 9 A schematic diagram of an aircraft seat device in a fifth embodiment is shown, the aircraft seat device having a restoring module, the restoring module having a spring element designed as a gas pressure spring and a lever transmission;

[0038] Fig.10 shows a schematic detailed view of a pivotable backrest element with a spring element designed as a gas spring and a lever mechanism;

[0039] Fig.11 shows a schematic detailed view of a reset module having a spring element designed as a gas pressure spring and a lever transmission;

[0040] Fig.12 A schematic diagram of an aircraft seat device in a sixth embodiment is shown, the aircraft seat device having a restoring module having a spring element designed as a gas pressure spring and a lever transmission having a torsion tube;

[0041] Fig.13 a schematic detail view showing a pivotable backrest element in an upright seat position;

[0042] Fig.14 a schematic detail view showing a pivotable backrest element in a comfort position;

[0043] Fig.15 is a schematic diagram of an aircraft seat arrangement in a seventh embodiment, the aircraft seat arrangement having a pivotable backrest with a lower backrest rotation point and a return module having a spring element designed as a leaf spring element;

[0044] Fig.16 shows a schematic representation of an aircraft seat arrangement in an eighth embodiment, the aircraft seat arrangement having a seat shell element, which forms a seat bottom and a lower backrest element, and a return module having a spring element designed as a leaf spring element;

[0045] Fig.17 shows a schematic diagram of an aircraft seat row with an aircraft seat arrangement in a ninth embodiment, the aircraft seat arrangement having a backrest with an upper backrest rotation point and a return module;

[0046] Fig.18 shows a schematic rear view of an aircraft seat in a ninth embodiment;

[0047] Fig.19 shows a schematic side view of an aircraft seat in a ninth embodiment;

[0048] Fig. 20 shows a schematic diagram of an upper backrest element with a restoring module having two spring elements designed as helical springs;

[0049] Fig.21A schematic diagram of an upper backrest element of an aircraft seat arrangement in a tenth embodiment is shown, the upper backrest element having a restoring module with two spring elements designed as rod springs; and

[0050] Fig. 22 A highly schematic illustration of a lower backrest element of an aircraft seat arrangement in an eleventh embodiment is shown. DETAILED DESCRIPTION

[0051] Figures 1 to 4 An aircraft seat arrangement in a first embodiment is shown. Here, the aircraft seat arrangement is part of an aircraft seat 10a. The aircraft seat 10a stands upright in the aircraft cabin of the aircraft in the installed state. The aircraft seat 10a is arranged to be firmly mounted on the cabin floor of the aircraft cabin in the installed state. The aircraft seat arrangement has a mounting unit 12a. With the aid of the mounting unit 12a, the aircraft seat 10a can stand upright on the cabin floor of the aircraft cabin. The cabin floor constitutes a mounting plane. The aircraft seat 10a is configured as part of an aircraft seat row 14a. The aircraft seat 10a is preferably configured as part of an aircraft seat row 14a comprising more than one aircraft seat 10a. An aircraft seat row 14a having two aircraft seats 10a, 16a is shown by way of example in the figures. The aircraft seat row 14a shown by way of example has a second aircraft seat 16a. Another 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 that only one aircraft seat 10a is described in detail below. In principle, it is also conceivable that the aircraft seat row 14a has three or more aircraft seats 10a, 16a. Here, the mounting unit 12a is designed as a common mounting unit 12a for the aircraft seats 10a, 16a of the aircraft seat row 14a. The mounting unit 12a comprises two seat feet 18a, 20a. The seat feet 18a, 20a are each coupled to fastening rails via a fitting, not shown in detail, which fastening rails are firmly connected to the cabin floor. The fitting can be firmly locked in the fastening rails.

[0052] The mounting unit 12a has two transverse supports 22a, 24a. The transverse supports 22a, 24a are designed as support tubes. The front transverse support 22a is arranged in the front region of the aircraft seat 10a. The rear transverse support 24a is arranged in the rear region of the aircraft seat 10a. The transverse supports 22a, 24a extend in the transverse direction of the aircraft seat 10a. The transverse supports 22a, 24a extend at least substantially through the entire transverse extension of all aircraft seats 10a of the aircraft seat row 14a. The aircraft seat device has two seat structure elements 26a, 28a. The two seat structure elements 26a, 28a are each arranged on one side of a seat area 30a of the aircraft seat device. The two seat structure elements 26a, 28a are each arranged on the side of the seat area 30a formed by the aircraft seat 10a. The seat structure elements 26a, 28a are designed as seat separators. The seat structure elements 26a, 28a are arranged on the transverse supports 22a, 24a. Seat structure elements 26a, 28a are fastened to transverse carriers 22a, 24a spaced apart from each other in the transverse direction. Seat structure elements 26a, 28a are connected to transverse carriers 22a, 24a in a positioning manner. Seat structure elements 26a, 28a are connected to front transverse carrier 22a on their front ends respectively. Here, seat structure elements 26a, 28a are preferably connected to front transverse carrier 22a in a force fit and / or form fit manner. Seat structure elements 26a, 28a are configured to be substantially L-shaped. Seat structure elements 26a, 28a each have a first sub-region, which is substantially horizontally oriented in the installed state. Seat structure elements 26a, 28a each have a second sub-region, which is substantially vertically oriented in the installed state. The second sub-region of seat structure elements 26a, 28a is arranged in the rear region of aircraft seat 10a. The second sub-region of seat structure elements 26a, 28a extends to the rear end of seat structure elements 26a, 28a. The second sub-region of the seat structural elements 26a, 28a constitutes the rear region of the seat structural elements 26a, 28a. Thus, the seat structural elements 26a, 28a extend upwards away from the mounting unit 12a, in particular the mounting plane, in their rear region. The seat structural elements 26a, 28a extend upwards in their rear region substantially to the armrest height X. The seat structural elements 26a, 28a extend to the armrest height X of the aircraft seat 10a. The armrest height X is 650 mm. In principle, it can be preferably envisaged that the armrest height X is located in a region between 500 mm and 700 mm.

[0053] The seat structural elements 26a, 28a designed as seat separators are provided to fasten different components of the respective aircraft seat 10a, 16a to the aircraft seat 10a, 16a, as described at least in part in detail below. In principle, it is also conceivable that the mounting unit 12a has no seat structural elements 26a, 28a or has seat structural elements 26a, 28a of a different design and that the respective components of the aircraft seat 10a, 16a are attached to the mounting unit 12a in a different manner.

[0054] The aircraft seat arrangement comprises a seat bottom 32a. The seat bottom 32a forms the seat area 30a. The seat bottom 32a forms the seat surface of the aircraft seat 10a. The seat bottom 32a has a body and a cushioning element firmly arranged on the body. The cushioning element forms the seat surface of the aircraft seat 10a. The seat bottom 32a is attached to the mounting unit 12a. The seat bottom 32a is attached in particular to the transverse carriers 22a, 24a. The seat bottom 32a is coupled to the backrest 34a. The seat bottom 32a is directly coupled to the backrest 34a.

[0055] The aircraft seat arrangement comprises a backrest 34a. Here, the backrest 34a is arranged so that a person sitting on the aircraft seat 10a can support his back on the backrest 34a, and the aircraft seat arrangement is part of the aircraft seat 10a. The backrest 34a preferably has a cushioning portion, which is not shown in detail. The backrest 34a constitutes a backrest support surface. The backrest 34a is arranged on the rear end of the seat bottom 32a. The backrest 34a is arranged pivotably relative to the mounting unit 12a. The backrest 34a is attached to the seat structural elements 26a, 28a. Here, the aircraft seat 10a constitutes a seat direction. The seat direction is defined as the direction in which a passenger sits on the aircraft seat 10a. The seat direction is orthogonal to the backrest surface of the backrest 34a and extends parallel to the mounting plane in the direction of the front end of the seat bottom 32a.

[0056] The backrest 34a is pivotally constructed. The backrest 34a is arranged to pivot between the upright seat position and the comfort position. The backrest 34a is arranged to pivot relative to the mounting unit 12a. The backrest 34a can pivot relative to the seat structure elements 26a, 28a. The backrest 34a has a pivotable backrest element 36a. The pivotable backrest element 36a is pivotally supported on the mounting unit 12a. The pivotable backrest element 36a is pivotally attached to the seat structure elements 26a, 28a. The seat structure elements 26a, 28a each have a supporting position 38a, 40a for supporting the backrest 34a. The supporting positions 38a, 40a are arranged to support the pivotable backrest element 36a thereon. The pivotable backrest element 36a is pivotally attached to the seat structure elements 26a, 28a through the supporting positions 38a, 40a. The bearing locations 38a, 40a are designed as bearing receptacles. The bearing locations 38a, 40a define the position, in particular the height, of the rotation axis 44a about which the backrest 34a, in particular the pivotable backrest element 36a, is pivotably supported. Figure 3 In FIG. 1 , the backrest 34a is schematically shown in dotted form in a comfort position. The pivotable backrest element 36a is Figure 3 The pivotable backrest element 36a' is shown in dotted form in the comfort position. The pivotable backrest element 36a' is pivoted backwards from the upright seat position by about 10 degrees against the seat direction to its comfort position. In principle, it is also conceivable that the pivotable backrest element 36a' in the comfort position is pivoted backwards by only 5 or 8 degrees from the upright seat position.

[0057] The aircraft seat device has a supporting device 42a. The supporting device 42a is arranged to pivotally support the backrest 34a between the upright seat position and the comfort position. The supporting device 42a is arranged to pivotally support the pivotable backrest element 36a between the upright seat position and the comfort position. The supporting device 42a constitutes the rotation axis 44a. The pivotable backrest element 36a can be pivoted around the rotation axis 44a by means of the supporting device 42a. The supporting device 42a has two supporting bolts 46a, 48a. The supporting bolts 46a, 48a constitute the rotation axis 44a. The supporting bolts 46a, 48a are respectively connected to one of the supporting positions 38a, 40a of one of the seat structure elements 26a, 28a. The supporting bolts 46a, 48a are preferably arranged on the corresponding supporting positions 38a, 40a in a rotationally fixed manner. The pivotable backrest element 36a is rotatably supported on the supporting bolts 46a, 48a. Preferably, the pivotable backrest element 36a is pivotably supported on the support bolts 46a, 48a via a sliding bearing. In principle, it is also conceivable that the pivotable backrest element 36a is rotatably supported on the support bolts 46a, 48a by means of a rolling bearing. In principle, it is also conceivable that the support bolts 46a, 48a are rotatably attached to the corresponding support positions 38a, 40a of the seat structure elements 26a, 28a via suitable bearings.

[0058] The pivotable backrest element 36a has a backrest frame 60a. The backrest frame 60a constitutes the bearing structure of the pivotable backrest element 36a. The backrest frame 60a is configured as a revolving frame. The backrest frame 60a is preferably configured to be substantially U-shaped. The backrest frame 60a has two lateral frame elements and an upper frame element, which connects the two lateral frame elements to the upper end of the backrest frame 60a. At the lower end, the backrest frame 60a is preferably open. The lower end of the backrest frame 60a constitutes the lower end of the pivotable backrest element 36a. The supporting bolts 46a, 48a are each attached to the backrest frame 60a of the pivotable backrest element 36a on the facing lateral frame elements at the lower end of the backrest frame 60a.

[0059] The pivotable backrest element 36a has a shell element 62a. The shell element 62a is configured as a plate-like element. The shell element 62a is formed by fiber reinforced plastic. The shell element 62a is formed, for example, by GFK or CFK. The shell element 62a is configured to constitute the backrest support surface of the pivotable backrest element 36a. The shell element 62a is arranged in the inner region of the pivotable backrest element 36a, which is tensioned by the backrest frame 60a. The shell element 62a is firmly connected to the backrest frame 60a of the pivotable backrest element 36a. The shell element 62a is firmly connected to the lateral frame element of the backrest frame 60a at least in a sub-region. Preferably, the shell element 62a is attached to the upper frame element of the backrest frame 60a at the upper end. The shell element 62a preferably constitutes the backrest profile of the pivotable backrest element 36a. The shell element 62a is configured to have a cushioning element of the backrest 34a arranged thereon.

[0060] The pivotable backrest element 36a has a transverse carrier 66a. The transverse carrier 66a is arranged in the region above the bearing positions 38a, 40a. The transverse carrier 66a is arranged approximately in the middle of the pivotable backrest element 36a when viewed in the vertical direction. The transverse carrier 66a is attached between the lateral frame elements of the backrest frame 60a. The transverse carrier 66a extends between the lateral frame elements of the backrest frame 60a. The transverse carrier 66a is firmly connected to the corresponding lateral frame elements of the backrest frame 60a respectively. The transverse carrier 66a is preferably screwed to the lateral frame elements of the backrest frame 60a. In principle, it is also conceivable that the transverse carrier 66a is bonded to the lateral frame elements of the backrest frame 60a, or is otherwise connected in a form-fitting, force-fitting and / or material-fitting manner. The transverse carrier 66a is preferably provided for strengthening the backrest frame 60a, in particular for strengthening the entire pivotable backrest element 36a. Preferably, the transverse carrier 66a can be provided as a further mounting element on which the backrest 34a is fastened. For example, it is conceivable that a pivotable table element, a cup holder, a tray holder or a high document bag is attached to the backrest 34, in particular the pivotable backrest element 36a, on the transverse carrier 66a.

[0061] The backrest 34a is designed as a backrest with a high backrest rotation point. The backrest rotation point is formed by the rotation axis 44a of the bearing device 42a. The backrest rotation point, i.e. the rotation axis 44a of the bearing device 42a, is arranged above the knee area 50a of the aircraft seat 10a. The knee area 50a of the aircraft seat 10a extends from the cabin bottom to a height of 650 mm. The knee area 50a is arranged as an area in which a passenger sitting behind the aircraft seat 10a can place his knees.

[0062] In order to form a high backrest rotation point, the seat structure elements 26a, 28a form their support positions 38a, 40a for supporting the backrest 34a in the high area. The seat structure elements 26a, 28a each form their support positions 38a, 40a on the upper end. The seat structure elements 26a, 28a form their support positions 38a, 40a on the upper end of the second sub-region behind it, which is away from the installation plane. The support positions 38a, 40a of the seat structure elements 26a, 28a are arranged above the knee area 50a. The support positions 38a, 40a of the seat structure elements 26a, 28a are arranged at the armrest height X. The support positions 38a, 40a for supporting the pivotable backrest element 36a define a rotation axis 44a arranged above the knee area 50a of the backrest 34a.

[0063] The pivotable backrest element 36a constitutes the backrest 34a above the bearing positions 38a, 40a of the seat structure elements 26a, 28a. The pivotable backrest element 36a constitutes only the upper region of the backrest 34a. The pivotable backrest element 36a is configured as an upper backrest element. The pivotable backrest element 36a constitutes the backrest support surface of the backrest 34a in the region above the armrest height X. The pivotable backrest element 36a is preferably arranged substantially only in the region above the armrest height X. The region only for attaching the backrest element 36a to the seat structure elements 26a, 28a extends below the armrest height X.

[0064] The backrest 34a has a lower backrest element 52a. The lower backrest element 52a is rigidly constructed. The lower backrest element 52a is preferably immovably constructed. The lower backrest element 52a constitutes the lower region of the backrest 34a. The lower backrest element 52a constitutes a backrest support surface in the lower region of the backrest 34a. The lower backrest element 52a is firmly fastened to the seat structure elements 26a, 28a. The lower backrest element 52a extends substantially between the height of the transverse carriers 22a, 24a of the mounting unit 12a and the lower end of the pivotable backrest element 36a. The lower backrest element 52a preferably extends to just below the armrest height X. The lower backrest element 52b extends from the height of the transverse carriers 22a, 24a to a height of about 450mm to 700mm measured from the mounting plane. The lower backrest element 52a preferably extends to a height of 600mm measured from the mounting plane.

[0065] The lower backrest element 52a is formed by a shell element. The lower backrest element 52a is formed by a shell made of fiber reinforced plastic. For example, it is conceivable that the lower backrest element 52a is composed of a GFK shell or a CFK shell. The lower backrest element 52a preferably has an easily bendable shape. The lower backrest element 52a is laterally connected to one of the seat structure elements 26a, 28a by every two fastening elements 54a. In principle, it is also conceivable that the lower backrest element 52a is at least partially formed in one piece with the seat bottom 32a, especially the seat shell. In principle, it is also conceivable that the lower backrest element 52a is at least partially or completely formed by a covering.

[0066] The aircraft seat arrangement has a reset module 56a. The reset module 56a is arranged to reset the backrest 34a from the comfort position to the upright seat position. The reset module 56a is arranged to reset the backrest 34a from its pivoted seat position to the upright seat position. The reset module 56a is arranged to reset the pivotable backrest element 36a. The reset module 56a is arranged to provide a reset force to reset the backrest 34a, in particular to reset the pivotable backrest element 36a. The reset module 56a is arranged to apply a reset force to the pivotable backrest element 36a to reset the backrest 34a. The reset module 56a is at least substantially arranged in the area above the bearing positions 38a, 40a of the seat structure elements 26a, 28a. The reset module 56a is at least substantially arranged above the armrest height X, i.e., on the side facing away from the mounting plane. The reset module 56a is at least mostly arranged above the knee area 50a of the backrest 34a. By such an arrangement of the restoring module 56a, the knee region 50a of the backrest 34a can preferably be substantially free of components of the restoring module 56a. In particular, the larger components of the restoring module 56a can advantageously be arranged above the armrest height X and thus outside the knee region 50a of the backrest 34a.

[0067] The reset module 56a has a spring element 58a to provide a reset force. In principle, it is also conceivable that the reset module 56a has a plurality of spring elements 58a to provide a reset force. The spring element 58a is arranged to apply a spring force to the pivotable backrest element 36a so that the pivotable backrest element 36a pivots in the direction of its upright seat position. The spring force of the spring element 58a forms the reset force of the reset module 56a. The spring element 58a is functionally arranged between the pivotable backrest element 36a and the mounting unit 12a. The spring element 58a is arranged to be supported on the mounting unit 12a with a first side. The spring element 58a is arranged to be supported on the backrest 34a with a second side, in particular on the pivotable backrest element 36a. Thus, the spring element 58a can transfer the reset force from the fixed mounting unit 12a to the pivotable backrest element 36a.

[0068] The spring element 58a is configured as a leaf spring element. The spring element 58a configured as a leaf spring element is configured as an elongated member. The spring element 58a configured as a leaf spring element is functionally arranged between the lower backrest element 52a and the pivotable backrest element 36a. The spring element 58a configured as a leaf spring element is attached to the lower backrest element 52a with its first lower end. The spring element 58a configured as a leaf spring element is supported on the lower backrest element 52a with its lower end. The spring element 58a configured as a leaf spring element is attached in the upper region of the lower backrest element 52a. Therefore, the spring element 58a configured as a leaf spring element partially extends into the region below the rotation axis 44a, i.e., the armrest height X. The spring element 58a configured as a leaf spring element is attached to the pivotable backrest element 36a with its second upper end. The spring element 58a configured as a leaf spring element is supported on the pivotable backrest element 36a with its second upper end. The spring element 58a designed as a leaf spring element preferably extends into a central region of the pivotable backrest element 52a.

[0069] In order to attach the spring element 58a, which is configured as a leaf spring element, to the pivotable backrest element 36a, the reset module 56a has a first fastening unit 64a. The spring element 58a, which is configured as a leaf spring element, is firmly attached to the pivotable backrest element 36a by means of the first fastening unit 64a. The spring element 58a, which is configured as a leaf spring element, is rigidly and immovably connected to the pivotable backrest element 36a by means of the first fastening unit 64a. In principle, it is also conceivable that the spring element 58a, which is configured as a leaf spring element, is movably connected to the pivotable backrest element 36a by means of the first fastening unit 64a at least with one degree of freedom. In addition, it is also conceivable that the spring element 58a, which is configured as a leaf spring element, rests only on the pivotable backrest element 36a with its upper end. Here, it is conceivable that the spring element 58a, which is configured as a leaf spring element, slides with its upper end on the pivotable backrest element 36a, in particular on the rear side of the shell element 62a. The spring element 58a designed as a leaf spring element is attached to the transverse carrier 66a for transmitting the restoring force. The spring element 58a designed as a leaf spring element is directly attached to the transverse carrier 66a via a fastening unit 64a. Via the transverse carrier 66a, the restoring force provided by the spring element 58a designed as a leaf spring element can be uniformly transmitted to both sides of the pivotable backrest element 36a.

[0070] In order to attach the spring element 58a configured as a leaf spring element to the lower backrest element 52a, the reset module 56a has a second fastening unit 68a. The spring element 58a configured as a leaf spring element is attached to the lower backrest element 52a in a loss-proof manner through the second fastening unit 68a. The spring element 58a configured as a leaf spring element is movably attached to the lower backrest element 52a through the second fastening unit 68a. The second fastening unit 68a has a fastening body 70a. The fastening body 70a is firmly attached to the rear side of the lower backrest element 52a. The fastening body 70a of the second fastening unit 68a has a receiving portion, which is arranged to receive the spring element 58a configured as a leaf spring element. The spring element 58a configured as a leaf spring element is displaceably supported in the receiving portion of the fastening body 70a. The receiving portion of the fastening body 70a constitutes a displacement axis, along which the spring element 58a configured as a leaf spring element is displaceably supported. The displacement axis is oriented vertically in the installed state. The fastening unit 68a has two fastening elements 72a, 74a, which attach the spring element 58a, which is configured as a leaf spring element, to the fastening body 70a. The fastening elements 72a, 74a are configured as fastening screws. In principle, it is also conceivable that the fastening elements 72a, 74a are configured in a different way. In order to attach to the fastening body 70a, the spring element 58a, which is configured as a leaf spring element, has two through-grooves 76a, 78a. The fastening elements 72a, 74a are guided by the through-grooves 76a, 78a to attach the spring element 58a, which is configured as a leaf spring element.

[0071] The spring element 58a configured as a leaf spring element is at least partially integrated into the pivotable backrest element 36a. The spring element 58a configured as a leaf spring element is partially integrated into the shell element 62a of the pivotable backrest element 36a. The spring element 58a configured as a leaf spring element is arranged to be received in the shell element 62a of the pivotable backrest element 36a. The shell element 62a of the pivotable backrest element 36a has a middle area 80a. The middle area 80a is arranged centrally between the lateral frame elements of the backrest frame 60a with respect to the transverse direction. The spring element 58a configured as a leaf spring element is at least partially integrated into the middle area 80a of the shell element 62a. The shell element 62a has a receiving area 82a for the spring element 58a configured as a leaf spring element on its rear side in the middle area 80a. The receiving area 82a extends from the lower end of the shell element 62a in the middle area 80a to the area below the transverse carrier 66a. In principle, it is also conceivable that the spring element 58a designed as a leaf spring element rests only on the rear side of the shell element 62a in the middle region 80a. It is also conceivable that the spring element 58a designed as a leaf spring element does not contact the shell element 62a in the middle region 80a.

[0072] The pivotable backrest element 36a has elastic ribs 84a, 86a extending laterally outwards from the middle area 80a in the lower area. In the embodiment, three elastic ribs 84a, 86a are shown as examples on each side. The elastic ribs 84a, 86a extend from the middle area 80a to the lateral frame elements of the backrest frame 60a. The ribs 84a, 86a arranged adjacently on one side of the middle area 80a are spaced apart from each other in the vertical direction. The elastic ribs 84a, 86a can be elastically deformed independently of each other. The elastic ribs 84a, 86a have a shape that bends forward along the seat direction. The elastic ribs 84a, 86a are preferably formed with the shell element 62a, especially with the middle area 80a one-piece type. In principle, it can also be imagined that the elastic ribs 84a, 86a are at least partially formed separately from the shell element 62a. Here, it is particularly conceivable that ribs 84a, 86a are partially constituted as separate elements, which are connected to the middle area 80a of shell element 62a, especially shell element 62a. Here, it is particularly conceivable that the ribs 84a, 86a constituted separately can be detachably attached to shell element 62a. Thus, when ribs 84a, 86a are damaged, ribs 84a, 86a can be advantageously easily replaced. Preferably, ribs 84a, 86a with different rigidities can be particularly easily arranged at different positions of pivotable backrest element 36a by ribs 84a, 86a constituted detachably. Thus, pivotable backrest element 36a can be constituted particularly easily and differently rigidly in different sub-areas. Preferably, ribs 84a, 86a of different shapes can be easily arranged at different positions of pivotable backrest element 36a by ribs 84a, 86a constituted detachably. As a result, the pivotable backrest element 36 a can be configured particularly easily with different or adaptable ergonomic features.

[0073] The reset module 56a has a locking unit 88a. The locking unit 88a is arranged to lock or unlock the reset module 56a. The locking unit 88a is arranged to lock the backrest 34a, i.e. the pivotable backrest element 36a, at least in the upright seat position and the comfort position. Preferably, it is also conceivable that the locking unit 88a is arranged to lock the pivotable backrest element 36a in another position. Here, the other position of the pivotable backrest element 36a is particularly configured as a pivotable position, which is located between the upright seat position and the comfort position. The locking unit 88a has a locked state and an unlocked state. In its locked state, the locking unit 88a locks the reset module 56a, and the reset module 56a cannot apply a reset force to the pivotable backrest element 36a. In its unlocked state, the locking unit 88a unlocks the reset module 56a, and the reset module 56a can apply a reset force to the pivotable backrest element 36a. The locking unit 88a is arranged to lock the pivotable backrest element 36a in its locked state at its current position. In the locked state of the locking unit 88a, the pivotable backrest element 36a is fixed 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 firmly fixed relative to the mounting unit 12a. Preferably, the pivotable backrest element 36a is firmly fixed relative to the seat structure elements 26a, 28a in the locked state of the locking unit 88a.

[0074] The locking unit 88a is preferably arranged between the pivotable backrest element 36a, in particular the backrest frame 60a and one of the seat structural elements 26a, 28a in terms of functional technology. In principle, it is also conceivable that the locking unit 88a is arranged between the backrest frame 60a and the two seat structural elements 26a, 28a in terms of functional technology. The locking unit 88a preferably has at least one locking element. The locking element of the locking unit 88a is preferably arranged to lock the reset module 56a in the locked state of the locking unit 88a. The locking element of the locking unit 88a is preferably arranged to directly lock the pivotable backrest element 36a. The locking element of the locking unit 88a is arranged to lock the pivotable backrest element 36a in a form-fitting manner. The locking element of the locking unit 88a is arranged to engage in the corresponding form-fitting element of the locking unit 88a in the locked state of the locking unit 88a in a form-fitting manner. The locking unit 88a has corresponding form-fitting elements for each stoppable position, i.e., for the upright seat position and the comfort position of the pivotable backrest element 36a. In principle, it is also conceivable that the locking unit 88a is arranged to lock the pivotable backrest element 36a in a force-fitting manner and has at least one force-fitting element for this purpose. In principle, it is also conceivable that the locking unit 88a is arranged to lock the pivotable backrest element 36a in a force-fitting manner and has at least one force-fitting element for this purpose. In principle, it is also conceivable that the locking unit 88a is arranged to lock the pivotable backrest element 36a in a force-fitting manner and a form-fitting manner. The locking unit 88a has an actuating element 90a, by means of which the locking unit 88a can be adjusted from a locked state to an unlocked state. The actuating element 90a is arranged to be actuated by a passenger sitting on the aircraft seat 10a. The actuating element 90a is preferably configured as a button. The actuating element 90a is coupled to the locking element of the locking unit 88a by a suitable connecting element, such as, in particular, a Bowden cable, so that the locking element is adjusted between its locked position and unlocked position.

[0075] 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 positions 38a, 40a of the seat structure 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 element and the correspondingly formed shape-fitting element of the locking unit 88a for locking the pivotable backrest element 36a are arranged above the bearing positions 38a, 40a and the armrest height X. The individual components of the locking unit 88a, for example, in particular the actuating element 90a and the Bowden cable, can also be partially arranged below the armrest height X.

[0076] The aircraft seat arrangement has two armrests 92a, 94a. The armrests 92a, 94a are part of an aircraft seat 10a of an aircraft seat row 14a. The armrests 92a, 94a are each arranged at the side of a seat area 30a of the aircraft seat 10a. The armrests 92a, 94a are attached at an armrest height X. The armrests 92a, 94a are attached to the mounting unit 12a at an armrest height X with a rear end. 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 locations 38a, 40a of seat structural elements 26a, 28a configured 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 backrest 34a. The armrests 92a, 94a are attached to the seat structure elements 26a, 28a by the same bearing bolts 46a, 48a as the pivotable backrest element 36a. The armrests 92a, 94a are preferably pivotally attached to the seat structure elements 26a, 28a. The armrests 92a, 94a can be pivoted by the same axis of rotation 44a as the pivotable backrest element 36a. In principle, it is also conceivable that the armrests 92a, 94a are attached to the seat structure elements 26a, 28a in a rotationally fixed manner. The actuating element 90a of the locking unit 88a is preferably introduced into one of the armrests 92a, 94a.

[0077] Alternatively, it is also conceivable that the spring element 58a designed as a leaf spring element is attached directly to the mounting unit 12a. Here, it is conceivable that the spring element 58a designed as a leaf spring element is attached directly to the rear transverse carrier 24a of the mounting unit 12a, instead of being attached to the lower backrest element 52a. Here, it is conceivable that the spring element 58a designed as a leaf spring element is arranged in the lateral area, directly in the area of ​​one of the laterally arranged seat structure elements 26a, 28a. As a result, the middle area of ​​the knee area 50a of the backrest 34a can advantageously be designed without a spring element 58a.

[0078] exist Figures 5 to 22 The following description and drawings are essentially limited to the differences between the embodiments, wherein, for components with the same names, in particular for components with the same reference numerals, reference can also be made in principle to the drawings and / or the description of other embodiments, in particular Figures 1 to 4 To distinguish the embodiments, the letter a is appended to Figures 1 to 4 After the reference numerals of the embodiments in the Figures 5 to 22 In the embodiment of the present invention, the letter a is replaced by letters b to k.

[0079] Figure 5 and Figure 6A second embodiment of an aircraft seat arrangement according to the invention is shown. Here, the aircraft seat arrangement is part of an aircraft seat 10b. The aircraft seat 10b stands upright in the aircraft cabin of an aircraft in the installed state. The aircraft seat arrangement has a mounting unit 12b. With the aid of the mounting unit 12b, the aircraft seat 10b can stand upright on the cabin floor of the aircraft cabin. The aircraft seat 10b is configured as part of an aircraft seat row 14b. The aircraft seat row 14b shown by way of example has a second aircraft seat 16b. Here, the mounting unit 12b is configured as a common mounting unit for the aircraft seats 10b, 16b of the aircraft seat row 14b. The mounting unit 12b comprises two seat feet 18b, 20b. The mounting unit 12b has two transverse carriers 22b, 24b.

[0080] The aircraft seat device has two seat structure elements 26b, 28b. The two seat structure elements 26b, 28b are each arranged on one side of the seat area 30b of the aircraft seat device. The two seat structure elements 26b, 28b are each arranged on the side of the seat area 30b formed by the aircraft seat 10b. The seat structure elements 26b, 28b are configured as seat partitions. The seat structure elements 26b, 28b are arranged on the transverse carriers 22b, 24b. The seat structure elements 26b, 28b are configured to be essentially L-shaped. Therefore, the seat structure elements 26b, 28b extend upwards away from the mounting unit 12b, in particular the mounting plane, in their rear region. The seat structure elements 26b, 28b extend upwards in their rear region to essentially the armrest height X. The seat structure elements 26b, 28b extend to the armrest height X of the aircraft seat 10b.

[0081] The aircraft seat arrangement comprises a backrest 34b. The backrest 34b is arranged so that a person sitting on the aircraft seat 10b can support his back on the backrest 34b, and the aircraft seat arrangement is a part of the aircraft seat 10b. The backrest 34b is arranged pivotably relative to the mounting unit 12b. The backrest 34b is attached to the seat structure elements 26b, 28b. The backrest 34b is arranged to pivot between the upright seat position and the comfort position. The backrest 34b has a pivotable backrest element 36b. The pivotable backrest element 36b is pivotably supported on the mounting unit 12b. The pivotable backrest element 36b is pivotably attached to the seat structure elements 26b, 28b. The seat structure elements 26b, 28b each have a support position 38b, 40b for supporting the backrest 34b. The support positions 38b, 40b are arranged to support the pivotable backrest element 36b thereon.

[0082] The aircraft seat device has a supporting device 42b. The supporting device 42b is arranged to pivotally support the backrest 34b between the upright seat position and the comfort position. The supporting device 42b is arranged to pivotally support the pivotable backrest element 36b between the upright seat position and the comfort position. The supporting device 42b forms a rotation axis 44b. The pivotable backrest element 36b can be pivoted around the rotation axis 44b by means of the supporting device 42b. The supporting device 42b has two supporting bolts 46b, 48b. The supporting bolts 46b, 48b form the rotation axis 44b. The supporting bolts 46b, 48b are each connected to one of the supporting positions 38b, 40b of one of the seat structure elements 26b, 28b.

[0083] The pivotable backrest element 36b has a backrest frame 60b. The backrest frame 60b constitutes the load-bearing structure of the pivotable backrest element 36b. The backrest frame 60b is configured as a revolving frame. The backrest frame 60b is preferably configured as a substantially U-shaped. The backrest frame 60b has two lateral frame elements and an upper frame element, which connects the two lateral frame elements to the upper end of the backrest frame 60b. On the lower end, the backrest frame 60b is preferably open. The lower end of the backrest frame 60b constitutes the lower end of the pivotable backrest element 36b. The supporting bolts 46b, 48b are each attached to the backrest frame 60b of the pivotable backrest element 36b on the facing lateral frame elements on the lower end of the backrest frame 60b.

[0084] The backrest 34b is designed as a backrest with a high backrest rotation point. The backrest rotation point, i.e. the rotation axis 44b of the bearing device 42b, is arranged above the knee area 50b of the aircraft seat 10b. In order to form the high backrest rotation point, the seat structure elements 26b, 28b form their bearing positions 38b, 40b for supporting the backrest 34b in the high area. The bearing positions 38b, 40b of the seat structure elements 26b, 28b are arranged above the knee area 50b. The bearing positions 38b, 40b of the seat structure elements 26b, 28b are arranged at the armrest height X.

[0085] Unlike the first embodiment, the pivotable backrest element 36b has a covering 100b. The covering 100b is stretched on the backrest frame 60b. The covering 100b is formed by a fabric stretched between the lateral frame elements of the backrest frame 60b. In principle, it is conceivable that the covering 100b is also attached to the upper frame element of the backrest frame 60b. The covering 100b extends from the lower end of the backrest frame 60b into the upper end region of the backrest frame 60b.

[0086] The backrest 34b has a lower backrest element 52b. The lower backrest element 52b is rigidly constructed. The lower backrest element 52b is preferably immovably constructed. The lower backrest element 52b constitutes the lower region of the backrest 34b. The lower backrest element 52b constitutes a backrest support surface in the lower region of the backrest 34b. The lower backrest element 52b is firmly fastened to the seat structure elements 26b, 28b. The lower backrest element 52b is formed by a shell element. The lower backrest element 52b is composed of fiber reinforced plastic. The lower backrest element 52b is preferably formed by multi-layer fiber reinforced plastic. For example, it is conceivable that the lower backrest element 52b is composed of one or more GFK layers or one or more CFK layers. The lower backrest element 52b has a main area 102b. The main area 102b basically constitutes the backrest support surface of the lower backrest element 52b and is basically constructed in the same way as the lower backrest element of the first embodiment.

[0087] Unlike the first embodiment, the lower backrest element 52b has a lip 104b on its upper end. The lip 104b is directly connected to the upper end of the main area 102b of the lower backrest element 52b. The lip 104b constitutes the upper end area of ​​the lower backrest element 52b. The lip 104b is formed in a single piece with the rest of the lower backrest element 52b. The lip 104b is arranged centrally on the upper end of the lower backrest element 52b in the transverse direction. In principle, it is also conceivable that the lower backrest element 52b also has two or more eccentrically arranged lips 104b, which are arranged on its upper end. If the lower backrest element 52b has a plurality of lips 104b on its upper end, these lips 104b are preferably arranged symmetrically with respect to the middle axis of the lower backrest element 52b. The lip 104b of the lower backrest element 52b extends above the support positions 38b, 40b for supporting the pivotable backrest element 36b. The lip 104b of the lower backrest element 52b extends to the rear of the area of ​​the pivotable backrest element 36b, in particular to the rear of the cover 100b of the pivotable backrest element 36b. The lip 104b is arranged so that the cover 100b of the pivotable backrest element 36b can be attached thereto with its lower end. The cover 100b is attached to the front side 106b of the lip 104b of the lower backrest element 52b with its lower end. The cover 100b is preferably removably attached to the front side 106b of the lip 104b by means of a fleece tape and a hook tape. In principle, it is also conceivable that the cover 100b is connected to the lip 104b of the lower backrest element 52b in other ways, for example, by bonding.

[0088] The aircraft seat arrangement has a resetting module 56b. The resetting module 56b is provided for resetting the backrest 34b from the comfort position to the upright seat position. The resetting module 56b is provided for resetting the backrest 34b from the pivoted seat position to the upright seat position. The resetting module 56b is at least substantially arranged in the area above the bearing positions 38b, 40b of the seat structural elements 26b, 28b. The resetting module 56b is at least substantially arranged above the armrest height X, i.e. on the side facing away from the mounting plane. The resetting module 56b is at least mostly arranged above the knee region 50b of the backrest 34b.

[0089] The reset module 56b has a spring element 58b to provide a reset force. The spring element 58b is arranged to exert a spring force on the pivotable backrest element 36b so that the pivotable backrest element 36b is pivoted in the direction of the upright seat position. The spring element 58b is configured as a leaf spring element. The spring element 58b configured as a leaf spring element is attached to the lower backrest element 52b with its first lower end. The spring element 58b configured as a leaf spring element is attached in the upper region of the lower backrest element 52b. The spring element 58b configured as a leaf spring element is attached in the main region 102b of the lower backrest element 52b below the lip 104b.

[0090] In order to attach the spring element 58b configured as a leaf spring element to the pivotable backrest element 36b, the reset module 56b has a first fastening unit 64b. Through the first fastening unit 64b, the spring element 58b configured as a leaf spring element is firmly attached to the pivotable backrest element 36b. The pivotable backrest element 36b has a transverse carrier 66b. The transverse carrier 66b is arranged in the area above the bearing position 38b, 40b. The transverse carrier 66b is arranged behind the cover 100b. The spring element 58b configured as a leaf spring element is directly attached to the transverse carrier 66b by the fastening unit 64b. In order to attach the spring element 58b configured as a leaf spring element to the lower backrest element 52b, the reset module 56b has a second fastening unit 68b. Through the second fastening unit 68b, the spring element 58b configured as a leaf spring element is attached to the lower backrest element 52b in a loss-proof manner. The spring element 58 b , which is designed as a leaf spring element, is movably attached to the lower backrest element 52 b via the second fastening unit 68 b .

[0091] The reset module 56b has a locking unit 88b. The locking unit 88b is arranged to lock or unlock the reset module 56b. The locking unit 88b is arranged to lock the backrest 34b, i.e. the pivotable backrest element 36b, at least in the upright seat position and the comfort position. The locking unit 88b is preferably arranged between the pivotable backrest element 36b, in particular the backrest frame 60b and one of the seat structure elements 26b, 28b in terms of functional technology. The locking unit 88b is arranged above the knee area 50b of the backrest 34b. The locking unit 88b is preferably arranged in the area above the bearing position 38b, 40b of the seat structure elements 26b, 28b. The locking unit 88b is preferably basically, i.e. mostly, arranged above the armrest height X.

[0092] Figure 7 A third embodiment of an aircraft seat arrangement according to the invention is shown. The aircraft seat arrangement is part of an aircraft seat 10c which is partially shown. The aircraft seat 10c is Figures 1 to 4 The aircraft seat of the first embodiment is constructed essentially identically and is therefore not described in detail here. The aircraft seat has a mounting unit, which is not shown in detail. The aircraft seat arrangement comprises two seat structural elements, which are connected to the mounting unit, which are not shown in detail and are designed as seat partitions. The seat structural elements extend to the armrest height X of the aircraft seat 10c.

[0093] The aircraft seat arrangement comprises a backrest 34c. The backrest 34c constitutes a backrest support surface. The backrest 34c is attached to a seat structural element. The backrest 34c is pivotably constructed. The backrest 34c is arranged to pivot between an upright seat position and a comfort position. The backrest 34c has a pivotable backrest element 36c. The backrest 34c is constructed as a backrest with a high backrest rotation point. The backrest rotation point is formed by the rotation axis 44c of the bearing device 42c. The pivotable backrest element 36c is pivotably attached to the seat structural element. The seat structural elements each have a supporting position 38c, 40c for supporting the backrest 34c. The pivotable backrest element 36c has a backrest frame 60c. The backrest frame 60c constitutes a bearing structure of the pivotable backrest element 36c. The pivotable backrest element 36c has a shell element 62c. The shell element 62c is constructed as a plate-shaped element. The shell element 62c is formed by fiber reinforced plastic. The shell element 62c is formed, for example, from GFK or CFK. The shell element 62c is arranged to form the backrest support surface of the pivotable backrest element 36c. The shell element 62c is firmly connected to the backrest frame 60c of the pivotable backrest element 36c. The shell element 62c preferably forms the backrest contour of the pivotable backrest element 36c. The backrest 34c has a lower backrest element, which is not shown in detail. The lower backrest element is also formed by a shell element.

[0094] The aircraft seat device has a reset module 56c. The reset module 56c is provided for resetting the backrest 34c from the comfort position to the upright seat position. The reset module 56c is provided for resetting the pivotable backrest element 36c. The reset module 56c is provided to provide a reset force to reset the backrest 34c, in particular to reset the pivotable backrest element 36c. The reset module 56c has a spring element 58c to provide the reset force. The spring element 58c is configured as a leaf spring element. Different from the first embodiment, the spring element 58c configured as a leaf spring element is at least partially formed in one piece with the pivotable backrest element 36c. The spring element 58c configured as a leaf spring element is formed in one piece with the shell element 62c of the pivotable backrest element 36c. The spring element 58c configured as a leaf spring element is formed by the middle area 80c of the shell element 62c. The spring element 58c configured as a leaf spring element is integrated into the middle area 80c of the shell element 62c. The spring element 58c designed as a leaf spring element is embedded in the fiber-reinforced layer of the shell element 62c. The spring element 58c designed as a leaf spring element is preferably formed as a leaf spring element that is embedded in the shell element 62c by a manufacturing method. However, it is also conceivable in principle that the spring element 58c designed as a leaf spring element is formed by a fiber layer of the shell element 62c in the middle area 80c itself.

[0095] At the upper end, the spring element 58c, which is formed in one piece with the shell element 62c, can form a transverse reinforcement element 108c. The transverse reinforcement element 108c is formed in one piece with the spring element 58c and is therefore formed in one piece with the shell element 62c. The transverse reinforcement element 108c is provided, like the transverse carrier of the first embodiment, for better introduction of the restoring force into the pivotable backrest element 36c. The pivotable backrest element 36c preferably does not have a separate transverse carrier in this embodiment. In principle, it is also conceivable that the spring element 58c, which is formed as a leaf spring element, does not have a transverse reinforcement element 108c. The pivotable backrest element 36c has elastic ribs 84c, 86c extending laterally outward from the middle area 80c in the lower region. The elastic ribs 84c, 86c extending outward can also preferably be formed in one piece with the spring element 58c, which is formed as a leaf spring element. In order to attach the spring element 58c designed as a leaf spring element to the lower backrest element, the restoring module 56c has a fastening unit 68c, which is designed identically to the fastening unit in the first embodiment. The fastening unit 68c is composed of at least through grooves 76c, 78c designed as elongated holes in the lower end of the spring element 58c.

[0096] The reset module 56c has a locking unit, not shown in detail here, which is configured substantially the same as the locking unit in the previous embodiment. The locking unit is preferably arranged between the pivotable backrest element 36c, in particular the backrest frame 60c and one of the seat structure elements in terms of functional technology. The locking unit is preferably arranged in the area above the bearing position of the seat structure element. The locking unit is preferably arranged substantially, i.e. mostly, above the armrest height X.

[0097] Figure 8 A fourth embodiment of an aircraft seat device according to the invention is shown. The aircraft seat device is part of a partially shown aircraft seat 10d. The aircraft seat has a mounting unit 12d. With the aid of the mounting unit 12d, the aircraft seat 10d can be erected on the cabin floor of the aircraft cabin. The mounting unit 12d has two transverse carriers 24d. The aircraft seat device has two seat structure elements 26d, 28d. The two seat structure elements 26d, 28d are each arranged on one side of a seat area 30d of the aircraft seat device. The two seat structure elements 26d, 28d are each arranged on the side of the seat area 30d formed by the aircraft seat 10d. The seat structure elements 26d, 28d are configured as seat partitions. The seat structure elements 26d, 28d are arranged on the transverse carrier 22d. The seat structure elements 26d, 28d are configured to be substantially L-shaped. Therefore, the seat structure elements 26d, 28d extend upwards away from the mounting unit 12d, in particular the mounting plane, in their rear region. The seat structural elements 26d, 28d extend in their rear region upwards substantially to the armrest height X. The seat structural elements 26d, 28d extend to the armrest height X of the aircraft seat 10d.

[0098] The aircraft seat device comprises a backrest 34d. The backrest 34d is arranged pivotably relative to the mounting unit 12d. The backrest 34 is attached to the seat structure elements 26d, 28d. The backrest 34d is arranged to pivot between the upright seat position and the comfort position. The backrest 34d has a pivotable backrest element 36d. The pivotable backrest element 36d is rotatably supported on the mounting unit 12d. The seat structure elements 26d, 28d each have a supporting position 38d, 40d for supporting the pivotable backrest element 36d. The aircraft seat device has a supporting device 42d. The supporting device 42d is arranged to pivotally support the backrest 34d between the upright seat position and the comfort position. The supporting device 42d is arranged to pivotally support the pivotable backrest element 36d between the upright seat position and the comfort position. The supporting device 42d constitutes a rotation axis 44d. The supporting device 42d has two supporting bolts 46d, 48d. The support bolts 46d, 48d form the axis of rotation 44d. The support bolts 46d, 48d are each connected to one of the bearing positions 38d, 40d of one of the seat structural elements 26d, 28d. The backrest 34d is designed as a backrest with a high backrest rotation point. The backrest rotation point, i.e. the axis of rotation 44d of the bearing device 42d, is arranged above the knee area 50d of the aircraft seat 10d. In order to form the high backrest rotation point, the seat structural elements 26d, 28d form their bearing positions 38d, 40d for supporting the backrest 34d in the high area. The bearing positions 38d, 40d of the seat structural elements 26d, 28d are arranged above the knee area 50d. The bearing positions 38d, 40d of the seat structural elements 26d, 28d are arranged at the armrest height X.

[0099] The pivotable backrest element 36d has a backrest frame 60d. The backrest frame 60d constitutes the bearing structure of the pivotable backrest element 36d. The pivotable backrest element 36d has a shell element 62d. The shell element 62d is formed by fiber reinforced plastic. The shell element 62d is firmly connected to the backrest frame 60d of the pivotable backrest element 36d. The shell element 62d of the pivotable backrest element 36d has a middle area 80d. The pivotable backrest element 36d has elastic ribs 84d, 86d extending laterally outward from the middle area 80d in the lower area. The elastic ribs 84d, 86d are preferably formed in one piece with the shell element 62d, especially with the middle area 80d.

[0100] 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 support surface in the lower region of the backrest 34d. The lower backrest element 52d is firmly fastened to the seat structure elements 26d, 28d. The lower backrest element 52d extends substantially between the height of the transverse carriers 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.

[0101] The aircraft seat arrangement has a reset module 56d. The reset module 56d is provided for resetting the backrest 34d from the comfort position to the upright seat position. The reset module 56d is provided for resetting the pivotable backrest element 34d. The reset module 56d is provided to provide a reset force to reset the backrest 34d, in particular to reset the pivotable backrest element 36d. The reset module 56d has a spring element 58d to provide the reset force. The spring element 58d is configured as a leaf spring element. In contrast to the previous embodiment, the spring element 58d configured as a leaf spring element is at least partially configured as a single piece with the lower backrest element 52d.

[0102] The spring element 58d configured as a leaf spring element is formed in one piece with the lower backrest element 52d configured as a shell element. The spring element 58d configured as a leaf spring element is formed by the middle area of ​​the lower backrest element 52d. The spring element 58d configured as a leaf spring element is partially integrated into the lower shell element. The spring element 58d configured as a leaf spring element is embedded in the fiber reinforcement layer of the lower backrest element 52d configured as a shell element. The spring element 58d configured as a leaf spring element is preferably formed as a leaf spring element embedded in the lower backrest element 52d by a manufacturing method. The spring element 58d configured as a leaf spring element extends from the lower backrest element 52d to the middle of the pivotable backrest element 36d.

[0103] In order to attach the spring element 58d configured as a leaf spring element to the pivotable backrest element 36d, the reset module 56d has a first fastening unit 64d. The pivotable backrest element 36d has a transverse carrier 66d. The transverse carrier 66d is arranged in the area above the bearing position 38d, 40d. The spring element 58d configured as a leaf spring element is directly attached to the transverse carrier 66d via the fastening unit 64d. The spring element 58d configured as a leaf spring element is connected to the transverse carrier 66d axially movably. The spring element 58d configured as a leaf spring element has two through-grooves configured as elongated holes, through which the spring element 58d is displaceably connected to the transverse carrier 66d via two fastening elements of the fastening unit 64d, such as screws. The first fastening unit 64d for attaching the spring element 58d configured as a leaf spring element can preferably be configured equivalently to the second fastening unit of the first embodiment for attaching the spring element configured as a leaf spring element to the lower backrest element.

[0104] The reset module 56d has a locking unit 88d. The locking unit 88d is arranged to lock or unlock the reset module 56d. The locking unit 88d is arranged to lock the backrest 34d, that is, the pivotable backrest element 36d, at least in the upright seat position and the comfort position. The locking unit 88d is preferably arranged between the pivotable backrest element 36d, in particular the backrest frame 60d and one of the seat structure elements 26d, 28d in terms of functional technology. The locking unit 88d is arranged above the knee area 50d of the backrest 34d. The locking unit 88d is preferably arranged in the area above the support position 38d, 40d of the seat structure elements 26d, 28d. The locking unit 88d is preferably basically, that is, mostly arranged above the armrest height X.

[0105] Figures 9 to 11A fifth embodiment of an aircraft seat device according to the invention is shown. The aircraft seat device is part of a partially shown aircraft seat 10e. The aircraft seat device has a mounting unit 12e. With the aid of the mounting unit 12e, the aircraft seat 10e can be erected on the cabin floor of the aircraft cabin. The mounting unit 12e has two transverse carriers 24e. The aircraft seat device has two seat structure elements 26e, 28e. The two seat structure elements 26e, 28e are each arranged on one side of a seat area 30e of the aircraft seat device. The two seat structure elements 26e, 28e are each arranged on the side of the seat area 30e formed by the aircraft seat 10e. The seat structure elements 26e, 28e are formed as seat partitions. The seat structure elements 26e, 28e are arranged on the transverse carrier 24e. The seat structure elements 26e, 28e are formed to be substantially L-shaped. Therefore, the seat structure elements 26e, 28e extend upwards away from the mounting unit 12e, in particular the mounting plane, in their rear region. The seat structural elements 26e, 28e extend in their rear region upwards substantially to the armrest height X. The seat structural elements 26e, 28e extend to the armrest height X of the aircraft seat 10e.

[0106] The aircraft seat arrangement comprises a backrest 34e. The backrest 34e is arranged pivotably relative to the mounting unit 12e. The backrest 34 is attached to the seat structure elements 26e, 28e. The backrest 34e is arranged to pivot between an upright seat position and a comfort position. The backrest 34e has a pivotable backrest element 36e. The pivotable backrest element 36e is rotatably supported on the mounting unit 12e. The seat structure elements 26e, 28e each have a support position 38e, 40e for supporting the pivotable backrest element 36e.

[0107] The aircraft seat device has a bearing device 42e. The bearing device 42e is arranged to pivotally support the backrest 34e between the upright seat position and the comfort position. The bearing device 42e is arranged to pivotally support the pivotable backrest element 36e between the upright seat position and the comfort position. The bearing device 42e forms an axis of rotation 44e. The bearing device 42e has two bearing bolts 46e, 48e. The bearing bolts 46e, 48e form the axis of rotation 44e. The bearing bolts 46e, 48e are each connected to one of the bearing positions 38e, 40e of one of the seat structure elements 26e, 28e. The backrest 34e is designed as a backrest with a high backrest rotation point. The backrest rotation point, i.e. the axis of rotation 44e of the bearing device 42e, is arranged above the knee area 50e of the aircraft seat 10e. In order to form a high backrest rotation point, the seat structural elements 26e, 28e form their support positions 38e, 40e for supporting the backrest 34e in the high area. The support positions 38e, 40e of the seat structural elements 26e, 28e are arranged above the knee area 50e. The support positions 38e, 40e of the seat structural elements 26e, 28e are arranged at the armrest height X.

[0108] The pivotable backrest element 36e has a backrest frame 60e. The backrest frame 60e constitutes the bearing structure of the pivotable backrest element 36e. The pivotable backrest element 36e can preferably be constructed similarly to the pivotable backrest elements of the first two embodiments and have a shell element or a covering. The backrest 34e also has a lower backrest element, not shown in detail here, which constitutes the lower area of ​​the backrest 34e.

[0109] The aircraft seat arrangement has a reset module 56e. The reset module 56e is provided for resetting the backrest 34e from the comfort position to the upright seat position. The reset module 56e is provided for resetting the pivotable backrest element 34e. The reset module 56e is provided to provide a reset force to reset the backrest 34e, in particular to reset the pivotable backrest element 36e. The reset module 56e has a spring element 58e to provide the reset force. Different from the previous embodiment, the spring element 58e is configured as a gas spring. The spring element 58e configured as a gas spring is configured to provide the reset force of the reset module 56e. The spring element 58e configured as a gas spring is arranged above the bearing position 38e, 40e of the seat structure element 26e, 28e.

[0110] The reset module 56e has a lever transmission 110e. The lever transmission 110e is arranged to convert the spring force of the spring element 58e configured as a gas pressure spring into a pivoting movement of the pivotable backrest element 36e. The lever transmission 110e has a basic retaining element 112e. The basic retaining element 112e is rigid and connected to the mounting unit 12e in a rotationally fixed manner. The basic retaining element 112e is preferably connected to the seat structure element 26e in a rotationally fixed manner. The basic retaining element 112e is attached to the seat structure element 26e in a rotationally fixed manner, in particular, by a supporting bolt 46e of a supporting device 42e. The basic retaining element 112e has a first fastening receiving portion 114e. The spring element 58e configured as a gas pressure spring is attached to the first fastening receiving portion 114e in a pivotally supported manner with a first end. The basic retaining element 112e has a second fastening receiving portion 116e. The lever transmission 110e has a lever element 118e. The lever element 118e is pivotally attached to the base holding element 112e via the second fastening receptacle 116e. The lever element 118e of the lever transmission 110e is pivotally connected with its first end via the second fastening receptacle 116e to the base holding element 112e. The lever element 118e extends upwardly away from the mounting plane in the upright seat position of the backrest 34e in the installed state (see FIG. Fig. 9 and Fig.10 The spring element 58e, which is designed as a gas pressure spring, is rotatably connected with its second end via a bearing point 120e to a second end of the lever element 118e.

[0111] The lever transmission 110e has a coupling element 122e, which connects the lever transmission 110e to the pivotable backrest element 36e. The coupling element 122e is attached to the bearing position 120e with its first end. The coupling element 122e is rotatably connected with the second end of the spring element 58e, which is configured as a gas pressure spring, and the second end of the lever element 118e. The coupling element 122e is rotatably connected with the pivotable backrest element 36e with its second end. The coupling element 122e is rotatably connected with the backrest frame 60e of the pivotable backrest element 36e with its second end, preferably via a bearing position not shown in detail.

[0112] The reset module 56e has a locking unit 88e. The locking unit 88e is arranged to lock or unlock the reset module 56e. The locking unit 88e is arranged to lock the backrest 34e, i.e. the pivotable backrest element 36e, at least in the upright seat position and the comfort position. The locking unit 88e is arranged to directly lock the spring element 58e configured as a gas spring. In the locked state of the locking unit 88e, the spring element 58e configured as a gas spring is locked and cannot provide a spring force. In the unlocked state of the locking unit 88e, the spring element 58e configured as a gas spring is unlocked and can provide its spring force as a reset force. The locking unit 88e is arranged in the spring element 58e configured as a gas spring. The locking unit 88e is internally formed in the spring element 58e configured as a gas spring. The locking unit 88e is formed in one piece with the spring element 58e configured as a gas spring.

[0113] If the pivotable backrest element 36e is pivoted backwards in its comfort position, the spring element 58e designed as a gas spring is compressed. The lever element 118e and the spring element 58e designed as a gas spring are also pivoted backwards in the comfort position of the pivotable backrest element 36e via the fastening receptacles 114e, 116e of the base holding element 112e. If the spring element 58e designed as a gas spring is now actuated, i.e. unlocked, the spring element 55e designed as a gas spring presses the lever element 118e and thus the pivotable backrest element 36e connected to the lever transmission 110e via the coupling element 122e upwards and thus into its upright seat position.

[0114] The entire lever transmission 110e, the spring element 58e configured as a gas spring, and the locking unit 88e integrally formed with the spring element 58e are arranged above the armrest height X. The entire reset module 56e is arranged above the bearing positions 38e, 40e of the seat structure elements 26e, 28e for the pivotable backrest element 36e. The reset module 56e is arranged completely above the knee area 50e of the backrest 34e. The entire reset module 56e is arranged on one side of the pivotable backrest element 36e. The reset module 56e is arranged only on the side facing the left seat structure element 26e. The reset module 56e can thus be arranged particularly space-saving.

[0115] Figure 12 to Figure 14The sixth embodiment of an aircraft seat device according to the invention is shown. The aircraft seat device is part of a partially shown aircraft seat 10f. The aircraft seat device has a mounting unit 12f. With the aid of the mounting unit 12f, the aircraft seat 10f can be erected on the cabin floor of the aircraft cabin. The mounting unit 12f has two transverse carriers 22f, 24f. The aircraft seat device has two seat structure elements 26f, 28f. The two seat structure elements 26f, 28f are each arranged on one side of a seat area 30f of the aircraft seat device. The two seat structure elements 26f, 28f are each arranged on the side of the seat area 30f formed by the aircraft seat 10f. The seat structure elements 26f, 28f are configured as seat partitions. The seat structure elements 26f, 28f are arranged on the transverse carrier 24f. The seat structure elements 26f, 28f are configured to be substantially L-shaped. Therefore, the seat structure elements 26f, 28f extend upwards away from the mounting unit 12f, in particular the mounting plane, in their rear region. The seat structural elements 26f, 28f extend in their rear region upwards substantially to armrest height X. The seat structural elements 26f, 28f extend to armrest height X of the aircraft seat 10f.

[0116] The aircraft seat device comprises a backrest 34f. The backrest 34f is arranged pivotably relative to the mounting unit 12f. The backrest 34f is attached to the seat structure elements 26f, 28f. The backrest 34f is arranged to pivot between the upright seat position and the comfort position. The backrest 34f has a pivotable backrest element 36f. The pivotable backrest element 36f is pivotably supported on the mounting unit 12f. The seat structure elements 26f, 28f each have a supporting position 38f, 40f for supporting the pivotable backrest element 36f. The aircraft seat device has a supporting device 42f. The supporting device 42f is arranged to pivotally support the backrest 34f between the upright seat position and the comfort position. The supporting device 42f is arranged to pivotally support the pivotable backrest element 36f between the upright seat position and the comfort position. The supporting device 42f constitutes the rotation axis 44f. The bearing device 42f has two bearing bolts 46f, 48f. The bearing bolts 46f, 48f form the rotation axis 44f. The bearing bolts 46f, 48f are each connected to one of the bearing positions 38f, 40f of one of the seat structural elements 26f, 28f. The backrest 34f is configured as a backrest with a high backrest rotation point. The backrest rotation point, i.e. the rotation axis 44f of the bearing device 42f, is arranged above the knee area 50f of the aircraft seat 10f. In order to form the high backrest rotation point, the seat structural elements 26f, 28f form their bearing positions 38f, 40f for supporting the backrest 34f in the high area. The bearing positions 38f, 40f of the seat structural elements 26f, 28f are arranged above the knee area 50f. The bearing positions 38f, 40f of the seat structural elements 26f, 28f are arranged at the armrest height X.

[0117] The pivotable backrest element 36f has a backrest frame 60f. The backrest frame 60f constitutes the bearing structure of the pivotable backrest element 36f. The pivotable backrest element 36f can preferably be constructed similarly to the pivotable backrest elements of the first two embodiments and have a shell element or a covering. The backrest 34f also has a lower backrest element, not shown in detail here, which constitutes the lower area of ​​the backrest 34f.

[0118] The aircraft seat arrangement has a resetting module 56f. The resetting module 56f is provided for resetting the backrest 34f from the comfort position to the upright seat position. The resetting module 56f is provided for resetting the pivotable backrest element 34f. The resetting module 56f is provided to provide a resetting force for resetting the backrest 34f, in particular for resetting the pivotable backrest element 36f. The resetting module 56f has a spring element 58f for providing the resetting force. The spring element 58f is provided with a spring element 58f. Figures 9 to 11 The spring element 58f configured as a gas pressure spring is also configured as a gas pressure spring in the fifth embodiment of the present invention. The spring element 58f configured as a gas pressure spring is arranged to provide the restoring force of the restoring module 56f. The spring element 58f configured as a gas pressure spring is arranged above the bearing position 38f, 40f of the seat structure element 26f, 28f.

[0119] The reset module 56f has a lever transmission 110f. The lever transmission 110f is arranged to convert the spring force of the spring element 58f, which is configured as a gas pressure spring, into a pivoting movement of the pivotable backrest element 36f. Unlike the fifth embodiment, the lever transmission 110f is arranged on both sides of the backrest frame 60f. The lever transmission 110f is arranged on the two lateral frame elements of the backrest frame 60f. Here, the lever transmission 110f is arranged on the inner side of the two lateral frame elements of the backrest frame 60f. The lever transmission 110f has two eccentric elements 124f, 126f. The eccentric elements 124f, 126f are each pivotally attached to the inner side of the lateral frame element of the backrest frame 60f. The eccentric elements 124f, 126f are coaxially arranged with each other. The eccentric elements 124f, 126f each have a first attachment point 128f, 130f.

[0120] The lever transmission 110f has a torsion tube 132f. The torsion tube 132f connects the two eccentric elements 124f, 126f to each other. The torsion tubes 132f are both attached to the first attachment points 128f, 130f of the eccentric elements 124f, 126f in a rotationally fixed manner. The torsion tube 132f connects the eccentric elements 124f, 126f at their first attachment points 128f, 130f. The first eccentric element 124f is arranged on the left side of the pivotable backrest element 36f facing the left seat structure element 26f. The first eccentric element 124f has a second attachment point 134f, through which the spring element 58f, which is configured as a gas pressure spring, is attached to the first eccentric element 124. The spring element 58f, which is configured as a gas pressure spring, is attached to the second attachment point 134f of the first eccentric element 124f with its second end. The spring element 58f configured as a gas pressure spring is rotatably attached to the mounting unit 12f with a first end. Preferably, the spring element 58f configured as a gas pressure spring is rotatably attached to the support bolt 46f of the support device 42f with its first end. The second eccentric element 126f is arranged on the right side of the pivotable backrest element 36f facing the right seat structure element 28f. The second eccentric element 126f also has a second attachment point 136f. The lever transmission 110f has a lever element 138f, which is pivotably attached to the second attachment point 136f of the second eccentric element 126f. The lever element 138f is pivotably attached to the attachment point 136f of the second eccentric element 126f with its second end. The lever element 138f is rotatably attached to the mounting unit 12f with its first end. Preferably, the lever element 138f is rotatably attached to the support bolt 48f of the support device 42f with its first end.

[0121] By extending or shortening the spring element 58f, which is designed as a gas spring, the eccentric elements 124f, 126f are rotated. If the pivotable backrest element 36f is pivoted backward in its comfort position, the spring element 58f, which is designed as a gas spring, is compressed. As a result, the eccentric elements 124f, 126f are pivoted. If the spring element 58f, which is now designed as a gas spring, is actuated, i.e. unlocked, the spring element 58f, which is designed as a gas spring, presses the first eccentric element 124f via the second attachment point 134f and rotates the first eccentric element 124f and thus the pivotable backrest element 36f into its upright seat position. The restoring force of the spring element 58f, which is designed as a gas spring, is transmitted to the opposite side of the backrest frame 60f via the torsion tube 132f. As a result, the pivotable backrest element 36f is pressed evenly into the upright seat position on both sides.

[0122] The entire lever mechanism 110f, the spring element 58f designed as a gas pressure spring, and the locking unit 88f designed integrally with the spring element 58f are arranged above the armrest height X. The entire restoring module 56f is arranged above the bearing points 38f, 40f of the seat structure elements 26f, 28f for the pivotable backrest element 36f. The restoring module 56f is arranged completely above the knee region 50f of the backrest 34f.

[0123] Fig.15 A seventh embodiment of an aircraft seat device according to the invention is shown. The aircraft seat device is part of a partially shown aircraft seat 10g. The aircraft seat device has a mounting unit 12g. With the aid of the mounting unit 12g, the aircraft seat 10g can be erected on the cabin floor of the aircraft cabin. The mounting unit 12g has two transverse carriers 24g. The aircraft seat device has two seat structure elements 26g, 28g. The two seat structure elements 26g, 28g are each arranged on one side of a seat area 30g of the aircraft seat device. The two seat structure elements 26g, 28g are each arranged on the side of the seat area 30g formed by the aircraft seat 10g. The seat structure elements 26g, 28g are configured as seat partitions. The seat structure elements 26g, 28g are configured to be substantially L-shaped. The seat structure elements 26g, 28g each have a first sub-area, which is oriented substantially horizontally in the installed state. The seat structure elements 26g, 28g each have a second sub-area, which is oriented substantially vertically in the installed state. The second sub-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 transverse carrier 24g. Therefore, the seat structural elements 26g, 28g extend upwards away from the mounting unit 12g, in particular the mounting plane, in their rear region. The seat structural elements 26g, 28g extend upwards in their rear region substantially to the height X of the armrest. The seat structural elements 26g, 28g extend to the height X of the armrest of the aircraft seat 10g.

[0124] The aircraft seat arrangement comprises a backrest 34g. The backrest 34g is arranged pivotably relative to the mounting unit 12g. The backrest 34g is attached to the seat structure elements 26g, 28g. The backrest 34g is arranged to pivot between the upright seat position and the comfort position. The backrest 34g has a pivotable backrest element 36g. Different from the previous embodiment, the backrest 34g is configured as a backrest with a lower backrest rotation point. The backrest 34g preferably does not have a lower backrest element rigidly connected to the seat structure elements 26g, 28g. The pivotable backrest element 36g extends into the area of ​​the seat bottom of the aircraft seat 10g. The pivotable backrest element 36g extends into the area below the seat surface formed by the seat bottom. The pivotable backrest element 36g is pivotally supported in the area below the armrest height X.

[0125] The pivotable backrest element 36g is pivotally attached to the seat structure element 26g, 28g. The seat structure element 26g, 28g each has a supporting position 38g, 40g for supporting the pivotable backrest element 34g. In order to constitute the lower backrest rotation point, the seat structure element 26g, 28g constitutes its supporting position for supporting the pivotable backrest element 36g in the lower area. The supporting position 38g, 40g of the seat structure element 26g, 28g is preferably arranged in the lower third of the seat structure element 26g, 28g, especially in the lower third of the second sub-area of ​​the seat structure element 26g, 28g. The supporting position 38g, 40g of the seat structure element 26g, 28g is arranged in the knee area 50g of the backrest 34g. The supporting position 38g, 40g of the seat structure element 26g, 28g is arranged below the armrest height X.

[0126] The aircraft seat arrangement has a bearing device 42g. The bearing device 42g is arranged to pivotally support the pivotable backrest 34g between an upright seat position and a comfort position. The bearing device 42g forms 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 has two bearing bolts 46g, 48g. The bearing bolts 46g, 48g form the rotation axis 44g. The bearing bolts 46g, 48g are each connected to one of the bearing positions 38g, 40g of one of the seat structure elements 26g, 28g.

[0127] The pivotable backrest element 36g has a backrest frame 60g. The backrest frame 60g extends into the area below the bearing position 38g, 40g of the seat structure element 26g, 28g. The pivotable backrest element 36g has a shell element 62g, which is firmly connected to the backrest frame 60g of the pivotable backrest element 36g. The shell element 62g of the pivotable backrest element 36g has a middle area 80g and elastic ribs 84g, 86g extending laterally outward from the middle area 80g in the lower area.

[0128] The aircraft seat device has a reset module 56g. The reset module 56g is provided for resetting the backrest 34g from the comfort position to the upright seat position. The reset module 56g is provided for resetting the pivotable backrest element 36g. The reset module 56g has a spring element 58g to provide a reset force. The spring element 58g is configured as a leaf spring element. The spring element 58g configured as a leaf spring element is functionally arranged between the pivotable backrest element 36g and the mounting unit 12g. Different from other embodiments, the spring element 58g configured as a leaf spring element is directly attached to the mounting unit 12g, in particular to the rear transverse carrier 24g, with its first lower end. The spring element 58g configured as a leaf spring element is supported on the rear transverse carrier 24g of the mounting unit with its lower end. In order to attach the spring element 58g configured as a leaf spring element to the rear transverse carrier 24g, the reset module 56g has a fastening unit 68g. The spring element 58g designed as a leaf spring element is firmly attached to the mounting unit 12g by means of the fastening unit 68g. The fastening unit 68g preferably has a clamping element which surrounds the rear transverse carrier 24g and is thus firmly attached to the transverse carrier 24g. The spring element 58g designed as a leaf spring element is preferably attached to the rear transverse carrier 24g movably in at least one vertical direction by means of the fastening unit 68g. The spring element 58g designed as a leaf spring element is attached with a second upper end to the pivotable backrest element 36g. In order to attach the spring element 58g designed as a leaf spring element to the pivotable backrest element 36g, the reset module 56g has a fastening unit 64g.

[0129] The reset module 56g has a locking unit 88g. The locking unit 88g is provided to lock or unlock the reset module 56g. The locking unit 88g is preferably arranged in the region above the bearing position 38g, 40g of the seat structure element 26g, 28g. The entire reset module 56g, except for the subregion of the spring element 58g designed as a leaf spring extending to the transverse carrier 24g of the mounting unit 12g, is arranged above the bearing position 38g, 40g of the seat structure element 26g, 28g, i.e. above the rotation axis 44g of the pivotable backrest element 36g.

[0130] Fig.16An eighth embodiment of an aircraft seat device according to the invention is shown. The aircraft seat device is part of a partially shown aircraft seat 10h. The aircraft seat device has a mounting unit 12h. With the aid of the mounting unit 12h, the aircraft seat 10h can be erected on the cabin floor of the aircraft cabin. The mounting unit 12h has two transverse carriers 24h. The aircraft seat device has two seat structure elements 26h, 28h. The two seat structure elements 26h, 28h are each arranged on one side of a seat area 30h of the aircraft seat device. The two seat structure elements 26h, 28h are each arranged on the side of the seat area 30h formed by the aircraft seat 10h. A pivotable backrest element 36h is pivotably attached to the seat structure elements 26h, 28h. The seat structure elements 26h, 28h each have a support position 38h, 40h for supporting the pivotable backrest element 34h.

[0131] The aircraft seat arrangement comprises a seat bottom 32h. The seat bottom 32h has a load-bearing body. The seat bottom 32h also has a cushioning element, which is attached to the body. The seat bottom 32h is attached to a mounting unit 12h. The aircraft seat arrangement comprises a backrest 34h. The backrest 34h is arranged pivotably relative to the mounting unit 12h. The backrest 34h is attached to the seat structure elements 26h, 28h. The backrest 34h is configured as a backrest with a high backrest rotation point. The backrest 34h has a lower backrest element 52h. The lower backrest element 52h constitutes a lower region of the backrest 34h. The lower backrest element 52h constitutes a backrest support surface in the lower region of the backrest 34h. The lower backrest element 52h is rigidly connected to the mounting unit 12h. The backrest 34h is arranged to pivot between an upright seat 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 constructed essentially identically to the pivotable backrest element in the first embodiment and is therefore not described in detail here.

[0132] Unlike the aforementioned embodiment, the seat structure elements 26h, 28h are not configured as seat partitions. The aircraft seat device has a seat shell element 140h. The seat shell element 140h forms the body of the lower backrest element 52h and the seat bottom 32h in one piece. The seat shell element 140h forms the body of the seat bottom 32h in the lower front area. In the rear area, the seat shell element 140h forms the lower backrest element 52h. The seat shell element 140h is formed by fiber reinforced plastic. The seat shell element 140h is preferably formed by CFK or GFK. In principle, it is also conceivable that the seat shell element 140h is formed by other suitable fiber reinforced plastics. The seat shell element 140h is configured as a substantially L-shaped in a side view. Unlike the aforementioned embodiment, the seat structure elements 26h, 28h are formed in one piece with the seat shell element 140h. The seat structure elements 26h, 28h are at least partially formed by the body of the lower backrest element 52h and the seat bottom 32h. The seat shell element 140h has side regions 142h, 144h. The side regions 142h, 144h each constitute the lateral end of the seat shell element 140h when viewed in the transverse direction. The seat structure 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 constitute one of the seat structure elements 26h, 28h. Preferably, the seat shell element 140h has at least one reinforcement element in its side regions 142h, 144h to constitute the seat structure elements 26h, 28h. The reinforcement elements can be, for example, formed as inserts, which are inserted into the side regions 142h, 144h of the seat shell element 140h. The reinforcement elements formed as inserts can be, for example, made of metal such as aluminum or magnesium. In principle, it is also conceivable that the reinforcement elements of the local reinforcement are formed of CFK or GFK.

[0133] The seat shell element 140h extends in its side regions 142h, 144h until it passes through the upper edge of the lower backrest element 52h formed thereby, in which side regions 142h, 144h the seat structural elements 26h, 28h are formed. The seat shell element 140h extends in its side regions 142h, 144h until it passes through the armrest height X, in which side regions 142h, 144h the seat structural elements 26h, 28h are formed. The seat shell element 140h forms a bearing point 38h, 40h for the seat structural elements 26h, 28h in each of its side regions 142h, 144h in the upper end region. The seat shell element 140h forms a bearing point 38h, 40h for the seat structural elements 26h, 28h in each of its side regions 142h, 144h in the upper end region, by which the pivotable backrest element 36h is pivotably supported. The pivotable backrest element 36h is directly pivotably connected to the seat shell element 140h via bearing points 38h, 40h.

[0134] The aircraft seat arrangement has a supporting device 42h. The supporting device 42h is arranged to pivotally support the pivotable backrest element 36h between the upright seat position and the comfort position. The supporting device 42h forms a rotation axis 44h. The supporting device 42h has two supporting bolts 46h, 48h. The supporting bolts 46h, 48h are each connected to one of the supporting positions 38h, 40h of the seat structure element 26h, 28h formed by the seat shell element 140h. The supporting bolts 46h, 48h are firmly connected to the seat shell element 140h. The pivotable backrest element 36h is directly pivotably attached to the seat shell element 140h via the supporting bolts 46h, 48h.

[0135] The seat shell element 140h is designed to be wider than the pivotable backrest element 36h. The seat shell element 140h surrounds the pivotable backrest element 36h, in particular its backrest frame 60h, at its lower end with the upper end of the side regions 142h, 144h in which the bearing positions 38h, 40h are arranged. The bearing bolts 46h, 48h extend from the side regions 142h, 144h of the seat shell element 140h inwards in the direction of the backrest frame 60h of the pivotable backrest element 36h. The pivotable backrest element 36h is pivotably mounted on the bearing bolts 46h, 48h.

[0136] The aircraft seat arrangement has a reset module 56h. The reset module 56h is arranged to reset the backrest 34h from the comfort position to the upright seat position. The reset module 56h is arranged to reset the pivotable backrest element 36h. The reset module 56h is arranged to provide a reset force to reset the backrest 34h, in particular to reset the pivotable backrest element 36h. The reset module 56h has a spring element 58h to provide the reset force. The spring element 58h is configured as a leaf spring element. The reset module 56h can preferably be configured as in one of the aforementioned embodiments. For example, the reset module 56h is configured substantially identically to the reset module in the first embodiment.

[0137] The spring element 58h configured as a leaf spring element is functionally arranged between the seat shell element 140h and the pivotable backrest element 36h. The spring element 58h configured as a leaf spring element is attached to the seat shell element 140h, in particular to the lower backrest element 52h formed by the seat shell element 140h, with its first lower end. In order to attach the spring element 58h configured as a leaf spring element to the seat shell element 140h, the reset module 56h has a fastening unit 68h. The spring element 58h configured as a leaf spring element is movably attached to the seat shell element 140h via the fastening unit 68h. In order to attach the spring element 58h configured as a leaf spring element to the pivotable backrest element 36h, the reset module 56h has a fastening unit 64h. The pivotable backrest element 36h has a transverse carrier 66h. The spring element 58h configured as a leaf spring element is directly attached to the transverse carrier 66h via the fastening unit 64h.

[0138] The reset module 56h has a locking unit 88h. The locking unit 88h is configured to lock or unlock the reset module 56h. The locking unit 88h is preferably arranged between the pivotable backrest element 36h, in particular the backrest frame 60h and the seat shell element 140h in terms of functional technology. The locking unit 88h is arranged above the knee area 50h of the backrest 34h. The locking unit 88h is preferably arranged in the area above the bearing position 38h, 40h of the seat structure element 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.

[0139] Figures 17 to 20A ninth embodiment of an aircraft seat arrangement according to the invention is shown. Here, the aircraft seat arrangement is part of an aircraft seat 10i. The aircraft seat 10i stands upright in the aircraft cabin of an aircraft in the installed state. The aircraft seat arrangement has a mounting unit 12i. With the aid of the mounting unit 12i, the aircraft seat 10i can stand upright on the cabin floor of the aircraft cabin. The aircraft seat 10i is preferably designed as part of an aircraft seat row 14i, which includes more than one aircraft seat 10i. In these figures, an aircraft seat row 14i with three aircraft seats 10i, 16i, 146i is shown by way of example. The aircraft seat row 14i shown by way of example has a second aircraft seat 16i and a third aircraft seat 146i. The second aircraft seat 16i is designed as a middle seat of the aircraft seat row 14i and is arranged between two other aircraft seats 16i, 146i. The other aircraft seats 16i, 146i of the aircraft seat row 14i are preferably designed substantially identically to the first aircraft seat 10i, so that only one aircraft seat 10i is described in detail below.

[0140] The mounting unit 12i has two transverse supports 22i, 24i. The transverse supports 22i, 24i are designed as support tubes. The transverse supports 22i, 24i extend at least substantially through the entire transverse extension of all aircraft seats 10i of the aircraft seat row 14i. The aircraft seat arrangement has two seat structure elements 26i, 28i. The two seat structure elements 26i, 28i are each arranged on one side of a seat area 30i of the aircraft seat arrangement. The two seat structure elements 26i, 28i are each arranged on the side of the seat area 30i formed by the aircraft seat 10i. The seat structure elements 26i, 28i are designed as seat separators. The seat structure elements 26i, 28i designed as seat separators are provided to fasten different components of the corresponding aircraft seat 10i, 16i, 146i to the aircraft seat 10i, 16i, 146i. Therefore, the seat structure elements 26i, 28i extend upwards away from the mounting unit 12i, in particular the mounting plane, in their rear region. The seat structural elements 26i, 28i extend in their rear region upwards substantially to the armrest height X. The seat structural elements 26i, 28i extend to the armrest height X of the aircraft seat 10i.

[0141] The aircraft seat arrangement comprises a backrest 34i. The backrest 34i is arranged so that a person sitting on the aircraft seat 10i can support his back on the backrest 34i, and the aircraft seat arrangement is part of the aircraft seat 10i. The backrest 34i is arranged pivotably relative to the mounting unit 12i. The backrest 34i is attached to the seat structure elements 26i, 28i. The backrest 34i is arranged to pivot between an upright seat position and a comfort position. The backrest 34i has a pivotable backrest element 36i. The pivotable backrest element 36i is pivotably supported on the mounting unit 12i. The pivotable backrest element 36i is pivotably attached to the seat structure elements 26i, 28i. The seat structure elements 26i, 28i each have a support position 38i, 40i for supporting the backrest 34i. The support positions 38i, 40i are arranged to support the pivotable backrest element 36i thereon.

[0142] The aircraft seat arrangement has a bearing device 42i. The bearing device 42i is arranged to pivotally support the backrest 34i between an upright seat position and a comfort position. The bearing device 42i is arranged to pivotally support the pivotable backrest element 36i between an upright seat position and a comfort position. The bearing device 42i forms an axis of rotation 44i. The pivotable backrest element 36i can be pivoted about the axis of rotation 44i by means of the bearing device 42i. The bearing device 42i has two bearing bolts 46i, 48i. The bearing bolts 46i, 48i form the axis of rotation 44i. The bearing bolts 46i, 48i are each connected to one of the bearing positions 38i, 40i of one of the seat structure elements 26i, 28i.

[0143] The pivotable backrest element 36i has a backrest frame 60i. The backrest frame 60i constitutes the load-bearing structure of the pivotable backrest element 36i. The backrest frame 60i is designed as a revolving frame. The backrest frame 60i has two lateral frame elements and an upper frame element, which connects the two lateral frame elements to the upper end of the backrest frame 60i. The lower end of the backrest frame 60i constitutes the lower end of the pivotable backrest element 36i. The supporting bolts 46i, 48i are each attached to the backrest frame 60i of the pivotable backrest element 36i on the facing lateral frame elements at the lower end of the backrest frame 60i. The backrest 34i is designed as a backrest with a high backrest rotation point. The backrest rotation point, i.e. the rotation axis 44i of the bearing device 42i, is arranged above the knee area 50i of the aircraft seat 10i. In order to form a high backrest rotation point, the seat structural elements 26i, 28i form their bearing positions 38i, 40i for supporting the backrest 34i in the high area. The bearing positions 38i, 40i of the seat structural elements 26i, 28i are arranged above the knee area 50i. The bearing positions 38i, 40i of the seat structural elements 26i, 28i are arranged at the armrest height X.

[0144] The pivotable backrest element 36i has a shell element 62i. The shell element 62i is configured as a plate-shaped element. The shell element 62i is formed of fiber reinforced plastic. The shell element 62i is formed, for example, of GFK or CFK. The shell element 62i is configured to constitute a backrest support 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 tensioned by the backrest frame 60i. The shell element 62i is firmly connected to the backrest frame 60i of the pivotable backrest element 36i. The shell element 62i is configured to have a cushioning element of the backrest 34i placed thereon.

[0145] The pivotable backrest element 36i has elastic ribs 84i, 86i extending laterally outward from the middle area 80i in the lower area. In the embodiment, three elastic ribs 84i, 86i are shown as examples on each side. The elastic ribs 84i, 86i can be elastically deformed independently of each other. The elastic ribs 84i, 86i are preferably formed in one piece with the shell element 62i, especially with the middle area 80i. The shell element 62i constitutes the elastic ribs 84i, 86i in its lower area. The lower area is preferably formed by the lower third of the shell element 62i. The shell element 62i has a plurality of narrow grooves 148i, 150i in its lower area to constitute the ribs 84i, 86i. The narrow grooves 148i, 150i extend from the lateral outer edge of the shell element 62i to the front of the middle area 80i. The narrow grooves 148i, 150i separate the elastic ribs 84i, 86i stacked on each other.

[0146] The backrest 34i has a lower backrest element 52i. The lower backrest element 52i is rigidly constructed. The lower backrest element 52i is preferably immovably constructed. The lower backrest element 52i constitutes the lower region of the backrest 34i. The lower backrest element 52i constitutes a backrest support surface in the lower region of the backrest 34i. The lower backrest element 52i is firmly fastened to the seat structure elements 26i, 28i. The lower backrest element 52i extends substantially between the height of the transverse carriers 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 composed of a GFK shell or a CFK shell. In principle, it is also conceivable that the lower backrest element 52i is composed of another material, such as a sheet, a film or a multilayer structure with a honeycomb structure. The lower backrest element 52i has an upper region 152i. The upper region 152i constitutes approximately the upper quarter of the lower backrest element 52i. The uppermost 5-10 cm of the lower backrest element 52i constitute the upper region 152i. The backrest element 52i has a lip 104i at its upper end. The lip 104i constitutes 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 constitutes the upper end of the upper region 152i of the lower backrest element 52i. The lip 104i is formed in one piece with the rest of the lower backrest element 52i. The lip 104i is arranged centrally on the upper end of the lower backrest element 52i in the transverse direction.

[0147] The lower backrest element 52i is flexibly formed in its upper region 152i. The lower backrest element 52i is more flexibly formed in its upper region 152i than in its main region 102i arranged below it. The lower backrest element 52i is elastically deflectable in its upper region 152i. In order to form flexibility in the upper region 152i, the lower backrest unit 52i has a recess pattern 154i in the upper region 152i. The recess pattern 154i is formed by at least one recess 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. The recess pattern 154i is formed in the present embodiment by a plurality of recesses 156i arranged at a distance from each other and configured as narrow grooves. The recess 156i configured as a slot extends from the upper edge of the lower backrest element 52i below the lip 104i. In principle, it is also conceivable that the recess 156i extends only to the lower edge of the lip 104i. The recess 156i configured as a slot has a width of 10 mm. In principle, it is also conceivable that the recess 156i configured as a slot has a width in the range of 5 mm to 30 mm. In the embodiment, four recesses 156i configured as slots are shown by way of example. In principle, it is also conceivable that the recess pattern 154i has a different number of recesses 156i configured as slots. In principle, it is also conceivable that the recess 156i configured as a slot is configured narrower.

[0148] In principle, it is also conceivable that the lower backrest element 52i is formed from a combination of different materials. For example, it is conceivable that the upper region 152i or the lip 104i of the lower backrest element 52i is formed from a different material than the main region 102i. For example, it is conceivable that the main region 102i is formed from a flexurally rigid fiber composite material or sheet material and the upper region is formed from a flexible plastic or fiber composite material that is firmly attached to the main region 102i. If the lower backrest unit 52i is formed from a fiber composite material, the upper flexible region 152i is preferably composed of a smaller number of fiber composite layers than the main region 102i. As a result, the upper region 152i can be particularly easily configured to be more flexible than the main region 102i, and the lower backrest element 52i can advantageously be configured in one piece.

[0149] The aircraft seat arrangement has a reset module 56i. The reset module 56i is arranged to reset the backrest 34i from the comfort position to the upright seat position. The reset module 56i is arranged to reset the backrest 34i from its pivoted seat position to the upright seat position. The reset module 56i is arranged to reset the pivotable backrest element 36i. The reset module 56i is arranged to provide a reset force to reset the backrest 34i, in particular to reset the pivotable backrest element 36i. The reset module 56i is at least substantially arranged in the area above the bearing positions 38i, 40i of the seat structure elements 26i, 28i. The reset module 56i is at least substantially arranged above the armrest height X, i.e. on the side facing away from the mounting plane. The reset module 56i is at least mostly arranged above the knee area 50i of the backrest 34i.

[0150] The reset module 56i has a locking unit 88i. The locking unit 88i is arranged to lock or unlock the reset module 56i. The locking unit 88i is arranged to lock the backrest 34i, i.e. the pivotable backrest element 36i, at least in the upright seat position and the comfort position. The locking unit 88i is arranged to lock the backrest 34i in its upright seat position. The locking unit 88i is arranged to lock the pivotable backrest element 36i in the upright seat position. The locking unit 88i can lock the pivotable backrest element 36i in the comfort position and the upright seat 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 the current position, i.e. the upright seat position or the comfort position. In the locked position of the locking unit 88i, the pivotable backrest element 36i is fixed in a position, i.e. the upright seat position or the comfort position, in a form-fitting manner. In the locked position of the locking unit 88i, the pivotable backrest element 36i is fixed in position relative to the mounting unit 12i. Preferably, the locking unit 88i is only provided for locking the backrest 34i, i.e. the pivotable backrest element 36i, in the upright seat position and the comfort position. The locking unit 88i is preferably arranged mostly above the bearing positions 38i, 40i. The locking unit 88i is arranged between the seat structure elements 26i, 28i and the pivotable backrest element 36i.

[0151] The locking unit 88i has a first locking module 172i. The first locking module 172i of the locking unit 88i is arranged on the left side of the pivotable backrest element 36i. The first locking module 172i is arranged between the first left seat structure element 26i and the backrest frame 60i. The first locking module 172i is functionally arranged between the left bearing bolt 46i and the left side frame element of the backrest frame 38i. The locking unit 88i has a second locking module 174i. The second locking module 174i of the locking unit 88i is arranged on the right side of the pivotable backrest element 36i. The second locking module 174i is arranged between the second right seat structure element 28i and the backrest frame 38i. The second locking module 174i is functionally arranged between the right bearing bolt 48i and the right side frame element of the backrest frame 38i. The two locking modules 172i, 174i are provided together for locking the backrest 34i, in particular the pivotable backrest element 36i. The two locking modules 172i, 174i of the locking device 70i are constructed substantially identically. The locking modules 172i, 174i are constructed substantially in a mirror image of each other. Preferably, in the locking modules 172i, 174i, only the actuation attachments or elements for transmitting the actuation force are different. The locking modules 172i, 174i have substantially identical structures that are mirror images of each other.

[0152] The locking module 172i has a first locking unit 176i. The first locking unit 176i is arranged to be fastened to the pivotable backrest element 36i. The first locking unit 176i constitutes the part of the locking module 172i facing the pivotable backrest element 36i. The locking module 172i has a second locking unit 178i. The second locking unit 178i is arranged to be mounted on the support bolt 46i in a loss-proof manner. The second locking unit 178i constitutes the part of the locking module 172i facing the mounting unit 12i. The first locking unit 176i and the second locking unit 178i of the locking module 172i are movably supported to each other. The first locking unit 176i and the second locking unit 178i are movably supported to each other around the rotation axis 44i by attaching to the pivotable backrest element 36i or the support bolt 46i through the support of the pivotable backrest element 36i. The first locking unit 176i has a locking element that is adjustable in a spring-loaded manner between a locking position and a release position. The locking element is provided for a positive-locking connection with the second locking unit 178i.

[0153] The reset module 56i has a first spring element 58i to provide a reset force. The reset module 56i has a second spring element 158i to provide a reset force. Different from the previous embodiment, the reset module has two spring elements 58i, 158i. The spring elements 58i, 158i are each arranged on one side of the backrest frame 60i. The spring elements 58i, 158i are each attached to the lateral frame elements of the backrest frame 60i. The spring elements 58i, 158i are each attached to the outer side of the lateral frame elements of the backrest frame 60i in the illustrated embodiment. The spring elements 58i, 158i are configured as bending springs. The spring elements 58i, 158i are preferably configured as metal bending springs. The spring elements 58i, 158i are arranged to provide a spring force.

[0154] The spring force of the spring element 58i, 158i forms the reset force of the reset module 56i. The spring element 58i, 158i is arranged between the pivotable backrest element 36i and the mounting unit 12i in terms of functional technology. The spring element 58i, 158i is arranged to be supported on the mounting unit 12i with a first side. The spring element 58i, 158i is arranged to be supported on the pivotable backrest element 36i with a second side. The spring element 58i, 158i is arranged between one of the seat structure elements 26i, 28i and the lateral frame element of the backrest frame 60i in terms of effect technology. The spring element 58i, 158i is each identically constructed and equivalently attached to the backrest frame 60i. Therefore, only one spring element 58i and its attachment will be described below, wherein the description can be used to illustrate the second spring element 158i. The spring element 58i is constructed as a helical spring. The spring element 58i has a spiral middle region 160i and two spring legs 162i, 164i protruding from the middle region 160i. The reset module 65i has a support element 166i, by which the spring element 58i is attached to the backrest frame 60i. The support element 166i is designed as a supporting cylinder. The support element 166i has a cylindrical jacket surface, on which the spring element 58i rests with its spiral middle region 160i. The spring element 58i surrounds the support element 166i with its spiral middle region 160i. The support element 166i is firmly attached to the outer side of the lateral frame element of the backrest frame 60i. Preferably, the support element 166i is screwed to the outer side of the lateral frame element of the backrest frame 60i in a fixed manner by a screw connection.

[0155] The first spring leg 162i is provided for supporting on the bearing bolt 46i. The first spring leg 162i is provided for supporting on the first locking unit 176i. In order to support the first spring leg 162i, the reset module 56i has a first support element 168i. The first spring leg 162i is supported on the support element 168i, which is 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 provided for supporting on the backrest element 36i. The second spring leg 164i is provided for supporting on the lateral frame element of the backrest frame 60i. The reset module 56i has a second support element 170i for supporting the second spring leg 164i. The second support element 170i is provided for supporting the second spring leg 164i on the backrest frame 60i. The support element 170i is configured as a support bolt, which is firmly attached to the side surface of the lateral frame element of the backrest frame 60i. The support element 170i is preferably mounted by means of a screw connection. The spring element 58i bears against the support element 170i in order to be supported by its spring legs 164i.

[0156] By means of 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 evenly on both sides of the pivotable backrest element 36i. As a result, a further reinforcement of the backrest frame 60i, in particular between two lateral frame elements in the middle region, can advantageously be omitted. As a result, the pivotable backrest element 36i can advantageously be constructed in a simple manner.

[0157] 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 each attached to the inner side of the corresponding lateral frame element of the backrest frame 60i. By attaching the spring elements 58i, 158i and / or the locking modules 172i, 174i of the locking unit 88i in the backrest frame 60i, the pivotable backrest element 36i can be formed particularly advantageously.

[0158] The aircraft seat arrangement has a lower covering module 182i. The lower covering module 182i is arranged to at least partially cover the lower region of the backrest 34i toward the rear side. The lower covering module 182i is preferably arranged to cover at least one subregion of the lower backrest element 52i. The lower covering module 182i covers the lower backrest element 52i in the subregion backward. The lower covering module 182i has a covering element 184i. The covering element 184i is arranged in the upper region of the lower backrest element 52i. The covering element 184i is arranged centrally on the lower backrest element 52i on its rear side. The covering element 184i covers at least the lip 104i and the upper region 152i of the lower backrest element 52i. The covering element 184i is arranged to cover the flexible upper region 152i of the lower backrest element 52i backward. The covering element 184i is connected to the lower backrest element 52i. Preferably, the cover element is detachably 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 pocket 188i or another additional unit.

[0159] The covering element 184i does not cover the lower region of the lower backrest element 52i. The lower backrest element 52i forms a visible surface 186i in its lower region, which is not covered toward the rear. The visible surface of the lower backrest element 52i is not covered by the covering element 184i of the covering module 182i. The visible surface 186i of the lower backrest element 52i can be covered with a coating or a film. In principle, it is also conceivable that the backrest element 52i has no covering on its visible surface 186i. The lower backrest element 52i forms a kick plate of the backrest 34i with its visible surface 186i.

[0160] The aircraft seat arrangement has an upper covering module 190i. The upper covering module 190i is arranged to cover the upper region of the backrest 34i, in particular the pivotable backrest element 36i, backwards. The upper covering module 190i has a covering element 192i. The covering element 192i preferably extends through the entire rear side of the upper pivotable backrest element 36i. The upper covering module 190i preferably covers the laterally arranged locking modules 172i, 174i of the locking unit 88i. It is preferably conceivable that the upper covering module 190i has individually detachable covering elements in the region of the locking modules 172i, 174i, which can be separated from the backrest element 36i individually in order to easily reach the locking modules 172i, 174i. The covering element 192i forms a document pocket 194i in its upper region. The document pocket 194i is arranged in the head region of the backrest 34i. The aircraft seat arrangement also has a pivotable table 196i. The pivotable table can be folded onto the covering element 192i of the upper covering module 190i.

[0161] Fig.21The tenth embodiment of an aircraft seat device according to the invention is shown. The aircraft seat device is constructed substantially identically to the aircraft seat device of the ninth embodiment. The aircraft seat device comprises a backrest 34j. The backrest 34j is arranged so that a person sitting on an aircraft seat 10j can support his back on the backrest 34j, of which the aircraft seat device is a part. The backrest 34j has a pivotable backrest element 36j. The pivotable backrest element 36j is pivotably supported on a mounting unit 12j. The aircraft seat device has a supporting device 42j. The supporting device 42j is arranged so that the backrest 34j is pivotably supported between an upright seat position and a comfort position. The pivotable backrest element 36j has a backrest frame 60j. The aircraft seat device has a resetting module 56j. The resetting module 56j is arranged for resetting the backrest 34j from the comfort position to the upright seat position. The resetting module 56j has a locking unit 88j. The locking unit 88j is arranged to lock or unlock the resetting module 56j. The locking unit 88j is provided to lock the backrest 34j, ie the pivotable backrest element 36j, at least in the upright seating position and in the comfort position.

[0162] The reset module 56j has a first spring element 58j and a second spring element 158j to provide a reset force. Different from the previous embodiment, the spring elements 58j, 158j are configured as rod spring elements. The rod spring elements 58j, 158j are each arranged between a support element 170j placed on the backrest frame 60j and a support element 168j attached to the locking unit 178j. The spring element 58j configured as a rod spring element is each supported on the corresponding support element 168j, 170j with the same first side in the end region. The reset module 56j has a steering element 198j, and the spring element 58j configured as a rod spring element can be supported on the steering element 198j with an opposite second side. The steering element 198j is arranged between the two support elements 168j, 180j. The steering element 198j is basically arranged in the middle between the two support elements 168j, 170j. The steering element 198j is configured as a support bolt, which is attached to the backrest frame. The deflection element 198j is screwed to the outside of the lateral frame elements of the backrest frame 60j.

[0163] Fig. 22An alternative design of the lower backrest element 52k in another embodiment is shown. The basic implementation scheme of the aircraft seat device is substantially the same as the design scheme of the ninth embodiment. The lower backrest element 52k is flexibly configured in its upper region 152k. The lower backrest element 52k is more flexibly configured in its upper region 152k than in its main region 102k arranged below it. The lower backrest element 52k is elastically deflectable in its upper region 152k. In order to form flexibility in the upper region 152k, the lower backrest unit 52k has a recess pattern 154k in the upper region 152k. The recess pattern 154k is composed of at least one recess 156k introduced into the lower backrest element 52k. The recess pattern 154k is only arranged in the upper region 152k. The recess 156k is configured as a corrugated recess 156k in this embodiment. The corrugated recess 156k extends in the transverse direction. A plurality of wave-shaped recesses 156 k are preferably arranged in a row spaced apart from one another in the transverse direction. In principle, it is also conceivable that the recesses 156 k have other shapes or are formed in different shapes.

[0164] Description of reference numerals:

[0165] 10 Aircraft Seat 68 Fastening Unit

[0166] 12 Mounting unit 70 Fastening body

[0167] 14 Aircraft seat row 72 fastening elements

[0168] 16 Aircraft seats 74 Fastening elements

[0169] 18 seat feet 76 through slot

[0170] 20 seat feet 78 through slot

[0171] 22 horizontal carrier 80 middle area

[0172] 24 Horizontal carrier 82 storage area

[0173] 26 seat structural elements 84 ribs

[0174] 28 seat structural elements 86 ribs

[0175] 30 Seat Area 88 Locking Units

[0176] 32 Seat bottom 90 Actuating element

[0177] 34 backrest 92 armrest

[0178] 36 pivotable backrest element 94 armrest

[0179] 38 Support position

[0180] 40 Support position

[0181] 42 Support device 100 Covering

[0182] 44 rotation axis 102 main area

[0183] 46 support bolt 104 lip

[0184] 48 Support bolt 106 front side

[0185] 50 knee area 108 transverse reinforcement element

[0186] 52 lower backrest element 110 lever transmission

[0187] 54 fastening element 112 base retaining element

[0188] 56 Reset module 114 Fastening storage part

[0189] 58 Spring element 116 fastening receiving portion

[0190] 60 backrest frame 118 lever element

[0191] 62 shell element 120 support position

[0192] 64 fastening unit 122 coupling element

[0193] 66 transverse carrier 124 eccentric element

[0194] 126 eccentric element 178 second locking unit

[0195] 128 attachment points 180 body

[0196] 130 attachment points 182 lower cover module

[0197] 132 torsion tube 184 covering element

[0198] 134 attachment points 186 visible surface

[0199] 136 attachment points 188 literature pockets

[0200] 138 lever element 190 cover module

[0201] 140 seat shell element 192 covering element

[0202] 142 Side area 194 Literature pocket

[0203] 144 side areas 196 tables

[0204] 146 Aircraft seats 198 Steering components

[0205] 148 Slot

[0206] 150 Slot

[0207] 152 Upper Area

[0208] 154 concave pattern

[0209] 156 recess

[0210] 158 Spring element

[0211] 160 Middle Area

[0212] 162 Spring Legs

[0213] 164 Spring Legs

[0214] 166 Support element

[0215] 168 Support element

[0216] 170 Support element

[0217] 172 Locking module

[0218] 174 Locking module

[0219] 176 First Locking Unit

Claims

1. An aircraft seat arrangement, comprising: a mounting unit (12a; 12b; 12c; 12d; 12e; 12f; 12g; 12h), the mounting unit (12a; 12b; 12c; 12d; 12e; 12f; 12g; 12h) being arranged for mounting on a cabin bottom and having at least one transverse carrier (22a, 24a; 22b, 24b; 22c, 24c; 22d, 24d; 22e, 24e; 22f, 24f; 22g, 24g; 22h, 24h); two seat structures The two seat structural elements (26a, 28a; 26b, 28b; 26c, 28c; 26d, 28d; 26e, 28e; 26f, 28f; 26g, 28g; 26h, 28h) are each arranged on one side of the seat area (30a; 30b; 30c; 30d; 30e; 30f; 30g; 30h). side and each having a support position (38a, 40a; 38b, 40b; 38c, 40c; 38d, 40d; 38e, 40e; 38f, 40f; 38g, 40g; 38h, 40h); a backrest (34a; 34b; 34c; 34d; 34e; 34f; 34g; 34h), the backrest being connected by the seat structure element (26a, 28a; 26b, 28b; 26c, 28c; 26d, 28d; 26e, 28e; 26f, 28f; 26g, 28g; 26h , 28h) of the support position (38a, 40a; 38b, 40b; 38c, 40c; 38d, 40d; 38e, 40e; 38f, 40f; 38g, 40g; 38h, 40h); and a support device (42a; 42b; 42c; 42d; 42e; 42f; 42g; 42h) arranged to pivotally support the backrest (34a; 34b; 34c; 34d; 34e; 34f; 34g; 34h) between an upright seating position and a comfort position, in, The backrest (34a; 34b; 34c; 34d; 34e; 34f; 34g; 34h) comprises a pivotable backrest element (36a; 36b; 36c; 36d; 36e; 36f; 36g; 36h), characterized by at least one resetting module (56a; 56b; 56c; 56d; 56e; 56f; 56g; 56h), which is at least configured to provide for the backrest (34a; 34b; 34c; 34d; 34e; 34f; 34g; 34h) to be pivotable from the backrest element A restoring force for restoring the comfort position to the upright seat position is arranged at least substantially in the area above the bearing point (38a, 40a; 38b, 40b; 38c, 40c; 38d, 40d; 38e, 40e; 38f, 40f; 38g, 40g; 38h, 40h) of the seat structure element (26a, 28a; 26b, 28b; 26c, 28c; 26d, 28d; 26e, 28e; 26f, 28f; 26g, 28g; 26h, 28h) of the seat structure element (26a, 28a; 26b, 28b; 26c, 28c; 26d, 28d; 26e, 28e; 26f, 28f; 26g, 28g; 26h, 28h) 2. The aircraft seat device according to claim 1, It is characterized in that The seat structure elements (26a-26h, 28a-28h) extend in their rear region upwards away from the mounting unit (12a-12h) at least substantially to the backrest height (X), wherein the seat structure elements (26a-26h, 28a-28h) each have at their rear upper end the support position (38a-38h, 40a-40h) for supporting the pivotable backrest element (36a-36h).

3. An aircraft seat device according to claim 1 or 2, It is characterized in that The restoring module (56a-56h) has at least one spring element (58a-58h), which is provided for providing a restoring force.

4. An aircraft seat arrangement according to any one of the preceding claims, It is characterized in that The backrest (34a-34h) has a lower backrest element (36a-36h) which forms a lower region of the backrest (34a-34h) and is fastened to the seat structure element (26a-26h, 28a-28h).

5. The aircraft seat device according to claim 4, It is characterized in that The lower backrest element (36a-36h) extends from the height of the at least one transverse carrier (22a-22h, 24a-24h) to a height of 450 mm-700 mm measured from the mounting plane.

6. Aircraft seat arrangement according to claims 3 and 4, It is characterized in that The spring elements (58a-58h) are designed as leaf spring elements and are arranged to be attached to the lower backrest element (36a-36h) or to the mounting unit (12a-12h).

7. An aircraft seat arrangement at least according to claim 3, It is characterized in that The backrest (34a-34h) has a transverse carrier (66a-66h) in the area above the bearing point (38a-38h, 40a-40h), to which the spring element (58a-58h) designed as a leaf spring element is attached in order to transmit a restoring force to the pivotable backrest element (36a-36h).

8. An aircraft seat arrangement at least according to claim 4, It is characterized in that The lower backrest element (36a-36h) has an upper lip (104b) at its upper end, which extends into a region above the support point (38a-38h, 40a-40h) for supporting the backrest (34a-34h).

9. Aircraft seat arrangement according to any one of the preceding claims, It is characterized in that The pivotable backrest element (36a-36h) has a backrest frame (60a-60h) and a covering (100a-100h) stretched on the backrest frame (60b-60h) or a shell element (62a-62h) connected to the backrest frame (60-60h).

10. The aircraft seat device according to claim 1, It is characterized in that The restoring module (56a-56h) has a spring element (58e-58f) designed as a gas pressure spring, which is arranged in a region above the bearing point (38a-38h, 40a-40h).

11. An aircraft seat arrangement according to any one of the preceding claims, It is characterized in that The restoring module (56a-56h) has at least one lever transmission (110e-110f), which is arranged to transmit a restoring force to the pivotable backrest element (36a-36h).

12. An aircraft seat arrangement according to any one of the preceding claims, It is characterized in that The restoring module (56a-56h) has a torsion tube (132f) which transmits the restoring force from one side of the pivotable backrest element (36a-36h) to the opposite side.

13. An aircraft seat arrangement according to any one of the preceding claims, It is characterized in that The bearing point (38a-38h, 40a-40h) for supporting the pivotable backrest element (36a-36h) defines a rotation axis (44a-44h), which is arranged above the knee area (50a-50h) of the backrest (34a-34h).

14. The aircraft seat device according to claim 6, It is characterized in that The spring element (58a-58h) for providing a restoring force, which is designed as a leaf spring element, is formed in one piece with the lower backrest element (36a-36h).

15. An aircraft seat arrangement at least according to claim 3, It is characterized in that The spring element (58a-58h) for generating a restoring force is at least partially formed in one piece with the pivotable backrest element (36a-36h).

Images