Aircraft seat actuation device

Abstract

The invention is based on an aircraft seat actuation device for actuating a mechanism (22), in particular a locking mechanism, comprising a Bowden cable (30) for actuating the mechanism (22), and comprising an actuation module (36) for actuating the Bowden cable (30). According to the invention, the actuation module (36) for actuating the Bowden cable (30) has at least one toggle lever unit (38) which comprises at least a first toggle lever element (40) and a second toggle lever element (42) which are mounted pivotably with respect to one another.

Description

[0001] September 8, 2025

[0002] Aircraft seat actuation device

[0003] State of the art

[0004] The invention relates to an aircraft seat actuation device according to the preamble of claim 1.

[0005] An aircraft seat actuation device for actuating a mechanism, in particular a locking mechanism, with a Bowden cable for actuating the mechanism, and with an actuating module for actuating the Bowden cable, has already been proposed.

[0006] Actuating modules known from the prior art for actuating a Bowden cable have a pivot lever that can be actuated by means of a push button, to which an inner cable of the Bowden cable to be actuated is attached. When actuated, the pivot lever is swung outwards by a base body to which it is attached. This results in the actuating modules known from the prior art having an installation depth of 30 mm or more, since the pivot lever requires space to the rear to be fully adjusted in order to actuate the Bowden cable. This is particularly disadvantageous in confined spaces, such as in armrests. For the actuating modules known from the prior art, sufficiently wide armrests must be provided, or if an actuating module is provided on each side of the armrest, the corresponding actuating modules cannot be arranged in identical longitudinal positions within the armrest.

[0007] The object of the invention is, in particular, to provide a generic device with improved properties with regard to installation space requirements and complexity. This object is achieved according to the invention by the features of claim 1, while advantageous embodiments and further developments of the invention can be found in the dependent claims.

[0008] Advantages of the invention REC 17460 WO

[0009] The invention relates to an aircraft seat actuation device for actuating a mechanism, in particular a locking mechanism, with a Bowden cable for actuating the mechanism, and with an actuating module for actuating the Bowden cable.

[0010] It is proposed that the actuating module for actuating the Bowden cable comprises a toggle lever unit including at least a first toggle lever element and a second toggle lever element, which are pivotably mounted relative to each other. An "aircraft seat actuation device" is preferably understood to be a device designed to actuate a mechanism of an aircraft seat assembly by an operator, in particular a passenger. The aircraft seat actuation device is preferably designed for manual actuation by an operator. The aircraft seat actuation device is designed to transmit an actuating force and / or actuating movement exerted by an operator to the mechanism to be actuated. The aircraft seat actuation device is preferably designed as part of an aircraft seat assembly.The aircraft seat actuation device can preferably be used to actuate various mechanisms of an aircraft seat or an aircraft seat section that can be operated by means of a Bowden cable. An "aircraft seat actuation device" is preferably understood to be a device that forms at least part of an aircraft seat or an entire aircraft seat. In particular, an "aircraft seat" is understood to be a seat that is intended to be mounted on a cabin floor in an aircraft cabin and on which a passenger can sit during a flight. The aircraft seat actuation device has at least one seat base that forms a seating surface. The aircraft seat actuation device has a backrest that forms a backrest surface. The backrest is preferably pivotably mounted relative to the seat base.Preferably, the backrest is pivotably mounted between an upright sitting position and a comfort position. The backrest is preferably pivotally connected to a fixed seat component. This pivoting mounting allows the aircraft seat to be moved into different functional positions. A "pivotally mounted backrest" is preferably understood to mean a backrest that, in normal operation, can be pivoted between a maximally upright sitting position and a comfort position adjusted backwards from the upright sitting position (REC 17460 WO). The upright sitting position is designed as a TTL (Taxi, Takeoff, Landing) position of the aircraft seat, which must be set for safety reasons during certain phases of an aircraft journey.The term "mechanism" preferably refers to a group of parts that are at least partially movable relative to each other and that work together to generate movement or perform a specific action. For example, the mechanism is designed as a locking mechanism. Preferably, the mechanism is designed as a gas spring or a mechlock, or comprises a gas spring or a mechlock. A "mechlock" preferably refers to a linearly extendable, mechanically lockable spring mechanism that is preferably lockable in any position, particularly via a mechanical spring. A mechlock preferably has two bearing elements that are linearly displaceable relative to each other along a displacement axis between a minimum position and a maximum position, and which can be locked in the minimum position, the maximum position, and steplessly in intermediate positions via a spring element.The bearing elements are preferably lockable by means of a spring element by means of a frictional locking mechanism. One bearing element is preferably designed as a cylinder, and the other as a bearing rod slidably mounted within the cylinder. The spring element can preferably be designed as a coil spring. In principle, it would also be conceivable for the mechanism to be designed as a simple locking mechanism comprising two locking elements that are movable relative to each other and can be moved between a release position and a locked position. A "locking mechanism" is preferably understood to mean a mechanism for fixing a movable component of the aircraft seat, such as, in particular, a backrest, in different positions relative to a mounting structure, especially a stand unit.An "actuating module" is preferably understood to be a module designed to actuate a mechanism by transmitting an actuating force and / or an actuating movement over an actuating path. The actuating module is designed to transmit an actuating force and / or an actuating movement from a location where an actuating element, such as a push button, a pull element, or a rotary element, is arranged to the location where the mechanism to be actuated is situated.

[0011] For example, it is conceivable that the actuation module is intended to operate a REC 17460 WO

[0012] To transmit actuating force and / or an actuating movement from a front area of ​​an armrest to a backrest or seat base area in which the mechanism to be actuated is located. A "knee lever unit" is preferably understood to be a unit comprising at least two pivotally connected toggle lever elements which, in a position, preferably an unactuated position, are arranged at an angle to each other and which, preferably in an actuated position, can be brought into an at least substantially extended position. In the extended position, the toggle lever elements are arranged at least in partial areas at least substantially coaxially to each other. Each toggle lever element has a toggle lever axis that runs between a first bearing point, at which the toggle lever element is movably mounted, and a pivot element at which the toggle lever element is movably coupled to the other toggle lever element.The two toggle lever axes of the two toggle lever elements enclose a toggle lever angle with each other. Preferably, the toggle lever elements of the toggle lever unit are arranged at a toggle lever angle to each other in an unactuated state. In an unactuated state, the toggle lever elements are preferably arranged at a toggle lever angle of 95 degrees to 120 degrees, particularly preferably 105 degrees to 115 degrees, to each other. In a fully actuated state, the toggle lever elements are preferably aligned at a toggle lever angle of 125 degrees to 145 degrees, more preferably 130 degrees to 140 degrees, to each other. Preferably, the toggle lever elements are aligned at a toggle lever angle of 136 degrees to each other in a fully actuated state. The toggle lever unit is preferably designed to exert an actuating force and / or actuating movement in a lever line in which the toggle lever elements are aligned in the fully actuated state.The toggle lever unit has at least one joint through which the two toggle lever elements are pivotably connected to each other. The toggle lever elements are preferably designed such that actuation of one toggle lever element causes a force-amplifying movement of the other toggle lever element. The toggle lever unit is preferably designed to amplify an actuating force exerted on it. Preferably, the actuating module has only one toggle lever unit. However, it is also conceivable that the actuating module has several toggle lever units. A "toggle lever element" is preferably understood to be an elongated element that is rotatably mounted at least in an end region facing away from a second toggle lever element. REC 17460 WO.

[0013] Preferably, at least one of two toggle lever elements, which are movably coupled to each other, is pivotably and axially displaceably mounted at one end region. A toggle lever element is movably, and in particular pivotably, connected to the corresponding toggle lever element at an end region facing the corresponding toggle lever element. The term "provided for" is to be understood in particular as being specially designed and / or equipped. The fact that an object is provided for a specific function is to be understood in particular as the object fulfilling and / or performing this specific function in at least one application and / or operating state. An embodiment according to the invention can advantageously provide a particularly simple and low-profile aircraft seat actuation device.By integrating the toggle lever unit into the actuating module, an actuation path applied by an operator to the actuating module can advantageously be converted into a larger actuation path for actuating the Bowden cable. This allows the actuating module to be designed with a particularly low profile.

[0014] It is further proposed that an inner cable of the Bowden cable be attached to the second toggle lever element. "Attached" is preferably understood to mean firmly connected, so that a force can be transmitted between the toggle lever element and the inner cable of the Bowden cable. This allows the Bowden cable to be connected to the toggle lever unit for actuation by means of the actuating module in a particularly advantageous and simple manner.

[0015] Furthermore, it is proposed that the actuating module comprises a base body to which a Bowden cable housing is attached. The base body preferably has a receiving area in which the Bowden cable housing is arranged in an assembled state and can be supported against the base body. This allows the Bowden cable, and in particular the Bowden cable housing, to be attached for actuation by the toggle lever unit particularly easily and advantageously.

[0016] It is further proposed that the first and second toggle lever elements be articulated together via a joint element. This allows the toggle lever elements to be coupled together particularly easily to form the toggle lever unit. REC 17460 WO

[0017] Furthermore, it is proposed that the joint element be formed by a sliding shell, via which the two toggle lever elements are slidably coupled to each other. This allows the joint element to be designed particularly simply.

[0018] It is further proposed that the actuating module comprises a base body to which the first toggle lever element is rotatably mounted. A "base body" is preferably understood to be an assembly base body to which components of the actuating module are attached in an assembled state. The base body is preferably designed for attachment to an aircraft seat component or an aircraft seat area component. Preferably, the base body is designed for integration into an armrest, a console element, or a backrest. The base body is preferably designed to connect the actuating module to the aircraft seat component, for example, the armrest. The actuating module is attached to the aircraft seat component, for example, the armrest, via the base body. The base body forms part of a bearing point for mounting the first toggle lever element.Preferably, the base body forms at least one bearing pin or bearing receptacle for mounting the first toggle lever element. This allows the toggle lever unit to be attached particularly easily.

[0019] Furthermore, it is proposed that the actuating module has a base body on which the second toggle lever element is slidably mounted along a bearing axis via a sliding bearing. The second toggle lever element is linearly displaceable and rotatable via the sliding bearing. When the toggle lever unit is actuated, the sliding bearing allows the second toggle lever element to pivot relative to the first toggle lever element and simultaneously exert a relative movement to the base body of the mounting module. This axial displacement along the bearing axis actuates the Bowden cable. This allows the second toggle lever unit to be mounted particularly advantageously within the toggle lever assembly. The axial displaceability of the second toggle lever element advantageously enables actuation of the Bowden cable.

[0020] It is further proposed that the sliding bearing form an elongated hole in the second toggle lever element, via which the second toggle lever element is slidably and rotatably mounted on the base body. The length of the elongated hole advantageously provides an adjustment range for the toggle lever unit and thus an actuation range with which the REC 17460 WO

[0021] The Bowden cable is actuated by the toggle lever unit, as specified. This allows the sliding bearing to be designed particularly advantageously.

[0022] Furthermore, it is proposed that the actuating module includes a push button for actuating the actuating module, which is formed by the first toggle lever element. A "push button" is preferably understood to be an actuating element designed to be actuated by a pressure force applied by an operator and to transmit this pressure force as an actuating force to the toggle lever unit. When actuated, the push button is designed to be adjusted by an actuating travel, which the push button transmits to the toggle lever unit. The push button is formed integrally with the first toggle lever element. The push button is preferably formed by a projection of the first toggle lever element that, in a mounted state and in the unactuated position, extends over an outer surface of the aircraft seat element, in particular the armrest.This makes it particularly easy to integrate an actuating element for actuating the actuating module.

[0023] It is further proposed that the two toggle lever elements, in an unactuated state of the actuating module, enclose a toggle lever angle between 95 degrees and 120 degrees. Preferably, the angle enclosed between the two toggle lever elements in an unactuated state lies between 105 degrees and 115 degrees, and particularly preferably between 110 degrees and 112 degrees. The angle between the two toggle lever elements is measured between their toggle lever axes, with one toggle lever axis of a toggle lever element passing through the bearing point at which the toggle lever element is pivotably mounted, in particular on the base body of the actuating module, and the joint at which the two toggle lever elements are pivotally connected. This allows the toggle lever unit to be designed particularly advantageously for efficiently translating an actuating force and an actuating stroke.

[0024] Furthermore, it is proposed that the actuating module in one embodiment be free of a return spring. A "return spring" is preferably understood to be a spring element designed to exert a return force on the toggle lever unit in order to move it back to its unactuated position. "Free of a return spring" preferably means that no return spring is present and that return is achieved by a tensile force of the Bowden cable REC 17460 WO and / or an internal return force of the toggle lever elements. In an alternative embodiment, it is also conceivable that the actuating module has a return spring that ensures proper return of the toggle lever unit after actuation. The return spring could be designed as a spring element that is functionally arranged between the base body of the actuating module and one of the toggle lever elements.For example, the spring element could be designed as an integral leaf spring. This allows the actuation module to be designed particularly simply.

[0025] It is further proposed that the actuation module be composed solely of a base body, the first toggle lever element, and the second toggle lever element. In principle, it would also be conceivable for the actuation module to include additional components for attachment to the aircraft seat component, particularly the armrest. This would allow the actuation module to be designed in a particularly simple and cost-effective manner.

[0026] Furthermore, it is proposed that the actuating module has a maximum depth extension of 15 mm, and that the toggle lever unit, in an actuated state, does not extend beyond the base body of the actuating module in any depth direction. Depth extension is defined as the extension from a contact surface of the base body, where the base body rests against the aircraft seat component, for example, the armrest, in a mounted state, to a rear end of the base body measured orthogonally to the contact surface. The depth extension specifies the extent to which the actuating module extends into the aircraft seat component, for example, the armrest, in a mounted state. The depth extension is the maximum extension of the actuating module in any depth direction.The depth extension indicates how far the actuating module extends into an aircraft seat component, particularly the armrest. Preferably, the depth extension is less than 30 mm, more preferably less than 20 mm, and most preferably less than 16 mm. This allows for a particularly flat actuating module that can be advantageously installed in a space-saving manner.

[0027] The aircraft seat actuation device according to the invention is not to be limited to the application and embodiment described above. In particular, the aircraft seat actuation device according to the invention may, in order to fulfill a function described herein in REC 17460 WO, have a different number of individual elements, components and units than that specified herein.

[0028] Drawings

[0029] Further advantages will become apparent from the following description of the drawing. The drawing illustrates an embodiment of the invention. The drawing, the description, and the claims contain numerous features in combination. A person skilled in the art will expediently consider the features individually and combine them into meaningful further combinations.

[0030] They show:

[0031] Fig. 1 shows a schematic representation of an aircraft seat row, with an aircraft seat device comprising an aircraft seat actuation device for actuating a mechanism, and an actuation module for this purpose.

[0032] Fig. 2 shows a detailed view of an armrest of the aircraft seat device, into which an actuating module of the aircraft seat actuating device is integrated.

[0033] Fig. 3 shows a sectional view through the armrest with two actuation modules for two adjacent aircraft seats that adjoin the armrest.

[0034] Fig. 4 shows a schematic view of the actuating module with the Bowden cable and a toggle lever unit attached to a base body, in an unactuated state.

[0035] Fig. 5 shows a schematic sectional view of the actuating module with the Bowden cable and the toggle lever unit, which is attached to a base body, in an unactuated state.

[0036] Fig. 6 shows a schematic sectional view through the actuating module in an unactuated state.

[0037] Fig. 7 a schematic view of the actuating module with the Bowden cable and the toggle lever unit, which is attached to a base body, in a fully actuated state, REC 17460 WO

[0038] Fig. 8 shows a schematic sectional view of the actuating module with the Bowden cable and the toggle lever unit, which is attached to a base body, in the fully actuated state.

[0039] Fig. 9 shows a schematic sectional view through the actuating module in the fully actuated state.

[0040] Fig. 10 is a schematic superimposed sectional view through the actuating module, in the actuated and unactuated states, Fig. 11 is a schematic exploded view of the actuating module, and Fig. 12 is another schematic exploded view of the actuating module.

[0041] Description of the exemplary embodiment

[0042] Figures 1 to 12 show an aircraft seat actuation device according to the invention. The aircraft seat actuation device is part of an aircraft seat assembly 10. Figure 1 shows an exemplary aircraft seat assembly 10. The aircraft seat assembly 10 is part of an aircraft seat 12. The aircraft seat 12 is shown here as part of a row of seats 14. In principle, it would also be conceivable for the aircraft seat 12 to be designed as an individual seat. It would also be conceivable for the aircraft seat assembly 10 to be designed as part of an aircraft seat configured as a business class or first class seat, which has a housing and is designed for adjustment into a substantially flat reclining position. The aircraft seat 12 has a mounting unit 16, a seat base 18, and a backrest 20. The seat base 18 and the backrest 20 are preferably mountable on a floor, in particular a cabin floor, via the mounting unit 16.The seat base 18 and the backrest 20 are attached to the support unit 16. The backrest 20 is preferably pivotably mounted on the support unit 16. The aircraft seat 12 has a bearing unit (not shown) by which the backrest 20 is pivotably connected to the support unit 16. Preferably, the backrest 20 is pivotably mounted on seat dividers of the support unit 16 by means of the bearing unit. The backrest 20 is preferably pivotable between an upright sitting position and a maximum comfort position. The backrest 20 is preferably lockable at least in the upright sitting position and the comfort position. The aircraft seat assembly 10 has a mechanism 22 by which the backrest 20 can be locked. The backrest 20 is preferably lockable at least in the upright sitting position and in the maximum comfort position by means of the mechanism 22.Mechanism 22 is designed as a locking mechanism. Preferably, mechanism 22 comprises a gas spring. Alternatively, mechanism 22 could also have a Mechlock or another mechanical spring with a locking mechanism. Mechanism 22, in particular the gas spring, has an actuated state and an unactuated state. In the unactuated state, mechanism 22 is in a locked position. In the locked position, mechanism 22, in particular the gas spring, locks the backrest 20, so that it is locked in its current position. In the actuated state, mechanism 22, in particular the gas spring, is in a release position. In the release position, mechanism 22, in particular the gas spring, releases the backrest 20, allowing it to pivot between the upright sitting position and the maximum comfort position.Preferably, the mechanism 22, in particular the gas spring, supports a pivoting of the backrest 20 in an adjustment direction, preferably in the direction of the upright sitting position, in the release position.

[0043] The aircraft seat 12 comprises a first armrest 24 and a second armrest 26. The armrests 24 and 26 are each arranged laterally to a seat area of ​​the aircraft seat 12. The armrests 24 and 26 are each connected to the support unit 16. A connection to the backrest 20 would also be conceivable. Preferably, the armrests 24 and 26 are pivotally connected to a seat divider of the support unit 16. However, it would also be conceivable for the armrests 24 and 26 to be rigidly and non-adjustably connected to the support unit 16 or the backrest 20. The armrest 24 preferably has a base body 28. The base body 28 can be formed in one piece or from several shell elements. Preferably, the base body 28 is made of a plastic. The armrest 24 forms an armrest surface on its upper side. The base body 28 is designed as a hollow body. The basic body 28 forms an interior space.

[0044] The aircraft seat actuation device is designed to actuate mechanism 22, in particular mechanism 22 designed as a locking mechanism. The aircraft seat actuation device includes a Bowden cable 30. The Bowden cable REC 17460 WO

[0045] The Bowden cable 30 is designed to actuate the mechanism 22, in particular the locking mechanism. The Bowden cable 30 is designed to transmit an actuating force and an actuating movement to the mechanism 22, in particular the locking mechanism. The gas spring of the mechanism 22 is preferably actuated via the Bowden cable 30. The mechanism 22 can be moved from the unactuated state to the actuated state by means of the Bowden cable 30. The Bowden cable 30 preferably has a Bowden cable housing 32 and an inner cable 34 slidably mounted in the Bowden cable housing 32. The inner cable 34 protrudes from the Bowden cable housing 32 at both ends and has a coupling element at each end by means of which the inner cable 34 can be connected to an element to be actuated or to an actuating element.

[0046] The aircraft seat actuation device has an actuation module 36. The actuation module 36 is designed to actuate the Bowden cable 30. The actuation module 36 is designed to transmit an operator's actuation force to the Bowden cable 30. The actuation module 36 is designed to be actuated by an operator, for example, a passenger. By means of the actuation module 36, an operator can actuate the mechanism 22 via the Bowden cable 30, in particular to switch it from an unactuated state to an actuated state. By means of the actuation module 36, the inner cable 34 of the Bowden cable 30 can be pulled by actuation. The actuation module 36 is designed to exert a tensile force on the inner cable 34 of the Bowden cable 30 when actuated by an operator.

[0047] The aircraft seat actuation device is at least partially arranged in the armrest 24. The Bowden cable 30 runs at least partially within the armrest 24. The Bowden cable 30 is located in the interior space defined by the base body 28 of the armrest 24. The actuating module 36 for actuating the Bowden cable 30 is integrated into the armrest 24. The actuating module 36 is located on a side wall of the base body 28 of the armrest 24. The base body 28 of the armrest 24 has a recess in which the actuating module 36 is located. The actuating module 36 extends into an interior space defined by the base body 28 of the armrest 24. The actuating module 36 is preferably located in a front area of ​​the armrest 24. The Bowden cable 30 is preferably guided from a rear area of ​​the armrest 24 in the interior to the actuating module 36 REC 17460 WO, which is located in a front area of ​​the armrest 24.In principle, it would also be conceivable that the aircraft seat actuation device and thus the Bowden cable 30 and the actuation module 36 are integrated into another component of the aircraft seat 12 or an aircraft seat area, such as a backrest 20 or a console element.

[0048] The actuating module 36 has a toggle lever unit 38 for actuating the Bowden cable 30. The toggle lever unit 38 is designed to transmit a pulling movement to the Bowden cable 30, i.e., to the inner cable 34 of the Bowden cable 30. The toggle lever unit 38 is designed to convert an operator's actuating movement into a pulling movement to the Bowden cable 30, i.e., to the inner cable 34 of the Bowden cable 30. The toggle lever unit 38 is preferably designed to translate an actuating force applied by the operator into a pulling force on the Bowden cable 30, i.e., on the inner cable 34 of the Bowden cable 30. The toggle lever unit 38 is preferably designed to convert an actuating movement performed by the operator into a pulling movement of the Bowden cable 30, in particular of the inner cable 34 of the Bowden cable 30.The pulling motion transmitted by the toggle lever unit 38 to the Bowden cable 30, in particular its inner cable 34, is equal to the actuation distance performed by the user. An actuation distance of 5 mm performed by the user results in a pulling motion of 5 mm in the Bowden cable 30. Preferably, the maximum actuation distance from the unactuated state to the fully actuated state is only 5 mm. However, it would also be conceivable for the maximum actuation distance to be between 15 and 5 mm, for example, 10 mm or 8 mm. This allows a small actuation distance to generate an advantageously large pulling motion for actuating the Bowden cable 30, thus enabling particularly simple actuation of the Bowden cable 30 and consequently of the mechanism 22.

[0049] The toggle lever unit 38 comprises a first toggle lever element 40 and a second toggle lever element 42, which are pivotally mounted relative to each other. The two toggle lever elements 40, 42 are each movably, in particular rotatably, mounted at an end region facing away from the other toggle lever element 40, 42. The two toggle lever elements 40, 42 are each coupled to the other toggle lever element 40, 42 at an end region facing the other toggle lever element 40, 42. The first toggle lever element 40 and the second toggle lever element 42 are connected via a joint element REC 17460 WO.

[0050] The two toggle lever elements 40 and 42 are articulated together. The joint element 44, through which the two toggle lever elements 40 and 42 are articulated together, is designed as a sliding shell. The joint element 44, designed as a sliding shell, is formed by one of the toggle lever elements 40 and 42. The first toggle lever element 40 forms the joint element 44, designed as a sliding shell, at its second end region, which faces the second toggle lever element 42. The joint element 44, designed as a sliding shell, is formed integrally with the first toggle lever element 40. The joint element 44, designed as a sliding shell, is designed as a recess on an inner surface 46 of the first toggle lever element 40. The joint element 44, designed as a sliding shell, is preferably designed as an elongated groove with a rounded bottom. The joint element 44, designed as a sliding shell, is preferably designed as an elongated groove with a substantially semicircular cross-section.

[0051] The second toggle lever element 42 has a joint element 48. The joint element 48 of the second toggle lever element 42 is configured correspondingly to the joint element 44 formed by the first toggle lever element 40. In particular, the toggle lever element 40, 42, which does not have the joint element 44 configured as a joint shell, has a correspondingly configured joint element 48. The joint element 48 formed by the second toggle lever element 42 is arranged at a second end of the second toggle lever element 42. At this second end, the second toggle lever element 42 has a projection 50. The projection 50 forms the joint element 48 at its end. The projection 50 is rounded at its end to form the joint element 48. The projection 50, which forms the corresponding joint element 48 at its end, is configured correspondingly to the elongated groove formed by the joint element 44 configured as a sliding shell.The joint element 48 formed by the projection 50 engages in the joint element 44, which is designed as a joint shell, when assembled. In this state, the joint element 48 formed by the projection 50 can pivot within the joint element 44, which is designed as a joint shell.

[0052] The first toggle lever element 40 is pivotally mounted. The first toggle lever element 40 is rotatably mounted via a first bearing point 52 of the toggle lever unit 38. The first toggle lever element 40 is rotatably mounted about a pivot axis. The first toggle lever element 40 is pivotally mounted in its first end region, which faces away from the second toggle lever element 42. The first toggle lever element 40 is rotatably mounted REC 17460 WO. The second toggle lever element 42 is pivotally mounted. The second toggle lever element 42 is pivotally mounted in its first end region, which faces away from the first toggle lever element 40. The second toggle lever element 42 is rotatably and axially displaceably mounted via a second bearing point 54 of the toggle lever unit 38. The second toggle lever element 42 is rotatably mounted and displaceably mounted along a displacement axis.In contrast to the first toggle lever element 40, the second toggle lever element 42 is additionally mounted so that it can be slidably displaced, allowing the two toggle lever elements 40, 42 to be displaceable relative to each other along the displacement axis when actuated. The second toggle lever element 42 is rotatably and axially displaceably mounted via a sliding bearing 76. The bearing point 52 of the first toggle lever element 40 and the bearing point 54 of the second toggle lever element 42 define a lever line of the toggle lever unit 38.

[0053] The actuating module 36 has a base body 56. The base body 56 forms the basic structure of the actuating module 36. The actuating module 36 is attached to the aircraft seat assembly 10 via the base body 56. The base body 56 has a base plate 58. In an assembled state, the front face 60 of the base plate 58 forms a termination of the actuating module 36. Preferably, in an assembled state, the front face 60 is flush with the side wall of the base body 28 of the armrest 24. The base plate 58 forms a rear face 62, which, in an assembled state, faces the interior of the base body 28 of the armrest 24 or is located within it.

[0054] The actuating module 36 is connected to the armrest 24 via the base body 56. The toggle lever unit 38 is connected to the base body 56. The first toggle lever element 40 is rotatably mounted on the base body 56. The base body 56 forms the first bearing point 52 of the toggle lever unit 38. The base body 56 has a connecting element 64. The first bearing point 52 is located at a first end of the base body 56, which, in an assembled state, faces the Bowden cable 30. The connecting element 64 is located at a first end of the base body 56, which, in an assembled state, faces the Bowden cable 30. The connecting element 64 is located on the rear side 62 of the base plate 58. The connecting element 64 is integrally formed with the base plate 58. The connecting element 64 is designed as a raised section extending away from the rear side 62 of the base plate 58. The connecting element 64 preferably has a profile as described in REC 17460 WO

[0055] The connecting element 64 has a substantially rectangular basic shape. It has two parallel side walls. A bearing pin 66 is arranged on each side wall of the connecting element 64. The bearing pins 66 are preferably formed integrally with the connecting element 64. The bearing pins 66 could also be designed as inserted pins. The bearing pins 66 form the first bearing point 52 for the first toggle lever element 40. The bearing pins 66 form the pivot axis for the first toggle lever element 40. The first toggle lever element 40 has two spaced-apart webs 68. The spaced-apart webs 68 of the first toggle lever element 40 are spaced apart from each other at a distance corresponding to the width of the connecting element 64 of the base body 56. The first toggle lever element 40 engages the connecting element 64 of the base body 56 of the actuating module 36 with its webs 68.The webs 68 each have a bearing receptacle 70, which corresponds to the bearing pins 66. In an assembled state, the first toggle lever element 40, with its webs 68, engages the connecting element 64 of the base body 56, and the bearing pins 66 are arranged in the bearing receptacles 70 of the toggle lever element 40. The first toggle lever element 40 is rotatably mounted on the bearing pins 66 of the connecting element 64 of the base body 56 via its bearing receptacles 70. For assembly on the bearing pins 66, the webs 68 of the first toggle lever element 40 are elastically deflectable.

[0056] The second toggle lever element 42 is rotatably mounted on the base body 56. The second toggle lever element 42 is rotatably and axially displaceably mounted on the base body 56. The second toggle lever element 42 is rotatably and displaceably mounted on the base body 56 via the sliding bearing 76. The second bearing point 54 is formed by the sliding bearing 76. The base body 56 forms the second bearing point 54 of the toggle lever unit 38. The base body 56 has two spaced-apart connecting webs 72. The two connecting webs 72 are spaced apart from each other in a transverse direction of the base body 56. The two connecting webs 72 are spaced apart from each other at a distance greater than the width of the second toggle lever element 42. In an assembled state, the second toggle lever element 42 is positioned between the two connecting webs 72. The connecting webs 72 are arranged on the back 62 of the base plate 58.The connecting webs 72 are formed integrally with the base plate 58. The connecting webs 72 are each preferably thin-walled webs extending from the rear side 62 of the base plate 58. The connecting webs 72 are arranged at a second end of the base body 56, which, in an assembled state, faces away from the Bowden cable 30. The connecting webs 72 extend from the second end of the base body 56 preferably to a central region, and more preferably to the connecting element 64 of the base body 56. The sliding bearing 76 has two bearing pins 74 for supporting the second toggle lever element 42. Each connecting web 72 has a bearing pin 74 on its inner side facing the other connecting web 72 at the second end of the base body 56. The bearing journals 74 are arranged coaxially to each other.The bearing pins 74 are preferably formed integrally with the respective connecting web 72. The bearing pins 74 could also be designed as inserted pins. The bearing pins 74 form the second bearing point 54 for the second toggle lever element 42. The bearing pins 74 form the pivot axis for the second toggle lever element 42. The second bearing point 54 is arranged at a second end of the base body 56, which, in an assembled state, faces away from the Bowden cable 30.

[0057] The second toggle lever element 42 is slidably mounted on the base body 56 of the actuating module 36 via the sliding bearing 76 along a bearing axis. The second toggle lever element 42 is slidably and rotatably mounted on the base body 56 of the actuating module 36 via the sliding bearing 76 along the bearing axis. The second toggle lever element 42 has a base body 80. The base body 80 of the first toggle lever element 42 is preferably elongated. The base body 80 preferably has a U-shaped cross-section. The base body 80 of the first toggle lever element 42 preferably has two spaced-apart, parallel side walls and a top wall connecting the side walls. The sliding bearing 76 forms two elongated holes 78 in the second toggle lever element 42, via which the second toggle lever element 42 is slidably and rotatably mounted on the base body 56.The elongated holes 78 are each provided in the two parallel side walls of the base body 80 of the second toggle lever element 42. The elongated holes 78 in both side walls of the base body 80 of the second toggle lever element 42 are identical and arranged congruently in the transverse direction. It would also be conceivable, in principle, that the base body 80 is formed from a solid material and the sliding bearing 76 has only one elongated hole 78 extending transversely through the entire base body 80. The elongated holes 78 in the second toggle lever element 42 correspond to the bearing pins 74 on the connecting webs 72 of the base body 56 of the actuating module 36. In an assembled state, the bearing pins 74 of the base body 56 of the actuating module 36 engage in the corresponding elongated hole 78 of the second toggle lever element 42. The bearing pins 74 are axially displaceable in the elongated holes 78 in the assembled state.The bearing pins 74 are rotatably mounted in the elongated holes 78 in the assembled state. The second toggle lever element 42 is axially displaceable and rotatable along the elongated holes 78 and connected to the base body 56 of the actuating module 36 via the elongated holes 78 and the bearing pins 74. The elongated holes 78 define an adjustment range that can be provided by means of the toggle lever unit 38.

[0058] The actuating module 36 has a push button 82 for actuating the actuating module 36. The toggle lever unit 38, and thus the Bowden cable 30 connected to the actuating module 36, can be actuated by means of the push button 82. The push button 82 is designed to be actuated, in particular pressed, by an operator, especially a passenger. The push button 82 is designed to transmit an actuating force and movement applied by an operator to the toggle lever unit 38. The base plate 58 of the base body 56 has an opening 84. In an assembled state, the push button 82 extends through the opening 84 of the base plate 58. The opening 84 is designed to correspond to the push button 82. The opening 84 is slightly larger than the push button 82. In its unactuated state, the push button 82 extends beyond the front surface 60 of the base plate 58 of the base body 56.In its unactuated state, the push button 82 protrudes beyond the front surface 60 of the base plate 58 of the base body 56. The push button 82 is formed by the first toggle lever element 40. The push button 82 is formed by a projection of the first toggle lever element 40. The first toggle lever element 40 forms the push button 82 at its second end region, which faces the second toggle lever element 42. The push button 82 is located in the second end region where the recess is also located, which forms the joint element 44 of the first toggle lever element 40, designed as a sliding shell. The joint element 44, designed as a sliding shell, is preferably located on an inner surface of the push button 82. The push button 82 forms a pressure surface 86, which is designed to allow a REC 17460 WO.

[0059] The operator presses the push button 82 to actuate it. In an unactuated state, the pressure surface 86 of the push button 82 is inclined towards the front surface 60 of the base plate 58. In a fully actuated state, the pressure surface 86 of the push button 82 is preferably substantially flush with the front surface 60 of the base plate 58.

[0060] The toggle lever elements 40, 42 each define a toggle lever axis 100, 102 between their respective bearing points 52, 54, where the toggle lever elements 40, 42 are pivotally connected to the base body 56, and the joint element 48, where the two toggle lever elements 40, 42 are pivotally coupled to each other. The toggle lever axis 100, 102 of each toggle lever element 40, 42 forms an imaginary axis between the connection points of the respective toggle lever element 40, 42. A toggle lever angle can preferably be measured between the toggle lever axes 100, 102 of the two toggle lever elements 40, 42, at which the two toggle lever elements 40, 42 are positioned relative to each other.

[0061] In the unactuated state of the actuating module 36, the two toggle lever elements 40, 42 enclose a toggle lever angle of essentially 110 degrees. Preferably, the toggle lever angle enclosed by the two toggle lever elements 40, 42 of the toggle lever unit 38 in the unactuated state is between 100 degrees and 120 degrees, particularly preferably between 105 degrees and 115 degrees. In the unactuated state, the two toggle lever elements 40, 42 of the toggle lever unit 38 preferably enclose a toggle lever angle of 111 degrees. In a fully actuated state, the two toggle lever elements 40, 42 of the toggle lever unit 38 are preferably arranged coaxially to each other in certain areas, essentially coaxially. In a fully actuated state, the two toggle lever elements 40, 42 of the toggle lever unit 38 are preferably aligned at a toggle lever angle of 130 degrees to 140 degrees to each other.In a fully actuated state, the two toggle lever elements 40, 42 of the toggle lever unit 38 preferably enclose a toggle lever angle of 136 degrees.

[0062] The Bowden cable 30 is connected to the actuating module 36. The Bowden cable housing 32 of the Bowden cable 30 is connected to the base body 56 of the actuating module 36. The Bowden cable housing 32 of the Bowden cable 30 is preferably connected to the connecting element 64 of the base body 56. The connecting element 64 has a receiving area 88 in which the Bowden cable housing 32 is connected. The REC 17460 WO

[0063] The receiving area 88 forms a through-hole that extends through the connecting element 64. The through-hole of the receiving area 88 extends in the connecting element 64 from a first end of the base body 56, which faces the Bowden cable 30, to an opposite end of the connecting element 64, which faces the second toggle lever element 42. In an assembled state, the inner cable 34 of the Bowden cable 30 is guided through the through-hole of the receiving area 88 to the second toggle lever element 42. At the first end, which faces away from the second toggle lever element 42, the receiving area 88 has a retaining area in which the Bowden cable housing 32 is supported. In the retaining area, the receiving area 88 has a larger diameter than in the through-hole. In the retaining area, the receiving area 88 has a diameter that is adapted to the Bowden cable housing 32.In its assembled state, the Bowden cable housing 32 is supported in the holding area of ​​the receiving area 88.

[0064] The inner cable 34 of the Bowden cable 30 is connected to the second toggle lever element 42 of the toggle lever unit 38. The second toggle lever element 42 has a positive locking element 90 to which a corresponding positive locking element 92 of the inner cable 34 of the Bowden cable 30 can be positively engaged. The inner cable 34 of the Bowden cable 30 has the positive locking element 92 at its end. The positive locking element 92 of the inner cable 34 can, for example, be designed as a thickening. The positive locking element 90 of the second toggle lever element 42 is preferably arranged in the first end region of the second toggle lever element 42, where it is also mounted. In an assembled state, the Bowden cable 30 with its inner cable 34 is firmly connected to the second toggle lever element 42. By pivoting and axially displacing the second toggle lever element 42 during actuation, a tensile force is exerted on the inner cable 34 of the Bowden cable 30 and the Bowden cable 30 is thus actuated.

[0065] The actuating module 36 has a depth of 15 mm. This depth is measured from the support surface of the base plate 58 on the armrest 24, perpendicular to the front 60. The depth extends from the front 60 to the most distant point of the base body 56, measured perpendicularly. The toggle lever unit 38, in particular the two toggle lever elements 40, 42, do not extend beyond this depth in the fully actuated state. Furthermore, the toggle lever unit 38 does not extend beyond any part of the base body 56 of the actuating module 36 in any direction when actuated. This allows for a particularly low-profile actuating module 36.

[0066] To actuate the actuating module 36, an operator applies an actuating force to the push button 82. This actuating force moves the push button 82, and thus the first toggle lever element 40 of the toggle lever unit 38, which forms the push button 82, in the direction of the actuated position, in particular pivoting it. Due to the articulated coupling of the second toggle lever element 42 with the first toggle lever element 40, the second toggle lever element 42 is also moved. In doing so, the second toggle lever element 42 is both rotated and axially moved via the sliding bearing 76. The second toggle lever element 42 is pushed away from the first toggle lever element 40 along the adjustment axis by the movement of the first toggle lever element 40. This pulls the inner cable 34 of the Bowden cable 30, which is connected to the second toggle lever element 42, away from the Bowden cable sheath 32 connected to the base body 56. This causes the Bowden cable 30 to be actuated by means of the knee lever unit 38.The actuation path of the Bowden cable 30 is determined by the length of the elongated hole 78. The Bowden cable 30 actuates the mechanism 22, in particular moving it from a locked position to its released position. When the actuating force is released from the push button 82, the toggle lever unit 38, and thus the actuating module 36, returns to its unactuated position. The actuating module 36 is preferably free of a return spring. The return force is preferably transmitted to the toggle lever unit 38 via the mechanism 22 and the Bowden cable 30. However, it would also be conceivable for the actuating module 36 to have a return spring arranged between the base body 56 and one of the toggle lever elements 40, 42, which pushes or pulls it back to the unactuated position when the actuating force is released by an operator.

[0067] Figure 3 shows a sectional view of a further actuating module 94. This additional actuating module 94 is identical in design to the previously described actuating module 36 and is intended for actuating a mechanism of an adjacent aircraft seat. Due to the low height of the actuating modules 36 and 94, they can advantageously be integrated in the same longitudinal position within the armrest 24. The two actuating modules 36 and 94 can be arranged one behind the other in the same longitudinal position in the transverse direction of the armrest 24. Since the actuating modules 36 and 94 have the same depth in the actuated position as in the unactuated position, a collision with the other actuating module 36 and 94 cannot occur, even in the actuated position.In principle, it would also be conceivable that two actuation modules 36, 94 are arranged one above the other or next to each other on the same side of an aircraft seat component, in particular the armrest 24.

[0068] The aircraft seat 12 has a leg rest 96 arranged at a front end of the seat base 18. The leg rest 96 is pivotably mounted at a front end of the seat base 18. The leg rest 96 can be pivoted between a folded-down stowage position and a working position oriented substantially parallel to the seat base 18. In the working position, the leg rest 96 extends the seating area of ​​the seat base 18 forward. The aircraft seat assembly 10 has a mechanism 98 for adjusting the leg rest 96. The mechanism 98 is preferably formed by a Mechlock or a gas spring. The aircraft seat assembly 10 preferably has a further actuating module 94 arranged in the armrest 26. The further actuating module 94 is identical in design to the actuating module 36 described above.A Bowden cable of the actuating module 94 is connected to the mechanism 98 for actuating the leg rest 96.

[0069] Reference sign

[0070] 10 aircraft seat fittings

[0071] 12 aircraft seats

[0072] 14th row of seats

[0073] 16 Mounting unit

[0074] 18 Seat floor

[0075] 20 Backrest

[0076] 22 Mechanism

[0077] 24 Armrest

[0078] 26 Armrest

[0079] 28 Basic bodies

[0080] 30 Bowden cable

[0081] 32 Bowden cable housing

[0082] 34 Inner train

[0083] 36 Actuating module

[0084] 38 toggle lever unit

[0085] 40 toggle lever element

[0086] 42 Knee lever element

[0087] 44 Joint element

[0088] 46 Inside

[0089] 48 Joint element

[0090] 50 Survey

[0091] 52 bearing point

[0092] 54 bearing point

[0093] 56 basic shapes

[0094] 58 Base plate

[0095] 60 Front

[0096] 62 Back

[0097] 64 Connecting element

[0098] 66 Bearing pin web bearing mount connecting web bearing pin sliding bearing elongated hole base body push button opening pressure surface mounting area positive locking element positive locking element actuating module leg support mechanism toggle lever axis toggle lever axis

Claims

- 25 - REC 17460 WO September 8, 2025 Claims 1. Aircraft seat actuation device for actuating a mechanism (22), in particular a locking mechanism, with a Bowden cable (30) for actuating the mechanism (22), and with an actuating module (36) for actuating the Bowden cable (30), characterized in that the actuating module (36) for actuating the Bowden cable (30) has at least one toggle lever unit (38) comprising at least a first toggle lever element (40) and a second toggle lever element (42) which are pivotably mounted relative to each other.

2. Aircraft seat actuation device according to claim 1, characterized in that an inner cable (34) of the Bowden cable (30) is attached to the second knee lever element (42).

3. Aircraft seat actuation device according to claim 1 or 2, characterized in that the actuation module (36) has a base body (56) to which a Bowden cable sheath (32) of the Bowden cable (30) is attached.

4. Aircraft seat actuation device according to one of the preceding claims, characterized in that the first toggle lever element (40) and the second toggle lever element (42) are pivotally connected to each other via a joint element (48).

5. Aircraft seat actuation device according to claim 3, characterized in that the joint element (48) is formed by a sliding shell via which the two toggle lever elements (40, 42) are slidably coupled to each other.

6. Aircraft seat actuation device according to one of the preceding claims, characterized in that the actuation module (36) has a base body (56) on which the first toggle lever element (40) is rotatably mounted. REC 17460 WO 7. Aircraft seat actuation device according to one of the preceding claims, characterized in that the actuation module (36) has a base body (56) on which the second toggle lever element (42) is slidably mounted via a sliding bearing (76) along a bearing axis.

8. Aircraft seat actuation device according to claim 7, characterized in that the sliding bearing (76) forms an elongated hole (78) in the second toggle lever element (42) via which the second toggle lever element (42) is slidably and rotatably mounted on the base body (56).

9. Aircraft seat actuation device according to one of the preceding claims, characterized in that the actuation module (36) has a push button (82) for actuating the actuation module (36) which is formed by the first toggle lever element (40).

10. Aircraft seat actuation device according to one of the preceding claims, characterized in that the two toggle lever elements (40, 42) enclose a toggle lever angle between 95 degrees and 120 degrees in an unactuated state of the actuating module (36).

11. Aircraft seat actuation device according to one of the preceding claims, characterized in that the actuation module (36) has a depth extension of 15 mm, and the toggle lever unit (38) in an actuated state does not extend beyond a base body (56) of the actuation module (36) in a depth direction.

12. Aircraft seat comprising an actuator, in particular a gas spring and an aircraft seat actuation device according to one of the preceding claims, for actuating the actuator.

Images