Abstract: An attachment housing is for fastening to an exterior side of an aircraft. The attachment housing has a functional compartment. The functional compartment is divided in two, and has a ventilation compartment and a protective compartment. A surrounding wall is configured to separate the ventilation compartment from an environment. The surrounding wall has at least one ventilation opening for air exchange between the ventilation compartment and the environment. A dividing wall is arranged between the ventilation compartment and the protective compartment. The dividing wall has at least one passage opening for air exchange between the ventilation compartment and the protective compartment. The passage opening is configured to counter act a penetration of water, moisture, or particles into the protective compartment.

Abstract: An attachment housing is for fastening to an exterior side of an aircraft. The attachment housing has a functional compartment. The functional compartment is divided in two, and has a ventilation compartment and a protective compartment. A surrounding wall is configured to separate the ventilation compartment from an environment. The surrounding wall has at least one ventilation opening for air exchange between the ventilation compartment and the environment. A dividing wall is arranged between the ventilation compartment and the protective compartment. The dividing wall has at least one passage opening for air exchange between the ventilation compartment and the protective compartment. The passage opening is configured to counter act a penetration of water, moisture, or particles into the protective compartment.

Abstract: Aircraft seat having a first seat element and a second seat element, the second seat element being mounted so as to be adjustable relative to the first seat element, a spring element that moves the second seat element relative to the first seat element being provided, it being possible for the force acting on the second seat element by the spring element to be released by an actuating element such that the spring element is deactivated in a first switching position of the actuating element, and the spring element is activated in a second switching position of the actuating element, where a force limitation element is provided, by which the force acting on the second seat element by the spring element can be limited to a predetermined value such that intermediate states between the first and the second switching positions can also be set.

Abstract: The invention relates to a floor connection assembly for the mechanical connection of an aircraft seat to a floor structure of an aircraft, comprising at least three fastening points, wherein the floor connection assembly can be fastened on at least three fastening points with in each case one fastening element to the floor structure. The floor connection assembly comprises an adapter plate, wherein the mechanical connection between the adapter plate and the fastening elements is supported about at least one axis in a substantially torque-free manner.

Abstract: The present invention relates to an aircraft seat having a seat base, a seat unit, and a floor attachment assembly, where a first side of the seat base is configured to be fastened to the seat unit, and a second side of the seat base is configured to be fastened to the floor attachment assembly, and the floor attachment assembly is configured to be mechanically connected to a floor structure of an aircraft in order to fasten the aircraft seat to the aircraft, where the seat base is formed by at least one flexurally rigid shell component, where the shell component has a cavity for receiving at least one functional element, with the cavity being closed.

Abstract: The invention relates to an aircraft seat comprising an adjusting device, the aircraft seat comprising at least one adjustable seat element. The seat element has an adjustable state and a locked state, the seat element being adjustable by means of manual force application and/or force application by a spring element and/or force application due to the weight of parts of the aircraft seat only in the adjustable state. The adjusting device comprises at least one control element and at least one locking element, the locking element being movable by means of the control element between a locking position in which the seat element is locked, and a neutral position in which the seat element is adjustable. The control element is an electronic and/or electric switch, and the locking element can be moved between the locking position and the neutral position by means of an electrically operated actuator which can be actuated by means of signals from the switch.

Abstract: The invention relates to a floor attachment assembly for mechanically connecting two aircraft seats to a floor structure of an aircraft, which assembly comprises four attachment points. The floor attachment assembly can be attached to the floor structure by means of one attachment element in each case at the four attachment points. The floor attachment assembly comprises two adapter plates, the two adapter plates being interconnected by means of a connection element. The mechanical connection between at least one of the adapter plates and at least one of the attachment elements is movable along at least one axis. Furthermore, the invention relates to a corresponding aircraft seat.

Abstract: Aircraft seat having a first seat element and a second seat element, the second seat element being mounted so as to be adjustable relative to the first seat element, a spring element that moves the second seat element relative to the first seat element being provided, it being possible for the force acting on the second seat element by the spring element to be released by an actuating element such that the spring element is deactivated in a first switching position of the actuating element, and the spring element is activated in a second switching position of the actuating element, where a force limitation element is provided, by which the force acting on the second seat element by the spring element can be limited to a predetermined value such that intermediate states between the first and the second switching positions can also be set.

Abstract: The present invention relates to an aircraft seat having a seat base, a seat unit, and a floor attachment assembly, where a first side of the seat base is configured to be fastened to the seat unit, and a second side of the seat base is configured to be fastened to the floor attachment assembly, and the floor attachment assembly is configured to be mechanically connected to a floor structure of an aircraft in order to fasten the aircraft seat to the aircraft, where the seat base is formed by at least one flexurally rigid shell component, where the shell component has a cavity for receiving at least one functional element, with the cavity being closed.

Abstract: The invention relates to an aircraft seat having a seat assembly, wherein the seat assembly comprises a seat base and a seat surface assembly. The seat surface assembly is translationally movable in one direction relative to the seat base and can be blocked in at least one position. A force-limiting device is provided which, when activated, allows a relative movement between the seat base and the blocked seat surface assembly. Furthermore, the aircraft seat has a rocking ability about a transverse axis between the seat base and at least parts of the seat surface assembly, wherein the rocking ability of the seat surface assembly can be blocked by a blocking element. A force-limiting device is provided, which, when activated, allows a rocking movement of the blocked seat surface assembly.

Abstract: The invention relates to a floor attachment assembly for mechanically connecting two aircraft seats to a floor structure of an aircraft, which assembly comprises four attachment points. The floor attachment assembly can be attached to the floor structure by means of one attachment element in each case at the four attachment points. The floor attachment assembly comprises two adapter plates, the two adapter plates being interconnected by means of a connection element. The mechanical connection between at least one of the adapter plates and at least one of the attachment elements is movable along at least one axis. Furthermore, the invention relates to a corresponding aircraft seat.

Abstract: The invention relates to an aircraft seat comprising an adjusting device, the aircraft seat comprising at least one adjustable seat element. The seat element has an adjustable state and a locked state, the seat element being adjustable by means of manual force application and/or force application by a spring element and/or force application due to the weight of parts of the aircraft seat only in the adjustable state. The adjusting device comprises at least one control element and at least one locking element, the locking element being movable by means of the control element between a locking position in which the seat element is locked, and a neutral position in which the seat element is adjustable. The control element is an electronic and/or electric switch, and the locking element can be moved between the locking position and the neutral position by means of an electrically operated actuator which can be actuated by means of signals from the switch.

Abstract: Embodiments of the invention elate to an aircraft seat incorporating a holding device, such as a drink holder and a holding device, such as a drinker holder. In specific embodiments, the holding device allows an improved retention of receptacles having a stem, a bowl, and a foot. According to specific embodiments, the holding device incorporates a holding plate that has a recess for receiving the receptacle in the region of the bowl, at least one peripheral region of the recess extending as far as an edge of the holding plate, the holding plate being arranged in the use position such that the recess is freely accessible.

Abstract: The invention relates to a vehicle seat (1), which comprises at least one recess (12) and one movable carrier platform (3), wherein the carrier platform (3) can be moved out of a park position into a use position. The carrier platform (3) comprises a mechanical connector (4), wherein the carrier platform (3) is held in the recess (12) when in the park position, wherein, in the use position, on the carrier platform (3), a carrier module (5) comprising a mechanical connection device (6) can be connected to the connector (4) of the carrier platform (3).

Abstract: The invention relates to an aircraft seat having a seat assembly, wherein the seat assembly comprises a seat base and a seat surface assembly. The seat surface assembly is translationally movable in one direction relative to the seat base and can be blocked in at least one position. A force-limiting device is provided which, when activated, allows a relative movement between the seat base and the blocked seat surface assembly. Furthermore, the aircraft seat has a rocking ability about a transverse axis between the seat base and at least parts of the seat surface assembly, wherein the rocking ability of the seat surface assembly can be blocked by a blocking element. A force-limiting device is provided, which, when activated, allows a rocking movement of the blocked seat surface assembly.

Abstract: The invention relates to a floor connection assembly for the mechanical connection of an aircraft seat to a floor structure of an aircraft, comprising at least three fastening points, wherein the floor connection assembly can be fastened on at least three fastening points with in each case one fastening element to the floor structure. The floor connection assembly comprises an adapter plate, wherein the mechanical connection between the adapter plate and the fastening elements is supported about at least one axis in a substantially torque-free manner.

Abstract: The invention relates to a backrest for a vehicle seat, wherein the backrest includes a plurality of backrest modules. The backrest modules comprise a central portion, and at least one backrest module is mechanically linked to one or two further backrest modules of similar type at the central portion.

Abstract: The structural element of an aircraft fuselage, with stringers running in the longitudinal direction of the aircraft fuselage and ribs running transversely to the stringers in the circumferential direction of the fuselage. According to the invention, at least one of the stringers running in the longitudinal direction of the aircraft fuselage is designed as a fastening rail for elements to be installed in the aircraft fuselage.

Abstract: The invention relates to a method for fastening an element of airplane interior equipment to a supporting structure in an airplane, comprising the steps of connecting the element of the airplane interior equipment to a first fixing device by using a first locking device, pivoting the element of the airplane interior equipment relative to the supporting structure, and connecting the element of the airplane interior equipment to a second fixing device by using a second locking device. Thus the element of the airplane interior equipment is fastened relative to the supporting structure.

Abstract: The invention relates to a backrest for a vehicle seat, wherein the backrest includes a plurality of backrest modules. The backrest modules comprise a central portion, and at least one backrest module is mechanically linked to one or two further backrest modules of similar type at the central portion.