DE102019134391A1 - Aircraft module fairing device - Google Patents

Abstract

The invention is based on an aircraft module cladding device (10a; 10b; 10c; 10d; 10e) with at least one aircraft module (12a; 12b; 12c), in particular aircraft seat module, with at least one panel (18a; 18d; 18e), which in an assembled state it is provided to at least partially cover the at least one aircraft module (12a; 12b; 12c), and with at least one connection unit (28a; 30a; 28b; 28c; 28d; 28e) which is provided to connect the at least one panel (18a; 18d; 18e) to be connected to the at least one aircraft module (12a; 12b; 12c), the at least one connection unit (28a, 30a; 28b; 28c; 28d; 28e) comprising at least one connection element (32a; 32b; 32d; 32e) , which is arranged on the at least one panel (18a; 18d; 18e) and comprises at least one connecting element (36a; 36b; 36c) which is provided for the purpose of connecting the at least one connecting element (32a; 32b; 32d; 32e) to the to attach at least one aircraft module (12a; 12b; 12c). It is vo It is suggested that the at least one connection unit (28a; 30a; 28b; 28c; 28d; 28e) comprises at least one compensating unit (48a; 48b; 48c; 48d; 48e) which is provided for a compensating movement of the at least one connecting element (36a; 36b; 36c) and / or the at least one connecting element (32a; 32b; 32d; 32e) in relation to the at least one aircraft module (12a; 12b; 12c) and / or in relation to the at least one panel (18a; 18d; 18e) in a defined compensation area (34a; 34b; 34c; 34d; 34e).

Description

The invention relates to an aircraft module cladding device according to the preamble of claim 1.

It is already an aircraft module cladding device with at least one aircraft module, in particular aircraft seat module, with at least one panel, which in an assembled state is provided to at least partially cover the at least one aircraft module, and with at least one connection unit, which is provided for the at least one panel to be connected to the at least one aircraft module, wherein the at least one connection unit comprises at least one connection element which is arranged on the at least one panel and comprises at least one connection element which is provided to fasten the at least one connection element to the at least one aircraft module, has been proposed.

The object of the invention is in particular to provide a device of the generic type with improved properties with regard to assembly and interchangeability. The object is achieved according to the invention by the features of claim 1, while advantageous configurations and developments of the invention can be found in the subclaims.

Advantages of the invention

The invention is based on an aircraft module cladding device with at least one aircraft module, in particular aircraft seat module, with at least one panel, which in an assembled state is provided to at least partially cover the at least one aircraft module, and with at least one connection unit, which is provided for the at least to connect a panel to the at least one aircraft module, wherein the at least one connection unit comprises at least one connection element, which is arranged on the at least one panel, and comprises at least one connection element, which is provided to connect the at least one connection element to the at least one aircraft module attach.

It is proposed that the at least one connection unit comprises at least one compensation unit, which is provided to allow a compensation movement of the at least one connection element and / or the at least one connection element with respect to the at least one aircraft module and / or with respect to the at least one panel in a defined compensation area . As a result of the configuration according to the invention, the at least one aircraft module can be covered easily and quickly with the at least one panel, whereby an advantageously simple and rapid production of the aircraft module cladding device according to the invention is made possible. This allows an advantageously simple assembly and / or disassembly of the at least one panel on the at least one aircraft module. The at least one panel can thereby advantageously be replaced quickly and easily. The at least one connection unit is advantageously adapted automatically during assembly by means of the at least one compensation unit, so that assembly can take place advantageously quickly and reliably. Furthermore, a distortion of the panel can advantageously be avoided by the configuration according to the invention. In this way, an advantageously optimal appearance, in particular a wrinkle-free appearance, of the at least one panel can be ensured. Furthermore, short-term damage to the at least one panel, in particular through overstretching, and / or long-term damage to the at least one panel, in particular through creeping with delay, can advantageously be avoided. An “aircraft module” is to be understood as meaning, in particular, a component in an aircraft cabin of the aircraft, preferably permanently connected to an aircraft. The at least one aircraft module is particularly preferably designed as an aircraft seat module. The aircraft seat module is preferably part of an aircraft seat device which comprises at least one passenger seat. The aircraft seat module is preferably designed as a storage console, as a housing, in particular a shell, as a handrail, as a bumper strip and / or as an end strip. In principle, the aircraft seat module can also be designed as another part of the at least one passenger seat that is to be covered with at least one panel. In principle, the at least one aircraft module can also be designed as another part in the aircraft cabin to be covered with at least one panel, for example as a cabin monument, as a toilet module, as a kitchen module, as a cabin ceiling unit, in particular a luggage compartment and / or a service module, and / or as a cabin wall unit. A “panel” is to be understood in particular as a thin-walled component which is provided for cladding an object. “Provided” is to be understood in particular as specifically designed and / or equipped. The fact that an object is provided for a specific function should be understood in particular to mean that the object fulfills and / or executes this specific function in at least one application and / or operating state. The at least one panel is preferably designed as a flat component. In principle, it is also conceivable that the at least one panel as a narrow, thin-walled bar or is designed as a thin-walled profile element. The at least one panel is preferably designed as a cover element. The at least one panel is provided in particular to cover the at least one aircraft module, in particular opposite an aircraft cabin. In this way, an advantageously appealing look can be created. In principle, the at least one panel can also be provided, in particular, to protect the at least one aircraft module to be covered from damage, in particular due to environmental influences. “Covering” is to be understood in particular to mean that the at least one aircraft module in the assembled state is invisible to a person in the aircraft cabin. The at least one panel preferably covers the at least one aircraft module, in particular at least partially, preferably largely, and particularly preferably completely. A “connecting unit” is to be understood in particular as a unit which is provided to couple and / or connect the at least one panel and the at least one aircraft module to one another. The at least one connection unit is preferably provided to connect the at least one panel to the at least one aircraft module via the at least one connection element and the at least one connection element. In the assembled state, the at least one connection element is preferably arranged on a side facing the at least one aircraft module, in particular an underside and / or a rear side, of the at least one panel. The at least one connection element is preferably connected to the at least one panel in a materially bonded manner, in particular glued, and / or positively connected. In principle, the at least one connection element can also be arranged on the at least one aircraft module. The at least one connection element is preferably designed in the shape of a pin. The at least one connection element particularly preferably has an at least substantially T-shaped basic shape in at least one sectional plane. “At least essentially” should be understood to mean, in particular, that a deviation from a predefined value is in particular less than 25%, preferably less than 10% and particularly preferably less than 5% of the predefined value. The at least one connection unit preferably has a connection direction. The connection direction is preferably perpendicular to a surface of the at least one panel facing the at least one aircraft module. The at least one panel preferably has at least one visible side. The at least one visible side preferably forms a surface of the at least one panel facing away from the at least one aircraft module. Preferably, one of the side facing the at least one aircraft module, in particular the underside and / or the rear side, of the at least one panel opposite, in particular an upper side and / or front side, of the at least one panel is designed as the at least one visible side. A “visible side” is to be understood as meaning, in particular, a side of the at least one panel which faces away from the at least one aircraft module in the assembled state and is visible from a person in the aircraft cabin. The at least one connection element is provided in particular to establish a fixed connection to the at least one connection element by means of a form fit and / or force fit, in particular at least up to a defined dismantling force. The at least one connection element is preferably provided to connect the at least one connection element to the at least one aircraft module in a captive manner. The term “captively connected” is to be understood in particular to mean that the at least one panel is attached to the at least one aircraft module in such a way that the at least one panel remains permanently connected to the at least one aircraft module under normal operating conditions, the at least one panel in particular by applying a Disassembly force can be separated from the at least one aircraft module. The frictional connection is preferably designed as a frictional connection. The form fit is preferably achieved by means of at least one latching element. The at least one connecting element is preferably designed as a clip, which is provided in particular to fix the at least one connecting element. The at least one connecting element is preferably designed to correspond to the at least one connecting element. The at least one connection element is preferably designed to correspond to the at least one connection element. The at least one connection element is preferably provided during assembly to be plugged into the at least one connection element. The at least one connecting element is preferably provided in the assembled state to fix the at least one connecting element. The at least one compensation unit is preferably provided to compensate for manufacturing tolerances for a position of the at least one connection element on the at least one panel and / or for a position of the at least one connection element on the at least one panel. A “compensating movement” should be understood to mean, in particular, a movement of two components that are movably mounted relative to one another, the movement being provided in particular to offset, in particular to displace, the at least one connecting element relative to the at least one aircraft module and / or relative to the at least one panel. That is particularly preferred at least one compensation unit is provided to align the at least one connecting element, in particular precisely, to the at least one connecting element. The at least one connecting element and the at least one connecting element are preferably supported in relation to one another in the assembled state at least essentially free of force and / or torque. Under “at least essentially free of force and / or torque” is to be understood in particular that the at least one connecting element absorbs at most a weight force of the at least one panel and the at least one connecting element, but in particular no forces and / or torques caused by a possible offset are caused between the at least one connecting element and the at least one connecting element. In this way, a static overdetermination, which in particular can cause tension in the at least one panel, can advantageously be avoided. The compensating movement is preferably provided to relieve a connection between the at least one connection element and the at least one panel. As a result, a possible tension can advantageously be removed from the at least one connection element. Furthermore, the formation of bumps and / or folds on the at least one panel can thereby advantageously be avoided. A “defined compensation area” is to be understood in particular as an area which allows a compensation movement on at least one limited path, in particular one axis, on at least one limited area and / or in at least one limited angular range.

Furthermore, it is proposed that the at least one connecting element and / or the at least one connecting element is mounted in the defined compensation area so as to be movable in translation and / or in rotation at least essentially in one plane. This configuration enables a two-dimensional compensating movement to be made possible in a particularly advantageous manner. As a result, the at least one panel can advantageously be installed in a simple manner. The at least one connecting element and / or the at least one connecting element is particularly preferably designed to be displaceable in the plane. In principle, it would also be conceivable for the at least one connecting element and / or the at least one connecting element to be movably mounted in three dimensions, in particular by a resilient mounting. A compensation perpendicular to the plane can thereby advantageously be achieved. The compensation movement within the plane preferably comprises at least two degrees of freedom.

It is further proposed that the at least one connecting element and / or the at least one connecting element are / is mounted so as to be translationally movable in at least one direction with respect to the at least one aircraft module. With this configuration, manufacturing tolerances for a position of the at least one connection element on the at least one panel and / or for a position of the at least one connection element on the at least one panel can advantageously be compensated for. Furthermore, manufacturing tolerances for a position of the at least one connection element and / or for a position of the at least one connection element relative to the at least one aircraft module can advantageously be compensated for. The at least one direction is preferably arranged in the plane. The at least one connecting element and / or the at least one connecting element are preferably mounted, in particular jointly, movably in the plane relative to the at least one aircraft module and / or to the at least one panel. The at least one connecting element and / or the at least one connecting element preferably has a neutral position. The at least one connecting element and / or the at least one connecting element is preferably arranged centrally in the at least one compensation unit in the neutral position. The at least one connecting element and / or the at least one connecting element is preferably displaceable and / or pivotable in the at least one direction and / or in a direction opposite to the at least one direction, starting from the neutral position. The at least one connection element and / or the at least one connection element is preferably mounted such that it can be displaced in the at least one direction in a translatory manner over an extension of at most 6 mm with respect to the at least one aircraft module. The at least one connecting element and / or the at least one connecting element are preferably mounted such that they can be displaced in the at least one direction starting from the neutral position by a maximum of 3 mm with respect to the at least one aircraft module.

In addition, it is proposed that the at least one connecting element and / or the at least one connecting element are / is pivotably mounted relative to the at least one aircraft module. With this configuration, manufacturing tolerances for a position of the at least one connection element on the at least one panel and / or for a position of the at least one connection element on the at least one panel can be compensated particularly advantageously. Furthermore, manufacturing tolerances for a position of the at least one connection element and / or for a position of the at least one connection element relative to the at least one aircraft module can be compensated for in a particularly advantageous manner. The at least one connecting element and / or the at least is preferably a connection element, in particular in the plane, rotatably mounted pivotably over an angular range of at most 30 degrees with respect to the at least one aircraft module. The at least one connecting element and / or the at least one connecting element is preferably mounted so as to be pivotable, in particular in the plane, starting from the neutral position by a maximum of 15 degrees relative to the at least one aircraft module.

It is further proposed that the at least one compensation unit has at least one fastening element which is provided for a non-positive, positive and / or material connection with the at least one aircraft module or the at least one panel. As a result of this configuration, the compensation unit can advantageously be easily mounted on the at least one aircraft module or on the at least one panel. The at least one fastening element is preferably inserted in a recess of the at least one aircraft module or attached to the surface of the at least one panel facing the at least one aircraft module. The at least one fastening element is provided in particular to hold the at least one connection element or the at least one connection element within the defined compensation area.

It is further proposed that the at least one fastening element, in the assembled state, is arranged at least partially flush with an outer surface of the at least one aircraft module. With this configuration, the at least one fastening element can advantageously be integrated into an outer surface of the at least one aircraft module. This achieves an advantageously compact design. Furthermore, this configuration can provide an advantageously flat surface on the at least one aircraft module, whereby a risk of damage to the at least one panel by the at least one fastening element is advantageously avoided. As a result, the at least one panel can be installed quickly and safely. The at least one fastening element is preferably arranged at least partially offset from the outer surface of the at least one aircraft module. The at least one fastening element preferably at least partially forms a depression opposite the outer surface of the at least one aircraft module. As a result, the at least one connection element can advantageously be arranged close to the at least one fastening element, as a result of which the at least one panel can advantageously be arranged close to the at least one aircraft module.

It is also proposed that the at least one compensating unit has at least one movably mounted compensating element which is provided to carry out the compensating movement. With this configuration, a compensating movement of the at least one connecting element can be implemented in a particularly advantageous manner. The at least one compensation element is preferably provided to be displaced and / or deformed in the plane, in particular within the defined compensation area. The at least one compensating element is preferably movably supported in the plane. The at least one compensating element is particularly preferably provided to support the at least one connecting element in a moveable manner.

Furthermore, it is proposed that the at least one compensating element is coupled to the at least one fastening element in the assembled state. With this configuration, the at least one compensating element can be stored particularly advantageously. The at least one compensating element is preferably mounted in a floating manner with respect to the at least one fastening element. “Floating” is to be understood as meaning that the at least one compensating element is at least essentially movably mounted in one plane, in particular with at least two degrees of freedom, the at least one compensating element in particular translationally and / or rotationally in this plane, in particular within of the defined compensation area, is movable. The at least one compensating element is particularly preferably arranged directly on the at least one fastening element. The at least one compensating element is preferably mounted so as to be movable with respect to the at least one fastening element. The at least one compensating element is preferably at least partially enclosed in a form-fitting manner by the at least one fastening element, the at least one compensating element being movably supported with respect to the at least one fastening element.

It is further proposed that the at least one compensating element is designed as a plate which has at least one recess for receiving the at least one connecting element. As a result of this configuration, the at least one connecting element can advantageously be easily connected to the at least one compensating element. The at least one compensating element is preferably designed as a punched-out plate. The at least one compensating element is preferably formed from aluminum. The at least one compensating element particularly preferably has the at least one recess which is provided for the at least one Record connecting element. The at least one connecting element is preferably coupled to the at least one compensating element. The at least one connecting element is preferably latched in the at least one compensating element.

It is also proposed that the at least one compensating element is designed as a spring element. With this configuration, the at least one connecting element can advantageously be variably positioned. Furthermore, a defined neutral position of the at least one connecting element can advantageously be assumed by this configuration, whereby the at least one panel can advantageously be installed in a simple manner. The at least one compensating element is preferably provided to allow a resilient movement of the at least one connecting element in the plane. The at least one compensating element is preferably firmly connected to the at least one connecting element and / or the at least one fastening element. The at least one compensating element is preferably designed in a meandering manner, at least in sections.

It is further proposed that the at least one compensating element is formed in one piece with the at least one fastening element and in one piece with the at least one connecting element. This configuration enables the at least one compensating unit to be mounted in an advantageously simple and rapid manner. Furthermore, the at least one compensation unit can advantageously be produced simply by means of this configuration. The at least one compensating element is preferably formed from a plastic. The at least one fastening element, the at least one compensating element and the at least one connecting element are preferably formed from the same material. The at least one fastening element, the at least one compensating element and the at least one connecting element are preferably manufactured together in one manufacturing step, in particular injection molded.

It is further proposed that the at least one connection element is movably supported in relation to the at least one panel in the assembled state. As a result of this configuration, the at least one connecting element can advantageously perform the compensating movement automatically, in particular without an additional compensating element. Furthermore, by means of this configuration, an existing aircraft module cladding device from the prior art can be retrofitted with the possibility of a compensating movement by means of a panel according to the invention, without the at least one aircraft module having to be structurally changed. The at least one fastening element is preferably firmly connected to the at least one panel. The at least one fastening element is preferably connected to the at least one panel in a materially bonded manner, in particular glued, and / or positively connected. The at least one fastening element and the at least one panel particularly preferably form an intermediate space in which the at least one connection element is at least partially arranged. The at least one connection element is preferably mounted in a form-fitting manner by means of the intermediate space. The at least one connection element is preferably mounted in a floating manner, in particular in the intermediate space.

It is also proposed that the at least one fastening element is provided to exert a clamping force on the at least one compensation element and / or on the at least one connection element. With this configuration, the development of noise due to vibrations during operation of the aircraft based on the at least one compensation unit and / or the at least one connection unit can advantageously be avoided. Furthermore, the defined neutral position of the at least one connecting element or of the at least one connecting element can advantageously be assumed by this configuration, whereby the at least one panel can advantageously be installed in a simple manner. The at least one compensating element is preferably at least partially positively enclosed by the at least one fastening element, the at least one compensating element being movably supported with respect to the at least one fastening element. The at least one fastening element preferably has at least one fastening extension which is provided to at least partially enclose the at least one compensating element and / or the at least one connection element in a form-fitting manner. The at least one fastening extension is particularly preferably designed in the form of a plate. The at least one fastening extension is preferably provided to clamp the at least one compensating element or the at least one connecting element by means of the clamping force. The at least one fastening extension is preferably pretensioned in the direction of the side of the at least one panel facing the at least one aircraft module. As a result, the at least one compensating element and / or the at least one connecting element can advantageously be easily fixed in a position opposite the at least one fastening element. In principle, the at least one fastening element, in particular on the at least one fastening extension, can also have a coating which is provided for a compensating movement of the at least one To inhibit compensating element and / or the at least one connecting element.

The aircraft module cladding device according to the invention should not be restricted to the application and embodiment described above. In particular, the aircraft module cladding device according to the invention can have a number of individual elements, components and units that differs from a number of individual elements, components and units mentioned herein in order to fulfill a mode of operation described herein.

Figure list

Further advantages emerge from the following description of the drawings. Five exemplary embodiments of the invention are shown in the drawing. The drawing, the description and the claims contain numerous features in combination. The person skilled in the art will expediently also consider the features individually and combine them into meaningful further combinations.

• 1 eine Flugzeugsitzvorrichtung mit einer erfindungsgemäßen Flugzeugmodulverkleidungsvorrichtung in einer schematischen Darstellung in einem ersten Ausführungsbeispiel,
• 2 ein Paneel und Anbindungselemente der erfindungsgemäßen Flugzeugmodulverkleidungsvorrichtung in einer schematischen Darstellung in dem ersten Ausführungsbeispiel,
• 3 eine Verbindungseinheit der erfindungsgemäßen Flugzeugmodulverkleidungsvorrichtung in einer schematischen Explosionsdarstellung in dem ersten Ausführungsbeispiel,
• 4 die Verbindungseinheit der erfindungsgemäßen Flugzeugmodulverkleidungsvorrichtung in einem montierten Zustand in einer schematischen Darstellung in dem ersten Ausführungsbeispiel,
• 5 ein Anbindungselement einer erfindungsgemäßen Flugzeugmodulverkleidungsvorrichtung in einer perspektivischen schematischen Darstellung in einem zweiten Ausführungsbeispiel,
• 6 das Anbindungselement der erfindungsgemäßen Flugzeugmodulverkleidungsvorrichtung in einer perspektivischen schematischen Darstellung in dem zweiten Ausführungsbeispiel,
• 7 eine Verbindungseinheit der erfindungsgemäßen Flugzeugmodulverkleidungsvorrichtung in einer perspektivischen schematischen Darstellung in dem zweiten Ausführungsbeispiel,
• 8 die erfindungsgemäße Flugzeugmodulverkleidungsvorrichtung in einer perspektivischen schematischen Schnittdarstellung in dem zweiten Ausführungsbeispiel,
• 9 eine Verbindungseinheit einer erfindungsgemäßen Flugzeugmodulverkleidungsvorrichtung in einer perspektivischen schematischen Darstellung in einem dritten Ausführungsbeispiel,
• 10 die erfindungsgemäße Flugzeugmodulverkleidungsvorrichtung in einer perspektivischen schematischen Darstellung in dem dritten Ausführungsbeispiel,
• 11 die erfindungsgemäße Flugzeugmodulverkleidungsvorrichtung in einer perspektivischen schematischen Darstellung in dem dritten Ausführungsbeispiel,
• 12 eine erfindungsgemäße Flugzeugmodulverkleidungsvorrichtung in einer perspektivischen schematischen Darstellung in einem vierten Ausführungsbeispiel und
• 13 eine erfindungsgemäße Flugzeugmodulverkleidungsvorrichtung in einer perspektivischen schematischen Darstellung in einem fünften Ausführungsbeispiel.

Show it:

• 1 an aircraft seat device with an aircraft module cladding device according to the invention in a schematic representation in a first embodiment,
• 2 a panel and connection elements of the aircraft module cladding device according to the invention in a schematic representation in the first embodiment,
• 3 a connection unit of the aircraft module cladding device according to the invention in a schematic exploded view in the first embodiment,
• 4th the connection unit of the aircraft module cladding device according to the invention in an assembled state in a schematic representation in the first embodiment,
• 5 a connection element of an aircraft module cladding device according to the invention in a perspective schematic representation in a second exemplary embodiment,
• 6th the connection element of the aircraft module cladding device according to the invention in a perspective schematic representation in the second embodiment,
• 7th a connection unit of the aircraft module cladding device according to the invention in a perspective schematic representation in the second embodiment,
• 8th the aircraft module cladding device according to the invention in a perspective schematic sectional illustration in the second exemplary embodiment,
• 9 a connection unit of an aircraft module cladding device according to the invention in a perspective schematic representation in a third exemplary embodiment,
• 10 the aircraft module cladding device according to the invention in a perspective schematic representation in the third embodiment,
• 11 the aircraft module cladding device according to the invention in a perspective schematic representation in the third embodiment,
• 12th an aircraft module cladding device according to the invention in a perspective schematic representation in a fourth embodiment and
• 13th an aircraft module cladding device according to the invention in a perspective schematic representation in a fifth exemplary embodiment.

Description of the exemplary embodiments

In the 1 to 4th an aircraft module cladding device 10a is shown in a first exemplary embodiment. The first exemplary embodiment is intended in particular for composite structures, such as sandwich units with a honeycomb core or a foam core. The aircraft module cladding device 10a comprises an aircraft module 12a. The aircraft module 12a is designed as an aircraft seat module. The aircraft module 12a is part of an aircraft seat device 14a. The aircraft seat device 14a comprises a passenger seat 16a. The aircraft module cladding device 10a is part of the aircraft seat device 14a in the present case. In the present case, the aircraft module 12a is designed as a storage console. Alternatively, the aircraft module 12a could also be designed as an enclosure, in particular a shell, as a handrail, as a bumper strip and / or as an end strip. The aircraft seat device 14a is provided to be raised in an aircraft cabin (not shown in detail) of an aircraft.

The aircraft module cladding device 10a comprises a panel 18a which, in an assembled state, is provided to at least partially cover the aircraft module 12a. In the 1 the panel 18a is shown with an imaginary cutout for better illustration. The panel 18a is designed as a thin-walled component. The Panel 18a is designed as a flat component. The panel 18a is provided to cover the aircraft module 12a. The panel 18a is designed as a cover element. The panel 18a is provided to cover the aircraft module 12a with respect to the aircraft cabin. In the assembled state, the aircraft module 12a is partially invisible to a person in the aircraft cabin. In the present case, the panel 18a partially covers the aircraft module 12a in the assembled state.

The panel 18a has a visible side 20a. The visible side 20a forms a surface 22a of the panel 18a facing away from the aircraft module 12a. The panel 18a has a side 24a facing the aircraft module 12a. A side of the panel 18a opposite the side 24a of the panel 18a facing the aircraft module 12a is designed as the visible side 20a. In the present case, the visible side 20a is designed as an upper side or front side. The side of the panel 18a opposite the side 24a of the panel 18a facing the aircraft module 12a is designed as a side of the panel 18a facing away from the aircraft module 12a. The side 24a of the panel 18a facing the aircraft module 12a is designed in the present case as an underside or rear side of the panel 18a.

The aircraft module cladding device 10a comprises at least one further panel 26a which, in an assembled state, is also provided to at least partially cover the aircraft module 12a. In principle, the aircraft module 12a can also have only a single panel. The further panel 26a is designed essentially identically to the panel 18a in terms of its mode of operation. In the 1 the further panel 26a is shown with a further imaginary cutout for better illustration.

The aircraft module cladding device 10a comprises a connection unit 28a, which is provided to connect the panel 18a to the aircraft module 12a ( 3 and 4th ). The aircraft module cladding device 10a comprises further connection units 30a, which are provided to connect the panel 18a to the aircraft module 12a ( 1 ). The further connection units 30a are designed identically to the connection unit 28a. Alternatively, the further connection units 30a could also be designed at least partially differently from the connection unit 28a. In principle, it would also be conceivable that the aircraft module cladding device 10a comprises only a single connection unit 28a, which is provided to connect the panel 18a to the aircraft module 12a. The connection unit 28a is provided to couple the panel 18a and the aircraft module 12a to one another. The connection unit 28a is provided to connect the panel 18a and the aircraft module 12a to one another, in particular in a loss-proof manner.

The connection unit 28a comprises a connection element 32a ( 2 ). The connection element 32a is arranged on the panel 18a. The connection element 32a is designed in the shape of a pin. The connection element 32a has an at least substantially T-shaped basic shape in at least one sectional plane. In the assembled state, the connection element 32a is arranged on the side 24a of the panel 18a facing the aircraft module 12a. The connection element 32a is materially connected to the panel 18a. The connection element 32a is glued to the panel 18a ( 2 ). In principle, the connection element 32a can also be arranged on the aircraft module 12a. The connection element 32a is mounted in a defined compensation area 34a so that it can be moved translationally and rotationally at least essentially in one plane. The connection element 32a is designed to be displaceable in the plane. The connection element 32a is mounted such that it can move translationally in at least one direction with respect to the aircraft module 12a. In the assembled state, the connection element 32a is mounted such that it can be displaced in translation in the at least one direction over an extension of at most 6 mm with respect to the aircraft module 12a. The connection element 32a is mounted pivotably with respect to the aircraft module 12a. The connection element 32a is rotatably mounted in the plane over an angular range of at most 30 degrees relative to the aircraft module 12a.

The connection unit 28a comprises a connection element 36a ( 3 ). The connection element 36a is provided to fasten the connection element 32a to the aircraft module 12a. The connection element 36a is provided to connect the connection element 32a to the aircraft module 12a in a captive manner. The connection unit 28a is provided to connect the panel 18a to the aircraft module 12a via the connection element 32a and the connection element 36a. The connecting element 36a is designed as a bracket. The clamp is provided to fix the connection element 32a. The connecting element 36a is formed from a bent sheet metal. The connecting element 36a has an essentially omega-shaped basic shape in at least one sectional plane. The connecting element 36a forms two opposing clamping extensions 40a on an inner side 38a of the connecting element 36a. The clamping extensions 40a are bent out to one another from the connecting element 36a, which is designed as a sheet metal. The clamping extensions 40a are provided to to hold the connecting element 32a non-positively and / or positively. The connection unit 28a has a connection direction 42a. The connection direction 42a is oriented perpendicular to a surface 44a of the panel 18a facing the aircraft module 12a. The clamping extensions 40a each have at least one mandrel 46a, which is provided to hold the connecting element 32a in a direction opposite to the connecting direction 42a in a form-fitting manner in the connecting element 36a. The at least one mandrel 46a is provided to intervene plastically in the connection element 32a when the connection element 32a is loaded in the direction opposite to the connection direction 42a. The clamping extensions 40a are provided to clamp the connecting element 32a.

In the assembled state, the connecting element 36a is provided to fix the connecting element 32a. The connecting element 36a is mounted in the defined compensation region 34a such that it can be moved translationally and rotationally at least essentially in the plane. The connecting element 36a is designed to be displaceable in the plane. The connecting element 36a is mounted such that it can move translationally in at least one direction with respect to the at least one aircraft module 12a. The connecting element 36a has a neutral position to the compensation unit 48a ( 4th ). In the neutral position, the connecting element 36a is arranged centrally in the compensation unit 48a. Starting from the neutral position, the connecting element 28a can be displaced in the at least one direction and in a direction opposite to the at least one direction. The connecting element 36a is mounted in a translatory manner in the at least one direction over an extension of at most 6 mm with respect to the aircraft module 12a. The connecting element 36a is mounted such that it can be displaced in the at least one direction, starting from the neutral position, by a maximum of 3 mm relative to the aircraft module 12a. The connecting element 36a is mounted so as to be translationally displaceable along an axis 62a. The axis 62a is arranged in the plane. The connecting element 36a is mounted so as to be translationally displaceable along a further axis 85a. The further axis 85a is arranged in the plane. The further axis 85a is arranged perpendicular to the axis 62a in at least one operating state, in particular in the neutral position. In principle, it would also be conceivable for the connecting element 36a and / or the connecting element 32a to be movably mounted in three dimensions, in particular by a resilient mounting. The at least one direction is arranged in the plane. The connecting element 36a is mounted pivotably with respect to the aircraft module 12a. The connecting element 36a is rotatably mounted in the plane over an angular range of at most 30 degrees relative to the aircraft module 12a. A pivot axis, not shown in more detail, about which the connecting element 36a can pivot, is oriented perpendicular to the plane. The pivot axis, not shown in more detail, is formed perpendicular to the axis 62a and to the further axis 85a. The connecting element 36a is mounted in the plane, starting from the neutral position, so as to be pivotable at most by 15 degrees relative to the aircraft module 12a. In the assembled state, the connecting element 36a and the connecting element 32a are jointly movably supported in the plane relative to the aircraft module 12a.

The connection element 32a is intended to be inserted into the connection element 36a during assembly. The connection element 32a is provided to establish a connection with the connection element 36a that is fixed at least up to a defined dismantling force by means of a form fit and a force fit. The frictional connection is designed as a frictional connection. The frictional engagement is achieved by clamping the connecting element 32a by means of the connecting element 36a. In the assembled state, the connecting element 36a and the connecting element 32a are at least essentially free of force and / or torque relative to one another. The compensating movement is provided to relieve a connection between the connection element 32a and the panel 18a.

The connection unit 28a comprises a compensation unit 48a ( 3 and 4th ). The compensation unit 48a is provided to allow a compensation movement of the connecting element 36a with respect to the aircraft module 12a and with respect to the panel 18a in the defined compensation area 34a. The compensation unit 48a is provided to allow a compensation movement of the connection element 32a with respect to the aircraft module 12a in the defined compensation area 34a. The compensation unit 48a is provided to compensate for manufacturing tolerances for a position of the connecting element 32a on the panel 18a. The compensation movement is provided to move the connecting element 36a with respect to the aircraft module 12a and / or with respect to the panel 18a. The compensation unit 48a is provided to align the connecting element 36a exactly with the connecting element 32a.

The compensation unit 48a has a fastening element 50a. The fastening element 50a is provided for a force-fit, form-fit and / or material connection with the aircraft module 12a. Alternatively, the fastening element 50a can also be provided for a force-fitting, form-fitting and / or material connection with the panel 18a. The Fastening element 50a is inserted in a recess, not shown in detail, of aircraft module 12a. The recess of the aircraft module 12a is designed in particular as a cutout in a wall of the aircraft module 12a. The wall of the aircraft module 12a is formed, for example, from a composite structure. The composite structure is formed, for example, as a sandwich unit with a honeycomb core, in particular a honeycomb structure. The fastening element 50a is intended to be inserted into the wall of the aircraft module 12a. Alternatively, the fastening element 50a can also be attached to the surface 22a of the panel 18a facing the aircraft module 12a. The fastening element 50a is provided to hold the connecting element 36a within the defined compensation area 34a.

In the assembled state, the fastening element 50a is arranged partially flush with an outer surface 52a of the aircraft module 12a. The fastening element 50a is at least partially offset from the outer surface 52a of the aircraft module 12a. The fastening element 50a at least partially forms a recess 54a opposite the outer surface 52a of the aircraft module 12a. The fastening element 50a has a plurality of positioning extensions 56a. In the present case, the fastening element 50a has four positioning extensions 56a. The positioning extensions 56a are each designed like wings. The positioning extensions 56a are provided to provide a shoulder to support the fastening element 50a on the outer surface 52a of the aircraft module 12a. This enables an advantageously simple assembly. The fastening element 50a has a plurality of latching structures 58a. The latching structures 58a form barbs. The latching structures 58a are provided to connect the fastening element 50a to the aircraft module 12a in a form-fitting manner, in particular to anchor them in the aircraft module 12a. In the assembled state, the latching structures 58a engage in the aircraft module 12a, in particular in the wall of the aircraft module 12a. As an alternative or in addition, it would be conceivable that the fastening element 50a, in the assembled state, is connected to the aircraft module 12a in a materially bonded manner, in particular by means of an adhesive bond.

The compensation unit 48a has a movably mounted compensation element 60a. The compensation element 60a is mounted displaceably along the axis 62a. The compensation element 60a is mounted displaceably along the further axis 85a. The compensation element 60a is rotatably pivoted in the plane. The connecting element 36a is mounted so as to be translationally movable relative to the compensating element 60a along the axis 62a. The connecting element 36a is mounted so as to be displaceable by at least 1 mm relative to the compensating element 60a along the axis 62a. In this way, an offset during assembly can advantageously be compensated for in a variable manner. The compensating element 60a is designed as a plate which has a recess 64a for receiving the connecting element 36a. The compensation element 60a is designed as a punched-out plate. The compensation element 60a is formed from aluminum in the present case. The recess 64a is designed as a passage for the connecting element 36a. In the assembled state, the connecting element 36a is partially arranged in the compensating element 60a. The recess 64a is designed as a guide for a translational movement of the connecting element 36a. The connecting element 36a is coupled to the compensating element 60a. The connecting element 36a is locked in the compensating element 60a.

The compensating element 60a designed as a plate has a rectangular basic shape. Alternatively, another basic shape that appears suitable to a person skilled in the art is also conceivable, for example a round or oval basic shape. The rectangular basic shape of the compensating element 60a has rounded edges 68a on an outer contour 66a of the compensating element 60a. The rounded edges 68a are provided to facilitate a rotatability of the compensating element 60a within the fastening element 50a.

The recess 64a extends over an entire thickness of the compensating element 60a designed as a plate. The recess 64a is rectangular. A maximum length of the recess 64a is greater than a maximum extension of the connecting element 36a in the assembled state, measured parallel to the axis 62a. The rectangular recess 64a has rounded portions 70a, the radius of which is one half of a maximum width of the recess 64a. The maximum length of the recess 64a is at least three times as large as the maximum width of the recess 64a.

The compensation element 60a is arranged directly on the fastening element 50a. The compensating element 60a is coupled to the fastening element 50a in the assembled state. The compensation element 60a is movably mounted with respect to the fastening element 50a. The compensation element 60a is floatingly mounted with respect to the fastening element 50a. The compensating element 60a is at least partially enclosed in a form-fitting manner by the fastening element 50a, the compensating element 60a being movably supported with respect to the fastening element 50a. The Compensation element 60a is provided to carry out the compensation movement. The compensation element 60a is provided to be displaced in the plane within the defined compensation area 34a. The compensation element 60a is movably supported in the plane. The compensation element 60a is provided to support the connecting element 36a in a moveable manner.

The fastening element 50a is provided to exert a clamping force on the compensating element 60a. The compensating element 60a is at least partially enclosed in a form-fitting manner by the fastening element 50a, the compensating element 60a being movably supported with respect to the fastening element 50a. The fastening element 50a has a plurality of fastening extensions 72a. The fastening extensions 72a are provided to at least partially enclose the compensating element 60a in a form-fitting manner. The fastening extensions 72a form an insert 74a of the fastening element 50a, which is provided to receive the compensating element 60a. The fastening extensions 72a are provided to clamp the compensating element 60a by means of the clamping force. The fastening element 50a has a latching extension 76a. The latching extension 76a is provided to prevent the compensating element 60a from moving out of the insert 74a. The latching extension 76a is wedge-shaped.

In the 5 to 13th four further embodiments of the invention are shown. The following descriptions and the drawings are essentially limited to the differences between the exemplary embodiments, whereby with regard to identically designated components, in particular with regard to components with the same reference numerals, in principle also to the drawings and / or the description of the other exemplary embodiments, in particular the 1 to 4th , can be referenced. To distinguish the exemplary embodiments, the letter a is the reference number of the exemplary embodiment in FIG 1 to 4th re-enacted. In the embodiments of 5 to 13th the letter a is replaced by the letters b to e.

In the 5 to 8th an aircraft module cladding device 10b is shown in a second exemplary embodiment. The second exemplary embodiment is intended in particular for composite structures. The aircraft module cladding device 10b comprises an aircraft module 12b ( 8th ), which is only partially shown for reasons of clarity. The aircraft module cladding device 10b comprises a panel (not shown in more detail) which, in an assembled state, is provided to at least partially cover the aircraft module 12b.

The aircraft module cladding device 10b comprises a connection unit 28b, which is provided to connect the panel to the aircraft module 12b ( 8th ). The aircraft module cladding device 10b comprises further connection units, not shown in detail, which are provided to connect the panel to the aircraft module 12b.

The connection unit 28b comprises a connection element 32b ( 5 and 6th ). The connection element 32b is intended to be arranged on the panel. In the assembled state, the connection element 32b is arranged on a side of the panel facing the aircraft module 12b. The connection element 32b is provided to be materially connected to the panel. In the present case, the connection element 32b has four elevations 78b, which each form a connection surface for a material connection of the connection element 32b with the panel ( 5 and 6th ). The connection element 32b is designed in the shape of a pin. The connection element 32b has an at least substantially T-shaped basic shape in at least one sectional plane. The connection element 32b is mounted in a defined compensation area 34b such that it can move translationally and rotationally at least essentially in one plane. The connection element 32b has two latching structures 80b ( 5 and 6th ). The latching structures 80b of the connecting element 32b form barbs.

The connection unit 28b comprises a connection element 36b. The connecting element 36b is provided to fasten the connecting element 32b to the aircraft module 12b. The connecting element 36b is designed in the shape of a shaft. The connecting element 36b is provided to fix the connecting element 32b. The connecting element 36b is designed to correspond to the connecting element 32b. The connecting element 36b has two opposing locking projections 82b.

The connection unit 28b has a connection direction 42b. The connection direction 42b is oriented perpendicular to a surface of the panel facing the aircraft module 12b. The connection element 32b is intended to be inserted into the connection element 36b during assembly. The connection element 32b is provided to establish a connection to the connection element 36b that is fixed at least up to a defined dismantling force by means of a form fit. The latching structures 80b of the connecting element 32b are provided for that To connect the connecting element 32b with the connecting element 36b in a form-fitting manner, in particular to anchor it in the connecting element 36b. The latching structures 80b of the connecting element 32b form a form fit with the latching projections 82b of the connecting element 36b in the assembled state. The latching structures 80b of the connecting element 32b are provided to enter into a captive connection with the latching projections 82b of the connecting element 36b.

The connection unit 28b comprises a compensation unit 48b. The compensation unit 48b is provided to allow a compensation movement of the connecting element 36b with respect to the aircraft module 12b and with respect to the panel 18b in the defined compensation area 34b. The compensation unit 48b is provided to allow a compensation movement of the connection element 36b and the connection element 32b with respect to the aircraft module 12b in the defined compensation area 34b.

The compensation unit 48b has a fastening element 50b. The fastening element 50b is provided for a force-fit, form-fit and / or material connection with the aircraft module 12b. The fastening element 50b is inserted in a recess 84b of the aircraft module 12b. The recess 84b of the aircraft module 12b is designed as a cutout in a wall of the aircraft module 12b.

In the assembled state, the fastening element 50b is arranged partially flush with an outer surface 52b of the aircraft module 12b. The fastening element 50b is at least partially offset from the outer surface 52b of the aircraft module 12b. The fastening element 50b at least partially forms a recess 54b opposite the outer surface 52b of the aircraft module 12b. The fastening element 50b has a plurality of positioning extensions 56b. In the present case, the fastening element 50b has four positioning extensions 56b. The fastening element 50b has a plurality of latching structures 58b. The latching structures 58b of the fastening element 50b form barbs. The latching structures 58b of the fastening element 50b are provided to connect the fastening element 50b to the aircraft module 12b in a form-fitting manner, in particular to anchor it in the aircraft module 12b.

The compensation unit 48b has two partly movably mounted compensation elements 60b. In the present case, the connecting element 36b is mounted so as to be translationally immovable with respect to the compensating elements 60b along an axis 62b. The connecting element 36b is mounted such that it can move in translation with respect to the compensating elements 60b along a further axis 85b. The further axis 85b is arranged in the plane. The further axis 85b is aligned perpendicular to the axis 62b in at least one operating state. The connecting element 36b is mounted so as to be translationally displaceable in the at least one direction along the further axis 85b over an extension of at most 6 mm. The connecting element 36b is mounted pivotably with respect to the aircraft module 12b. The connecting element 36b is rotatably mounted in the plane over an angular range of at most 30 degrees relative to the aircraft module 12b. A pivot axis, not shown in detail, about which the connecting element 36b is pivotable, is oriented perpendicular to the plane. The connecting element 32b is mounted such that it can be displaced in relation to the connecting element 36b along the axis 62b in a translatory manner over an extension of at most 2 mm.

The compensation elements 60b are each designed as a spring element. The compensation elements 60b are provided to be deformed in the plane within the defined compensation area 34b. The compensating elements 60b are provided to allow a resilient movement of the connecting element 36b in the plane. The connecting element 36b is coupled to the compensating elements 60b. The compensation elements 60b are arranged directly on the fastening element 50b. The compensation elements 60b are firmly connected to the connecting element 36b and the fastening element 50b. The compensating elements 60b are configured in sections in a meandering manner. The compensating elements 60b are each arranged between the fastening element 50b and the connecting element 36b. The compensating elements 60b are formed in one piece with the fastening element 50b and in one piece with the connecting element 36b. The compensation elements 60b are formed from a plastic. The plastic is preferably fiber-reinforced. In principle, the compensating elements 60b can also be designed as elastomers, in particular to enable resilient deformation of the compensating elements 60b. The fastening element 50b, the compensating elements 60b and the connecting element 36b are formed from the same material. The fastening element 50b, the compensating elements 60b and the connecting element 36b are manufactured together in one manufacturing step, in particular by injection molding.

In the 9 to 11 an aircraft module cladding device 10c is shown in a third exemplary embodiment. The third exemplary embodiment is intended in particular for sheet metal structures. The aircraft module cladding device 10c comprises an aircraft module 12c ( 10 and 11 ), which for the sake of clarity is only partially shown. The aircraft module 12c has at least one wall. In the present case, the wall of the aircraft module 12c is formed from a sheet metal. The aircraft module cladding device 10c comprises a panel (not shown in more detail) which, in an assembled state, is provided to at least partially cover the aircraft module 12c.

The aircraft module cladding device 10c comprises a connection unit 28c which is provided to connect the panel to the aircraft module 12c. The connection unit 28c comprises a connection element not shown in detail in this exemplary embodiment. The connection element is arranged on the panel. The connection element is mounted in a defined compensation area 34c so as to be translationally and rotationally movable at least essentially in one plane. The connection unit 28c has a connection direction 42c.

The connection unit 28c comprises a connection element 36c. The connection element 36c is provided to fasten the connection element to the aircraft module 12c. The connecting element 36c is designed identically to the connecting element 36a from the first exemplary embodiment. The connection element is provided to establish a connection with the connection element 36c that is fixed at least up to a defined dismantling force by means of a form fit and a force fit. The connecting element 36c is mounted in the defined compensation area 34c so that it can move at least essentially in a translatory and rotational manner in the plane.

The connection unit 28c comprises a compensation unit 48c. The compensation unit 48c is provided to allow a compensation movement of the connecting element 36c and the connection element with respect to the aircraft module 12c in the defined compensation area 34c. In the assembled state, the connecting element 36c and the connecting element are jointly movably supported in the plane relative to the aircraft module 12c.

The compensation unit 48c has a fastening element 50c. The compensation unit 48c has a movably mounted compensation element 60c. The compensation element 60c is mounted in a floating manner with respect to the fastening element 50c. The fastening element 50c is provided for a force-fit and / or form-fit connection with the aircraft module 12c. The fastening element 50c is arranged on an inside of the aircraft module 12c that faces away from the panel. In the present case, the fastening element 50c is connected to the aircraft module 12c by means of two rivets 86c. The fastening element 50c is designed as a plate. The fastening element 50c is designed as a punched-out plate. The fastening element 50c is formed from aluminum in the present case. The fastening element 50c designed as a plate has two elevations 88c which are provided to set a defined distance between a large part of the fastening element 50c and a wall of the aircraft module 12c. The distance is at least one thickness of the compensation element 60c. The distance is at most 150% of the thickness of the compensation element 60c. A through hole 90c for each of the rivets 86c is arranged on the elevations 88c. The fastening element 50c embodied as a plate has a recess 92c for receiving the connecting element 36c. The recess 92c is designed as a passage for the connecting element 36c. A size of the recess 92c limits the compensation area 34c. The recess 92c extends over an entire thickness of the fastening element 50c, which is designed as a plate. The recess 92c of the fastening element 50c is rectangular.

The connecting element 36c is mounted so as to be translationally movable relative to the compensating element 60c along an axis 62c. The connecting element 36c is mounted so as to be translationally displaceable by at least 5 mm relative to the compensating element 60c along the axis 62c. The compensating element 60c is designed as a plate which has a recess 64c for receiving the connecting element 36c. The compensation element 60c is designed as a punched-out plate. The compensation element 60c is formed from aluminum in the present case. The recess 64c is designed as a passage for the connecting element 36c. In the assembled state, the connecting element 36c is partially arranged in the compensating element 60c and in the fastening element 50c. The recess 64c is designed as a guide for a translational movement of the connecting element 36c. The connecting element 36c is coupled to the compensating element 60c. The connecting element 36c is locked in the compensating element 60c.

The compensating element 60c designed as a plate has a rectangular basic shape. The rectangular basic shape of the compensating element 60c has two radii 94c on an outer contour 66c of the compensating element 60c. The radii 94c are provided to facilitate a rotatability of the compensating element 60c between the elevations 88c of the fastening element 50c. The recess 64c extends over the entire thickness of the compensating element 60c designed as a plate. The recess 64c is rectangular educated. The compensation element 60c is provided to be displaced in the plane within the defined compensation area 34c.

The aircraft module 12c has a recess 96c which extends over an entire thickness of the wall of the aircraft module 12c ( 11 ). The recess 96c of the aircraft module 12c is provided to enable the connection element to be connected to the connection element 36c through the wall of the aircraft module 12c.

In the 12th an aircraft module cladding device 10d is shown in a fourth exemplary embodiment. The aircraft module cladding device 10d comprises an aircraft module (not shown in more detail). The aircraft module cladding device 10d comprises a panel 18d which, in an assembled state, is provided to at least partially cover the aircraft module.

The aircraft module cladding device 10d comprises a connection unit 28d which is provided to connect the panel 18d to the aircraft module. The connection unit 28d comprises a connection element 32d. The connection element 32d is arranged on the panel 18d. The connection element 32d is mounted in a defined compensating area 34d such that it can move translationally and rotationally at least essentially in one plane. The connection element 32d is provided to be displaced in the plane within the defined compensation area 34d.

The connection unit 28d comprises a connection element not shown in detail. The connection element is provided to fasten the connection element 32d to the aircraft module. The connecting element is designed identically to the connecting element 36a from the first exemplary embodiment.

The connection element 32d is provided to establish a connection with the connection element that is fixed at least up to a defined dismantling force by means of a form fit and a force fit. The connecting element is immovably mounted on the aircraft module. In the present case, the connecting element is arranged in a stationary manner on the aircraft module.

The connection unit 28d comprises a compensation unit 48d. The compensation unit 48d is provided to allow a compensation movement of the connection element 32d with respect to the panel 18d in the defined compensation area 34d. The compensation unit 48d is provided to allow a compensation movement of the connection element 32d with respect to the aircraft module and the panel 18d in the defined compensation area 34d. The compensation unit 48d is provided to compensate for manufacturing tolerances for a position of the connecting element on the aircraft module.

The compensation unit 48d has a fastening element 50d. The fastening element 50d is provided for a material connection with the panel 18d. In the assembled state, the connection element 32d is movably supported with respect to the panel 18d. The fastening element 50d is firmly connected to the panel 18d. The fastening element 50d is materially connected to the panel 18d. The fastening element 50d is glued to the panel 18d.

The fastening element 50d rests continuously on the panel 18d along an outer contour 98d of the fastening element 50d. The fastener 50d has a plurality of through holes 100 on, which are provided for receiving adhesive. The fastening element 50d has a concave basic shape to the panel 18d. In the assembled state, the fastening element 50d and the panel 18d form an intermediate space 102d in which the connecting element 32d is partially arranged. The connection element 32d is mounted in a form-fitting manner by means of the intermediate space 102d. The connection element 32d is floatingly mounted in the intermediate space 102d. The fastening element 50d is provided to hold the connection element 32d within the defined compensation area 34d. The fastening element 50d is provided to exert a clamping force on the connection element 32d. The fastening element 50d has two fastening extensions 104d, which are provided to partially enclose the connection element 32d in a form-fitting manner. The fastening extensions 104d are formed at least substantially parallel to an adjoining surface 44d of the panel 18d. The fastening extensions 104d are plate-shaped. The fastening extensions 104d are provided to clamp the connection element 32d by means of the clamping force. The fastening extensions 104d are pretensioned in the direction of the side 24d of the panel 18d facing the aircraft module. As a result, an advantageously simple prepositioning of the connecting element 32d can be made possible, which enables an advantageously easy assembly. The fastening extensions 104d are provided to enable the connection element 32d to be introduced into the space 102d and / or to enable the connection element 32d to be removed from the space 102d, in particular if the fastening element 50d is connected to the panel 18d. The fastening extensions 104d are designed to be reversibly deformable. This can lead to an introduction and / or removal of the connecting element 32d are advantageously made possible. The fastening extensions 104d are designed so that they can be bent open in a direction which is oriented perpendicular to the surface 44d of the panel 18d and faces away from the surface 44d. The connection element 32d can be removed and / or pushed in laterally between the fastening extensions 104d. As a result, the connection element 32d can be arranged on the panel 18d particularly advantageously afterwards, in particular after the fastening element 50d has been connected to the panel 18d. As a result, the connection element 32d can be exchanged in a particularly advantageous manner without having to manipulate the panel 18d itself.

In the 13th an aircraft module cladding device 10e is shown in a fifth exemplary embodiment. The aircraft module cladding device 10e comprises an aircraft module (not shown in greater detail). The aircraft module cladding device 10e comprises a panel 18e which, in an assembled state, is provided to at least partially cover the aircraft module.

The aircraft module cladding device 10e comprises a connection unit 28e which is provided to connect the panel 18e to the aircraft module. The connection unit 28e comprises a connection element 32e. The connection element 32e is arranged on the panel 18e. The connection element 32e is mounted in a defined compensating area 34e such that it can move translationally and rotationally at least essentially in one plane. The connection element 32e is provided to be displaced in the plane within the defined compensation area 34e.

The connection unit 28e comprises a connection element not shown in detail. The connection element is provided to fasten the connection element 32e to the aircraft module. The connecting element is designed identically to the connecting element 36a from the first exemplary embodiment.

The connection element 32e is provided to establish a connection with the connection element that is fixed at least up to a defined dismantling force by means of a form fit and a force fit. The connecting element is immovably mounted on the aircraft module. In the present case, the connecting element is arranged in a stationary manner on the aircraft module.

The connection unit 28e comprises a compensation unit 48e. The compensation unit 48e is provided to allow a compensation movement of the connection element 32e with respect to the panel 18e in the defined compensation area 34e. The compensation unit 48e is provided to allow a compensation movement of the connection element 32e with respect to the aircraft module and the panel 18e in the defined compensation area 34e. The compensation unit 48e is provided to compensate for manufacturing tolerances for a position of the connecting element on the aircraft module.

The compensation unit 48e has a fastening element 50e. The fastening element 50e is provided for a material connection with the panel 18e. In the assembled state, the connection element 32e is movably supported with respect to the panel 18e. The fastening element 50e is firmly connected to the panel 18e. The fastening element 50e is materially connected to the panel 18e. The fastening element 50e is glued to the panel 18e. The fastening element 50e rests partially on the panel 18e along an outer contour 98e of the fastening element 50e. The fastening element 50e is designed like a bridge. The fastening element 50e partially spans the connection element 32e. On two opposite sides 106e of the fastening element 50e, the fastening element 50e is not connected to the panel 18e. On the two opposite sides 106e, the fastening element 50e is formed without contact with the panel 18e. The fastening element 50e has a multiplicity of through holes 100e which are provided for receiving adhesive. The fastening element 50e has a concave basic shape to the panel 18e. In the assembled state, the fastening element 50e and the panel 18e form an intermediate space 102e in which the connecting element 32e is partially arranged. The gap 102e is open to the sides 106e. As a result, an advantageously narrow fastening element 50e can be provided which can be arranged, for example, on a curved surface 44e of the panel 18e. The connection element 32e is mounted in a form-fitting manner by means of the intermediate space 102e. The connection element 32e is floatingly mounted in the intermediate space 102e. The fastening element 50e is provided to hold the connection element 32e within the defined compensation area 34e. The fastening element 50e is provided to exert a clamping force on the connection element 32e. The fastening element 50e has two fastening extensions 104e which are provided to partially enclose the connection element 32e in a form-fitting manner. The fastening extensions 104e are formed at least substantially parallel to the adjoining surface 44e of the panel 18e. The fastening extensions 104e are plate-shaped. The fastening extensions 104e are provided to clamp the connection element 32e by means of the clamping force. The fastening extensions 104e are pretensioned in the direction of the side 24e of the panel 18e facing the aircraft module.

List of reference symbols

10

Aircraft module fairing device

12th

Aircraft module

14th

Aircraft seat assembly

16

Passenger seat

18th

Panel

20th

Visible side

22nd

surface

24

page

26th

Panel

28

Connection unit

30th

Connection unit

32

Connection element

34

Compensation area

36

Connecting element

38

inside

40

Clamping process

42

Connection direction

44

surface

46

mandrel

48

Compensation unit

50

Fastener

52

Exterior surface

54

deepening

56

Positioning process

58

Locking structure

60

Compensation element

62

axis

64

Recess

66

Outer contour

68

Edge rounding

70

Rounding

72

Attachment extension

74

Inset

76

Detent process

78

Elevation

80

Locking structure

82

Detent process

84

Recess

85

axis

86

rivet

88

Elevation

90

Through hole

92

Recess

94

radius

96

Recess

98

Outer contour

100

Through hole

102

Space

104

Attachment extension

106

page

Claims (14)

Aircraft module cladding device with at least one aircraft module (12a; 12b; 12c), in particular aircraft seat module, with at least one panel (18a; 18d; 18e) which, in an assembled state, is provided for the at least one aircraft module (12a; 12b; 12c) at least partially to cover, and with at least one connection unit (28a; 30a; 28b; 28c; 28d; 28e), which is provided to the at least one panel (18a; 18d; 18e) with the at least one aircraft module (12a; 12b; 12c) connect, wherein the at least one connection unit (28a, 30a; 28b; 28c; 28d; 28e) comprises at least one connection element (32a; 32b; 32d; 32e) which is arranged on the at least one panel (18a; 18d; 18e), and at least one connecting element (36a; 36b; 36c) which is provided to fasten the at least one connecting element (32a; 32b; 32d; 32e) to the at least one aircraft module (12a; 12b; 12c), characterized in that the at least one connection unit (28a; 30a; 28b; 28c; 28d; 28e) comprises at least one compensating unit (48a; 48b; 48c; 48d; 48e) which is provided for a compensating movement of the at least one connecting element (36a; 36b; 36c) and / or of the at least one connecting element (32a; 32b; 32d; 32e) in relation to the at least one aircraft module (12a; 12b; 12c) and / or in relation to the at least one panel (18a; 18d; 18e) in a defined compensation area (34a; 34b; 34c; 34d; 34e). Aircraft module fairing device according to Claim 1 , characterized in that the at least one connecting element (36a; 36b; 36c) and / or the at least one connecting element (32a; 32b; 32d; 32e) in the defined compensation area (34a; 34b; 34c; 34d; 34e) at least in Is mounted in a translatory and / or rotationally movable manner essentially in one plane. Aircraft module fairing device according to Claim 1 or 2 , characterized in that the at least one connecting element (36a; 36b; 36c) and / or the at least one connecting element (32a; 32b; 32d; 32e) is translationally movable in at least one direction with respect to the at least one aircraft module (12a; 12b; 12c) are / is stored. Aircraft module cladding device according to one of the preceding claims, characterized in that the at least one connecting element (36a; 36b; 36c) and / or the at least one connecting element (32a; 32b; 32d; 32e) can be pivoted with respect to the at least one aircraft module (12a; 12b; 12c ) are / is stored. Aircraft module cladding device according to one of the preceding claims, characterized in that the at least one compensating unit (48a; 48b; 48c; 48d; 48e) has at least one fastening element (50a; 50b; 50c; 50d; 50e) which leads to a non-positive, positive and / or a material connection with the at least one aircraft module (12a; 12b; 12c) or the at least one panel (18a; 18d; 18e) is provided. Aircraft module fairing device according to Claim 5 , characterized in that the at least one fastening element (50a; 50b) in the assembled state is arranged at least partially flush with an outer surface (52a; 52b) of the at least one aircraft module (12a; 12b). Aircraft module cladding device according to one of the preceding claims, characterized in that the at least one compensating unit (48a; 48b; 48c) has at least one movably mounted compensating element (60a; 60b; 60c) which is provided to carry out the compensating movement. Aircraft module fairing device according to Claim 5 or 6th and Claim 7 , characterized in that the at least one compensating element (60a, 60b; 60c) is coupled to the at least one fastening element (50a; 50b; 50c) in the assembled state. Aircraft module fairing device according to Claim 7 , characterized in that the at least one compensating element (60a; 60b; 60c) is designed as a plate which has at least one recess (64a; 64b; 64c) for receiving the at least one connecting element (36a; 36b; 36c). Aircraft module fairing device according to Claim 7 , characterized in that the at least one compensating element (60b) is designed as a spring element. Aircraft module fairing device according to Claim 7 , characterized in that the at least one compensating element (60b) is formed in one piece with the at least one fastening element (50b) and in one piece with the at least one connecting element (36b). Aircraft module cladding device according to one of the Claims 1 to 5 , characterized in that the at least one connection element (32d; 32e) is movably mounted in relation to the at least one panel (18d; 18e) in the assembled state. Aircraft module cladding device according to one of the Claims 1 to 9 , characterized in that the at least one fastening element (50a; 50d; 50e) is provided to exert a clamping force on the at least one compensating element (60a) and / or on the at least one connecting element (32d; 32e). Connection unit (28a; 28b; 28c; 28d; 28e) of an aircraft module cladding device (10a; 10b; 10c; 10d; 10e) according to one of the Claims 1 to 13th .

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