Support system for equipment in the cabin interior of an aircraft

Abstract

A support system (10) for equipment (14) of a cabin interior of an aircraft, the system comprising: - a panel structure (16); - an air guiding structure (18); and - a support structure (20); wherein the panel structure (16) is configured to form at least a portion of an interior side wall of an aircraft cabin (12); wherein the air duct structure (18) comprises air ducts (22) and an air exchange opening (24) of an air supply system for an aircraft cabin (12), wherein the air exchange opening (24) is arranged along an upper edge of the panel structure (16); wherein the upper edge of the panel structure (16) is configured as a bi-functional interface (26), for which the air exchange opening (24) is formed by surrounding wall parts arranged to act statically with the panel structure (16) for load transfer purposes for at least temporarily fixing the support structure (20), and for which the air exchange opening (24) provides air exchange with a cabin interior; wherein the support structure (20) has a carrier (28) for supporting equipment (14) of a cabin interior; and wherein the support structure (20) has a first mounting interface (30) at one end for fixing the bi-functional interface, and wherein the support structure (20) has a mounting interface (32) at another end for connection to a second support point in the cabin; and wherein the bi-functional interface (26) provides support along the length of the upper edge region of the panel structure (16) and provides an air exchange flow (29) along the length of the upper edge, the air exchange flow (29) also being provided in regions with a mounted support structure (20); wherein the bi-functional interface (26) has an integrated air duct forming the surrounding wall parts, the air duct being provided by the panel structure (16) itself; wherein the air exchange opening (24) is formed as a grid (36), wherein openings between the grid (36) provide the air exchange and a grid structure spanning the opening provides structural rigidity for load bearing purposes; wherein the first mounting interface (30) of the support structure (20) to the bi-functional interface (26) is configured as a flexible, removable connector (38); wherein the connector (38) is configured as a male plug having at least two arms (40); wherein the arms can be clipped into the bi-functional interface (26); wherein the plurality of arms of the connector (38) are dependent on the weight of the equipment (14) of the cabin carried by the support structure (20); and wherein the second support point can be provided on a hat rack or an overhead storage compartment and the support structure can be fastened to the support point on the hat rack via a hook-like connection.

Description

FIELD OF THE INVENTIONThe present invention relates to a cabin interior equipment support system of an aircraft, an aircraft cabin configuration and an aircraft.BACKGROUND OF THE INVENTIONAircraft cabin design is becoming increasingly important as a factor in the sale of an aircraft. In particular, customization of cabin layouts according to the needs of an airline is important to an aircraft manufacturer. Airlines may need to change the cabin configuration depending on the billing situation of the flight, which requires not only high flexibility for the arrangement of passenger seats, but also a flexible arrangement of other equipment. Such flexible arrangements of the equipment of a cabin can be difficult to integrate into the cabin structure.US 5 549 258 A describes baggage trays for retrofitting existing aircraft with larger overhead baggage trays compatible with the existing aircraft tray support structure for original equipment trays. US 2 912 724 A describes a cabin panel with integrated ventilation ducts for a window. US 2012 / 0 156 979 A1 describes an aircraft fuselage side wall having an air interspace. DE 10 2006 049 030 B3 describes a loudspeaker system for an aircraft cabin. US 2012 / 0 025 018 A1 describes a partition wall between two flight class regions. DE 10 2008 048 499 A1 describes an overhead stowage box holder. DE 10 2005 054 890 A1 describes a fastening structure for fixing interior equipment components of an aircraft passenger cabin. DE 10 2006 016509 A1 describes a fastening system for an add-on element on a fastening structure.SUMMARY OF THE INVENTIONThere may therefore be a need for an aircraft cabin interior equipment support system that allows flexibility while providing simplified support options.The object of the invention is achieved by the subject matter of the independent claims, wherein further embodiments are incorporated in the dependent claims.According to the present invention, a cabin interior equipment support system of an aircraft comprises a panel structure, an air guiding structure and a support structure. The panel structure is configured to form at least a portion of an interior sidewall of an aircraft cabin. The air guiding structure comprises air ducts and an air exchange opening of an air supply system for an aircraft cabin; the air exchange opening is arranged along an upper edge of the panel structure. The upper edge of the panel structure is configured as a bi-functional interface for which the air exchange opening is formed by surrounding wall parts which are arranged to statically act with the panel structure for load bearing purposes for at least temporarily fixing the support structure, and for which the air exchange opening provides an air exchange with a cabin interior. The mounting structure has a carrier for supporting equipment of a cabin interior. At one end, the mounting structure has a first mounting interface for fixing to the bifunctional interface. At another end, the mounting structure has a second mounting interface for connection to a second support point in the cabin. The bi-functional interface provides support along the length of the region of the top edge of the panel structure and provides an air exchange flow along the length of the top edge, the air exchange flow also being provided in regions with a mounted bracket structure.This support system has the effect that a support structure can be arranged in a continuous or stepped manner along the panel structure of the side wall of the cabin. This allows cabin equipment to be positioned within the cabin in a flexible manner and supports adjustment options for changes in the cabin layout.In one example, the panel structure is an integral structure. In most cases, the panel structure may be provided with a "channel" or an opening for intersecting a window. In addition, the panel structure is provided to integrate an air guiding structure, an insulation mat and other parts such as loudspeakers, lighting elements or signs. The panel structure could also integrate loudspeakers or lighting functions if realized in one piece or at least a section thereof. This means that the panel structure could function as a loudspeaker by oscillating the panel structure by means of actuators. Thin optical fibre elements could also be integrated in the panel structure made of one piece for integrating the lighting function in the panel structure. This concept of multifunctional panel could reduce the parts required, resulting in less weight and less time consuming manufacturing.The air guiding structure provides ventilation of air in the cabin produced by an air supply system for an aircraft. It is attachable to the panel structure or integrally embedded in the panel structure. Ventilation refers to supplying and discharging air into and from a cabin interior.The air exchange opening therefore functions as inlet and outlet for air ventilation in the cabin and is a structural element which is used in combination with the upper edge of the panel structure to form a bi-functional interface.The term "bi-functional interface" means that the interface functions as a load bearing interface for fixing a support structure and an air exchange interface for providing an air exchange flow within the cabin. It functions as a support rail with continuously stepped structural interfaces. This allows a flexible arrangement of cabin parts within the cabin.The support structure is a support that can support equipment of a cabin, such as screens, screens, class separators, or curtains. The support structure is configured to allow air to pass therethrough when connected to the bi-functional interface. Such structures can be realized using a 3D printing method or using other production methods.The second support point can be provided, for example, on a hat rack or an overhead storage compartment. In one example, the support structure may be attached to the hatrack at the second support location via a hook-type connection.Therefore, a support system is provided for mounting cabin equipment in a continuously stepped manner within the cabin to achieve the greatest possible space for custom adjustment.According to an example, the bi-functional interface is provided by an air duct forming the surrounding wall parts, wherein the air duct is connected to the panel structure along the upper edge of the panel structure.This means that the air duct walls reinforce the upper edge region of the panel structure for load transfer reasons.In one example, the air duct, also referred to as a supply duct, may be screwed or glued to the upper edge of the panel structure or attached by means of another form of attachment to achieve a statically effective assembly.According to the invention, the bi-functional interface comprises an integrated air duct forming the surrounding wall parts, which air duct is provided by the panel structure itself.In this case, the air duct / supply duct is integrally formed by the panel structure. This means that the air channels are integrated in the production of the panel structure and the panel structure and the air guiding structure form one piece.According to the invention, the exchange opening is formed as a grid, wherein openings between the grid provide the air exchange and a grid structure spanning the opening provides structural rigidity for load bearing purposes.In other words, the bi-functional interface is configured as the grid.According to another example, the replacement opening may be configured as a slot.The bi-functional interface consists of the panel structure and the air exchange opening. According to one example, the air exchange opening can be statically effectively mounted on the panel structure, in another example, the air exchange opening can be embedded in the panel structure itself.According to an example, the panel structure is configured to function as a loudspeaker, wherein at least a part of the panel structure is oscillated by actuators. The panel structure may function as a loudspeaker by oscillating at least a part of the panel structure. The oscillation is produced by means of actuators which are mounted on the panel structure.According to another example, the panel structure provides a lighting element, wherein the lighting element comprises at least one of the group of embedded LED elements, light fibers embedded in the panel structure, and light elements insertable into the panel structure.According to the invention, the first mounting interface of the mounting structure to the bi-functional interface is configured as a flexible removable connector. The connector is configured as a male plug having at least two arms. The arms are clippable into the bi-functional interface; the plurality of arms of the connector depend on the weight of the cabin equipment supported by the support structure.In one example, the arms may be of any snap and snap type for connection to the grid or slot of the bi-functional interface. Alternatively, the arms could be screwed into the bifunctional interface or attached by means of velcro.According to an example, the equipment of the cabin supported by the support structure comprises at least one of the group of shields, screens, partitions, and infotainment equipment.According to the present invention, an aircraft cabin configuration is also provided, which has at least one mounting system according to one of the preceding claims and at least one further cabin part. The mounting structure is connected to the further cabin part by a second support point or layer. The support system is configured to be installed in an aircraft so as to extend along the cabin in a longitudinal direction for providing support options for cabin equipment along the cabin in the longitudinal direction in a substantially continuous manner. This allows the airline to adapt the cabin equipment position to the required cabin configuration per flight in a simple and quick manner.According to the present invention, there is also provided an aircraft comprising a fuselage and a cabin area provided within the fuselage. The cabin area is surrounded by an internal cabin structure. The internal cabin structure is at least partially provided by an aircraft cabin configuration according to the preceding example.According to one aspect of the invention, a support system for fastening equipment of a cabin interior is realized by tensioning an adapter from the panel structure of the side wall to a second support point on the parcel shelf or the overhead storage compartment. The adapter or the mounting structure is fixed to an air exchange opening. The air exchange opening is provided as a bifunctional interface for fixing the mounting structure and at the same time for passing an air exchange flow through the region connected to the mounting structure. The existing air exchange opening gives the possibility of arranging the support structure with the equipment of a cabin mounted thereto in a flexible and continuously stepped manner. This allows the airline operator to arrange the position of equipment of a cabin depending on the cabin configuration.These and other aspects of the present invention will be apparent from and with reference to the embodiments described hereinafter.BRIEF DESCRIPTION OF THE DRAWINGSEmbodiments of the invention will be described below with reference to the following drawings. The following are shown: FIG. 1 shows a support system on one side of an aircraft cabin; FIG. 2 shows a panel structure and a bi-functional interface; FIG. 3 shows a mounting structure connection to the bifunctional interface; FIG. 4 shows a cross section of the mounting structure connection to the bifunctional interface; and FIG. 5 shows an aircraft cross section and the position of the support system within the cabin.DESCRIPTION OF EMBODIMENTSFIG. 1 shows a support system 10 in an aircraft cabin 12 for fastening equipment 14 of a cabin interior. The support system comprises a panel structure 16, an air guiding structure 18 and a mounting structure 20. The panel structure is at least partially configured to form an interior sidewall of an aircraft cabin.The air guiding structure comprises air lines 22 and an air exchange opening 24 of an air supply system (not shown) for an aircraft cabin. The air exchange opening is arranged along an upper edge of the panel structure. The air exchange opening or the air channel can either be a separate component fixed to the panel structure or integrated into the panel structure. This can be realized by including the air exchange opening and also the air conduit in the panel structure.The upper edge of the panel structure is configured as a bi-functional interface 26 for which the air exchange opening 24 is formed by surrounding wall parts arranged to statically act with the panel structure 16 for load bearing purposes for at least temporarily fixing the support structure 20 and for which the air exchange opening provides air exchange with a cabin interior.The support structure 20 includes a bracket 28 for supporting equipment of a cabin interior, such as a shield. The mounting structure 20 has a first mounting interface 30 for fixing the bifunctional interface 26 at one end and a second mounting interface 32 for connection to a second support point in the cabin.In case the support structure is attached to the bi-functional interface, the bi-functional interface simultaneously provides support along the length of the upper edge area of the panel structure and also in areas with a mounted support structure an air exchange flow 29 along the length of the upper edge area.FIG. 2 shows the bifunctional interface formed by an air exchange opening 24 or an air duct which forms the surrounding wall parts. The bi-functional interface is formed by the integrated air duct forming the surrounding wall parts, which air duct is provided by the panel structure 16 itself. The air conduits and the air channels are embedded in the panel structure. Fixing the air-guiding structure to the panel structure is therefore no longer necessary. This reduces the number of parts and improves the rigidity of the panel structure. Alternatively, the air duct may be screwed or glued to the panel structure.Figure 3 shows the support structure 20 to be attached to the bi-functional interface 26 The replacement opening is provided as a grid 36, or in other words the grid is the bi-functional interface which still provides the air replacement in the area where the support structure is mounted. The lattice structure, which spans the opening, provides structural rigidity for load transfer reasons.FIG. 4 shows a cross section of the first mounting interface of the mounting structure 20 fixed to the bifunctional interface. The fixture of the support structure is configured as a flexible removable connector 38. The connector is configured as a male plug having at least two arms 40. The arms are clipped into the bi-functional interface, with the airflow 42 of the air exchange opening of the bi-functional interface flowing through the connector 38 of the support structure.The plurality of arms of the connecting part is variably dependent on the weight of the cabin equipment supported by the support structure. That is, when equipment of the cabin is heavy, the connecting piece of the support structure has more arms for supporting the loads inputted from the weight of the equipment of the cabin.Figure 5 shows a cross section of the cabin to illustrate the positioning of the support system in the cabin. As shown, the support system may be positioned along the panel structure of the cabin.It is to be noted that embodiments of the invention have been described with reference to different subject matters. In particular, some embodiments have been described with respect to an aircraft cabin equipment support system, whereas other embodiments have been described with respect to the aircraft cabin configuration or the aircraft. However, unless otherwise noted, a person skilled in the art can grasp from the above and the following description that, in addition to each combination of features belonging to one type of subject matter, any combination between features relating to other subject matter should also be considered to be disclosed with this application. However, all features may be combined together, providing synergy effects that are more than a mere summation of the features.While the invention has been illustrated and described in detail in the drawings and the foregoing description, the drawings and description are to be regarded as illustrative in nature and exemplary in nature and not as restrictive. The invention is not limited to the disclosed embodiments. Other variations of the disclosed embodiments may be understood and made by those skilled in the art upon practicing the claimed invention, from a study of the drawings, the disclosure, and the dependent claims.In the claims, the word "comprising" does not exclude other elements or steps, and the indefinite article "a" or "an" does not exclude a plurality. A single device or other entity may perform the functions of multiple items recited in the claims. The mere fact that certain measures are recited in mutually different dependent claims is no indication that a combination of these measures is not advantageously usable. Neither of the reference numerals in the claims should be interpreted as limiting the scope of protection.

Claims

A support system (10) for equipment (14) of an aircraft cabin interior, the system comprising: - a panel structure (16); - an air guiding structure (18); and - a support structure (20); wherein the panel structure (16) is configured to form at least a portion of an interior sidewall of an aircraft cabin (12); wherein the air guiding structure (18) comprises air conduits (22) and an air exchange opening (24) of an air supply system for an aircraft cabin (12), wherein the air exchange opening (24) is arranged along an upper edge of the panel structure (16); wherein the upper edge of the panel structure (16) is configured as a bi-functional interface (26) for which the air exchange opening (24) is formed by surrounding wall parts which are arranged to act statically with the panel structure (16) for load bearing purposes for at least temporarily fixing the mounting structure (20), and for which the air exchange opening (24) provides air exchange with a cabin interior; wherein the mounting structure (20) comprises a support (28) for supporting equipment (14) of a cabin interior; and wherein the mounting structure (20) comprises at one end a first mounting interface (30) for fixing the bi-functional interface, and wherein the mounting structure (20) comprises at another end a mounting interface (32) for connection to a second supporting location in the cabin; and wherein the bi-functional interface (26) provides support along the length of the area of the top edge of the panel structure (16) and provides an air exchange flow (29) along the length of the top edge, the air exchange flow (29) also being provided in areas with a mounted bracket structure (20); wherein the bi-functional interface (26) has an integrated air channel forming the surrounding wall parts, the air channel being provided by the panel structure (16) itself; wherein the air exchange opening (24) is formed as a grid (36), wherein openings between the grid (36) provide the air exchange and a grid structure spanning the opening provides structural rigidity for load removal purposes; wherein the first mounting interface (30) of the bracket structure (20) to the bi-functional interface (26) is configured as a flexible removable connector (38); wherein the connector (38) is configured as a male plug having at least two arms (40); wherein the arms are clippable into the bi-functional interface (26); wherein the plurality of arms of the connector (38) are dependent on the weight of the cabin equipment (14) supported by the support structure (20); and wherein the second support location is provideable to a hatrack or an overhead storage bin and the support structure is attachable to the hatrack at the support location via a hook-type connection.The support system (10) according to claim 1, wherein the bi-functional interface (26) is provided by an air duct forming the surrounding wall parts, the air duct being connected to the panel structure (16) along the upper edge of the panel structure (16).The support system (10) according to any of the preceding claims, wherein the panel structure (16) is configured to function as a loudspeaker, wherein at least a part of the panel structure (16) is oscillated by means of actuators.The support system (10) according to any one of the preceding claims, wherein the panel structure (16) provides a lighting element, wherein the lighting element comprises at least one of the group of: - embedded LED elements, - light fibers embedded in the panel structure (16), and - light elements insertable into the panel structure (16).The support system (10) of any preceding claim, wherein the cabin equipment (14) supported by the support structure (20) comprises at least one of the group of: shields, screens, partitions, curtains, and infotainment equipment.An aircraft cabin configuration comprising: - at least one support system (10) according to any of the preceding claims, and - at least one further cabin part; wherein the support structure (20) is connected to a second support location on the further cabin part, wherein the support system is configured to be installed in an aircraft so as to extend along the cabin in a longitudinal direction for providing support options for cabin equipment along the cabin in the longitudinal direction in a substantially continuous manner.An aircraft comprising - a fuselage, and - a cabin area provided within the fuselage; wherein the cabin area is enclosed by an internal cabin structure, and wherein the internal cabin structure is at least partially provided by an aircraft cabin configuration according to the preceding claim.

Images