Control system for the cabin of an aircraft, data distribution device and aircraft

Abstract

A control system (1) for a cabin (101) of an aircraft (100) is described, comprising a main processing unit (2), at least one galley control unit (3; 3A, 3C), and a spatially separate data distribution unit (4) comprising a first processing unit (41) and a second processing unit (42) autonomous from the first. The first and second processing units (41, 42) are connected via an interface circuit (44) for data exchange. The first processing unit (41) is configured to provide an actuation signal for activating a cabin function based on a cabin output signal received from the main processing unit (2).The second computing unit (42) is configured to provide a switching signal based on a control command received from a display unit (31) of the galley control device (3; 3A, 3C), which causes an energy control device (32) to switch an electrical consumer (L) on or off, and which is configured to provide a display signal based on a cabin output signal received from the first computing unit (41) in order to display information on the display unit (31).

Description

[0001] The present invention relates to a control system for the cabin of an aircraft, a data distribution device, in particular for the control system, and an aircraft.

[0002] In modern aircraft, e.g. in commercial aircraft, one or more galleys are usually provided within the cabin, in which meals for passengers or crew members are stored and / or prepared. These galleys are usually implemented in the form of so-called cabin monuments, i.e. as prefabricated shelf- or cupboard-like installation groups. In addition to galleys, toilets are also usually implemented as cabin monuments. The installation groups for galleys have several compartments or shelf segments. These compartments usually contain containers for storing food and drinks, service carts or mobile containers (trolleys or galley carts), as well as functional units such as warming ovens, refrigerators, coffee machines, or similar. These functional units represent electrical consumers, for whose operation and electrical (overload) protection a switch panel is usually provided on the monument.

[0003] In order to provide passengers with as much space as possible, attempts are made to integrate cabin monuments into aircraft cabins in the most space-saving way possible.

[0004] Galleys are therefore typically located near the aircraft entrances, and there is a need to further reduce the space required by galleys or, more generally, the space required by cabin features. At the same time, especially in passenger aircraft, the need for in-cabin service and surveillance functions is increasing. For example, surveillance cameras are often installed in aircraft cabins, whose images are displayed on a monitor, allowing flight crew to constantly monitor passengers. Passengers should also be able to communicate with flight crew at any time.

[0005] To meet these requirements, DE 20 2017 004 091 U1 proposes a cabin monument in the form of a combined toilet / galley unit, with a display mounted on the monument on which the images recorded by a surveillance camera can be shown. In order to implement surveillance functions, service functions and other cabin functions, such as switching the seatbelt signs on and off, in a space-saving and efficient manner, a control device network is generally provided. For example, DE 10 2007 051 196 A1 describes coupling surveillance cameras to a control device network in the form of a bus system via a data distribution device in the form of a switch, wherein the control device network also includes a so-called flight attendant panel (FAP) for the flight crew to set and control cabin functions, such as lighting or ventilation, as well as for feedback from passengers, e.g.seat-related service requests.

[0006] It is one of the objects of the present invention to provide a system for a cabin of an aircraft in which the space available for a galley in the cabin is used efficiently and the functionality in the galley area is improved.

[0007] This problem is solved by the subject matter of the independent claims.

[0008] According to a first aspect of the invention, a control system for a cabin of an aircraft is provided, which has a main processing unit, at least one galley operating device and a data distribution device.

[0009] The main processing unit (HRE) has a first interface configured for the exchange of cabin data and a distribution interface. The cabin data can, for example, be control commands entered by a flight attendant via a flight attendant panel (FAP), such as the command to activate the seatbelt signs above the seats or communication data during a telephone conversation between several flight attendants. Furthermore, cabin data can be read from a data storage device and, for example, contain information about the cabin layout of the respective aircraft or about the occupancy of individual shelves in the galley with containers or functional units.In addition, the HRE can also receive cabin data via an application server from which passengers can select services, for example a data set containing the information that a passenger sitting in a specific seat has booked a specific service. The HRE is set up to provide cabin output signals based on the cabin data at the distribution interface and to receive cabin input signals. This can be achieved, for example, by the HRE comprising one or more processors and a data memory with an operating system. The cabin output signals are signals that contain information about the status of a cabin component or about the function to be performed in the cabin and are optionally provided for further processing. For example, the cabin output signals contain the information whether a cabin symbol, such asan indicator light should be switched on or off, communication data, or status information about the galley, e.g., energy consumption. Cabin output signals are signals received from the cabin and can contain the information described above.

[0010] The at least one galley control device has a display device configured for inputting control commands and outputting information based on display signals, and a power control device (ESD). The ESD comprises a supply input configured for connection to an electrical power supply of the aircraft, a plurality of supply outputs configured for connecting electrical consumers of a galley, and a control interface. The ESD is configured to establish or interrupt an electrical connection between each of the consumer outputs and the supply input. The display device thus forms, on the one hand, an input device. For example, the display device can have a touch-sensitive surface (touchscreen) via which certain commands can be manually typed.Furthermore, the display device also represents an output or playback device on which information or images can be reproduced based on the display signals. In functional terms, the ESE forms a type of switch cabinet for switching the individual electrical consumers in the galley on and off. The information as to which of the individual consumer outputs and the supply input an electrical connection should be established or interrupted is contained in a signal received at the control interface, which is explained below. Optionally, the ESE can also be configured as an electrical overload protection device, which automatically interrupts the electrical connection between the supply input and the respective supply output when a current flow threshold is reached at a respective supply output.The ESE can, for example, have relays, in particular solid-state relays, to carry out the aforementioned functions.

[0011] The data distribution device is arranged spatially separate from the galley control device. For example, the galley control device can be arranged directly on the galley's cabin monument, while the data distribution device is arranged on the outer wall of the aircraft cabin or integrated into it.

[0012] The data distribution device comprises a first processing unit with a first control interface connected to the distribution interface of the main processing unit, a plurality of second control interfaces, and a first coupling interface. The first processing unit is configured to provide an actuation signal for actuating a cabin function at one or more of the second control interfaces based on a cabin output signal received from the main processing unit, and to provide received cabin output signals at the first coupling interface. The first processing unit can therefore, for example, receive a signal from the main computer at the first control interface containing the command to activate a cabin signal, e.g., the fasten seatbelt sign.Based on this cabin output signal, the first processing unit generates a corresponding actuation signal and provides it to the corresponding second control interface. Conversely, a signal from a smoke detector, for example, indicating the detection of smoke, can be received at one of the second control interfaces. The first processing unit generates a cabin input signal from this signal and transmits it via the first control interface to the distribution interface of the HRE. This generates cabin data from this signal and transmits it, for example, to the FAP, where the information about the smoke detection is output.

[0013] The data distribution device further comprises a second computing unit that is autonomous from the first computing unit and has a first interface that is connected to the display device, a second interface that is connected to the control interface of the energy control device of the galley operating device, and a second coupling interface that is connected to the first coupling interface of the first computing unit.The second computing unit is configured to provide a switching signal at the second interface based on the control command received from the display device, which causes the energy control device to establish or interrupt an electrical connection between one or more of the consumer outputs and the supply input, and is configured to provide a display signal at the first interface based on a cabin output signal received at the second coupling interface.

[0014] The second processing unit forms a control device for the galley. This allows flight personnel to enter a control command via the display device, for example, a command to turn on a coffee machine in the galley. The second processing unit receives this control command at the first interface and, based on this command, generates a switching signal that is applied to the control interface of the energy control device via the second interface of the second processing unit. This switching signal contains the information regarding which of the energy control device's supply outputs should be electrically connected to the energy control device's supply input. A further function of the second processing unit is to exchange data with the first processing unit via the second coupling interface.In particular, the second processing unit generates a display signal based on the cabin output signals received therein, which is provided at the first interface. Based on the information contained therein, a corresponding, particularly visual, output is generated on the display device. This creates an interface between the galley and the HRE. This enables communication between the galley and the main processing unit via the display device.

[0015] The second processing unit is autonomous from the first processing unit, meaning that the first and second processing units function independently of one another. In particular, in the event of an operational error in the first processing unit, this does not impair the operability of the second processing unit. This can be achieved, for example, by separate processors or separate processor cores, each running separate operating systems, as well as by separate data memories. The first and second coupling interfaces are each designed so that only data that is not critical to the security of the other processing unit can be exchanged between the processing units. This can be achieved, for example, by hardware data filtering. The autonomous execution of the second processing unit improves the operational reliability of the control system.

[0016] A further advantage of the control system according to the invention is that the second processing unit is integrated into the data distribution device located spatially separate from the galley control device. In this way, space can be saved in the galley itself, for example by arranging only the galley control device there, while the data distribution device is accommodated elsewhere in the cabin. This also advantageously enables the retrofitting of existing galleys, since the spatial division of the cabin monument does not have to be changed in order to implement the control functions performed by the second processing unit. The integration of the second processing unit together with the first processing unit into a common data distribution device, providing an interface between the processing units, simultaneously expands the functionality available in the galley.

[0017] According to a second aspect of the invention, an on-board network for an aircraft is provided, comprising the control system according to the first aspect of the invention and a layout memory module. The layout memory module is designed to store information specific to the respective aircraft about the arrangement and configuration of individual components of a cabin of the aircraft as cabin data, wherein the layout memory module is connected to the main processing unit via the first interface. One of the advantages of this on-board network is that, as cabin data, for example, data about the layout of the galley, such as the type of electrical consumers in the galley, their arrangement within the galley, or their electrical power requirements, are stored in a central memory module of the aircraft, and the DVV of the control system can be used to configure the electrical consumers, for example.In this way, individual adaptation of the configuration of a galley of a particular aircraft is made considerably easier.

[0018] According to a third aspect of the invention, a data distribution device for the control system is provided. This device comprises the first processing unit and the second processing unit. The first processing unit comprises a first connection device, which has the first control interface, and a second connection device, which has the second control interface. The first and second connection devices can be designed, for example, as plugs or sockets and contain electrical contact devices that form the respective interfaces. The first processing unit can be formed, for example, by a first processor and a first data memory. Alternatively, instead of the first processor, an FPGA (Field Programmable Gate Array) can be provided, i.e., an integrated circuit into which a logic circuit can be loaded.The second processing unit comprises a third connection device which has the first interface and the second interface. The second processing unit can be formed, for example, by a second processor and a second data memory. Alternatively, instead of the first processor, an FPGA (Field Programmable Gate Array) can be provided, i.e. an integrated circuit into which a logic circuit can be loaded. Furthermore, the data distribution device comprises an interface circuit which forms the first coupling interface of the first processing unit and the second coupling interface of the second processing unit and connects them to one another, in particular connects them in such a way that the second processing unit is autonomous from the first processing unit. The coupling interfaces can be designed, for example, as a serial interface.The second interface of the second processing unit can be implemented, for example, as a CAN interface or an ARINC interface. The data distribution device designed in this way offers the advantages mentioned above for the first aspect of the invention.

[0019] Advantageously, the data distribution device comprises a processor as the first or second processor, an FPGA, and at least one data memory, wherein the processor and the FPGA are connected to each other via the interface circuit and can each access the data memory. The processor, the FPGA, and the at least one data memory together form the first and second computing units.

[0020] According to a fourth aspect of the invention, an aircraft is provided which has a galley with a plurality of electrical loads and which has a control system according to the first aspect of the invention. In this case, each electrical load of the galley is connected to a respective supply output of the energy control unit. The supply input of the energy control unit is connected to an electrical supply network of the aircraft, for example to a 115 volt AC voltage. The display device is arranged on the galley, for example attached to a shelf compartment of the cabin monument. The data distribution device is arranged spatially separate from the galley, for example beneath an interior paneling of a fuselage structure of the aircraft.Since the galley and data distribution device are spatially separated, the space required by the galley can be reduced or at least maintained while improving functionality, resulting in a spacious aircraft cabin.

[0021] Advantageous embodiments and further developments of the invention emerge from the subclaims which refer back to the independent claims in conjunction with the description.

[0022] According to one embodiment of the control system, the second interface is further configured for connection to the electrical consumers and / or functional units of the galley in order to receive status signals from them, each representing a state of the respective consumer or functional unit. The second computing unit is configured to provide, based on a respective status signal, a display signal at the first interface and / or a cabin input signal at the second coupling interface. The functional units can be, for example, storage containers for drinks or food or trolleys. The status signals can, for example, contain information about the electrical power requirement of a respective consumer, a fill level of a respective container, or similar operating information.This information can be converted into corresponding signals by the second processing unit, which are then visualized on the display device or made accessible via the first processing unit of the HRE. This advantageously enables the implementation of a wide range of control or regulation functions, such as energy management for multiple galleys, where the current power requirements of the other galleys are shown on the display, allowing flight crew to decide whether or not to activate an additional consumer.

[0023] According to one embodiment of the control system, the second computing unit has a camera interface configured to connect to one or more camera devices and to receive image signals provided by the camera device, which represent an image captured by the camera device. The second computing unit is configured to provide image output signals at the first interface based on the image signals, and the display device is configured to display an image captured by the camera device based on the image output signals. According to this embodiment, an interface is provided at the second computing device for an image stream from a camera device, such that this image stream can be displayed on the display device via the second computing device. This allows a cabin monitoring function to be easily integrated into the control system.Since the second processing unit is designed autonomously from the first, the reliability of a cabin monitoring system is also increased. The camera interface can be designed as an Ethernet interface, for example.

[0024] The camera interface is optionally designed to supply electrical power to the camera device. This can be achieved, for example, by designing the camera interface as a Power-over-Ethernet interface.

[0025] According to a further embodiment of the control system, the second processing unit has a WLAN antenna. This enables wireless communication between the second processing unit and other cabin components or other components of the control system. For example, this can enable wireless data exchange with other galley control devices, e.g., data regarding the load requirements of electrical consumers, or with other data distribution devices of the control system.

[0026] Optionally, the WLAN antenna can be configured for communication based on the WAIC standard. WAIC stands for "Wireless Avionics Intra-Communications" and refers to an aviation-specific communications standard for wireless data transmission within an aircraft's closed network. The technical details of this standard are familiar to those skilled in the art and are contained, for example, in the International Telecommunication Union's ITU-R M.2197 report from November 2010.

[0027] Optionally, the first interface and / or the camera interface can be formed by the Wi-Fi antenna. This advantageously reduces the amount of cabling required. Furthermore, the display device can be carried by the flight crew or removed from the galley.

[0028] Alternatively or additionally, the WLAN antenna can be configured for data exchange with a WLAN access point (WAP), which is preferably assigned to a different domain of the aircraft's onboard network than the control system. In particular, the control system can be assigned to a higher security level of the network than the WAP. In this way, data can advantageously be exchanged between the second computing unit and, for example, an application server from which passengers can select services.

[0029] According to a further embodiment of the control system, the second computing unit has an additional supply connection which is designed for connection to an electrical power supply, such that the second computing unit can be supplied with electrical power independently of the first computing unit. Thus, in addition to a supply connection which connects both the first and the second computing unit to an electrical power supply of the aircraft, for example a 28-volt direct current supply, a further supply connection is optionally provided which is specifically intended for the second computing unit. This further increases the reliability of the second computing unit. This additional supply connection can, for example, be integrated into the above-mentioned third connection device of the second computing device.

[0030] According to a further embodiment, the distribution interface of the main processing unit and the first control interface of the first processing unit are connected via a data line. This data line can be formed, in particular, by optical fibers, for example, by fiber optic cables, or by electrical conductors, such as conventional copper wires. Fiber optic cables have the advantage of allowing very high data transmission speeds. Electrical conductors, in contrast, are more cost-effective.

[0031] According to one embodiment of the data distribution device, the first processing unit is formed on a first circuit board, and the second processing unit is formed on a second circuit board. The first and second circuit boards are arranged in a common housing. Accordingly, the first, second, and third connection devices, or recesses for them, are also provided on the housing.

[0032] Alternatively, the first circuit board can be arranged in a first housing and the second circuit board in a separate second housing, with the second housing being attached to the first housing. Accordingly, the two processing units are housed in different housings, which are, however, attached to one another. This achieves a modular design, which is particularly advantageous for retrofitting a second processing unit to an existing data distribution device that already includes a first processing unit. Furthermore, this also allows for better shielding of the second processing unit from the optional WLAN antenna.

[0033] According to a further alternative, the first and second computing units can be formed on a common circuit board.

[0034] "Connected" or "coupled" refers to components of an aircraft's control system or on-board network, or their interfaces, as being connected to one another in a manner suitable for data exchange. This can be achieved, in particular, via wired data lines, such as a bus system, network cables, fiber optic cables, or the like, or by means of wireless data transmission, such as WLAN, Bluetooth, infrared, or the like.

[0035] The invention is explained below with reference to the figures of the drawings. The figures show: Fig. 1 is a simplified plan view of an aircraft according to an embodiment of the present invention; Fig. 2 is a schematic view in block diagram form of a control system according to an embodiment of the present invention; Fig. 3 shows a schematic-functional representation of a data distribution device according to an embodiment of the present invention; Fig. 4 is a simplified perspective view of a data distribution device according to an embodiment of the present invention; and Fig. 5 a simplified perspective view of a data distribution device according to another embodiment of the present invention.

[0036] In the figures, the same reference symbols denote identical or functionally identical components, unless otherwise stated.

[0037] Fig. 1 shows a plan view of an aircraft 100, in particular of a cabin 101 of the aircraft 100. The aircraft 100 has several galleys 102 arranged in the cabin 101. In the Fig. In the aircraft 100 shown by way of example in Figure 1, a total of three galleys 102 are provided, two of which are arranged in an entrance area 103 near the cockpit 104 and near the rear 105 of the aircraft 100, respectively. A further galley 102 is arranged between the other galleys 102 with respect to an aircraft longitudinal axis 106.

[0038] The galleys 102 are in Fig. 1 are merely symbolically represented as blocks and are realized as cabin monuments, i.e., as prefabricated shelf- or cabinet-like units. These can, in particular, feature a multitude of drawers for accommodating containers and / or trolleys or galley carts. Furthermore, the galleys include a multitude of electrical appliances L, e.g., in the form of coffee machines, warming ovens, refrigerators, lighting, or similar.

[0039] The aircraft 100 further comprises an on-board network 200, which is Fig. 2 is shown in a simplified block diagram by way of example. The on-board network N shown as an example comprises a control system 1, an optional operating station in the form of a so-called flight attendant panel 201 (FAP 201 for short), for the flight crew to set and control cabin functions, an optional application server 202, and a layout memory module 203 in the form of a non-volatile memory. Furthermore, the on-board network N can comprise one or more switches 204 and a passenger input device 205.

[0040] Using the FAP 201, flight crew can enter control commands for operating cabin functions, such as lighting, air conditioning, or cabin signals, for example, by pressing a button or flipping a switch. A cabin signal could be, for example, an illuminated signal indicating to a passenger that their seatbelt should be fastened. Furthermore, flight crew can also use the FAP 201 to make cabin announcements or conduct telephone conversations, for example, with the cockpit crew. Commands entered via the FAP 201 are an example of cabin data.

[0041] The application server 202 contains optional services for passengers, such as a music library or a list of food and beverage options. A passenger can request these services, for example, via a passenger input device 205 located at their seat. Passenger input device 205 can be implemented, for example, as a display device similar to a tablet PC with a touch-sensitive surface. The data records contained in the application server 202 also constitute an example of cabin data.

[0042] The layout memory module 203 is a non-volatile data memory, for example a FLASH EEPROM memory, and contains information specific to the respective aircraft 100 about the arrangement and configuration of individual components of the cabin, for example about the number and distribution of seats (not shown) in the cabin 101, about the arrangement and switching levels of the lamps of the cabin lighting (not shown) and the arrangement, shelf layout and electrical consumers L of the individual galleys 102. The data contained in the layout memory module 203 is another example of cabin data.

[0043] The control system 1 comprises a main processing unit 2, abbreviated HRE 2, at least one galley operating device 3, abbreviated BBV 3, and a data distribution device 4, abbreviated DVV 4.

[0044] The HRE 2 has a first interface 21, which is set up to exchange cabin data, and a distribution interface 22. As in Fig. 2, both the FAP 201 and the layout memory module 203 are connected to the HRE 2 via the first interface 21. Optionally, the layout memory module 203 can also be coupled directly to the FAP 201 and connected only via this to the first interface 21 of the HRE. The first interface 21 can be an Ethernet interface, for example. The application server 202 can be connected to the HRE 2, in particular, via a separate additional interface 23, for example in the form of a BUS interface according to an ARINC standard such as ARINC 429, for data exchange. The distribution interface 22 can be designed, for example, as a CAN BUS interface and is used for data exchange between the HRE 2 and the DVV 4. It is also conceivable for the distribution interface to be designed as a fiber optic interface, which is configured to receive and provide optical signals.

[0045] The HRE 2 is configured to provide cabin output signals based on the cabin data at the distribution interface 22 and to receive cabin input signals, in particular to process them into cabin data and optionally provide them at the first interface 21 and / or the additional interface 23. For this purpose, the HRE 2 can comprise a processor (not shown), a memory (not shown), an associated operating system, and processing software.

[0046] The Fig. The control system illustrated by way of example in Figure 2 comprises three BBVs 3A, 3B, and 3C, each of which is assigned to a respective galley 103. The BBVs 3A and 3C are constructed identically and each have a display device 31 and a display device 31 as an input device. No separate display device 31 is provided on the BBV 3B, since the BBV 3B uses the display device of the BBV 3A.

[0047] The display device 31 is configured for inputting control commands and outputting information based on display signals. The display device 31 can, in particular, be designed in the manner of a tablet PC and serves as an input device for the flight crew. For example, the flight crew can select to switch a specific electrical consumer L in the galley on or off using a command displayed by the display device 31. Furthermore, the display device 31 can display information, e.g., about the status of an electrical consumer L, or images captured with a camera device C, based on received display signals.

[0048] The energy control device 32, abbreviated to ESE 32, has a supply input 32a, a plurality of supply outputs 32b, and a control interface 32c. The supply input 32a is designed for connection to an electrical power supply F of the aircraft 100, for example, to a 115 volt AC power system of the aircraft 100, as shown in Fig. 2 is symbolically represented. The number of supply outputs 32b can, in particular, correspond to the number of electrical consumers L. The supply outputs 32b serve to connect the electrical consumers L of the galley 102. The control interface 32c is configured to receive switching signals from the DVV, as will be explained in detail below, and can be implemented as a BUS interface, for example as a CAN BUS or as an ARINC 812 interface.

[0049] The ESE 32 is configured to establish or interrupt an electrical connection between each of the load outputs 32b and the supply input 32a. The ESE 32 thus forms a switching device that switches the individual loads L on or off. The ESE is optionally configured as an electrical overload protection device, which automatically switches off the respective load L if a threshold current flow is reached. For this purpose, the ESE 32 can comprise a plurality of relays (not shown), in particular solid-state relays.

[0050] The BBV 3 can in particular be arranged directly on the respective galley 102, as shown in Fig. 2 is symbolically represented by the dashed line representing the galley 102. For example, the display device 31 can be attached, preferably detachably, to the cabin monument of the galley 102. The ESE 32 can also be integrated into the cabin monument 32 of the galley 102.

[0051] The DVV 4 is arranged spatially separate from the BBV 3, in particular separate from the galley 102. For example, the DVV 4 can be arranged in the area to the side of an entrance door 107, e.g., beneath an interior panel or interior cover (not shown) that covers the fuselage structure of the aircraft 100 toward the cabin interior. This spatial separation is extremely advantageous because it eliminates the need to provide additional space at the galley 102, allowing the galley 102 to be more compact and / or the space available for the galley 102 to be used more efficiently.

[0052] Fig. 3 shows an exemplary and schematic view of the DVV 4. The DVV has a first processing unit 41, a second processing unit 42, and an interface circuit 44. The first processing unit 41 preferably comprises a first processor 401, a first data memory 402, a first connection device 411, and a second connection device 412. The connection devices 411, 412 can, for example, be designed as plug sockets and have electrical contacts for conductive connection to the processor 401. The first connection device 411 contains at least one first control interface 41a. The second connection device 412 has at least one second interface 42b. Fig. 3, the second connection device 412 shown as an example has a total of five second interfaces 42b. The first connection device 411 can have, for example, Ethernet and / or CAN bus interfaces as first control interfaces 41a. It is also conceivable for the first control interface 41a to be embodied as a fiber optic interface configured to receive and provide optical signals. The first processing unit 41 further comprises an operating system.

[0053] The second computing unit 42 preferably has a second processor 403, a second data memory 404, a third connection device 423, an optional additional supply connection 45, and an optional WLAN antenna 43. The third connection device 423 and the additional supply connection 45 can each be designed as a plug socket and have electrical contacts for conductive connection to the processor 403. The third connection device 423 has a first interface 42a and a second interface 42b. In addition, an optional camera interface 42d and optional further functional interfaces 42e can be provided. The first interface 42a is designed, for example, as an Ethernet interface, preferably a Power-over-Ethernet interface. The second interface 42b is preferably a BUS interface, e.g., a CAN-BUS or an ARINC-812 interface.The camera interface 42d can, in particular, be an Ethernet interface, preferably a Power-over-Ethernet interface. The other optional functional interfaces 42e can also include (Power-over-)Ethernet interfaces and / or bus interfaces such as CAN-BUS or ARINC-812 interfaces. Instead of two processors 401, 403, only a single processor and an additional FPGA can be provided.

[0054] The WLAN antenna 43 is particularly designed for communication based on the WAIC standard. Optionally, the WLAN antenna 43 can also form the first interface 42a of the second processing unit 42 and / or the camera interface 42d. Furthermore, it is conceivable that the WLAN antenna 43 forms an interface for data exchange with a WLAN access point 206, abbreviated to WAP 206, of the on-board network 200.

[0055] The interface circuit 44 forms a first coupling interface 41c of the first processing unit 41 and a second coupling interface 42c of the second processing unit 41. The interface circuit 44 can be designed, for example, as a serial interface and connects the first and second processing units 41, 42 such that they can exchange data. In particular, the interface circuit 44 forms a data filter that only permits the exchange of certain data in order to prevent the second processing unit 42 from being impaired in its function by an operating error of the first processing unit 41. The first and second processing units 41, 42 also have separate operating systems and are thus autonomous.

[0056] The first and second processing units 41, 42 can be supplied with power, for example, via the first connection device 411. For example, the first connection device 411 can contain a Power-over-Ethernet interface (not shown) for this purpose. The optional additional supply connection 45 is designed as a redundant supply connection for connection to an electrical power supply F of the aircraft, so that the second processing unit 42 can be supplied with electrical power independently of the first processing unit 41. For example, the second processing unit 42 can be connected via the additional supply connection 45 to a 28 volt DC power supply of the aircraft 100, as shown in Fig. 3 is shown as an example.

[0057] As in Fig. As shown in Figure 2, the first control interface 41a of the first processing unit 41 is connected to the distribution interface 22 of the HRE 2. The second interface 41b of the first processing unit 41 is connected to a cabin component 108 for activating a cabin function. The cabin component 108 can, for example, be a cabin illuminated sign, such as a seatbelt light, which, as a cabin function, signals to the passenger that the seatbelts should be fastened. Other cabin components can, for example, be smoke sensors, switches, lamps for the cabin lighting, or control lights on control panels (so-called attendant indication panels) for the flight crew.

[0058] As in Fig. 2 is still shown and based on the Fig. 3, the first coupling interface 41c of the first computing unit 41 and the second coupling interface 42c of the second computing unit 42 are connected to one another.

[0059] In Fig. 2 also shows that the first interface 42a of the second processing unit 42 is connected to the display device 31, and the second interface 42b of the second processing unit 42 is connected to the control interface 32c of the ESE 32 of the galley operating device 3. Optionally, the second interface 42b of the second processing unit 42 can additionally be connected to one or more of the electrical consumers L or other functional units of the galley of the galley 102, such as trolleys or the like. This makes it possible, for example, to receive status signals from a sensor mounted there, which represent the current energy consumption of the consumer(s) L, the fill level of a trolley, or other status information. As shown in Fig. 2, the second processing unit 42 of the BBV 3A can additionally be connected to the ESE 32 of the further BBBV 3B. This can be realized, for example, via one of the additional functional interfaces 42e (in Fig. 2 not shown).

[0060] The first processing unit 41 is configured to provide an actuation signal for actuating a cabin function at one or more of the second control interfaces 41b based on a cabin output signal received from the main processing unit 2. For example, the flight crew can enter a command to activate the fasten seatbelt sign at the FAP 201. This command is forwarded as a packet of cabin data to the HRE 2, which generates a corresponding cabin output signal therefrom and provides it at the distribution interface 22. The first processing unit 41 receives this cabin output signal at the first control interface 41a and generates a corresponding actuation signal therefrom, which it provides at the second control interface 41b. At the cabin component 108, in this case the fasten seatbelt sign in the form of a cabin illuminated sign, is switched on by the actuation signal.In addition, the first computing unit 41 is configured to provide the received cabin output signals to the first coupling interface 41c, i.e. to transmit a corresponding data set to the second computing unit 42.

[0061] The second computing unit 42 is configured to provide a display signal at the first interface 42a based on a cabin output signal received at the second coupling interface 42c. In the above-mentioned example, according to which the cabin output signal represents a command to switch on the seat belt signs, the second computing unit 42 generates a display signal from this signal, which can be reproduced as an image by the display device. In this way, information about the status of the seat belt signs can be made available to the flight crew on the display device. A particular advantage of the control system 1 is that cabin information can be made accessible to the flight crew in a simple manner at the galley 103, without requiring additional installation space in the galley.It is conceivable, for example, that the user interface displayed by the display device 31 is always synchronized with the input state of the FAP 201.

[0062] The second computing unit 42 is also configured to provide a switching signal at the second interface 42b based on a control command received from the display device 31, which causes the ESE 32 to establish or interrupt an electrical connection between one or more of the consumer outputs 32b and the supply input 32a. Thus, by making a corresponding input via the user interface of the display device 31 of the BBV 3A, the operating personnel can switch the consumers L of the galley 103 connected to the ESE 32 of the BBV 3A and the consumers L of the galley 103 connected to the ESE 32 of the BBV 3B on or off individually or in groups.

[0063] If several galleys 103 are present, these can either be connected with their ESEs 32 to a common DVV 4, as shown in Fig. 2 for the BBVs 3A and 3B. Alternatively or additionally, several DVVs 4 can be provided. In Fig. 2, for example, another DVV 4 of the galley 103 is functionally assigned to the BVV 3C. Since all DWs 4 are coupled to the HRE 2 via the first control interface 41a of the first processing unit 41, data exchange between the DVVs 4 can take place in a simple manner. Due to the possible data exchange between the first and second processing units 41, 42, galley-specific status information, such as energy consumption or food inventory in the respective galley, can be exchanged as cabin input and output signals via the HRE 2. In this way, a variety of advantageous functionalities can be implemented, such as energy management for the galleys 103 in order to optimize the utilization of the energy supply F.

[0064] Furthermore, the HRE 2 advantageously forms an interface to the application server 202. The services requested by passengers can thus be easily converted into cabin output signals, forwarded to the DWs 4, and provided there as display signals at the first interface 42a via the second processing unit 42 due to the interface circuit 43. This enables the operating personnel to display information about a service requested by a passenger on the display device 31 on the galley 103 in an extremely efficient and simple manner.

[0065] As in Fig. 2, the optional camera interface 42d is connected to a camera device C, which, for example, records a surveillance video of at least one area of ​​the cabin 101. The camera device C can therefore be coupled to the control system 1 via the optional camera interface 42d. For this purpose, the optional camera interface 42d is configured to connect to one or more camera devices C and to receive image signals provided by the camera device C, which represent an image captured by the camera device C. As already explained above, the camera interface 42d is implemented, for example, as a Power-over-Ethernet interface, so that the camera device C can also be supplied with power via this interface.

[0066] The second computing unit 42 is configured to provide image output signals at the first interface 42a based on the image signals. The image output signals thus represent a special form of display signals. The display device 31 is accordingly configured to display an image captured by the camera device C based on the image output signals. Put simply, the surveillance video from the camera device C can be displayed on the display device 31. In this way, a surveillance system can be coupled to the control system 1. Since the first and second computing devices 41, 42 are independent of one another, the reliability of the surveillance system is improved.

[0067] As already explained, the WLAN antenna 43 can be configured for data exchange with the WAP 206 as well as for data exchange with further second computing devices 42 of further DWs 4 of the control system 1. The second computing unit 42 is therefore optionally configured to provide a WLAN output signal at the WLAN antenna 43. The WLAN output signal can be, for example, a cabin input signal, a display signal, a switching signal, or a status signal representing a state of a consumer L or a functional unit of a galley 103. For example, status information from functional units of the galley 103 can be transmitted from the second computing unit 42 directly to the application server 202 via the WAP 206. For example, this can be used to store in the application server 202 whether a particular beverage or other service is still available.Furthermore, a display signal can be transmitted to the display device 31. This saves cabling effort and allows flight personnel to remove the display device 31 from the galley 103 and carry it with them without disruptive cabling. Furthermore, signals can be exchanged between the second processing units of the various DWs 4.

[0068] As in Fig. 2, the FAP 201, the layout memory module 203, the switch 204, and the components of the control system 1, except for the ESE 32, are assigned to a first domain 221 of the on-board network 200. The ESE 32 of the control system 1, the application server 202, the passenger input device 205, and the WAP 206 are assigned to a second domain 222 of the on-board network 200. The first domain 221 has a higher security level than the second domain 222. In particular, it can be provided that the second domain 222 does not contain any flight safety-relevant functions, and the components of the second domain 222 do not have access to functions of the first domain 221.

[0069] As in Fig. 2, the control system 1 may additionally comprise one or more additional data distributors 5, abbreviated to ZDV 5. In Fig. 2, only an additional data distributor 5 is shown, which is connected to the HRE 2. Preferably, a first interface 51 of the ZDV 5 is connected to the distributor interface 22 or to an additional interface of the HRE (not shown). The ZDV 5 can have a similar structure to the first processing unit 41 of the DVV 4, i.e., it can contain a processor and a memory. Furthermore, the ZDV 5 comprises one or more second interfaces 52, to which cabin components 108 are connected. The ZDV 5 is configured to provide an actuation signal for actuating a cabin function of the cabin component 108 at one or more of the second interfaces 52 based on a cabin output signal received from the main processing unit 2. Optionally, the ZDV 5 can also be configured to receive feedback signals from the cabin component 108 at the second interface, e.g.in the form of signals representing the power requirement, the operating status or similar status information of the cabin component 108, and to provide received feedback signals at the first interface 51 as cabin input signals.

[0070] Optionally, different groups of cabin components 108 can be assigned to the ZDV 5 and the first computing device 41 of the DVV 4. For example, only those cabin components 108 whose operation must be ensured throughout the entire flight operation of an aircraft can be assigned to the first computing device 41 of the DVV4, while only comfort functions, such as reading lights for passengers, are assigned to the ZDV 5 as cabin components 108.

[0071] The optional switch 204 of the on-board network 204 is connected, for example, via Ethernet, to the FAP 201. Optionally, the switch 204 can alternatively or additionally be connected to one of the functional interfaces 42e of the second computing device 42 of the DVV4, for example, via a Power over Ethernet connection. In this way, additional systems or components, such as an additional cabin monitoring system with one or more camera devices, can optionally be integrated into the on-board network 200 and / or coupled to the control system 1.

[0072] Fig. Figure 4 schematically shows an exemplary design of a DVV 4. This comprises a housing 470 and a base plate 473. The base plate 473 has several fastening devices 474, which are provided for fastening the base plate 474 to a structural component (not shown) of the aircraft 100. In Fig. 4, the base plate 473 has a rectangular shape and four fastening devices 474, which are provided in the corners of the base plate.

[0073] As in Fig. 4, the first computing unit 41 and the second computing unit 42 are arranged in the housing 470, i.e., in an interior space defined by the housing 470 and the base plate 473. The first computing unit 41 is formed on a first printed circuit board 450, for example, in the form of the first processor 401 (in Fig. 4 not shown) and the first memory 402 (in Fig. 4 not shown).

[0074] The second computing unit 42 is formed on a second circuit board 455, for example in the form of the second processor 403 (in Fig. 4 not shown) and the second memory 404 (in Fig. 4 not shown). The optional WLAN antenna 43 can also be formed on the second circuit board 455. Alternatively, the computing unit 42 can have a further circuit board 456 on which the WLAN antenna 43 is formed, as shown by way of example in Fig. 4. Furthermore, both computing units 41, 42 can also be formed on a single circuit board 450, 455. The WLAN antenna 43 can also be arranged on this common circuit board.

[0075] As in Fig. 4, the first and second circuit boards 450, 455 are arranged in a common housing 470. For example, the first circuit board 450 can be arranged directly adjacent to the base plate 474, while the second circuit board 455 and the optional additional circuit board 456 are arranged on the side of the first circuit board 450 facing away from the base plate 474. Furthermore, the second circuit board 455 and the optional additional circuit board 456 are arranged such that they only overlap a portion of the first circuit board 450.

[0076] The interface circuit 44 may be formed on an interface circuit board 444. As shown in Fig. 4, the interface circuit board 444 can extend transversely from the base plate 474. Several slots (not shown) can be provided on the interface circuit board 444, into which the first circuit board 450, the second circuit board 455, and the optional additional circuit board 456 are plugged.

[0077] As in Fig. 4, several recesses are formed on the housing 470, into which the first connection device 411, the second connection device 412, and the third connection device 423 are inserted. Optionally, a further connection device 413 of the first computing device 41 can be provided, which contains one or more of the second control interfaces 41b of the first computing unit 41. In Fig. 4, the connection devices 411, 412, 413, and 423 are schematically illustrated as plug sockets. The first and second connection devices 411, 412 of the first computing unit 41 are provided on a cover plate 475 of the housing 470, which extends along the base plate 473. The third connection device 423 of the second computing device 42 is provided in the area of ​​the interface circuit board 444. In this way, a connector plug S, which is intended for connection to the BBV 3, can be plugged in in a space-saving manner, as shown in Fig. 4 is shown schematically and by way of example.

[0078] The Fig. 5 DVV 4 shown as an example differs from that of the Fig. 4 in that the first circuit board 450 is arranged in a first housing 471, which is preferably closed, and the second circuit board 455 and the optional further circuit board 456 are arranged in a separate second housing 472. The first housing 471 has a flat cover plate 475. The second housing 472 can, for example, be designed in the form of a flat cuboid and be configured such that contact devices (not shown) provided on an end face 472A can be contacted to the interface circuit board 444, for example by being plugged into it, as shown in Fig. 5 is indicated by the arrow P.

[0079] The second housing 472 is fastened to the first housing 471, for example by means of fastening devices 476 provided on the second housing 472.

[0080] Although the present invention has been explained above using exemplary embodiments, it is not limited thereto but can be modified in a variety of ways. In particular, combinations of the above embodiments are also conceivable. LIST OF REFERENCE SYMBOLS 1 control system 2 Main processing unit 3, 3A, 3B, 3C galley control device 4 Data distribution device 5 additional data distributors 21 first interface of the main processing unit 22 Distribution interface of the main processing unit 31 Display setup 32 Energy control device 32a Supply input of the energy control device 32b Supply outputs of the energy control device 32c Control interface of the energy control device 41 first computing unit of the data distribution device 41a first control interface of the first computing unit 41b second control interfaces of the first computing unit 41c first coupling interface of the first computing unit 42 second computing unit of the data distribution device 42a first interface of the second computing unit 42b second interface of the second computing unit 42c second coupling interface of the second computing unit 42d Camera interface of the second processing unit 42e Functional interfaces of the second processing unit 43 WLAN antenna of the second processing unit 44 Interface circuit 45 Additional supply connection of the second computing unit 51 first interface of the additional data distributor 52 second interface of the additional data distributor 100 aircraft 101 cabin 102 galley 103 Entrance area 104 Cockpit 105 Rear 106 Aircraft longitudinal axis 107 Entrance door 108 cabin components 200 on-board network 201 Flight Attendant Panel 202 application servers 203 Layout memory module 204 Switch 205 Passenger input device 206 WLAN access point 221 first domain of the on-board network 222 second domain of the on-board network 401 first processor of the first computing unit 402 first data memory of the first computing unit 403 second processor of the second computing unit 404 second data memory of the second computing unit 411 first connection device of the first computing device 412 second connection device of the first computing device 413 additional connection device of the first computing device 423 third connection device of the second computing device 444 Interface board 450 first circuit board 455 second circuit board 456 additional circuit boards 470 housing 471 first housing 472 second housing 472A Front side of the second housing 473 base plate 474 Fastening device 475 cover plate 476 fastening devices C Camera setup F electrical power supply L electrical consumption P Arrow S connector plug

Claims

[1] Control system (1) for a cabin (101) of an aircraft (100), comprising: a main processing unit (2) with a first interface (21) which is set up to exchange cabin data, and a distribution interface (22), wherein the main processing unit (2) is configured to provide cabin output signals based on the cabin data and to receive cabin input signals at the distribution interface (22), at least one galley operating device (3; 3A, 3C) with a display device (31) which is arranged to input control commands and to output information based on display signals, and an energy control device (32) with a supply input (32a) which is designed for connection to an electrical energy supply (F) of the aircraft, with a plurality of supply outputs (32b) which are designed for connecting electrical consumers (L) of an on-board galley (102), and with a control interface (32c), wherein the energy control device (32) is designed to establish or interrupt an electrical connection between each of the consumer outputs (32b) and the supply input (32a), a data distribution device (4) spatially separated from the galley operating device (3, 3A, 3C) with a first processing unit (41) having a first control interface (41a) connected to the distribution interface (22) of the main processing unit (2), having a plurality of second control interfaces (41b), and having a first coupling interface (41c), wherein the first computing unit (41) is configured to provide an actuation signal for actuating a cabin function at one or more of the second control interfaces (41b) on the basis of a cabin output signal received from the main computing unit (2) and to provide received cabin output signals at the first coupling interface (41c), and a second computing unit (42) autonomous from the first computing unit (41) having a first interface (42a) connected to the display device (31), a second interface (42b) connected to the control interface (32c) of the energy control device (32) of the galley operating device (3, 3A, 3C), and a second coupling interface (42c) connected to the first coupling interface (41c) of the first computing unit (41), wherein the second computing unit (42) is configured to provide a switching signal at the second interface (42b) on the basis of the control command received from the display device (31), which switching signal causes the energy control device (32) to establish or interrupt an electrical connection between one or more of the consumer outputs (32b) and the supply input (32a), and which is configured to provide a display signal at the first interface (42a) on the basis of a cabin output signal received at the second coupling interface (42c). [2] Control system (1) according to claim 1, wherein the second interface (42b) is further designed for connection to the electrical consumers (L) and / or to functional units of the galley in order to receive status signals from them in each case, which represent a state of the respective consumer (L) or of the respective functional unit, and wherein the second computing unit (42) is designed to provide a display signal at the first interface (42a) and / or a cabin input signal at the second coupling interface (42c) on the basis of a respective status signal. [3] Control system (1) according to claim 1 or 2, wherein the second computing unit (42) has a camera interface (42d) which is configured for connection to one or more camera devices (C) and for receiving image signals provided by the camera device (C) which represent an image captured by the camera device (C), wherein the second computing unit (42) is configured to provide image output signals at the first interface (42a) on the basis of the image signals, and wherein the display device (31) is configured to display an image captured by the camera device (C) on the basis of the image output signals. [4] Control system (1) according to claim 3, wherein the camera interface (42d) is designed to supply electrical energy to the camera device (C). [5] Control system (1) according to claim 4, wherein the camera interface (42d) is designed as a Power-over-Ethernet interface [6] Control system (1) according to one of the preceding claims, wherein the second computing unit (42) has a WLAN antenna (43). [7] Control system (1) according to claim 6, wherein the WLAN antenna (43) is designed for communication based on the WAIC standard. [8] Control system (1) according to claim 6 or 7, wherein the first interface (42a) and / or the camera interface (42d) is formed by the WLAN antenna (43). [9] Control system (1) according to one of claims 6 to 8, wherein the WLAN antenna is configured for data exchange with a WLAN access point (206) of an on-board network (200) of the aircraft (100). [10] Control system (1) according to claim 9, wherein the WLAN access point (206) is assigned to a different domain of the on-board network (200) than the control system (1). [11] Control system (1) according to one of the preceding claims, wherein the second computing unit (42) has an additional supply connection (45) which is designed for connection to an electrical energy supply (F), so that the second computing unit (42) can be supplied with electrical energy independently of the first computing unit (41). [12] Control system (1) according to one of the preceding claims, wherein the distribution interface (22) of the main processing unit (2) and the first control interface (41a) of the first processing unit (41) are connected by means of a data line, wherein the data line is preferably formed by optical fibers or by electrical conductors. [13] On-board network (200) for an aircraft comprising: a control system (1) according to one of the preceding claims; and a layout memory module (203) which is designed to store specific information on the arrangement and to store the configuration of individual components of a cabin of the aircraft (100) as cabin data; wherein the layout memory module (203) is connected to the main processing unit (2) via the first interface (21). [14] Data distribution device (4) for a control system (1) according to one of claims 1 to 12, comprising: a first computing unit (41) with a first connection device (411) having a first control interface (41a) and a second connection device (412) having a second control interface (42b); a second computing unit (42) with a third connection device (423) which has a first interface (42a) and a second interface (42b), an interface circuit (44) which forms a first coupling interface (41c) of the first computing unit (41) and a second coupling interface (42c) of the second computing unit (41) and connects them to one another. [15] Data distribution device (4) according to claim 14, wherein the first computing unit (41) is formed on a first circuit board (450) and the second computing unit (42) is formed on a second circuit board (455), and wherein the first and the second circuit board (450, 455) are arranged in a common housing (470) or the first circuit board (450) is arranged in a first housing (471) and the second circuit board (455) is arranged in a separate second housing (472), wherein the second housing (472) is attached to the first housing (471). [16] Data distribution device (4) according to claim 14, wherein the first computing unit (41) and the second computing unit (42) are formed on a common printed circuit board (450; 455) [17] Aircraft (100), comprising a galley (102) with several electrical loads (L), a control system (1) according to one of claims 1 to 12, wherein an electrical load (L) of the galley (102) is connected to a respective supply output (32b) of the energy control unit (32), wherein the supply input (32a) of the energy control unit (32) is connected to an electrical supply network (F) of the aircraft (100), wherein the display device (31) is arranged on the galley (102), and wherein the data distribution device (4) is arranged spatially separated from the galley (102).

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