Modular components for hybrid networks in aircraft and aircraft

Abstract

The present application relates to a modular element (60) for a hybrid power distribution and data communication network (600) for an aircraft, comprising a section (20t) of a bus and a set of data links (50t) extending substantially in parallel along the length (L) of the modular element. The bus section comprises connection points (24) at different positions distributed along its length. The data link set comprises connection points (54) at different positions distributed along its length, each arranged near the connection point (24) of the bus section. The data link set also comprises a data link (56) between each connection point and a cross connection point (55, 55a, 55b). The bus section (20t) and the data link set (50t) comprise interconnection points (27a, 57a, 27b, 57b) which enable the modular element to be linked to a first other modular element and a second other modular element arranged longitudinally in series with the modular element. The present application also relates to an aircraft comprising the modular element.

Description

Technical Field

[0001] The present invention relates to the field of power supply to equipment items of an aircraft. An aircraft, in particular a transport aircraft, comprises electrical equipment items distributed in particular in its fuselage. These electrical equipment items must be electrically powered and for some of these electrical equipment items must be linked to a data communication network. To this end, the aircraft comprises power cable harnesses and data communication cable harnesses. The power cable harnesses typically extend between the electrical core of the aircraft (notably allowing the arrival of power from power generation and / or conversion sources) and the electrical equipment items to be powered. Communication cable harnesses typically extend between communication equipment items of the aircraft, such as switches complying with part 7 of the ARINC 664 standard, and electrical equipment items linked to these communication equipment items. Background Art

[0002] In modern aircraft, more and more functions are implemented electrically. These functions sometimes require more different voltages than in older generation aircraft (e.g., 28VDC, 115VAC, 230VAC, 270VDC, 540VDC) and require numerous data communication links between different equipment items of the aircraft. As a result, the wiring harness is more complex, larger in capacity and heavier than in older generation aircraft. The implementation of the wiring harness is also more complex. Therefore, it would be desirable to simplify the power distribution and data links of the electrical equipment items of the aircraft.

[0003] Different wiring harnesses are specific to each type of aircraft and also vary with the aircraft configuration specific to the airline operating this aircraft. For example, depending on whether certain electrical equipment items are installed or not installed in the fuselage, the wiring harness includes or does not include cables allowing power supply and data links for said equipment items. As a result, the list of electrical equipment items that must be installed in a specific aircraft must be fully defined and fixed long before the production of said aircraft, so that the wiring harness specific to this aircraft can be designed, produced and installed in a timely manner. This list must be defined in advance because aircraft are usually produced by assembling fuselage sections in which wiring harness sections are pre-installed, after which the wiring harness sections are connected to each other. Now, it would be desirable to be able to modify the list of electrical equipment items that must be installed in said aircraft before an even earlier stage in the production of said aircraft.

[0004] Furthermore, since the wiring harness is produced specifically according to the list of electrical equipment items installed in the aircraft and the location of said equipment items in the fuselage, it is difficult to modify the aircraft configuration after the aircraft has been delivered to the airline. Now, such modifications may be necessary, for example, when the aircraft is resold to another airline or in the event that the airline wants to add new electrical equipment items in the aircraft. It would therefore be desirable to be able to modify the list and location of the electrical equipment items of an aircraft more easily. Summary of the invention

[0005] It is an object of the present invention, among other things, to provide at least a partial solution to these problems.

[0006] According to a first aspect of the present invention, the present invention relates to an aircraft, the aircraft comprising:

[0007] -body;

[0008] - a group of generators, the group of generators comprising at least a first generator and a second generator;

[0009] - a group of items of electrical equipment distributed in the fuselage; and

[0010] - an electricity distribution network, said electricity distribution network comprising:

[0011] - a bus group, the bus group comprising at least a first bus and a second bus; and

[0012] -Switch system.

[0013] The following are the things worth noting about this aircraft:

[0014] - Each bus of the bus group extends at least partially in the longitudinal direction of the fuselage;

[0015] - the first bus and the second bus follow isolated paths in the fuselage;

[0016] - the switching system is electrically linked to the first generator and the second generator and to the first bus and the second bus;

[0017] - the switching system comprises a so-called normal operating mode in which the switching system is configured for electrically linking the first generator to the first bus and for electrically linking the second generator to the second bus;

[0018] - each bus in the bus set comprises connection points at different positions distributed along its length; and

[0019] - Each of the items of electrical equipment in the group of items of electrical equipment is linked to a connection point of a bus in the group of buses via a local power supply line.

[0020] The bus group corresponds to the unchanged infrastructure of the power distribution network of the aircraft. Different electrical equipment items are each linked to the connection point of the bus by a local power supply line. Therefore, it is possible to easily add new electrical equipment items to the fuselage without modifying this infrastructure: for this purpose, it is sufficient to install a local power supply line between this new equipment item and the connection point of the bus. Preferably, this connection point is selected to be as close as possible to the new electrical equipment item on the bus under consideration, specifically to facilitate the installation of a local power supply line between the electrical equipment item and the bus. This addition of new electrical equipment items can also be provided during the production of the aircraft and during the modification of the aircraft configuration after the aircraft is delivered to the airline. For example, it is also easy to move the electrical equipment items in the fuselage of the aircraft when modifying the aircraft configuration: for this purpose, it is sufficient to remove its original local electrical supply line, move the electrical equipment item to its new position in the fuselage and install a new local power supply line to another connection point of the bus. Using a bus group instead of a cable harness also enables the weight and cost of the power distribution network of the aircraft to be reduced. Indeed, the electrical conductors of a bus used in common by several items of electrical equipment require smaller dimensions than the sum of the dimensions of the individual cables in the wiring harness that power these same items of electrical equipment. Assuming that the first bus and the second bus follow isolated paths in the fuselage, in normal operating mode, the two buses are completely independent of each other and the buses do not run the risk of being jointly exposed to faults or damage (for example, in the event of an engine explosion...). The power supply to the items of electrical equipment linked to a bus is therefore completely independent of the other bus. Therefore, in the event of a fault affecting one of the buses, only the items of electrical equipment linked to the connection points of this bus risk losing their power supply. The items of electrical equipment linked to the other bus then continue to be powered normally, since their power supply is completely independent of the bus affected by the fault.

[0021] According to different embodiments which can be implemented independently of each other or in combination:

[0022] - the first bus also extends partially in the first wing of the aircraft, and the second bus also extends partially in the second wing of the aircraft;

[0023] - the first generator and the second generator are electrically linked to the switching system via a bus. Advantageously, the first generator is electrically linked to the switching system via dedicated conductors of the first bus and the second generator is electrically linked to the switching system via dedicated conductors of the second bus;

[0024] - the power distribution network further comprises a third bus and a fourth bus, the buses extending at least partially in the longitudinal direction of the fuselage, the first bus, the second bus, the third bus and the fourth bus following an isolated path in the fuselage of the aircraft. Advantageously, the set of generators further comprises a third generator and a fourth generator, and in the normal operating mode, the switching system is configured for electrically linking the third generator to the third bus and electrically linking the fourth generator to the fourth bus;

[0025] - the switching system comprises a so-called reconfigured operating mode which can be activated in case of a fault in the electricity distribution network, in which operating mode the switching system is configured to:

[0026] . establishing electrical links between generators in the set of generators and buses in the set of buses, these electrical links being modified compared to the electrical links established in the normal operating mode; and / or

[0027] . Establishing an electrical link between the buses in the bus group;

[0028] - the switching system comprises a main switching device and at least one auxiliary switching device remote from the main switching device. Advantageously, in a reconfigured operating mode of the switching system, the at least one auxiliary switching device can be controlled to establish one or more electrical links between buses in the bus group;

[0029] - at least one of the buses of the bus group comprises at least two modular sections arranged end to end and electrically linked to each other. Advantageously, the auxiliary switching device is electrically linked to two consecutive modular sections of the bus so as to establish an electrical link between similar electrical conductors of the two modular sections in normal operating mode and to establish an electrical link between electrical conductors of at least one of the two modular sections on the one hand and electrical conductors of the other bus on the other hand in a reconfigured operating mode.

[0030] According to a second aspect of the present invention, the present invention relates to a modular element for a hybrid power distribution and data communication network for an aircraft. The modular element is noteworthy in that it comprises:

[0031] - a section of a power distribution bus extending along the length of the modular element; and

[0032] - a set of data links extending along the length of the modular element substantially parallel to the bus section,

[0033] And in that:

[0034] - the bus section comprises connection points at different positions distributed along its length;

[0035] - the data link group comprises connection points at different positions distributed along its length and each arranged near a connection point of the bus section;

[0036] - said data link set comprises connection points, called cross-connection points, provided for receiving a cross-connection frame;

[0037] - said set of data links comprises at least one data link between each of said connection points distributed along its length on the one hand and said cross-connection point on the other hand;

[0038] - the bus segment and the data link group each comprise a first interconnection point provided for linking the bus segment and the data link group, respectively, to a bus segment and a data link group of a first other modular element arranged longitudinally in series with the modular element at a first longitudinal end of the modular element; and

[0039] -The bus segment and the data link group each include a second interconnection point, which is provided for linking the bus segment and the data link group to the bus segment and the data link group of a second other modular element arranged longitudinally in series with the modular element at a second longitudinal end of the modular element opposite to the first longitudinal end.

[0040] Assembling modular elements according to the invention makes it possible to construct a hybrid power distribution and data communication network for an aircraft. With regard to power distribution, this network offers the same advantages as those described with reference to the first aspect of the invention. This network also offers similar advantages with regard to data communication. Using modular elements according to the invention to construct the network makes it possible to easily adapt this network to any type of aircraft, without requiring a bus or a plurality of data link groups that are specific to the aircraft under consideration, in particular with regard to their length. Using one or more types of modular elements of predetermined length makes it possible to adapt such a network to any aircraft and also makes it possible to combine and minimize development costs.

[0041] According to different embodiments which can be implemented independently of each other or in combination:

[0042] - Data links correspond to optical fibers;

[0043] - said cross-connection point comprises a subgroup of data links terminating in at least one connector, called a cross-connect connector, provided for incorporation in said cross-connection frame. Advantageously, said cross-connection point further comprises at least one fixing provided for allowing fixing of said cross-connection frame to said modular elements. And advantageously:

[0044] . said cross-connection point on the one hand and said first interconnection point of said set of data links on the other hand being located in the vicinity of said first longitudinal end of said modular element;

[0045] said first interconnection point of said set of data links comprises a sub-set of data links terminating at least one connector referred to as a first interconnection connector; and

[0046] . the arrangement of said cross-connect points and said first interconnection points is provided for allowing said cross-connect connector and said first interconnection connector to be incorporated in said cross-connect frame so as to enable linking of said set of data links to said set of data links of said first other modular element in said cross-connect frame;

[0047] - The modular elements are such that:

[0048] The connection points distributed along the bus section and the connection points distributed along the data link group, each arranged near the connection point of the bus section, form a plurality of pairs of connection points distributed along the modular element; and

[0049] . Each pair of connection points is provided for receiving a hybrid power distribution and data communications junction box, the junction box being configured to allow connection of one or more local power distribution and / or data distribution links to one or more items of electrical equipment of the aircraft;

[0050] The bus section comprises at least one flexible portion provided for allowing the modular element to deform in response to deformations of the fuselage of an aircraft when the modular element is mounted in the fuselage of the aircraft.

[0051] The present invention also relates to an aircraft, the aircraft comprising a fuselage and a group of electrical equipment items distributed in the fuselage. The aircraft is noteworthy in that:

[0052] - the aircraft comprises a hybrid power distribution and data communications network comprising a modular set of elements as described above; and

[0053] - Each of the items of electrical equipment of the group of items of electrical equipment is linked to a connection point of the bus section of a modular element via a local power supply link and / or to a connection point of the group of data links of the modular element by a local data link.

[0054] In a specific embodiment:

[0055] - the modular elements of a first subset of said set of modular elements are assembled together so as to form a first hybrid power distribution and data communication sub-network extending longitudinally at least partially in said fuselage of said aircraft;

[0056] - the modular elements of a second subset of said set of modular elements are assembled together so as to form a second hybrid power distribution and data communications subnetwork extending longitudinally at least partially in said fuselage of said aircraft; and

[0057] - The first sub-network and the second sub-network follow isolated paths in the fuselage.

[0058] In another specific embodiment, which may be combined with the previous embodiments, two consecutive modular elements are electrically linked to each other by means of:

[0059] - at least one flexible connection; or

[0060] - at least one connecting element configured to slide on said section of the bus of at least one of said two modular elements.

[0061] In yet another specific embodiment which can be combined with the previous embodiments, said cross-connection frame of the modular elements receives:

[0062] - an interconnection connector of said first other modular element; and

[0063] - a set of links between said first interconnection connector of said modular element and said interconnection connector of said first other modular element.

[0064] According to a third aspect of the present invention, the present invention relates to an aircraft, the aircraft comprising:

[0065] -body;

[0066] - a group of items of electrical equipment distributed in the fuselage; and

[0067] -Hybrid power distribution and data communications networks.

[0068] The following are the things worth noting about this aircraft:

[0069] - The hybrid power distribution and data communication network comprises:

[0070] - a bus group comprising at least one power distribution bus; and

[0071] - at least one data link group,

[0072] - said hybrid power distribution and data communication network is configured in such a way that each bus of said bus group is associated with a data link group;

[0073] - Each bus of the bus group extends at least partially in the longitudinal direction of the fuselage;

[0074] - each data link group extends substantially parallel to said bus with which it is associated;

[0075] - each bus in the bus set comprises connection points at different positions distributed along its length; and

[0076] - each data link group comprises connection points at different positions distributed along its length and each arranged near a connection point of the bus with which the data link group is associated, so as to form a plurality of pairs of connection points each comprising a connection point of the bus and a connection point of the associated data link group; and

[0077] - Each of the items of electrical equipment in the group of items of electrical equipment is linked to a pair of connection points via a local power supply link and / or via a local data link.

[0078] For the first aspect of the invention, the bus group corresponds to the unchanged infrastructure of the power distribution network of the aircraft. The network provides the same advantages as those described with reference to the first aspect of the invention. The at least one data link group corresponds to the unchanged infrastructure of the data communication network. The electrical equipment items that require a data communication link are each linked to the connection point of the data link group via a local data link. That provides advantages similar to those of the power distribution network with respect to adding or moving electrical equipment items. When the equipment item requires both power supply and data link, the fact that each connection point of the data link group is located near the connection point of the bus associated with the data link group makes it possible to facilitate the connection of the equipment item to the infrastructure of the power distribution network and the infrastructure of the data communication network: the local power supply route and the local data link can therefore travel together between the electrical equipment item and the connection point.

[0079] In one embodiment, the hybrid power distribution and data communication network comprises a set of junction boxes, each junction box being connected to a pair of connection points. Advantageously, the junction boxes in the set of junction boxes comprise:

[0080] . at least one power supply connector, the at least one power supply connector being configured to cooperate with a connection point of the bus belonging to the pair of connection points to which the junction box is connected;

[0081] . at least one data link connector, at least one data link connector configured to cooperate with a connection point of the data link group belonging to the pair of connection points to which the junction box is connected; and

[0082] . A set of positions provided for receiving an interface module;

[0083] . an electrical link set extending between the power supply connector and a different location provided for receiving the interface module; and

[0084] . A data link group extending between the data link connector and a different position provided for receiving the interface module.

[0085] Furthermore, advantageously, the aircraft comprises:

[0086] . at least one electrical interface module in the location of the junction box and / or at least one data link interface module in the location of the junction box; and

[0087] . At least one local power supply link between said at least one electrical interface module and an item of electrical equipment of the aircraft and / or at least one local data link between said at least one data link interface module and an item of electrical equipment of the aircraft.

[0088] The electrical interface module is for example selected from the following group:

[0089] -Electrical connection module;

[0090] -Electrical switching module;

[0091] - voltage conversion module; and

[0092] -Electrical protection module.

[0093] The data link interface module is for example selected from the following group:

[0094] -Data link connection module;

[0095] -Data link conversion module;

[0096] - Wireless data link module; and

[0097] -Data acquisition and centralization module.

[0098] Advantageously, the aircraft comprises a hybrid interface module in place of a junction box, which ensures the functionality of an electrical interface module and of a data link interface module.

[0099] Furthermore, advantageously, the aircraft is such that:

[0100] - data links in said set of data links associated with said bus correspond to optical fibers;

[0101] - said set of data links extending between the data link connector and the different locations provided for receiving the interface module comprises:

[0102] .Data link converter;

[0103] . a data link via optical fiber between the data link connector and the data link converter;

[0104] . A data link using electrical signals between a data link converter and various locations provided for receiving an interface module.

[0105] In a specific embodiment that can be combined with the previous embodiment:

[0106] - at least one bus of the bus group comprises at least two modular sections arranged end-to-end and electrically linked to each other;

[0107] - each of said at least two modular sections of said at least one bus forms part of a modular element also comprising a set of data links extending substantially parallel to the modular section in question; and

[0108] - said sets of data links of consecutive modular elements are linked to each other to form said set of data links associated with the bus under consideration.

[0109] According to a fourth aspect of the invention, the invention relates to a modular element for an electrical power distribution network of an aircraft.

[0110] This modular element is notable in that it comprises: a section of a power distribution bus extending along the length of the modular element; and in that:

[0111] - the bus section comprises connection points at different positions distributed along its length;

[0112] - the bus section comprises a first interconnection point provided for linking the bus section at a first longitudinal end of the modular element to a bus section of a first other modular element arranged longitudinally in series with the modular element;

[0113] - the bus section comprises a second interconnection point provided for linking the bus section to a bus section of a second further modular element arranged longitudinally in series with the modular element at a second longitudinal end of the modular element opposite to the first longitudinal end;

[0114] - the bus section comprises a set of electrical conductors, these electrical conductors of the bus section being housed in a casing corresponding to a structural component of the aircraft; and

[0115] The casing comprises an opening facing the connection point of the bus section so as to allow connecting at least one item of electrical equipment of the aircraft to the bus section by means of a local electrical link.

[0116] Assembling the modular elements according to the invention makes it possible to construct an electrical power distribution network for an aircraft. This network offers the same advantages as those described with reference to the first and second aspects of the invention with regard to electrical power distribution. The modular elements according to the invention comprise casings corresponding to structural parts of said aircraft, that is to say parts participating in its mechanical structure, with the result that the weight of the aircraft is saved. Indeed, these modular elements do not require specific casings to protect and insulate their electrical conductors.

[0117] According to different embodiments which can be implemented independently of each other or in combination:

[0118] - said structural component of the aircraft is provided for cooperating with a fixing of at least one luggage compartment of the aircraft for supporting this luggage compartment;

[0119] - said structural component of the aircraft corresponds to a floor track section of the aircraft;

[0120] - at least one of the first and second interconnection points comprises a connector provided for slidingly absorbing relative movements between the modular element on the one hand and the first or second further modular element, respectively, on the other hand;

[0121] - A modular element is provided for a hybrid power distribution and data communication network for an aircraft and comprises a set of data links extending substantially parallel to the bus sections along the length of the modular element. The modular element is such that:

[0122] The data link group includes connection points at different positions distributed along its length and each arranged near the connection point of the bus section;

[0123] . the data link set comprises connection points called cross-connection points provided for receiving cross-connection frames;

[0124] . said data link set comprises at least one data link between each of said connection points distributed along its length on the one hand and said cross connection point on the other hand;

[0125] . the data link group comprises a first interconnection point provided for linking the data link group to a data link group of a first other modular element arranged longitudinally in series with the modular element at a first longitudinal end of the modular element; and

[0126] .The data link group includes a second interconnection point, which is provided for linking the data link group to a data link group of a second other modular element arranged longitudinally in series with the modular element at a second longitudinal end of the modular element opposite to the first longitudinal end.

[0127] The invention also relates to an aircraft comprising a fuselage and a set of items of electrical equipment distributed in said fuselage.

[0128] The following are the things worth noting about this aircraft:

[0129] - the aircraft comprises an electric power distribution network comprising a modular set of elements as described above; and

[0130] - Each of the items of electrical equipment in the group of items of electrical equipment is linked via a local power supply line to a connection point of a bus section of a modular element.

[0131] In a specific embodiment:

[0132] - the modular elements of a first subset of said set of modular elements are assembled together so as to form a first power distribution subnetwork extending longitudinally at least partially in said fuselage of said aircraft;

[0133] - the modular elements of a second subset of said set of modular elements are assembled together so as to form a second power distribution subnetwork extending longitudinally at least partially in said fuselage of said aircraft; and

[0134] - The first sub-network and the second sub-network follow isolated paths in the fuselage.

[0135] In another specific embodiment that can be combined with the previous embodiment:

[0136] - Two consecutive modular elements are electrically linked to each other by means of at least one connecting element configured to slide over said section of the bus of at least one of said two modular elements.

[0137] In other specific embodiments that can be combined with the previous embodiments:

[0138] - the aircraft comprises a set of luggage compartments fixed to modular elements of the set of modular elements;

[0139] The aircraft comprises a floor comprising a track at least part of which is formed by a set of modular elements. BRIEF DESCRIPTION OF THE DRAWINGS

[0140] The invention will be better understood by reading the following description and examining the accompanying drawings.

[0141] Figure 1 schematically represents an aircraft including a power distribution network according to an embodiment of the invention;

[0142] Figure 2 schematically represents an aircraft including a power distribution network according to another embodiment of the invention;

[0143] Figure 3 is along Figure 2 A cross-sectional view taken along line IIa-IIa of ;

[0144] Figure 4 It is a perspective view of the bus;

[0145] Figure 5 yes Figure 1 a schematic diagram of a portion of the fuselage of the aircraft shown;

[0146] Figure 6a and Figure 6b Schematically shows a specific embodiment of the Figure 2 A portion of a power distribution network of an aircraft is shown including an auxiliary switch;

[0147] Figure 7a and Figure 7b Schematically shows a specific embodiment of the Figure 1 or Figure 2 A portion of a power distribution network of an aircraft is shown including an auxiliary switch;

[0148] Figure 8 Schematically represents modular elements of a hybrid power distribution and data communications network for an aircraft according to an embodiment of the present invention;

[0149] Fig. 9 Schematically represents modular elements of a hybrid power distribution and data communications network for an aircraft according to another embodiment of the present invention;

[0150] Fig.10 and Fig.11 Respectively and Figure 8 and Fig. 9 Data links of corresponding modular components;

[0151] Fig.12 An example of the interconnection of two modular elements is shown;

[0152] Fig.13 A modular element equipped with a junction box is schematically represented;

[0153] Fig.14 Schematically represents an aircraft including a hybrid power distribution and data communications network comprising a modular set of elements;

[0154] Fig.15 Schematically represents an aircraft including a hybrid power distribution and data communications network according to an embodiment of the present invention;

[0155] Fig.16 Schematically shows Fig.15 A bus of a hybrid network and a data link group associated with the bus;

[0156] Fig.17 Schematically shows Fig.16 A bus equipped with a junction box and the data link group;

[0157] Fig.18 and Fig.19 Two examples of junction boxes according to embodiments of the present invention are schematically represented;

[0158] Fig. 20 yes Fig.15 a schematic diagram of a portion of the fuselage of the aircraft shown;

[0159] Fig.21a and Fig. 22 Shows electrical equipment items and Fig.18 or Fig.19 Connections to junction boxes such as the junction box shown;

[0160] Figure 21b Indicates that by Fig.21a An example of a junction box as seen in a cross-sectional view taken along line IIIa-IIIa of ;

[0161] Fig.23 An example of a bus segment is shown whose structural shell supports at least one luggage compartment of an aircraft;

[0162] Fig.24 An example of a bus segment is shown, the structural shell of which corresponds to the seat tracks of an aircraft. DETAILED DESCRIPTION

[0163] According to an embodiment according to the first aspect of the present invention, Figure 1The aircraft 1 shown comprises a fuselage F and a set of generators comprising a first generator G1 associated with an engine E1 of the aircraft and a second generator G2 associated with an engine E2 of the aircraft. The aircraft 1 also comprises an electrical power distribution network 200. The electrical power distribution network comprises a set of buses comprising a first bus 120, 120a and a second bus 220, 220a. Each of the two buses comprises at least one portion 120, respectively 220 extending in the longitudinal direction of the fuselage F. The two buses follow isolated paths in the fuselage F of the aircraft, respectively, in the left part (or port) of the fuselage for the portion 120 of the first bus and in the right part (or starboard) of the fuselage for the portion 220 of the second bus. This makes it possible to avoid common faults on the two buses in the event of an event in a part of the fuselage. Advantageously, the first bus comprises a portion 120a in the left wing of the aircraft and the second bus comprises a portion 220a in the right wing of the aircraft. Similar conductors of section 120a and similar conductors of section 120 are electrically linked to each other. Likewise, similar conductors of section 220a and similar conductors of section 220 are electrically linked to each other. The power distribution network 200 also includes a switching system 30. This switching system is electrically linked to the first generator G1 and the second generator G2 and is linked to the first bus 120, 120a and the second bus 220, 220a. The switching system 30 includes a so-called normal operating mode, in which the switching system is configured to electrically link the first generator G1 to the first bus 120, 120a and the second generator G2 to the second bus 220, 220a. In a specific embodiment, the first generator G1 is electrically linked to the switching system 30 via a dedicated conductor (or bar) of the first bus 120, 120a, and the second generator G2 is electrically linked to the switching system via a dedicated conductor of the second bus 220, 220a. For example, a first generator G1 located in the left wing of the aircraft, close to the engine E1, is linked to a dedicated conductor of this portion 120a of the first bus through a local power supply circuit between this generator and the portion 120a of the first bus. Similarly, a second generator G2 located in the right wing of the aircraft, close to the engine E2, is linked to a dedicated conductor of this portion 220a of the second bus through a local power supply circuit between this generator and the portion 220a of the second bus. That makes it possible to avoid laying specific lines in the wings and fuselage of the aircraft. The aircraft 1 also comprises a group of items of electrical equipment distributed in the fuselage, each bus of the group comprising connection points at different positions distributed along its length. For the sake of clarity of the figure, in Figure 1 These items of electrical equipment and these connection points are not shown in the diagram, but are shown in the diagram showing a portion of the fuselage F. Figure 5 Thus, the aircraft 1 includes Figure 540j group of electrical equipment items in the portion of the fuselage shown. Each of these electrical equipment items requires power supply to operate. In the portion of the first bus 120 shown in the figure, the first bus includes connection points 24a...24h at different positions distributed along its length. In the portion of the second bus 220 shown in the figure, the second bus includes connection points 24i...24p at different positions distributed along its length. Each of the electrical equipment items in the electrical equipment items in the group of electrical equipment items is linked to the connection point of the bus in the bus group via a local power supply line 42. Thus, for example, electrical equipment item 40a is linked to connection point 24a of the first bus 120. Electrical equipment items 40b, 40c and 40d are linked to connection point 24d. Electrical equipment items 40e and 40f are linked to connection point 24g. Electrical equipment item 40g is linked to connection point 24i of the second bus 220. Electrical equipment items 40h and 40i are linked to connection point 24l. Electrical equipment item 40j is linked to connection point 24o. Advantageously, the connection points 24a, 24d, 24g, 24i, 24l and 24o of the local power supply circuits 42 that receive items of electrical equipment are equipped with junction boxes, which are provided with taps or connectors that make it easy to connect these local power supply circuits 42. And advantageously, other connection points that do not receive local power supply circuits are not equipped with such junction boxes to limit the weight of the aircraft. In a specific exemplary embodiment, two consecutive connection points of the bus are spaced apart by a distance of approximately 50 cm to 70 cm. This distance corresponds, for example, to the distance between two structural frames of the aircraft. In most of the fuselage, a junction box can be installed, for example, every four or five connection points. However, in fuselage areas corresponding to a particularly high density of items of electrical equipment, all connection points or sometimes one of every two connection points can be equipped with a junction box.

[0164] The bus group forms the infrastructure of the power distribution network 200 of the aircraft. Different electrical equipment items 40a...40i are each linked to the connection point of the bus by a local power supply line 42. Therefore, it is possible to easily add new electrical equipment items to the fuselage without modifying this infrastructure: for this purpose, it is sufficient to place a local power supply line in a suitable position between this new equipment item and the connection point of the bus. Preferably, this connection point is selected to be as close as possible to the new electrical equipment item on the bus under consideration. This addition of new electrical equipment items can also be carried out during the construction of the aircraft and during the modification of the aircraft configuration after the aircraft is delivered to the airline. For example, it is also easy to move the electrical equipment items in the fuselage of the aircraft during the modification of the aircraft configuration: for this purpose, it is sufficient to remove its original local electrical supply line, move the electrical equipment items to their new position in the fuselage and place a new local power supply line to another connection point of the bus in a suitable position. Using a bus group instead of a cable harness also enables the weight of the power distribution network of the aircraft to be reduced. Indeed, the electrical conductors of a bus used in common by several items of electrical equipment need to be smaller in size than the sum of the sizes of the individual cables in the wiring harness that power these same items of electrical equipment.

[0165] exist Figure 2 In another embodiment shown, the aircraft 1 further comprises a third generator G3 near the engine E1 and a fourth generator G4 near the engine E2. The bus group further comprises a third bus 320, 320a and a fourth bus 420, 420a. The third bus and the fourth bus each comprise a portion 320, respectively 420 extending in the longitudinal direction of the fuselage F. The four buses are arranged in the fuselage along isolated paths, such as Figure 3As shown. As indicated before, the portion 120 of the first bus runs in the left part of the fuselage, and the portion 220 of the second bus runs in the right part of the fuselage. Likewise, the portion 320 of the third bus runs in the left part of the fuselage, and the portion 420 of the fourth bus runs in the right part of the fuselage. The portions 120 of the first bus and 220 of the second bus run in the upper part of the fuselage, while the portions 320 of the third bus and 420 of the fourth bus run in the lower part of the fuselage. Advantageously, the third bus includes the portion 320a in the left wing of the aircraft, and the fourth bus includes the portion 420a in the right wing of the aircraft. Like the first bus 120, 120a and the second bus 220, 220a, the third bus 320, 320a and the fourth bus 420, 420a are also linked to the switching system 30. In normal operating mode, the switching system 30 is configured to electrically link the third generator G3 to the third bus and link the fourth generator G4 to the fourth bus. In a specific embodiment, the third generator G3 is electrically linked to the switching system 30 via dedicated conductors (or strips) of the third bus 320, 320a, and the fourth generator G4 is electrically linked to the switching system via dedicated conductors of the fourth bus 420, 420a. For example, the third generator G3 located in the left wing of the aircraft, close to the engine E1, is linked to the dedicated conductors of this portion 320a of the third bus through a local power supply circuit between this generator and the portion 320a of the third bus. In the same way, the fourth generator G4 located in the right wing of the aircraft, close to the engine E2, is linked to the dedicated conductors of this portion 420a of the fourth bus through a local power supply circuit between this generator and the portion 420a of the fourth bus.

[0166] exist Figure 4In the exemplary embodiment shown, the bus 20 in the bus group includes a group of strip-shaped electrical conductors 25a, 25b, 25c. Although three electrical conductors 25a, 25b and 25c are represented in the figure, the number of this electrical conductor should not be interpreted as limiting the present invention. Those skilled in the art will be able to adjust the number of strips according to the different voltages to be distributed to the electrical equipment items of the aircraft by means of the power distribution network 200 and according to the number of required individual isolations. These strips run parallel or substantially parallel along the length of the bus 20. The strips are separated from each other by an electrically insulating material 22, such as a plastic material or air. The group of strips is surrounded by a housing 28. According to an embodiment, this housing is formed by an electrically insulating material. According to another embodiment, the housing 28 is formed by a conductive material. The electrically insulating material 22 is then arranged between the electrical conductors 25a, 25b and 25c on the one hand and the housing 28 on the other hand. This other embodiment is advantageous because it enables the use of the housing 28 as a current return conductor (e.g., a neutral conductor with alternating current, 0 volt direct current, etc.) and / or as an electromagnetic shield that enables the electromagnetic interference caused to items of electrical equipment of the aircraft by the current circulating in the electrical conductors 25a, 25b, 25c to be avoided. The portion of the bus 20 shown in the figure comprises a connection point 24. This connection point comprises an opening 29 in the housing 28, for example, on the top face of the housing (in the figure). The opening 29 thus defines two parts 28a and 28b of the top face of the housing 28. When the insulating material corresponds to a plastic material, the portion of the set of electrical conductors 25a, 25b, 25c that is located facing the opening 29 does not have this insulating material, so as to allow the connection device to be connected to the electrical conductors 25a, 25b, 25c through the opening 29. Such a connection device corresponds, for example, to a connector comprising a plurality of sets of spring-formed blades that can be placed in appropriate positions on a strip.

[0167] Advantageously, the switching system 30 comprises a so-called reconfigured operating mode, which can be activated in the event of a fault in the power distribution network. In the reconfigured operating mode, according to a first variant, the switching system 30 is configured to establish electrical links between the generators G1, G2 (and possibly G3, G4 according to an embodiment) in the group of generators on the one hand and the buses in the bus group on the other hand, which are modified by comparison with the electrical links established in the normal operating mode. According to a second variant, the switching system 30 is configured to establish electrical links between the buses in the bus group. This second variant can be combined with the first variant. For example, in the event of a fault in the generator G3 (which in normal mode supplies power to the third bus 320, 320a), the switching system modifies the electrical links so that the first bus 120, 120a and the third bus 320, 320a are supplied by the generator G1.

[0168] In a specific embodiment, the switching system includes a main switching device and at least one auxiliary switching device remote from the main switching device. Figure 1 , Figure 2 and Figure 3 The switching system 30 shown and described previously ensures, for example, the functionality of the power backbone of the aircraft. The at least one auxiliary switching device is controlled by the switching system 30, to which the at least one auxiliary switching device is linked via a specific communication link or communication network of the aircraft. Figure 6a and Figure 6b In the example shown, the auxiliary switching device 32a is remotely located at the end of a bus in the bus group, for example in the rear or front part of the fuselage F of the aircraft. The auxiliary switching device 32a comprises, for example, four switches K1, K2, K3, K4 corresponding to contactors that can be controlled by the switching system 30. For example, these contactors comprise at least as many contacts as there are electrical conductors 25a, 25b, 25c, etc. in the bus. In the normal operating mode of the switching system, as shown in FIG. Figure 6a As shown, the contacts of switches K1 , K2 , K3 , and K4 are open, so that the switches do not establish links between buses 120 , 220 , 320 , and 420 . Figure 6b A situation is shown in which a fault X has occurred on the first bus 120. This fault has the effect of electrically isolating the two parts 120x and 120y of the first bus 120 from each other. As a result, in normal operating mode, the part 120y of the first bus is no longer supplied by the first generator G1 via the switching system 30. In order to provide a solution to this problem, in the reconfigured operating mode, the switching system controls the remote auxiliary switching device 32a in such a way that the contacts of the switch K1 are closed. This has the effect of linking similar conductors of the part 120y of the first bus to each other on the one hand and similar conductors of the third bus 320 to each other on the other hand. This part 120y of the first bus is then supplied by the third generator G3 via the switching system 30.

[0169] In an advantageous embodiment, at least one of the buses in the bus group comprises at least two sections arranged end to end and electrically linked to each other. This is particularly interesting when the aircraft 1 is formed by assembling sections of the fuselage F. These sections of the fuselage are then pre-equipped with bus sections that are linked to each other during or after assembling the sections of the fuselage. For example, each of the parts 120, 220, 320 and 420 of the first, second, third and fourth buses consists of an assembly of bus sections arranged end to end and electrically linked to each other. According to a first alternative, the bus section is specific to the fuselage section in which the bus section is incorporated. According to a second alternative, each bus section incorporated in the fuselage section consists of an assembly of modular bus sections arranged end to end and electrically linked to each other. Advantageously, these modular bus sections correspond to the length of the wired quantity, which is cleverly selected to allow different sections of the fuselage to be pre-equipped by combining modular sections corresponding to these predefined lengths.

[0170] Specifically, the auxiliary switching device 32b is electrically linked to two consecutive sections (or two modular sections) of the bus. Figure 7a and Figure 7b In the example shown, the auxiliary switching device 32b is placed at a suitable position between the sections 120j and 220j of the two buses on the one hand and the sections 120k and 220k of the two buses on the other hand. The sections 120j and 120k correspond to two consecutive sections of the first bus 120. The sections 220j and 220k correspond to two consecutive sections of the second bus 220. The auxiliary switching device 32b comprises, for example, four switches K11, K12, K13, K14 corresponding to contactors that can be controlled by the switching system 30. For example, these contactors comprise at least as many contacts as there are electrical conductors 25a, 25b, 25c, etc. in the bus. In normal operating mode of the switching system, as in Figure 7a As shown, the contacts of switches K11 and K12 are closed to establish an electrical link between similar electrical conductors of sections 120j and 120k of the first bus on the one hand and similar electrical conductors of sections 220j and 220k of the second bus on the other hand. The contacts of switches K13 and K14 are open in such a way that the switches do not establish a link between the first bus and the second bus. Figure 7bA situation is shown in which a fault X has occurred on the section 120j of the first bus 120. Although not represented in the figure, the switching system 30 is considered to be on the left side of the sections 120j and 220j in the figure. The fault X has the effect of interrupting the power supply to the section 120k by the generator G1 via the switching system 30 and the section 120j. To solve this problem, in the reconfigured operating mode, the switching system 30 commands the opening of the contacts of the switch K11 and the closing of the contacts of the switch K14. This has the effect of linking similar contacts of the section 220j of the second bus and similar contacts of the section 120k of the first bus to each other. This section 120k of the first bus is then powered by the second generator G2 via the switching system 30 and the section 220j.

[0171] According to an embodiment according to the second aspect of the present invention, Figure 8 As shown, modular elements 60 for a hybrid power distribution and data communications network for an aircraft include:

[0172] a power distribution bus section 20t extending along the length L of the modular element 60; and

[0173] - A set of data links 50t extending along said length L of the modular element substantially parallel to the power distribution bus section 20t.

[0174] Preferably, the power distribution bus segment 20t and the data link group 50t are installed to be fixed to each other. Figure 8 In the example shown, the power distribution bus segment 20t and the data link set 50t are fixed to a common support 62. In another exemplary embodiment, not shown, the data links of the data link set 50t are attached to the power distribution bus segment 20t. In a specific embodiment in which these data links correspond to optical fiber ribbon cables, these optical fiber ribbon cables are, for example, glued to the face of the power distribution bus segment 20t.

[0175] According to a first alternative, the data links of said set 50t of data links correspond to twisted pairs of copper or aluminium wires. According to another alternative, the data links correspond to optical fibres. In addition to a significant weight saving, these optical fibres offer the advantage of being insensitive to any electromagnetic interference that may be generated when the current circulates in the bars of the power distribution bus segment 20t.

[0176] The power distribution bus segment 20t comprises connection points 24 at different positions distributed along its length. The data link group 50t comprises connection points 54 at different positions distributed along its length and each arranged close to (or facing) the connection point 24 of the power distribution bus segment 20t. The modular element 60 thus comprises a plurality of pairs of connection points, each of which comprises a connection point 24 of the power distribution bus segment 20t on the one hand and a connection point 54 of the data link group 50t located near the connection point 24 on the other hand. The power distribution bus segment 20t comprises a first interconnection point 27a, and the data link group 50t comprises a first interconnection point 57a. These first interconnection points 27a and 57a are located at a first longitudinal end Ext1 of the modular element 60. These first interconnection points 27a and 57a are provided for linking the power distribution bus segment 20t and the data link group 50t to a bus segment and a data link group of a first other modular element arranged longitudinally in series with the modular element 60, respectively. The power distribution bus segment 20t comprises a second interconnection point 27b, and the data link group 50t comprises a second interconnection point 57b. These second interconnection points 27b and 57b are located at the second longitudinal end Ext2 of the modular element 60. These second interconnection points 27b and 57b are provided for linking the power distribution bus segment 20t and the data link group 50t to the bus segment and the data link group of a second other modular element arranged longitudinally in series with the modular element 60, respectively.

[0177] The data link set 50t also comprises at least one connection point, called a cross-connection point, provided for receiving a cross-connection frame. According to a first variant, this at least one cross-connection point is located at a longitudinal end of the modular element 60. Figure 8 In the example shown, the data link set 50t comprises two cross-connection points 55a and 55b, which are located at the first longitudinal end Ext1 and the second longitudinal end Ext2 of the modular element 60, respectively. Fig. 9 In the second variant shown, the at least one cross-connection point 55 is located between two connection points 54 of the set of data links 50t. These two variants can be combined with each other: the modular element 60 then comprises one or two cross-connection points 55a, 55b at at least one of its longitudinal ends Ext1, Ext2 and at least one cross-connection point located between two connection points 54.

[0178] The data link set 50t also comprises at least one data link between each of the connection points distributed along its length on the one hand and the cross connection point on the other hand. Figure 8 and Fig. 9 For the sake of clarity, these data links 56 are not shown in the figure. Figure 8The corresponding data link Fig.10 As shown, at least one data link is provided between each cross-connection point 55a, 55b on the one hand and each connection point 54a, 54b ... 54f on the other hand. For example, the data link group 50t includes at least one data link 56b1 between the cross-connection point 55a and the connection point 54b and at least one data link 56b2 between the cross-connection point 55b and the connection point 54b. Although Fig.10 Only one link is shown, but several data links 56 may be provided between each cross-connection point 55a, 55b and different connection points 54a ... 54f. In particular, when the data links are implemented by means of optical fibers, each link shown in the figure may actually correspond to a group of optical fibers, for example eight optical fibers.

[0179] Advantageously, said set of data links 50t also comprises data links 58 between the first interconnection point 57a and the second interconnection point 57b. These data links 58 are used in particular to enable communication passing through several modular elements 60 to be established.

[0180] In the schematic diagram, the Fig. 9 The corresponding data link Fig.11 In the example shown, at least one data link 56a, 56b ... 56f is provided between the cross-connection point 55 and each connection point 54a, 54b ... 54f. In addition, at least one data link 58b is provided between the cross-connection point 55 and each interconnection point 57a, 57b.

[0181] The one or more cross-connection points are provided for receiving a cross-connection frame. The modular element 60 comprises, for example, at least one fixing provided for allowing the cross-connection frame to be fixed to the modular element. This fixing may specifically correspond to a nut or a screw, to a mechanical part provided for cooperating with a part of the cross-connection frame to clamp the cross-connection frame to the modular element, etc. Advantageously, in the cross-connection points 55, 55a, 55b, the data link 56 reaches one or more cross-connection connectors which may be incorporated in the corresponding cross-connection frame.

[0182] In with Figure 8 In the case of modular elements 60i, 60i+1 similar to the modular elements 60 shown, Fig.12An example of the interconnection of two consecutive modular elements is shown. A first end Ext1 of a modular element 60i+1 is connected to a second end Ext2 of a modular element 60i. To this end, the two ends are arranged end to end close to each other in such a way that a first interconnection point 27a of the power distribution bus segment 20t of the modular element 60i+1 faces a second interconnection point 27b of the power distribution bus segment 20t of the modular element 60i, and a first interconnection point 57a of said data link group 50t of the modular element 60i+1 faces a second interconnection point 57b of said data link group 50t of the modular element 60i. Similar conductors of the interconnection points 27a and 27b are electrically linked to each other by means of an electrical link 66. In a first exemplary embodiment, the interconnection points 27a and 27b correspond to terminal blocks, and the electrical link 66 corresponds to a cable of an appropriate section. In a second exemplary embodiment, the interconnection points 27a and 27b correspond to connectors. The electrical link 66 corresponds, for example, to the connection of said connectors. In particular, when these connectors are connected, they can slide longitudinally relative to each other in order to absorb the longitudinal displacement of the two modular elements relative to each other, in particular when the structure of the aircraft in which the modular elements are installed is deformed. The cross-connection frame 64 is installed to receive the interconnection point 57a of the modular element 60i+1 and the interconnection point 57b of the modular element 60i and the cross-connection point 55a of the modular element 60i+1 and the cross-connection point 55b of the modular element 60i. Advantageously, these interconnection points and cross-connection points are equipped with connectors that are then combined in the cross-connection frame. The cross-connection frame enables the required interconnection to be installed, for example, by means of a jumper link. It also allows the combination of such equipment items when the generation of an interconnection requires active elements of the switch or router type. These active elements correspond, for example, to switches or routers of Ethernet or USB type. When the data link is of a wired type (for example, a twisted pair of copper or aluminum conductors), the jumper link corresponds to a wired jumper link, or when the data link corresponds to an optical fiber, the jumper link corresponds to an optical jumper link. The cross-connection frame receiving the interconnection points 57a, 57b and the cross-connection points 55a, 55b allows the installation of jumper links to create different types of interconnections. A first type of interconnection corresponds to the interconnection of a first link between one of the cross-connection points 55a, 55b and a connection point 24 of the data link group of one of the modular elements 60i, 60i+1 with a second link between one of the cross-connection points 55a, 55b and a connection point 24 of the data link group of one of the modular elements 60i, 60i+1. A second type of interconnection corresponds to the interconnection of a first link between one of the cross-connection points 55a, 55b and a connection point 24 of the data link group of one of the modular elements 60i, 60i+1 with a second link arriving at one of the interconnection points 57a, 57b.The third type of interconnection corresponds to the interconnection of a first link arriving at one of the interconnection points 57a, 57b with a second link arriving at the other of the interconnection points 57a, 57b. Several modes of installation of the cross-connection frame 64 are possible without departing from the scope of the invention. According to a first example, the cross-connection frame is fixed to at least one of the modular elements 60i, 60i+1 so as to cover the cross-connection points 55a, 55b and the interconnection points 57a, 57b that enter into the cross-connection frame through one or more cutouts of the cross-connection frame. According to a second example, the cross-connection frame is fixed to at least one of the modular elements 60i, 60i+1 close to its ends Ext2, Ext1 or to the structure of the aircraft close to the ends Ext2, Ext1 of the modular elements 60i, 60i+1, without the cross-connection frame covering these interconnection points and cross-connection points. The interconnection points 57a, 57b and cross-connection points 55a, 55b are then arranged in the data link group 50t long enough and flexible enough to allow the interconnection points and cross-connection points to be joined at the ends of the data links in the cross-connect frame 64.

[0183] exist Fig.13 In the specific embodiment shown, each of the different pairs of connection points 24, 54 of the modular element 60 is provided for receiving a hybrid power distribution and data communication junction box 68. Such a hybrid junction box allows one or more local power supply distribution and / or data distribution links to be connected to one or more electrical equipment items of the aircraft. The use of a hybrid junction box facilitates the connection of electrical equipment items to the modular element 60: thus, it is not necessary to connect each electrical equipment item to the power distribution bus section 20t and the data link in the data link group 50t. The junction box 68 is, for example, provided with a connector that facilitates the connection of a local link to the electrical equipment item. Advantageously, only when the electrical equipment item is connected to a pair of connection points is this pair of connection points equipped with a junction box. This makes it possible to avoid an unnecessary increase in the weight of the aircraft.

[0184] In another specific embodiment, the power distribution bus segment 20t includes at least one flexible portion provided to allow the modular element 60 to deform in response to deformation of the fuselage F of the aircraft when the modular element 60 is installed in the fuselage F of the aircraft. For example, to create such a flexible portion, each conductive element of the power distribution bus segment 20t includes a spring over a portion of its length.

[0185] In a specific exemplary embodiment, the length L of the modular element 60 is between 3 meters and 10 meters, preferably between 6 meters and 10 meters. In particular, two consecutive pairs of connection points of the modular element are spaced apart by a distance of about 50 cm to 70 cm. This distance corresponds, for example, to the distance between two structural frames of an aircraft. In most of the fuselage, a junction box 68 can be installed, for example, every four or five pairs of connection points. However, in fuselage areas corresponding to a particularly high density of electrical equipment items, all pairs of connection points or sometimes one of every two pairs of connection points can be equipped with a junction box.

[0186] The invention also relates to an aircraft 1 comprising a fuselage F and a group of electrical equipment items distributed in the fuselage. Fig.14 As shown, the aircraft comprises a hybrid power distribution and data communication network 600, which comprises a modular element group 60a...60q similar to the modular element 60 described above. The hybrid network 600 comprises a first hybrid power distribution and data communication sub-network 160, 160a. This first hybrid sub-network is formed by assembling between two modular elements 60a...60h forming a first subset of the modular element group. The first hybrid sub-network comprises a portion 160 extending longitudinally in the fuselage F of the aircraft. Advantageously, it also comprises a portion 160a extending in the left wing of the aircraft. The hybrid network 600 also comprises a second hybrid power distribution and data communication sub-network 260, 260a. The second hybrid sub-network is formed by assembling between the modular elements 60i...60q forming the second subset of the modular element group themselves. The second hybrid sub-network comprises a portion 260 extending longitudinally in the fuselage F of the aircraft. Advantageously, it also comprises a portion 260a extending in the right wing of the aircraft. The first subnetwork 160, 160a and the second subnetwork 260, 260a are arranged along isolated paths in the fuselage F, for example, in the left part of the fuselage for the first subnetwork and in the right part of the fuselage for the second subnetwork, as shown in FIG. Fig.14 As shown. Two consecutive modular elements, for example, as shown in FIG. Fig.12 Each item of electrical equipment in the group of items of electrical equipment is linked to a connection point 24 of a power distribution bus segment 20t of a modular element 60a ... 60q via a local power supply link and / or to a connection point 54 of the data link group 50t of the modular element via a local data link. Fig.14For the sake of clarity, items of electrical equipment and local links are not represented. The use of modular elements according to the invention to construct the hybrid network 600 makes it possible to easily adapt this network to any type of aircraft, without requiring buses or groups of multiple data links that are specific to the aircraft under consideration, in particular as to their length. The use of one or several types of modular elements of predetermined length makes it possible to adapt this network to any type of aircraft.

[0187] According to an embodiment according to the third aspect of the present invention, Fig.15 The aircraft 1 shown comprises a fuselage F and a group of generators, the group of generators comprising a first generator G1 associated with an engine E1 of the aircraft and a second generator G2 associated with an engine E2 of the aircraft. The aircraft 1 also comprises a hybrid power distribution and data communication network 600. The hybrid network 600 comprises a bus group, the bus group comprising a first bus and a second bus. Each bus in the bus group is associated with a data link group. Each data link group extends substantially parallel to the bus associated with it. The first bus and the data link group associated with this first bus form a first hybrid power distribution and data communication subnetwork 160, 160a. The second bus and the data link group associated with this second bus form a second hybrid power distribution and data communication subnetwork 260, 260a. Each of these two subnetworks comprises at least a portion 160, respectively 260 extending in the longitudinal direction of the fuselage F. The two subnetworks are arranged along isolated paths in the fuselage F of the aircraft, respectively, in the left part (or port) of the fuselage for the portion 160 of the first subnetwork and in the right part (or starboard) of the fuselage for the portion 260 of the second subnetwork. That makes it possible to avoid common faults on the two subnetworks in the event of an incident in a part of the fuselage. Advantageously, the first subnetwork comprises the portion 160a in the left wing of the aircraft and the second subnetwork comprises the portion 260a in the right wing of the aircraft. Advantageously, the power distribution network also comprises a switching system 30. This switching system is electrically linked to the first generator G1 and the second generator G2 and to the first bus of the first subnetwork 160, 160a and the second bus of the second subnetwork 260, 260a. The switching system 30 comprises a so-called normal operating mode in which the switching system is configured to electrically link the first generator G1 to the first bus and the second generator G2 to the second bus. The aircraft 1 also comprises a group of items of electrical equipment distributed in the fuselage. In order Fig.15 For the sake of clarity, these electrical equipment items are not shown in the figures.

[0188] like Fig.16As shown, each bus 20 in the bus group includes connection points 24 at different positions distributed along its length, and each data link group 50 includes connection points 54 at different positions distributed along its length. The connection points 54 are each arranged to be close to (or facing) the connection point 24 of the bus 20 associated with the data link group 50, so as to form a plurality of pairs of connection points each including a connection point 24 of the bus and a connection point 54 of the associated data link group. In a specific exemplary embodiment, two consecutive pairs of connection points are spaced apart by a distance of about 50 cm to 70 cm. This distance corresponds, for example, to the distance between two structural frames of an aircraft.

[0189] Although the hybrid power distribution and data communication network 600 has been described in the specific case where it comprises two sub-networks 160, 160a and 260, 260a, the third aspect of the invention is by no means limited to this number of sub-networks. For example, the hybrid network 600 may comprise four sub-networks along isolated paths in the fuselage of the aircraft in the same manner as the power distribution network 200 according to the first aspect of the invention may comprise four buses along isolated paths in the fuselage.

[0190] In an advantageous embodiment, at least one bus 20 of the bus group comprises at least two modular sections arranged end-to-end and electrically linked to each other. This at least one bus forms part of one of the subnetworks 160, 160a or 260, 260a. Each of the at least two modular sections of the at least one bus forms part of a modular element, which also comprises a set of data links extending substantially parallel to the modular section under consideration. Such a modular element corresponds, for example, to the modular element 60 according to an embodiment of the second aspect of the invention. The sets of data links of consecutive modular elements are linked to each other to form the set of data links 50 associated with the bus 20 under consideration.

[0191] Advantageously, the hybrid power distribution and data communications network 600 comprises a set of junction boxes, each junction box 70 being connected to a pair of connection points 24, 54, such as Fig.17 These junction boxes are provided to allow the connection of items of electrical equipment of the aircraft to the connection points 24 of the bus 20 and to the connection points 54 of the data link group 50. Moreover, advantageously, the number of junction boxes 70 installed on the power distribution and data distribution subnetwork varies according to the density of items of electrical equipment in the fuselage F of the aircraft. For example, in a fuselage region where the density of items of electrical equipment is moderate, a junction box may be installed every four or five pairs of connection points 24, 54, such as Fig.17 In fuselage areas where the density of electrical equipment items is high, junction boxes may be installed every two pairs of connection points, or even at every pair of connection points, such as Fig.17 as shown in the top portion of .

[0192] Advantageously, the data link set 50 also comprises at least one specific connection point, called cross-connection point 55. This at least one cross-connection point 55 is provided for receiving a cross-connection frame 64. The data link set 50 comprises data links between the cross-connection point 55 and the different connection points 54. The cross-connection frame enables the data links to be linked to each other by means of jumper links.

[0193] Each of the items of electrical equipment in the group of items of electrical equipment is linked to a pair of connection points via a local power supply line 42 and / or via a local data link 43, such as Fig. 20 As shown. Aircraft 1 includes a group of electrical equipment items 40a...40j in the part representing fuselage F in the figure. Except for energy-independent equipment item 40g, these electrical equipment items each need power supply to operate. Electrical equipment items except equipment item 40d each also need data link. Each electrical equipment item is linked to a single pair of connection points by means of the local power supply circuit 42 and / or local data link 43, preferably via junction box 70a...70f. In the fuselage part shown in the figure, part 160 of the first subnetwork is equipped with three junction boxes 70a, 70b, 70c, and part 260 of the second subnetwork is equipped with three junction boxes 70d, 70e, 70f. Electrical equipment item 40a is linked to junction box 70a by local power supply circuit 42 and by local data link 43. Electrical equipment items 40b and 40c are linked to junction box 70b by local power supply circuit 42 and by local data link 43. Item 40d of electrical equipment is linked to junction box 70b only via local power supply line 42. Items 40e and 40f of electrical equipment are linked to junction box 70c via local power supply line 42 and via local data link 43. Item 40g of electrical equipment is linked to junction box 70d only via local data link 43. Items 40h and 40i of electrical equipment are linked to junction box 70e via local power supply line 42 and via local data link 43. Item 40j of electrical equipment is linked to junction box 70f via local power supply line 42 and via local data link 43. In a specific exemplary embodiment, junction boxes 70a, 70b, 70c on the one hand and junction boxes 70d, 70e, 70f on the other hand are installed on part 160 of the first subnetwork and on part 260 of the second subnetwork, respectively, every four or five pairs of connection points. When the pairs of connection points are spaced apart, for example, by 50 cm, two consecutive junction boxes are then spaced apart by about 2 meters.

[0194] exist Fig.18In the specific embodiment shown, the junction box 70 includes a power supply connector 724, a data link connector 754 and a group of positions E1, E2...E6 provided for receiving interface modules respectively. The power supply connector 724 is provided for cooperating with the connection point 24 of the pair of connection points to which the junction box is connected. The data link connector 754 is provided for cooperating with the connection point 54 of the data link group belonging to the pair of connection points to which the junction box is connected. When the data link of the distribution network 600 corresponds to an optical fiber, this data link connector corresponds to at least one multi-fiber connector, for example. The junction box 70 also includes an electrical link group 72 and a data link group 75, the electrical link group extending between the power supply connector 724 and the different positions E1, E2...E6 provided for receiving interface modules, and the data link group extending between the data link connector 754 and the different positions provided for receiving interface modules.

[0195] exist Fig.19 In the variant shown, the data link of the distribution network 600 corresponds to an optical fiber, and the junction box 70 also includes a data link converter 78. This converter is provided for converting the communication through the optical fiber into a wired communication, and vice versa. The data link group 75 then includes a data link 75a through the optical fiber between the data link connector 754 and the data link converter 78 and a data link 75b using an electrical signal between the data link converter 78 and the different positions E1, E2 ... E6 provided for receiving the interface module. This variant provides the advantage of allowing the communication through the optical fiber on the data link group of the hybrid power distribution and data communication network 600. Therefore, these communications are not sensitive to electromagnetic interference. These communications through the optical fiber are converted into wired communications in the junction box 70, which allows the data link 75b to be wired connected to the interface module that can be installed in the position E1, E2 ... E6. Since the interface module is likely to be replaced or moved, this wired connection exhibits better reliability than the optical connection. Indeed, compared to the optical connection, this wired connection is less sensitive to dust and vibration.

[0196] In the exemplary embodiment, connectors 724 and 754 are arranged on the back of the junction box 70. The electrical link group 72 and the data link group 75 are created by means of the backplane of the junction box. These links arrive on connectors of the backplane, which are arranged facing the positions E1, E2 ... E6 so that the interface modules that may be installed in the positions can be plugged into these connectors.

[0197] exist Fig.21aIn the first specific embodiment shown, electrical equipment items 40k...40q are connected to electrical interface modules Pa, Pb and / or to data link interface modules Da, Db through local power supply lines 42k...42q. In the example shown in the figure, electrical interface modules Pa, Pb are installed in positions E2, E6 of junction box 70, respectively, and data link interface modules Da, Db are installed in positions E3, E5 of junction box 70, respectively. In this first embodiment, electrical equipment items requiring power supply and data link are linked to electrical interface modules through local power supply lines and to data link interface modules through local data links. For example, electrical equipment item 40k is linked to electrical interface module Pa through local power supply lines 42k and is linked to data link interface module Da through local data links 43k. Advantageously, local power supply lines 42k...42q and local data links 43k...43q terminate at connectors capable of cooperating with connectors of interface modules. Advantageously, moreover, the back of the terminal box 70 comprises supports provided for holding the connectors of the local power supply circuits and the local data links in place so that these connectors are connected to the corresponding connectors of the interface module when the interface module is mounted in its corresponding position of the terminal box. That advantageously enables the removal and installation of the interface module in the positions E1, E2 ... E6 of the terminal box without having to manipulate the connectors of the different data links. That also enables then to avoid connection errors of said links.

[0198] exist Figure 21b In the example shown, the junction box includes a backplane 73. Connectors 724 and 754 are fixed to the backplane. These connectors are arranged in such a way that when the junction box is installed on a pair of connection points, as shown in the figure, the power supply connector 724 is linked to the connection point of the bus 20, and the data link connector 754 can receive the connector of the end 54x of the data link of the connection point of the data link group 50. In the figure, the interface module Da is represented as being inserted into the position of the junction box 70. This interface module is linked to the backplane 73 by means of a power supply connector 72i and a data link connector 75i. Arrow F represents the direction in which the interface module is pulled out of the junction box 70 (in the figure, upward) and the direction in which the interface module is inserted into the junction box (in the figure, downward). The local data links 43k and 43l to the electrical equipment items 40k and 40l terminate at the corresponding connectors Ck and C1 linked to the interface module. Advantageously, as indicated previously, the back side of the terminal box 70 (in said figure, represented at the bottom) comprises a support, not represented, provided for holding the connectors Ck and Cl in place. Although this example is described for the interface module Da, this example is by no means limited to this interface module and this example can be applied to all interface modules of the terminal box.

[0199] Specifically, each electrical interface module is selected from the following group:

[0200] an electrical connection module enabling the establishment of an electrical connection between the conductors of the bus and the connectors provided for the local power supply circuit to the item of electrical equipment, via the set of electrical links 72 of the terminal box;

[0201] an electrical switching module enabling control of the power supply of the item of electrical equipment from a remote system. This electrical switching module comprises a switch placed in series on the electrical connection between a conductor of the bus (via the electrical link 72 of the junction box) and a connector provided for a local power supply circuit to the item of electrical equipment. The switching module is linked to the remote system via one of the data links of the set of data links 75. Based on commands received from the remote system, the switching module controls the opening or closing of the switch in order to control the power supply of the item of electrical equipment;

[0202] a voltage conversion module comprising a converter powered by the voltage present on the conductors of the bus via the set of electrical links 72 of the terminal box. This converter corresponds, for example, to a transformer, to a DC-DC voltage converter, to a transformer-rectifier set, etc. At least one output of the converter is linked to a connector provided for a local power supply circuit to an item of electrical equipment; and

[0203] - Electrical protection module. This electrical protection module comprises a circuit breaker placed in series on the electrical connection between the conductors of the bus (via the set of electrical links 72 of the junction box) and the connectors provided for the local electrical power supply circuit to the item of electrical equipment.

[0204] And in particular, each data link interface module is selected from the following group:

[0205] a data link connection module enabling at least one connection to be established between a data link in said set 50 of data links associated with the bus 20 and a connector provided for a local data link to an item of electrical equipment via one of the data links in the set 75 of data links of the junction box;

[0206] - a data link converter module. This module comprises a converter that links to a data link in said data link group 50 associated with the bus 20 via one of the data links in the data link group 75 of the junction box. Furthermore, this converter is linked to a connector provided for a local data link to the item of electrical equipment. For example, this converter enables an optical data link on said data link group to be converted into a wired data link on a local data link. In another example, this converter enables an Ethernet type data link on said data link group to be converted into a USB type data link on a local data link;

[0207] - a wireless data link module. This module comprises a wireless communication transceiver linked to a data link in the set 50 of data links associated with the bus 20 via one of the data links in the set 75 of data links in the junction box. The local data link between this interface module and the item of electrical equipment is then of the wireless type, for example of the WiFi type; and

[0208] - Data acquisition and concentration module. The items of electrical equipment linked to this module by local data links are, for example, sensors. Said module comprises an electronic circuit linked to a data link in said set of data links 50 associated with the bus 20 via one of the data links in the set of data links 75 of the junction box. This electronic circuit is provided for acquiring the data supplied by the sensors, for concentrating the data originating from different sensors and for transmitting these data via said data links in said set of data links.

[0209] Specifically, the junction box 70 may include a hybrid interface module that ensures the electrical interface module function as described above and the data link interface module function as described above. In some cases, this hybrid interface module may encounter a large number of position constraints of the junction box 70.

[0210] exist Fig. 22In the second specific embodiment shown, electrical equipment items 40r, 40s are connected to corresponding connectors 79r, 79s of junction box 70 by corresponding local links 423r, 423s respectively. These local links belong to hybrid power supply and data link type. Connector 79r and connector 79s of junction box are linked to electrical interface module P and data link interface module D by links inside junction box respectively. Therefore, connector 79r is linked to electrical interface module P by electrical link 412r and is linked to data link interface module D by data link 413r. Connector 79s is linked to electrical interface module P by electrical link 412s and is linked to data link interface module D by data link 413s. Preferably, for all the connectors, the pin-outs of different connectors 79r, 79s of junction box are similar. That enables to use exactly the same hybrid local links between connectors to which these electrical equipment items of different electrical equipment items and junction box are connected. As a result, the connection of electrical equipment items is simplified by means of the hybrid local links. Although this second specific embodiment is described using two electrical equipment items and two interface modules, the embodiment is by no means limited to these numbers of electrical equipment items and interface modules. Advantageously, for the local links of the electrical equipment items of the first specific embodiment, the internal links 412r, 412s, 413r, 413s terminate at connectors that can cooperate with the connectors of the interface modules P and D. The back of the junction box 70 includes a support provided for holding the connectors of the internal links in place so that these connectors are connected to the corresponding connectors of the interface modules when the interface modules are installed in their corresponding positions of the junction box. That advantageously enables the removal and installation of the interface modules in the positions E1, E2 ... E6 of the junction box without having to manipulate the connectors of the different internal links. That also enables the connection errors of the links to be avoided then.

[0211] According to the fourth aspect of the present invention and by Fig.23In the embodiment shown, modular elements 60i, 60i+1 for an electrical power distribution network of an aircraft each comprise a housing 28. Each modular element comprises a bus section whose electrical conductors are housed in the housing 28, not shown in the figure. The bus section extends along the length of the modular element under consideration. The bus section of the modular element 60i, 60i+1 comprises a first interconnection point 27a at a first longitudinal end and a second interconnection point 27b at a second longitudinal end. The first interconnection point 27a and the second interconnection point 27b are provided for linking the bus section to a bus section of another modular element arranged longitudinally in series with the modular element under consideration. Thus, in the example shown in the figure, the second interconnection point 27b of the modular element 60i is linked to the first interconnection point 27a of the modular element 60i+1. Advantageously, the link between the buses of two consecutive modular elements corresponds to a connection that enables the absorption of longitudinal deformations of the aircraft. This connection is produced, for example, by means of a connector provided for allowing the conductor elements participating in the connection to slide. The shell 28 corresponds to a structural component of the aircraft, in this case a component provided for supporting a luggage compartment 96 in the cabin of the aircraft. This component is, for example, a metal component or a component made of composite material, the thickness of which is selected to support the thickness of the luggage compartment. When the component is a metal made of aluminum, it comprises, for example, one face 5 mm thick and other faces 2 mm thick. The shell 28 corresponding to each modular element 60i, 60i+1 is fixed to a set of structural frames 94 of the aircraft by means of fixings not represented in the figure. The shells 28 of the different modular elements support the luggage compartment 96 by means of fixings 95. Although not necessary, these fixings 95 can be mounted to slide on the shell 28 of the modular element so as to allow the luggage compartment to slide along the length of the fuselage of the aircraft. In the example shown in the figure, the length of the shell 28 corresponding to each modular element extends along two inter-frame spaces of the fuselage of the aircraft. The term inter-frame space here denotes the space between two consecutive structural frames of the fuselage. Without departing from the scope of the invention, the length of the shell 28 can also extend along a single inter-frame space or along a higher number of inter-frame spaces. The bus section of the modular element comprises connection points 24 at different positions distributed along its length. An opening of the housing 28 is provided facing each connection point 24 so as to allow at least one item of electrical equipment of the aircraft to be connected to the bus section by means of a local electrical link. In the example shown in the figures, the connection points are distributed on the bus section corresponding to each modular element so as to have a connection point 24 for each inter-frame space of the fuselage of the aircraft. Other arrangements are possible without departing from the scope of the invention, for example one connection point for two inter-frame spaces of the fuselage.

[0212] The modular elements 60i, 60i+1 form part of a power distribution network for the aircraft, for example a power distribution network similar to the network 200 or 600 already described with reference to the first and second aspects of the invention. In an advantageous embodiment, each modular element further comprises a data link set, such as the modular elements described with reference to the second aspect of the invention. Therefore, this advantageous embodiment is not described further, all embodiments described with reference to the second aspect of the invention also apply.

[0213] exist Fig.24 In another embodiment shown, the housing 28 of the bus section of the modular element forms part of a floor rail section 98 of the aircraft. To this end, the housing corresponds to a structural component of the aircraft. The floor rail may correspond to a floor rail other than that provided for fixing seats or even to a seat rail provided for fixing seats in the cabin of the aircraft. For the sake of readability, only a portion of the length of the floor rail section 98 is shown in the figure. From an electrical point of view, each modular element is similar to the one described with reference to FIG. Fig.23 The modular elements 60i, 60i+1 described. Therefore, these modular elements can be arranged in series and linked to each other by interconnection points 27a, 27b. In the case of each modular element corresponding to a floor track segment of an aircraft, the floor track segment is placed in series in the cabin of the fuselage of the aircraft to produce a floor track so that the power distribution network of the aircraft can be constructed. In the exemplary embodiment shown in the figure, the three electrical conductors 25a, 25b, 25c of the bus segment are accommodated in the housing 28. However, this example does not limit the number of conductors that the bus can include. Preferably, the conductor elements are arranged horizontally inside the housing 28 so as to allow the connection points 24 to be produced on the sides of the floor track segment 98. The term horizontal here means that when the floor track segment is installed on the floor of the cabin of the fuselage of the aircraft and the aircraft is parked on the ground, the conductor elements are arranged horizontally. The opening 29 of the housing 28 is provided to face each connection point 24 so as to allow at least one electrical equipment item of the aircraft to be connected to the bus segment by means of a local electrical link. Conventionally, when the floor track is a seat track, the top portion of the seat track comprises a groove 97 allowing the seat to be secured.

[0214] Without departing from the scope of the present invention, the different embodiments, examples, variants and alternatives described with respect to the various aspects of the present invention may be combined with each other. For example, in a non-limiting manner, the power distribution network 200 of an aircraft according to the first aspect of the present invention may be produced by assembling modular elements 60 in accordance with the second aspect of the present invention. Similarly, the hybrid power distribution and data communication network 600 according to the third aspect of the present invention may be produced by assembling modular elements according to the second aspect of the present invention. And for example, the junction box 68 described with respect to the second aspect of the present invention may be similar to the junction box 70 described in more detail with respect to the third aspect of the present invention.

Claims

1. A modular element (60) for a hybrid power distribution and data communication network (600) for an aircraft, characterized in that The modular elements include: - a power distribution bus section (20t) extending along the length (L) of the modular element; and - a set of data links (50t) extending along the length of the modular element substantially parallel to the power distribution bus section (20t), And it is characterized by: - the power distribution bus section comprises connection points (24) at different locations distributed along its length; - the data link group comprises connection points (54) at different positions distributed along its length and each arranged near a connection point (24) of the power distribution bus section; - said data link set (50t) comprises connection points, called cross-connection points (55, 55a, 55b), provided for receiving a cross-connection frame (64); - the set of data links (50t) comprises at least one data link (56) between each of the connection points (54) distributed along its length on the one hand and the cross-connection points (55, 55a, 55b) on the other hand; - the power distribution bus section (20t) and the data link group (50t) each comprise a first interconnection point (27a, 57a) provided for linking the power distribution bus section and the data link group, respectively, to a bus section and a data link group of a first other modular element arranged longitudinally in series with the modular element at a first longitudinal end (Ext1) of the modular element; and - The power distribution bus segment and the data link group each include a second interconnection point (27b, 57b), which is provided for linking the power distribution bus segment and the data link group to the bus segment and the data link group of a second other modular element arranged longitudinally in series with the modular element at a second longitudinal end (Ext2) of the modular element opposite to the first longitudinal end (Ext1).

2. The modular element according to claim 1, characterized in that The data link corresponds to an optical fiber.

3. The modular element according to claim 1 or 2, characterized in that The cross-connect points (55, 55a, 55b) comprise a subset of data links terminating in at least one connector, referred to as a cross-connect connector, provided for incorporation in the cross-connect frame (64).

4. The modular element according to claim 3, characterized in that The cross-connection point further comprises at least one fixing provided for allowing fixing of the cross-connection frame to the modular elements.

5. The modular element according to claim 3, characterized in that: - said cross-connection point (55a) on the one hand and said first interconnection point (57a) of said set of data links on the other hand are located in the vicinity of said first longitudinal end (Ext1) of said modular element; - said first interconnection point (57a) of said set of data links comprises a sub-set of data links terminating in at least one connector referred to as a first interconnection connector; and - the arrangement of the cross-connection point (55a) and the first interconnection point (57a) is provided to allow the cross-connect connector and the first interconnection connector to be combined in the cross-connection frame (64) so ​​as to enable the data link group (50t) to be linked to the data link group of the first other modular element in the cross-connection frame.

6. The modular element according to claim 1 or 2, characterized in that: - the connection points (24) distributed along the power distribution bus section (20t) and the connection points (54) distributed along the data link group (50t) each arranged near the connection point (24) of the power distribution bus section form a plurality of pairs of connection points distributed along the modular element; and - Each pair of connection points is provided for receiving a hybrid power distribution and data communications junction box (68) configured to allow connection of one or more local power distribution and / or data distribution links to one or more items of electrical equipment (40a...40j) of the aircraft.

7. The modular element according to claim 1 or 2, characterized in that The power distribution bus section (20t) comprises at least one flexible portion provided for allowing the modular element to deform in response to deformation of a fuselage (F) of an aircraft (1) when the modular element is installed in the fuselage (F) of the aircraft.

8. An aircraft (1) comprising a fuselage (F) and a group of electrical equipment items (40a ... 40j) distributed in said fuselage, characterized in that: - the aircraft comprises a hybrid power distribution and data communications network (600) comprising a set of modular elements (60) according to any one of the preceding claims; and - Each of the electrical equipment items (40a...40j) in the group of electrical equipment items is linked to a connection point (24) of the power distribution bus section (20t) of the modular element via a local power supply link (42) and / or is linked to a connection point (54) of the data link group (50t) of the modular element via a local data link (43).

9. The aircraft according to claim 8, characterized in that: - modular elements of a first subset of said group of modular elements are assembled together so as to form a first hybrid power distribution and data communication subnetwork (160, 160a) extending longitudinally at least partially in said fuselage (F) of said aircraft; - modular elements of a second subset of said group of modular elements are assembled together so as to form a second hybrid power distribution and data communication subnetwork (260, 260a) extending longitudinally at least partially in said fuselage of said aircraft; and - said first hybrid power distribution and data communication subnetwork and said second hybrid power distribution and data communication subnetwork are along isolated paths in said fuselage.

10. The aircraft according to claim 8 or 9, characterized in that Two consecutive modular elements are electrically linked together by means of: - at least one flexible connection; or - at least one connecting element configured to slide on said section of the bus of at least one of two of said modular elements.

11. The aircraft according to claim 8 or 9, characterized in that The cross-connection frame (64) of modular elements accommodates: - an interconnection connector (57b) of said first other modular element; as well as - a set of links between the first interconnection connector (57a) of said modular element and said interconnection connector (57b) of said first other modular element.

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