FR3069969B1 - MODULAR ELEMENT FOR A MIXED NETWORK OF AN AIRCRAFT - Google Patents

Abstract

The modular element (60) for a mixed electrical power distribution and data communication network (600) of an aircraft comprises a busbar section (20t) and a data link assembly (50t) extending substantially parallel along a length (L) of the modular element. The busbar section has connection points (24) at different locations along its length. The set of data links has connection points (54) at different locations along its length, each located near a connection point (24) of the busbar section. It also includes a data link (56) between each of the connection points (54) and a patch point (55, 55a, 55b). The busbar section (20t) and the set of data links (50t) have interconnection points (27a, 57a, 27b, 57b) for connecting the modular element to a first and second second modular elements arranged longitudinally in series with the modular element.

Description

Modular element for a mixed network of an aircraft.

The present invention relates to the field of electrical power equipment of an aircraft. The aircraft, in particular the transport aircraft, comprise electrical equipment distributed in particular in their fuselage. These electrical equipment must be electrically powered and, for some of them, must be connected to a data communication network. For this purpose, the aircraft comprise power cable harnesses and data communication cables. The harnesses of electric power cables generally extend between an electric core of the aircraft (allowing in particular the arrival of electric power from sources of generation and / or deconversion of electrical power) and the electrical equipment to be supplied. The communication cable harnesses generally extend between aircraft communication equipment, for example a switch compliant with the ARINC 664 part 7 standard, and the electrical equipment connected to these communications equipment.

In modern aircraft, more and more functions are being implemented electrically. These functions sometimes require electrical voltages more varied than in the older generations of aircraft (eg 28VDC, 115VAC, 230VAC, 270VDC, 540VDC, etc.), as well as many data communications links between different aircraft equipment. As a result, the harnesses are more complex, larger and of higher mass than in older generations of aircraft. The implementation of harnesses is also more complex. Therefore, it would be desirable to simplify the electrical power distribution and data links of aircraft electrical equipment.

The different harnesses are specific to each type of aircraft and also depend on a configuration of the aircraft specific to the aircraft company operating this aircraft. For example, depending on whether some electrical equipment is installed or not installed in the fuselage, the harnesses include or do not include cables for power supply and data links of said equipment. As a result, the list of electrical equipment to be installed in a particular aircraft must be defined and frozen sufficiently early before the manufacture of said aircraft so as to be able to design, manufacture and install in time the harnesses specific to this aircraft. This list must be defined by as much earlier than the aircraft are generally manufactured by assembly of fuselage sections in which pre-installed sections of harnesses are connected between them after assembly of the fuselage sections. It would be desirable to be able to modify the list of electrical equipment to be installed in the aircraft until a more advanced stage of manufacture of said aircraft. On the other hand, the harnesses being specifically manufactured according to the list of electrical equipment installed in the aircraft, as well as positions in the fuselage of said equipment, a modification of the configuration of the aircraft after its delivery to an airline is difficult. . However, such a modification may be necessary, for example when a resale of the aircraft to another airline or if the airline company wishes to add new electrical equipment in the aircraft. Therefore, it would be desirable to be able to more easily modify the list and the positions of the electrical equipment of an aircraft. SUMMARY OF THE INVENTION

The present invention is intended in particular to provide a solution, at least partially, to these problems.

According to a first aspect of the invention, the invention relates to an aircraft comprising: a fuselage; a set of electric generators, comprising at least a first electric generator and a second electric generator; - a set of electrical equipment, distributed in the fuselage; and an electrical power distribution network comprising: a set of busbars, comprising at least a first set of bars and a second set of bars; and - a switching system,

This aircraft is remarkable in that: - each busbar of the set of busbars extends, at least partly, in a longitudinal direction of the fuselage; the first busbars and the second busbars use segregated paths in the fuselage; the switching system is electrically connected to the first electric generator and the second electric generator, as well as to the first set of barbs and to the second set of bars; the switching system comprises a ditnormal operating mode, in which it is configured to electrically connect the first electric generator to the first busbar and the second electric generator to the second busbar; each busbar of the set of busbars has connection points at different locations distributed along its length; and - each of the electrical equipment of the electrical equipment set is connected to a connection point of a busbar of the busbar set via a local power supply connection. The set of busbars corresponds to an invariant infrastructure of the electrical power distribution network of the aircraft. The different electrical equipments are each connected to a point of connection of a busbar by a local power supply connection. It is thus possible to easily add a new electrical equipment in the fuselage, without modifying this infrastructure: it is sufficient for this to leave in place a local power supply link between this new equipment and a connection point of a busbar. Preferably, this connection point is chosen as close as possible, on the considered set of bars, of the new electrical equipment, in particular to facilitate lamise in place of the local power supply link between the electrical equipment and the busbar. This addition of new electrical equipment can be provided both during the manufacture of the aircraft, and during a modification of the configuration of the aircraft after its delivery to an airline company. It is also easy to move electrical equipment in the fuselage of the aircraft, for example during a modification of the configuration of the aircraft: it suffices to remove its original local power supply, to bring the electrical equipment to its new position in the fuselage and set up a new local power supply to another connection point of a set of bars. The use of a set of busbars rather than cable harnesses also makes it possible to reduce the weight as well as the cost of distributing electrical power of the aircraft. In fact, the electrical conductors of a busbar commonly used by several electrical equipment require a smaller dimension than the sum of the dimensions of separate cables in harnesses, feeding the same electrical equipment.

According to various embodiments that can be implemented in isolation or combined with one another: the first busbar also extends partly in a first antenna of the aircraft and the second busbar also extends partly in a second airfoil. the aircraft; - The first electric generator and the second electric generator electrically sontreliés to the switching system via busbars. Advantageously, the first electrical generator is electrically connected to the switching system via dedicated conductors of the first set of debars and the second electrical generator is electrically connected to the switching system via dedicated conductors of the second set of debars; the electrical power distribution network also comprises a third busbar and a fourth busbar which extend, at least in part, in a longitudinal direction of the fuselage, the first, second, third and fourth busbars passing through segregated paths in the fuselage of the aircraft. Advantageously, the set of electric generators further comprises a third electric generator and a fourth electric generator and, in the normal operating mode, the switching system is configured to electrically connect the third electric generator to the third busbar and the fourth electrical generator to the fourth busbar; - The switching system comprises a reconfigured operating mode, which can be activated in the event of a failure in the power distribution network, in which it is configured for:. establish electrical connections between the electric generators of the set of electric generators and the busbars of the busbar assembly, these electrical connections being modified with respect to electrical connections established in the normal operating mode, and / or. establishing electrical connections between busbars of the set of bus bars; the switching system comprises a main switching device and at least one remote secondary switching device of the main switching device. Advantageously, in the reconfigured operating mode of the switching system, the at least one secondary switching device is operable to establish one or more electrical connections between busbars of the set of busbars; at least one of the busbars of the set of busbars comprises at least two modular sections arranged end to end and electrically connected to one another. Advantageously, a secondary switching device is electrically connected to two modular modular segments of a busbar, so as to establish electrical connections between similar electrical conductors of the two modular sections in the normal operating mode and to establish electrical connectionsbetween a part of the electrical conductors of at least one of the two modular segments and secondly of the electrical conductors of another set of bars, in the reconfigured operating mode.

According to a second aspect of the invention, the invention relates to a modular element for a mixed network of electrical power distribution and data communication of an aircraft. This modular element is remarkable in that it comprises: a section of an electric power distribution busbar extending along a length of the modular element; and a set of data links, this set of data links extending along said length of the modular element, substantially parallel to the busbar section, and in that: the busbar section comprises connection points at different locations distributed along its length; the set of data links comprises connection points at different locations distributed along its length and each located close to a point of connection of the busbar section; the set of data links comprises a connection point, called a patch point, intended to receive a patching bay; the set of data links comprises at least one data link between, on the one hand, each of the connection points distributed according to the length of the connection and, on the other hand, the patching point; the busbar section and the set of data links each have a first interconnection point provided for connecting the busbar and the set of data links respectively to a busbar section and a set of data links; data links of a first other modular element disposed longitudinally in series with the modular element at a first longitudinal end of the modular element; and - the busbar section and the set of data links each have a second interconnection point for connecting the busbar and the set of data links respectively to a busbar section and to a set of data links. data links of a second other modular element longitudinally disposed in series with the modular element, at a second longitudinal end of the modular element opposite the first longitudinal end. The assembly of modular elements in accordance with the invention makes it possible to construct a mixed power distribution and data communication network of an aircraft. With regard to the distribution of electric power, this network has the same advantages as those described with reference to the first aspect of the invention. This network also has similar advantages in terms of data communication. The use of modular elements according to the invention for building the network makes it possible to easily adapt this network to any type of aircraft, without requiring busbars or sets of data links specific to the aircraft considered. , especially as regards their length. The use of one or a few types of modular elements of predetermined lengths makes it possible to adapt such a network to any aircraft, and also to pool and minimize development costs.

According to various embodiments that can be implemented in isolation or combined with one another: the data links correspond to optical fibers; the mixing point comprises a subset of data links terminated by at least one connector, called the patching connector, which can be integrated in the patching bay. Advantageously, the stirring point furthermore comprises at least one attachment provided to allow the fixing of the mixing bay to the modular element. In an advantageous way:. the mixing point on the one hand and the first interconnection point of the set of data links on the other hand are located near the first longitudinal end of the modular element; . the first interconnection point of the set of data links comprises a subset of data links terminated by at least one connector, said first interconnect connector; and. the layout of the patch point and the first interconnection point is provided to allow integration of the patching connector and the first interconnect connector into the patch bay, so as to allow the linkage of the data links to be connected to the patch. set of data outputs of the first other modular element in the drive bay; the modular element is such that: the connection points distributed along the busbar section and the connection points distributed along the set of data links, each arranged near a connection point of the busbar section, form pairs of busbars. connection points distributed along the modular element; and. each pair of connection points is provided to receive a mixed electrical power distribution and data communication branch configured to enable the connection of one or more local power distribution and / or data distribution links to one or more several electrical equipment of the aircraft; - The busbar section comprises at least a flexible portion provided to allow deformations of the modular element in response todeformations of a fuselage of an aircraft when the modular element is installed in said fuselage of an aircraft. The invention also relates to an aircraft comprising a fuselage and a set of electrical equipment distributed in the fuselage.This aircraft is remarkable in that: the aircraft comprises a mixed power distribution and data communication network comprising a set of modular elements as mentioned above; and - each of the electrical equipment of the electrical equipment set is connected to a connection point of the busbar section of a modular element via a local power supply connection and / or a connection point of the set of data links of saidmodular element by a local data link.

In a particular embodiment: modular elements of a first subset of the set of modular elements are assembled together so as to form a first mixed subnetwork of electrical power distribution and data communication extending , at least in part, longitudinally in the fuselage of the aircraft; modular elements of a second subset of the set of modular elements are assembled together so as to form a second mixed subnetwork of electrical power distribution and data communication extending, at least in part, longitudinally in the fuselage of the aircraft; and the first subnetwork and the second subnetwork borrow segregated paths in the fuselage.

In another particular embodiment that can be combined with the preceding embodiment, two consecutive modular elements are electrically interconnected by means of: at least one flexible connection; or - at least one connection element configured to slide on the busbar section of at least one of the two modular elements.

In still another particular embodiment that can be combined with the previous ones, the patching bay of a modular element receives: an interconnection connector of the first other modular element; and a set of links between the first interconnect connector of the modular element and the interconnection connector of the first other modular element.

According to a third aspect of the invention, the invention relates to an aircraft comprising: a fuselage; - a set of electrical equipment, distributed in the fuselage; and a mixed network of electric power distribution and data communication.

This aircraft is remarkable in that: the mixed power distribution and data communication network comprises: a set of busbars, comprising at least one set of electric power distribution bars; and at least one set of data links, the mixed power distribution and data communication network is configured such that a set of data links is associated with each set of bars of the set of debarres ; each busbar of the set of busbars extends, at least in part, in a longitudinal direction of the fuselage; each set of data links extends substantially parallel to the busbar with which it is associated; each busbar of the set of busbars has connection points at different locations distributed along its length; and each set of data links has disconnection points at different locations distributed along its length and arranged each close to a connection point of the busbar associated with the set of data links, so as to form pairs of points. connection system each comprising a connection point of the debarreset and a connection point of the associated data linket; and - each of the electrical equipment of the electrical equipment set is connected to a pair of connection points via a local power supply link and / or via a local data link.

As for the first aspect of the invention, the set of debarres corresponds to an invariant infrastructure of the electrical power distribution network of the aircraft. It has the same advantages as those described with reference to the first aspect of the invention. The at least one set of data links corresponds to the invariant infrastructure of the data communication network. The electrical equipment required for a data communication link is each connected to a connection point of the set of data links by a local data link. This has advantages similar to those of the electrical power distribution network with respect to the addition or removal of electrical equipment. When equipment requires both a power supply and a data link, the fact that each connection point of the set of data links is located close to a connection point of the busbar to which the set of links is associated data, facilitates the connection of the equipment to the power distribution network infrastructure and the data communication network infrastructure: the local power supply and the local data link can thus electrical equipment and said connection points.

In one embodiment, the mixed power distribution and data communication network comprises a set of branch boxes, each branch box is attached to a pair of connection points. Advantageously, a branch box of the set of junction boxes comprises: at least one power supply connector configured tooperate with the connection point of the busbar belonging to the set of connection points to which the termination box is connected; . at least one data link connector configured to cooperate with the connection point of the set of data links belonging to the pair of connection points to which the drop box is connected; and. a set of locations for receiving interface modules; . a set of electrical links extending between the power supply connector and the different locations provided for receiving the interface modules; and. a set of data links extending between the data links connector and the different locations for receiving the interface modules.

Still advantageously, the aircraft comprises: at least one electrical interface module in a junction box location and / or at least one data link interface module in a junction box location; and. at least one local power supply link between said at least one electrical interface module and electrical equipment of the aircraft and / or at least one local data link between said at least one data link interface module and a device electric aircraft.

The electrical interface module is for example selected by the following set: - an electrical connection module; an electrical switching module; - a voltage conversion module; and - an electrical protection module.

The data link interface module is for example chosen from the following set: a data link connection module; a data link conversion module; - a wireless data link module; and a data acquisition and concentration module.

Advantageously, the aircraft comprises, in a location of the junction box, a mixed interface module providing an electrical interface module function and a data link interface module function.

Advantageously, the aircraft is such that: - the data links of the set of data links associated with the busbar game correspond to optical fibers; the set of data links extending between the data links connector and the different locations provided for receiving the interface modules comprises: a data link converter; . fiber optic data links between the data link connector and the data link converter; . data links using electrical signals between the data link converter and the different locations for receiving the interface modules.

In a particular embodiment that can be combined with the prior art: at least one busbar of the set of busbars comprises at least two modular sections arranged end to end and electrically connected to each other; - Each of the at least two modular sections of the at least one set of debars is part of a modular element also comprising a set of data links extending substantially parallele modular section considered; and - the sets of data links of consecutive modular elements are interconnected to form the set of data links associated with the busbar considered. DETAILED DESCRIPTION: The invention will be better understood on reading the description which follows and on examining the appended figures.

FIG. 1 schematically represents an aircraft comprising an electric power distribution network, according to one embodiment of the invention;

FIG. 2 diagrammatically represents an aircraft comprising an electric power distribution network, in accordance with another embodiment of the invention;

Fig. 3 is a sectional view taken along the line 11a-11a of Fig. 2;

Figure 4 is a perspective view of a busbar;

Figure 5 is a schematic view of a portion of the fuselage of the aircraft shown in Figure 1;

FIGS. 6a and 6b show, schematically, a portion of the electrical power distribution network of the aircraft shown in FIG. 2, comprising secondary switches according to a particular embodiment;

FIGS. 7a and 7b show schematically a portion of the electric power distribution network of the aircraft shown in FIG. 1 or in FIG. 2, comprising secondary switches in accordance with a particular embodiment;

FIG. 8 schematically represents a modular element for a mixed network of electrical power distribution and data communication of an aircraft, according to one embodiment of the invention;

FIG. 9 schematically represents a modular element for a mixed network of electric power distribution and data communication of an aircraft, in accordance with another embodiment of the invention;

Figures 10 and 11 show data links of the modular elements respectively corresponding to Figures 8 and 9;

Figure 12 shows an example of interconnection of two modular elements;

Figure 13 schematically shows a modular element equipped with junction boxes;

FIG. 14 schematically represents an aircraft comprising a mixed power distribution and data communication network, comprising a set of modular elements;

FIG. 15 schematically represents an aircraft comprising a mixed network of electrical power distribution and data communication, in accordance with one embodiment of the invention;

FIG. 16 schematically represents a busbar of the FIG. 15 network and a set of data links associated with this busbar;

FIG. 17 schematically shows the busbar and the data link assembly of FIG. 16, equipped with derivation boxes;

Figures 18 and 19 schematically show two examples of branch boxes according to embodiments of the invention;

Figure 20 is a schematic view of a portion of the fuselage of the aircraft shown in Figure 15;

Figures 21a and 22 illustrate the connection of electrical equipment to a junction box such as those shown in Figure 18 or Figure 19.

Fig. 21b shows an exemplary junction box as seen in sectional view taken along the line IIIa-IIIa of Fig. 21a.

According to an embodiment in accordance with the first aspect of the invention, the aircraft 1 represented in FIG. 1 comprises a fuselage F and a set of electric generators comprising a first generatorG1 associated with an engine E1 of the aircraft and a second generator G2associated with an engine E2 of the aircraft. The aircraft 1 also comprises an electric power distribution network 200. The electric power distribution network comprises a set of busbars, among which a first busbar 120, 120a and a second busbar 220, 220a. Each of the two busbars comprises at least one part 120, respectively 220, extending in a longitudinal direction of the fuselage F. These two busbars take segregated paths in the fuselage F of the aircraft, respectively in a left part of the fuselage (or port) for the part 120 of the first busbar and in a right part of the fuselage (or starboard) for the part 220 of the second game debarres. This makes it possible to avoid a common fault on the two sets of decares in the event of an incident in a part of the fuselage. Advantageously, the first busbar comprises a portion 120a in a left wing of the aircraft and the second busbar has a portion 220a in a right wing of the aircraft. Similar conductors of part 120a and part 120 are electrically connected to each other. Likewise, similar conductors of portion 220a and portion 220 are electrically connected to each other. The electrical power distribution network 200 also comprises a switching system 30. This switching system is electrically electrically strapped to the first electric generator G1 and the second electric generator G2, as well as to the first busbar 120, 120a and the second busbar 220, 220a. The switching system 30 comprises a so-called normal operating mode, in which it is configured to electrically connect the first electric generator G1 to the first busbar 120, 120a and the second electrical generator G2 to the second set of bar 220, 220a. In a particular embodiment, the first electric generator G1 is electrically connected to the switching system 30 via dedicated conductors (or bars) of the first set of debars 120, 120a and the second electrical generator G2 is electrically connected to the switching system via dedicated conductors of the second busbar 220, 220a. For example, the first generator G1 located in the left wing of the aircraft, close to the engine E1, is connected to dedicated conductors of the portion 120a of the first busbar, by a local power supply connection between this generator and this part120a of the first busbar. Similarly, the second generatorG2 located in the right wing of the aircraft, close to the engine E2, is connected to dedicated conductors of the portion 220a of the second busbar, bya local power supply connection between the generator and this part 220a of the second busbar. This makes it possible to avoid the routing of specific wirings in the wings and in the fuselage of the aircraft. Aircraft 1 also comprises a set of electrical equipment distributed in the fuselage and each set of bars of the set of landing gates comprises connection points at different locations distributed along its length. For reasons of clarity of the figure, these electrical equipment and these connection points are not shown in Figure 1, but in Figure 5 illustrating a portion of the fuselage F. Thus, the aircraft 1comporte a set of electrical equipment 40a. .. 40j in the fuselage portion shown in Figure 5. These electrical equipment each require a power supply to operate. The first set of bars 120 has connection points 24a ... 24h at different locations distributed along its length, in its part shown in the figure. The second busbar 220 has connection points 24i ... 24p at different locations distributed along its length, in its partierepresentée in the figure. Each of the electrical equipment of the electrical equipment assembly is connected to a connection point of a busbar set of the busbar assembly, via a local power supply link 42. Thus, for example, electrical equipment 40a is connected to the connection point 24a of the first busbar 120. The electrical equipment 40b, 40c and 40d are connected to the connection point 24d. The electrical equipment 40e and 40f are connected to the connection point 24g. The electrical equipment 40g is connected to the connection point 24i of the second busbar 220. The electrical equipment 40h and 40i are connected to the connection point 24I. The electrical equipment 40j is connected to the connection point 24o. Advantageously, the connection points 24a, 24d, 24g, 24i, 24I and 24o receiving local electrical supply links 42of electrical equipment are equipped with junction boxes provided with plugs or connectors making it possible to easily connect these power connections. Local electrical 42. Advantageously, the other connection points not receiving a local power supply link are not equipped with such junction boxes to limit the mass of the aircraft. In a particular embodiment, two consecutive connection points of a busbar are spaced apart by a distance of about 50 to 70 cm. This distance corresponds for example to the distance between two structural frames of the aircraft. The junction boxes can for example be installed every 4 or 5 connection points in a major part of the fuselage. However, in areas of the fuselage corresponding to a particularly high density of electrical equipment, all connection points, or sometimes a connection point out of two, may be equipped with junction boxes. The set of busbars forms an infrastructure of the electrical power distribution network 200 of the aircraft. The different electrical equipment 40a ... 40i are each connected to a point of connection of a busbar by a local power supply connection42. It is thus possible to easily add new electrical equipment in the fuselage, without modifying this infrastructure: it suffices for this to put in place a local power supply connection between this new equipment and a connection point of a busbar. Preferably, this connection point is chosen as close as possible, on the set of bars considered, of the new electrical equipment. This addition of new electrical equipment can be provided both during the manufacture of the aircraft, and during a modification of the configuration of the aircraft after its delivery to an airline. It is also easy to move electrical equipment in the fuselage of the aircraft, for example during a modification of the configuration of the aircraft: it suffices to remove the original local power supply, to bring the electrical equipment to its new position in the fuselage and to set up a new local power supply link to another disconnection point of a busbar. The use of a set of busbars rather than cable harnesses also makes it possible to reduce the power distribution network of the electric power of the aircraft. In fact, the electrical conductors of a busbar commonly used by several electrical equipment require a smaller dimension than the sum of the dimensions of separate cables in harnesses, feeding the same electrical equipment.

In another embodiment shown in Figure 2, the aircraft1 further comprises a third generator G3 near the engine E1 and a fourth generator G4 near the engine E2. The set of busbars further comprises a third busbar 320, 320a and a fourth busbar 420, 420a. The third busbar and the fourth busbar each comprise a portion 320, respectively420, extending in a longitudinal direction of the fuselage F. The four bus bars take segregated paths in the fuselage, as shown in FIG. , part 120 of the first busbar travels in a left part of the fuselage and part 220 of the second busbar runs in a right part of the fuselage. Similarly, the part 320 of the third busbar runs in a left part of the fuselage and the part 420 of the fourth busbar runs in a right part of the fuselage. Part 120 of the first set of bars and part 220 of the second set of bars run in an upper part of the fuselage, while part 320 of the third busbar and part 420 of the fourth set of busbars run in a lower part of the fuselage. Advantageously, the third busbar comprises part 320a in the left wing of the aircraft and the fourth busbarcomporte part 420a in the right wing of the aircraft. As the first busbar 120, 120a and the second busbar 220, 220a, the third busbar 320, 320a and the fourth busbar 420, 420a are also connected to the switching system 30. In the normal operating mode, the system switch 30 is configured to electrically connect the third generator G3 to the third set of bars and the fourth generator G4 to the fourth set of barges. In a particular embodiment, the third electrical generator G3 is electrically connected to the switching system 30 via dedicated conductors (or bars) of the third set of busbars 320, 320a and the fourth electrical generator G4 is electrically connected to the switching system via dedicated conductors of the fourth busbar 420,420a. For example, the third generator G3 located in the left wing of the aircraft, near the engine E1, is connected to dedicated conductors of part 320a of the third busbar, by a local power supply link between this generator and this part 320a of the third game debarres. Similarly, the fourth generator G4 located in the right wing of the aircraft, close to the engine E2, is connected to dedicated conductors of the portion 420a of the fourth busbar, by a local power supply connection between this generator and this part 420a of the fourth game debarres.

In an exemplary embodiment shown in FIG. 4, a set 20 of the set of busbars comprises a set of electric conductors corresponding to bars 25a, 25b, 25c. Although three bars 25a, 25b and 25c are shown in the figure, this number of barges should not be interpreted in a limiting manner of the invention. The craftman will be able to adapt the number of bars according to the different electrical ratings to be distributed to the electrical equipment of the aircraft via the electrical power distribution network 200 and depending on the number of separate segregations required. These bars run parallel to or substantially parallel path along a length of the clearance 20 game.They are separated from each other by an electrically insulating material 22, for example a plastic or air.The set of bars is surrounded by an envelope 28. According to one embodiment, this envelope is formed of an electrically insulating material. According to another embodiment, the envelope 28 is formed of an electrically conductive material. An electrically insulating material 22 is then placed between the bars 25a, 25b and 25c on the one hand and the envelope 28 on the other hand. This other embodiment is advantageous because it makes it possible to use the envelope 28 as an electrical current return conductor (for example AC neutral conductor, 0 volts in continuous voltage, etc.) and / or as a shielding electromagnetic circuit for preventing electromagnetic disturbances of electrical equipment of the aircraft by electric currents flowing in the bars 25a, 25b, 25c. The busbar portion 20 shown in the figure comprises a connection point 24. This connection point comprises an opening 29 of the envelope 28, for example on an upper face (in the figure) of said envelope. The opening 29 thus delimits two parts 28a and 28b of the upper faces of the envelope 28. The part of the set of bars 25a, 25b, 25c situated opposite the opening 29 is devoid of insulator 28 when this insulator corresponds to a plastic material, so as to allow the connection of a connecting means on the bars 25a, 25b, 25c through the opening 29. Such a connection means corresponds for example to a connector comprising sets of spring blades, susceptible to be set up on the bars.

Advantageously, the switching system 30 comprises a so-called reconfigured operating mode, which can be activated in the event of a failure in the power distribution network. In the reconfigured operating mode, according to a first variant, the switching system 30 is configured to establish electrical connections between, on the one hand, the electric generators G1, G2 (and possibly G3, G4 according to the embodiment) of the electric generator set. and on the other hand the busbars of the set of bars games, these electrical connections being modified with respect to electrical connections established in the normal operating mode. According to a second variant, the switching system 30 is configured to establish electrical connections between busbars of the set of bars. This second variant can be combined with the first variant. For example, in the event of a failure of the generator G3 (which feeds the third busbar 320, 320a in the normal operating mode), the switching system modifies the electrical connections so as to supply the first busbar 120, 120a, as well as the busbar. third set of debars 320, 320a, from the generator G1.

In a particular embodiment, the switching system comprises a main switching device and at least one remote secondary switching device of the main switching device. The main switching device is similar to the switching system shown in Figures 1, 2 and 3 and previously described. It ensures for example an electric heart function of the aircraft. The at least one secondary switching device is controlled by the switching system 30 to which it is connected by a specific communication link or by a communication network of the aircraft. In the example shown in FIGS. 6a and 6b, a secondary switching device 32a is deported at one end of the busbars of the set of clearances, for example in a rear part or in a front part of the fuselage F of the aircraft. . The secondary switching device 32 has four switches K1, K2, K3, K4, corresponding for example to contactors that can be controlled by the switching system 30. For example, these contactors comprise at least as many contacts as the busbars comprise of electrical conductors 25a, 25b, 25c, etc. In the normal operating mode of the switching system, as shown in FIG. 6a, the switch contacts K1, K2, K3 and K4 are open, so that they do not establish any connection between the busbars 120, 220, 320. and 420. FIG. 6b illustrates a situation in which a failure X has occurred on the first busbar 120. This failure has the effect of electrically isolating between them two portions 120x and 120y of the first set 120. As a result, in normal operation, the part 120y of the first busbar is no longer supplied by the first generatorG1 via the switching system 30. To solve this problem, in the reconfigured operating mode, the switching system controls the remote switching device. 32a, so as to close the contacts of the switch K1. This has the effect of connecting between the similar conductors on the one hand the portion 120y of the first set of debars and the other part of the third busbar 320. This portion 120y of the first busbar is then powered by the third generator G3 viale switching system 30.

In an advantageous embodiment, at least one of the bar sets of the set of busbars comprises at least two sections arranged end to end and electrically connected to each other. This is particularly interesting when the aircraft 1 is formed by assembling fuselage fuselage F. These fuselage sections are then pre-equipped strips of busbars that are interconnected during or after assembly of the fuselage sections. For example, each of the parts 120, 220, 320 and 420 of the first, second, third and fourth sets of beams is composed of an assembly of busbar sections arranged end to end and electrically connected to each other. According to a first alternative, the sections of busbars are specific to the sections of fuselage in which they are integrated. According to a second alternative, each section of busbars integrated into a fuselage section is formed of an assembly of modular sections of busbars arranged end to end and electrically connected to each other. Advantageously, these modular busbar sections correspond to a limited number of lengths judiciously chosen so as to allow the pre-equipment of the different fuselage sections by combining modular paths corresponding to these predefined lengths.

In particular, a secondary switching device 32b is electrically electrically strapped to two consecutive sections (or two modular sections) of a busbar. In an example shown in FIGS. 7a and 7b, a secondary switching device 32b is set up between two busbar sections 120j and 220j and second two busbar segments 120k and 220k. The sections 120j and 120k correspond to two consecutive sections of the first busbar 120. The sections 220j and 220k correspond to two consecutive sections of the second busbar 220. The secondary switching device 32b has four switches K11, K12, K13, K14, corresponding for example to contactors that can be controlled by the switching system 30. For example, these contactors comprise at least one of the contacts that the busbars comprise of electrical conductors 25a, 25b, 25c, and so on. In the normal operating mode of the switching system, as shown in FIG. 7a, the contacts of the switches K11 and K12 are closed so as to establish electrical connections between similar electrical conductors of the sections 120j and 120k of the first busbar on the one hand and 220j and 220k of the second game debars on the other hand. The contacts of the switches K13 and K14 are open, so that they do not establish any connection between the first set of debars and the second set of bars. FIG. 7b illustrates a situation in which a failure X has occurred on the section 120j first set of debars 120. The switching system 30, although not shown in the figure, is considered to be on the left of the sections 120j and 220j in the figure. Failure X has the effect of interrupting the power supply 120k the game ga generator G1via the switching system 30 and the set of bars 120j. To solve this problem, in a reconfigured operation mode, the switching system 30 controls the opening of the contacts of the switch K11 and the closing of the contacts of the switch K14. This has the effect of connecting together the similar contacts section 220j of the second busbar and the section 120k of the first set of bars. This section 120k of the first busbar is then powered by the second generator G2 via the switching system 30 and the game debarres 220j.

According to an embodiment in accordance with the second aspect of the invention, as represented in FIG. 8, the modular element 60 for a mixed power distribution and data communication network of an aircraft comprises: a section of a game electrical power distribution bars 20t, extending along a length L of the modular element 60; and a set of data links 50t, this set of data links extending along said length L of the modular element, in a manner substantially parallel to the busbar section 20t.

Preferably, the busbar section 20t and the set of data links 50t are mounted integral with each other. For this, in the example shown in FIG. 8, the busbar section 20t and the set of data links 50t are fixed on a common carrier 62. In another embodiment, not shown, the data links of FIG. the set of data links 50t are attached to the busbar section 20t. In a particular embodiment in which these data links correspond to optical fiber plies, these fiber optic plies are for example glued to one face of the busbars 20t.

According to a first alternative, the data links of the set of data links 50t correspond to twisted pairs of copper or aluminum wires. According to another alternative, the data links correspond to optical fibers. In addition to a significant gain in mass, these optical fibers have the advantage of being insensitive to possible electromagnetic disturbances that could be produced when electrical current circulates in bars of the busbar section 20t.

The busbar section 20t has connection points 24 at different locations distributed along its length. The set of data links 50t has connection points 54 at different locations distributed along its length and each arranged near (or opposite) a connection point 24 of the busbar section 20t. The modular element 60 thus comprises pairs of connection points, each comprising on the one hand a connection point 24 of the busbar section 20t and on the other hand the connection point 54 of the set of data links 50t, located near said connection point 24. The busbar slot 20t includes a first interconnection point 27a and the set of data links 50t has a first interconnect 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 connecting the busbar 20t and the set of data links. Respectively, to a busbar section and to a set of data links of a first other modular element arranged longitudinally in series with the modular element 60. The busbar section 20c includes a second interconnection point 27b and the assembly data link 50t has a second interconnection point 57b. These second interconnection points 27b and 57b are located at a second longitudinal end Ext2 of the modular element 60. These second interconnection points 27b and 57b are provided for connecting the busbar section 20t and the set of data links 50t respectively. to a busbar section and to a set of data links of another second modular element arranged longitudinally in series with the modular element 60. The set of data links 50t also comprises at least one connection point, called a mixing point. , intended to receive a brewing baiede. According to a first variant, this at least one unbrushing point is situated at a longitudinal end of the modular element 60. In the example represented in FIG. 8, the set of data links 50t comprises two brewing points 55a and 55b situated respectively at the first longitudinal end Ext1 and at the second longitudinal end Ext2 of the modular element 60. According to a second variantillustrated in FIG. 9, the at least one stirring point 55 is situated between two connection points 54 of the set of links. 50t data. These two variants can be combined together: the modular element 60comporte then one or two brewing points 55a, 55b to at least one of the longitudinal ends Ext, Ext2, and at least one point of separation between two connection points 54. The set of data links 50t also comprises at least one data link between, on the one hand, each of the connection points distributed along its length and, on the other hand, the patching point. These data links 56 are not shown in FIGS. 8 and 9 for reasons of clarity of said figures. As shown in FIG. 10 schematically illustrating the data links corresponding to FIG. 8, at least one data link is provided between, on the one hand, each mixing point 55a, 55b and on the other hand each connection point 54a, 54b. 54f. For example, the set of data links 50t has at least one data link 56b1 between the scrubbing point 55a and the connection point 54b and at least one data link 56b2 between the patch point 55b and the connection point 54b.Several Data links 56 may be provided between each debriding point 55a, 55b and the different connection points 54a ... 54f, although only one link is shown in FIG. 10. In particular, when the data links are implemented at By means of optical fibers, each link shown in the figure may in fact correspond to a set of optical fibers, for example 8 optical fibers.

Advantageously, the set of data links 50 also includes data links 58 between the first interconnection point 57a and the second interconnection point 57b. These data links 58 are particularly useful for establishing communications through several modular elements 60.

In the example shown in FIG. 11 schematically illustrating the data links corresponding to FIG. 9, at least one data link 56a, 56b,..., 56f is provided between the debreading point 55 and each connection point 54a, 54b. ... 54f. In addition, at least one data link 58b is provided between the mixing point 55 and each interconnection point 57a, 57b.

The brewing point (s) is (are) intended to receive a stirring bay. The modular element 60 has for example at least oneadjustment provided to allow the fixing of the mixing bay on the modular element. This attachment may in particular correspond to a nut or a screw, a mechanical part provided to cooperate with a part of the brewing chamber so as to clap it on the modular element, etc.. Advantageously, in the brewing points 55, 55a, 55b, the data links 56 arrive on one or more brewing connectors that can be integrated into the corresponding brewing bay.

An example of interconnection of two modularconscious elements is illustrated in FIG. 12, in the case of modular elements 60i, 60i + 1 similar to the modular element 60 shown in FIG. 8. The first end Ext1 of the modular element 60i + 1 is connected to the second Ext2 end of the modular element 60i. For this, these two ends are arranged end to end, close to each other, so that the first interconnection point 27a of the busbar 20t of the modular element 60i + 1 faces the second point of interconnection 27b of the busbar 20t of the modular element 60i and the first interconnection point 57a of the set of data links 50t of the modular element 60i + 1 faces the second interconnection point 57b of the set of links of 50t data of the modular element 60i. The similar drivers of the connection points 27a and 27b are electrically interconnected by means of electrical connections 66. In a first exemplary embodiment, the connection points 27a and 27b correspond to terminal blocks and the electrical connections 66 correspond to cables of appropriate section. In a second embodiment, the connection points 27a and 27b correspond to sub-connectors. The electrical connections 66 then correspond for example to a connection of said connectors. In particular, when they are connected, these connectors can slide longitudinally relative to each other so as to absorb longitudinal displacements of the two modular elements relative to each other, especially during structural deformations of the aircraft in which the modular elements are installed. A patch bay 64 is installed to receive the interconnection points 57a of the modular element 60i + 1 and 57b of the modular element 60i, as well as the stirring points 55a of the modular element 60i + 1 and 55b of the modular element 60i. Advantageously, these interconnection and brewing points are equipped with connectors which are then integrated into the brewing bay. The mixing bay allows the necessary interconnections to be put in place, for example by means of jumpers. It also allows the integration of active elements such as switch or router type, when such equipment is needed to achieve the interconnections. These active elements correspond, for example, to switches or routers of Ethernet or USB type. Garters correspond to filament jumpers when the data links are of wired type (for example twisted pairs of copper or aluminum wires) or to optical jumpers when the data links correspond to optic fibers. The brewing bay receiving the points of interconnection 57a, 57b and the brewing points 55a, 55b, allows the establishment of garters to achieve different types of interconnections. A first type of interconnection corresponds to an interconnection of a first link between one of the patching points 55a, 55b and a connection point 24 of the data link assembly of one of the modular elements 60i, 60i + 1, with a second link between one of the patch points 55a, 55b and a connection point 24 of the data link assembly of one of the modular elements 60i, 60i + 1. A second type of interconnectioncorresponds to an interconnection of a first link between one of the brewing points 55a, 55b and a connection point 24 of the given data link assembly of one of the modular elements 60i, 60i + 1, with a second arrival arriving at one of the points of interconnection 57a, 57b. A third type of interconnection is an interconnection of a first link arriving at one of the points of interconnection 57a, 57b, with a second link arriving at the other point of interconnection 57a, 57b. the mixing bay 64 are possible without departing from the scope of the invention. According to a first example, the mixing bay is fixed on at least one of the modular elements 60i, 60i + 1 so as to cover the brewing points 55a, 55b and the points of interconnection 57a, 57b, which enter the bay of brewing by one or more cuts thereof. According to a second example, the brewing bay isfixed either on at least one of the modular elements 60i, 60i + 1, near its end Ext2, Ext1, or on the structure of the aircraft near the ends Ext2, Ext1 of the elements modular 60i, 60i + 1, without the patching bay covers these interconnection points and brewing. The interconnection points 57a, 57b and the patch points 55a, 55b are then set at data link ends of the data link assemblies 50t sufficiently long and sufficiently flexible to allow the integration of said interconnection and patching points into the slot. Brewing 64.

In a particular embodiment shown in FIG. 13, each of the different pairs of connection points 24, 54 of the modular element 60 is designed to receive a mixed distribution box for electrical power distribution and data communication 68. junction box allows the connection of one or more local power distribution and / or data distribution links to one or more electrical equipment of the aircraft. The use of mixed junction boxes makes it easy to connect the electrical equipment to the modular elements 60: thus, it is not necessary to connect each electrical equipment to the set of gates 20t and to a data link of the set of data links 50 . The junction box 68 is for example provided with connectors facilitating the connection of local links to the electrical equipment. Advantageously, a pair of connection points is equipped with a junction box only if an electrical equipment is matched to this pair of connection points. This avoids an unnecessary increase in the mass of the aircraft.

In another particular embodiment, the stretcher section 20t comprises at least one flexible part intended to allow deformations of the modular element 60 in response to deformations of the fuselage F of an aircraft when the modular element is installed in said fuselage. of an aircraft. For example, to provide such a flexible portion, each electrically conductive member of the busbar portion 20 includes a spring over a portion of its length.

In a particular embodiment, the length L of a modular element 60 is between 3 and 10 meters, preferably between 6 and 10 meters. In particular, two consecutive pairs of connection points of the modular element are spaced apart by a distance of about 50 to 70 cm. This distance corresponds for example to the distance between two structural frames of the aircraft. The junction boxes 68 may for example be installed every 4 or 5 pairs of connection points in a major part of the fuselage. However, in areas of the fuselage corresponding to a particularly high density of electrical equipment, all couples of connection points, or sometimes a couple of connection connections out of two, can be equipped with junction boxes. The invention also relates to an aircraft 1 comprising an assembly F and a set of electrical equipment distributed in the fuselage. As shown in FIG. 14, the aircraft comprises a network of electrical power distribution and data communication 600 comprising a set of modular elements 60a ... 60qsimilar to the aforementioned modular element 60. The mixed network 600 comprises a first mixed sub-network of electrical power distribution and data communication 160, 160a. This first mixed sub-network is formed by assembling between them modular elements 60a ... 60h forming a first subset of the set of modular elements. The first mixed network includes a portion 160 which extends longitudinallyin the fuselage F of the aircraft. Advantageously, it also includes a part 160a which extends in the left wing of the aircraft. The mixed network600 also includes a second mixed power distribution and data communication subnetwork 260, 260a. The second mixed subnetwork is formed by assembling between themmodular elements 60i ... 60q forming a second subset of the set of modular elements. The second mixed sub-network comprises a portion 260 which extends longitudinally in the fuselage F of the aircraft. Advantageously, it also includes a portion 260a which extends in the right wing of the aircraft. The first sub-network 160, 160a and the second sub-network 260, 260a take segregated paths in the fuselage F, for example in a left part of the fuselage for the first sub-network and in a right part of the fuselage for the second sub-network, as shown FIG. 14. Two consecutive modular elements are, for example, assembled together as described with reference to FIG. 12.Each electrical equipment of the set of electrical equipment is truncated at a connection point 24 of the busbar section 20t of FIG. a modular element 60a ... 60q via a local power supply link and / or at a connection point 54 of the data link set 50tdudit modular element by a local data link. For reasons of clarity in Figure 14, electrical equipment and local links are not shown. The use of modular elements according to the invention to build the mixed network 600 makes it easy to adapt this network to any type of aircraft, without the need for busbars or sets of data links specific to the aircraft in question, particularly with regard to their length. The use of one or a few types of modular elements of predetermined lengths makes it possible to adapt such a network to any type of aircraft.

According to an embodiment according to the third aspect of the invention, the aircraft 1 represented in FIG. 15 comprises a fuselage F and a set of electric generators comprising a first generatorG1 associated with an engine E1 of the aircraft and a second generator G2associated with an engine E2 of the aircraft. The aircraft 1 also comprises a mixed power distribution and data communication network 600. The mixed network 600 comprises a set of debarres games, among which a first busbar and a second set of debars. A set of data links is associated with each set of debars in the set of busbars. Each set of data links extends substantially parallel to the busbar with which it is associated. The first busbar and the set of data links associated with this first busbar form a first mixed sub-network of power distribution and data communication 160,160a. The second busbar and the set of data links associated with this second busbar form a second sub-network of electrical power distribution and data communication 260, 260a. Each of the two sub-networks comprises at least 160 parts, respectively 260, extending in a longitudinal direction of the fuselage F. These two sub-networks take segregated paths in the fuselage F of the aircraft, respectively in a left part of the fuselage (or port) for the part 160 of the first sub-network and in a right part of the fuselage (or starboard) for the part 260 of the second sub-network. This makes it possible to avoid a common fault on the two sub-networks in the event of an incident in a part of the fuselage. Advantageously, the first sub-network comprises a portion 160a in a left wing of the aircraft and the second sub-network comprises a portion 260a in a right wing of the aircraft. Advantageously, the electric power distribution network also comprises a switching system 30.This switching system is electrically connected to the first electric generator G1 and the second electric generator G2, as well as to the first set of bars of the first subarray 160, 160a and the second game debars second subnet 260, 260a. The switching system 30comprises a so-called normal operating mode, in which it is configured to electrically connect the first electric generator G1 to the first set of bars and the second electric generator G2 to the second set of barges. The aircraft 1 also comprises a set of electrical equipment distributed in the fuselage. For the sake of clarity of the figure, these electrical equipment are not shown in FIG.

As shown in FIG. 16, each set of bars 20 of the set of busbars has connection points 24 at different locations distributed along its length and each set of data links 50 has connection points 54 at different locations distributed along its length. . The connection points 54 are each located near (or opposite) a connection point 24 of the busbar 20 with which the set of data links 50 is associated, so as to form pairs of connection points each comprising a point connection 24 of the busbar and a connection point 54 of the set of data links associated. In a particular embodiment, two consecutive pairs of connection points are spaced apart by a distance of about 50 to 70 cm. This distance corresponds for example to the distance between two structural frames of the aircraft.

Although the mixed network of electrical power distribution and data communication 600 has been described in the particular case where it comprises 2 sub-networks 160, 160a and 260, 260a, the third aspect of the invention is in no way limited to this number of under networks. For example, the mixed network 600 may comprise four sub-networks borrowing segregated paths in the fuselage of the aircraft, in the same way that the electrical power distribution network 200 according to the first aspect of the invention may comprise four sets of bars borrowing segregated scrolls in the fuselage.

In an advantageous embodiment, at least one set of bars 20 of the set of busbars comprises at least two modular sections arranged end to end and electrically connected to each other. This at least one busbar is part of one of the sub-networks 160, 160a or 260,260a. Each of said at least two modular sections of the at least one busbar is part of a modular element also comprising a set of data links extending substantially parallel modular section considered. 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 interconnected so as to form the set of data links 50 associated with the busbar 20 considered.

Advantageously, the mixed power distribution and data communication network 600 comprises a set of branch boxes, each branch box 70 being connected to a pair of connection points 24, 54 as shown in FIG. derivation are provided to allow the connection of the electrical equipment of the aircraft to the connection points 24 of the deck 20 and the connection points 54 of the set of data links 50. Advantageously still, the number of distribution boxes 70 installed on the power distribution and data distribution subnetworks are a function of the density of electrical equipment in the fuselage F of the aircraft. For example, in areas of the fuselage where the density of electrical equipment is average, the junction boxes can be installed every 4 or 5 connection terminal pairs 24, 54, as shown in the lower part of Figure 17. In areas of the fuselage fuselage where the density of the electrical equipment is higher, the junction boxes can be installedisall 2 couples of connection points, or even on each couple of points of connection, as shown in the upper part of Figure 17.

Advantageously still, the set of data links 50comporte at least one particular connection point, called brewing point55. This at least one patching point 55 is provided for receiving a patching box 64. The set of data links 50 comprises data links between the patch point 55 and different connection points 54. The patching bay connects between they are said data connections by means of garters.

Each of the electrical equipment of the set of electrical equipment is connected to a pair of connection points via a local power supply link 42 and / or via a local data link43, as shown in FIG. 20. The aircraft 1 comprises an assembly of electrical equipment 40a ... 40j in the portion of the fuselage Freprésentée in the figure. These electrical equipments each require a power supply to operate, except for the 40g equipment that is self-powered. Electrical equipment, except 40d equipment, also each requires a data link. Each electrical equipment is connected to a single pair of connection points, using said local links 42 and / or 43, preferably via a derivation box 70a ... 70f. In the fuselage portion shown in the figure, the part 160 of the first sub-array is equipped with 3 junction boxes 70a, 70b, 70c and the portion 260 of the second sub-array is equipped with 3 junction boxes 70d, 70e, 70f. The electrical equipment 40a is connected to the branch box 70a by a local power supply link 42 and a local data link 43. The electrical equipment 40b and 40c are connected to the branch box 70b by a local power supply connection 42 and by a local data link 43. The electrical equipment 40d is connected to the junction box 70b only by a local power supply 42. The electrical equipment 40 and 40f are connected to the junction box 70c by an electrical power connection 42 and a local data link 43. The electrical equipment 40g is connected to the junction box 70d only by a local data link 43. The electrical equipment 40h and 40i are connected to the junction box 70e by a power connection. electrically local 42 and by a local data link 43. Electrical equipment 40j is connected to the junction box 70f by a local power supply connection 42 and a local data link 43. In a particular embodiment, the junction boxes 70a, 70b, 70c on the one hand and 70d, 70e, 70f on the other hand are installed every 4 or 5 pairs of connection points, respectively on the part 160 of the first subnet and on the part 260 of the second subnet. When the pairs of connection points are spaced for example by 50 cm, two consecutive diverter boxes are then spaced apart by about 2 meters.

In an embodiment shown in FIG. 18, a derivation box 70 comprises a power supply connector 724, a data link connector 754 and a set of slots E1, E2,... E6, each designed to receive a module interface. The power supply connector 724 is provided to cooperate 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 co-operating with the connection point 54 of the set of data links belonging to the pair of connection points to which the junction box is connected. This data link connector corresponds, for example, to at least one multi-fiber optical connector when the data links of the distribution network 600 correspond to optical fibers. The junction box 70 also comprises a set of electrical connections 72 extending between the power supply connector 724 and the different locations E1, E2,... E6 provided for receiving the interface modules, as well as a set of data links. 75 extending between the data link connector 754 and the different locations for receiving the interface modules.

In a variant shown in FIG. 19, the data links of the distribution network 600 correspond to optical fibers and the junction box 70 furthermore comprises a data link converter 78. This converter is designed to convert optical fiber communications into wired communications. and reciprocally. The plurality of data links 75 then comprise optical fiber data links 75a between the data link connector 754 and the data link converter 78, as well as data links 75b using electrical signals between the link converter. 78 and the different locations E1, E2, ... E6 provided for receiving the interface modules. This variant has the advantage of providing fiber optic communications over the set of data links of the mixed power and data communication network 600. These communications are thus insensitive to electromagnetic disturbances. These fiber optic communications are transformed into wired communications in the derivation box 70, which allows a wired connection of the data links 75b with the interface modules that can be installed in the locations E1, E2,... E6. Such a wired connection is more reliable than an optical connection in that the interface modules are likely to be replaced or moved. Indeed, such a wired connection is less sensitive to dust and vibrations than an optical connection.

In an exemplary embodiment, the connectors 724 and 754 are arranged on a rear face of the junction box 70. The electrical links 72 and the data links 75 are made by means of a backplane card of the junction box. These links arrive on the backplane boards of the backplane, arranged next locations E1, E2, ... E6 so that the interfaces modulesusceptible to be installed in said locations can be plugged on these connectors.

In a first particular embodiment shown in FIG. 21a, electrical equipments 40k... 40q are connected to electrical interface modules Pa, Pb via local power supply links 42k ... 42q and / or to modules data link interface Da, Db by local data links 43k ... 43q. In the example shown in the figure, the electrical interface modules Pa, Pbs are respectively installed in the locations E2, E6 of the derivation box 70 and the data link interface modules Da, Db are respectively installed in the slots E3, E5 of the derivation box 70. In this first embodiment, an electrical equipment which requires a power supply and a data link is connected to an electrical interface module by a local power supply link and to a link interface module. data by a local data link. For example, the electrical equipment 40k is connected to the electrical interface module Pa by a local power supply link 42k and the data link interface module Da by a local data link 43k. Advantageously, the local power supply links 42k ... 42q and the local data links 43k ... 43q are terminated by connectors capable of cooperating with connectors of the interface modules. Still advantageously, the rear face of the junction box 70cases supports provided for holding in position the connectors of the local power supply links and local data links, such that these connectors are connected to the corresponding connectors of the interface modules when the interface modules are installed in their respective locations of the derivation box. This advantageously makes it possible to remove and set up the interface modules in the locations E1, E2,... E6 of the derivation box without having to manipulate the connectors of the different data links. This also makes it possible to avoid connection errors of said links.

In an example shown in FIG. 21b, the junction box comprises a backplane board 73. The connectors 724 and 754 are integral with the backplane board. These connectors are arranged so that when the junction box is installed on a couple of connection joints, as shown in the figure, the power supply connector 724 is connected to the connection point of the busbar 20 and the data link connector 754 can receive a connector of a 54x end of data links from the connection point of the set of data links 50. In the figure, the interface module Da is shown inserted into a location of the junction box 70. The interface is connected to the backplane board 73 by means of a power supply connector 72i and a data link connector 75i. The arrow F represents a direction of extraction (towards the top of the figure) and insertion (downwards in the figure) of the interface module in the junction box 70. The local data links 43k and 43Ito the electrical equipment 40k and 40I are terminated by respective loops Ck and Cl connected to the interface module. Advantageously, as indicated above, the rear face of the derivation box 70 (shown below in the figure) comprises nonreprésentés supports provided to maintain in position the connectors Ck and Cl. Although this example is described for the interface module Da it is not limited to this interface module and can be applied to all the interface modules of the junction box.

In particular, each electrical interface module is selected from the following set: an electrical connection module, making it possible to establish an electrical connection between conductors of the busbar, via the electrical connections 72 of the junction box, and the connectors for local power connections to electrical equipment; - An electrical switching module for controlling the electrical power supply of an electrical equipment from a system. This electrical switch module comprises a switchplaced in series on an electrical connection between the conductors of the clearance set (via the electrical connections 72 of the junction box) and a connector provided for a local power supply connection to the electrical equipment. The switching module is connected to the system via one of the data links 75. According to commands received from the remote system, the switching module controls the opening or closing of the switch so as to control the electrical supply of the equipment electric; an electric voltage conversion module which comprises a converter powered from the electrical voltages present on the conductors of the busbar, via the electrical connections 72 of the derivation box. This converter corresponds for example to a transformer, a DC-DC voltage converter, a transformer-rectifier assembly, etc. At least one output of the converter is connected to a connector provided for a local power supply connection to an electrical equipment; and - an electrical protection module. This electrical protection module has a circuit breaker placed in series on an electrical connection between the conductors of the busbar (via the electrical connections 72 of the bypass box) and a connector provided for a local power supply connection to an electrical equipment.

More particularly, each data link interface module is chosen from the following set: a data link connection module, making it possible to establish at least one connection between a data link of the set of data links 50 associated with the busbar 20, via one of the links 75 of the junction box, and a connector provided for a local data link to an electrical equipment; a data link conversion module. This module comprises a converter connected to a data link of the set of data links 50 associated with the busbar 20, via one of the links 75 of the shunt box. In addition, this converter is connected to a connector for a local data link to an electrical equipment. For example, this converter converts an optical data link on the set of data links to a wire data link on the local data link. In another example, the converter converts an Ethernet data link on the set of data links to a USB data link on the local data link; - a wireless data link module. This module comprises a wireless communication transceiver, connected to a data link of the set of data links 50 associated with the busbar 20, on one of the links 75 of the junction box. The local data links between this interface module and electrical equipment are then wireless type, for example WiFi type; and a data acquisition and concentration module. The electrical equipment connected to this module by local data links are for example sensors. The module comprises an electronic circuit connected to a data link of the set of data links 50 associated with the busbar 20, via one of the links 75 of the junction box. This electronic circuitry is provided for acquiring data provided by the sensors, for concentrating data from different sensors, and for transmitting this data over said data link of the set of data links.

In particular, the junction box 70 may comprise a mixed interface module providing an electrical interface module function, as mentioned above, and a data link interface module function, as mentioned above. Under certain circumstances, this mixed interface module may respond to congestion constraints of the junction box locations 70.

In a second particular embodiment shown in FIG. 22, electrical equipments 40r, 40s are each connected to a respective connector 79r, 79s of the junction box 70, by respective local links 423r, 423s. These local links are of the type of electric power supply and data link. The connector 79r and the connector 79s of the junction box are each connected to an electrical interface module P and to a data link interface module D by links internal to the junction box. Thus, the connector 79r is traced to the electrical interface module P by an electrical connection 412r and the data link interface module D by a data link 413r. The connector 79s is connected to the electrical interface module P by an electrical connection. 412s and the data link interface module D by a data link 413s. Preferably, the pin-out of the different connectors 79r, 79s of the junction box is similar for all of said connectors. This makes it possible to use identical local links between the different electrical equipment and the connectors of the junction boxes to which these electrical equipments are connected. This results in a simplification of electrical equipment connections by means of said mixed local connections. Although this second particular embodiment is described with two electrical equipment and two interface modules, it is not limited to these numbers of electrical equipment and interface modules. Advantageously, as for the local connections of the electrical equipment of the In a first particular embodiment, the internal links 412r, 412s, 413r, 413s are terminated by connectors capable of cooperating with connectors of the interface modules P and D. The front facet of the junction box 70 comprises supports intended to hold in position the connectors of said internal links, such that these connectors are connected to the corresponding connectors of the interface modules when the interface modules are installed in their respective locations of the junction box. This advantageously removes and set up the interface modules in the locations E1, E2,... E6 of the junction box without having to manipulate the connectors of the various internal links. This also makes it possible to avoid connection errors of said links.

The various embodiments, examples, variants and alternatives described in connection with the various aspects of the invention can be combined with each other without departing from the scope of the invention. For example, without limitation, the electrical power distribution network 200 of an aircraft according to the first aspect of the invention can be achieved by assembling modular elements 60 complying with the second aspect of the invention. In the same way, the mixed power distribution and data communication network 600conforms with the third aspect of the invention can be realized by assembling modular elements according to the second aspect of the invention. For example, the branch boxes 68 described in connection with the second aspect of the invention may be similar to the branch boxes 70 described in more detail in connection with the third aspect of the invention.

Claims (7)

1- modular element (60) for a mixed power distribution network and data communication (600) of an aircraft, characterized in that it comprises: - a section of a power distribution busbar (20t), extending along a length (L) of the modular element; and a set of data links (50t), this set of data links extending along said length of the modular element, substantially parallel to the busbar section (20t), and in that: - the section busbar arrangement comprises connection points (24) at different locations distributed along its length; the set of data links comprises connection points (54) at different locations distributed along its length and each located close to a connection point (24) of the busbar section; - The set of data links (50t) comprises a connection point, said brewing point (55, 55a, 55b), provided to receive a drive bay (64); the set of data links (50t) comprises at least one data link (56) between, on the one hand, each of the connection points (54) distributed along its length and, on the other hand, the mixing point (55, 55a, 55 (b); - the busbar section (20t) and the set of data links (50t) each comprise a first interconnection point (27a, 57a) provided for carrying the busbar section and the set of data links respectively. a busbar section and a set of data links of a first other modular element disposed longitudinally in series with the modular element at a first longitudinal end (Ext1) of the modular element; and - the busbar section and the set of data links each have a second interconnection point (27b, 57b) for connecting the busbar section and the set of data links respectively to a section of the busbar. and a plurality of data links of a second other modular element disposed longitudinally in series with the modular element, at a second longitudinal end (Ext2) of the modular element opposite the first longitudinal end (Ext1). 2- modular element according to claim 1, characterized in that the data links (56, 58) correspond to optical fibers. 3- modular element according to one of claims 1 or 2, characterized in that the mixing point (55, 55a, 55b) comprises a subset of data links terminated by at least one connector, saidconnector brewing, provided to be integrated into the patch bay (64). 4- modular element according to claim 3, characterized in that the stirring point further comprises at least one fastener provided forpermettre fixing the mixing bay on the modular element. 5- modular element according to one of claims 3 or 4, characterized in that: - the mixing point (55a) on the one hand and the first interconnection point (57a) of the set of data links d on the other hand are located close to the first longitudinal end (Ext1) of the modular element; the first interconnection point (57a) of the set of data links comprises a subset of data links (58) terminated by at least one connector, said first interconnection connector; and - the arrangement of the mixing point (55a) and the first interconnection point (57a) is provided to allow the integration of the mating connector and the first interconnection connector into the mating bay (64) so as to allow connecting the set of data links (50t) to the set of data links of the first other module element in the patch bay. 6- modular element according to any one of the preceding claims, characterized in that: - the connection points (24) distributed along the busbar section (20t) and the connection points (54) distributed along the set of data links (50t), each arranged near a connection point (24) of the busbar section, form pairs of connection points distributed along the modular element; and - each pair of connection points is provided to receive a mixed electrical power distribution and data communication terminal box (68) configured to allow the connection of one or more local electrical power distribution and / or distribution links. data to one or more electrical equipment (40a ... 40j) of the aircraft. 7- modular element according to any of the preceding claims, characterized in that the busbar section (20t) comprises at least a flexible portion provided to allow dédeformation of the modular element in response to unfuselage deformations (F ) an aircraft (1) when the modular element is installed in said fuselage of an aircraft. 8- Aircraft (1), comprising a fuselage (F) and a set of electrical equipment (40a ... 40j) distributed in the fuselage, characterized in that: - the aircraft comprises a mixed network of electrical power distribution and communication data set (600) comprising a set of modular elements (60) according to any one of the preceding claims; and each of the electrical equipment (40a ... 40j) of the electrical equipment assembly is connected to a connection point (24) of the busbar section (20t) of a modular element via a local power supply connection. (42) and / or at a connection point (54) of the set of data links (50t) of said modular element by a local data link (43). 9- Aircraft according to claim 8, characterized in that: - modular elements (60a ... 60h) of a first subset of the set of modular elements are assembled together so as to form a first sub- mixed power distribution and data communication network (160, 160a) extending, at least in part, longitudinally in the fuselage (F) of the aircraft; modular elements (60i ... 60q) of a second subset of the set of modular elements are assembled together so as to form a second mixed power distribution and data communication subnetwork (260, 260a) extending, at least in part, longitudinally in the fuselage of the aircraft; and the first subnetwork and the second subnetwork borrow segregated paths in the fuselage. 10- Aircraft according to one of claims 8 or 9, characterized in that two consecutive modular elements (60i, 601 + 1) are interconnectedelectrically by means of: - at least one flexible connection; or - at least one connection element configured to slide on the busbar section of at least one of the two modular elements. 11- Aircraft according to any one of claims 8 to 10 combined with claim 5, characterized in that the drive bay (64) of a modular element (60i + 1) receives: - an interconnect connector (57b) of the first other modular element (60i); and a set of links between the first interconnect connector (57a) of the modular element (60i + 1) and the interconnect connector (57b) of the first other modular element (60i).