EP3808012A1

EP3808012A1 - Device and method for data communication in an aircraft subassembly

Info

Publication number: EP3808012A1
Application number: EP19737836.7A
Authority: EP
Inventors: Patrick Gonidec; Jean-Paul Rami
Original assignee: Safran Nacelles SAS
Current assignee: Safran Nacelles SAS
Priority date: 2018-06-18
Filing date: 2019-06-04
Publication date: 2021-04-21
Also published as: FR3082687B1; WO2019243694A1; US20210285382A1; US11773788B2; FR3082687A1

Abstract

The invention relates to the communication between electronic systems (10, 11) in an aircraft subsassembly, such as a propulsive assembly (1). According to the invention, said communication is at least partially performed by light signals transmitted through at least one internal space (1A) of the subassembly, said internal space defining an optical channel. To this end, at least one of these systems (10) comprises an emitter (20) arranged so as to emit a light signal and to modulate it according to data to be transmitted generated by this system (10), and at least one other of these systems (11) comprises at least one receiver (31) for receiving said light signal.

Description

Device and method for data communication in an aircraft sub-assembly

The present invention relates to communication between electronic systems in an aircraft sub-assembly, in particular in an aircraft propulsion assembly.

An aircraft propulsion unit communicates a large number of low-level data and signals either within the propulsion assemblies or between the propulsion assemblies and the aircraft.

The communication of such data is carried out by electrical or optical cables which pose numerous integration problems.

Optical cables are for example known from document US 5,960,626 A.

Typically, the electrical cables are shielded, which increases their bulk and the weight of the aircraft. In addition, the stiffness of the shielded cables leads to integration difficulties in the propulsion units. This results in an increase in the cost of the propulsion units and, in certain cases, a modification of the shape of the aerodynamic lines.

The communication of such data can also be carried out by carrier currents, that is to say by transmission of low level signals in electric power cables.

The implementation of carrier currents is however delicate since high power signals are liable to pollute low level signals and the protection of these low level signals against external electromagnetic effects requires shields of power cables thus increasing their volume. .

An object of the present invention is to overcome the aforementioned drawbacks by proposing an aircraft subassembly facilitating the integration of communication systems, reducing manufacturing or assembly costs, and / or limiting the risks of signal pollution low levels by high frequency signals.

To this end, the invention relates to an aircraft sub-assembly such as a propulsion unit, comprising data processing systems. In a nonlimiting manner, these data processing systems can be chosen from: a full authority digital regulation calculator, called "FADEC"; a thrust reverser control system, called “ETRAS”, for controlling the opening and closing of a thrust reverser of the propulsion unit; one or more systems for measuring and / or analyzing physical parameters such as gas acceleration, pressure or flow; one or more position sensors; etc.

This aircraft sub-assembly comprises at least one interior volume defining an optical channel.

It should be noted that this optical channel is not necessarily intended to provide a clear line between a transmitter and a receiver of an optical signal. Indeed, light can be transmitted in a very congested volume by multiple reflections and diffusions on surfaces present in the volume defining the optical channel.

In this optical channel or interior volume, communications by wireless light signals are transmitted in free space in this interior volume. In other words, the light signals propagate in the interior volume without being guided.

Advantageously, communications by wireless light signals can be implemented by multiple reflections and diffusions on surfaces present in this volume.

According to the invention, at least one of the data processing systems comprises at least one transmitter capable of transmitting a light signal in said at least one optical channel. In the present document, this emitted light signal is also called “emission signal”. Said at least one transmitter is arranged to modulate the light signal as a function of data to be transmitted generated by this data processing system. In addition, at least one other of the data processing systems comprises at least one receiver capable of receiving the light signal emitted by said at least one transmitter.

Such an aircraft subset makes it possible to communicate data by reducing the number of electrical or optical cables.

This limits or avoids the drawbacks associated with communication by electrical or optical cables.

In particular, the inventors believe that this invention can make it possible to reduce the overall mass of a propulsion unit up to 90 kg.

Such wireless communication also ensures the independence of low-level signals from high-power signals.

In addition, in the event of removal of the engine, the invention makes it possible to avoid the disconnection of cables at the level of the pylon. The invention also makes it possible to communicate members mounted on supports movable relative to one another, such as for example a sliding cover of thrust reverser and the fixed structure which supports it.

In one embodiment, the at least one transmitter can include a light emitting diode.

In one embodiment, said at least one other of the data processing systems can be arranged to transmit a return signal in the at least one optical channel. Preferably, the return signal can be in a bandwidth different from that of the transmission signal.

Such bandwidth segregation can for example be effected by a difference in modulation of the light signals by the use of signals of different colors filtered in color on reception.

In one embodiment, the aircraft subassembly may include a wall defining two interior volumes. These two volumes respectively form a first and a second optical channel. According to this embodiment, the sub-assembly comprises at least one transmission module capable of transmitting in the second optical channel a light signal emitted in the first optical channel.

Such a transmission module makes it possible to transmit a light signal through a substantially opaque wall or partition.

According to a first variant, the transmission module can comprise a receiver arranged to receive the light signal emitted in the first optical channel, a transmitter arranged to emit the light signal in the second optical channel, and an electric cable passing through the wall so as to transmit the light signal from the receiver of this transmission module to the transmitter of this transmission module in the form of an electrical signal. These two elements can be merged into a single transceiver, part of which crosses the wall.

According to a second variant, the wall may include a translucent part forming the transmission module.

These two variants can be combined: for example, a first wall can comprise a transmission module according to the first variant and a second wall can comprise a transmission module according to the second variant.

In one embodiment, the aircraft subassembly may comprise a pylon having an interior volume constituting an optical channel. In another embodiment, the aircraft subassembly may comprise a portable digital tablet, this tablet constituting a data processing system comprising at least one of said at least one transmitter and / or comprising at least one said at least one receiver.

Such a tablet can allow a maintenance agent to dialogue with data processing systems of the propulsion unit or of the aircraft when at least one of the pod covers is open: the volume included under the open cover constitutes an optical channel capable of transmitting maintenance data by light signals under standard lighting conditions.

According to another aspect, the invention also relates to a data communication method implementing a subset of aircraft as defined above.

Other characteristics and advantages of the invention will appear on reading the non-limiting description which follows and the appended figures, in which:

Figures 1 to 7 are schematic views in partial longitudinal section of an aircraft subassembly according to the invention;

Figure 8 is a schematic cross-sectional view of an aircraft sub-assembly according to the invention in the maintenance configuration.

Identical or similar elements are identified by identical reference signs in all of the figures.

An aircraft sub-assembly according to the invention is shown in FIG. 1. This sub-assembly comprises a propulsion unit 1 and a pylon 2 connected to a wing 3 of the aircraft.

In the following description, the propulsion unit 1 taken as an example consists of a nacelle and a turbofan engine, and includes a thrust reverser. Of course, the present invention can be implemented in any type of aircraft and any type of corresponding propulsion unit.

The subset of FIG. 1 comprises multiple data processing systems, in particular a full control digital control computer 10 (FADEC), a thrust reverser control system 11 (ETRAS) arranged to control the opening and closing the thrust reverser, systems for measuring and analyzing physical parameters such as the acceleration, pressure or flow of a gas, and position sensors. In general, the invention can be implemented in a propulsion unit provided with all the data processing systems necessary for its operation.

Referring to Figure 1, the sub-assembly which is illustrated therein comprises a plurality of interior volumes IA, IB, 2A ... These volumes are delimited by walls, partitions or components of this sub-assembly. For example, the volume IA is delimited by an internal wall 106 and an external wall 108 of a middle section of the nacelle of the propulsion unit 1, by a wall 100 separating the middle section of an upstream section of the nacelle, and by a wall 102 separating the middle section from a rear section of the nacelle. For another example, the volume 2A is a volume delimited by the walls of the pylon 2.

These interior volumes are volumes already existing in the propulsion systems of the prior art. These volumes are generally narrow and cluttered with elements or bodies constituting obstacles. These volumes are relatively protected from external light without necessarily being optically closed. The invention therefore takes advantage of such confined volumes to communicate data using light signals emitted in these volumes which thus define optical channels, by direct lines or multiple diffusions or reflections on the surfaces present in these volumes.

According to the invention, at least one of the data processing systems, for example the FADEC 10, comprises at least one transmitter 20 capable of transmitting a light signal in the optical channel IA. This transmitter 20 is arranged to modulate the light signal as a function of the data to be transmitted generated by this data processing system 10. In addition, at least one other of the data processing systems, for example ETRAS 11, comprises at least a receiver 31 able to receive the light signal emitted by the transmitter 20.

To communicate data in the opposite direction, the ETRAS 11 - or more generally said at least one other of the data processing systems - can be arranged to send a return signal in the optical channel IA, preferably in a different bandwidth of the bandwidth of the transmission signal. To do this, the ETRAS 11 - or this other data processing system - may include a return transmitter 41 capable of emitting a light signal in the optical channel IA and arranged to modulate this light signal as a function of the data to be transmitted generated by this other data processing system 11.

In this example, the FADEC 10 comprises a return receiver 50 capable of receiving the return light signal emitted by the return transmitter 41. FIG. 2 illustrates such a communication between FADEC 10 and ETRAS 11: the FADEC 10 transmits an order to ETRAS 11 by emission of a light signal in the optical channel IA via the transmitter 20. The light signal emitted by the transmitter 20 is represented by arrows in solid line: this order signal transmitted by the transmitter 20 is in this example reflected on the wall 102 before arriving at the receiver 31, due to the presence of an obstacle 91. Conversely, ETRAS 11 transmits a return signal to FADEC 10 by sending a light signal in the optical channel IA via the return transmitter 41. The light signal transmitted by the return transmitter 41 is represented by an arrow in line interrupted. In this example, the return signal emitted by the return transmitter 41 arrives directly at the return receiver 50, possibly with multi-reflections between the engine and the covers taking into account the geometry of the volume (between cover and engine for example).

The above applies of course to communication between any pair of data processing systems separated by an optical channel defined by an interior volume of an aircraft sub-assembly.

For example, with reference to the embodiment which has just been described, the data processing system 11 may consist not of an ETRAS but of a system for controlling the variation in section of a secondary nozzle of the propulsion unit (not shown).

FIG. 3 illustrates a communication between the FADEC 10 and an actuator 12 provided for modifying the geometry of a high pressure turbine (not shown) of the propulsion unit 1. Such an actuator 12 is commonly designated by the acronym "VSV" ("Variable Stator Valve" in English).

In the example of FIG. 3, the FADEC 10 transmits an order to the actuator 12 by emission of a light signal in the optical channel IA via the transmitter 20. The light signal emitted by the transmitter 20 is represented by an arrow in solid line and arrives in this example directly at a receiver 36 mounted on the wall 102 so that the receiver 36 opens into the optical channel IA. A transmitter 26 is mounted on the wall 102 facing the receiver 36 so that this transmitter 26 opens into a volume IB defining an optical channel of the rear section of the nacelle. The receiver 36 and the transmitter 26 can be connected by an electric cable passing through the wall 102 so as to transmit the light signal from the receiver 36 to the transmitter 26 in the form of an electric signal. The light signal is then re-emitted by the transmitter 26 in the optical channel IB to arrive at a receiver 32 of the actuator 12 (arrows in solid line). In this example, the command signal emitted by the transmitter 26 is reflected on an obstacle 92 before arriving at the receiver 32 of the actuator 12. In the example of FIG. 3, the actuator 12 transmits a return signal to the FADEC 10 by emission of a light signal in the optical channel IB via a return transmitter 42. The light signal emitted by this return transmitter 42 is shown by dashed arrows. In this example, the return signal emitted by the return transmitter 42 arrives at a return receiver 56 after reflection on the obstacle 92. The return receiver 56 is mounted on the wall 102 so that this return receiver 56 opens into the channel IB optics. A return transmitter 46 is mounted on the wall 102 facing the return receiver 56 so that this return transmitter 46 opens into the optical channel IA. The return receiver 56 and the return transmitter 46 can be connected by an electric cable passing through the wall 102 so as to transmit the light signal from the return receiver 56 to the return transmitter 46 in the form of an electric signal.

The invention thus makes it possible to communicate a signal through a wall separating two interior volumes respectively forming a first and a second optical channel.

In the example described above, the transmitter 26 and the receiver 36 constitute a transmission module: the receiver 36 is arranged to receive the light signal transmitted in the optical channel IA, the transmitter 26 is arranged to transmit the signal bright in the optical channel IB. Thus, this transmission module is able to transmit in the optical channel IB a light signal emitted in the optical channel IA.

The return transmitter 46 and the return receiver 56 constitute another similar transmission module.

Alternatively, a part of the wall delimiting two optical channels can be translucent so as to constitute a transmission module requiring no transmitter or receiver.

Other examples of data transmission between data processing systems are represented in FIGS. 4 to 7: in the same way as in the examples of FIGS. 2 and 3, the order signals are represented by solid lines and the signals back not broken lines.

FIG. 4 illustrates a data transmission between, on the one hand, a system 13 for measuring a physical parameter such as the flow of air entering the nacelle and, on the other hand, the FADEC 10.

FIG. 5 illustrates a data transmission between a computer (not shown) located in the aircraft and a system 14, for example a locking system ("Tertiary Lock System") offset towards the rear of the nacelle. FIG. 6 illustrates a data transmission between a sensor 15 and TETRAS 11. This sensor 15 can be powered or autonomous.

FIG. 7 illustrates a mutual data transmission between a computer (not shown) located on the aircraft and the FADEC 10.

In the example of FIG. 8, a portable digital tablet 19 constitutes a data processing system. This tablet 19 includes a transmitter 29 and a receiver 39.

Of course, the invention is not limited to the examples which have just been described and numerous modifications can be made to these examples without departing from the scope of the invention. For example, the modulation of the light signal can comprise a frequency and / or amplitude modulation of the carrier wave, and / or a modification of the color of the light signal. For example again, a transmitter and a receiver of a data processing system can be coupled in a single member.

In the case where a receiver and a transmitter can see each other in a straight line, it will be advantageous to reduce the opening angle of the emitted light or to focus it towards the receiver, for example by emitting substantially parallel rays aimed at the receiver . This is particularly advantageous in a fairly heavily polluted light environment, for example when a cover is open or in the vicinity of an orifice not protected from outside light.

Claims

1. Aircraft sub-assembly comprising data processing systems, this aircraft sub-assembly comprising at least one interior volume (IA) defining an optical channel, at least one of the data processing systems (10 ) comprising at least one transmitter (20) capable of transmitting a light signal in said at least one optical channel (IA), said at least one transmitter (20) being arranged to modulate the light signal as a function of data to be transmitted generated by this system processing system (10), and in that at least one other of the data processing systems (11) comprises at least one receiver (31) capable of receiving the light signal emitted by said at least one transmitter (20) , characterized in that the interior volume allows communication by wireless light signals emitted in this volume by direct lines or multiple diffusions or reflections on the surfaces present in this volume.

2. Aircraft sub-assembly, characterized in that it is a propulsion unit

(1).

3. Aircraft sub-assembly, characterized in that it comprises data processing systems comprising

- a full-authority digital control computer (10), and / or

- a thrust reverser control system (11) arranged to control the opening and closing of a thrust reverser of the propulsion unit (1), and / or

- one or more systems for measuring and / or analyzing physical parameters such as the acceleration, pressure or flow of a gas, and / or

- one or more position sensors.

4. Aircraft subassembly according to any one of the preceding claims, in which the at least one transmitter (20) comprises a light-emitting diode.

5. Aircraft subassembly according to any one of the preceding claims, in which said at least one other of the data processing systems (11) is arranged to transmit a return signal in the at least one optical channel ( IA), the return signal preferably being in a bandwidth different from that of the transmission signal.

6. aircraft subassembly according to any one of the preceding claims, comprising a wall (102) delimiting two interior volumes (IA, IB), these two volumes (IA, IB) respectively forming a first and a second optical channel , and comprising at least one transmission module capable of transmitting in the second optical channel (IB) a light signal transmitted in the first optical channel (IA).

7. The aircraft subassembly according to claim 6, in which the transmission module comprises a receiver (36) arranged to receive the light signal transmitted in the first optical channel (IA), a transmitter (26) arranged to transmit the light signal in the second optical channel (IB), and an electric cable passing through the wall (102) so as to transmit the light signal from the receiver (36) of this transmission module to the transmitter (26) of this transmission module in the form of an electrical signal.

8. The aircraft subassembly according to claim 6 or 7, wherein the wall comprises a translucent part forming a transmission module.

9. Aircraft subassembly according to any one of claims 1 to 8, comprising a pylon (2) having an interior volume (2A) constituting an optical channel.

10. Aircraft subassembly according to any one of claims 1 to 9, comprising a portable digital tablet (19; Fig.8), this tablet (19) constituting a data processing system comprising at least one said at least one transmitter (29) and / or comprising at least one of said at least one receiver (39).

11. A method of data communication using a subset of aircraft according to any one of claims 1 to 10.