FR3052903A1 - METHOD FOR INSTALLING A DATA TRANSFER SYSTEM BETWEEN AN AIRCRAFT AND THE GROUND - Google Patents

Abstract

The invention relates to a method for installing a transfer system (150) in an aircraft (100) comprising an avionics bay (104) with a wireless transmission system (112), two engines (108a-b), each equipped with a computer (110a-b), the installation method comprising: for each motor (108a-b), - a step of selecting a two-wire electrical cable (114a-b) present in the aircraft (100), extending between said engine (108a-b) and the avionics bay (104) and not connected to an electrical circuit in normal operation of the aircraft (100), - a step of installing a first converter (116a-b) in the vicinity of said engine (108a-b), and a second converter (118a-b) in the avionics bay (104), - a step of connecting the first converter (116a-b) between the computer (110a-b) of said motor (108a-b) and the electric cable (114a-b), and - a step of connecting the second converter (118a-b) between said electrical cable (11a-b) 4a-b) and the wireless transmission system (112). Such a method of installing a transfer system (150) makes it possible to simply create a network for transferring data from the motors to the ground.

Description

Method for installing a data transfer system between an aircraft and the ground

TECHNICAL AREA

The present invention relates to a method of installing a data transfer system between an aircraft and the ground and an aircraft equipped with such a transfer system with the ground.

STATE OF THE PRIOR ART

In the context of the maintenance of an aircraft, it is necessary that the data relating to each engine of the aircraft is retrieved by a system on the ground. These data, which are then processed, help improve maintenance and reduce costs.

Each engine has a control system that interfaces between cockpit controls and a motor computer. The control system, sometimes called FADEC ("Full Authority Digital Engine Control" in Anglo-Saxon terminology), ensures, among other things, the transmission of engine parameters to the cockpit.

Each aircraft also typically includes a tool that collects data from each engine that was collected during a flight. Such a tool is called EHM ("Engine Health Monitoring" in Anglo-Saxon terminology).

For new aircraft, the data transmitted as part of the EHM tool is transmitted at a rate of the order of lOMbit / s, through an Ethernet network deployed in the aircraft, such as the AFDX network ("Avionics Full Duplex"). In Anglo-Saxon terminology).

This data is then transmitted, through such a network, from the engine computer to a wireless communication system of the aircraft and the communication system can then communicate with a ground system that can process the data collected to establish maintenance recommendations.

For older aircraft, data is transmitted via a system called Aircraft Condition Monitoring Systems (ACMS), but the parameters that can be recorded are limited.

When an older aircraft is equipped with a recent engine, it is difficult to transmit all desired data to the wireless transmission system of the aircraft

Indeed, the network of the aircraft is limited in bandwidth and does not allow to transmit a large amount of data. Conventionally, for a network based on the ARESfC 429 standard, the bandwidth is 10OKbit / s.

It is also difficult to add a new cable between the engine and the cockpit.

It is also difficult to add a wireless transmission system to the engine because of integration and cost issues.

SUMMARY OF THE INVENTION

An object of the present invention is to propose a method of installing a data transfer system between an aircraft and the ground which makes it possible to transfer a large number of data from the engine, without implying significant modifications of the data. For this purpose, a method of installing a transfer system in an aircraft comprising an avionics bay with a wireless transmission system, two wings, and for each wing, an engine equipped with a transmission system, is proposed for this purpose. a computer and attached to said wing, the installation method comprising; for each engine, - a step of selecting a two-wire electrical cable present in the aircraft, extending between said engine and the avionics bay and not connected to an electrical circuit in usual operation of the aircraft, - a step of installing a first converter in the vicinity of said engine, - a step of installing a second converter in the avionics bay, - a step of connecting the first converter between the computer of said engine and the electric cable, and - A step of connecting the second converter between said power cable and the wireless transmission system.

Thus, such a method of installing a system for transferring an aircraft to the ground allows simple high-bandwidth data transmission, without changing the architecture of the aircraft The invention also proposes a aircraft comprising: - an avionics bay, - two wings, - for each wing, a motor attached to said wing, and - a transfer system which comprises: - a wireless transmission system installed in the avionics bay, and for each engine a computer mounted near said engine and collecting operating data of said engine, a two-wire electrical cable present in the aircraft, extending between said motor and the wireless transmission system and not connected to an electrical circuit in usual operation of the aircraft, - a first converter connected between the computer and the electric cable, and - a second converter connected between the electrical cable and the sy wireless transmission system.

Advantageously, the first converter is a converter that converts a digital signal from a 4-wire Ethernet cable to a 2-wire cable, and the second converter is a converter that converts a digital signal from a 2-wire cable to a cable. 4-wire Ethernet.

Advantageously, the electric cable is a cable connected to a fuel flow meter at the engine.

BRIEF DESCRIPTION OF THE DRAWINGS

The characteristics of the invention mentioned above, as well as others, will appear more clearly on reading the following description of an exemplary embodiment, said description being made with reference to FIG. unique which shows a top view of an aircraft according to the invention.

DETAILED DESCRIPTION OF EMBODIMENTS

Fig. unique shows an aircraft 100 which comprises a transfer system 150 and a fuselage 102 in front of which is arranged an avionics bay 104 located at the rear of the cockpit or under the cockpit and on both sides of which are attached wings 106a-b.

For each wing 106a-b, the aircraft 100 also has a motor 108a-b fixed under said wing 106a-b.

Each engine 108a-b is equipped with a llOa-b computer such as for example a computer of a FADEC system, EEC ("Electronic Engine Control"), or ECU ("Engine Control Unit"). The computer allows among other things to collect the operating data of the engine.

The transfer system 150 transfers the data from each engine 108a-b collected by the computer 1 10a-b to a wireless transmission system 112 of the aircraft 100 and located in the avionics bay 104.

The wireless transmission system 112 is a ground-to-ground transmission system that allows data to be transferred to a ground system 10 of the type having a compatible wireless receiver.

For each engine 108a-b, the aircraft 100 comprises a two-wire electrical cable 114a-b present in the aircraft 100 and extending between said engine 108a-b and the avionics bay 104, and more particularly the transmission system. wirelessly 112 when connected to it. This electric cable 114a-b is a cable which is put in place during the construction of the aircraft 100 but which is not used for the usual operation of the aircraft 100, that is to say it is not connected to an electrical circuit. For example, the electric cable 114a-b is used during the construction of the aircraft 100 or until delivery, but not after when the aircraft 100 is in normal operation. The usual operation is defined as the operation of the aircraft 100 after its delivery to a commercial airline operator.

For each electrical cable 114a-b, the transfer system 150 comprises a first converter 116a-b and a second converter 118a-b which are 2-wire Ethernet converters.

The first converter 116a-b is connected between an Ethernet port of the computer llOa-b and the electric cable 114a-b, and the second converter 118a-b is connected between the electric cable 114a-b and an Ethernet port of the control system. wireless transmission 112.

The first converter 116a-b is a converter that converts a digital signal from a 4-wire Ethernet cable to a 2-wire cable, and the second converter 118a-b is a converter that converts a digital signal from a 2-wire cable. wires to a 4-wire Ethernet cable.

Each converter 116a-b, 118a-b is for example a commercial converter such as the converter Devolo or C4Line.

Each first converter 116a-b is installed in the vicinity of the associated motor 108a-b and each second converter 118a-b is installed in the avionics rack 104.

The transfer system 150 thus comprises: - the wireless transmission system 112 of the avionics bay, - for each engine 108a-b, - the computer 110a-b mounted near the engine 108a-b and collecting the operating data of said motor 108a-b, the two-wire electrical cable 114a-b, the first converter 116a-b connected between the computer 110a-b and the electric cable 114a-b, and the second converter 118a-b connected between the electric cable 114a-b and the wireless transmission system 112.

The electric cable 114a-b and the converters 116a-b, 118a-b create an Ethernet network which makes it possible to transfer the data from the motor 108a-b to the wireless transmission system 112 with a sufficient bandwidth of at least lOMbit / s allowing to implement an EHM tool that can use a large amount of data without modifying the architecture of the aircraft 100.

Different Ethernet protocols can be used, such as the Asymmetric Digital Subscriber Line (ADSL), VDSL (Very-high-bit-rate Digital Subscriber Line), and PLC (Power Line Carrier) protocols.

The wireless transmission system 112 can use any appropriate protocol allowing a sufficient bandwidth such as 3G, 4G, WIFI.

Any electrical cable 114a-b as defined above may be suitable, but according to a particular embodiment, the electric cable 114a-b is the cable connected to the fuel flow meter at the engine 108a-b to transfer the flowmeter data. fuel to the aircraft instrumentation as a data logger of the avionics bay 104. These two wires are used to transfer data according to the ARINC429 protocol. The temporary measuring system of the fuel flow meter consists of a sensor measuring the fuel flow in the core zone of the engine 108a-b, this sensor is connected to a data acquisition box installed at the engine 108a-b, which itself transmits this data according to the ARINC429 protocol to a data logger in the avionics bay 104 using the two wires installed for this purpose. After this measurement, the cable 114a-b remains in place in the aircraft 100 but is electrically disconnected at each end of any electrical circuit.

This electric cable 114a-b is used to precisely measure the fuel consumption and thus confirm the engine performance just before the delivery of the aircraft 100, while subsequently, this electric cable 114a-b remains in the aircraft 100 without being used.

A method of installing such a transfer system 150 in the aircraft 100 includes; for each engine 108a-b, - a step of selecting a two-wire electrical cable 114a-b present in the aircraft (100), extending between said engine (108a-b) and the avionics bay (104) and not connected to an electrical circuit in usual operation of the aircraft 100, - a step of installing a first converter 116a-b in the vicinity of said engine 108a-b, - a step of installing a second converter 118a in the avionics bay 104, a step of connecting the first converter 116a-b between the computer 1 10a-b of said motor 108a-b and the electric cable 114a-b, and a connection step of the second converter 118a. b between said electric cable 114a-b and the wireless transmission system 112 of the aircraft 100.

Claims (4)

1) A method of installing a transfer system (150) in an aircraft (100) having an avionics bay (104) with a wireless transmission system (112), two wings (106a-b), and for each wing (106a-b), a motor (108a-b) equipped with a computer (1 10a-b) and attached to said wing (106a-b), the installation method comprising: for each engine (108a-b) b), - a step of selecting a two-wire electrical cable (114a-b) present in the aircraft (100), extending between said engine (108a-b) and the avionics bay (104) and not connected to an electrical circuit in normal operation of the aircraft (100), - a step of installing a first converter (116a-b) in the vicinity of said engine (108a-b), - an installation step of a second converter (118a-b) in the avionics bay (104), - a step of connecting the first converter (116a-b) between the computer (1 10a-b) of said engine (108a-b) and the cable electrical (114a-b), and - a step of connecting the second converter (118a-b) between said electrical cable (114a-b) and the wireless transmission system (112). 2) Aircraft (100) comprising: - an avionics bay (104), - two wings (106a-b), - for each wing (106a-b), a motor (108a-b) fixed to said wing (106a-b) ), and - a transfer system (150) which comprises: - a wireless transmission system (112) installed in the avionics bay (104), and for each engine (108a-b), - a computer (110a-b) ) mounted near said engine (108a-b) and collecting operating data of said engine (108a-b), - a two-wire electrical cable (114a-b) present in the aircraft (100), extending between said motor (108a-b) and the wireless transmission system (112) and not connected to an electrical circuit in usual operation of the aircraft (100), - a first converter (116a-b) connected between the computer (1) 10a-b) and the power cable (114a-b), and - a second converter (118a-b) connected between the power cable (114a-b) and the wireless transmission system (112). 3) Aircraft (100) according to claim 2, characterized in that the first converter (116a-b) is a converter which converts a digital signal from a 4-wire Ethernet cable to a 2-wire cable, and in that the second converter (118a-b) is a converter that converts a digital signal from a 2-wire cable to a 4-wire Ethernet cable. 4) Aircraft (100) according to one of claims 2 or 3, characterized in that the electric cable (114a-b) is a cable connected to a fuel flow meter at the engine (108a-b).