Aircraft parking guidance and information system

Abstract

The invention relates to a guidance and information system (1) for parking an aircraft, said system (1) comprising at least one thermal camera for measuring the infrared energy of the area of ​​the aircraft containing an auxiliary power unit when the aircraft is in a predetermined parking position, and configured to detect the operation or shutdown of the auxiliary power unit from infrared energy measurements taken by said thermal camera and to control the display of an alert information to the pilot on a display module (40) when the auxiliary power unit has been detected as operating. Figure 1

Description

Title of the invention: Guidance and information system for parking an aircraft Technical field

[0001] The present invention relates to the field of aeronautics and more particularly concerns a guidance and information system for parking an aircraft. Prior art

[0002] Nowadays, in airports, it is known to install a guidance and information system for the parking of an aircraft, known as VDGS (for Visual Docking Guidance System), on the parking points of the aircraft. Such a system makes it possible, during the approach of the aircraft during taxiing, to determine the positioning of the aircraft relative to a predetermined parking location in order to guide the pilot to park the aircraft on said location using information displayed on a dedicated electronic panel.

[0003] In a known solution, the system comprises a display panel installed opposite the aircraft parking point and one or two laser sensors for determining the positioning of the aircraft relative to the location as it approaches the parking point. Information on the positioning of the aircraft relative to the parking point, obtained from the laser measurements, is displayed on the panel to enable the pilot to adapt the trajectory of the aircraft so that it comes into precise position on the location.

[0004] In a known manner, the system may also comprise a standard Red Green Blue (RGB) type camera making it possible to identify the type of aircraft by recognizing certain distinctive elements such as its landing gear, the shape of the cockpit windshield, etc.

[0005] The system can be connected to ground equipment, for example of the ground power unit type (commonly called GPU for Ground Power Unit) or air conditioning unit (commonly called ACU for Air Conditioning Unit), in order to display their operating status.

[0006] Despite this, the pilot may be tempted to leave his engines running while parking, particularly the auxiliary power unit (commonly called APU for Auxiliary Power Unit). Thus, such operation leads to an increase in fuel consumption. For example, a standard auxiliary power unit consumes between 150 and 400 liters per hour of fuel compared to 15 to 150 kilowatts for a ground-based electrical power unit. Furthermore, such operation leads to an increase in emissions of polluting gases, particularly carbon dioxide, and / or toxic gases, particularly unburned hydrocarbons (HC) and acidic nitrogen oxide and nitrogen dioxide (NOx), which presents another major disadvantage. Finally, such operation generates a significant noise level, which presents another disadvantage.

[0007] There is therefore a need for a simple and effective solution to at least partially remedy these drawbacks. Statement of the invention

[0008] For this purpose, the invention firstly relates to a guidance and information system for parking an aircraft, said aircraft comprising at least one auxiliary power unit, said system comprising a detection device, a control module and a display module, said detection device being configured to transmit and receive signals in order to detect the aircraft, the control module being configured to determine the positioning of said aircraft relative to a predetermined parking location from the signals received by the detection device, to generate information relating to said positioning and to send the generated information to the display module, said display module being configured to receive and display the information relating to the positioning of the aircraft in order to guide the pilot to maneuver the aircraft to the predetermined parking location,said system being remarkable in that it further comprises a location module configured to receive waves from the area in which the auxiliary power unit is located (or carry out measurements in said area) when the aircraft is parked at the predetermined location, and in that the control module is configured to, from waves received (or measurements carried out), by said location module, determine the operating state or the shutdown state of the auxiliary power unit in the detected area and to control the display of alert information for the pilot on the display module when the auxiliary power unit has been detected in operating state.

[0009] Information relating to the operation of the auxiliary power unit can be displayed as soon as the operation of said auxiliary power unit is detected.

[0010] The system according to the invention makes it possible to inform the pilot of the aircraft that the auxiliary power unit is in operation during parking so that said pilot stops its operation, thus reducing fuel consumption, emissions of harmful compounds and the noise generated by the aircraft. The system according to the invention makes it possible in particular to reduce the carbon footprint of the aircraft. In addition, the information displayed is visible to both ground personnel and the pilot in order to improve efficiency and safety, including alerting ground personnel of excessive fuel consumption when a ground power unit and / or air conditioning unit are operating in parallel with the auxiliary power unit.

[0011] In one embodiment, the location module comprises at least one thermal camera configured to measure the infrared energy released by the aircraft in the area intended to comprise the auxiliary power unit of the parked aircraft in order to allow the control module to determine the operating state or the shutdown state of the auxiliary power unit according to the amplitude of the infrared waves received.

[0012] Preferably, the at least one thermal camera is located at the location of the display module which is particularly suitable for carrying out these detections.

[0013] According to one aspect of the invention, the at least one thermal camera is configured to be calibrated as a function of the outside temperature in order to avoid confusing the heat released by the auxiliary power unit and the heat reverberation on the ground. For example, the at least one thermal camera can compare the measured infrared image with that of the “theoretical” parked aircraft from a database of images taken in the real environment. The type of parked aircraft can advantageously be known to the guidance system, given its connection to the airport information system.

[0014] Alternatively or additionally, the location module comprises at least one microphone oriented towards the area intended to comprise the auxiliary power unit of the parked aircraft and configured to measure the sound waves emitted in said area to determine the operating state or the shutdown state of the auxiliary power unit according to the amplitude of the received sound waves. Such a microphone or plurality of microphones makes it possible to detect the high-frequency sound fingerprint of the auxiliary power unit. For example, the system can search a database for the sound spectrum of the auxiliary power unit of the parked aircraft and compare it to its measurement. The database can be refined by experimental on-site measurements which take the environment into account.

[0015] Preferably, the at least one microphone is located at the location of the display module which is particularly suitable for carrying out these detections.

[0016] In one embodiment, the system is configured to determine or detect the operation or shutdown of a ground power unit connected to the aircraft and / or an air conditioning unit connected to the aircraft and to control the display of the alert information only when the ground power unit and / or the air conditioning unit are in operation. Thus, the system according to the invention, when connected to the system airport information system, can display the operating status of fixed auxiliary equipment such as ground power unit and / or air conditioning unit also connected to the airport information system. The pilot can thus safely decide to shut down the aircraft's auxiliary power unit or keep it running in the event of a malfunction of the auxiliary equipment.

[0017] In one embodiment, the system is configured to generate an alert when an auxiliary power unit is detected while a ground power unit and / or an air conditioning unit are already in operation. Thus, when the pilot turns the auxiliary power unit back on in order to take off again, the ground power unit and / or the air conditioning unit can be stopped and disconnected, in particular by ground personnel. Using either the auxiliary power unit, or the ground power unit and / or the air conditioning unit allows in particular an accurate measurement of the actual carbon footprint of the aircraft, knowing on the one hand the carbon footprint of the ground power unit and / or the air conditioning unit and on the other hand the carbon footprint of the auxiliary power unit.

[0018] Advantageously, the system is configured to control, preferably automatically, the stopping of a ground power supply unit and / or an air conditioning unit in operation when the start-up of an auxiliary power unit has been detected or when an auxiliary power unit has been detected in operation in order to reduce in particular the carbon footprint of the aircraft.

[0019] In one embodiment, the detection device comprises at least one source of light amplification by stimulated emission of radiation, for example one or two. Such a source is a simple and effective means of determining the positioning of the aircraft during its approach to the parking point.

[0020] The invention also relates to a method for managing the parking of an aircraft at a predetermined location by a system as presented previously, said method comprising the steps of:

[0021] - reception, by the location module, of waves coming from the area in which the aircraft's auxiliary power unit is located when the aircraft is at the predetermined location,

[0022] - determination, by the control module, of the operating or stopping state of the auxiliary power group from the waves received by the location module,

[0023] - display, by the display module, of alert information intended for the pilot when an auxiliary power unit has been detected in working order.

[0024] In one embodiment, the location module comprising at least one thermal camera oriented towards the area comprising the auxiliary power unit of the parked aircraft, the detection of said auxiliary power unit is carried out by measuring, via the at least one thermal camera, the energy of the infrared waves in said area.

[0025] Alternatively or additionally, the location module comprising at least one microphone oriented towards the area comprising the auxiliary power unit of the parked aircraft, the detection of said auxiliary power unit is carried out by measuring, via the at least one microphone, the amplitude of the sound waves in said area.

[0026] Preferably, the method comprises a step of detecting the operation of a ground power supply unit connected to the aircraft and / or an air conditioning unit connected to the aircraft, the display of the alert information being carried out only when a ground power supply unit and / or an air conditioning unit has / have been determined to be in operating condition.

[0027] Advantageously, the method comprises, a ground power supply unit and / or an air conditioning unit being in operation, a step of determining or detecting the operation of the auxiliary power unit and a step of generating an alert when the operation of the auxiliary power unit has been detected. In other words, in this case, the method comprises a step of generating an alert when an auxiliary power unit is detected while a ground power supply unit and / or an air conditioning unit are in operation in order to reduce costs and pollution.

[0028] Advantageously, the method comprises a step of controlling the stopping of a ground-based electrical power supply unit and / or an air conditioning unit in operation when the starting of the auxiliary power unit has been detected.

[0029] The invention also relates to a computer program product characterized in that it comprises a set of program code instructions which, when executed by one or more processors, configure the processor(s) to implement a method as presented previously. Brief description of the drawings

[0030] Other characteristics and advantages of the invention will become apparent from reading the description which follows. This is purely illustrative and must be read in conjunction with the appended drawings in which:

[0031] [Fig.l] [Fig.l] schematically illustrates an embodiment of the system according to the invention.

[0032] [Fig.2] [Fig.2] schematically illustrates an example of an approach of an aircraft taxiing guided by the system of [Fig.l], in top view.

[0033] [Fig.3] [Fig.3] schematically illustrates an example of parking an aircraft informed by the system of [Fig.l], in side view.

[0034] [Fig.4] [Fig.4] schematically illustrates an embodiment of the method according to the invention. Description of the embodiments

[0035] [Fig. 1] shows an example of system 1 according to the invention. System 1 can be mounted on a post or fixed to a wall.

[0036] The system 1 according to the invention allows assistance in parking an aircraft 100 (visible in [Fig.2]), in particular an airplane, on a predetermined parking location 200 ([Fig.2]) during its taxiing approach to said predetermined parking location 200.

[0037] Still with reference to [Fig.2], the aircraft 100 comprises an auxiliary power unit 100A housed in the rear part of the fuselage. The auxiliary power unit 100A makes it possible to produce energy on board the aircraft 100 to supply the various on-board systems on the ground (electrical voltage, pneumatic and hydraulic pressures, air conditioning, etc.) when the main engines of the aircraft 100 are stopped in order to save fuel, and to start the engines. The auxiliary power unit 100A is for example in the form of a turbojet engine emitting heat.

[0038] The predetermined parking location 200 delimits the area of ​​the tarmac on which the aircraft 100 must stand during its refueling and / or its maintenance, for example the area of ​​the tarmac located at the gate boarding level between two rotations of a passenger transport aircraft.

[0039] The system 1 is preferably installed at the end of the predetermined parking location 200 and so that the pilot (or co-pilot) of the aircraft 100 can view it in order to be guided.

[0040] With reference to [Fig.l], the system 1 comprises a detection device 10, location module 20, a control module 30 and a display module 40.

[0041] Detection device 10

[0042] The detection device 10 is configured to transmit and receive signals in order to detect an aircraft 100 placed facing said detection device 10.

[0043] The detection device 10 is used mainly when taxiing during the approach of the aircraft.

[0044] To this end, the detection device 10 may advantageously comprise at least one source of light amplification by stimulated emission of radiation (or "laser"). In the non-limiting example of [Fig. 1], the detection device 10 comprises two laser sources 110.

[0045] The signals reflected on the aircraft are transmitted by the detection device 10 to the control module 30.

[0046] Location module 20

[0047] The location module 20 is configured to receive waves (or measurements) of the area in which the auxiliary power unit 100A is located when the aircraft 100 is parked.

[0048] To this end, the location module 20 may in particular comprise one or more thermal cameras (or infrared cameras) and / or one or more microphones.

[0049] Each thermal camera is configured to measure the infrared energy of the objects, in particular by measuring the amplitudes of the infrared waves emitted by the objects, in particular the auxiliary power unit 100A.

[0050] Each thermal camera is oriented so as to measure the infrared energy of the area of ​​the aircraft 100 comprising the auxiliary power unit 100A, for example the tail of the fuselage of the aircraft 100, when said aircraft 100 is on the predetermined parking location 200.

[0051] Each thermal camera is configured to be calibrated according to the outside temperature in order to avoid confusing the heat of the air rising from the ground by reverberation with the heat emitted by the auxiliary power unit 100A.

[0052] Preferably, the system 1 comprises at least one temperature sensor (not shown) and is configured to carry out automatic calibration of each thermal camera as a function of the measured temperature.

[0053] Each thermal camera is configured to transmit its infrared energy measurements to the control module 30.

[0054] Each microphone is oriented towards the area intended to comprise the auxiliary power unit 100A of the parked aircraft 100, for example the tail of the aircraft 100.

[0055] Each microphone is configured to measure the sound waves emitted in said area in order to allow the control module 30 to determine the operating state or the stopping state of the auxiliary power unit 100A according to the amplitude of the sound waves received.

[0056] Control module 30

[0057] The control module 30 is configured to determine the positioning of the aircraft 100 relative to the predetermined parking location 200 from the signals received from the detection device 10. The positioning of the aircraft 100 is determined in space in terms of orientation relative to the predetermined parking location 200 and advantageously also in terms of distance.

[0058] The control module 30 is configured to generate data to be displayed relating to positioning the aircraft 100 from the determined positioning of the aircraft 100 relative to the predetermined parking location 200 and to send the generated data to the display module 40.

[0059] These data include, for example, the positioning of the aircraft 100 relative to a set of markers materializing the location or direction indications (right-left, distance, etc.) that the pilot must follow to guide the aircraft 100 to the predetermined parking location 200.

[0060] The control module 30 is configured to detect an operating state of the auxiliary power unit 100A from the waves or measurements received by the location module 20 and to control the display of alert information intended for the pilot on the display module 40 when the auxiliary power unit 100A has been detected in operating state.

[0061] The control module 30 is configured to determine the operating state of a ground power supply unit 300 connected to the aircraft 100 and of an air conditioning unit 400 connected to the aircraft 100.

[0062] The control module 30 is configured to control the display, on the display module 40, of operating information of the ground electrical power supply unit 300 and the air conditioning unit 400 when the ground electrical power supply unit 300 and the air conditioning unit 400 are in operation.

[0063] The control module 30 is configured to generate an alert, and preferably display it on the display module 40, when the ground-mounted electrical power supply unit 300 and / or the air conditioning unit 400 are in operation and the auxiliary power unit 100A has been detected.

[0064] The control module 30 is configured to command the stopping of the electrical power supply of the aircraft 100 by the ground electrical power supply unit 300 and / or the air conditioning unit 400 when the auxiliary power unit 100A has been detected.

[0065] The control module 30 comprises a processor capable of implementing a set of instructions making it possible to carry out these functions.

[0066] In the example of the figures, in particular with reference to [Fig.l], the control module 30 is integrated into the display module 40.

[0067] Display module 40

[0068] The display module 40 is configured to receive, from the control module 30, the data relating to the positioning of the aircraft 100 and to display said data in order to guide the pilot to maneuver the aircraft 100 to the predetermined parking location 200.

[0069] In the example of the figures, in particular with reference to [Fig.l], the module display 40 is in the form of a panel integrating the detection device 10 and the control module 30, the location module 20 being mounted above the panel in order to clearly visualize and / or measure the sound level of the tail of the aircraft 100 when it includes the auxiliary power unit 100A.

[0070] The display module 40 makes it possible, for example, to display the type 41 of aircraft 100 (obtained, for example, by recognition using an RGB camera (not shown) or the detection device 10 and a recognition algorithm, for example based on artificial intelligence), a forward 42 or stop command, a central marker 43 for parking the aircraft 100 on the predetermined parking location 200 and two left 44 and right 45 guidance markers to indicate to the pilot in which direction he must maneuver the aircraft 100 to reach the predetermined parking location 200.

[0071] Example of implementation

[0072] First, the aircraft 100 approaches the predetermined parking location 200 on which it is intended to park. When the aircraft 100 positions itself facing the system 1, in particular facing the detection device 10, the detection device 10 emits signals towards the aircraft 100 and receives the signals which have been reflected on said aircraft 100 in order to transmit them to the control module 30. In a preliminary step E0, the control module 30 then determines the positioning of the aircraft 100 relative to the predetermined parking location 200 and then generates guidance indications for the pilot, which are displayed on the display module 40.

[0073] Once parked, the aircraft 100 comes to a stop, the brakes are applied and the ground power supply unit 300 and the air conditioning unit 400 are connected to the aircraft 100 and started (i.e. put into operation) in a step EL

[0074] The control module 30 detects the connections and the start-up of the ground power supply unit 300 and the air conditioning unit 400 and then controls the display of their operating status on the display module 40 for the pilot in a step E2. The control module 30 can optionally receive the value of the air temperature at the outlet of the air conditioning unit 400 or at the connection of the air conditioning unit 400 to the aircraft 100 to also display it on the display module 40.

[0075] Simultaneously, the location module 20 measures the amplitude of the waves (infrared and / or sound) received from the area corresponding to the location where the auxiliary power unit 100A of the aircraft 100 is located and sends these measurements to the control module 30 in a step E3.

[0076] When the control module 30 detects that the auxiliary power unit 100A is releasing heat, in particular beyond a predetermined quantity, the module control 30 deduces that the auxiliary power unit 100A is in operation (step E4) and then commands the display of an alert on the display module 40 for the pilot in a step E5.

[0077] When the pilot sees the alert on the display module 40, he preferably interrupts the operation of the auxiliary power unit 100A in a step E6 in order to reduce the carbon footprint of the aircraft 100.

[0078] When the aircraft 100 must leave the predetermined parking location 200, the pilot starts the auxiliary power unit 100A in a step E7 in order to start its engines and to air-condition and electrically power the aircraft 100 autonomously.

[0079] The control module 30 then detects the operation of the auxiliary power unit 100A from the measurements received from the location module 20 in a step E8 and then commands in a step E9 the stopping of the ground power supply unit 300 and the air conditioning unit 400 which are then disconnected by the ground personnel or else sends a request for stopping and disconnecting the ground power supply unit 300 and the air conditioning unit 400 to the ground personnel, for example displayed on a human-machine interface of the ground power supply unit 300 and on a human-machine interface of the air conditioning unit 400.

[0080] Stopping ground equipment as soon as the operation of the 100A auxiliary power unit is detected makes it possible to reduce carbon emissions, electricity containing more or less carbon depending on the country (for example, between 50 g and 1000 g / kWh).

Claims

Claims

1. System (1) for guidance and information for parking an aircraft (100), said aircraft (100) comprising at least one auxiliary power unit (100A), said system (1) comprising a detection device (10), a control module (30) and a display module (40), said detection device (10) being configured to transmit and receive signals in order to detect the aircraft (100), the control module (30) being configured to determine the positioning of said aircraft (100) relative to a predetermined parking location (200) from the signals received by the detection device (10), to generate information relating to said positioning and to send the generated information to the display module (40),said display module (40) being configured to receive and display information relating to the positioning of the aircraft (100) in order to guide the pilot to maneuver the aircraft (100) to the predetermined parking location (200), said system (1) being characterized in that it further comprises a location module (20) configured to receive waves from the area in which the auxiliary power unit (100A) is located when the aircraft (100) is parked at the predetermined location (200), and in that the control module (30) is configured to, from waves received by said location module (20), determine the operating state or the shutdown state of the auxiliary power unit (100A) in the detected area and to control the display of alert information for the pilot on the display module (40) when the auxiliary power unit (100A) has been detected in operating state.

2. System (1) according to claim 1, wherein the location module (20) comprises at least one thermal camera configured to measure the infrared energy released by the aircraft (100) in the area intended to comprise the auxiliary power unit (100A) of the parked aircraft (100) in order to allow the control module (30) to determine the operating state or the shutdown state of the auxiliary power unit (100A) according to the amplitude of the infrared waves received.

3. System (1) according to any one of the preceding claims, wherein the location module (20) comprises at least one mi- microphone, oriented towards the area intended to comprise the auxiliary power unit (100A) of the parked aircraft (100) and configured to measure the sound waves emitted in said area in order to allow the control module (30) to determine the operating state or the shutdown state of the auxiliary power unit (100A) according to the amplitude of the sound waves received.

4. System (1) according to any one of the preceding claims, wherein the control module (30) is configured to determine the operation or shutdown of a ground power supply unit (300) connected to the aircraft (100) and / or an air conditioning unit (400) connected to the aircraft (100) and to control the display of the alert information only when the ground power supply unit (300) and / or the air conditioning unit (400) are in operation.

5. System (1) according to any one of the preceding claims, wherein the control module (30) is configured to generate an alert when an auxiliary power unit (100A) is detected in operation while a ground power unit (300) and / or an air conditioning unit (400) are in operation.

6. System (1) according to any one of the preceding claims, wherein the control module (30) is configured to command the stopping of a ground power unit (300) and / or an air conditioning unit (400) in operation when the starting of an auxiliary power unit (100A) has been detected.

7. System (1) according to any one of the preceding claims, in which the detection device (10) comprises at least one source of light amplification by stimulated emission of radiation.

8. Method for managing the parking of an aircraft (100) at a predetermined location, by a system (1) according to any one of the preceding claims, said method comprising the steps of: - reception (E3), by the location module (20), of waves coming from the area in which the auxiliary power unit (100A) of the aircraft (100) is located when the aircraft (100) is at the predetermined location (200), - determination (E4), by the control module (30), of the operating or shutdown state of the auxiliary power unit (100A) from waves received by the location module (20), - display (E5), by the display module (40), of alert information to the pilot when an auxiliary power unit (100A) has been detected in working order.

9. Method according to claim 8, in which, the location module (20) comprising at least one thermal camera oriented towards the area comprising the auxiliary power unit (100A) of the parked aircraft (100), the detection of said auxiliary power unit (100A) is carried out by measuring, via the at least one thermal camera, the infrared energy in said area.

10. Method according to any one of claims 8 or 9, in which, the location module (20) comprising at least one microphone oriented towards the area comprising the auxiliary power unit (100A) of the parked aircraft (100), the detection of said auxiliary power unit (100A) is carried out by measuring, via the at least one microphone, the amplitude of the sound waves in said area.

11. A method according to any one of claims 8 to 10, said method comprising a step of determining the operation of a ground power supply unit (300) connected to the aircraft (100) and / or an air conditioning unit (400) connected to the aircraft (100), the display of the alert information being carried out only when a ground power supply unit (300) and / or an air conditioning unit (400) have been determined to be in operation.

12. A method according to any one of claims 8 to 11, said method comprising a step of controlling the stopping of a ground power unit (300) and / or an air conditioning unit (400) in operation when the starting of the auxiliary power unit (100A) has been detected.

13. A computer program product characterized in that it comprises a set of program code instructions which, when executed by one or more processors, configure the processor(s) to implement a method according to any one of claims 8 to 12.

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