System and method for automatically detecting leakage noise in an aircraft

Abstract

The present invention proposes a system and method for detecting leakage noise in an aircraft, making it possible to perform ground tests in complete safety and within the entire cabin pressurization range, thereby avoiding the need to use multiple in-flight tests, the system comprising: at least one acquisition device (3), which is intended to be installed in at least one area of ​​interest in the aircraft (11), the acquisition device (3) being configured to acquire data related to the current noise in the area of ​​interest and data related to the current pressure gradient between the cabin and the outside of the aircraft, and a monitoring device (5), which is configured to control the acquisition of data by the at least one acquisition device and receive the acquired data to detect any leakage noise in the at least one area of ​​interest.

Description

Technical Field

[0001] The present invention relates to the field of leakage noise testing on board an aircraft and more particularly to leakage noise detection in a region of interest of an aircraft. Background Art

[0002] Prior to shipment, the aircraft is subject to a series of ground and in-flight tests and trials, including leakage noise testing. Specifically, at a certain stage of development, a pressurization test is performed on the aircraft on the ground, during which a test compressor injects air into the aircraft to increase the cabin pressure. The increased pressure creates a pressure gradient between the cabin and the outside to simulate the pressure gradient that the aircraft is subject to in flight. The maximum gradient achieved is equal to the maximum gradient obtained in flight plus a certain margin of about 33%. Once the pressure has stabilized, the operator approaches the aircraft to manually inspect the aircraft from the outside to detect leakage noise, mainly at the door frames.

[0003] However, for operator safety reasons, the pressurization of the aircraft cannot be increased above a certain threshold. For this reason, during these tests, the pressure gradients represent the climb phase of the aircraft, rather than the cruise phase when the gradients are higher. Therefore, the ground tests do not represent all phases of flight and therefore do not take into account the evolution of the leakage noise depending on the various pressure gradients. Moreover, the ground tests are not easy and depend on the weather conditions during the tests. Moreover, the manual tests performed from outside the aircraft can generate non-noise leakage detections that are not particularly relevant to the acoustic comfort of the cabin.

[0004] Therefore, additional leakage noise detection tests are performed in flight. During these flight tests, the pilot flies through the cabin and records any abnormal noises, including leakage noise. Once on the ground, these recordings are scrutinized and analyzed in order to detect any anomalies. However, these in-flight tests are very expensive and require a lot of time, which may affect the delivery deadline of the aircraft.

[0005] The object of the present invention is to propose a system for detecting leakage noise in an aircraft which overcomes the above-mentioned drawbacks and allows a thorough and accurate detection of the leakage noise while avoiding the necessity of resorting to multiple in-flight tests. Summary of the invention

[0006] The present invention is directed to a system for detecting leakage noise in an aircraft, comprising:

[0007] at least one acquisition device, intended to be installed in at least one region of interest of the aircraft, said acquisition device being configured to acquire data relating to the current noise in said region of interest and to data relating to the current pressure gradient between the cabin and the outside of the aircraft, said current pressure gradient being from a plurality of operational pressure gradients representative of various phases of flight, and

[0008] A monitoring device is configured to: control the acquisition of data by the at least one acquisition device; and receive the acquired data to detect any leakage noise in the at least one region of interest.

[0009] The system makes it possible to carry out ground tests in complete safety and over the entire cabin pressurization range, by attaching acquisition devices to the areas of interest and by controlling the acquisition of data from a monitoring device from outside the aircraft. It should be noted that the cabin pressurization range represents the various phases of flight: climb, descent and cruise, corresponding to a pressure gradient of about 0 to 9 psi. These tests can be carried out early in the life cycle of the aircraft, thus avoiding the use of repeated in-flight tests. Thus, defects can be fixed early in the life cycle of the aircraft, thereby meeting shipping periods and deadlines. In addition, the system makes it possible to detect relevant leaks that generate noise, thereby avoiding false detections. In addition, the same detection system can also be used in flight to produce noise maps throughout the cabin.

[0010] Advantageously, said at least one acquisition device is connected to said monitoring device via a wireless network.

[0011] The wireless link allows fast and simple installation and synchronization of the detection system and reliable real-time transmission of data while avoiding the use of very long cables.

[0012] Advantageously, the monitoring device is configured to:

[0013] associating acquired data related to the current noise with acquired data related to the current pressure gradient representing the cabin pressurization level,

[0014] performing spectrum analysis on the acquired data related to the current noise, thereby forming acquired spectrum data,

[0015] comparing the acquired spectrum data with reference spectrum data for the same pressure gradient, and

[0016] Based on the comparison, any leakage noise in the at least one region of interest is detected according to at least one pressure gradient value.

[0017] The system makes it possible to automatically process and analyze data, as well as to autonomously and in real time determine anomalies associated with leakage noise.

[0018] Advantageously, said monitoring means are configured to automatically trigger the recording of noise by said at least one acquisition means at a predetermined pressure gradient value.

[0019] This allows automatic recording at relevant pressure gradients without any intervention.

[0020] Advantageously, the system comprises a set of noise acquisition devices intended to be installed in a corresponding set of areas of interest of the aircraft, each acquisition device comprising a microcomputer and at least one microphone, at least one of the acquisition devices being equipped with a pressure sensor for measuring the pressure in the cabin of the aircraft, the acquisition devices equipped with the pressure sensor being configured to determine each current pressure gradient by comparing the current pressure with an initial pressure measured before pressurization of the cabin.

[0021] This allows easy and rapid simultaneous detection of leakage noise in a plurality of regions of interest and allows accurate, easy and rapid determination of pressure gradients.

[0022] Advantageously, each acquisition device comprises a set of microphones intended to be arranged at respective monitoring locations of the area of ​​interest, and the monitoring device is configured to locate locations exhibiting anomalies based on noise acquisition data from the respective microphones.

[0023] This allows for easier maintenance by accurately locating areas exhibiting abnormalities.

[0024] Advantageously, the monitoring device comprises a graphical interface configured to indicate the installation configuration of the acquisition devices and microphones in various areas of interest of the aircraft, and also to indicate the connection to the wireless network and the operability of each acquisition device and each microphone.

[0025] This makes it possible to check the correct connection and correct operation of the individual components throughout the test.

[0026] As an example, each region of interest of the aircraft corresponds to any region from the following regions: passenger doors, cargo doors, sliding windows in the cockpit, and any region having elements passing through a pressurized portion of the aircraft (eg, a hydrophobic drain).

[0027] Advantageously, the system comprises a support with articulated arms, the support being intended to be attached to a region of interest of an aircraft and each articulated arm being intended to support a microphone.

[0028] This allows the acquisition device to be attached quickly and in a variety of configurations.

[0029] The present invention is also directed to a protective shell (of the PELI type), which comprises a unit designed to accommodate a monitoring device, a set of acquisition devices and a set of microphones of a monitoring system according to any one of the aforementioned characteristics, and the protective shell also comprises a power supply system designed to charge the monitoring device and the acquisition device.

[0030] This makes it possible to have a compact detection system that is well protected and easy to transport and recharge.

[0031] The present invention is also directed to a method for detecting leakage noise in an aircraft, comprising the following steps:

[0032] acquiring data relating to current noise in at least one region of interest of the aircraft and data relating to current pressure gradients of a plurality of operational pressure gradients between a cabin and the outside of the aircraft representing various phases of flight, and

[0033] The acquisition of data is controlled and the acquired data is received such that any leakage noise in the at least one region of interest can be detected.

[0034] Advantageously, the method comprises the following steps:

[0035] At least one noise acquisition device is installed in at least one region of interest in the cabin of the aircraft, the acquisition device comprising a set of microphones arranged at respective monitoring positions of the corresponding region of interest,

[0036] Pressurize the aircraft cabin according to a series of pressure gradients,

[0037] controlling the at least one acquisition device by means of a monitoring device from outside the aircraft, the monitoring device being connected to the acquisition device via a network, and

[0038] The acquisition data is analyzed using an acquisition device or a monitoring device to detect any leakage noise in the region of interest based on the various pressure gradient values.

[0039] Advantageously, the analysis of the acquired data comprises correlating the acquired data with reference data, comprising the following steps:

[0040] associating acquired data related to the current noise with acquired data related to the current pressure gradient representing the cabin pressurization level,

[0041] performing spectrum analysis on the acquired data related to the current noise, thereby forming acquired spectrum data,

[0042] comparing the acquired spectrum data with reference spectrum data, and

[0043] Based on the comparison, any leakage noise in the at least one region of interest is detected according to at least one pressure gradient value. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] Other particular features and advantages of the system and method according to the invention will become more apparent when reading the following description given by way of non-limiting indication in conjunction with the accompanying drawings, in which:

[0045] Figure 1 A system for detecting leakage noise in an aircraft according to an embodiment of the present invention is schematically shown;

[0046] Figure 2 A system for detecting leakage noise in an aircraft according to a preferred embodiment of the present invention is schematically shown;

[0047] Figure 3 Schematically shown in more detail Figure 2 Leakage noise detection system;

[0048] Figure 4 Schematically shows a reference according to a preferred embodiment of the present invention Figure 2 and Figure 3 A method for detecting leakage noise in an aircraft;

[0049] Figure 5 Schematically shows a support for a detection system according to a preferred embodiment of the present invention;

[0050] Figure 6 shows a graphic displayed on an interface of a monitoring device according to one embodiment of the present invention, which gives a general configuration of the connections; and

[0051] Figure 7 A protective housing designed to incorporate a detection system according to a preferred embodiment of the present invention is shown. DETAILED DESCRIPTION

[0052] In particular, the principle of the invention is to automatically detect leakage noise in an aircraft, allowing the tests to be performed on the ground and at multiple operating pressure gradients.

[0053] Figure 1 A system for detecting leakage noise in an aircraft according to the invention is schematically shown.

[0054] According to the invention, the detection system 1 comprises at least one acquisition device 3 and a monitoring device 5. The acquisition device 3 is configured to measure noise and at least one of the acquisition devices 3 is also equipped with a pressure sensor 7.

[0055] More specifically, each acquisition device 3 is intended to be mounted in an area of ​​interest of the aircraft (for example on a door) to acquire data relating to the current noise in the area of ​​interest. The acquisition device 3 equipped with a pressure sensor 7 is also configured to acquire data relating to the current pressure gradient between the cabin and the outside of the aircraft.

[0056] The monitoring device 5 is configured to: control the acquisition of data by the acquisition device 3; and receive the acquired data in order to detect any leakage noise in the region of interest of the aircraft. The detection system thus makes it possible not only to record the noise, but also to process it autonomously with respect to the pressure gradient. Furthermore, the acquisition device 3 is advantageously connected to the monitoring device 5 via a wireless network 9.

[0057] Figure 2 A system for detecting leakage noise in an aircraft according to one embodiment of the present invention is schematically shown.

[0058] According to this embodiment, the detection system 1 comprises a monitoring device 5 and a plurality of acquisition devices 31R to 34R and 31L to 34L. In this example, the detection system 1 comprises eight acquisition devices 31R to 34R and 31L to 34L intended to be installed to eight doors D1R to D4R and D1L to D4L of the aircraft 11. Of course, the number of acquisition devices 3 can be as required, and likewise the areas of interest are not limited to passenger doors or crew doors, but can also be sliding windows in the cockpit, cargo doors and any area with elements that pass through a pressurized part of the aircraft (e.g. a hydrophobic drain).

[0059] Figure 3 Schematically but in more detail Figure 2 Leakage noise detection system.

[0060] Each acquisition device 31R, ..., 34L comprises a microcomputer 41 (e.g. the size of a credit card) and one or more microphones 43. Advantageously, the acquisition device 3 comprises a plurality of microphones 43 that can be arranged at various monitoring positions of the area of ​​interest. For example, in the case of a door, the microphone 43 can be located at each corner of the door. Each microphone 43 is configured, for example, to record noise up to about 135 dB. In addition, each acquisition device 3 is equipped with an integrated Wi-Fi antenna 45 that supports, for example, a frequency of several GHz and is designed for point-to-point connection from any location inside the cabin to a wide area around the aircraft 11. In addition, at least one of the acquisition devices 31R to 34L is equipped with a pressure sensor 7 for measuring the pressure in the cabin of the aircraft 11.

[0061] The monitoring device 5 comprises a main microcomputer 51 (e.g., the size of a credit card) equipped with a Wi-Fi antenna 55 and configured to control the acquisition device 3 via the wireless network 9. Furthermore, the monitoring device 5 comprises a graphical interface 57 designed to indicate the installation configuration of the acquisition devices 3 and the microphones 43 in the various areas of interest D1R to D4R and D1L to D4L of the aircraft 11, as well as the connection to the wireless network 9 and the status of the operability of each of the acquisition devices 3 and each of the microphones 43. The graphical interface 57 also allows the user to control the detection system by triggering actions and by providing information related to the aircraft or the detection method.

[0062] The monitoring device 5 also comprises a memory 52 which can be used, for example, to store data relating to the aircraft. Furthermore, each of the acquisition device and the monitoring device is also equipped with a power supply battery 59 .

[0063] Figure 4 Reference Figure 2 and Figure 3 A method for detecting leakage noise in an aircraft according to one embodiment of the present invention is schematically shown.

[0064] The method involves detecting leakage noise in an aircraft on the ground and includes the steps of installing a detection system, pressurizing the aircraft, and processing and analyzing data to detect leakage anomalies.

[0065] Steps E1 and E2 involve the installation of the detection system, during which a plurality of acquisition devices are positioned inside the aircraft at corresponding areas of interest.

[0066] More specifically, in step E1 , one (or more) supports having articulated arms are attached to each door D1R to D4R and D1L to D4L of the aircraft 11 .

[0067] Figure 5 A support for a detection system according to one embodiment of the present invention is schematically shown.

[0068] The support 61 comprises a base 62 equipped with an attachment device 63 and a plurality of articulated arms 64. Each articulated arm 64 is formed by a plurality of segments 65 which are linearly connected to each other by a pivot connection 66 or a ball bearing connection 67. The connection can be blocked by screws, nuts or other blocking means. One end of each articulated arm 64 is attached to the base 62 by a pivot connection 66 and the other end is connected by a ball bearing connection 67 to a support element or clamping element 68 designed to support and hold the microphone 43 in all degrees of freedom. Figure 5The example shows a support 61 comprising two articulated arms 64 , thus being able to support two microphones 43 , and an attachment device 63 comprising two suction cups designed to be firmly attached to a solid surface, for example a certain plane of the aircraft 11 .

[0069] Thus, two supports 61 are attached to each door D1R to D4R and D1L to D4L of the aircraft 11, and each of four articulated arms 64 supports a microphone 43. The arms 64 are articulated so that each microphone 43 monitors the area around the corresponding corner of the door D1R to D4R and D1L to D4L, so that the entire door is completely monitored by four microphones 43, which are connected to the same microcomputer 41.

[0070] In step E2, a Wi-Fi access point 71 (e.g., two access points) using a dynamic host configuration protocol (DHCP) is installed on the aircraft 11 to provide a wireless connection using automatic configuration of IP parameters between the monitoring device 5 located outside the aircraft 11 and each acquisition device 3 located inside the aircraft 11. Therefore, a dynamic IP address is automatically assigned to each acquisition device 3, while the monitoring device 5 can have a static IP address.

[0071] Step E3 involves the activation of the detection system 1 , including initializing and setting the parameters of the acquisition device 3 and the monitoring device 5 and the Wi-Fi access point 71 , respectively.

[0072] In step E4, the graphical interface 57 of the monitoring device 5 indicates the installation layout of the acquisition devices 3 and the microphones 43 in the various zones of interest D1R to D4R and D1L to D4L of the aircraft 11. The graphical interface 57 also indicates the status of the connection to the wireless network 9 and the operability of each of the acquisition devices 3 and each of the microphones 43.

[0073] In particular, the graphical interface 57 displays all the data relating to the connection of the various elements of the detection system and data relating to the aircraft. In particular, the memory 52 of the monitoring device 5 allows the user to specify data relating to the aircraft 11 being tested.

[0074] Figure 6 A graphic displayed on an interface of a monitoring device according to one embodiment of the present invention is shown, which gives a general configuration of the connections.

[0075] According to this example, the interface 57 of the monitoring device 5 comprises a touch screen that displays the layout of the aircraft 11 being inspected and its identity (e.g. MSN 127), as well as the selected area of ​​interest. In this example, the area of ​​interest corresponds to the right doors D1R to D4R and the left doors D1L to D4L of the aircraft 11. Each acquisition device 31R to 34R and 31L to 34L is represented by a circular graphic icon displayed on the location where it is installed (i.e., the doors D1R to D4R, D1L to D4L). The color of the circular icon indicates the connection status of the acquisition device 31R to 34R and 31L to 34L, and the number indicates the number of microphones 43 that are operable in this area. The pressure inside the aircraft and the pressure gradient (e.g. ΔP = 5.1 PSI) are also displayed, where it is known that the pressure gradient is zero at the beginning. In addition, the interface 57 comprises: buttons 73 and 74 (see step E6), respectively controlling the automatic mode and the manual mode; buttons related to parameter settings; and a start button.

[0076] According to this example, the acquisition devices 31R, 33R, 31L and 32L located on the first and third right doors D1R, D3R and the first and second left doors D1L and D2L, respectively, are connected, and their associated microphones are all detected as being operable (here indicated by the number 4). The device 33L located on the third left door D3L is connected, and only three of its microphones are operable. In contrast, the devices 32R, 34R and 34L located on the second and fourth right doors D2R, D4R and the fourth left door D4L are not connected. It should be noted that by clicking on the icon, the user can obtain more information about the corresponding acquisition device.

[0077] In step E5, the cabin of the aircraft is pressurized according to various pressure gradient levels that can reach about 700 mbar, so as to model all the phases of flight. Specifically, air is injected into the aircraft 11 using a system of external compressors 81, which can be of GPU (ground power unit) type, or of the aircraft's auxiliary power unit APU, thus increasing the pressure 83 in the cabin and thus generating the following pressure gradients that simulate those to which the aircraft 11 is subjected in flight.

[0078] In step E6, acquisition means 31R to 34L are controlled from the outside and from an area situated at a sufficiently safe distance from aircraft 11 via monitoring means 5 through wireless network 9. Monitoring and detection of leakage noises can be performed using manual mode or automatic mode.

[0079] In manual mode 73, the user controls the start or stop of recording of each acquisition device 31R to 34L. For example, by simultaneously triggering the start of eight acquisition devices 31R to 34L each equipped with four microphones 43, the user can recover a "32" audio file, allowing real-time noise detection on the monitoring device 5 via the wireless network 9.

[0080] In the automatic mode 74, the monitoring device 5 sends a trigger signal (for example, periodically) to each acquisition device 31R to 34L to trigger the start of recording. As an example, a trigger signal is sent every two minutes, and each trigger signal is designed to command the acquisition device 31R to 34L to perform an automatic recording within ten seconds. In addition, each acquisition device 31R to 34L equipped with a battery 59 is capable of recording the noise related to its area of ​​interest and may autonomously process and analyze its recordings. A file containing the current recording of each of the acquisition devices 31R to 34L and the pressure gradient corresponding to the recordings, and possibly also containing an analysis of these recordings, is automatically sent to the monitoring device 5. The monitoring device 5 stores the files received from the various acquisition devices 31R to 34L in its memory 52.

[0081] As a variant, the monitoring device 5 is configured to automatically trigger the recording of noise by the acquisition devices 31R to 34L at predetermined pressure gradient values ​​representing flight phases at various altitudes, such as 300 mbar, 350 mbar, 450 mbar, 500 mbar, 550 mbar, 600 mbar, 650 mbar, etc. Specifically, the acquisition device 31R equipped with the pressure sensor 7 determines each current pressure gradient by comparing the current pressure with the initial pressure measured before the cabin is pressurized. Each pressure gradient value is sent to the monitoring device 5. Then, whenever the pressure gradient reaches the relevant level pre-recorded in its memory 52, the monitoring device 5 sends a trigger signal to the acquisition devices 31R to 34L to record the noise.

[0082] In steps E7 to E10 , the monitoring means 5 are configured to process the data received from the various acquisition means 31R to 34L in order to detect leakage noise. These steps make it possible to associate the acquired data with the reference data.

[0083] More specifically, in step E7 , the monitoring device 5 is configured to correlate the acquired data 84 relating to the current noise with data relating to the current pressure gradient ΔP representative of the cabin pressurization level.

[0084] In step E8, the monitoring device 5 is configured to perform a spectrum analysis on the acquired data related to the current noise sensed by the microphone 43 of each of the acquisition devices 31R to 34L, thereby forming acquired spectrum data 85. Each spectrum can be calculated in a conventional manner using digital signal processing, for example using a Fast Fourier Transform (FFT). For example, a specific frequency range between 4kHz and 12kHz measured using a third octave band is of interest.

[0085] More specifically, for each noise recording performed by each microphone 43, the static interruption time (not contaminated by transient events) is determined. Next, the average SIL for each one-third octave band centered at frequencies such as 4 kHz, 8 kHz and 16 kHz is calculated using the following formula: special :

[0086]

[0087] In step E9, the monitoring device 5 is configured to compare the acquired spectrum data 85 with reference spectrum data pre-recorded in a database 86 containing known records of leakage noises originating from areas similar to the area of ​​interest (here, the door of the aircraft). More specifically, the average value SIL special Compared to the reference mean SIL determined based on one-third octave bands ref For comparison, the one-third octave bands are centered on the same frequency range from a learning database containing known leakage noise recordings obtained in the same context. In other words, the comparison is performed for the same pressure gradient values ​​and the same monitoring positions. For example, the average SIL obtained at a given pressure gradient by a microphone installed in the upper right corner of a given door is special Compared with the reference average SIL obtained at the same pressure gradient value and the same position ref Make a comparison.

[0088] In step E10, the monitoring device 5 is configured to detect any leakage noise in each region of interest according to each pressure gradient value based on the comparison. Specifically, if the deviation between the acquired spectrum data 85 and the reference spectrum data 86 exceeds a predetermined threshold value S, the corresponding region of interest is considered to exhibit leakage noise and needs to be inspected and possibly repaired.

[0089] Advantageously, a specific repair type is associated with a specific type of leakage detection having a well-identified spectral signature.

[0090] More specifically, the monitoring device 5 is configured to locate the position exhibiting abnormality based on the noise acquisition data from each microphone 43. Therefore, the abnormality is accurately located using the monitoring position covered by the microphone 43 that has sensed the leakage noise. This makes it possible to identify a defective door, and by detecting the deviation relative to the threshold value S for each microphone, the defective area of ​​the door can be identified more accurately. The result is reported directly on the touch screen 57 of the monitoring device 5 in real time.

[0091] It should be noted that, as a variation, steps E8 to E10 involving digital processing of the spectrum, comparison of acquired spectrum data with reference spectrum data, and detection of leakage noise can be performed individually and automatically by each of the acquisition devices 31R to 34L, and the analysis results are sent to the monitoring device 5 in real time.

[0092] Advantageously, the various records and analyses are stored in fixed and / or removable storage means by the monitoring device 5. These data can then be uploaded to a dedicated server to generate statistics and enrich the reference spectrum data.

[0093] Advantageously, the detection system 1 can also be used in flight to generate a noise map throughout the cabin. In particular, once the system is installed in the aircraft 11, a single operator is sufficient to quickly and efficiently survey the entire cabin.

[0094] Figure 7 A protective housing designed to accommodate a detection system therein according to a preferred embodiment of the present invention is shown.

[0095] The protective case 101 is of the PELI type, easily transportable and comprises a storage unit or compartment 103 designed to house the monitoring means 5, the acquisition means 3 and the microphone 43 of the detection system 1. In particular, the dimensions of each element of the detection system 1 do not exceed those of a mobile phone, thus making it possible to incorporate the entire detection system into the case 101 in a compact and safe manner.

[0096] Furthermore, the housing 101 comprises a power supply system 105 which is designed to charge the monitoring device 5 and the individual acquisition devices 3 .

Claims

1. A system for detecting leakage noise in an aircraft, comprising: at least one acquisition device (3) intended to be installed in at least one region of interest of the aircraft (11), the acquisition device (3) being configured to acquire noise acquisition data relating to current noise in the region of interest and pressure gradient data relating to current pressure gradient between a cabin and the outside of the aircraft, the current pressure gradient being from a plurality of operational pressure gradients representative of various phases of flight, and A monitoring device (5) is configured to: control the acquisition of the noise acquisition data and the pressure gradient data by the at least one acquisition device; and receive the noise acquisition data and the pressure gradient data to detect any leakage noise in the at least one area of ​​interest by processing the noise acquisition data from each acquisition device and comparing the processed noise acquisition data from each acquisition device with reference noise acquisition data, wherein the reference noise acquisition data is obtained at the same pressure gradient value and the same position, and the reference noise acquisition data is reference spectrum data.

2. The system according to claim 1, characterized in that The at least one acquisition device (3) is connected to the monitoring device (5) via a wireless network (9).

3. The system according to claim 1 or 2, wherein: Processing the noise acquisition data from each acquisition device and comparing the processed noise acquisition data from each acquisition device with reference noise acquisition data includes: associating noise acquisition data related to said current noise with pressure gradient data related to said current pressure gradient representing a cabin pressurization level, performing spectrum analysis on the noise acquisition data related to the current noise, thereby forming acquired spectrum data, comparing the acquired spectrum data with reference spectrum data for the same pressure gradient, and Based on the comparison, any leakage noise in the at least one region of interest is detected according to the pressure gradient value.

4. The system according to claim 1 or 2, characterized in that: The monitoring device (5) is configured to automatically trigger the recording of noise by the at least one acquisition device at a predetermined pressure gradient value.

5. The system according to claim 2, characterized in that The system comprises a set of acquisition devices, which are intended to be installed in a set of corresponding areas of interest of the aircraft, each acquisition device (3) comprising a microcomputer (41) and at least one microphone (43), and at least one of the set of acquisition devices is equipped with a pressure sensor (7) for measuring the pressure in the cabin of the aircraft, the acquisition device equipped with the pressure sensor (7) being configured to determine each current pressure gradient by comparing the current pressure with an initial pressure measured before pressurization of the cabin.

6. The system according to claim 5, characterized in that Each acquisition device comprises a set of microphones (43) intended to be arranged at respective monitoring locations of the area of ​​interest, and the monitoring device (5) is configured to locate locations exhibiting anomalies based on the noise acquisition data from the respective microphones.

7. The system according to claim 5 or 6, characterized in that: The monitoring device (5) comprises a graphical interface (57) configured to indicate the installation configuration of the acquisition devices (3) in various areas of interest of the aircraft, and also to indicate the connection to the wireless network (9) and the operability of each of the acquisition devices.

8. The system according to claim 1 or 2, characterized in that: Each region of interest of the aircraft corresponds to any of the following regions: a passenger door, a cargo door, a sliding window in the cockpit, and any region having an element passing through a pressurized portion of the aircraft.

9. The system according to claim 5 or 6, characterized in that: The system comprises a support (61) with articulated arms, the support being intended to be attached to the region of interest of the aircraft and each articulated arm being intended to support a microphone (43).

10. A method for detecting leakage noise in an aircraft, comprising the following steps: acquiring, using at least one acquisition device, noise acquisition data relating to current noise in at least one region of interest of the aircraft and pressure gradient data relating to a current pressure gradient between a cabin and the outside of the aircraft, the current pressure gradient being from a plurality of operational pressure gradients representing various phases of flight, and Controlling the acquisition of the noise acquisition data and the pressure gradient data and receiving the noise acquisition data and the pressure gradient data enables detecting any leakage noise in the at least one region of interest by processing the noise acquisition data from each acquisition device and comparing the processed noise acquisition data from each acquisition device with reference noise acquisition data, wherein the reference noise acquisition data is obtained at the same pressure gradient value and the same position, and the reference noise acquisition data is reference spectrum data.

11. The method according to claim 10, characterized in that The method further comprises the following steps: At least one acquisition device is installed in at least one region of interest in the cabin of the aircraft, the acquisition device comprising a set of microphones arranged at respective monitoring positions of the corresponding region of interest, pressurizing the cabin of the aircraft according to a series of pressure gradients, controlling the at least one acquisition device by means of a monitoring device from outside the aircraft, the monitoring device being connected to the acquisition device via a network, and The noise acquisition data is analyzed using the acquisition device or the monitoring device to detect any leakage noise in the region of interest based on the respective pressure gradient values.

12. The method according to claim 11, wherein: Processing the noise acquisition data from each acquisition device and comparing the processed noise acquisition data from each acquisition device with the reference noise acquisition data comprises the following steps: associating noise acquisition data related to said current noise with pressure gradient data related to said current pressure gradient representing a cabin pressurization level, performing spectrum analysis on the noise acquisition data related to the current noise, thereby forming acquired spectrum data, comparing the acquired spectrum data with reference spectrum data, and Based on the comparison, any leakage noise in the at least one region of interest is detected according to at least one pressure gradient value.

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