Device for detecting impact, associated detection system and aircraft equipped with such a system

Abstract

The present invention relates to an autonomous impact detection device (3), comprising: at least one impact detector (DC); at least one wireless transmitting device (MC) configured to transmit information collected by the impact detector (DC); at least one energy storage device (MS) configured to supply energy to the impact detector (DC) and the wireless transmitting device (MC); at least one Seebeck module (GE1) configured to supply power to the energy storage device (MS) when a temperature gradient is applied thereto; and comprising a second Seebeck module (GE2) so that when the device (3) is subjected to a temperature gradient, a voltage generated by the first Seebeck module (GE1) and a voltage generated by the second Seebeck module (GE2) have opposite polarities.

Description

Technical Field

[0001] The technical field of the present invention is the technical field of collision detection.

[0002] The present invention relates to a crash detection device and in particular to a crash detection device configured to operate autonomously due to the use of a Seebeck module. The invention also relates to a detection system comprising a plurality of detection devices according to the invention and an aircraft equipped with such a system. Background Art

[0003] In a known manner, aircraft may include fuselages made of composite materials or, alternatively, metal. Both types of fuselages are susceptible to damage during an impact, and it is important to be able to detect when such an impact occurs. The risk of impact is particularly significant when an aircraft is parked at an airport, where vehicles circulating (trailers, trucks, etc.) can easily come into contact with the aircraft and damage its fuselage.

[0004] In practice, to detect impact-related damage, operators perform visual inspections of the aircraft's exterior surfaces, which is both time-consuming and expensive, given that the aircraft must be immobilized. Visual detection of impact-related damage is difficult, as damage to composite materials is often internal and not readily apparent from the outside. To overcome this drawback, patent application FR 3 073 500 has proposed the use of detection members positioned on the interior surface of the fuselage. Each detection member is equipped with an impact sensor, wireless communication devices, and energy storage devices. However, the system described in this application does not support autonomous implementation. It is, of course, proposed to harvest the energy supplied by the sensors to power the storage devices, but this solution is difficult to implement in practice, as the vibrations must be within a frequency range suitable for the sensors in order to generate sufficient power.

[0005] Therefore, there is a need for an impact detection device that can operate autonomously. Summary of the Invention

[0006] The present invention provides a solution to the above-mentioned problem by proposing a shock detection device incorporating a Seebeck module.

[0007] A first aspect of the present invention relates to an autonomous impact detection device comprising:

[0008] - at least one impact detector;

[0009] - at least one wireless transmitting device configured to transmit information collected by the impact detector;

[0010] - at least one energy storage device configured to supply energy to the impact detector and the wireless transmitting device;

[0011] - at least one module for gathering energy by the Seebeck effect, configured to supply energy to the storage device when a temperature gradient is applied thereto.

[0012] In addition to the features mentioned in the preceding paragraphs, the system according to the first aspect of the invention may have one or more of the following supplementary features, considered individually or in all technically possible combinations thereof.

[0013] Advantageously, the wireless transmitting device is further configured to receive energy via radio frequency in order to power the storage device.

[0014] Advantageously, the Seebeck module (hereinafter referred to as the first Seebeck module) is arranged according to a first configuration, and the device includes a second Seebeck module arranged according to a second configuration, so that when the device is subjected to a temperature gradient, the voltage generated by the first Seebeck module has an opposite sign to the voltage generated by the second Seebeck module.

[0015] Advantageously, the device comprises a supervisor configured to distribute energy to the different components of the device, preferably parameterizable to supply the different components of the device only when a sufficient amount of energy is required to supply the different components of the device.

[0016] Advantageously, the apparatus comprises a memory configured to store measurements made by the one or more impact detectors, and computing means coupled to the memory, the computing means being configured to perform pre-processing or processing of the data acquired by the impact detectors.

[0017] Advantageously, the device comprises a first group comprising impact detectors and a second group comprising one or more Seebeck modules, the first and second groups being connected so that energy generated by the Seebeck modules at the level of the second group can be transmitted to the first group.

[0018] A second aspect of the invention relates to a system for detecting an impact on a structure, the detection system comprising:

[0019] - a plurality of detection devices according to the first aspect of the invention positioned on the surface of the structure, each detection device being associated with an identifier, the identifier being related to a predetermined area of the structure;

[0020] a plurality of communication devices located close to the structure and configured to communicate with detection devices of the plurality of detection devices in order to collect measurements made by said devices and to associate them with identifiers of the corresponding devices.

[0021] Advantageously, each communication device comprises energy storage means and / or memory.

[0022] A third aspect of the present invention relates to an aircraft comprising a fuselage and a detection system according to the second aspect of the present invention, the detection system being configured to detect an impact on the fuselage, the detection device of the impact detection system being arranged on an inner surface of the fuselage, and the plurality of communication devices of the impact detection system being arranged in the aircraft.

[0023] The invention and its various applications will be better understood by reading the following description and by examining the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] [ Figure 1 ] shows a schematic diagram of a first embodiment of an apparatus according to the first aspect of the present invention.

[0025] [ Figure 2 ] shows a schematic diagram of the structure of a Seebeck cell.

[0026] [ Figure 3 ] shows a schematic diagram of a first exemplary embodiment of a Seebeck module of an apparatus according to the first aspect of the present invention.

[0027] [ Figure 4 ] shows a schematic diagram of a first exemplary embodiment of a set of two Seebeck modules of an apparatus according to the first aspect of the invention.

[0028] [ Figure 5 ] shows a schematic diagram of a second embodiment of the device according to the first aspect of the present invention.

[0029] [ Figure 6 ] shows a schematic diagram of a third embodiment of the device according to the first aspect of the present invention.

[0030] [ Figure 7 ] shows a schematic diagram of a fourth embodiment of the device according to the first aspect of the present invention.

[0031] [ Figure 8 ] shows a schematic diagram of a fifth embodiment of the device according to the first aspect of the present invention.

[0032] [ Figure 9 ] shows a schematic diagram of an aircraft equipped with a detection system according to the second aspect of the invention.

[0033] [ Figure 10 ] shows a schematic diagram of a system according to the second aspect of the invention or a communication device of an aircraft according to the third aspect of the invention. DETAILED DESCRIPTION

[0034] These figures are presented for illustrative purposes and in no way limit the present invention. Unless otherwise stated, identical elements appearing in different figures have a single reference number.

[0035] [ Figure 1 ]The first aspect of the invention illustrated relates to an autonomous collision detection device 3.

[0036] The device 3 according to the first aspect of the present invention includes at least one impact detector DC. The impact detector DC can be selected, for example, from an accelerometer or, alternatively, a piezoelectric sensor. In one embodiment, the device 3 includes multiple impact detectors DC, the properties of which can be the same or different. Thus, by selecting detectors of the same properties, for example, a redundant measurement system can be established to ensure accuracy. Alternatively, detectors of different properties can be selected, each sensitive to different signals.

[0037] The device 3 according to the first aspect of the invention further comprises at least one wireless transmitting device MC provided with an antenna AN, which is configured to transmit the information collected by the one or more impact detectors DC. The wireless transmitting device MC can be, for example, a communication device of the RFID type, a 4G communication device, a Wifi communication device or alternatively a WAIC (Wireless Avionics Intracommunication) communication device. The wireless communication device MC makes it possible to quickly transmit the data measured by the one or more impact detectors DC, which presents certain advantages when data must be collected regularly and / or on a large number of devices 3 according to the first aspect of the invention. This further ensures the freedom of implantation of the detection device 3 according to the invention, since the detection device 3 does not require any physical connection to transmit the measurement data.

[0038] The device 3 according to the first aspect of the invention further comprises at least one energy storage means MS configured to supply energy to the impact detector DC and the wireless transmitting means MC. In one embodiment the storage means MS is selected from among a battery, a capacitor or alternatively a supercapacitor.

[0039] The device 3 according to the first aspect of the invention further comprises at least one Seebeck module GE. In general, a Seebeck module GE comprises one or more Seebeck cells CE, such as Figure 2, and includes a first surface S1 intended to be exposed to a first temperature T1 and a second surface S2 intended to be exposed to a second temperature T2. The temperature gradient ΔT applied to the Seebeck module GE is equal to the difference between the temperature T2 to which the second surface S2 of the Seebeck cell CE is exposed and the temperature T1 to which the first surface S1 of the Seebeck cell CE is exposed, such that ΔT = T2 - T1. The presence of this temperature gradient ΔT causes a voltage V to appear at the terminals of the Seebeck cell CE, the sign of which depends on the Seebeck coefficient of the material used and the sign of the gradient ΔT applied to the Seebeck cell. Hereinafter, by convention, a positive gradient ΔT > 0 will result in a positive voltage V > 0, and a negative gradient ΔT < 0 will result in a negative voltage V < 0.

[0040] An exemplary embodiment of a Seebeck module GE according to the present invention is Figure 3 is illustrated in FIG, where the Seebeck module GE is fixed to the inner surface SI of a wall 10 (eg the fuselage of an aircraft) in order to benefit from the internal temperature T int and external temperature T ext For example, in the case of an aircraft, significant temperature differences exist during flight phases or, alternatively, during storage phases under high external temperature conditions. More specifically, the Seebeck module GE includes a Seebeck cell CE having a first surface S1 and a second surface S2, and a heat sink RA fixed to the second surface S2 of the Seebeck cell. Furthermore, the heat sink RA includes fins capable of effectively thermalizing the second surface S2 of the Seebeck cell CE. In this example, the first surface S1 of the Seebeck cell is fixed at the level of the inner surface S1 of a wall 10, such as the inner surface of an aircraft fuselage. This fixing is preferably performed using an adhesive AD that is a good thermal conductor to ensure good thermalization of the first surface S1 of the Seebeck cell in contact with the inner surface of the wall 10. In this configuration, the temperature gradient ΔT applied to the Seebeck module is therefore equal to the difference between the temperature T2 of the second surface S2 of the Seebeck cell CE and the temperature T1 of the first surface S1 of the Seebeck cell CE. For example, if the wall 10 is the fuselage of an aircraft, during the flight phase, the temperature T1 of the first surface is typically between -20°C and -30°C, or even in extreme cases -50°C to -60°C, while the temperature T2 of the second surface is typically equal to 0°C due to the presence of the heat sink. Therefore, during the flight phase, the temperature gradient ΔT applied to the Seebeck module is typically between 20°C and 60°C. Taking into account these temperature ranges and power requirements of the order of tens of mW, a Seebeck cell CE of a few tens of millimeters (for example 40x40 mm) may be sufficient. As an example, the table below illustrates the charging time of the storage device MS (the left column shows the capacitance of the storage device in farads, denoted C(F)) as a function of the temperature gradient ΔT applied to the Seebeck module and the time.

[0041] [Table 1]

[0042]

[0043] exist Figure 4 In one embodiment illustrated in FIG, the device according to the first aspect of the invention comprises a second Seebeck module GE2 configured in an opposite manner compared to the previously described Seebeck module (hereinafter referred to as the first Seebeck module GE1). In other words, assuming that the Seebeck cell CE comprises a first surface S1 and a second surface S2, when the device 3 according to the first aspect of the invention is fixed to a surface, the Seebeck cell CE of the first Seebeck module GE1 is in contact with the surface 10 via its first surface S1, while the Seebeck cell CE of the second Seebeck module GE2 is in contact with the surface 10 via its second surface S2. In other words, in Figure 4 In the example illustrated in FIG and for the second Seebeck module GE2, the heat sink RA is fixed on the first surface S1 of the Seebeck cell CE and the second surface S2 of the Seebeck cell CE is fixed at the level of the inner surface of the wall 10. Therefore, in this embodiment, regardless of the internal temperature T int and external temperature T ext Regardless of the sign of the temperature gradient ΔT between , the device 3 according to the first aspect of the invention is able to generate a positive (or negative) voltage. Figure 4 In FIG, for each Seebeck cell CE, the dashed arrows indicate the significance of the temperature gradient required to obtain a positive voltage V at the terminals of the corresponding Seebeck module.

[0044] exist Figure 5 In one embodiment illustrated in FIG, the device 1 according to the first aspect of the invention comprises an energy supervisor SE configured to distribute energy to the different components of the device 3 according to the first aspect of the invention.

[0045] exist Figure 6 In one embodiment illustrated in FIG, the wireless transmitter MC / RF is also configured to receive energy via radio frequency. Thus, when the Seebeck module GE does not enable sufficient charging of the storage device MS, the latter can be remotely recharged and / or different components of the device 3 can be supplied with energy. The wireless transmitter MC / RF thus represents a supplementary device for supplying energy to the Seebeck module GE. In practice, the wireless transmitter MC / RF can be used as a substitute for the Seebeck module GE when the temperature gradient is insufficient and when the Seebeck module GE is therefore unable to power the device 3 according to the first aspect of the invention. It should be noted that this is particularly advantageous in the case of an aircraft 1, as small gradients are typically observed when the aircraft 1 is on the ground. However, it is precisely when the aircraft 1 is parked on the ground that safety measures allow the transmission of radio frequency frequencies capable of supplying the necessary energy to the device 3.

[0046] exist Figure 7 In one embodiment illustrated in FIG, the device 3 according to the first aspect of the invention comprises a memory MM configured to store the measurement results performed by the one or more impact detectors DC. Consequently, the measurement results performed by the device 3 do not have to be transmitted immediately, but only at regular intervals. In this embodiment, the device 3 according to the first aspect of the invention further comprises a computing device CP coupled to the memory MM, configured to perform pre-processing or processing on the data acquired by the one or more impact detectors DC. For example, the pre-processing or processing may include selecting the acquired data to be stored in the memory MM and / or transmitted by the wireless communication device MC.

[0047] exist Figure 8 In one embodiment illustrated in FIG, the device 3 according to the first aspect of the invention comprises a first group 31, e.g. in the form of a first housing, comprising one or more impact detectors DC, and a second group 32, e.g. in the form of a second housing, comprising one or more Seebeck modules GE, the first group 31 and the second group 32 being connected such that energy generated by the Seebeck modules GE at the level of the second group 32 can be transferred to the first group 31. Thus, when the most suitable position for detecting an impact and the most suitable position for generating energy by the Seebeck modules GE are not identical, one or more Seebeck modules can be displaced.

[0048] A second aspect of the invention relates to a system for detecting impacts on a structure, the detection system comprising: a plurality of autonomous detection devices 3 according to the first aspect of the invention positioned on a surface S1 of the structure, each detection device 3 being associated with an identifier, which identifier is related to a predetermined area of the structure; and a plurality of communication devices, which are close to the structure and are configured to communicate with a detection device 3 of the plurality of detection devices 3 so as to collect measurement results performed by said devices 3 and associate them with the identifier of the corresponding device 3.

[0049] In the remainder of the description, the system according to the second aspect of the invention will be described by way of application, wherein the structure to be monitored is the fuselage of an aircraft. A person skilled in the art will appreciate that such a system can be used in other situations. Thus, Figure 9A third aspect of the invention, illustrated in FIG, relates to an aircraft 1 comprising a fuselage 10 and an impact detection system according to the second aspect of the invention. The detection system comprises a plurality of autonomous detection devices 3 according to the first aspect of the invention, positioned on the inner surface S1 of the fuselage 10 of the aircraft 1. In addition, each autonomous detection device 3 is associated with an identifier, which is associated with a predetermined fuselage region 10, so that, knowing the identifier of the device 3 that has detected the impact, the region in which the impact occurred can be known.

[0050] In one embodiment, an adhesive is used to fix the detection device 3 to the inner surface S1 of the fuselage 10. The use of an adhesive makes it easier to position and reposition the detection device 3. In addition, this fixing method reduces the risk of damaging the fuselage 10 during the fixing of the detection device 3.

[0051] The aircraft 1 according to the third aspect of the invention further comprises a plurality of communication devices 4 arranged in the aircraft 1 and configured to communicate with a detection device 3 of the plurality of detection devices 3 in order to collect measurements made by said devices 3 and to associate them with identifiers of the corresponding devices 3. Preferably, the plurality of communication devices 4 are positioned so as to be able to communicate with all detection devices 3 of the plurality of detection devices 3. It is important to note that a communication device 4 can communicate with one or more detection devices 3. It is also important to note that one or more detection devices 3 can be positioned so as not to be able to communicate with any communication device 4. However, the latter can be interrogated using a portable communication device 4', for example during control or maintenance operations.

[0052] In one embodiment, the communication devices 4 are powered by a power supply network 12' that connects the various communication devices 4 to the power supply of the aircraft 1. The energy thus received can then be transmitted to each detection device 3 by means of radio frequency reception RF. To this end, each communication device 4 comprises wireless communication means MC' / RF' configured to operate as a wireless communication device or as a means for transmitting energy by radio frequency to the detection device 3. Assuming that the communication device 4 has an antenna AN' with a gain equal to 3 dBi and a loss due to the cable of 4.4 dB, and that the autonomous detection device 3 has an antenna AN with a gain equal to 4.5 dBi, the following table 2 illustrates the power transmitted (in dBm and W) and the power received (in dBm and mW) at the level of the detection device 3 as a function of the distance between the communication device 4 considered and the detection device 3 considered.

[0053] [Table 2]

[0054]

[0055] Therefore, a person skilled in the art will ensure that this information is taken into account during the positioning of the communication device 4 and / or positioning of the detection device 3, while obviously adapting to the assumptions made above.

[0056] exist Figure 10 In one embodiment illustrated in FIG, each communication device 4 includes an energy storage device MS', such as a battery, which is configured to power the communication device 4 when the power supply network 12' is no longer supplying energy. This is particularly the case when the aircraft 1 is parked for an extended period. Thus, even without an external power source, the communication device 4 of the aircraft 1 can continue to interrogate the detection device 3 or even power the detection device 3 via radio frequency if necessary. In one embodiment, the communication device 4 also includes an energy supervisor SE', which is responsible for managing the energy of the communication device 4 and, in particular, the energy storage device MS'.

[0057] In the same manner, the communication devices 4 are connected to the communication network 12 and can transmit the data collected from the detection devices 3 by the communication devices 4 over the communication network 12 for subsequent processing, for example, by the onboard computer 5 or, alternatively, by a centralized maintenance server. In one embodiment, each communication device 4 includes a memory MM' (e.g., a hard disk), and when the power supply network 12' is no longer supplying energy, the data collected from the detection devices 3 is stored in the memory MM' and then transmitted over the communication network when the power supply network 12' is again supplying energy. In one embodiment, the communication devices 4 include a computing device CP' (e.g., a processor) so that the data stored in the memory MM' can be processed.

[0058] In one embodiment, fuselage 10 is a composite fuselage. Indeed, composite fuselage damage is particularly difficult to detect by visual inspection, and a detection system such as that described in the second aspect of the present invention makes such detection more reliable. However, as will be seen above, the present invention can be implemented on any type of fuselage (made of composite materials, metal materials, etc.).

Claims

1. Autonomous impact detection equipment (3), including: - at least one collision detector (DC); - at least one wireless transmitting means (MC) configured to transmit information collected by said collision detector (DC); - at least one energy storage means (MS) configured to supply energy to said collision detector (DC) and said wireless transmitting means (MC); a first Seebeck module (GE1) configured to supply energy to said storage means (MS) when a temperature gradient is applied thereto; The device is characterized in that it comprises a second Seebeck module (GE2) configured to supply energy to the storage device (MS) when a temperature gradient is applied thereto, wherein the first Seebeck module (GE1) is arranged according to a first configuration and wherein the second Seebeck module (GE2) is arranged according to a second configuration, so that when the device (3) is subjected to a temperature gradient, the voltage generated by the first Seebeck module (GE1) and the voltage generated by the second Seebeck module (GE2) have opposite signs.

2. The device (3) according to the preceding claim, characterized in that The wireless transmitting device (MC / RF) is further configured to receive energy via radio frequency to power the storage device (MS).

3. The device (3) according to claim 1, comprising a supervisor (SE) configured to distribute energy to different components of the device (3).

4. The device (3) according to claim 1, comprising: a memory configured to store measurements made by one or more collision detectors (DC); and computing means (CP) coupled to said memory (MM), said computing means (CP) being configured to perform pre-processing or processing of the data acquired by said impact detector (DC).

5. The device (3) according to claim 1 comprises a first group (31) comprising the impact detector (DC) and a second group (32) comprising one or more Seebeck modules (GE), the first group (31) and the second group (32) being connected so that the energy generated by the Seebeck modules (GE) at the level of the second group (32) can be transmitted to the first group (31).

6. An impact detection system for detecting an impact on a structure (10), the impact detection system comprising: - a plurality of devices (3) according to one of the preceding claims positioned on a surface (S1) of the structure (10), each device (3) being associated with an identifier, the identifier being related to a predetermined area of the structure (10); a plurality of communication devices (4) located close to the structure (10) and configured to communicate with devices (3) of the plurality of devices (3) in order to collect measurements made by the devices (3) and to associate them with identifiers of the corresponding devices (3).

7. An impact detection system according to claim 6, wherein each communication device (4) comprises energy storage means and / or memory.

8. Aircraft (1), including: A fuselage and an impact detection system according to claim 6, the impact detection system being configured to detect an impact on the fuselage, the device (3) of the impact detection system being arranged on an inner surface (SI) of the fuselage, and the plurality of communication devices (4) of the impact detection system being arranged in the aircraft (1).

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