Method and device for detecting a disconnection situation in a conduit forming part of a fuel manifold pumping system of an aircraft.

Abstract

- Method and device for detecting a disconnection situation in a conduit forming part of a fuel manifold pumping system of an aircraft.- The process (P) includes a receiving step (E1) to receive a value of the quantity of fuel in the collector, a processing step (E2) comprising a substep (E2A) to classify the value received at the receiving step (E1) into a so-called normal value or an so-called abnormal value, a substep (E2B) to calculate the value of a health indicator, from said received value, as well as a predetermined number of values ​​received previously, and a substep (E2C) to compare the value of the health indicator thus calculated to a threshold so as to be able to detect a disconnection situation, as well as an alert step (E3) to issue an alert in the event of detection of a disconnection situation, said process (P) thus making it possible, taking into account the quantity of fuel present in the collector, to reliably detect a disconnection situation and to alert operators, in particular maintenance operators.Figure for the abridged version: Fig. 4.

Description

Title of the invention: Method and device for detecting a disconnection situation of a conduit forming part of a fuel manifold pumping system of an aircraft. technical field

[0001] The present invention relates to a method and a device for detecting a disconnection situation of a conduit forming part of a fuel manifold pumping system of an aircraft. State of the art

[0002] It is known that an aircraft, in particular a transport aircraft, includes a fuel system to supply fuel to the aircraft's engines.

[0003] This fuel supply system generally includes manifolds that receive fuel from fuel tanks, in particular tanks installed in the wings of a transport aircraft, and pumps to transmit the fuel from the manifolds to the engines.

[0004] Each collector cell is also equipped with an injection pump to maintain the fuel level in the collector. For this purpose, a drain line is connected to the outlet of the injection pump.

[0005] It can happen, due in particular to wear or a problem with the seal between the discharge pipe and the injection pump, that the discharge pipe becomes mechanically separated from the injection pump and can thus move. Although such a disconnection does not prevent the fuel system from functioning because the manifold still contains fuel due to its positioning and the aircraft has several manifolds, it can cause damage to the manifold, primarily through movement of the pipe during flight.

[0006] Consequently, without having an immediate impact, such a disconnection may result in medium or long-term wear of the manifold, which may generate significant repair costs and require the aircraft to be grounded.

[0007] There is therefore a need to have a reliable solution to alert operators, in particular maintenance operators, of such a disconnection situation. Description of the invention

[0008] The present invention aims to provide a solution to meet the aforementioned need. It relates to a method for detecting a disconnection situation of a Conduit forming part of a fuel manifold pumping system of an aircraft.

[0009] According to the invention, said method comprises the following sequence of successive steps, which are implemented iteratively: - a receiving step, implemented by a receiver, to receive a value of the quantity of fuel present in said collector; - a processing step, implemented by a processing unit of a computer, said processing step comprising: • a classification sub-step to classify the value received at the reception step, where appropriate into a so-called normal value or an so-called abnormal value; • a calculation substep to calculate the value of a health indicator, based on said received value, whether normal or abnormal, as well as a predetermined number of values ​​received in previous iterations forming a sliding window; and • a comparison substep to compare the value of the health indicator, calculated in the calculation substep, to a threshold in order to detect a disconnection situation; and - an alert step, implemented by a sender, to issue an alert at least in the event of detection of a disconnection situation.

[0010] Thus, thanks to the invention, by taking into account the amount of fuel available in the manifold, it is possible to reliably detect a disconnection of a fuel manifold pumping system line on an aircraft and to issue a corresponding alert. This allows maintenance personnel or other persons caring for the aircraft to be alerted and informed as soon as such a disconnection occurs and is detected, and thus to take appropriate action.

[0011] In a preferred embodiment, at the calculation substep, the value of the health indicator: - is equal to zero, if the value received is normal; - is calculated using the following expression, if the received value is abnormal: HI = 100 (NI / (N1+N2)) where: • NI is the number of abnormal values ​​in the sliding window; and • N2 is the number of normal values ​​in the sliding window.

[0012] Advantageously, in the classification substep, a measured value is considered: - as an abnormal value, if it is less than or equal to a first predetermined threshold value; and - as a normal value, if it is greater than said first predetermined threshold value and less than or equal to a second predetermined threshold value, the second predetermined threshold value being greater than the first predetermined threshold value.

[0013] Moreover, advantageously, if, at the classification substep, the received value is greater than the second predetermined threshold value, the calculation substep, the comparison substep and the alert step are not implemented for this received value.

[0014] Moreover, advantageously, the said series of successive steps is implemented after each flight of the aircraft.

[0015] In a particular embodiment, the method includes an alert inhibition operation enabling the alert step to be inhibited for a given duration so that no alert is issued at the alert step during that given duration.

[0016] Furthermore, advantageously, at the alert stage, the value of the health indicator calculated in the calculation sub-stage is displayed on a screen.

[0017] Furthermore, advantageously, said method also includes a preliminary step of measuring the value of the quantity of fuel in said collector, this measured value being able to be used as a value to be taken into account at the receiving step.

[0018] The present invention also relates to a device for detecting a disconnection situation of a conduit forming part of a fuel manifold pumping system of an aircraft.

[0019] According to the invention, said device comprises at least: - a receiver configured to receive a value of the quantity of fuel present in said collector; - a processing unit of a computer configured for: • classify the value received from the receiver, where applicable, as a so-called normal value or an so-called abnormal value; • calculate the value of a health indicator, based on the received value, whether normal or abnormal, and a predetermined number of previously received values, forming a sliding window; and • compare the value of the health indicator thus calculated to a threshold in order to detect a disconnection situation; and - a transmitter configured to issue an alert at least when a disconnection situation is detected. Brief description of the figures

[0020] The accompanying figures will clearly illustrate how the invention can be implemented. In these figures, identical reference numerals designate similar elements.

[0021] Fig. 1 is a block diagram of a device for detecting a disconnection situation in a conduit that is part of a fuel manifold pumping system of an aircraft.

[0022] Fig. 2 is a partial perspective view of an aircraft wing, showing the position of a fuel collector.

[0023] Fig. 3 is a partial, perspective view of a fuel manifold pumping system.

[0024] Fig. 4 schematically illustrates a method for detecting a disconnection situation.

[0025] Fig. 5 is a graph illustrating measured and received values ​​of the amount of fuel present in the fuel collector, which are used to calculate the values ​​of a health indicator.

[0026] Fig. 6 is a graph illustrating successive calculated values ​​of a health indicator. Detailed description

[0027] The device 1, which illustrates the invention and is schematically represented in a particular embodiment in [Fig. 1], is intended to detect a disconnection situation on an aircraft, in particular on a transport aircraft.

[0028] More specifically, the device 1 is intended to detect a disconnection of a conduit 2 (or pipe) of a pumping system 3 ([Fig. 3]) forming part of an aircraft fuel supply system. The fuel supply system, which is intended to supply fuel to the aircraft engines, typically includes manifolds 4 that receive fuel from fuel tanks before it is delivered to the aircraft engines by the pumping system 3.

[0029] As schematically shown in [Fig. 2], in a particular embodiment, a manifold 4, to which the device 1 can be applied, is arranged in a wing 5 of the aircraft AC. The pumping system 3 includes, in particular, an injection pump 6 associated with the manifold 4, a wall 4A of which is schematically shown in [Fig. 3], and which is intended to maintain a fuel level in the manifold. The conduit 2 is attached to the outlet of the injection pump 6.

[0030] The device 1 is intended to detect a disconnection situation corresponding to a disconnection of such a conduit 2 from the injection pump 6. Without having an immediate impact, such a disconnection could produce medium or long-term wear of the manifold 4, wear which could generate significant repair costs and require immobilization of the aircraft on the ground.

[0031] Also, to detect a disconnection situation as described above, the device 1 comprises, as shown in [Fig. 1], a set 7 of units, including one less: - a receiver 8 configured to receive a value of the quantity of fuel actually present in the manifold 4; - a processing unit 9 of a computer 10, which is configured to: • classify the value received from the receptor 8 (via a link 11), mainly into a so-called normal value or an so-called abnormal value; • calculate the value of a Health Indicator (HI), based on the received (and classified) value, whether normal or abnormal, as well as a predetermined number of previously received values ​​forming a sliding window as specified below; and • compare the value of the health indicator (HI) thus calculated to a threshold in order to detect a disconnection situation; and - a transmitter 12 configured to issue an alert at least when it is informed by the processing unit 9 (via a link 13) of the detection of a disconnection situation.

[0032] The transmitter 12, for example a display device, preferably includes a screen 14 configured to display, where appropriate, a visual message representing an alert. The transmitter 12 may also display on the screen 14 the value of the health indicator HI, calculated by the processing unit 9.

[0033] As an alternative or in addition, the transmitter 12 can also emit an audible alert.

[0034] The computer 10 also includes a database 15 for recording the values ​​of the quantity of fuel (in the manifold 4), received successively via the receiver 8.

[0035] The device 1 further comprises a measuring system 16 which is intended to measure, in a routine manner, the quantity of fuel present in the manifold 4, and this at successive times. At least some of these measured values ​​are received via the receiver 8.

[0036] The measuring system 16 is a standard system installed on the aircraft, which measures the quantity of fuel present in the manifold 4, for example using standard capacitance-type measuring probes or any other type of sensor, particularly during flight. These measurements are recorded in the measuring system 16 or in a suitable memory of a system or computer on the aircraft.

[0037] Device 1 (namely assembly 7) can be a device on board the aircraft or, preferably, a device installed on the ground, for example at an airport.

[0038] In a preferred embodiment, the device 1 is installed at an airport regularly served by the aircraft and is used, for example, by aircraft maintenance personnel. In this case, in a preferred implementation, the receiver 8 is installed and configured to query the measuring system 16 (or another aircraft system containing measurements taken by the measuring system 16) each time the aircraft arrives at an airport gate, so that it transmits, via a wireless data transmission link 17, the latest measured value of the quantity of fuel present in the collector 4. This value received via the receiver 8 is then used by the device 1, as described above.

[0039] In one embodiment, the device 1 is installed on the aircraft, and the receiver 8 is configured to receive the values ​​measured by the measuring system 16, via a conventional link 17, for example of the wired type, either directly from the measuring system 16, or from another system of the aircraft having the measurements made by the measuring system 16.

[0040] The device 1, as described above, is capable of implementing a method P for detecting a disconnection situation.

[0041] The process P comprises, as shown in [Fig. 4], a sequence SE of successive steps, which is implemented iteratively. This sequence SE of successive steps includes: - a reception step El, implemented by the receiver 8, to receive a value indicating the quantity of fuel present in the collector 4; - a processing step E2, implemented by the processing unit 9 of the computer 10. This processing step E2 includes: • a sub-step of classification E2A to classify the value received at the reception step El, where appropriate into a so-called normal value or an so-called abnormal value; • a calculation substep E2B to calculate the value of a health indicator HI, from said received value, whether normal or abnormal, as well as a predetermined number of values ​​received in previous iterations which form a sliding window 18 ([Fig.5]); and • a comparison substep E2C to compare the value of the health indicator HI (calculated in the calculation substep E2B) to a threshold S ([Fig.6]) in order to detect a disconnection situation; and - an alert step E3, implemented by transmitter 12, to issue an alert at least in the event of detection of an (abnormal) disconnection situation.

[0042] The aforementioned steps E1, E2 and E3 are now described in more detail.

[0043] In a particular embodiment, the reception step El is implemented after each flight of the aircraft, in particular when the device 1 is on board the aircraft, as indicated above.

[0044] Furthermore, in a preferred embodiment, the reception step El is implemented each time the aircraft returns to the airport where the device 1 is installed. In this case, the receiver 8 queries the aircraft system containing the measured values ​​to receive one or more measured values, for example, the value measured at the end of each flight. This reception step El is preferably implemented each time the aircraft arrives at an airport gate.

[0045] In the context of the present invention, the value V of the quantity of fuel present in the collector 4 can be a mass value (expressed, for example, in kg) or a volume value (expressed, for example, in m³). The measuring system 16 generally measures a volume value which can then: - be used as is, as a volume value; or - be converted, in the usual way, into a mass value.

[0046] Also, the method P also includes a preliminary step E0 in which the measuring system 16 measures the value V of the quantity of fuel in the collector 4. The measured values ​​are recorded in the measuring system 16 or in an appropriate memory of a system or computer of the aircraft, from where they are received by the receiver 8.

[0047] Fig. 5 illustrates a set of successive measured values ​​V (received via receiver 8) of the quantity of fuel, as a function of time T.

[0048] This [Fig.5] shows three areas of V values: - an IZ zone comprising Vj values ​​which are less than or equal to a predetermined threshold value V1; - a zone Z2 comprising the Vi values ​​that are greater than the threshold value VI and less than or equal to a threshold value V2, the threshold value V2 being greater than the threshold value VI; and - a zone Z3 comprising Vk values ​​that are greater than the threshold value V2.

[0049] By way of illustration only, and not limiting, for a collector 4 with a maximum fuel capacity of 1600 kg: - the threshold value V1 could correspond, for example, to 900 kg; and - the threshold value V2 could correspond, for example, to 1400 kg.

[0050] The purpose of the E2A classification sub-step is to compare each received value to the threshold values ​​VI and V2 so as to be able to position it in one of the zones Z1, Z2 and Z3.

[0051] More specifically, at the E2A classification substep, a value is received: - is considered an abnormal value if it is positioned in the Zl zone, that is, if it is less than or equal to the threshold value VI; - is considered a normal value if it is positioned in zone Z2, that is, if it is greater than the threshold value VI and less than or equal to the threshold value V2; and - is ignored as specified below, if it is positioned in the Z3 zone, that is to say if it is greater than the threshold value V2.

[0052] In the latter, if the value considered is greater than the threshold value V2, the calculation substep E2B, the comparison substep E2C, and the alert step E3 are not implemented for that value. Therefore, no health indicator is calculated and no alert is issued. This situation corresponds to a situation in which an aircraft auxiliary power unit (APU) is operating, such that manifold 4 is almost completely full.

[0053] Then, in the calculation substep E2A which follows the classification substep E21, the processing unit 8 calculates the value of the health indicator HI based on the last value received and based on whether it is considered normal or abnormal.

[0054] More specifically, the calculation is performed as follows by the processing unit 8: -if the received value is normal, the value of the health indicator HI is equal to zero; and - if the received value is abnormal, the value of the health indicator HI is calculated using the following expression: HI = 100 (NI / (N1+N2)) where: - NI is the number of abnormal values ​​in the sliding window 18 ([Fig.5]); and - N2 is the number of normal values ​​in the sliding window 18.

[0055] The sliding window 18 comprises a predetermined number of values, namely N1+N2 values, i.e., the last value considered (for example, the value Vjl in the example of [Fig. 5]) as well as the (N1+N2-1) values ​​(normal and / or abnormal) immediately preceding this last value. The predetermined number of values ​​can be chosen according to the aircraft or the power system to which the method P is applied. By way of simple, non-limiting illustration, it can be equal to 60. A minimum number of values ​​for the sliding window 18 can also be defined, for example, 5, from which the health indicator can be calculated in the calculation substep E2B even if said predetermined number is not reached. An example of a sliding window 18 with an arrow F indicating its direction of movement is shown in [Fig. 5].

[0056] Then, in the E2C comparison substep, the processing unit 8 compares the value of the health indicator HI (calculated in the E2B calculation substep) to a threshold S so as to be able to detect a disconnection situation.

[0057] More specifically, if the value of the health indicator HI is less than or equal to the threshold S ([Fig.6]), the situation is considered normal, i.e. without disconnection of conduit 2 ([Fig.3]).

[0058] On the other hand, if the value of the health indicator HI is greater than the threshold S, the situation is considered an (abnormal) disconnection situation corresponding to a disconnection of the conduit 2 of the injection pump 6 ([Fig. 3]).

[0059] Within the scope of the present invention, the value of the threshold S can be adapted to the intended application and in particular to the aircraft or the fuel system to which the process P is applied. The value of the threshold S, used in the comparison substep E2C, is preferably between 50 and 70, and is, for example, equal to 60.

[0060] Figure 6 is a graph illustrating an example of successive calculated values. of a health indicator. In this example, the values ​​of the health indicator HI are above the threshold S for several points. A successful maintenance operation (a reconnection of conduit 2) was carried out, as illustrated by the zero values ​​of the health indicator HI (representative of a normal situation) starting from the value HH.

[0061] Depending on the result of the E2C comparison substep (normal situation or disconnection situation), an alert is issued or not at the E3 alert step.

[0062] If a disconnection situation is detected, transmitter 12 emits a visual (and / or possibly audible) alert, particularly to warn maintenance personnel. This alert may be accompanied by the display of the calculated value of the HL health indicator.

[0063] If no disconnection situation is detected, the transmitter 12 does not issue any alert. In a particular embodiment, however, it can inform the operators of the actual situation.

[0064] The method P also includes an alert inhibition operation allowing an operator to inhibit the transmitter 12 for a given period, for example for a few days, to prevent an alert from being issued at the alert step E3 in the event of detection of a disconnection situation.

[0065] Such inhibition prevents an alert from being issued at each processing of a new value received, while waiting for the repair, even though the maintenance personnel have been alerted to a disconnection situation, but the repair has not yet been carried out.

[0066] Device 1 and method P, as described above, thus make it possible, taking into account the quantity V of fuel available in the collector 4, to detect, from in a completely reliable way, a situation of disconnection of conduit 2 and to issue a corresponding alert.

[0067] This allows maintenance personnel or other persons caring for the aircraft to be alerted and informed as soon as such a disconnection occurs and is detected. They can then take appropriate measures to prevent the occurrence or worsening of damage to the manifold, and also to any rib or stringer of the wing structure located near the manifold.

Claims

Demands

1. A method for detecting a disconnection situation in a conduit forming part of a fuel manifold pumping system of an aircraft, characterized in that it comprises the following sequence (SE) of successive steps, which are implemented iteratively: - a receiving step (El), implemented by a receiver (8), to receive a value of the quantity of fuel present in said collector (4); - a processing step (E2), implemented by a processing unit (9) of a computer (10), said processing step (E2) comprising: • a classification sub-step (E2A) to classify the value received at the reception step (El), where appropriate into a so-called normal value or an so-called abnormal value; • a calculation substep (E2B) to calculate the value of a health indicator (HI), from said received value, normal or abnormal, as well as from a predetermined number of values ​​received in previous iterations forming a sliding window (18); and • a comparison substep (E2C) to compare the value of the health indicator (HI), calculated in the calculation substep (E2B), to a threshold (S) in order to detect a disconnection situation; and - an alert step (E3), implemented by a transmitter (12), to issue an alert at least in the event of detection of a disconnection situation.

2. Method according to claim 1, characterized in that, at the calculation sub-step (E2B), the value of the health indicator: - is equal to zero, if the value received is normal; - is calculated using the following expression, if the received value is abnormal: HI = 100 (NI / (N1+N2)) where: • NI is the number of abnormal values ​​in the sliding window (18); and • N2 is the number of normal values ​​in the sliding window (18).

3. A method according to any one of claims 1 and 2, characterized in that at the classification substep (E2A), a received value is considered: - as an abnormal value, if it is less than or equal to a first predetermined threshold value (VI); and - as a normal value, if it is greater than said first predetermined threshold value (VI) and less than or equal to a second predetermined threshold value (V2), the second predetermined threshold value (V2) being greater than the first predetermined threshold value (VI).

4. Method according to claim 3, characterized in that if, at the classification substep (E2A), the received value is greater than the second predetermined threshold value (V2), the calculation substep (E2B), the comparison substep (E2C) and the alert step (E3) are not implemented for this received value.

5. A method according to any one of the preceding claims, characterized in that said sequence of successive steps (SE) is implemented after each flight of the aircraft.

6. A method according to any one of the preceding claims, characterized in that at the alert step (E3), the value of the health indicator (HI) calculated in the calculation substep (E2B) is displayed on a screen (14).

7. A method according to any one of the preceding claims, characterized in that it comprises an alert inhibition operation enabling the alert step (E3) to be inhibited for a given duration, so that no alert is issued at the alert step (E3) during that given duration.

8. A method according to any one of the preceding claims, characterized in that it comprises a preliminary step (EO) of measuring the value of the quantity of fuel in said collector (4), this measured value being able to be used as the value to be taken into account in the acceptance step (El).

9. A device for detecting a disconnection situation in a fuel line of a pumping system forming part of an aircraft fuel manifold, characterized in that it comprises at least: - a receiver (8) configured to receive a value of the quantity of fuel present in said collector (4); - a processing unit (9) of a computer (10) configured for: • classify the received value as either a normal value or an abnormal value; • calculate the value of a health indicator (HI), from said received value, normal or abnormal, as well as from a predetermined number of previously received values, forming a sliding window (18); and • compare the value of the health indicator (HI) thus calculated to a threshold (S) in order to detect a disconnection situation; and - a transmitter (12) configured to issue an alert at least when a disconnection situation is detected.

Images