A fuel leak management system, management method, and aircraft

Abstract

The application discloses a fuel leakage management system, a management method and an aircraft, and relates to the technical field of fuel leakage management systems, and aims to reduce the risk of fuel leakage and improve the safety of a fuel system. The management system comprises a fuel tank, a ventilation pipeline, a drainage pipeline, a gas supply device, a detection device and a control device; a separation cavity is arranged between an outer shell and an inner shell of the fuel tank; a ventilation air inlet of the ventilation pipeline is connected with the gas supply device; a ventilation air outlet of the ventilation pipeline is connected with a separation cavity air inlet; a separation cavity air outlet is connected with a drainage air inlet of the drainage pipeline; a drainage air outlet of the drainage pipeline is connected with a drainage device; the detection device is arranged on a connection path between the drainage air outlet and the drainage device; and the detection device and the control device are in communication connection. The application can realize the detection and control of fuel leakage in different working states by arranging the gas supply device, the detection device and the control device, can reduce the risk of fuel leakage, and can improve the safety of the fuel system.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, in particular to a fuel leakage management system, a management method and an aircraft. BACKGROUND

[0002] The auxiliary fuel tank of a civil aircraft is arranged in the cargo cabin of the fuselage. In order to ensure that the oil gas or liquid that is inadvertently leaked does not accumulate and increase the safety hazard, in the prior art, the auxiliary fuel tank is mostly designed as a sandwich structure, the inner shell stores fuel, the outer shell serves as a barrier layer for the leaked oil gas or liquid, and the cavity between the inner shell and the outer shell serves as a ventilation channel. An air inlet is arranged on the upper part of each auxiliary fuel tank, and the cavity is ventilated by supplying air through the pressurized gas introduced from the passenger cabin to blow away the oil gas or liquid that may be leaked in the cavity of the auxiliary fuel tank. However, since the pressurized gas in the passenger cabin is only generated during the flight stage of the aircraft, and the pressure difference increases with the increase of the flight altitude, this method still has limitations, i.e. this method is invalid when the aircraft is on the ground, and this method does not have the functions of real-time monitoring of leakage and ventilation control. SUMMARY

[0003] In view of the above-mentioned defects of the prior art, the technical problem to be solved by the present application is how to improve the real-time performance of fuel leakage detection and the flexibility of the ventilation system.

[0004] In order to solve at least one of the above-mentioned technical problems, the present application discloses a fuel leakage management system, a management method and an aircraft.

[0005] According to an aspect of the present disclosure, a fuel leakage management system is provided, comprising:

[0006] at least one fuel tank, a ventilation pipeline, a liquid discharge pipeline, an air supply device, a detection device and a control device;

[0007] The at least one fuel tank has an inner shell and an outer shell, and a cavity is formed between the outer shell and the inner shell; the cavity has a cavity air inlet and a cavity air outlet;

[0008] The first air inlet of the ventilation pipeline is connected with the air supply device; the ventilation air outlet of the ventilation pipeline is connected with the cavity air inlet;

[0009] The at least one fuel tank is connected with the liquid discharge air inlet of the liquid discharge pipeline through the cavity air outlet, and the liquid discharge air outlet of the liquid discharge pipeline is connected with a liquid discharge device of a fuel drive system;

[0010] The detection device is arranged on the connection path between the liquid discharge air outlet and the liquid discharge device; the detection device and the control device are communicatively connected.

[0011] In some possible embodiments, the fuel leakage management system further comprises a control valve;

[0012] One end of the control valve is connected with the fuel dispenser, and the other end is connected with the fuel inlet of the at least one fuel tank;

[0013] The control valve is further connected with the control device, for controlling the injection and stop of fuel injection.

[0014] In some possible embodiments, the number of the at least one fuel tank is multiple;

[0015] There are connecting channels between the multiple fuel tanks, so that fuel is injected into other fuel tanks through the fuel inlet of one of the fuel tanks.

[0016] In some possible embodiments, the fuel leakage management system further comprises a one-way valve and a gas filter;

[0017] The ventilation pipeline further comprises a second air inlet, which is connected with the cabin exhaust port of the fuel-driven system;

[0018] The one-way valve is arranged on the connecting path between the second air inlet and the cabin exhaust port, and the gas filter is arranged between the cabin exhaust port and the one-way valve.

[0019] In some possible embodiments, the fuel leakage management system further comprises a flow regulating device;

[0020] The flow regulating device is used to adjust the gas flow of the ventilation gas in the ventilation pipeline and / or the liquid discharge pipeline.

[0021] In some possible embodiments, the flow regulating device is arranged on the connecting path between the second air inlet and the cabin exhaust port, and the flow regulating device is connected with the one-way valve and the control device respectively.

[0022] In some possible embodiments, the flow regulating device is arranged on the connecting path between the liquid discharge air outlet and the liquid discharge device, and the flow regulating device is connected with the control device and the detection device respectively.

[0023] According to a second aspect of the present disclosure, a fuel leakage management method is provided, which is implemented based on the fuel leakage management system according to any one of the above, comprising:

[0024] The ventilation gas is provided to the first air inlet based on the gas supply device, so that the ventilation gas flows along the ventilation pipeline, the separation cavity and the liquid discharge pipeline to the detection device;

[0025] determining whether a leakage detection signal from the detection device is received; the leakage detection signal representing the presence of leaked fuel in the separation cavity;

[0026] generating a fuel control signal in the case that the leakage detection signal is received;

[0027] sending the fuel control signal to the control valve to cause the control valve to shut off and control fuel from being injected into the fuel tank.

[0028] According to a third aspect of the present disclosure, a fuel leakage management method is provided, implemented based on the fuel leakage management system according to any one of the above aspects, comprising:

[0029] providing the ventilation gas to the second air inlet based on the cabin exhaust outlet, so that the ventilation gas flows along the ventilation pipeline, the separation cavity, and the liquid discharge pipeline to the detection device;

[0030] determining whether a leakage detection signal from the detection device is received; the leakage detection signal representing the presence of leaked fuel in the separation cavity;

[0031] generating a flow control signal in the case that the leakage detection signal is received;

[0032] sending the flow control signal to the flow regulating device to cause the flow regulating device to switch the working mode and control the gas flow of the ventilation gas.

[0033] According to a fourth aspect of the present disclosure, a flying vehicle is provided, comprising the fuel leakage management system according to any one of the above aspects, and capable of performing the fuel leakage management method according to any one of the above aspects.

[0034] The present application has the following beneficial effects:

[0035] In the present application, by adding a gas supply device, a detection device, and a control device in the fuel leakage management system, the gas supply device can provide ventilation gas for the fuel leakage management system when the fuel drive system is not working, so that the fuel drive system can also detect fuel leakage through the detection device during fuel addition, improving the real-time and scene adaptability of fuel leakage detection, and interrupting fuel addition in the case of detecting fuel leakage, which can avoid continuous fuel leakage and timely maintenance; in the working state of the fuel drive system, the detection device performs real-time detection of fuel leakage, and the control device regulates the discharge of leaked fuel according to the detection result, thereby improving the timeliness of fuel leakage detection and the accuracy of regulating the discharge of leaked fuel, and further improving the efficiency of fuel discharge, avoiding oil and gas accumulation, and reducing the risk that may exist during driving of the fuel drive system. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] In order to more clearly illustrate the technical solution of the present invention, the following briefly introduces the drawings required for use in the embodiments or descriptions of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0037] Figure 1 This is a system architecture diagram corresponding to the fuel leakage management system in the prior art;

[0038] Figure 2 This is a diagram of the overall system architecture corresponding to a fuel leakage management system provided by an embodiment of the present invention;

[0039] Figure 3 A first system architecture diagram corresponding to a fuel leakage management system provided by an embodiment of the present invention;

[0040] Figure 4 A second system architecture diagram corresponding to a fuel leakage management system provided by an embodiment of the present invention;

[0041] Figure 5 A schematic diagram of the working logic of the flow regulating device provided in an embodiment of the present invention;

[0042] Figure 6 A third system architecture diagram corresponding to a fuel leakage management system provided by an embodiment of the present invention;

[0043] Figure 7 A first simulation result diagram corresponding to the fuel leakage management system provided by an embodiment of the present invention;

[0044] Figure 8 A second simulation result diagram corresponding to the fuel leakage management system provided by an embodiment of the present invention;

[0045] Figure 9 A third simulation result diagram corresponding to the fuel leakage management system provided by an embodiment of the present invention;

[0046] Figure 10 A fourth simulation result diagram corresponding to the fuel leakage management system provided by an embodiment of the present invention;

[0047] Figure 11 A fifth simulation result diagram corresponding to the fuel leakage management system provided by an embodiment of the present invention;

[0048] Figure 12 A sixth simulation result diagram corresponding to the fuel leakage management system provided by an embodiment of the present invention;

[0049] Figure 13 Another fuel leakage management system provided by the embodiment of the present application corresponds to the overall architecture diagram;

[0050] Figure 14 A fuel leakage management method provided by the embodiment of the present application corresponds to the flowchart diagram;

[0051] Figure 15 Another fuel leakage management method provided by the embodiment of the present application corresponds to the flowchart diagram;

[0052] Figure 16 A fuel leakage management device provided by the embodiment of the present application corresponds to the structural diagram;

[0053] Figure 17 Another fuel leakage management device provided by the embodiment of the present application corresponds to the structural diagram.

[0054] Wherein, the above-mentioned reference signs can correspond to: 100-fuel tank, 110-inner shell, 120-outer shell, 130-separation cavity, 131-separation cavity air inlet, 132-separation cavity air outlet, 140-oil inlet, 150-connection channel, 200-ventilation pipeline, 210-first air inlet, 220-second air inlet, 230-ventilation air outlet, 300-drainage pipeline, 310-drainage air inlet, 320-drainage air outlet, 400-one-way valve, 410-gas filter, 500-gas supply device, 600-detection device, 700-control device, 800-flow regulating device, 900-control valve, 910-filling gun, 1-cabin air outlet, 2-drainage device. DETAILED DESCRIPTION

[0055] The technical solutions in the embodiments of the present specification will be described clearly and completely in the following with reference to the drawings in the embodiments of the present specification. Obviously, the described embodiments are only part of the embodiments of the present specification, rather than all the embodiments. Based on the embodiments in the present specification, all other embodiments obtained by those skilled in the art without creative labor are within the scope of protection of the present application.

[0056] It is to be understood that the terms "first", "second", etc. can be used herein to describe various elements throughout the specification and claims, which are not necessarily intended to refer to chronology or order of one to another, but to distinguish one element from another. It will be appreciated that the use of such terms as "first", "second" and the like can be interchanged, as appropriate, to distinguish elements from one another. Furthermore, the terms "comprise", "comprising", "include", "including", and the like are to be construed open- ended, meaning that they include the listed steps or elements, but not excluding other steps or elements. Likewise, the term "sub-embodiment" does not necessarily exclude the inclusion of additional elements or steps.

[0057] Various exemplary embodiments, features, and aspects of the disclosure will be described herein with reference to the drawings. Like reference numerals in different drawings denote the same or similar functional elements. Although various aspects of embodiments are illustrated in the drawings, the drawings are not necessarily drawn to scale unless specifically noted.

[0058] The term "exemplary" is used herein to mean "serving as an example, instance, or illustration." Any implementation described herein as "exemplary" is not necessarily to be construed as preferred or advantageous over other implementations.

[0059] The term "and / or" used in this text is only used to describe the association relationship of the associated objects, which means that there can be three relationships, for example, A and / or B can represent three cases of A alone, A and B together, and B alone. In addition, the term "at least one" in this text means any one of a plurality or any combination of at least two of a plurality, for example, including at least one of A, B, and C can mean including any one or more elements selected from the set consisting of A, B, and C.

[0060] In addition, in order to better illustrate the present disclosure, numerous specific details are given in the specific embodiments below. Those skilled in the art should understand that the present disclosure can also be implemented without certain specific details. In some examples, methods, means, elements and circuits well known to those skilled in the art are not described in detail, in order to highlight the main idea of the present disclosure.

[0061] For the fuel-driven system, which can be any system driven by fuel, such as aircraft, automobile, etc., the fuel leakage management system can detect the fuel leakage of the fuel-driven system in different working states. In the embodiments of the present application, a civil aircraft is taken as a specific fuel-driven system, and the auxiliary fuel tank of the civil aircraft is taken as a specific fuel tank for example and illustrative description. In actual application, the fuel-driven system and the fuel tank are not limited, and can be any fuel-driven system capable of carrying the fuel leakage management system and capable of performing the fuel leakage management method.

[0062] For the civil aircraft, a fuel tank is usually provided to store fuel, in which the main fuel can be stored in the wing main tank, and the auxiliary fuel can be stored in the auxiliary fuel tank in the cargo compartment of the fuselage. The auxiliary fuel can increase the flight range of the aircraft in cooperation with the main fuel. According to the ignition source protection requirement, the ventilation and leakage of the enclosed area outside the fuel storage area is required to ensure that the oil gas leaked by accident can be carried away by the airflow without accumulation, thereby reducing the possibility of fuel tank explosion and reducing the harmfulness of explosion. Generally, the typical architecture of the auxiliary fuel tank ventilation and leakage system is as shown in Figure 1 The auxiliary fuel tank is usually designed as a double-layer structure, and a cavity is formed between the inner wall of the tank and the outer wall of the tank. An air inlet is arranged at the upper part of each auxiliary fuel tank, and the cavity is ventilated by forced air supply through the air inlet of the passenger cabin air conditioning system to blow off the oil gas or oil liquid that may be generated in the cavity of the auxiliary fuel tank. A discharge pipeline is arranged at the bottom of each auxiliary fuel tank, and after purging, the oil gas or oil liquid generated in the cavity of the auxiliary fuel tank is discharged to the outside safety area through the discharge rod.

[0063] However Figure 1 The scheme shown in the figure has no control ability for the gas introduced into the passenger cabin, and can only mechanically introduce the gas in the passenger cabin into the cavity between the inner and outer walls of the auxiliary fuel tank. The pressure difference between the passenger cabin and the external environment of the aircraft during flight provides differential pressure power to purge the cavity. However, when the aircraft is in the cruising stage, the above-mentioned pressure difference is large, which can cause a large amount of leakage of the passenger cabin gas through the cavity. At the same time, under the scheme of the prior art, when the aircraft is on the ground, real-time monitoring of leakage during fuel addition cannot be performed, which can cause the leakage to expand and aggravate the damage to the fuel tank.

[0064] Therefore, the fuel leakage management system disclosed in the present application can monitor fuel leakage and regulate ventilation gas in real time, thereby improving the ventilation and leakage efficiency and the safety of the fuel tank. The fuel leakage management system will be described below with reference to the accompanying drawings.

[0065] Figure 2 An overall system architecture diagram of a fuel leakage management system provided by an embodiment of the present application is shown in Figure 2As shown, the fuel leakage management system can include: a fuel tank 100, a ventilation pipeline 200, a drainage pipeline 300, a one-way valve 400, a gas filter 410, a gas supply device 500, a detection device 600, a control device 700, a flow regulating device 800, a control valve 900; in addition, when the fuel-driven system is in a refueling state, the fuel leakage management system can further include a refueling gun 910; based on Figure 2 the structure in the fuel leakage management system, different fuel leakage management methods can be performed when the fuel-driven system corresponds to different working states. The following will be described in combination with specific embodiments.

[0066] Embodiment one

[0067] Figure 3 A first system architecture diagram corresponding to a fuel leakage management system provided by an embodiment of the present application is shown; as Figure 3 shown, when the fuel-driven system is in a non-driving state, the structure participating in the work in a fuel leakage management system can at least include:

[0068] at least one fuel tank 100, a ventilation pipeline 200, a drainage pipeline 300, a gas supply device 500, a detection device 600, and a control device 700;

[0069] The at least one fuel tank 100 has an inner shell 110 and an outer shell 120, and a separation cavity 130 is formed between the outer shell 120 and the inner shell 110; the separation cavity 130 has a separation cavity air inlet 131 and a separation cavity air outlet 132;

[0070] For the fuel tank 100, it includes an inner shell 110 and an outer shell 120, the inner shell 110 is used to contain fuel, which can be fuel liquid or other fuel capable of providing driving force for the fuel-driven system, and the fuel tank is used to store fuel, which can be any fuel storage container with the same structure as the fuel tank in the present application; the outer shell 120 is used to isolate leakage and avoid further spreading of the leakage; a separation cavity 130 is formed between the inner shell 110 and the outer shell 120, which can contain the leaked fuel from the inner shell 110 and discharge the leaked fuel through its connection relationship. The leaked fuel can be in a liquid state or in a gaseous state due to changes in gas pressure, temperature, etc., and any embodiment of the present application does not limit the form of the leaked fuel.

[0071] In addition, the number and type of fuel tanks 100 can be one or multiple, which can be adaptively adjusted according to the performance requirements or structural design of different aircraft or different fuel-driven systems; for civil aircraft or other fuel-driven systems with main fuel tanks and auxiliary fuel tanks, the fuel tank 100 can be an auxiliary fuel tank or a main fuel tank. This embodiment and the corresponding drawings Figure 3Taking two auxiliary fuel tanks 100 as an example, the system architecture of a fuel leakage management system with multiple auxiliary fuel tanks is described.

[0072] When there are multiple fuel tanks 100 , connecting channels 150 exist between the multiple fuel tanks 100 , so that fuel can be injected into other auxiliary fuel tanks 100 through the fuel inlet 140 of one auxiliary fuel tank 100 .

[0073] like Figure 3 As shown, a connecting channel 150 is provided between the multiple auxiliary fuel tanks 100. Fuel flows between the multiple auxiliary fuel tanks 100 through the connecting channel 150. Therefore, the injection and stopping of fuel in the multiple auxiliary fuel tanks 100 can be controlled through a single fuel inlet 140, thereby improving the convenience of fuel injection control; at the same time, it can also reduce the number of control valves 900, reduce production costs and save internal space of the system.

[0074] The first air inlet 210 of the ventilation pipeline 200 is connected to the air supply device 500; the ventilation outlet 230 of the ventilation pipeline 200 is connected to the compartment air inlet 131;

[0075] The at least one fuel tank 100 is connected to the drain inlet 310 of the drain line 300 via the compartment air outlet 132, and the drain outlet 320 of the drain line 300 is connected to the drain device 2 of the fuel drive system;

[0076] Specifically, the ventilation duct 200 is used to introduce ventilation gas into the compartment 130. The ventilation duct 200 may include at least one air inlet and at least one air outlet, namely, a first air inlet 210 and a ventilation outlet 230. The first air inlet 210 of the ventilation duct 200 is connected to the air supply device 500 and is used to perform pressurized bleed air when the civil aircraft or other fuel-powered system is in a non-driven state, introducing external air as ventilation gas into the ventilation duct 200. As for the ventilation outlet 230, since it is connected to the compartment air inlet 131 and is used to introduce ventilation gas into the compartment 130, it can be concluded that the number of ventilation outlets 230 in the ventilation duct 200 needs to be adaptively adjusted according to the changes in the fuel tanks 100. It can be understood that the number of ventilation outlets 230 is equal to the number of fuel tanks 100. In this embodiment, there are two fuel tanks 100, so the number of ventilation outlets 230 is also two.

[0077] Among them, the non-driven state can be the stage when the aircraft is stationary on the ground, or the stage when the aircraft is refueling on the ground; the air supply device 500 can be an air compressor or other boosting equipment. The air supply device 500 is used to provide a pressure source to press the external gas into the ventilation pipe 200 as ventilation gas and enter the compartment 130.

[0078] The drain pipeline 300 is used to drain the leaked fuel from the vent gas in the compartment 130 of the fuel tank 100; the drain pipeline 300 can include at least one liquid inlet and at least one liquid outlet, i.e. a drain gas inlet 310 and a drain gas outlet 320; since the drain gas inlet 310 is connected with the compartment gas outlet 132 and is used to drain the vent gas carrying the leaked fuel from the compartment 130, the number of the drain gas inlets 310 in the drain pipeline 300 needs to be adjusted adaptively according to the changes of the fuel tank 100, and it can be understood that the number of the drain gas inlets 310 is equal to the number of the fuel tank 100; in the embodiment, the number of the fuel tank 100 is two, and the number of the drain gas inlets 310 is also two; the drain gas outlet 320 is connected with the drain device 2 of the fuel drive system, and the drain device 2 can be an aircraft drain rod or any device used to drain the leaked fuel from the drive system in other fuel drive systems; the vent gas carrying the leaked fuel gas or liquid flows from the compartment 130 to the drain device 2 along the drain pipeline 300, and then is drained out of the aircraft to improve the safety of the aircraft and reduce the risk of fuel explosion caused by fuel leakage.

[0079] The detection device 600 is arranged on the connection path between the drain gas outlet 320 and the drain device 2; the detection device 600 and the control device 700 are in communication connection.

[0080] The detection device 600 can be applied to any state of the fuel drive system, i.e. the fuel leakage can be detected at any time; the detection device 600 is arranged on the connection path between the drain gas outlet 320 and the drain device 2, which not only ensures that the leaked fuel can be drained out in time, but also ensures the accuracy and reliability of the fuel leakage detection; the detection device 600 can use an oil and gas detector or any other device capable of detecting fuel leakage. At the same time, the detection device 600 is in communication connection with the control device 700, so that the detection device 600 can send a leakage detection signal to the control device 700; the control device 700 can be an AFCU (Auxiliary Fuel Control Unit), which is used to receive the leakage detection signal sent by the detection device 600 and generate corresponding control information; the control information will be described in detail in the fuel leakage management method below.

[0081] The fuel leakage management system further includes a control valve 900; one end of the control valve 900 is connected with a refueling gun 910, and the other end is connected with the oil inlet 140 of the at least one auxiliary fuel tank 100; the control valve 900 is further connected with the control device 700, and is used to control the injection and stop of the fuel.

[0082] Specifically, since the embodiment can be applied to the non-driving state of the fuel-driven system, when the fuel-driven system is a civil aircraft, the non-driving state can at least correspond to the ground stationary state and the ground refueling state, so when the aircraft is in the ground refueling state, the fuel leakage needs to be stopped in time in the case of fuel leakage, and therefore the fuel leakage management system further comprises a control valve 900, one end of the control valve 900 can be connected with the refueling gun 910, and the other end can be connected with the oil inlet 140 of the auxiliary fuel tank 100; at the same time, the control valve 900 can also be in communication connection with the control device 700, so as to be closed in response to the fuel control signal sent by the control device 700, so that the refueling gun 910 stops injecting fuel into the auxiliary fuel tank 100. That is, when the detection device 600 detects that there is fuel leakage in the cavity 130, the detection device 600 sends a leakage detection signal to the control device 700, and after the control device 700 receives the leakage detection signal, a fuel control signal is generated and sent to the control valve 900, so that the control valve 900 changes from the open state to the closed state in response to the fuel control signal, so as to control the refueling gun 910 to stop injecting fuel into the auxiliary fuel tank 100.

[0083] In the embodiment, the gas supply device 500 is arranged so that the fuel-driven system can detect fuel leakage in the auxiliary fuel tank 100 in the non-driving state, thereby improving the scene adaptability and detection universality of the fuel leakage management system; further, since the fuel leakage can be detected during refueling, and the control device 700 and the control valve 900 are in communication connection, after detecting the fuel leakage, the fuel injection can be interrupted in time, avoiding the expansion of leakage, and reducing the invalid refueling time and the maintenance time, which improves the real-time, timeliness and safety of leakage detection, and also saves energy.

[0084] Embodiment two

[0085] In order to expand the scene applicability of the fuel leakage management system described above, so that it can not only be applied to the non-driving state of the fuel-driven system, but also be applied to the driving state of the fuel-driven system (i.e. the flight state of the civil aircraft); Figure 4 A second system architecture diagram corresponding to the fuel leakage management system provided by the embodiment of the application is shown. As shown in Figure 4 When the fuel-driven system is in the driving state, the structures participating in the work in the fuel leakage management system include:

[0086] At least one fuel tank 100, a ventilation pipeline 200, a drainage pipeline 300, a detection device 600 and a control device 700;

[0087] A one-way valve 400 and a gas filter 410;

[0088] The ventilation line 200 further includes a second air inlet 220; the second air inlet 220 is connected to the cabin exhaust port 1 of the fuel drive system;

[0089] The one-way valve 400 is disposed on the connection path between the second air inlet 220 and the cabin exhaust port; the gas filter 410 is disposed between the cabin exhaust port 1 and the one-way valve 400.

[0090] Specifically, the ventilation duct 200 is used to introduce ventilation gas into the compartment 130; the ventilation duct 200 may include at least two air inlets and at least one air outlet, namely a first air inlet 210, a second air inlet 220 and a ventilation outlet 230; the ventilation duct 200 is provided with two air inlets so that the fuel drive system corresponds to different ventilation gas sources in different states; when the fuel drive system is in a driving state, that is, when the civil aircraft is in a flight phase, the second air inlet 220 is connected to the cabin exhaust port 1 of the fuel drive system, and is used to introduce the gas in the cabin into the ventilation duct 200. In the present invention, the fuel drive system can be a civil aircraft, and the passenger cabin can be directly used as the cabin exhaust port 1, that is, during the flight phase of the aircraft, the second air inlet 220 is used to introduce the cabin gas as ventilation gas into the compartment 130.

[0091] In addition, due to the fluidity of gas, in order to ensure that the cabin gas is used as ventilation gas, a one-way valve 400 is provided on the connection path between the second air inlet 220 and the cabin exhaust port 1 in the flow direction of the ventilation duct 200, so that the cabin gas flows through the one-way valve 400 and enters the ventilation duct 200, while ensuring that the gas in the ventilation duct 200 does not flow into the cabin.

[0092] Furthermore, a gas filter 410 may be provided before the one-way valve 400 on the connection path between the second air inlet 220 and the cabin exhaust port 1. This allows the cabin air to be filtered before passing through the one-way valve 400 and entering the ventilation duct 200. This ensures the purity of the gas within the compartment 130, prevents dust and other impurities carried in the cabin air from interfering with and impacting the fuel leakage management system, and ensures the reliability and stability of the fuel leakage management system. In this embodiment, the placement of the gas filter 410 before the one-way valve 400 on the ventilation duct 200 is a preferred embodiment. In actual applications, the placement of the gas filter 410 and the one-way valve 400 on the ventilation duct 200 is not limited. Alternatively, the one-way valve 400 may be provided before the gas filter 410, which can also achieve the same effect of ensuring the purity of the gas within the compartment 130.

[0093] In addition, the fuel leakage management system can further comprise a flow regulating device 800 for adjusting the gas flow of the ventilation gas in the ventilation pipeline 200 and / or the liquid discharge pipeline 300. The flow regulating device 800 can be arranged in at least two positions in the fuel leakage management system, which will be described based on the present embodiment and embodiment three respectively.

[0094] The flow regulating device 800 is arranged on the connection path between the second air inlet 220 and the cabin air outlet 1, and the flow regulating device 800 is connected with the one-way valve 400 and the control device 700 respectively.

[0095] The flow regulating device 800 can have multiple apertures with different sizes, and the flow of the gas in the ventilation pipeline and / or the liquid discharge pipeline can be adjusted by adjusting the apertures with different sizes. Specifically, the flow regulating device 800 can be an adjustable flow limiting aperture with at least two sizes, which can be divided into a first aperture mode and a second aperture mode according to the sizes. The aperture size of the first aperture mode is smaller than that of the second aperture mode.

[0096] The flow regulating device 800 is arranged on the connection path between the second air inlet 220 and the cabin air outlet 1, and can be arranged after the one-way valve 400, that is, the gas filter 410, the one-way valve 400 and the flow regulating device 800 can be arranged in sequence on the connection path, or the one-way valve 400, the gas filter 410 and the flow regulating device 800 can be arranged in sequence, so that the gas flow of the cabin gas entering the ventilation pipeline can be adjusted. At the same time, the flow regulating device 800 can be connected with the control device 700 in communication, so as to switch between the first aperture mode and the second aperture mode in response to the flow control signal sent by the control device 700.

[0097] Figure 5 The working logic diagram of the flow regulating device provided by the embodiment of the present application is shown. As shown in Figure 5As shown, in the initial state, i.e. when the fuel drive system is in the undriven state, i.e. when the aircraft is on the ground, the flow regulating device 800 can be set to the first aperture mode. When the aircraft is driven and ascends, the pressure difference between the inside of the cabin and the outside of the fuselage gradually increases, and at this time the gas flow in the cavity 130 gradually increases. At this time, the flow regulating device 800 in the first aperture mode can reduce the cabin gas entering the cavity 130, thereby reducing the excessive loss of cabin gas. When the detection device 600 detects that there is leaked fuel in the cavity 130 and sends a leakage detection signal to the control device 700, the control device 700 generates a flow control signal for adjusting the aperture mode of the flow regulating device 800, so that the flow regulating device 800 switches from the first aperture mode to the second aperture mode, increases the gas flow, so that more cabin gas enters the cavity 130 as ventilation gas, increases the flow speed of the ventilation gas, thereby accelerating the discharge of the leaked fuel from the cavity 130, avoiding the accumulation of oil gas and / or fuel liquid in the cavity 130, reducing the risk of fuel explosion during the flight of the aircraft, and improving safety.

[0098] Embodiment three

[0099] Figure 6 A third system architecture diagram corresponding to the fuel leakage management system provided by the embodiment of the present application is shown in FIG. 3. Figure 6 As shown, when the fuel drive system is in the driven state, the structures involved in the work of the fuel leakage management system include all the structures in embodiment two, but the position of the flow regulating device 800 is different. The flow regulating device 800 is arranged on the connection path between the liquid discharge gas outlet 320 and the liquid discharge device 2, and the flow regulating device 800 is connected with the control device 700 and the detection device 600 respectively.

[0100] The flow regulating device 800 is arranged on the connection path between the liquid discharge gas outlet 320 and the liquid discharge device 2, and is arranged before the detection device 600, so that by adjusting the aperture mode of the flow regulating device, the gas flow to the detection device 600 is adjusted. At the same time, the flow regulating device 800 can also be in communication connection with the control device 700, so as to switch between the first aperture mode and the second aperture mode in response to the flow control signal sent by the control device 700. In addition, in this embodiment, the flow regulating device 800 is different from the flow regulating device 800 in embodiment three in position setting and connection relationship, and other aspects such as working principle and structure setting are the same as those in embodiment three, and therefore will not be described here.

[0101] From the simulation results of Example 2 and Example 3, it can be seen that the flow regulating device 800 is arranged in at least two positions in the fuel leakage management system, preferably the arrangement of Example 3, in which the flow regulating device 800 is arranged on the connection path between the liquid discharge gas outlet 320 and the liquid discharge device 2. Compared with the position arrangement in Example 2, in addition to reducing the loss of cabin gas, the static pressure inside the cavity 130 is higher, thereby reducing the pressure difference between the inner cavity 110 and the cavity 130, reducing the driving force of fuel leakage from the inner cavity 110 to the cavity 130, and further reducing the risk of fuel leakage.

[0102] The reasons why the structural arrangement of the fuel leakage management system in Example 3 is the preferred scheme will be described below in combination with the simulation results.

[0103] Figures 7-12 The simulation results of the gas flow and static pressure inside the fuel leakage management system cavity under different structural arrangements are shown in the following figures, in which the aircraft is simulated to fly in the cruise phase, the aircraft height is set to 35,000 ft, the cabin pressure is set to 799.7 mbar, and the external pressure of the fuselage is set to 238.4 mbar. Figure 7 The simulation result diagram of the static pressure inside the cavity 130 without arranging the flow regulating device 800 is shown in the following figure. Figure 8 The simulation result diagram of the static pressure inside the cavity 130 with the flow regulating device 800 arranged on the connection path between the second gas inlet 220 and the cabin gas outlet 1 is shown in the following figure. Figure 9 The simulation result diagram of the static pressure inside the cavity 130 with the flow regulating device 800 arranged on the connection path between the liquid discharge gas outlet 320 and the liquid discharge device 2 is shown in the following figure.

[0104] Figure 10 The simulation result diagram of the gas flow inside the cavity 130 without arranging the flow regulating device 800 is shown in the following figure. Figure 11 The simulation result diagram of the gas flow inside the cavity 130 with the flow regulating device 800 arranged on the connection path between the second gas inlet 220 and the cabin gas outlet 1 is shown in the following figure. Figure 12 The simulation result diagram of the gas flow inside the cavity 130 with the flow regulating device 800 arranged on the connection path between the liquid discharge gas outlet 320 and the liquid discharge device 2 is shown in the following figure.

[0105] In the figures, inlet is the cavity gas inlet 131, and outlet is the cavity gas outlet 132, as shown in Figures 7-12As shown, when the flow regulating device 800 is not provided, the pressure of the cavity inlet 131 is 799.1 mbar, the pressure of the cavity outlet 132 is 239.3 mbar, the average static pressure in the cavity 130 is 519.2 mbar, and the gas flow is 6.1 g / s; when the flow regulating device 800 is provided on the connection path between the first inlet 210, the second inlet 220, and the cabin exhaust 1, the pressure of the cavity inlet 131 is 528.6 mbar, the corresponding pressure of the cavity outlet 132 is 238.9 mbar, the average static pressure in the cavity 130 is 383.8 mbar, and the gas flow is 4.4 g / s; when the flow regulating device 800 is provided on the connection path between the liquid discharge outlet 320 and the liquid discharge device 2, the pressure of the cavity inlet 131 is 799.4 mbar, the pressure of the cavity outlet 132 is 573.1 mbar, the average static pressure in the cavity 130 is 686.3 mbar, and the gas flow is 4.4 g / s.

[0106] Therefore, when the flow regulating device 800 is provided on the connection path between the liquid discharge outlet 320 and the liquid discharge device 2, the static pressure inside the cavity 130 is higher, the pressure difference between the inner shell 110 and the cavity 130 can be reduced, the driving force of the fuel leakage from the inner shell 110 to the cavity 130 is reduced, and the risk of fuel leakage is further reduced; the position of the flow regulating device 800 has little effect on the gas flow inside the cavity 130, but can reduce the loss of cabin gas.

[0107] In addition, in Embodiment Two and Embodiment Three, in addition to the structures newly added compared with Embodiment One, for the structures included in Embodiment One, only the structure of the ventilation pipeline is different from that in Embodiment One, and other structures such as the fuel tank 100, the liquid discharge pipeline 300, the gas supply device 500, the detection device 600, the control device 700, and the like are consistent with the structure setting, position setting, connection relationship, and function of the structures in Embodiment One, and thus will not be described here.

[0108] Embodiment Four

[0109] Figure 13 An overall system architecture diagram of another fuel leakage management system provided by an embodiment of the present application is shown; that is, a system architecture diagram of a fuel leakage management system when the number of fuel tanks 100 is 1, as shown in FIG. 6. Figure 13 As shown, the fuel leakage management system can at least include:

[0110] The fuel tank 100, the ventilation pipeline 200, the liquid discharge pipeline 300, the gas supply device 500, the detection device 600, the control device 700, and the control valve 900;

[0111] The one-way valve 400, the gas filter 410, and the flow regulating device 800 can also be included.

[0112] The fuel tank 100 can include a cavity inlet 131 and a cavity outlet 132; the ventilation pipeline 200 can include a first inlet 210, a second inlet 220 and a ventilation outlet 230; the liquid discharge pipeline 300 can include a liquid discharge inlet 310 and a liquid discharge outlet 320;

[0113] The second inlet 220 is connected with the cabin outlet 1, and a gas filter 410 and a one-way valve 400 are sequentially arranged on the connection path; the first inlet 210 is connected with the gas supply device 500; the ventilation outlet 230 is connected with the cavity inlet 131, the cavity outlet 132 is connected with the liquid discharge inlet 310, the liquid discharge outlet 320 is connected with the liquid discharge device 2, and the detection device 600 is arranged on the connection path.

[0114] For each component of the fuel leakage management system, except that the number of fuel tanks and the number of inlets and outlets of the ventilation pipeline and the liquid discharge pipeline are different, the remaining structure, connection relationship, function and working principle are consistent with those in the above-mentioned embodiments, and will not be described here.

[0115] Figure 14 And Figure 15 The fuel leakage management method provided by the embodiments of the present application corresponds to the flowchart respectively; wherein the execution subject can be any electronic device capable of executing the training method, such as terminal, server and the like, wherein the terminal can be a tablet computer, a notebook computer, or a personal computer (PC) and the like. The server can be a single server, or a server cluster composed of multiple servers.

[0116] The fuel leakage management method will be described below based on Figure 14 and Figure 15 in combination with the above-mentioned embodiments. For an aircraft, the fuel leakage detection method is related to its working state, and corresponds to two different detection methods when refueling on the ground and when flying, and the execution subject can be the control device 700.

[0117] Please refer to Figure 14 For an aircraft in the ground refueling stage, a fuel leakage management method can be realized based on the fuel leakage management system of any one of the above-mentioned embodiments, and the method comprises:

[0118] Step S1401: providing the ventilation gas to the first inlet based on the gas supply device, so that the ventilation gas flows to the detection device along the ventilation pipeline, the cavity and the liquid discharge pipeline;

[0119] In one possible embodiment, when the civil aircraft is in the ground phase, the ventilation gas supply device can be manually opened to provide ventilation gas for the cavity, i.e. by opening the ventilation gas supply device to form a gas pressure difference, so that the external gas enters the ventilation pipeline from the first air inlet, flows into the cavity as the ventilation gas, and then flows to the drainage pipeline and the detection device, and flows out from the drainage device.

[0120] Step S1402: determining whether a leakage detection signal is received from the detection device; the leakage detection signal represents the presence of leaked fuel in the cavity;

[0121] When the ventilation gas flows along the ventilation pipeline, the cavity, and the drainage pipeline to the detection device, the detection device detects the ventilation gas to determine whether the ventilation gas carries fuel gas and / or fuel liquid; if the ventilation gas does not carry fuel gas and / or fuel liquid, it means that there is no leaked fuel in the cavity, i.e. there is no fuel leakage; if the ventilation gas carries fuel gas and / or fuel liquid, it means that there is leaked fuel in the cavity, i.e. there is fuel leakage, and a leakage detection signal is generated and sent to the control device.

[0122] Therefore, when the leakage detection signal is received, it can be determined that there is fuel leakage.

[0123] Step S1403: generating a fuel control signal when the leakage detection signal is received;

[0124] In one specific embodiment, if the leakage detection signal is received and the aircraft is in the fuel adding process of the ground phase, a fuel control signal for closing the control valve is generated.

[0125] Step S1404: sending the fuel control signal to the control valve to close the control valve and control the fuel to stop being injected into the fuel tank.

[0126] In one specific embodiment, the fuel control signal is sent to the control valve to close the control valve after receiving the fuel control signal, and the refueling gun is closed to stop the fuel from being injected into the inner shell of the fuel tank.

[0127] Based on the above steps, real-time detection of fuel leakage during refueling can be achieved, and fuel injection can be stopped in the case of fuel leakage to avoid continuous fuel leakage and timely maintenance. At the same time, fuel leakage detection can also be performed when the aircraft is in the ground phase and not refueling, so as to timely maintain and repair the fuel leakage.

[0128] In another embodiment, for an aircraft, there are other control methods for fuel leakage in different working phases; for example, Figure 15For an aircraft in a flight phase, a fuel leak management method can be implemented based on the fuel leak management system described in Embodiment 3 and / or Embodiment 4, and the method comprises:

[0129] Step S1501: providing the ventilation gas to the second air inlet based on the cabin air outlet, so that the ventilation gas flows to the detection device along the ventilation pipeline, the partition cavity and the liquid discharge pipeline;

[0130] In an available embodiment, when the civil aircraft is in a flight phase, the cabin air is introduced through the cabin air outlet to achieve the provision of the ventilation gas to the partition cavity, so that the cabin air enters the ventilation pipeline from the second air inlet, flows into the partition cavity as the ventilation gas, and then flows to the liquid discharge pipeline and the detection device, and flows out from the liquid discharge device.

[0131] Step S1502: determining whether a leak detection signal emitted by the detection device is received; the leak detection signal represents the presence of leaked fuel in the partition cavity;

[0132] Step S1502 has the same working principle as Step S1402, and will not be described here.

[0133] Step S1503: generating a flow control signal in the case where the leak detection signal is received;

[0134] In a specific embodiment, if the leak detection signal is received and the aircraft is in a flight phase, a flow control signal for adjusting the aperture mode of the flow regulating device is generated.

[0135] Step S1504: sending the flow control signal to the flow regulating device, so that the flow regulating device switches the working mode and controls the gas flow of the ventilation gas.

[0136] In a specific embodiment, the flow control signal is sent to the flow regulating device, so that the flow regulating device adjusts from the first aperture mode to the second aperture mode to increase the gas flow in the pipeline after receiving the flow control signal.

[0137] Based on the above steps, when no fuel leak is monitored, the flow regulating device remains in the first aperture mode, ensuring a stable and detectable gas flow through the detection device, which can avoid a large loss of cabin air. At the same time, the flow regulating device is arranged on the connection path between the liquid discharge air outlet and the liquid discharge device, which can reduce the pressure difference between the fuel tank inner shell and the partition cavity, and reduce the risk of fuel leakage to the interlayer.

[0138] The embodiments of the present application also provide a device corresponding to the fuel leak management method, as shown in Figure 16 and Figure 17 ​Figure 16 Fig. 1 is a structural schematic diagram of a fuel leakage management device according to an embodiment of the present application; Figure 16 As shown in Fig. 1, the device comprises:

[0139] a first gas providing module 1610, configured to provide the ventilation gas to the first gas inlet based on the gas supply device, so that the ventilation gas flows to the detection device along the ventilation pipeline, the separation cavity and the liquid discharge pipeline;

[0140] a first judging module 1620, configured to judge whether a leakage detection signal emitted by the detection device is received; the leakage detection signal represents that there is leaked fuel in the separation cavity;

[0141] a first signal generating module 1630, configured to generate a fuel control signal in the case that the leakage detection signal is received;

[0142] a first control module 1640, configured to send the fuel control signal to the control valve, so that the control valve closes the valve and controls fuel to stop being injected into the fuel tank.

[0143] Figure 17 Fig. 2 is a structural schematic diagram of another fuel leakage management device according to an embodiment of the present application; Figure 16 As shown in Fig. 2, the device comprises:

[0144] a second gas providing module 1710, configured to provide the ventilation gas to the second gas inlet based on the cabin exhaust port, so that the ventilation gas flows to the detection device along the ventilation pipeline, the separation cavity and the liquid discharge pipeline;

[0145] a second judging module 1720, configured to judge whether a leakage detection signal emitted by the detection device is received; the leakage detection signal represents that there is leaked fuel in the separation cavity;

[0146] a second signal generating module 1730, configured to generate a flow control signal in the case that the leakage detection signal is received;

[0147] a second control module 1740, configured to send the flow control signal to the flow adjusting device, so that the flow adjusting device switches the working mode and controls the gas flow of the ventilation gas.

[0148] The embodiments of the present application further provide a fuel driving system, which can comprise the fuel leakage management system according to any one of the above embodiments and can execute the fuel leakage management method according to any one of the above embodiments; the fuel driving system can be an aircraft, an aircraft or any system that needs fuel to drive.

[0149] The embodiment of the present application also provides an electronic device, which comprises a processor and a memory, wherein the memory stores at least one instruction, at least one program, a code set or an instruction set, and the at least one instruction, the at least one program, the code set or the instruction set is loaded and executed by the processor to implement the fuel leakage management method according to any one of the method embodiments.

[0150] The embodiment of the present application also provides a storage medium, which can be arranged in a server to save at least one instruction, at least one program, a code set or an instruction set for implementing the method embodiment, and the at least one instruction, the at least one program, the code set or the instruction set is loaded and executed by the processor to implement the fuel leakage management method according to any one of the method embodiments.

[0151] Optionally, in the embodiment of the present application, the storage medium can be located in at least one of a plurality of network servers of a computer network. Optionally, in the embodiment of the present application, the storage medium includes but is not limited to a U disk, a read-only memory (ROM), a random access memory (RAM), a mobile hard disk, a magnetic disk or an optical disk and various storage program codes.

[0152] As can be seen from the above embodiments of the present application, in the present application, the air supply device, the detection device and the control device are added to the fuel leakage management system, wherein the air supply device can provide ventilation gas for the fuel leakage management system when the fuel driving system is not working, so that the fuel driving system can also detect fuel leakage through the detection device during fuel addition, thereby improving the real-time performance and scene adaptability of fuel leakage detection, interrupting fuel addition in the case of fuel leakage, avoiding continuous fuel leakage and timely maintenance; in the working state of the fuel driving system, the detection device detects fuel leakage, and the control device regulates fuel addition and leakage fuel discharge, thereby improving the timeliness of fuel leakage detection and the accuracy of leakage fuel discharge regulation, and further improving the efficiency of fuel discharge, avoiding oil and gas accumulation and reducing the risk that may exist in the driving process of the fuel driving system.

[0153] It is to be understood that the phrases "in one embodiment" or "in another embodiment" as used throughout this detailed description do not refer to the same embodiment; however, such phrasing can refer to a particular embodiment, and thus, they can not necessarily refer to a different embodiment. It will be appreciated that the above description is intended to be illustrative only and not restrictive. Many embodiments will be apparent to those of skill in the art upon reviewing the above description. The scope of the technology should, therefore, be determined not with reference to the above description, but instead should be given with reference to the appended claims, along with their full scope of equivalents.

Claims

1. A fuel leak management system, characterized in that: The fuel leak management system comprises: At least one fuel tank (100), a ventilation pipeline (200), a liquid discharge pipeline (300), an air supply device (500), a detection device (600), and a control device (700); The fuel tank (100) comprises an inner shell (110) and an outer shell (120), wherein a compartment (130) is formed between the outer shell (120) and the inner shell (110); the compartment (130) comprises a compartment air inlet (131) and a compartment air outlet (132); The first air inlet (210) of the ventilation pipeline (200) is connected to the air supply device (500); the ventilation outlet (230) of the ventilation pipeline (200) is connected to the compartment air inlet (131); The at least one fuel tank (100) is connected to the drain air inlet (310) of the drain pipeline (300) via the compartment air outlet (132), and the drain air outlet (320) of the drain pipeline (300) is connected to the drain device (2) of the fuel drive system; The detection device (600) is provided on the connection path between the liquid discharge outlet (320) and the liquid discharge device (2); the detection device (600) is communicatively connected with the control device (700).

2. A fuel leakage management system according to claim 1, characterized in that: The fuel leakage management system further includes a control valve (900); One end of the control valve (900) is connected to the refueling gun (910), and the other end is connected to the fuel inlet (140) of the at least one fuel tank (100); The control valve (900) is also connected to the control device (700) and is used to control the injection and stop of fuel injection.

3. A fuel leakage management system according to claim 1, characterized in that: The at least one fuel tank (100) is plural in number; A connecting channel (150) exists between the plurality of fuel tanks (100), so that fuel can be injected into the other fuel tanks (100) through the fuel inlet (140) of one of the fuel tanks (100).

4. A fuel leakage management system according to claim 1, characterized in that: The fuel leakage management system further includes a one-way valve (400) and a gas filter (410); The ventilation pipeline (200) further comprises a second air inlet (220); the second air inlet (220) is connected to the cabin exhaust port (1) of the fuel drive system; The one-way valve (400) is arranged on the connection path between the second air inlet (220) and the cabin exhaust port (1); and the gas filter (410) is arranged between the cabin exhaust port (1) and the one-way valve (400).

5. A fuel leakage management system according to claim 4, characterized in that: The fuel leakage management system further includes a flow regulating device (800); The flow regulating device (800) is used to adjust the gas flow of the ventilation gas in the ventilation pipeline (200) and / or the drainage pipeline (300).

6. A fuel leakage management system according to claim 5, characterized in that: The flow regulating device (800) is provided on the connection path between the second air inlet (220) and the cabin exhaust port (1), and the flow regulating device (800) is respectively connected to the one-way valve (400) and the control device (700).

7. A fuel leakage management system according to claim 5, characterized in that: The flow regulating device (800) is arranged on the connection path between the liquid discharge outlet (320) and the liquid discharge device (2), and the flow regulating device (800) is respectively connected to the control device (700) and the detection device (600).

8. A fuel leakage management method, applied to the fuel leakage management system according to any one of claims 1 to 3, characterized in that: The method comprises: providing ventilation gas to the first air inlet based on the air supply device, so that the ventilation gas flows along the ventilation pipeline, the compartment and the drainage pipeline to the detection device; determining whether a leakage detection signal from the detection device is received, wherein the leakage detection signal indicates that there is leaked fuel in the compartment; generating a fuel control signal upon receiving the leak detection signal; The fuel control signal is sent to the control valve to close the control valve and control the fuel to stop being injected into the fuel tank.

9. A fuel leakage management method, applied to the fuel leakage management system according to any one of claims 4 to 7; characterized in that: The method comprises: Providing ventilation gas to the second air inlet based on the cabin exhaust port, so that the ventilation gas flows along the ventilation pipeline, the compartment and the drainage pipeline to the detection device; determining whether a leakage detection signal from the detection device is received, wherein the leakage detection signal indicates that there is leaked fuel in the compartment; generating a flow control signal upon receiving the leakage detection signal; The flow control signal is sent to the flow regulating device, so that the flow regulating device switches the working mode and controls the gas flow of the ventilation gas.

10. An aircraft, characterized in that: The aircraft comprises the fuel leakage management system according to any one of claims 1 to 7 and is capable of executing the fuel leakage management method according to any one of claims 8 to 9.

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