Fuel leakage management system, management method and aircraft

Abstract

The invention discloses a fuel leakage management system and method and an aircraft. The management system comprises a fuel tank, a ventilation pipeline, a liquid drainage pipeline, a gas supply device, a detection device and a control device. A separation cavity is formed between the outer shell and the inner shell of the fuel tank; a ventilation air inlet of the ventilation pipeline is connected with an air supply device; a ventilation air outlet of the ventilation pipeline is connected with the separation cavity air inlet; an air outlet of the separation cavity is connected with a liquid discharging air inlet of a liquid discharging pipeline, and a liquid discharging air outlet of the liquid discharging pipeline is connected with a liquid discharging device; a detection device is arranged on a connection path of the liquid discharge gas outlet and the liquid discharge device; the detection device is in communication connection with the control device. By arranging the gas supply device, the detection device and the control device, fuel leakage can be detected and controlled in different working states, the risk of fuel leakage can be reduced, and the safety of the fuel system is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a fuel leakage management system, a management method and an aircraft. Background Art

[0002] The auxiliary fuel tanks of civil aircraft are arranged in the cargo hold of the fuselage. In order to ensure that the accidentally leaked oil gas or oil liquid does not accumulate and increase safety hazards, in the prior art, most of the auxiliary fuel tanks are designed as a sandwich structure, with the inner shell storing fuel, the outer shell as a barrier layer for leaking oil gas or oil liquid, and the compartment between the inner and outer shells as a ventilation channel. A ventilation interface is set on the upper part of each auxiliary fuel tank, and the compartment is ventilated by introducing pressurized gas from the cabin to supply air to the compartment, so as to blow away the oil gas or oil liquid that may leak in the auxiliary fuel tank compartment. However, since the pressurized gas in the cabin is only produced during the flight phase of the aircraft, and the pressure difference increases with the increase of flight altitude, this method still has limitations, that is, this method fails when the aircraft is on the ground. At the same time, this method does not have the functions of real-time leakage monitoring and ventilation control. Summary of the invention

[0003] In view of the above-mentioned defects of the prior art, the technical problem to be solved by the present invention 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 invention discloses a fuel leakage management system, a management method and an aircraft.

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

[0006] At least one fuel tank, ventilation pipeline, drain pipeline, air supply device, detection device and control device;

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

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

[0009] The at least one fuel tank is connected to the drain air inlet of the drain pipeline through the compartment air outlet, and the drain air outlet of the drain pipeline is connected to the drain device of the fuel drive system;

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

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

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

[0013] The control valve is also connected to the control device and is used to control the injection and stop of fuel injection.

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

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

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

[0017] The ventilation pipeline also includes a second air inlet, which is connected to the cabin exhaust port of the fuel drive system;

[0018] The one-way valve is arranged on a connection 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 includes 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 drainage pipeline.

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

[0022] In some possible embodiments, the flow regulating device is disposed on a connection path between the liquid discharge outlet and the liquid discharge device, and the flow regulating device is respectively connected to the control device and the detection device.

[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 as described in any one of the above items, comprising:

[0024] Based on the air supply device providing the ventilation gas to the first air inlet, the ventilation gas flows along the ventilation pipeline, the compartment and the drainage pipeline to the detection device;

[0025] Determining whether a leakage detection signal sent by the detection device is received; the leakage detection signal indicates that there is leaked fuel in the compartment;

[0026] upon receipt of the leak detection signal, generating a fuel control signal;

[0027] 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.

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

[0029] Providing the ventilation gas to the second air inlet based on the cabin exhaust port, so that the ventilation gas flows toward the detection device along the ventilation pipeline, the compartment and the drainage pipeline;

[0030] Determining whether a leakage detection signal sent by the detection device is received; the leakage detection signal indicates that there is leaked fuel in the compartment;

[0031] generating a flow control signal upon receiving the leakage detection signal;

[0032] 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.

[0033] According to a fourth aspect of the present disclosure, an aircraft is provided, the aircraft comprising the fuel leakage management system as described in any one of the above items, and capable of executing the fuel leakage management method as described in any one of the above items.

[0034] The implementation of the present invention has the following beneficial effects:

[0035] In the present invention, an air supply device, a detection device and a control device are added to the fuel leakage management system, wherein the air supply device can provide ventilation gas to 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 the process of adding fuel, thereby improving the real-time and scene adaptability of fuel leakage detection, and interrupting the addition of fuel when a fuel leakage is detected, which can avoid further leakage of fuel and carry out maintenance in time; when the fuel drive system is in a working state, the detection device performs real-time detection of fuel leakage, and the control device regulates the emission of leaked fuel according to the detection result, thereby improving the timeliness of fuel leakage detection and the accuracy of regulating the emission of leaked fuel, thereby improving the efficiency of fuel emission, avoiding oil and gas accumulation, and reducing the possible risks of the fuel drive system during driving. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] In order to more clearly illustrate the technical solution of the present invention, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. 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 creative work.

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

[0038] Figure 2 An overall system architecture diagram 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 by 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] Fig. 9 A third simulation result diagram corresponding to the fuel leakage management system provided by an embodiment of the present invention;

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

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

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

[0049] Fig.13 An overall architecture diagram corresponding to another fuel leakage management system provided by an embodiment of the present invention;

[0050] Fig.14 A schematic diagram of a flow chart corresponding to a fuel leakage management method provided by an embodiment of the present invention;

[0051] Fig.15 A schematic flow chart corresponding to another fuel leakage management method provided by an embodiment of the present invention;

[0052] Fig.16 A schematic structural diagram corresponding to a fuel leakage management device provided in an embodiment of the present invention;

[0053] Fig.17 A structural schematic diagram corresponding to another fuel leakage management device provided in an embodiment of the present invention.

[0054] Among them, the above-mentioned figure marks can correspond respectively: 100-fuel tank, 110-inner shell, 120-outer shell, 130-compartment, 131-compartment air inlet, 132-compartment air outlet, 140-oil inlet, 150-connecting channel, 200-ventilation pipeline, 210-first air inlet, 220-second air inlet, 230-ventilation outlet, 300-drainage pipeline, 310-drainage air inlet, 320-drainage outlet, 400-check valve, 410-gas filter, 500-air supply device, 600-detection device, 700-control device, 800-flow regulating device, 900-control valve, 910-fuel gun, 1-cabin exhaust port, 2-drainage device. DETAILED DESCRIPTION

[0055] The following will be combined with the drawings in the embodiments of this specification to clearly and completely describe the technical solutions in the embodiments of this specification. Obviously, the described embodiments are only part of the embodiments of this specification, not all of the embodiments. Based on the embodiments in this specification, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0056] It should be noted that the terms "first", "second", etc. in the specification and claims of the present invention and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the data used in this way can be interchangeable where appropriate, so that the embodiments of the present invention described herein can be implemented in an order other than those illustrated or described herein. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions, for example, a process, method, system, product, or server that includes a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products, or devices.

[0057] Various exemplary embodiments, features and aspects of the present disclosure will be described in detail below with reference to the accompanying drawings. The same reference numerals in the accompanying drawings represent elements with the same or similar functions. Although various aspects of the embodiments are shown in the accompanying drawings, the drawings are not necessarily drawn to scale unless otherwise specified.

[0058] The word “exemplary” is used exclusively herein to mean “serving as an example, example, or illustration.” Any embodiment described herein as “exemplary” is not necessarily to be construed as preferred or advantageous over other embodiments.

[0059] The term "and / or" herein is only a description of the association relationship of the associated objects, indicating that there may be three relationships. For example, A and / or B can represent: A exists alone, A and B exist at the same time, and B exists alone. In addition, the term "at least one" herein represents any combination of at least two of any one or more of a plurality of. For example, including at least one of A, B, and C can represent 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 following specific embodiments. It should be understood by those skilled in the art that the present disclosure can also be implemented without certain specific details. In some examples, methods, means, components and circuits well known to those skilled in the art are not described in detail in order to highlight the subject matter of the present disclosure.

[0061] The fuel drive system can be any system that uses fuel as a drive source, such as an aircraft, a car, etc. The fuel leakage management system can detect fuel leakage of the fuel drive system under different working conditions. In the embodiment of the present invention, a civil aircraft is taken as a specific fuel drive system, and an auxiliary fuel tank of a civil aircraft is taken as a specific fuel tank for illustration and description. In actual applications, there is no limitation on the fuel drive system and the fuel tank, which can be any fuel drive system that can carry a fuel leakage management system and can execute a fuel leakage management method.

[0062] For civil aircraft, fuel tanks are usually set up to store fuel. The main fuel can be stored in the wing basic fuel tank, and the auxiliary fuel can be stored in the auxiliary fuel tank in the fuselage cargo hold. The auxiliary fuel can be used with the main fuel to increase the aircraft's flight range. According to the requirements for ignition source protection, ventilation and leakage must be carried out in a certain closed area outside the fuel storage area to ensure that the accidentally leaked oil and gas can be carried away by the airflow without accumulation, thereby reducing the possibility of fuel tank explosion and reducing the danger of explosion. Usually, the typical architecture of the auxiliary fuel tank ventilation and leakage system is as follows: Figure 1 As shown, the auxiliary fuel tank is usually designed as a double-layer structure, with a compartment formed between the inner wall and the outer wall of the tank. A ventilation interface is provided on the upper part of each auxiliary fuel tank, and the compartment is forced to be ventilated by the cabin air conditioning system bleed air to blow away the oil gas or oil liquid that may be generated in the auxiliary fuel tank compartment. A discharge pipeline is provided at the bottom of each auxiliary fuel tank, and after purging, the oil gas or oil liquid generated in the auxiliary fuel tank compartment is discharged to a safe area outside the aircraft through a drain rod.

[0063] but Figure 1 The solution shown does not have the ability to regulate the gas introduced into the cabin. It can only mechanically introduce the gas in the cabin into the compartment between the inner and outer walls of the auxiliary fuel tank, and use the pressure difference between the cabin and the environment outside the aircraft during flight to provide pressure difference power to purge the compartment. However, when the aircraft is in the cruising stage, the above pressure difference is large, which will cause a large amount of cabin gas to leak out through the compartment. At the same time, under the solution of the prior art, when the aircraft is on the ground, it is impossible to monitor the leakage in real time during the process of adding fuel, which will cause the leakage to expand and aggravate the damage to the fuel tank.

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

[0065] Figure 2 FIG. 2 shows an overall system architecture diagram corresponding to a fuel leakage management system provided by an embodiment of the present invention; Figure 2As shown, the fuel leakage management system may include: a fuel tank 100, a ventilation line 200, a drain line 300, a one-way valve 400, a gas filter 410, an air supply device 500, a detection device 600, a control device 700, a flow regulating device 800, and a control valve 900; in addition, when the fuel drive system is in a refueling state, the fuel leakage management system may also include a refueling gun 910; based on Figure 2 The structure in the embodiment can execute different fuel leakage management methods when the fuel drive system corresponds to different working states. The following will be described in conjunction with specific embodiments.

[0066] Embodiment 1

[0067] Figure 3 FIG. 4 shows a first system architecture diagram corresponding to a fuel leakage management system provided by an embodiment of the present invention; Figure 3 As shown, when the fuel drive system is in a non-driving state, a structure involved in the work of a fuel leakage management system may at least include:

[0068] At least one fuel tank 100, a ventilation line 200, a drain line 300, an air supply device 500, a detection device 600 and a control device 700;

[0069] The at least one 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;

[0070] The fuel tank 100 includes an inner shell 110 and an outer shell 120. The inner shell 110 is used to contain fuel, which can be liquid fuel or other fuel that can provide driving force for the fuel drive system. The fuel tank is used to store fuel and can be any fuel storage container with the same structure as the fuel tank in the present invention. The outer shell 120 is used to isolate the leakage to prevent the leakage from spreading further. A compartment 130 is formed between the inner shell 110 and the outer shell 120. The compartment 130 can contain the fuel leaked from the inner shell 110 and discharge the leaked fuel through its connection relationship. The leaked fuel can be in liquid form or in gaseous form due to changes in air pressure, temperature, etc. Any embodiment of the present invention does not limit the form of the leaked fuel.

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

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

[0073] like Figure 3 As shown, a connecting channel 150 is provided between the multiple auxiliary fuel tanks 100, and the fuel flows between the multiple auxiliary fuel tanks 100 through the connecting channel 150, and then the injection and stop injection of fuel in the multiple auxiliary fuel tanks 100 can be controlled through an oil inlet 140, which improves 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 system internal space.

[0074] The first air inlet 210 of the ventilation pipeline 200 is connected to the air supply device 500; the ventilation air 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 air inlet 310 of the drain pipeline 300 through 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;

[0076] Specifically, the ventilation pipeline 200 is used to introduce ventilation gas into the compartment 130; the ventilation pipeline 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 pipeline 200 is connected to the air supply device 500, and is used to perform pressurized air bleed when the civil aircraft or other fuel drive system is in a non-driving state, and introduce the external gas as ventilation gas into the ventilation pipeline 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 pipeline 200 needs to be adaptively adjusted according to the changes of the fuel tank 100, and it can be understood that the number of ventilation outlets 230 is equal to the number of fuel tanks 100. In this embodiment, the number of fuel tanks 100 is 2, and 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 pressurize the external gas into the ventilation pipeline 200 as ventilation gas and enter the compartment 130.

[0078] The drain line 300 is used to discharge the leaked fuel along with the ventilation gas from the compartment 130 of the fuel tank 100; the drain line 300 may include at least one liquid inlet and at least one liquid outlet, namely, a drain inlet 310 and a drain outlet 320; since the drain inlet 310 is connected to the compartment outlet 132 and is used to discharge the ventilation gas carrying the leaked fuel from the compartment 130, the number of the drain inlet 310 in the drain line 300 needs to be adaptively adjusted according to the changes in the fuel tank 100, and it can be understood that the number of the drain inlet 310 is equal to The number of fuel tanks 100; in the present embodiment, the number of fuel tanks 100 is 2, and the number of drain inlets 310 is also 2; the drain outlet 320 is connected to the drain device 2 of the fuel drive system, and the drain device 2 can be an aircraft drain rod, or any device in other fuel drive systems for discharging leaked fuel from the drive system, and the ventilation gas carries the leaked fuel gas or liquid, and flows from the compartment 130 along the drain pipeline 300 to the drain device 2, and then is discharged outside the aircraft, so as to improve the safety of the aircraft and reduce the risk of combustion and explosion due to fuel leakage.

[0079] The detection device 600 is disposed on the connection path between the liquid discharge outlet 320 and the liquid discharge device 2 ; the detection device 600 and the control device 700 are in communication connection with each other.

[0080] The detection device 600 can be applied to any state of the fuel drive system, that is, it can detect fuel leakage at any time; the detection device 600 is set on the connection path between the liquid discharge outlet 320 and the liquid discharge device 2, which not only ensures that the leaked fuel can be discharged 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 that can detect fuel leakage. At the same time, the detection device 600 is connected to the control device 700 in communication, 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 also 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 auxiliary fuel tank 100; the control valve 900 is also connected to the control device 700 for controlling the injection and stopping of fuel injection.

[0082] Specifically, since the present embodiment can be applied to the non-driving state of the fuel drive system, when the fuel drive system is a civil aircraft, the non-driving state can at least correspond to the ground stationary state and the ground refueling state. Therefore, when the aircraft is in the ground refueling state, in the event of fuel leakage, refueling needs to be stopped in time. Therefore, the fuel leakage management system also includes a control valve 900, one end of the control valve 900 can be connected to the refueling gun 910, and the other end can be connected to the fuel inlet 140 of the auxiliary fuel tank 100; at the same time, the control valve 900 can also be connected to the control device 700 for communication, so as to shut down 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 a fuel leakage in the cavity 130, the detection device 600 sends a leakage detection signal to the control device 700. After receiving the leakage detection signal, the control device 700 generates a fuel control signal and sends the fuel control signal to the control valve 900, so that the control valve 900 changes from an open state to a closed state in response to the fuel control signal, thereby controlling the refueling gun 910 to stop injecting fuel into the auxiliary fuel tank 100.

[0083] In this embodiment, the provision of the air supply device 500 enables the fuel drive system to detect fuel leakage in the auxiliary fuel tank 100 even when it is not driven, thereby improving the scenario adaptability and detection breadth of the fuel leakage management system; further, since fuel leakage can be detected during the refueling process, and the control device 700 is provided to communicate with the control valve 900, after the fuel leakage is detected, the fuel injection can be interrupted in time to avoid the leakage from expanding, while reducing the invalid refueling time and maintenance time, which not only improves the real-time, timeliness and safety of the leakage detection, but also achieves energy saving.

[0084] Embodiment 2

[0085] In order to expand the scenario applicability of the above-mentioned fuel leakage management system so that it can be applied not only to the non-driving state of the fuel drive system, but also to the driving state of the fuel drive system (i.e. the flight state of a civil aircraft); Figure 4 FIG. 2 shows a second system architecture diagram corresponding to a fuel leakage management system provided by an embodiment of the present invention; Figure 4 As shown, when the fuel drive system is in the driving state, the structures involved in the work in the fuel leakage management system include:

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

[0087] One-way valve 400 and gas filter 410;

[0088] The ventilation pipeline 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 a 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 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, on the connection path between the second air inlet 220 and the cabin exhaust port 1, a gas filter 410 can be arranged before the one-way valve 400, so that the cabin gas can enter the ventilation duct 200 after filtering through the one-way valve 400, thereby ensuring the purity of the gas in the compartment 130, avoiding the interference and influence of dust and other impurities carried in the cabin gas on the fuel leakage management system, and ensuring the reliability and stability of the fuel leakage management system. In this embodiment, on the path of the ventilation duct 200, the gas filter 410 is arranged first and then the one-way valve 400 is arranged. This position setting is a preferred implementation. In actual application, there is no limitation on the position setting of the gas filter 410 and the one-way valve 400 on the path of the ventilation duct 200. The one-way valve 400 can also be arranged first and then the gas filter 410, which can also achieve the effect of ensuring the purity of the gas in the compartment 130.

[0093] In addition, the fuel leakage management system may further include a flow regulating device 800, which is used to adjust the gas flow of the ventilation gas in the ventilation pipeline 200 and / or the drain pipeline 300. The setting of the flow regulating device 800 in the fuel leakage management system may include at least two positional relationships, which will be explained based on this embodiment and embodiment 3 respectively.

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

[0095] The flow regulating device 800 may have multiple apertures of different sizes, and the flow of gas in the ventilation duct and / or the drainage duct may be regulated by adjusting the apertures of different sizes; specifically, the flow regulating device 800 may be an adjustable flow limiting hole with at least two aperture sizes, which may be divided into a first aperture mode and a second aperture mode according to different sizes, and the aperture size of the first aperture mode is smaller than the aperture size 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 exhaust port 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 duct can be adjusted; at the same time, the flow regulating device 800 can be communicated with the control device 700 to switch between the first aperture mode and the second aperture mode in response to the flow control signal issued by the control device 700.

[0097] Figure 5 The working logic diagram of the flow regulating device provided by the embodiment of the present invention is shown; Figure 5As shown, in the initial state, that is, the fuel drive system is in an undriven state, that is, 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 the altitude rises, the pressure difference between the interior of the cabin and the exterior of the fuselage gradually increases. At this time, the gas flow inside the compartment 130 gradually increases. At this time, the flow regulating device 800 is in the first aperture mode, which can reduce the cabin gas from entering the compartment 130, thereby reducing the excessive loss of the cabin gas. When the detection device 600 detects that there is a fuel leak in the compartment 130, , and sends a leakage detection signal to the control device 700, the control device 700 will generate 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, increasing the gas flow rate, so that more cabin gas enters the compartment 130 as ventilation gas, and the flow speed of the ventilation gas is increased, thereby accelerating the discharge of the leaked fuel from the compartment 130, avoiding the accumulation of oil gas and / or fuel liquid in the compartment 130, reducing the risk of combustion and explosion during the flight of the aircraft, and improving safety.

[0098] Embodiment 3

[0099] Figure 6 A third system architecture diagram corresponding to a fuel leakage management system provided by an embodiment of the present invention is shown, such as Figure 6 As shown, when the fuel drive system is in the driving state, the structures involved in the work in the fuel leakage management system include all the structures in Example 2, but there is a difference in the position setting of the flow regulating device 800. The flow regulating device 800 is arranged on the connection path between the drain outlet 320 and the drain device 2, and the flow regulating device 800 is respectively connected to the control device 700 and the detection device 600.

[0100] The flow regulating device 800 is arranged on the connection path between the liquid discharge outlet 320 and the liquid discharge device 2, and is arranged before the detection device 600, so that the gas flow to the detection device 600 can be adjusted by adjusting the aperture mode of the flow regulating device; at the same time, the flow regulating device 800 can also be connected to the control device 700 for 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. In addition, in this embodiment, except for the different position setting and connection relationship, the flow regulating device 800 is the same as that in the third embodiment in other aspects such as the working principle and structural setting, so it is not repeated here.

[0101] It can be known from the second and third embodiments that the flow regulating device 800 is set in at least two positions in the fuel leakage management system, and the setting method of the third embodiment is preferred. In the third embodiment, the flow regulating device 800 is set on the connection path between the drain outlet 320 and the drain device 2. Compared with the position setting in the second embodiment, in addition to reducing the cabin gas loss, the static pressure inside the cavity 130 is higher, thereby reducing the pressure difference between the inside of the inner shell 110 and the cavity 130, reducing the driving force for the fuel in the inner shell 110 to leak into the cavity 130, and further reducing the risk of fuel leakage.

[0102] The following is an explanation of the reasons why the structure of the fuel leakage management system in the third embodiment is set as the preferred solution in combination with multiple simulation results.

[0103] Figure 7-12 The simulation results of the calculation of the gas flow and static pressure inside the fuel leakage management system compartment under different structural settings, simulating the aircraft's flight cruising phase and setting the aircraft altitude to 35,000 feet, the cabin pressure to 799.7 mbar, and the fuselage external pressure to 238.4 mbar; Figure 7 It is a schematic diagram of simulation results of calculating the static pressure inside the compartment 130 without setting the flow regulating device 800; Figure 8 A schematic diagram of simulation results of calculating the static pressure inside the compartment 130 in order to arrange the flow regulating device 800 on the connection path between the second air inlet 220 and the cabin exhaust port 1; Fig. 9 A schematic diagram of simulation results of calculating the static pressure inside the compartment 130 in order to dispose the flow regulating device 800 on the connection path between the liquid discharge outlet 320 and the liquid discharge device 2 .

[0104] Fig.10 It is a schematic diagram of simulation results of calculating the gas flow inside the compartment 130 without setting the flow regulating device 800; Fig.11 A schematic diagram of simulation results of calculating the gas flow inside the compartment 130 in order to arrange the flow regulating device 800 on the connection path between the second air inlet 220 and the cabin exhaust port 1; Fig.12 A schematic diagram of simulation results of calculating the gas flow rate inside the compartment 130 in order to dispose the flow regulating device 800 on the connection path between the liquid discharge outlet 320 and the liquid discharge device 2 .

[0105] In the figure, inlet is the air inlet 131 of the compartment, and outlet is the air outlet 132 of the compartment. Figure 7-12As shown in the figure, when the flow regulating device 800 is not provided, the pressure at the air inlet 131 of the compartment is 799.1 mbar, the pressure at the air outlet 132 of the compartment is 239.3 mbar, the average static pressure in the compartment 130 is 519.2 mbar, and the gas flow rate is 6.1 g / s; when the flow regulating device 800 is provided on the connection path between the first air inlet 210, the second air inlet 220 and the cabin exhaust port 1, the pressure at the air inlet 131 of the compartment is 528.6 mbar, and the air outlet 132 of the compartment is 239.3 mbar. The average static pressure in the compartment 130 is 519.2 mbar, and the gas flow rate is 6.1 g / s. The pressure corresponding to port 132 is 238.9 mbar, the average static pressure in the compartment 130 is 383.8 mbar, and the gas flow rate is 4.4 g / s; when the flow regulating device 800 is set on the connection path between the drainage outlet 320 and the drainage device 2, the pressure of the compartment air inlet 131 is 799.4 mbar, the pressure of the compartment air outlet 132 is 573.1 mbar, the average static pressure in the compartment 130 is 686.3 mbar, and the gas flow rate is 4.4 g / s.

[0106] It can be concluded that: the flow regulating device 800 is arranged on the connection path between the drain outlet 320 and the drain device 2, and the static pressure inside the compartment 130 is higher, which can reduce the pressure difference between the inner shell 110 and the compartment 130, and reduce the driving force for the fuel in the inner shell 110 to leak into the compartment 130, thereby reducing the risk of fuel leakage; the position setting of the flow regulating device 800 has little effect on the gas flow inside the compartment 130, but can reduce the cabin gas loss.

[0107] In addition, in Example 2 and Example 3, except for the newly added structure compared to Example 1, for the various structures included in Example 1, only the structure of the ventilation pipeline is different from that of the ventilation pipeline in Example 1, and other structures such as the fuel tank 100, the drain pipeline 300, the air supply device 500, the detection device 600, the control device 700 and other structures are consistent with the structural settings, position settings, connection relationships and functions in Example 1, so they are not repeated here.

[0108] Embodiment 4

[0109] Fig.13 FIG. 2 shows an overall system architecture diagram corresponding to another fuel leakage management system provided by an embodiment of the present invention; that is, a system architecture diagram corresponding to a fuel leakage management system when the number of fuel tanks 100 is 1, as shown in FIG. Fig.13 As shown, the fuel leak management system may include at least:

[0110] A fuel tank 100, a ventilation line 200, a drain line 300, an air supply device 500, a detection device 600, a control device 700, and a control valve 900;

[0111] It may also include a one-way valve 400, a gas filter 410, and a flow regulating device 800;

[0112] The fuel tank 100 may include a compartment air inlet 131 and a compartment air outlet 132; the ventilation line 200 may include a first air inlet 210, a second air inlet 220 and a ventilation air outlet 230; the drain line 300 may include a drain air inlet 310 and a drain air outlet 320;

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

[0114] For each component in the fuel leakage management system, except for the number of fuel tanks and the number of inlets and outlets of the ventilation pipes and the drain pipes, the rest of the structure, connection relationship, function, and working principle are consistent with those in the above embodiment and will not be repeated here.

[0115] Fig.14 as well as Fig.15 Flow charts corresponding to the fuel leakage management methods provided in the embodiments of the present invention; wherein the execution subjects can be any electronic devices capable of executing the training method, such as terminals, servers and other devices, wherein the terminals can be tablet computers, laptop computers, or personal computers (PCs) and other devices. The server can be a single server or a server cluster consisting of multiple servers.

[0116] The following will be based on Fig.14 and Fig.15 For an aircraft, the detection method of fuel leakage is related to its working state. There are two different detection methods corresponding to ground refueling and flight, and the execution subject can be the control device 700.

[0117] See also Fig.14 For an aircraft in the ground refueling stage, a fuel leakage management method can be implemented based on the fuel leakage management system described in any of the above embodiments, and the method includes:

[0118] Step S1401: providing the 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;

[0119] In a feasible embodiment, when the civil aircraft is in the ground stage, the air supply device can be manually opened to provide ventilation gas to the compartment, that is, by opening the air supply device to form a gas pressure difference, the outside gas enters the ventilation duct from the first air inlet, flows into the compartment as ventilation gas, and then flows to the drainage duct and the detection device, and flows out from the drainage device.

[0120] Step S1402: determining whether a leakage detection signal sent by the detection device is received; the leakage detection signal indicates that there is leaked fuel in the compartment;

[0121] When the ventilation gas flows along the ventilation pipe, the compartment and the drain pipe to the detection device, the detection device will detect 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 compartment, that is, 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 compartment, that is, there is a fuel leakage, and a leakage detection signal is generated at this time, and the leakage detection signal is sent to the control device.

[0122] Therefore, when a leak detection signal is received, it can be determined that a fuel leak exists.

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

[0124] In a specific embodiment, if a leak detection signal is received and the aircraft is in a refueling process during a 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 a specific embodiment, a fuel control signal is sent to the control valve, so that the control valve is shut off after receiving the fuel control signal, and the fuel gun is closed, so that the fuel stops being injected into the inner shell of the fuel tank.

[0127] Based on the above steps, real-time detection of fuel leakage during the refueling process can be achieved, and fuel injection can be stopped in time in the event of fuel leakage to prevent further fuel leakage and to perform timely maintenance. At the same time, if the aircraft is on the ground and not refueled, fuel leakage detection can also be performed so that fuel leakage can be repaired and maintained in time.

[0128] In another embodiment, for an aircraft, there are other control methods for fuel leakage at different operating stages; Fig.15For an aircraft in a flight phase, a fuel leakage management method can be implemented based on the fuel leakage management system described in the above-mentioned embodiment 3 and / or embodiment 4, and the method includes:

[0129] Step S1501: providing the ventilation gas to the second air inlet based on the cabin exhaust port, so that the ventilation gas flows toward the detection device along the ventilation pipeline, the compartment and the drainage pipeline;

[0130] In a feasible embodiment, when the civil aircraft is in the flight phase, cabin gas is introduced through the cabin exhaust port to provide ventilation gas for the compartment, so that the cabin gas enters the ventilation duct from the second air inlet, flows into the compartment as ventilation gas, and then flows to the drainage duct and the detection device, and flows out from the drainage device.

[0131] Step S1502: determining whether a leakage detection signal sent by the detection device is received; the leakage detection signal indicates that there is leaked fuel in the compartment;

[0132] The working principle of step S1502 is consistent with that of step S1402 and will not be repeated here.

[0133] Step S1503: generating a flow control signal when the leakage detection signal is received;

[0134] In a specific embodiment, if a leak detection signal is received and the aircraft is in a flight phase, a flow control signal for adjusting an 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, a flow control signal is sent to the flow regulating device, so that after receiving the flow control signal, the flow regulating device is adjusted from the first aperture mode to the second aperture mode to increase the gas flow in the pipeline.

[0137] Based on the above steps, when no fuel leakage is detected, the flow regulating device is maintained in the first aperture mode, ensuring a stable and detectable airflow flowing through the detection device, thereby avoiding a large loss of cabin gas; at the same time, the flow regulating device is arranged on the connection path between the drain outlet and the drain device, which can reduce the pressure difference between the inner shell and the compartment of the fuel tank, thereby reducing the risk of fuel leakage to the interlayer;

[0138] The embodiment of the present invention also provides a device corresponding to the fuel leakage management method, such as Fig.16 as well as Fig.17 As shown, Fig.16 is a structural schematic diagram corresponding to a fuel leakage management device, such as Fig.16 As shown, 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 along the ventilation pipeline, the compartment and the drainage pipeline to the detection device;

[0140] The first judgment module 1620 is used to judge whether a leakage detection signal sent by the detection device is received; the leakage detection signal indicates that there is leaked fuel in the compartment;

[0141] A first signal generating module 1630, configured to generate a fuel control signal upon receiving the leakage detection signal;

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

[0143] Fig.17 is a structural schematic diagram corresponding to another fuel leakage management device, such as Fig.16 As shown, the device comprises:

[0144] A second gas supply module 1710 is used to supply the 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;

[0145] The second judgment module 1720 is used to judge whether a leakage detection signal sent by the detection device is received; the leakage detection signal indicates that there is leaked fuel in the compartment;

[0146] A second signal generating module 1730 is used to generate a flow control signal when receiving the leakage detection signal;

[0147] The second control module 1740 is used to send 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.

[0148] An embodiment of the present invention also provides a fuel drive system, which may include a fuel leakage management system as described in any of the above embodiments, and can execute a fuel leakage management method as described in any of the above embodiments; the fuel drive system may be an aircraft, an aircraft, or any other system that requires fuel to drive.

[0149] An embodiment of the present invention also provides an electronic device, comprising: 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 a fuel leakage management method as described in any one of the method embodiments.

[0150] An embodiment of the present invention also provides a storage medium, which can be set in a server to store at least one instruction, at least one program, code set or instruction set used to implement the method embodiment. The at least one instruction, the at least one program, the code set or instruction set is loaded and executed by the processor to implement the fuel leakage management method as described in any one of the method embodiments.

[0151] Optionally, in an embodiment of the present invention, the above-mentioned storage medium may be located in at least one of a plurality of network servers of a computer network. Optionally, in an embodiment of the present invention, the above-mentioned storage medium includes, but is not limited to, various media that can store program codes, such as a USB flash drive, a read-only memory (ROM), a random access memory (RAM), a mobile hard disk, a magnetic disk or an optical disk.

[0152] It can be seen from the embodiments provided by the present invention that in the present invention, an air supply device, a detection device and a control device are added to the fuel leakage management system, wherein the air supply device can provide ventilation gas to 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 the process of adding fuel, thereby improving the real-time and scene adaptability of fuel leakage detection, and interrupting the addition of fuel in the event of fuel leakage can avoid continued leakage of fuel and carry out maintenance in time; when the fuel drive system is in a working state, the detection device performs fuel leakage detection, and the control device regulates the addition of fuel and the emission of leaked fuel, thereby improving the timeliness of fuel leakage detection and the accuracy of regulating the emission of leaked fuel, thereby improving the efficiency of fuel emission, avoiding oil and gas accumulation, and reducing the risks that may exist in the fuel drive system during driving.

[0153] It should be noted that various embodiments of the present disclosure have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes are obvious to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments. The choice of terms used in this article is intended to best explain the principles of the embodiments, practical applications, or technical improvements in the market, or to enable other ordinary skill in the art to understand the embodiments disclosed herein.

Claims

1. A fuel leakage management system, characterized in that: The fuel leak management system comprises: At least one fuel tank (100), a ventilation pipeline (200), a drain 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); 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 air 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 leak 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 a 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 comprises 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 arranged 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: Based on the air supply device providing ventilation gas to the first air inlet, the ventilation gas flows along the ventilation pipeline, the compartment and the drainage pipeline to the detection device; Determining whether a leakage detection signal sent by the detection device is received; the leakage detection signal indicates that there is leaked fuel in the compartment; upon receipt of the leak detection signal, generating a fuel control 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 sent by the detection device is received; 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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