Integrated design of a lightweight fuel transfer system and method for a seaplane

Abstract

The present application belongs to the field of aircraft fuel system, and relates to a kind of integrated design light weight fuel transfer system and method of seaplane. Including Ⅰ, Ⅱ, Ⅲ, Ⅳ, Ⅴ, Ⅵ oil tank on the wing of the aircraft, pressure refueling connector, pressure refueling control valve, oil level controller, pressure refueling control panel, oil pump, low oil level signal. One oil pump integrates the flow of oil transfer system and the flow of emergency oil discharge system two working states, maximally reduces the number of pump;Pressure refueling pipeline, oil transfer pipeline, emergency oil discharge pipeline are integrated designed, reduce the number of pipeline;Thirdly, the low oil level signal of oil tank and the low oil level signal of oil quantity measuring system are shared designed during oil transfer and emergency oil discharge, the on-off control of oil transfer system and the on-off control of pressure refueling are shared designed, the on and off of oil transfer are controlled by pressure refueling control valve, reduce the setting of oil transfer cut-off valve.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of aircraft fuel system, and relates to a water aircraft integrated design lightweight fuel transmission system and method. BACKGROUND

[0002] The aircraft fuel system is an important part of the aircraft, and the fuel system has the functions of rapid fuel filling, adjustment of the center of gravity of the aircraft, and rapid fuel discharge for rapidly reducing the weight of the aircraft, etc. The pressure fuel filling system, the fuel conveying system and the emergency fuel discharge system are the key to realizing the above functions. For the water aircraft, in order to improve the wave resistance of water take-off and landing, the center of gravity of the aircraft is usually reduced by adopting measures such as arranging the fuselage fuel tank and controlling the order of fuel consumption, and at the same time, in order to reduce the structural load of water take-off and landing, the system weight of the water aircraft should be strictly controlled. At this time, how to design a lightweight fuel system while achieving the functions of rapid fuel filling, reliable fuel conveying and center of gravity adjustment, and rapid fuel discharge and minimizing the system weight is the key to the design of the aircraft fuel system. SUMMARY

[0003] The purpose of the application is to provide a water aircraft integrated design lightweight fuel transmission system and method. The single-path transmission system can realize the functions of fuel filling, fuel conveying and fuel discharge.

[0004] The technical scheme of the application is as follows:

[0005] A water aircraft integrated design lightweight fuel transmission system, comprising No. 1 fuel tank, No. 2 fuel tank, No. 3 fuel tank, No. 4 fuel tank, No. 5 fuel tank on the wings of the aircraft, No. 6 fuel tank on the fuselage, pressure fuel filling connector, pressure fuel filling control valve, oil level controller, pressure fuel filling control panel, fuel conveying pump, low oil level signal device, and pipeline.

[0006] The No. 1 fuel tank, the No. 2 fuel tank, the No. 3 fuel tank and the No. 4 fuel tank are symmetrically arranged on both sides of the wings, the No. 1 fuel tank is symmetrical with the No. 4 fuel tank, the No. 2 fuel tank is symmetrical with the No. 3 fuel tank, and the No. 5 fuel tank is a central wing fuel tank; the No. 6 fuel tank is a fuselage fuel tank and is located at a low position in the middle of the fuselage, and the purpose of arranging the fuel tank is to reduce the center of gravity of the aircraft;

[0007] The inner side compartment of the No. 1 fuel tank, the No. 2 fuel tank, the No. 3 fuel tank and the No. 4 fuel tank is a collection tank (direct fuel supply tank), and the outer side compartment is a storage tank, the inner side compartment contains a low oil level signal device, and the outer side compartment contains a pressure fuel filling control valve and an oil level controller;

[0008] The No. 5 fuel tank and the No. 6 fuel tank respectively contain a pressure fuel filling control valve, an oil level controller, a fuel conveying pump and a low oil level signal device;

[0009] The pipeline is connected with a pressure refueling connector at one end and connected with pressure refueling control valves in No. I tank, No. II tank, No. III tank, No. IV tank, No. V tank, No. VI tank at the other end; an oil pump is arranged on the pipeline in No. V tank and No. VI tank;

[0010] The pressure refueling control panel is a control and indication device of the pressure refueling system, which receives oil amount signals of No. I / II / III / IV / V / VI tanks, high oil surface signals of oil surface controllers and valve position signals of pressure refueling control valves, automatically controls the work of the pressure refueling control valves and indicates the working state of the pressure refueling control valves through the pressure refueling control panel;

[0011] Further, the oil pump has two working modes, i.e. oil delivery mode and emergency oil discharge mode, and the oil pump outlet flow / pressure state of the two modes is different;

[0012] The aircraft wing is a single wing.

[0013] Further, the emergency oil discharge valve is arranged on the pipeline in the compartment outside No. I tank / No. IV tank;

[0014] Further, the emergency oil discharge port is arranged on the rear edge of the wing and connected with the emergency oil discharge valve in No. I tank / No. IV tank;

[0015] Further, the oil delivery and emergency oil discharge control panel is a control and indication device of the oil delivery system and the emergency oil discharge system, which receives valve position signals of pressure refueling control valves in No. I / II / III / IV tanks, working state signals of oil pumps in No. V / VI tanks, valve position signals of emergency oil discharge valves and high oil surface signals of oil surface controllers in No. I / II / III / IV tanks, and manually controls the work of the pressure refueling control valves, the oil pumps and the emergency oil discharge valves in No. I / II / III / IV tanks through the pressure refueling control valve switch, the oil pump switch and the emergency oil discharge valve switch on the oil delivery and emergency oil discharge control panel and indicates the working state of the pressure refueling control valves, the oil pumps and the emergency oil discharge valves;

[0016] Further, the oil pump is two, which belongs to a dual-redundancy control design.

[0017] A kind of integrated design light weight fuel delivery method of seaplane, including pressure refueling method, oil delivery method and emergency oil discharge method;

[0018] The pressure refueling method specifically includes:

[0019] The aircraft will be refueled according to the task needs before flight, and the conventional sequence of fueling is No. 1, No. 2, No. 3, No. 4, No. 5 and No. 6 fuel tanks, and the sequence of fueling is No. 1, No. 2, No. 3, No. 4, No. 6 and No. 5 fuel tanks when water take-off and landing is needed to be performed;

[0020] During the pressure fueling process, the pressure fueling connector is connected with the pressure fueling vehicle or other ground pressure fueling device, the maintenance personnel sets the fueling amount through the pressure fueling control panel, the pressure fueling control panel automatically controls the pressure fueling control valves of No. 1, No. 2, No. 3, No. 4, No. 5 and No. 6 fuel tanks to be connected, at this time, the fuel of the pressure fueling vehicle or other ground pressure fueling device flows through the pressure fueling control valves of No. 1, No. 2, No. 3, No. 4, No. 5 and No. 6 fuel tanks through the pipeline and then enters the bottom of each fuel tank, when the fuel amount of the fuel tank reaches the preset fueling amount, the pressure fueling control panel automatically controls the pressure fueling control valves of the corresponding fuel tank to be cut off;

[0021] If the pressure fueling control panel does not control the pressure fueling control valves to be cut off, when the liquid surface of No. 1, No. 2, No. 3, No. 4, No. 5 and No. 6 fuel tanks reaches the control oil surface of the oil surface controller, the oil surface controller sends a high oil surface signal, after receiving the signal, the pressure fueling control panel automatically controls the pressure fueling control valves to be cut off, and the fueling is completed when all the pressure fueling control valves are cut off.

[0022] The oil delivery method is specifically as follows:

[0023] During flight, the fuel consumption sequence is the outer compartments of No. 1, No. 2, No. 3 and No. 4 fuel tanks → No. 5 and No. 6 fuel tanks → the inner compartments of No. 1, No. 2, No. 3 and No. 4 fuel tanks;

[0024] When the fuel amount of No. 1, No. 2, No. 3 and No. 4 fuel tanks is low, including the fuel amount being low or the low oil surface signal of the low oil surface signaler, the crew receives the information and judges the oil delivery tank of No. 5 and No. 6 fuel tanks according to the fuel amount of No. 5 and No. 6 fuel tanks and the control demand of the aircraft center of gravity, when the aircraft center of gravity needs to be lowered, the fuel of No. 5 fuel tank is delivered first, and vice versa, the fuel of No. 6 fuel tank is delivered first;

[0025] After the oil delivery tank of No. 5 and No. 6 fuel tanks is determined, the crew controls the pressure fueling control valves of No. 1, No. 2, No. 3 and No. 4 fuel tanks to be connected through the pressure fueling control valve switches on the oil delivery and emergency fueling control panel, and controls the oil delivery pump of the oil delivery tank to be opened to the oil delivery position through the oil delivery pump switch on the oil delivery and emergency fueling control panel, at this time, the fuel of the oil delivery tank flows through the pressure fueling control valves of No. 1, No. 2, No. 3 and No. 4 fuel tanks through the pipeline after being pressurized by the oil delivery pump and then enters the bottom of the above-mentioned outer compartments, the crew determines whether to stop oil delivery according to whether the low oil surface signal of No. 1, No. 2, No. 3 and No. 4 fuel tanks or the oil delivery tank low oil surface signaler sends a low oil surface signal, when oil delivery needs to be stopped, the crew disconnects the oil delivery pump switch and the pressure fueling control valve switch on the oil delivery and emergency fueling control panel to control the oil delivery pump of the oil delivery tank to be closed and the pressure fueling control valves of No. 1, No. 2, No. 3 and No. 4 fuel tanks to be cut off.

[0026] If the crew forgets to stop the oil feeding operation, when the liquid surface of the No. I / II / III / IV oil tank reaches the control oil surface of the oil surface controller, the oil surface controller sends a high oil surface signal, and the oil feeding and emergency oil discharging control panel automatically controls the pressure to cut off the oil feeding control valve of the corresponding oil tank, which can prevent the oil feeding system from continuously feeding oil to the No. I / II / III / IV oil tank when the crew forgets to stop the oil feeding operation, so as to prevent the oil tank from being damaged or fuel from overflowing out of the machine.

[0027] The emergency oil discharging method is specifically as follows:

[0028] During the flight of the aircraft, the crew determines whether the fuel in the No. V / VI oil tank needs to be discharged according to the needs, and the emergency oil discharging sequence is the No. VI oil tank→the No. V oil tank.

[0029] When the crew determines the emergency oil discharging oil tank in the No. V / VI oil tank, the crew controls the emergency oil discharging oil tank oil feeding pump to be opened to the emergency oil discharging gear through the oil feeding pump switch on the oil feeding and emergency oil discharging control panel, and controls the left and right emergency oil discharging valves to be connected through the emergency oil discharging valve switch on the panel, at this time, the fuel in the emergency oil discharging oil tank is pressurized by the oil feeding pump, flows through the emergency oil discharging valve through the pipeline, reaches the emergency oil discharging port, and is discharged out of the machine. The crew determines whether to stop the emergency oil discharging according to the amount of the discharged fuel or whether the low oil surface signal of the emergency oil discharging oil tank is sent, when it is needed to stop the emergency oil discharging, the crew controls the left and right emergency oil discharging valves to be cut off through the emergency oil discharging valve switch on the panel, and controls the emergency oil discharging oil tank oil feeding pump to be closed through the oil feeding pump switch on the panel, at this time, the emergency oil discharging is finished.

[0030] Technical effects:

[0031] The seaplane integrated design lightweight fuel transfer system and method provided by the application comprehensively considers the requirements of seaplane gravity center weight control and lightweight design, and proposes a general seaplane integrated design lightweight fuel transfer and emergency fuel discharge system according to the characteristics of low gravity center to enhance the wave resistance ability and lightweight design to reduce the structural load of the seaplane during water take-off and landing. The system integrates the pressure fueling system, the fuel transfer system and the emergency fuel discharge system, first, the two working states of the fuel transfer system flow and the emergency fuel discharge system flow are integrated on one fuel transfer pump, which maximizes the reduction of the number of pumps, second, the pressure fueling pipeline, the fuel transfer pipeline and the emergency fuel discharge pipeline are integrated, which maximizes the sharing of pipelines and reduces the number of pipelines, third, the low oil level signalers of the fuel tank during fuel transfer and emergency fuel discharge and the low oil level signalers of the fuel quantity measuring system are shared, which avoids duplication, and finally, the on-off control of the fuel transfer system and the on-off control of the pressure fueling are shared, which controls the connection and cut-off of fuel transfer through the pressure fueling control valve, and reduces the setting of the fuel transfer cut-off valve. Through the above integrated design, the weight of the fuel system is maximized, which can increase the load capacity of the aircraft or increase the fuel weight, thereby increasing the range and improving the ability of the aircraft to perform long-range tasks, such as long-range sea rescue; at the same time, the number of system components is greatly reduced, the probability of fuel system failure is reduced, and the system reliability is improved, thereby reducing the use cost of the aircraft. The application has strong pertinence, maximizes the use of integrated design, can ensure the lightest weight on the basis of realizing the function, and can meet the design requirements of the pressure fueling system, the fuel transfer system and the emergency fuel discharge system of the seaplane. BRIEF DESCRIPTION OF DRAWINGS

[0032] Figure 1 is the principle schematic diagram of the seaplane integrated design lightweight fuel transfer and emergency fuel discharge system in the application.

[0033] Among them: inner partition 1, outer partition 2, pressure fueling connector 3, pressure fueling control valve 4, oil surface controller 5, fuel transfer pump 7, low oil level signaler 8, emergency fuel discharge valve 9, emergency fuel discharge port 10, pipeline 12. DETAILED DESCRIPTION

[0034] In order to make the purpose, technical scheme and advantages of the embodiments of the application clearer, the technical scheme in the embodiments of the application will be described clearly and completely below in combination with the embodiments of the application. Obviously, the described embodiments are part of the embodiments of the application, not all the embodiments. Based on the embodiments in the application, all other embodiments obtained by those skilled in the art without creative labor belong to the scope of protection of the application.

[0035] The features and exemplary embodiments of the various aspects of the present application will be described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present application. However, it will be apparent to one of ordinary skill in the art that the present application can be practiced without some or all of these specific details. The description of the embodiments is merely intended to provide a better understanding of the present application. The present application is not limited to any particular setting or method described below, but covers any modification, equivalent, and alternative of the structure, method, device, etc. without departing from the spirit of the present application. In the following description, well-known structures and techniques are not shown in order to avoid unnecessary obscuring of the present application.

[0036] In the description of the present application, it should be noted that the directions or positional relationships belonging to "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the described directions or positional relationships, only for the convenience of describing the present application and simplifying the description, and cannot be understood as a limitation of the present application. In addition, the ordinal numbers (for example, "first and second", etc.) are used to distinguish objects, and are not limited to the order, and cannot be understood as indicating or implying relative importance.

[0037] In the description of the present application, it should be noted that, unless otherwise explicitly specified and limited, "mounting", "connection", "connection" should be understood in a broad sense, which can be directly connected or indirectly connected through an intermediate medium. For those of ordinary skill in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0038] It should be noted that, in the case of no conflict, the embodiments of the present application and the features in the embodiments can be combined with each other, and each embodiment can be mutually referred to and quoted. The present application will be described in detail below with reference to and in combination with the embodiments.

[0039] Embodiment 1:

[0040] (1) A seaplane integrated design lightweight fuel transfer system, comprising No. I / II / III / IV / V fuel tank on the wing of the aircraft, No. VI fuel tank on the fuselage, pressure refueling connector 3, pressure refueling control valve 4, oil level controller 5, pressure refueling control panel, oil pump 7, low oil level signal 8, emergency oil drain valve 9, emergency oil drain port 10, oil transfer and emergency oil transfer control panel, pipeline 12.

[0041] No. I / II / III / IV fuel tank is symmetrically arranged on both sides of the wing, No. I fuel tank is symmetric with No. IV fuel tank, No. II fuel tank is symmetric with No. III fuel tank, and No. V fuel tank is a central wing fuel tank;

[0042] The No. 6 oil tank is a fuselage oil tank, which is arranged at a low position in the middle of the fuselage, and the purpose of the arrangement is to lower the gravity center of the aircraft;

[0043] The inner compartment 1 of the No. 1 / 2 / 3 / 4 oil tank is a collecting tank (direct oil supply tank), and the outer compartment 2 is a storage tank. The inner compartment 1 comprises a low oil level signal 8, and the outer compartment 2 comprises a pressure oil supply control valve 4 and an oil level controller 5.

[0044] The outer compartment 2 of the No. 1 / 4 oil tank comprises an emergency oil drain valve 9.

[0045] The No. 5 and No. 6 oil tanks respectively comprise a pressure oil supply control valve 4, an oil level controller 5, two oil pumps 7 and a low oil level signal 8.

[0046] The emergency oil drain port 10 is arranged at the trailing edge of the wing.

[0047] The pipeline 12 is used to connect the pressure oil supply joint 3 with the pressure oil supply control valve 4 in the No. 1 / 2 / 3 / 4 / 5 / 6 oil tank, the oil pump 7 in the No. 5 / 6 oil tank, the emergency oil drain valve 9 in the No. 1 / 4 oil tank, and connect the emergency oil drain valve 9 with the emergency oil drain port 10.

[0048] The pressure oil supply control panel is a control and indication device of the pressure oil supply system, which receives the oil quantity signal of the No. 1 / 2 / 3 / 4 / 5 / 6 oil tank, the high oil level signal of the oil level controller 5 and the valve position signal of the pressure oil supply control valve 4, and automatically controls the operation of the pressure oil supply control valve 4 and indicates the working state thereof through the panel.

[0049] The oil pump 7 has two working modes, i.e. oil supply mode and emergency oil drain mode, which correspond to two oil pump outlet flow / pressure states respectively.

[0050] The oil supply and emergency oil drain control panel is a control and indication device of the oil supply system and the emergency oil drain system, which receives the valve position signal of the pressure oil supply control valve 4 in the No. 1 / 2 / 3 / 4 oil tank, the working state signal of the oil pump 7, the valve position signal of the emergency oil drain valve 9 and the high oil level signal of the oil level controller 5 in the No. 1 / 2 / 3 / 4 oil tank. The pressure oil supply control valve switch, the oil pump switch and the emergency oil drain valve switch on the panel are used to manually control the working of the pressure oil supply control valve 4, the oil pump 7 and the emergency oil drain valve 9 in the No. 1 / 2 / 3 / 4 oil tank respectively and indicate the working state thereof.

[0051] The aircraft wing is a single upper wing.

[0052] The method comprises a pressure oil supply method, an oil supply method and an emergency oil drain method.

[0053] The pressure refueling method is specifically:

[0054] The aircraft will be refueled before flight according to the task requirements, and the conventional sequence of fuel refueling is No. 1 / 2 / 3 / 4 tank→No. 5 tank→No. 6 tank, and the fuel refueling sequence is No. 1 / 2 / 3 / 4 tank→No. 6 tank→No. 5 tank when water take-off and landing is required to be performed;

[0055] During the pressure refueling process, the pressure refueling connector 3 is connected to the pressure refueling vehicle or other ground pressure refueling device, the maintenance personnel sets the refueling amount through the pressure refueling control panel, the above-mentioned panel automatically controls the pressure refueling control valve 4 of No. 1 / 2 / 3 / 4 / 5 / 6 tank to be connected, at this time, the fuel of the pressure refueling vehicle or other ground pressure refueling device flows through the pipe 12, enters the bottom of each tank after passing through the pressure refueling control valve 4 of No. 1 / 2 / 3 / 4 / 5 / 6 tank, when the oil amount of the tank reaches the preset refueling amount, the pressure refueling control panel automatically controls the pressure refueling control valve 4 of the corresponding tank to be cut off, if the above-mentioned measures do not control the pressure refueling control valve 4 to be cut off, when the liquid surface of No. 1 / 2 / 3 / 4 / 5 / 6 tank reaches the control oil surface of the oil surface controller 5, the oil surface controller 5 sends a high oil surface signal, and the pressure refueling control panel automatically controls the pressure refueling control valve 4 to be cut off after receiving the signal, and the refueling is completed when all the pressure refueling control valves 4 are cut off.

[0056] The oil transfer method is specifically:

[0057] During flight, the fuel consumption sequence is No. 1 / 2 / 3 / 4 tank outer compartment 2→No. 5 / 6 tank→No. 1 / 2 / 3 / 4 tank inner compartment 1;

[0058] When the oil amount of No. 1 / 2 / 3 / 4 tank is low (the oil amount value is low or the low oil surface signal is sent by the low oil surface signaler 8), the crew receives the information and judges the oil transfer tank of No. 5 tank and No. 6 tank according to the fuel amount in No. 5 tank and No. 6 tank and the control requirements of the aircraft center of gravity, when the aircraft center of gravity needs to be lowered, the fuel in No. 5 tank is transferred first, otherwise, the fuel in No. 6 tank is transferred first;

[0059] When the oil tank in the No. V / VI oil tank is determined, the crew controls the opening and closing of the pressure oiling control valve 4 of the No. I / II / III / IV oil tank through the pressure oiling control valve switch on the oiling and emergency oiling control panel, and controls the opening of the oiling pump 7 of the oiling tank to the oiling position through the oiling pump switch on the panel. At this time, the fuel in the oiling tank is pressurized by the oiling pump 7 and then flows through the pressure oiling control valve 4 of the No. I / II / III / IV oil tank through the pipeline 12 to the bottom of the above-mentioned outer compartment 2. The crew determines whether to stop the oiling according to the oil quantity in the No. I / II / III / IV oil tank or whether the low oil level signal of the oil level signaler 8 of the oiling tank is sent. When the oiling needs to be stopped, the crew closes the oiling pump 7 of the oiling tank and cuts off the pressure oiling control valve 4 of the No. I / II / III / IV oil tank through the oiling pump switch and the pressure oiling control valve switch on the oiling and emergency oiling control panel. If the crew forgets to stop the oiling operation, when the liquid level in the No. I / II / III / IV oil tank reaches the control oil level of the oil level controller 5, the oil level controller 5 sends a high oil level signal. After the oiling and emergency oiling control panel receives the signal, the pressure oiling control valve 4 of the corresponding oil tank is automatically cut off, which can prevent the oiling system from continuously supplying oil to the No. I / II / III / IV oil tank when the crew forgets to stop the oiling operation, resulting in damage to the oil tank or fuel overflow outside the machine.

[0060] The emergency oiling method is specifically as follows:

[0061] During the flight of the aircraft, the crew determines whether the fuel in the No. V / VI oil tank needs to be emergency discharged according to the needs. The emergency oiling sequence is No. VI oil tank→No. V oil tank.

[0062] When the crew determines the emergency oiling tank in the No. V / VI oil tank, the crew opens the emergency oiling pump 7 of the emergency oiling tank to the emergency oiling position through the oiling pump switch on the oiling and emergency oiling control panel, and connects the left and right emergency oiling valves 9 through the emergency oiling valve switch on the panel. At this time, the fuel in the emergency oiling tank is pressurized by the oiling pump 7 and then flows through the emergency oiling valve 9 through the pipeline 12 to the emergency oiling port 10 and then is discharged outside the machine. The crew determines whether to stop the emergency oiling according to the quantity of the emergency discharged fuel or whether the low oil level signal of the emergency oiling tank low oil level signaler 8 is sent. When the emergency oiling needs to be stopped, the crew cuts off the left and right emergency oiling valves 9 through the emergency oiling valve switch on the oiling and emergency oiling control panel, and closes the emergency oiling pump 7 of the emergency oiling tank through the oiling pump switch on the panel. At this time, the emergency oiling is completed.

[0063] The above detailed description is a detailed description of the present application, which cannot be considered as being limited to these descriptions. For ordinary skilled persons in the technical field to which the present application belongs, some simple deductions and substitutions can be made without departing from the concept of the present application, which should be considered as belonging to the protection scope of the present application.

Claims

1. An integrated design lightweight fuel transfer system for a seaplane, characterized by, The pipeline is connected with the pressure refueling connector at one end and connected with the pressure refueling control valve in the No. 1 fuel tank, the No. 2 fuel tank, the No. 3 fuel tank, the No. 4 fuel tank, the No. 5 fuel tank and the No. 6 fuel tank at the other end; the pipeline in the No. 5 fuel tank and the No. 6 fuel tank is provided with the oil transfer pump; The No. 1 fuel tank and the No. 2 fuel tank are arranged on one side of the aircraft wing, the No. 3 fuel tank and the No. 4 fuel tank are arranged on the other side of the aircraft wing, the No. 1 fuel tank is symmetrical with the No. 4 fuel tank, the No. 2 fuel tank is symmetrical with the No. 3 fuel tank, and the No. 5 fuel tank is a central wing fuel tank; the No. 6 fuel tank is a fuselage fuel tank and is located at a low position in the middle of the fuselage; The inner side compartment of the No. 1 fuel tank, the No. 2 fuel tank, the No. 3 fuel tank and the No. 4 fuel tank is a collecting tank, the outer side compartment is a storage tank, the inner side compartment contains a low oil level signaler, and the outer side compartment contains a pressure refueling control valve and an oil level controller; The No. 5 fuel tank and the No. 6 fuel tank each contain a pressure refueling control valve, an oil level controller, an oil transfer pump and a low oil level signaler; The pipeline is connected with the pressure refueling connector at one end and connected with the pressure refueling control valve in the No. 1 fuel tank, the No. 2 fuel tank, the No. 3 fuel tank, the No. 4 fuel tank, the No. 5 fuel tank and the No. 6 fuel tank at the other end; the pipeline in the No. 5 fuel tank and the No. 6 fuel tank is provided with the oil transfer pump; The pressure refueling control panel is a control and indication device of the pressure refueling system, which receives the oil quantity signal of the No. 1 fuel tank, the No. 2 fuel tank, the No. 3 fuel tank, the No. 4 fuel tank, the No. 5 fuel tank and the No. 6 fuel tank, the high oil level signal of the oil level controller and the valve position signal of the pressure refueling control valve, automatically controls the work of the pressure refueling control valve through the pressure refueling control panel and indicates the working state thereof; the oil transfer pump has two working modes, namely an oil transfer mode and an emergency oil discharge mode, corresponding to the oil transfer pump outlet flow or pressure state of the two modes respectively; further comprising an emergency oil discharge valve, the emergency oil discharge valve is arranged on the pipeline in the outer side compartment of the No. 1 fuel tank and the No. 4 fuel tank; further comprising an emergency oil discharge port, the emergency oil discharge port is installed at the trailing edge of the wing on both sides of the wing and connected with the emergency oil discharge valve in the No. 1 fuel tank and the No. 4 fuel tank respectively; further comprising an oil transfer and emergency oil discharge control panel, the oil transfer and emergency oil discharge control panel is a control and indication device of the oil transfer system and the emergency oil discharge system, which receives the valve position signal of the pressure refueling control valve in the No. 1 fuel tank, the No. 2 fuel tank, the No. 3 fuel tank and the No. 4 fuel tank, the working state signal of the oil transfer pump in the No. 5 fuel tank or the No. 6 fuel tank, the valve position signal of the emergency oil discharge valve and the high oil level signal of the oil level controller in the No. 1 fuel tank, the No. 2 fuel tank, the No. 3 fuel tank and the No. 4 fuel tank, manually controls the work of the pressure refueling control valve, the oil transfer pump and the emergency oil discharge valve in the No. 1 fuel tank, the No. 2 fuel tank, the No. 3 fuel tank and the No. 4 fuel tank through the pressure refueling control valve switch, the oil transfer pump switch and the emergency oil discharge valve switch on the oil transfer and emergency oil discharge control panel respectively and indicates the working state thereof; the oil transfer pump is two, which is designed with double redundancy control.

2. The system of claim 1, wherein, The aircraft wing is a single wing.

3. A method for integrated design lightening of fuel transfer for seaplane using the system according to any one of claims 1-2, characterized in that, The pressure refueling method, the oil transfer method and the emergency oil discharge method are included.

4. The method of claim 3, wherein, The pressure refueling method specifically comprises the following steps: The aircraft will be refueled according to the task before flight, and the conventional sequence of fuel filling is No. 1 tank, No. 2 tank, No. 3 tank, No. 4 tank, No. 5 tank and No. 6 tank, and the sequence of fuel filling for water take-off and landing is No. 1 tank, No. 2 tank, No. 3 tank, No. 4 tank, No. 5 tank and No. 6 tank; During the pressure refueling process, the pressure refueling connector is connected with the pressure refueling vehicle or other ground pressure refueling device, the refueling amount is set by the maintenance personnel through the pressure refueling control panel, the pressure refueling control panel automatically controls the pressure refueling control valves of No. 1 tank, No. 2 tank, No. 3 tank, No. 4 tank, No. 5 tank and No. 6 tank to be connected, at this time, the fuel of the pressure refueling vehicle or other ground pressure refueling device flows through the pressure refueling connector, the pipeline, the pressure refueling control valves of No. 1 tank, No. 2 tank, No. 3 tank, No. 4 tank, No. 5 tank and No. 6 tank and then enters the bottom of each tank, when the oil amount of the tank reaches the preset refueling amount, the pressure refueling control panel automatically controls the pressure refueling control valves of the corresponding tank to be cut off; If the pressure refueling control panel does not control the pressure refueling control valves to be cut off, when the liquid level of No. 1 tank, No. 2 tank, No. 3 tank, No. 4 tank, No. 5 tank and No. 6 tank reaches the control oil level of the oil level controller, the oil level controller sends a high oil level signal, after receiving the signal, the pressure refueling control panel automatically controls the pressure refueling control valves to be cut off, and when all the pressure refueling control valves are cut off, the refueling is completed.

5. The method of claim 3, wherein, The oil delivery method is specifically as follows: During flight, the fuel consumption sequence is No. 1 tank, No. 2 tank, No. 3 tank, No. 4 tank, the outer compartment of No. 5 tank, No. 6 tank, No. 5 tank and No. 1 tank, No. 2 tank, No. 3 tank, No. 4 tank, the inner compartment of No. 5 tank; When the oil amount of No. 1 tank, No. 2 tank, No. 3 tank and No. 4 tank is low, including the low oil level signal sent by the low oil level signaler, when the crew receives the signal, the fuel tank for oil delivery of No. 5 tank and No. 6 tank is determined according to the fuel amount in No. 5 tank and No. 6 tank and the control requirement of the aircraft center of gravity, when the aircraft center of gravity needs to be lowered, the fuel of No. 5 tank is delivered first, otherwise, the fuel of No. 6 tank is delivered first; After the fuel tank for oil delivery of No. 5 tank or No. 6 tank is determined, the crew controls the pressure refueling control valves of No. 1 tank, No. 2 tank, No. 3 tank and No. 4 tank to be connected through the pressure refueling control valve switch on the oil delivery and emergency oil discharge control panel, and controls the oil delivery pump of the fuel tank for oil delivery to be opened to the oil delivery gear through the oil delivery pump switch on the oil delivery and emergency oil discharge control panel, at this time, the fuel of the fuel tank for oil delivery is pressurized by the oil delivery pump, flows through the pressure refueling control valves of No. 1 tank, No. 2 tank, No. 3 tank and No. 4 tank through the pipeline and then enters the bottom of the outer compartment of the above-mentioned tanks, whether the oil delivery is stopped is determined by the crew according to the oil amount of No. 1 tank, No. 2 tank, No. 3 tank and No. 4 tank or whether the low oil level signal is sent by the low oil level signaler of the fuel tank for oil delivery, when the oil delivery needs to be stopped, the crew disconnects the oil delivery pump of the fuel tank for oil delivery to be closed and the pressure refueling control valves of No. 1 tank, No. 2 tank, No. 3 tank and No. 4 tank to be cut off through the oil delivery pump switch and the pressure refueling control valve switch on the oil delivery and emergency oil discharge control panel. If the crew forgets to stop the oil feeding operation, when the liquid surface of the No. 1 oil tank, the No. 2 oil tank, the No. 3 oil tank and the No. 4 oil tank reaches the control oil surface of the oil surface controller, the oil surface controller sends a high oil surface signal, and the oil feeding and emergency oil discharging control panel automatically controls the pressure to cut off the oil feeding control valve of the corresponding oil tank according to the signal, so that the oil feeding system can be prevented from continuously feeding the No. 1 oil tank, the No. 2 oil tank, the No. 3 oil tank and the No. 4 oil tank when the crew forgets to stop the oil feeding operation, and the oil tanks are prevented from being damaged or the fuel is prevented from overflowing out of the aircraft.

6. The method of claim 3, wherein, The emergency oil discharging method specifically comprises the following steps: During the flight of the aircraft, the crew determines whether the fuel in the No. 5 oil tank and the No. 6 oil tank needs to be discharged according to the needs, and the emergency oil discharging sequence is the No. 6 oil tank→the No. 5 oil tank; When the crew determines the emergency oil discharging oil tank in the No. 5 oil tank and the No. 6 oil tank, the crew controls the emergency oil discharging oil tank oil feeding pump to be opened to the emergency oil discharging gear through the oil feeding pump switch on the oil feeding and emergency oil discharging control panel, and controls the left and right emergency oil discharging valves to be connected through the emergency oil discharging valve switch on the panel, so that the fuel in the emergency oil discharging oil tank is pressurized by the oil feeding pump, flows through the emergency oil discharging valve through the pipeline, reaches the emergency oil discharging port and is discharged out of the aircraft; the crew determines whether to stop the emergency oil discharging according to the amount of the discharged fuel or whether the low oil surface signal of the emergency oil discharging oil tank is sent, and when the emergency oil discharging needs to be stopped, the crew controls the left and right emergency oil discharging valves to be cut off through the emergency oil discharging valve switch on the oil feeding and emergency oil discharging control panel, and controls the emergency oil discharging oil tank oil feeding pump to be closed through the oil feeding pump switch on the panel, so that the emergency oil discharging is ended.

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