Light-weight fuel oil transmission system and method for integrated design of seaplane

Abstract

The invention belongs to the field of aircraft fuel systems, and relates to a seaplane integrated design lightweight fuel transmission system and method. Comprising oil tanks I, II, III, IV, V and VI, a pressure refueling connector, a pressure refueling control valve, an oil level controller, a pressure refueling control panel, an oil delivery pump and a low oil level annunciator, two working states of flow of an oil delivery system and flow of an emergency oil drainage system are integrated on one oil delivery pump, so that the number of pumps is reduced to the maximum extent; a pressure refueling pipeline, an oil conveying pipeline and an emergency oil discharging pipeline are integrally designed, so that the number of pipelines is reduced; thirdly, a low-oil-level annunciator of the oil tank and a low-oil-level annunciator of the oil mass measuring system are designed in common during oil transportation and emergency oil drainage, on-off control of an oil transportation system and on-off control of pressure refueling are designed in common, connection and disconnection of oil transportation are controlled through a pressure refueling control valve, and arrangement of an oil transportation stop valve is reduced.

Description

Technical Field

[0001] This invention belongs to the field of aircraft fuel systems, and relates to a lightweight fuel transfer system and method for integrated design of seaplanes. Background Technology

[0002] The aircraft fuel system is a crucial component of an aircraft. It functions to rapidly refuel, adjust the aircraft's center of gravity, and quickly release fuel to reduce weight when necessary. The pressurized refueling system, fuel delivery system, and emergency fuel dumping system are key to achieving these functions. For seaplanes, to improve their wave resistance during water takeoffs and landings, measures such as arranging fuselage fuel tanks and controlling fuel consumption sequence are typically employed to lower the aircraft's center of gravity. Simultaneously, to reduce structural loads during water takeoffs and landings, the system weight of seaplanes must be strictly controlled. Therefore, designing a lightweight fuel system that simultaneously achieves rapid refueling, reliable fuel delivery for center of gravity adjustment, and rapid fuel release while minimizing system weight is critical to aircraft fuel system design. Summary of the Invention

[0003] Purpose of the Invention: The purpose of this invention is to provide a lightweight fuel transfer system and method for integrated design of seaplanes. This reduces the structural weight of the aircraft, and the single-path transfer system can perform refueling, fuel transfer, and fuel discharge functions respectively.

[0004] The technical solution of the present invention is as follows:

[0005] A lightweight fuel transfer system for seaplanes with integrated design includes fuel tanks I, II, III, IV, and V located on the wings of the aircraft, fuel tank VI on the fuselage, a pressure refueling connector, a pressure refueling control valve, a fuel level controller, a pressure refueling control panel, a fuel pump, a low fuel level signal device, and pipelines.

[0006] Fuel tanks I, II, III, and IV are symmetrically arranged on both sides of the wing, with tanks I and IV being symmetrical, and tanks II and III being symmetrical. Fuel tank V is the center wing fuel tank; fuel tank VI is the fuselage fuel tank, located in the lower middle part of the fuselage. The purpose of this fuel tank arrangement is to lower the aircraft's center of gravity.

[0007] The inner compartments of oil tanks I, II, III, and IV are oil collection tanks (direct oil supply tanks), and the outer compartments are oil storage tanks. The inner compartments contain a low oil level signal device, and the outer compartments contain a pressure filling control valve and an oil level controller.

[0008] Each of the No. V and No. VI oil tanks contains a pressure filling control valve, an oil level controller, an oil pump, and a low oil level signal device.

[0009] One end of the pipeline is connected to a pressure filling connector, and the other end is connected to the pressure filling control valves in oil tanks I, II, III, IV, V, and VI respectively; oil pumps are installed on the pipelines in oil tanks V and VI.

[0010] The pressure refueling control panel is a control and indication device for the pressure refueling system. It receives the oil quantity signal from oil tanks I / II / III / IV / V / VI, the high oil level signal from the oil level controller, and the valve position signal from the pressure refueling control valve. The pressure refueling control panel automatically controls the operation of the pressure refueling control valve and indicates its working status.

[0011] Furthermore, the oil pump has two operating modes: oil delivery mode and emergency oil discharge mode, which correspond to the oil pump outlet flow / pressure status of the two modes, respectively.

[0012] The aircraft described is a high-wing monoplane.

[0013] Furthermore, it also includes an emergency oil drain valve, which is installed on the pipeline inside the outer compartment of the No. I / No. IV oil tank;

[0014] Furthermore, it also includes an emergency fuel drain port, which is installed on the trailing edge of the wings on both sides of the wing and connected to the emergency fuel drain valves in fuel tanks I and IV respectively;

[0015] Furthermore, it also includes an oil transfer and emergency oil drain control panel. The oil transfer and emergency oil drain control panel is a control and indication device for the oil transfer system and the emergency oil drain system. It receives the valve position signal of the pressure filling control valve of oil tanks I / II / III / IV, the working status signal of the oil pump in oil tanks V / VI, the valve position signal of the emergency oil drain valve, and the high oil level signal of the oil level controller in oil tanks I / II / III / IV. Through the pressure filling control valve switch, oil pump switch, and emergency oil drain valve switch on the oil transfer and emergency oil drain control panel, the operation of the pressure filling control valve, oil pump, and emergency oil drain valve of oil tanks I / II / III / IV, respectively, is manually controlled and their working status is indicated.

[0016] Furthermore, there are two oil pumps, which is a dual-redundant control design.

[0017] A lightweight fuel transfer method for integrated design of seaplanes includes a pressure refueling method, a fuel delivery method, and an emergency fuel release method.

[0018] The pressure refueling method is specifically as follows:

[0019] Before a flight, the aircraft will be refueled according to the mission requirements. The normal refueling order is tanks I, II, III, IV, V, and VI. When water takeoffs and landings are required, the refueling order is tanks I, II, III, IV, VI, and V.

[0020] During the pressure refueling process, the pressure refueling connector is connected to the pressure refueling truck or other ground pressure refueling device. The maintenance personnel set the refueling amount through the pressure refueling control panel. The pressure refueling control panel automatically controls the pressure refueling control valves of tanks I / II / III / IV / V / VI to open. At this time, the fuel from the pressure refueling truck or other ground pressure refueling device flows through the pipeline via the pressure refueling connector and into the bottom of each tank after passing through the pressure refueling control valves of tanks I / II / III / IV / V / VI. When the fuel level in the tank reaches the preset refueling amount, the pressure refueling control panel automatically controls the pressure refueling control valve of the corresponding tank to close.

[0021] If the pressure refueling control panel does not control the pressure refueling control valve to close, when the oil level in tanks I / II / III / IV / V / VI reaches the control oil level of the oil level controller, the oil level controller sends a high oil level signal. Upon receiving the signal, the pressure refueling control panel automatically controls the pressure refueling control valve to close. Refueling ends when all pressure refueling control valves are closed.

[0022] The oil transportation method is as follows:

[0023] During flight, the fuel consumption sequence is as follows: outer compartments of fuel tanks I, II, III, and IV → fuel tanks V and VI → inner compartments of fuel tanks I, II, III, and IV;

[0024] When the fuel levels in tanks I / II / III / IV are low, including when the fuel level is displayed as low or when the low fuel level signal is issued, the crew will determine which tank to transfer fuel to based on the fuel levels in tanks V and VI and the aircraft's center of gravity control requirements. If it is necessary to lower the aircraft's center of gravity, fuel will be transferred to tank V first; otherwise, fuel will be transferred to tank VI first.

[0025] Once the fuel tank in tanks V and VI is identified, the unit controls the pressure refueling control valves of tanks I, II, III, and IV to open via the pressure refueling control valve switch on the fuel supply and emergency fuel release control panel. It also controls the fuel pump in the fuel tank to open to the fuel supply position via the fuel pump switch on the fuel supply and emergency fuel release control panel. At this time, the fuel in the fuel tank is pressurized by the fuel pump and flows through the pipelines to the bottom of the outer compartment after passing through the pressure refueling control valves of tanks I, II, III, and IV. The unit decides whether to stop fuel supply based on the fuel level in tanks I, II, III, and IV or whether the fuel tank low fuel level signaler issues a low fuel level signal. When it is necessary to stop fuel supply, the unit disconnects the fuel pump switch and the pressure refueling control valve switch on the fuel supply and emergency fuel release control panel to close the fuel pump in the fuel tank and shut off the pressure refueling control valves of tanks I, II, III, and IV.

[0026] If the unit forgets to stop the fuel supply operation, when the fuel level in tanks I / II / III / IV reaches the control level of the fuel level controller, the fuel level controller will send a high fuel level signal. After receiving the above signal, the fuel supply and emergency fuel release control panel will automatically control the fuel filling control valve to close the pressure corresponding to the fuel tank pressure. This can prevent the fuel supply system from continuing to supply fuel to tanks I / II / III / IV when the unit forgets to stop the fuel supply operation, which could lead to damage to the fuel tanks or fuel overflow outside the machine.

[0027] The emergency oil release method is as follows:

[0028] During flight, the crew may determine whether it is necessary to release fuel from tanks V or VI as an emergency, and the emergency fuel release order is tank VI → tank V.

[0029] Once the generator set identifies the emergency fuel drain tank in tanks V or VI, it controls the emergency fuel drain tank pump to open to the emergency fuel drain position via the fuel pump switch on the fuel supply and emergency fuel drain control panel. The unit also controls the left and right emergency fuel drain valves to open via the emergency fuel drain valve switch on the panel. At this time, fuel from the emergency fuel drain tank is pressurized by the fuel pump, flows through the pipeline to the emergency fuel drain valve, and then reaches the emergency fuel drain port before being discharged outside the generator. The generator set determines whether to stop the emergency fuel drain based on the amount of fuel drained or whether the low fuel level signal device in the emergency fuel drain tank issues a low fuel level signal. When it is necessary to stop the emergency fuel drain, the generator set controls the left and right emergency fuel drain valves to close via the emergency fuel drain valve switch on the fuel supply and emergency fuel drain control panel, and controls the emergency fuel drain tank pump to close via the fuel pump switch on the panel. At this point, the emergency fuel drain is complete.

[0030] Technical effects:

[0031] This invention discloses a lightweight integrated fuel transfer system and method for seaplanes, comprehensively considering the requirements of seaplane center of gravity control and lightweight design. Addressing the characteristics of seaplanes during water takeoff and landing—namely, a low center of gravity enhancing wave resistance and lightweight design reducing structural load—this invention proposes a versatile lightweight integrated integrated fuel delivery and emergency fuel discharge system for seaplanes. This system integrates the pressure refueling system, fuel delivery system, and emergency fuel discharge system. First, a single fuel pump integrates both the flow rates of the fuel delivery system and the emergency fuel discharge system, minimizing the number of pumps. Second, the pressure refueling pipeline, fuel delivery pipeline, and emergency fuel discharge pipeline are integrated, maximizing pipeline sharing and reducing the number of pipelines. Third, the low fuel level indicator for the fuel tank during fuel delivery and emergency fuel discharge is shared with the low fuel level indicator of the fuel quantity measurement system, avoiding duplication. Finally, the on / off control of the fuel delivery system and the pressure refueling system are shared, with the pressure refueling control valve controlling the connection and disconnection of fuel delivery, reducing the need for separate fuel cut-off valves. By maximizing the reduction of fuel system weight through the aforementioned integrated design, the aircraft's payload capacity can be increased, or the fuel weight can be increased, thereby increasing the range and enhancing the aircraft's ability to perform long-range missions, such as long-range maritime rescue. Simultaneously, the number of system components is significantly reduced, lowering the probability of fuel system failure and thus improving system reliability and reducing aircraft operating costs. This invention is highly targeted, maximizing the use of integrated design to ensure functionality while minimizing weight, meeting the design requirements of seaplane pressure refueling systems, fuel delivery systems, and emergency fuel dumping systems. Attached Figure Description

[0032] Figure 1 This is a schematic diagram illustrating the principle of the lightweight oil transfer and emergency oil dumping system integrated into the design of a seaplane in this invention.

[0033] The components include: inner compartment 1, outer compartment 2, pressure refueling connector 3, pressure refueling control valve 4, oil level controller 5, oil pump 7, low oil level signal 8, emergency oil drain valve 9, emergency oil drain port 10, and pipeline 12. Detailed Implementation

[0034] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0035] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setup and method set forth below, but covers any improvements, substitutions, and modifications to the structures, methods, and devices without departing from the spirit of the invention. In the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring the invention.

[0036] In the description of this invention, it should be noted that the directions or positional relationships indicated by terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer" are based on the stated directions or positional relationships and are only for the convenience of describing and simplifying the invention, and should not be construed as limiting the invention. Furthermore, the use of ordinal numbers (e.g., "first and second," etc.) is for distinguishing objects and is not limited to this order, and should not be construed as indicating or implying relative importance.

[0037] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly, encompassing both direct connection and indirect connection via an intermediate medium. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances.

[0038] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in each other. The present invention will now be described in detail with reference to and in conjunction with the embodiments.

[0039] Example 1:

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

[0041] Fuel tanks I, II, III, and IV are symmetrically arranged on both sides of the wing. Fuel tank I is symmetrical with fuel tank IV, fuel tank II is symmetrical with fuel tank III, and fuel tank V is the center wing fuel tank.

[0042] Fuel tank VI is a fuselage fuel tank, located in the lower middle part of the fuselage. The purpose of this fuel tank arrangement is to lower the aircraft's center of gravity.

[0043] The inner compartment 1 of the No. I / II / III / IV oil tanks is an oil collection tank (direct oil supply tank), and the outer compartment 2 is an oil storage tank. The inner compartment 1 contains a low oil level signal device 8, and the outer compartment 2 contains a pressure filling control valve 4 and an oil level controller 5.

[0044] The outer compartment 2 of the No. I / IV oil tank contains an emergency oil drain valve 9;

[0045] The No. V and No. VI oil tanks each contain a pressure filling control valve 4, an oil level controller 5, two oil pumps 7, and a low oil level signal device 8.

[0046] The emergency fuel drain port 10 is installed on the trailing edge of both sides of the wing;

[0047] The pipeline 12 is used to connect the pressure filling connector 3 to the pressure filling control valve 4 in oil tanks I / II / III / IV / V / VI, the oil pump 7 in oil tank V / VI, and the emergency oil drain valve 9 in oil tank I / IV, and connect the emergency oil drain valve 9 to the emergency oil drain port 10.

[0048] The pressure refueling control panel is a control and indication device for the pressure refueling system. It receives the oil quantity signal from oil tanks I / II / III / IV / V / VI, the high oil level signal from the oil tank level controller 5, and the valve position signal from the pressure refueling control valve 4. The panel automatically controls the operation of the pressure refueling control valve 4 and indicates its working status.

[0049] The oil pump 7 has two operating modes: oil delivery mode and emergency oil discharge mode, which correspond to two different oil pump outlet flow / pressure states.

[0050] The oil transfer and emergency oil drain control panel is a control and indication device for the oil transfer system and the emergency oil drain system. It receives the valve position signal of the pressure filling control valve 4 of oil tanks I / II / III / IV, the working status 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 of oil tanks I / II / III / IV. Through the pressure filling control valve switch, oil pump switch, and emergency oil drain valve switch on the panel, the operation of the pressure filling control valve 4, oil pump 7, and emergency oil drain valve 9 of oil tanks I / II / III / IV, respectively, is manually controlled and their working status is indicated.

[0051] The aircraft described is a high-wing monoplane.

[0052] A lightweight fuel transfer method for integrated design of seaplanes includes a pressure refueling method, a fuel delivery method, and an emergency fuel release method.

[0053] The pressure refueling method is specifically as follows:

[0054] Before a flight, the aircraft will be refueled according to the mission requirements. The normal refueling order is tank I / II / III / IV → tank V → tank VI. When water take-off and landing are required, the refueling order is tank I / II / III / IV → tank VI → tank V.

[0055] During pressure refueling, pressure refueling connector 3 connects to the pressure refueling truck or other ground pressure refueling device. The maintenance personnel set the refueling volume through the pressure refueling control panel. The panel automatically controls the pressure refueling control valve 4 of tanks I / II / III / IV / V / VI to open. At this time, the fuel from the pressure refueling truck or other ground pressure refueling device flows through the pressure refueling connector 3 and pipeline 12 through the pressure refueling control valve 4 of tanks I / II / III / IV / V / VI and enters the bottom of each tank. When the fuel level in the tank reaches the preset refueling volume, the pressure refueling control panel automatically controls the pressure refueling control valve 4 of the corresponding tank to close. If the above measures fail to control the pressure refueling control valve 4 to close, when the fuel level in tanks I / II / III / IV / V / VI reaches the control level of the fuel level controller 5, the fuel level controller 5 sends a high fuel level signal. After receiving the signal, the pressure refueling control panel automatically controls the pressure refueling control valve 4 to close. Refueling ends when all pressure refueling control valves 4 are closed.

[0056] The oil transportation method is as follows:

[0057] During flight, the fuel consumption sequence is: outer compartment 2 of fuel tanks I / II / III / IV → fuel tank V / VI → inner compartment 1 of fuel tanks I / II / III / IV;

[0058] When the fuel level in tanks I / II / III / IV is low (either the fuel level reading is low or the low fuel level signaler 8 issues a low fuel level signal), the crew, upon receiving this information, determines which fuel tank to transfer to based on the fuel levels in tanks V and VI and the aircraft's center of gravity control requirements. If it is necessary to lower the aircraft's center of gravity, fuel from tank V will be transferred first; otherwise, fuel from tank VI will be transferred first.

[0059] Once the fuel tank in tanks V / VI is identified, the unit controls the pressure filling control valve 4 of tanks I / II / III / IV via the pressure filling control valve switch on the fuel supply and emergency fuel release control panel. It also controls the fuel pump 7 of the fuel tank to open to the fuel supply position via the fuel pump switch on the panel. At this time, the fuel in the fuel tank is pressurized by the fuel pump 7 and flows through pipeline 12, through the pressure filling control valve 4 of tanks I / II / III / IV, and into the bottom of the aforementioned outer compartment 2. The unit decides whether to stop fuel supply based on the fuel level in tanks I / II / III / IV or whether the fuel tank low fuel level signal 8 issues a low fuel level signal. When it is necessary to stop fuel supply... When the unit disconnects the oil pump switch and pressure filling control valve switch on the oil supply and emergency oil drain control panel, it controls the oil pump 7 in the oil tank to shut off and the pressure filling control valve 4 in tanks I / II / III / IV to close. If the unit forgets to stop the oil supply operation, when the oil level in tanks I / II / III / IV reaches the control oil level of the oil level controller 5, the oil level controller 5 sends a high oil level signal. After receiving the above signal, the oil supply and emergency oil drain control panel automatically controls the pressure filling control valve 4 of the corresponding oil tank to close. This can prevent the oil supply system from continuously supplying oil to tanks I / II / III / IV when the unit forgets to stop the oil supply operation, which could lead to damage to the oil tanks or fuel spillage outside the machine.

[0060] The emergency oil release method is as follows:

[0061] During flight, the crew may determine whether it is necessary to release fuel from tanks V or VI as an emergency, and the emergency fuel release order is tank VI → tank V.

[0062] Once the generator set identifies the emergency fuel drain tank in tanks V / VI, it controls the emergency fuel drain tank pump 7 to open to the emergency fuel drain position via the fuel pump switch on the fuel supply and emergency fuel drain control panel. It also controls the left and right emergency fuel drain valves 9 to open via the emergency fuel drain valve switch on the panel. At this time, the fuel in the emergency fuel drain tank, after being pressurized by the fuel pump 7, flows through pipeline 12, through the emergency fuel drain valve 9, and reaches the emergency fuel drain port 10 before being discharged outside the generator. The generator set determines whether to stop the emergency fuel drain based on the amount of fuel drained or whether the low fuel level signal device 8 of the emergency fuel drain tank issues a low fuel level signal. When it is necessary to stop the emergency fuel drain, the generator set controls the left and right emergency fuel drain valves 9 to close via the emergency fuel drain valve switch on the fuel supply and emergency fuel drain control panel, and controls the emergency fuel drain tank pump 7 to close via the fuel pump switch on the panel. At this point, the emergency fuel drain is complete.

[0063] The above detailed embodiments are a description of the present invention. It should not be considered that the specific embodiments of the present invention are limited to these descriptions. For those skilled in the art, several simple deductions and substitutions can be made without departing from the concept of the present invention, and all of these should be considered to fall within the protection scope of the present invention.

Claims

1. A lightweight fuel transfer system integrated into a seaplane design, characterized in that, This includes fuel tanks I, II, III, IV, and V located on the aircraft wings, fuel tank VI on the fuselage, pressure refueling connectors, pressure refueling control valves, fuel level controllers, pressure refueling control panels, fuel pumps, low fuel level signalers, and pipelines. Fuel tanks I and II are located on one side of the aircraft wing, and fuel tanks III and IV are located on the other side of the aircraft wing. Fuel tanks I and IV are symmetrical, and fuel tanks II and III are symmetrical. Fuel tank V is the center wing fuel tank; fuel tank VI is the fuselage fuel tank, located in the lower middle part of the fuselage. The inner compartments of oil tanks I, II, III, and IV are all oil collection tanks, and the outer compartments are oil storage tanks. The inner compartments contain a low oil level signal device, and the outer compartments contain a pressure filling control valve and an oil level controller. Both oil tanks V and VI contain a pressure filling control valve, an oil level controller, an oil pump, and a low oil level signal device. One end of the pipeline is connected to a pressure filling connector, and the other end is connected to the pressure filling control valves in oil tanks I, II, III, IV, V, V, and VI respectively; oil pumps are installed on the pipelines in oil tanks V and VI. The pressure refueling control panel is the control and indication device of the pressure refueling system. It receives oil quantity signals from oil tanks I, II, III, IV, V, and VI, high oil level signals from the oil level controller, and valve position signals from the pressure refueling control valve. The pressure refueling control panel automatically controls the operation of the pressure refueling control valve and indicates its working status.

2. The system as described in claim 1, characterized in that, The oil pump has two operating modes: oil delivery mode and emergency oil discharge mode, which correspond to the oil pump outlet flow rate or pressure status of the two modes, respectively.

3. The system as described in claim 1, characterized in that, The aircraft has a high-wing configuration.

4. The system as described in claim 1, characterized in that, It also includes an emergency oil drain valve, which is installed on the pipeline inside the outer compartment of the No. I and No. IV oil tanks.

5. The system as described in claim 4, characterized in that, It also includes an emergency fuel drain port, which is installed on the trailing edge of the wings on both sides of the wing and connected to the emergency fuel drain valves in fuel tanks I and IV, respectively.

6. The system as described in claim 5, characterized in that, It also includes an oil transfer and emergency oil drain control panel, which serves as the control and indication device for the oil transfer system and the emergency oil drain system. It receives valve position signals from the pressure filling control valves of oil tanks I, II, III, and IV; the operating status signal of the oil pump in oil tank V or VI; the valve position signal of the emergency oil drain valve; and the high oil level signal from the oil level controllers in oil tanks I, II, III, and IV. Through the pressure filling control valve switch, oil pump switch, and emergency oil drain valve switch on the control panel, the operation of the pressure filling control valves, oil pumps, and emergency oil drain valves of oil tanks I, II, III, and IV is manually controlled, and their operating status is indicated. Two oil pumps are used, featuring a dual-redundancy control design.

7. A lightweight fuel transfer method for seaplanes using the system described in any one of claims 1-6, characterized in that, This includes methods for pressurized refueling, oil transfer, and emergency oil release.

8. The method as described in claim 7, characterized in that, The pressure refueling method is specifically as follows: Before a flight, the aircraft will be refueled according to the mission requirements. The normal refueling order is tank 1, tank 2, tank 3, tank 4, tank 5, tank 6. When water takeoff and landing are required, the refueling order is tank 1, tank 2, tank 3, tank 4, tank 5, tank 6, tank 7, tank 8, tank 9. During the pressure refueling process, the pressure refueling connector is connected to the pressure refueling truck or other ground pressure refueling device. The maintenance personnel set the refueling amount through the pressure refueling control panel. The pressure refueling control panel automatically controls the pressure refueling control valves of tanks I, II, III, IV, V, and VI to be connected. At this time, the fuel from the pressure refueling truck or other ground pressure refueling device flows through the pipeline via the pressure refueling connector through the pressure refueling pipes and into the bottom of each tank. When the fuel level in the tank reaches the preset refueling amount, the pressure refueling control panel automatically controls the pressure refueling control valve of the corresponding tank to be cut off. If the pressure refueling control panel fails to close the pressure refueling control valve, when the oil levels in tanks I, II, III, IV, V, and VI reach the control oil level of the oil level controller, the oil level controller will issue a high oil level signal. Upon receiving this signal, the pressure refueling control panel will automatically close the pressure refueling control valve. Refueling will end when all pressure refueling control valves are closed.

9. The method as described in claim 7, characterized in that, The oil transportation method is specifically as follows: During flight, the fuel consumption sequence is as follows: fuel tank I, fuel tank II, fuel tank III, fuel tank IV, outer compartment of fuel tank V → fuel tank V, fuel tank VI → fuel tank I, fuel tank II, fuel tank III, fuel tank IV inner compartment. When the fuel levels in fuel tanks I, II, III, and IV are low, including when the fuel level is displayed as low or when the low fuel level signal is issued, the crew will determine which fuel tank to transfer fuel to based on the fuel levels in fuel tanks V and VI and the aircraft's center of gravity control requirements. If it is necessary to lower the aircraft's center of gravity, fuel will be transferred to fuel tank V first; otherwise, fuel will be transferred to fuel tank VI first. Once the fuel tank in tank V or tank VI is identified, the unit controls the pressure filling control valves of tanks I, II, III, and IV via the pressure filling control valve switch on the fuel supply and emergency drain control panel. Simultaneously, the unit controls the fuel supply pump in the fuel tank to open to the fuel supply position via the fuel pump switch on the fuel supply and emergency drain control panel. At this time, the fuel in the fuel tank is pressurized by the fuel pump and flows through the pipelines to tanks I, II, III, and IV. After entering the bottom of the outer compartment of the above-mentioned oil tanks through the refueling control valve, the unit decides whether to stop refueling based on the oil levels in oil tanks I, II, III, and IV, or whether the low oil level signal device of the oil tank issues a low oil level signal. When it is necessary to stop refueling, the unit disconnects the oil pump switch and the pressure refueling control valve switch on the oil supply and emergency oil release control panel to control the oil pump of the oil tank to close and the pressure refueling control valves of oil tanks I, II, III, and IV to cut off. If the generator unit forgets to stop the fuel supply operation, when the fuel levels in tanks I, II, III, and IV reach the control level of the fuel level controller, the fuel level controller will issue a high fuel level signal. Upon receiving the signal, the fuel supply and emergency fuel release control panel will automatically cut off the fuel filling control valve corresponding to the tank pressure. This prevents the fuel supply system from continuously supplying fuel to tanks I, II, III, and IV when the generator unit forgets to stop the fuel supply operation, which could lead to tank damage or fuel spillage outside the generator.

10. The method as described in claim 7, characterized in that, The emergency oil release method is as follows: During flight, the crew may determine whether it is necessary to release fuel from tanks V and VI as an emergency, and the emergency fuel release order is tank VI → tank V. Once the unit identifies the emergency fuel drain tanks in fuel tanks V and VI, it controls the emergency fuel drain tank pump to open to the emergency fuel drain position via the fuel pump switch on the fuel supply and emergency fuel drain control panel. It also controls the left and right emergency fuel drain valves to open via the emergency fuel drain valve switch on the panel. At this time, the fuel in the emergency fuel drain tank is pressurized by the fuel pump, flows through the pipeline to the emergency fuel drain valve, and then reaches the emergency fuel drain port before being discharged outside the machine. The unit decides whether to stop the emergency fuel drain based on the amount of fuel drained or whether the low fuel level signal device in the emergency fuel drain tank issues a low fuel level signal. When it is necessary to stop the emergency fuel drain, the unit controls the left and right emergency fuel drain valves to close via the emergency fuel drain valve switch on the fuel supply and emergency fuel drain control panel, and controls the emergency fuel drain tank pump to close via the fuel pump switch on the panel. At this point, the emergency fuel drain is complete.

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