Low-energy-consumption aircraft fuel supply system and method

Abstract

The invention discloses a low-energy-consumption aircraft fuel oil supply system and method, and relates to the field of aircraft fuel oil system design, the low-energy-consumption aircraft fuel oil supply system comprises an oil supply tank, an oil outlet is connected with an engine through an oil supply pipeline, the oil supply pipeline comprises two oil supply branches and an oil supply trunk, the two oil supply branches are arranged between the oil supply tank and the oil supply trunk in parallel, and the two oil supply branches are connected in parallel; each oil supply branch is provided with a pumping assembly. The comprehensive control unit comprises an operation time recording module and a calculation module, the operation time recording module and the calculation module are respectively used for recording respective operation durations of the two pumping assemblies and calculating an operation time difference value of the two pumping assemblies, and the comprehensive control unit controls the operation states of the pumping assemblies according to the operation time difference value; according to the fuel oil supply system, through automatic starting control of the two oil pumps, one oil pump works through an automatic starting control strategy, and extra energy loss caused by a double-oil-pump hot backup working mode is effectively reduced.

Description

Technical Field

[0001] The present invention belongs to the field of aircraft fuel system design, and more specifically, relates to a low-energy consumption aircraft fuel supply system and a supply method. Background Art

[0002] At present, with the accelerating evolution of the information-based war form, medium-altitude long-endurance unmanned aerial vehicles have become the core nodes of the modern battlefield situation awareness system, and their stay time in the air directly determines the continuity of battlefield information acquisition and the effectiveness of combat deployment. However, in the process of realizing high-altitude continuous cruise of current mainstream fuel-powered unmanned aerial vehicles, the problem of energy loss in the extraction of engine power has become increasingly prominent. The extraction of engine power not only leads to an increase in the fuel consumption rate of the engine, but also causes a decrease in the engine thrust, directly restricting the improvement of performance parameters such as the flight time and range of medium-altitude long-endurance unmanned aerial vehicles. The electric energy consumed by the aircraft fuel system comes from the engine shaft work extracted by the generator, which fundamentally stems from the power generated by the combustion of the aeroengine. There are large energy losses in the existing technology during the fuel supply process and the fuel transportation process, and the efficient utilization of the input energy of the fuel system cannot be achieved. Summary of the Invention

[0003] The object of the present invention is to provide a low-energy consumption aircraft fuel supply system and a supply method for the deficiencies existing in the prior art. The fuel supply system effectively reduces the additional energy loss brought by the dual-pump hot standby working mode by automatically starting and controlling two oil pumps and making one of the oil pumps work through an automatic start control strategy.

[0004] To achieve the above object, the present invention provides a low-energy consumption aircraft fuel supply system, including:

[0005] A fuel supply tank, the oil outlet of which is connected to the engine through a fuel supply pipeline. The fuel supply pipeline includes two fuel supply branches and a fuel supply main pipeline. The two fuel supply branches are arranged in parallel between the fuel supply tank and the fuel supply main pipeline, and a pumping component is respectively arranged on each fuel supply branch;

[0006] An integrated control unit, including an operation time recording module and a calculation module. The two modules are respectively used to record the respective operation durations of the two pumping components and to calculate the operation time difference between the two pumping components. The integrated control unit controls the operation state of the pumping components according to the operation time difference.

[0007] Further, it further includes an oil transfer tank. The oil outlet of the oil transfer tank is connected to the fuel inlet of an ejector pump. The fuel outlet of the ejector pump is connected to the oil inlet of the fuel supply tank. The high-pressure oil inlet of the ejector pump is connected to the fuel supply main pipeline through an oil transfer channel.

[0008] Further, the pumping assembly includes an oil pump and an oil pump check valve, and the oil pump is connected to the integrated control unit through an oil pump controller.

[0009] Further, an engine inlet flow sensor and an engine inlet pressure sensor, both connected to the integrated control unit, are sequentially arranged on the main oil supply line.

[0010] Further, an oil delivery passage control valve connected to the integrated control unit is arranged on the oil delivery passage.

[0011] Further, an oil tank low oil level signaler connected to the integrated control unit is arranged in the oil tank, and an oil delivery pipeline flow sensor connected to the integrated control unit is arranged at the outlet of the oil tank.

[0012] The present invention also provides a low - energy - consumption aircraft fuel supply method, which uses the above - mentioned low - energy - consumption aircraft fuel supply system. The method includes:

[0013] In the ground state, after the integrated control unit receives the automatic start instruction of the pumping assembly, it controls according to the cumulative working hours of the two pumping assemblies;

[0014] When the difference between the cumulative working hours of the two pumping assemblies is higher than the limit value of t hours, the integrated control unit starts the pumping assembly with less working hours;

[0015] When the difference between the cumulative working hours of the two pumping assemblies is lower than the limit value of t hours, the integrated control unit randomly starts one of the pumping assemblies;

[0016] During flight, when the engine inlet pressure is lower than the minimum limit value, the integrated control unit starts both pumping assemblies simultaneously.

[0017] Further, the integrated control unit controls the opening and closing of the oil delivery passage according to the parameters of the oil tank low oil level signaler.

[0018] Further, the integrated control unit adjusts the rotational speed of the pumping assembly according to the relationship between the engine inlet pressure, the oil delivery flow rate, and the engine fuel consumption.

[0019] When the integrated control unit starts one pumping assembly, the initial working rotational speed of the oil pump in the pumping assembly is set to 100% of its rated working rotational speed;

[0020] When the oil delivery passage is closed, the integrated control unit adjusts the working rotational speed of the oil pump to maintain the engine inlet pressure at 125% of the engine inlet minimum limit value.

[0021] When the oil delivery channel is opened, the integrated control unit adjusts the operating speed of the oil pump so that the engine inlet pressure is maintained at 125% of the lowest limit value of the engine inlet, and the oil output of the oil delivery tank is higher than the engine fuel consumption.

[0022] The present invention provides a low-energy aircraft fuel supply system and a supply method, and its beneficial effects are as follows:

[0023] 1. The fuel supply system also avoids the energy loss caused by the idling of the oil flow after the oil delivery of the oil delivery tank through the automatic control strategy of the oil delivery channel control valve, and finally realizes the low-energy operation of the oil pump through the automatic control of the operating speed of the working oil pump;

[0024] 2. During the flight of the fuel supply system, when the engine inlet pressure is lower than the lowest limit value, two oil pumps are automatically opened through the automatic start strategy. In addition, a manual start mode is set to realize the man-in-the-loop control and ensure the reliability of fuel supply to the engine;

[0025] 3. The fuel supply system controls the operation time deviation of the two oil pumps within a certain range through the automatic control strategy of the oil pump, which is convenient for maintaining the two oil pumps simultaneously and saves maintenance time.

[0026] Other features and advantages of the present invention will be described in detail in the following specific implementation part. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] By describing the exemplary embodiments of the present invention in more detail in conjunction with the drawings, the above and other objects, features, and advantages of the present invention will become more obvious. Among them, in the exemplary embodiments of the present invention, the same reference numerals generally represent the same components.

[0028] Figure 1 The working principle diagram of a low-energy aircraft fuel supply system according to an embodiment of the present invention is shown.

[0029] Description of the reference numerals in the drawings:

[0030] 1. First oil pump; 2. First one-way valve; 3. Second oil pump; 4. Second one-way valve; 5. Engine inlet flow sensor; 6. Engine inlet pressure sensor; 7. Low oil level signaler of the oil delivery tank; 8. Oil pipeline flow sensor; 9. First oil pump controller; 10. Second oil pump controller; 11. Oil delivery channel control valve; 12. Integrated control unit; 13. Ejector pump; 14. Oil delivery tank; 15. Fuel supply tank; 16. Engine. DETAILED DESCRIPTION OF THE INVENTION

[0031] The preferred embodiments of the present invention will be described in more detail below. Although the preferred embodiments of the present invention are described below, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to make the present invention more thorough and complete, and to fully convey the scope of the present invention to those skilled in the art.

[0032] The present invention provides a low-energy consumption aircraft fuel supply system, comprising:

[0033] A fuel supply tank, the oil outlet of which is connected to the engine through a fuel supply pipeline. The fuel supply pipeline includes two fuel supply branches and a fuel supply main line. The two fuel supply branches are arranged in parallel between the fuel supply tank and the fuel supply main line, and a pumping component is respectively arranged on each fuel supply branch;

[0034] An integrated control unit, including an operation time recording module and a calculation module. The two modules are respectively used to record the respective operation durations of the two pumping components and to calculate the operation time difference between the two pumping components. The integrated control unit controls the operation state of the pumping components according to the operation time difference.

[0035] Specifically, two fuel supply branches are arranged in parallel between the fuel supply tank and the engine in this supply system, and a pumping component is arranged on each fuel supply branch. The integrated control unit determines which pumping component pumps fuel to the engine according to the operation time of the pumping components. In this way, by using one pumping component to supply fuel to the engine, compared with the dual fuel pump hot standby working mode, this supply system can reduce additional energy consumption. One pumping component can adjust the rotation speed to make the output fuel pressure meet the minimum limit value of the engine inlet pressure, which not only ensures the normal operation of the engine, but also effectively controls the energy consumption required by the pumping component. In the dual fuel pump hot standby working mode adopted by existing unmanned aerial vehicles, one fuel pump is in the working state, and the other fuel pump is in the state of being ready to start at any time. In this way, both fuel pumps are in the hot start state, so the energy consumption avoidance of the fuel pumps will be greater than that of the supply system of this application.

[0036] Furthermore, it further includes a fuel transfer tank. The oil outlet of the fuel transfer tank is connected to the fuel inlet of the ejector pump, the fuel outlet of the ejector pump is connected to the oil inlet of the fuel supply tank, and the high-pressure oil inlet of the ejector pump is connected to the fuel supply main line through an oil transfer channel.

[0037] Specifically, when this supply system supplies fuel to the engine, it also first consumes the fuel in the fuel transfer tank to provide power for the engine. The fuel in the fuel transfer tank is sent to the fuel supply tank through the ejector pump, and then sent to the engine by the fuel supply tank and the pumping component. However, in order to enable the ejector pump to send the fuel in the fuel transfer tank into the fuel supply tank, a part of the fuel pumped out by the pumping component enters the fuel channel from the fuel supply main line, and then the high-pressure fuel is sent into the ejector pump through the fuel channel, so that the ejector pump can supply fuel normally.

[0038] Further, the pumping assembly includes an oil pump and an oil pump check valve, and the oil pump is connected to the integrated control unit through an oil pump controller.

[0039] Specifically, the fuel discharged from the fuel supply tank needs to be pressurized by the oil pump to meet the pressure requirements of the engine, so that the engine can operate normally. Moreover, an oil pump check valve is provided on the fuel supply branch to ensure that the fuel does not flow back on the fuel supply branch, so that the fuel pressure will not be affected, and the oil pump does not need to consume extra energy.

[0040] Further, a low fuel level signaler connected to the integrated control unit is provided in the fuel supply tank, and a fuel pipeline flow sensor connected to the integrated control unit is provided at the outlet of the fuel supply tank.

[0041] Further, a fuel supply passage control valve connected to the integrated control unit is provided on the fuel supply passage.

[0042] Further, an engine inlet flow sensor and an engine inlet pressure sensor connected to the integrated control unit are sequentially provided on the main fuel supply line.

[0043] Specifically, after the oil pump is started, it is necessary to identify the fuel reserve in the fuel supply tank through the low fuel level signaler in the fuel supply tank. When the fuel in the fuel supply tank is sufficient, the fuel in the fuel supply tank can be first discharged to the fuel supply tank and finally supplied to the engine; when the engine is running with the fuel in the fuel supply tank, it is necessary to open the fuel supply passage, and the high-pressure fuel in the fuel supply passage is sent to the ejector pump. In this way, under the action of the high-pressure fuel, the ejector pump can send the fuel in the fuel supply tank to the fuel supply tank. In this case, the fuel volume in the fuel supply tank will not decrease. In addition to pressurizing the fuel in the fuel supply tank to the engine inlet pressure value, the oil pump also needs to give a part of the pressure of the fuel discharged from the oil pump to the fuel supply passage, so that the ejector pump can continuously pump the fuel in the fuel supply tank into the fuel supply tank, and the oil pump does not need to operate at full load, only the fuel pressure pumped out by the oil pump needs to be not less than 125% of the engine inlet pressure. In this way, the monitoring of the fuel pressure value needs to rely on the engine inlet pressure sensor, and it is also necessary to ensure that the fuel volume discharged from the fuel supply tank is greater than the fuel consumption of the engine during operation. In this way, the monitoring of the fuel discharge volume from the fuel supply tank needs to rely on the fuel pipeline flow sensor.

[0044] The present invention also provides a low-energy consumption aircraft fuel supply method, which uses the above-mentioned low-energy consumption aircraft fuel supply system. The method includes:

[0045] In the ground state, after the integrated control unit receives the automatic start instruction of the pumping assembly, it is controlled according to the cumulative working time of the two pumping assemblies;

[0046] When the difference in the cumulative working hours of the two pumping components is higher than the limit value of t hours, the integrated control unit starts the pumping component with less working hours;

[0047] When the difference in the cumulative working hours of the two pumping components is lower than the limit value of t hours, the integrated control unit randomly starts one of the pumping components;

[0048] During flight, when the engine inlet pressure is lower than the minimum limit value, the integrated control unit starts both pumping components simultaneously.

[0049] Specifically, the value range of the difference t hours is 50 to 100 hours, and it can be freely set according to the drone operator.

[0050] When the supply system controls the start of the oil pump, the control mode is divided into an automatic start mode and a manual start mode, and the oil pump shutdown mode is a manual shutdown mode. After one oil pump works, the oil pump speed can be automatically adjusted according to the relationship between the engine inlet pressure, the oil delivery flow rate, and the engine fuel consumption. When the control mode is the manual control mode, it includes a first oil pump opening instruction, a second oil pump opening instruction, a first oil pump closing instruction, and a second oil pump closing instruction. After the integrated control unit sends the first oil pump opening instruction, the first oil pump is powered on to work; after the integrated control unit sends the second oil pump opening instruction, the second oil pump is powered on to work; after the integrated control unit sends the first oil pump closing instruction, the first oil pump is powered off and stops working; after the integrated control unit sends the second oil pump closing instruction, the second oil pump is powered off and stops working.

[0051] Furthermore, the integrated control unit controls the opening and closing of the oil delivery channel according to the parameters of the low oil level signaler of the oil delivery tank.

[0052] Furthermore, the integrated control unit adjusts the speed of the pumping component according to the relationship between the engine inlet pressure, the oil delivery flow rate, and the engine fuel consumption.

[0053] When the integrated control unit starts a pumping component, the initial working speed of the oil pump in the pumping component is set to 100% of its rated working speed;

[0054] When the oil delivery channel is closed, the integrated control unit adjusts the working speed of the oil pump to maintain the engine inlet pressure at 125% of the minimum engine inlet limit value;

[0055] When the oil delivery channel is open, the integrated control unit adjusts the working speed of the oil pump to maintain the engine inlet pressure at 125% of the minimum engine inlet limit value and make the oil output of the oil delivery tank higher than the engine fuel consumption.

[0056] Specifically, when the fuel supply system pumps fuel to the engine, first, according to the running time of the fuel pump, which fuel pump to work is selected. The fuel starts one fuel pump and adjusts it to 100% of the working speed, which can ensure the normal operation of the engine and ensure that the inlet pressure value of the engine does not exceed the minimum high limit value of the engine, thus ensuring the safe operation of the engine. To effectively reduce the energy consumption of the fuel pump, according to the opening and closing conditions of the oil delivery channel, the working speed of the fuel pump is reduced to a reasonable range. When the oil delivery channel is open, the fuel pressure pumped out by the fuel pump should not only meet 125% of the minimum limit value of the engine inlet pressure, but also part of the fuel needs to be input into the oil delivery channel to make the fuel pressure in the oil delivery channel higher than the fuel pressure in the fuel tank. In this way, the fuel in the fuel tank can be sent into the fuel supply tank through the ejector pump. At this time, all the fuel required by the engine is provided by the fuel tank, and the fuel output of the fuel tank is greater than the fuel consumption of the engine. When the oil delivery channel is closed, the ejector pump stops working, and the fuel pump can only pump the fuel in the fuel supply tank into the engine. The working speed of the fuel pump only needs to reach that the fuel pressure pumped out is not less than 125% of the minimum limit value of the engine inlet. In this way, through the above low-energy aircraft fuel supply system and supply method, based on the set automatic start control strategy of the fuel pump, the automatic control strategy of the oil delivery channel, and the fuel pump speed control strategy, low-energy fuel supply can be realized on the premise of stably supplying fuel to the engine.

[0057] In one embodiment, the minimum limit value and the maximum limit value of the inlet pressure value of the engine are 30 kPa to 300 kPa respectively. In this case, it only needs to maintain the fuel pressure pumped out by the fuel pump above 37.5 kPa.

[0058] Embodiment

[0059] As Figure 1 shown, the present invention provides a low-energy aircraft fuel supply system, including:

[0060] A fuel supply tank 15, the oil outlet of which is connected to the engine 16 through an oil supply pipeline. The oil supply pipeline includes two oil supply branches and an oil supply main pipeline. The two oil supply branches are arranged in parallel between the fuel supply tank 15 and the oil supply main pipeline, and a pumping component is respectively arranged on each oil supply branch;

[0061] A fuel tank 14, the oil outlet of which is connected to the fuel inlet of the ejector pump 13. The fuel outlet of the ejector pump 13 is connected to the oil inlet of the fuel supply tank 15. The high-pressure oil inlet of the ejector pump 13 is connected to the oil supply main pipeline through an oil delivery channel;

[0062] An integrated control unit 12, which controls each pumping component according to the fuel pressure value in the oil supply main pipeline, the fuel flow value in the oil supply main pipeline, the opening and closing state of the oil delivery channel, and the fuel level value in the fuel tank.

[0063] In this embodiment, the pumping assembly on the first fuel supply branch includes a first oil pump 1 and a first check valve 2 of the oil pump, and the pumping assembly on the second fuel supply branch includes a second oil pump 3 and a second check valve 4 of the oil pump. The first oil pump 1 and the second oil pump 2 are respectively connected to the integrated control unit 12 through a first oil pump controller 9 and a second oil pump controller 10.

[0064] In this embodiment, the oil pump controller is divided into a manual control mode and an automatic control mode.

[0065] In this embodiment, an engine inlet flow sensor 5 and an engine inlet pressure sensor 6, both connected to the integrated control unit 12, are sequentially arranged on the fuel supply main line.

[0066] In this embodiment, an oil pipeline control valve 11 connected to the integrated control unit 12 is arranged on the oil transmission channel.

[0067] In this embodiment, an oil tank low oil level signaler 7 connected to the integrated control unit 12 is arranged in the oil tank 14, and an oil pipeline flow sensor 8 connected to the integrated control unit 12 is arranged at the outlet of the oil tank 14.

[0068] The present invention also provides a low - energy - consumption aircraft fuel supply method. Using the above - mentioned low - energy - consumption aircraft fuel supply system, the method includes:

[0069] According to the running time difference between the two pumping assemblies, the integrated control unit 12 controls a certain fuel supply branch to supply fuel to the fuel supply main line;

[0070] According to the fuel level in the oil tank 14, the integrated control unit 12 controls the opening and closing state of the oil transmission channel;

[0071] According to the opening and closing state of the oil transmission channel, the integrated control unit 12 controls the running parameters of the pumping assembly on the fuel supply branch for fuel supply.

[0072] In this embodiment, controlling a certain fuel supply branch to supply fuel according to the running time difference between the two pumping assemblies includes:

[0073] In the ground state, when the running time difference between the first oil pump 1 and the second oil pump 3 is greater than t hours, the integrated control unit 12 starts the oil pump with less running time. When the running time difference between the two oil pumps is less than t hours, the integrated control unit randomly starts one of the oil pumps;

[0074] During flight, when the fuel pressure value in the fuel supply main line is lower than the minimum limit value, both oil pumps run simultaneously.

[0075] In this embodiment, controlling the opening and closing state of the oil transmission channel according to the fuel level in the oil tank 14 includes:

[0076] When the oil level in the oil supply tank 14 is lower than the set threshold value, the oil supply channel is closed;

[0077] When the oil level in the oil supply tank 14 is higher than the set threshold value, the oil supply channel is opened.

[0078] In this embodiment, controlling the operating parameters of the pumping assembly according to the opening and closing state of the oil supply channel includes:

[0079] When the integrated control unit 12 starts a certain oil pump, the initial operating speed of the started oil pump is set to 100% of its rated operating speed;

[0080] When the oil supply channel is closed, the integrated control unit 12 adjusts the operating speed of the oil pump to maintain the engine inlet pressure at 125% of the minimum limit value of the engine inlet;

[0081] When the oil supply channel is opened, the integrated control unit 12 adjusts the operating speed of the oil pump to maintain the engine inlet pressure at 125% of the minimum limit value of the engine inlet and make the oil output of the oil supply tank higher than the engine fuel consumption.

[0082] In summary, when the fuel supply system supplies fuel to the engine, it is necessary to first start a fuel pump to send the fuel in the fuel tank 14 and the supply fuel tank 15 into the engine 16. When the fuel pressure output by a fuel pump is higher than the minimum limit value of the engine, it is not necessary to start two fuel pumps simultaneously for fuel supply. Otherwise, it is necessary to start the first fuel pump 1 and the second fuel pump 3 simultaneously to ensure normal fuel supply to the engine and improve the reliability of fuel supply to the engine. When only one fuel pump needs to be started for pumping fuel, it is necessary to compare the cumulative working hours of the first fuel pump 1 and the second fuel pump 3 in advance. When the difference between the two fuel pumps is greater than t hours, start the fuel pump with less cumulative working hours for pumping fuel. When the difference between the two fuel pumps is less than t hours, randomly select a fuel pump for pumping fuel.When the oil pump starts to pump oil to the engine, at the beginning, the working speed of the oil pump is adjusted to 100% state, so that the fuel pressure pumped out by the oil pump is greater than the minimum limit value of the engine inlet pressure; then, the integrated control unit 12 monitors the fuel level in the fuel tank 14 through the low fuel level signaler 7 of the fuel tank. When the fuel in the fuel tank 14 is higher than the low fuel level signaler 7 of the fuel tank, the fuel transfer passage control valve 11 can be opened. In this way, a part of the fuel on the fuel supply main line will enter the ejector pump 13 through the fuel passage. The ejector pump 13 also has fuel from the fuel tank 14. The fuel entering the ejector pump 13 through the fuel passage has a certain pressure. In this way, the fuel in the fuel tank 14 can be ejected into the fuel supply tank 15 through the high-pressure fuel passage in the ejector pump 13, and it is ensured that the fuel output from the fuel tank 14 monitored by the fuel pipeline flow sensor 8 is greater than the fuel consumption of the engine, so that the inlet pressure value of the engine can be maintained at 125% of the minimum limit value. While ensuring the normal operation of the engine, the speed of the oil pump is reduced as much as possible, thereby reducing the energy consumption of the oil pump; however, when the fuel in the fuel tank 14 is lower than the low fuel level signaler 7 of the fuel tank, the fuel transfer passage control valve 11 needs to be closed. In this way, all the fuel for the operation of the engine 16 is provided by the fuel supply tank 15. The operating oil pump adjusts its speed under the control of the integrated control unit 12 and sends the fuel in the fuel supply tank 15 into the engine 16, as long as it is ensured that the inlet pressure value of the engine is maintained at 125% of the minimum limit value. In this way, the speed of the oil pump can also be effectively controlled, thereby achieving the effect of reducing the energy consumption of the oil pump; in addition, when the oil pump starts to operate and pump fuel to the engine, the working speed of the oil pump reaches 100% of the rated working speed. Then, according to the opening and closing conditions of the fuel transfer passage, the working speed of the oil pump is reduced to the minimum speed requirement, as long as it is ensured that the inlet pressure value of the engine is maintained at 125% of the minimum limit value. The working speed of the oil pump when the fuel transfer passage is open is higher than the working speed of the oil pump when the fuel transfer passage is closed. This is because when the fuel transfer passage is open, the fuel pressure pumped out by the oil pump not only needs to meet the requirement of the engine inlet pressure value, but also needs to reserve fuel pressure for the fuel transfer passage, so that the fuel transfer passage discharges a high-pressure fuel into the ejector pump, thereby pumping the fuel in the fuel tank into the fuel supply tank.

[0083] The embodiments of the present invention have been described above. The above description is exemplary and not exhaustive, and is not limited to the disclosed embodiments. Many modifications and variations are obvious to those of ordinary skill in the art in the technical field without departing from the scope and spirit of the described embodiments.

Claims

1. A low energy consumption aircraft fuel supply system, characterized in that: include: A fuel supply tank, the fuel outlet of which is connected to the engine through a fuel supply pipeline, the fuel supply pipeline comprising two fuel supply branches and a fuel supply trunk, the two fuel supply branches being arranged in parallel between the fuel supply tank and the fuel supply trunk, and each fuel supply branch being respectively provided with a pumping assembly; The integrated control unit includes an operating time recording module and a calculation module, wherein the two modules are respectively used to record the operating time of each of the two pumping components and to calculate the operating time difference between the two pumping components. The integrated control unit controls the operating status of the pumping components according to the operating time difference.

2. The low-energy aircraft fuel supply system according to claim 1, characterized in that: It also includes an oil delivery tank, the oil outlet of the oil delivery tank is connected to the fuel inlet of the ejector pump, the fuel outlet of the ejector pump is connected to the oil inlet of the oil supply tank, and the high-pressure oil inlet of the ejector pump is connected to the oil supply trunk line through an oil delivery channel.

3. The low energy consumption aircraft fuel supply system according to claim 1, characterized in that: The pumping assembly includes an oil pump and an oil pump one-way valve, and the oil pump is connected to the integrated control unit through an oil pump controller.

4. The low energy consumption aircraft fuel supply system according to claim 1, characterized in that: The oil supply trunk line is provided with an engine inlet flow sensor and an engine inlet pressure sensor connected to the integrated control unit in sequence.

5. The low energy consumption aircraft fuel supply system according to claim 2, characterized in that: The oil delivery channel is provided with an oil delivery channel control valve connected to the integrated control unit.

6. The low energy consumption aircraft fuel supply system according to claim 2, characterized in that: The oil tank is provided with an oil tank low oil level signaler connected to the integrated control unit, and the outlet of the oil tank is provided with an oil pipeline flow sensor connected to the integrated control unit.

7. A low-energy aircraft fuel supply method, using the low-energy aircraft fuel supply system according to any one of claims 1 to 6, characterized in that: The method includes: In the ground state, after receiving the automatic start command of the pumping assembly, the integrated control unit controls the two pumping assemblies according to the accumulated working time; When the difference between the accumulated working time of the two pumping components is higher than the limit value t hours, the integrated control unit starts the pumping component with less working time; When the difference between the accumulated working time of the two pumping components is lower than the limit value t hours, the integrated control unit randomly starts one of the pumping components; During flight, when the engine inlet pressure falls below the minimum limit, the integrated control unit starts both pumping assemblies simultaneously.

8. The low-energy consumption aircraft fuel supply method according to claim 7, characterized in that: The integrated control unit controls the opening and closing of the oil delivery channel according to the parameters of the low oil level signal device of the oil delivery tank.

9. The low-energy consumption aircraft fuel supply method according to claim 8, characterized in that: The integrated control unit adjusts the speed of the pumping components according to the relationship between the engine inlet pressure, oil flow and engine consumption. When the integrated control unit starts a pumping assembly, the initial operating speed of the oil pump in the pumping assembly is set to 100% of its rated operating speed; When the oil delivery channel is closed, the integrated control unit adjusts the operating speed of the oil pump to maintain the engine inlet pressure at 125% of the minimum limit of the engine inlet; When the oil delivery channel is opened, the integrated control unit adjusts the operating speed of the oil pump to maintain the engine inlet pressure at 125% of the engine inlet minimum limit and to make the oil output of the oil delivery tank higher than the engine fuel consumption.

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