High-stability supersonic target aircraft fuel system and oil sequence management method thereof

Abstract

This invention belongs to the field of target drone fuel systems, specifically relating to a high-stability supersonic target drone fuel system and its fuel sequence management method. The system includes a fuselage fuel tank, a first solenoid valve, a second solenoid valve, a pressurized fuel tank, a fuel pump, an overflow valve, an engine pump, a monitoring module, and a control module. The fuselage fuel tank comprises three sets of fuel tanks arranged sequentially. The first set of fuel tanks is located in the forward section of the target drone fuselage, while the second and third sets are respectively located in the fuel tanks in the middle of the target drone fuselage, positioned before and after the theoretical center of mass of the target drone. This invention places the first set of fuel tanks in the forward section of the fuselage. The fuel system prioritizes consuming fuel from the first set of tanks to adjust for the forward shift of the center of mass after booster separation, ensuring that the stability of the target drone after booster separation remains within a controllable range. Furthermore, because the first set of fuel tanks is positioned forward of the center of mass, only a small space in the forward section is required to complete the overall center of mass adjustment.

Description

Technical Field

[0001] This invention relates to a target drone fuel system, specifically to a high-stability supersonic target drone fuel system and its fuel sequence management method. Background Technology

[0002] Target drones are a type of aircraft used as training targets. They are a type of unmanned aerial vehicle (UAV) that uses remote control or pre-set flight paths and patterns to simulate target objects during training.

[0003] Currently, existing target drones are mainly launched with ground boosters. After boost separation, the target drone's center of gravity tends to shift forward significantly, affecting its stability after boost separation. Furthermore, during supersonic flight, the target drone's focal point shifts backward with increasing speed, which can also impact its stability during the supersonic flight phase. Summary of the Invention

[0004] The purpose of this invention is to solve the technical problems of existing target drones where the center of mass shifts forward significantly after boost separation, which easily affects the stability of the target drone after boost separation; and the problem that the focus of the target drone shifts backward as the flight speed increases during supersonic flight, which easily affects the stability of the target drone during the supersonic flight phase. The invention provides a highly stable supersonic target drone fuel system and its fuel sequence management method.

[0005] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0006] A highly stable supersonic target drone fuel system, characterized by:

[0007] It includes the engine block fuel tank, the first solenoid valve, the second solenoid valve, the pressurized fuel tank, the fuel pump, the overflow valve, the engine pump, the monitoring module, and the control module;

[0008] The airframe fuel tank consists of three sets of fuel tanks arranged sequentially from the nose to the tail along the longitudinal axis of symmetry of the target drone fuselage; the first set of fuel tanks has at least one tank, and the second and third sets of fuel tanks each have at least two tanks, with multiple tanks in the same set connected in series; the first set of fuel tanks is located in the forward section of the target drone fuselage, and the second and third sets of fuel tanks are located in the fuel tanks in the middle of the target drone fuselage, respectively, and are located before and after the theoretical center of mass of the target drone;

[0009] The fuel inlets of the second and third fuel tanks are connected to one end of the first and second solenoid valves, respectively. The fuel inlet of the first fuel tank, the other ends of the first and second solenoid valves, and one end of the overflow valve are connected to each other and then connected to the input end of the fuel pump. The other end of the overflow valve is connected to the overflow end of the pressurized fuel tank and then connected to the fuel filler / extractor of the target machine together with the other end of the first solenoid valve.

[0010] The output end of the fuel pump is connected to one end of the pressurized fuel tank, and the other end of the pressurized fuel tank is connected to the turbojet engine fuel port through the engine pump. The pressurized fuel tank is used to create the local fuel supply pressure environment required to supply fuel to the turbojet engine, and the engine pump is used to pressurize the fuel input to the turbojet engine a second time.

[0011] The first monitoring end of the monitoring module is set on the overflow valve to monitor the fuel pressure at the overflow valve in real time. The second monitoring end is set between the pressurized fuel tank and the engine pump to monitor the amount of fuel consumed by the turbojet engine in real time. The third monitoring end is set at the front turbine of the turbojet engine to monitor the actual speed of the turbojet engine in real time. The fourth monitoring end is set on the target drone body to monitor the actual acceleration of the target drone in real time.

[0012] The input terminal of the control module is electrically connected to the output terminal of the monitoring module. The control terminal is electrically connected to the control terminals of the first solenoid valve, the second solenoid valve, the fuel pump, and the engine pump, respectively. The control module is used to control the start and stop of the fuel pump and the engine pump, control the opening and closing of the first and second solenoid valves according to the amount of fuel consumed by the turbojet engine, calculate the thrust change of the target machine according to the actual acceleration, and control the speed of the engine pump and the fuel pump in real time according to the current speed and thrust change of the turbojet engine, thereby adaptively adjusting the fuel supply flow and pressure of the turbojet engine.

[0013] Furthermore, the airframe fuel tank includes nine fuel tanks arranged sequentially from the nose to the tail along the longitudinal axis of symmetry of the target aircraft fuselage. The nine fuel tanks are divided into three groups. The first group has one fuel tank, and the second and third groups each have four fuel tanks, with the four fuel tanks in the second and third groups connected in series.

[0014] The oil port of the last oil tank in the second and third groups of four oil tanks connected in series is connected to one end of the first solenoid valve and the second solenoid valve, respectively.

[0015] Furthermore, the monitoring module includes a pressure sensor, a flow meter, a speed sensor, and an accelerometer;

[0016] The probe of the pressure sensor is mounted on the overflow valve, and its output is electrically connected to the first input of the control module to monitor the pressure in the pressurized oil tank.

[0017] The flow meter is installed between the pressurized oil tank and the engine pump. Its output end is electrically connected to the second input end of the control module to obtain the amount of oil consumed by the turbojet engine in real time.

[0018] The speed sensor is located inside the turbine at the front end of the turbojet engine, and its output is electrically connected to the third input of the control module to monitor the actual speed of the turbojet engine in real time.

[0019] The accelerometer is integrated into the control module and is used to monitor the actual acceleration of the target drone in real time.

[0020] Furthermore, the control module includes a fuel controller, a flight control unit, and an ECU that are electrically connected in sequence;

[0021] The input terminal of the fuel controller is electrically connected to the output terminals of the pressure sensor and the flow meter, respectively, and the control terminal is electrically connected to the control terminals of the fuel pump, the first solenoid valve, and the second solenoid valve, respectively.

[0022] The output of the engine pump is connected to the turbojet engine through the third solenoid valve, the input of the ECU is electrically connected to the output of the speed sensor, and the control terminal is electrically connected to the control terminals of the engine pump and the third solenoid valve respectively.

[0023] The accelerometer is integrated into the flight control unit. The flight control unit controls the opening and closing of the first and second solenoid valves through the fuel controller based on the amount of fuel consumed by the turbojet engine. It calculates the thrust change of the target drone based on the actual acceleration, controls the start and stop of the fuel pump and engine pump through the fuel controller and ECU, and controls the speed of the fuel pump and engine pump in real time through the fuel controller and ECU based on the current speed and thrust change of the turbojet engine, thereby adaptively adjusting the fuel supply flow and pressure of the turbojet engine.

[0024] Furthermore, the other end of the overflow valve is connected to the oil filling / extraction port of the target machine via a manual valve.

[0025] Furthermore, the other end of the pressurized oil tank is connected to the engine pump via an oil filter.

[0026] Furthermore, the pressurized oil tank includes a metal outer shell and a vacuum soft oil bladder disposed within the metal outer shell.

[0027] Furthermore, the first, second, and third sets of fuel tanks are all polyurethane rubber film split soft fuel tanks.

[0028] Meanwhile, the present invention also provides a fuel sequence management method for a high-stability supersonic target drone fuel system, which is characterized by including the following steps:

[0029] Step 1: When the target drone takes off with a boost, the first and second solenoid valves are closed by the control module, and fuel is supplied to the fuel pump through the first set of fuel tanks.

[0030] Step 2: The control module calculates the current remaining fuel level of the first fuel tank based on the fuel consumption of the turbojet engine. When the current remaining fuel level of the first fuel tank is less than the preset minimum fuel level, the control module controls the first solenoid valve to open, and fuel is supplied to the fuel pump through both the first and second fuel tanks. After the fuel in the first fuel tank is consumed, fuel is supplied to the fuel pump through the second fuel tank alone.

[0031] Step 3: The control module calculates the current remaining fuel level in the second fuel tank based on the fuel consumption of the turbojet engine. When the current remaining fuel level in the second fuel tank is less than the preset minimum fuel level, the control module controls the second solenoid valve to open, and fuel is supplied to the fuel pump through both the second and third fuel tanks. After the fuel in the second fuel tank is consumed, fuel is supplied to the fuel pump through the third fuel tank alone.

[0032] The beneficial effects of this invention are:

[0033] 1. This invention possesses the capability to adjust the stability of the target drone after boost-separation. The invention incorporates a first set of fuel tanks in the forward section of the fuselage. After the engine starts, the fuel system prioritizes consuming fuel from these first set of tanks to adjust for the forward shift of the center of gravity caused by boost-separation, ensuring that the target drone's stability remains within a controllable range after boost-separation. Furthermore, because the first set of fuel tanks is positioned relatively far from the center of gravity, only a small amount of space in the forward section is required to complete the overall adjustment of the drone's center of gravity.

[0034] 2. This invention possesses the ability to adjust stability during supersonic flight. Existing supersonic target drones, during supersonic flight, experience a significant rearward shift of the focal point, increasing stability and reducing handling characteristics, thus affecting flight performance. This invention places two sets of fuel tanks in the midsection of the fuselage. The second set of fuel tanks is positioned before the theoretical center of gravity of the target drone, and the third set is positioned after it. When the target drone begins cruise flight, the solenoid valve in the fuel circuit of the third set of fuel tanks closes, prioritizing the consumption of fuel from the second set of fuel tanks. This controls the rearward shift of the target drone's center of gravity, thereby reducing the stability impact caused by fuel consumption. Attached Figure Description

[0035] Figure 1 This is a schematic diagram of the arrangement of three sets of fuel tanks and pressurized fuel tanks in an embodiment of a high-stability supersonic target drone fuel system of the present invention;

[0036] Figure 2 This is a schematic diagram of an embodiment of a high-stability supersonic target drone fuel system according to the present invention.

[0037] In the diagram: 1-First solenoid valve, 2-Second solenoid valve, 3-Add / Extract fuel port, 4-Manual valve, 5-Relief valve, 6-Fuel pump, 7-Fuel controller, 8-Fuel filter, 9-Flow meter, 10-Engine pump, 11-Third solenoid valve, 12-Pressure sensor, 13-First fuel tank, 14-Second fuel tank, 15-Third fuel tank, 16-Pressurized fuel tank, 17-Flight control unit, 18-Turbojet engine, 19-ECU, 20-Speed ​​sensor, 21-Accelerometer. Detailed Implementation

[0038] To make the objectives, advantages, and features of the present invention clearer, the following detailed description of a high-stability supersonic target drone fuel system and its fuel sequence management method, in conjunction with the accompanying drawings and specific embodiments, will further illustrate the present invention. The advantages and features of the present invention will become clearer according to the following specific embodiments. It should be noted that the accompanying drawings are all in a very simplified form and use non-precise proportions, used only to facilitate and clarify the explanation of the embodiments of the present invention; secondly, the structures shown in the drawings are often part of the actual structure.

[0039] This embodiment of a high-stability supersonic target drone fuel system specifically includes a fuel tank, a first solenoid valve 1, a second solenoid valve 2, a pressurized fuel tank 16, a fuel pump 6, an overflow valve 5, an engine pump 10, a monitoring module, and a control module.

[0040] Specifically, in this embodiment, the airframe oil tank includes three sets of oil tanks arranged sequentially from the head to the tail along the longitudinal axis of symmetry of the target aircraft fuselage; the number of the first set of oil tanks 13 is at least one, the number of the second set of oil tanks 14 and the number of the third set of oil tanks 15 are at least two, and multiple oil tanks in the same set are connected in series in sequence through oil-resistant hoses.

[0041] Specifically, the first set of fuel tanks 13 is located in the front section of the target drone fuselage, the second set of fuel tanks 14 and the third set of fuel tanks 15 are respectively located in the fuel tanks in the middle of the target drone fuselage, and the second set of fuel tanks 14 is located in front of the theoretical center of mass of the target drone, and the third set of fuel tanks 15 is located behind the theoretical center of mass of the target drone.

[0042] See Figure 1 In a preferred embodiment of the present invention, the airframe oil tank includes nine oil tanks arranged sequentially from the head to the tail along the longitudinal symmetrical axis of the target aircraft fuselage, namely oil tank No. 1 to oil tank No. 9. The nine oil tanks are divided into three groups. The first group has one oil tank 13, and the second and third groups each have four oil tanks 15. That is, oil tanks No. 2-5 are the second group oil tanks 14, and oil tanks No. 6-9 are the third group oil tanks 15. The second group oil tanks No. 2-5 and the third group oil tanks No. 6-9 are connected in series. The oil port of oil tank No. 5 is the oil port of the second group oil tank 14, and the oil port of oil tank No. 9 is the oil port of the third group oil tank 15.

[0043] In a preferred embodiment of the present invention, all of the above-mentioned oil tanks are polyurethane rubber film split soft oil tanks.

[0044] The fuel inlets of the second and third fuel tanks 15 are connected to one end of the first solenoid valve 1 and the second solenoid valve 2 via oil-resistant hoses. The fuel inlet of the first fuel tank 13, the other ends of the first and second solenoid valves 1 and 2, and one end of the overflow valve 5 are interconnected via oil-resistant hoses, and then connected to the input end of the fuel pump 6 via oil-resistant hoses. The other end of the overflow valve 5 is connected to the overflow end of the pressurized fuel tank 16 via an oil-resistant hose, and then connected to the target's fuel filler / extractor port 3 via an oil-resistant hose and the other end of the first solenoid valve 1. A manual valve 4 is also provided between the other end of the overflow valve 5 and the target's fuel filler / extractor port 3 for easy manual control of the fuel circuit.

[0045] The pressurized fuel tank 16 specifically includes a metal outer shell and a vacuum soft fuel bladder disposed within the metal outer shell. In this embodiment, the metal outer shell is specifically an aluminum alloy shell, whose main function is to withstand the pressure of the fuel bladder after pressurization. The pressurized fuel tank 16 is located in the fuel tank in the middle of the target aircraft fuselage, and is located after fuel tank No. 9. One end of the pressurized fuel tank 16 is connected to the output end of the fuel pump 6 through an oil-resistant hose, and the other end is connected to one end of the fuel filter 8 through an oil-resistant hose. The main function of the fuel filter 8 is to filter impurities in the fuel. The other end of the fuel filter 8 is connected to one end of the flow meter 9 through an oil-resistant hose. The other end of the flow meter 9 is connected to the input end of the engine pump 10 through an oil-resistant hose. The main function of the engine pump 10 is to perform secondary pressurization on the fuel input to the turbojet engine 18. The output end of the engine pump 10 is connected to the turbojet engine 18 through a third solenoid valve 11.

[0046] The first monitoring end of the monitoring module is located at the overflow valve 5 to monitor the fuel pressure at the overflow valve 5, thereby obtaining the fuel pressure in the pressurized fuel tank 16. The second monitoring end is located between the oil filter 8 and the engine pump 10 to record the amount of fuel consumed by the turbojet engine 18, which is convenient for subsequent calculation of the remaining fuel in each fuel tank. The third monitoring end is located at the front turbine of the turbojet engine 18 to monitor the actual speed of the turbojet engine 18 in real time. The fourth monitoring end is located on the target drone body to monitor the actual acceleration of the target drone in real time.

[0047] Specifically, in this embodiment, the monitoring module includes a pressure sensor 12, a flow meter 9, a speed sensor 20, and an accelerometer 21. The probe of the pressure sensor 12 is mounted on the overflow valve 5, and its output is electrically connected to the first input of the control module to monitor the pressure in the pressurized oil tank 16. The flow meter 9 is located between the oil filter 8 and the engine pump 10, and its output is electrically connected to the second input of the control module to record the amount of oil consumed by the turbojet engine 18. The speed sensor 20 is located at the turbine inside the front end of the turbojet engine 18, and its output is electrically connected to the third input of the control module to monitor the actual speed of the turbojet engine 18 in real time. The accelerometer 21 is integrated inside the control module to monitor the actual acceleration of the target drone in real time.

[0048] The control terminal of the control module is connected to the control terminals of the first solenoid valve 1, the second solenoid valve 2, the third solenoid valve 11, the fuel pump 6, and the engine pump 10, respectively. It is used to control the opening and closing of the first solenoid valve 1, the second solenoid valve 2, and the third solenoid valve 11, as well as the start and stop of the fuel pump 6 and the engine pump 10. At the same time, it controls the speed of the engine pump 10 and the fuel pump 6 in real time according to the current speed of the turbojet engine 18, thereby adaptively adjusting the fuel supply flow and pressure of the turbojet engine 18.

[0049] Specifically, in this embodiment, the control module includes a fuel controller 7, a flight control unit 17, and an ECU 19; the input terminal of the fuel controller 7 is electrically connected to the output terminals of the pressure sensor 12 and the flow meter 9, respectively, and the control terminal is electrically connected to the control terminals of the fuel pump 6, the first solenoid valve 1, and the second solenoid valve 2; the output terminal of the engine pump 10 is connected to the turbojet engine 18 through the third solenoid valve 11; the input terminal of the ECU 19 is electrically connected to the output terminal of the speed sensor 20, and the control terminal is electrically connected to the control terminals of the engine pump 10 and the third solenoid valve 11, respectively.

[0050] Accelerometer 21 is integrated inside flight control unit 17. Flight control unit 17 is used to control the opening and closing of first solenoid valve 1 and second solenoid valve 2 through fuel controller 7 based on the amount of fuel consumed by turbojet engine 18. Based on the actual thrust change of the target drone calculated by accelerometer 21, it controls the start and stop of fuel pump 6 and engine pump 10 through fuel controller 7 and ECU 19. Based on the current speed and thrust change of turbojet engine 18, it controls the speed of fuel pump 6 and engine pump 10 in real time through fuel controller 7 and ECU 19, thereby adaptively adjusting the fuel supply flow and pressure of turbojet engine 18.

[0051] Before the fuel system is activated, open manual valve 4, and open the first solenoid valve 1 and the second solenoid valve 2 via an external power source, so that the entire fuel system is in a connected state.

[0052] All air in the fuel tank and fuel lines is extracted through the filler / extractor port 3. After the vacuum is drawn, fuel is added through the filler / extractor port 3. During the filling process, the first solenoid valve 1, the second solenoid valve 2, and the manual valve 4 are kept open throughout. After the filling is completed, the filler / extractor port 3 is closed, the manual valve 4 is closed, and the power supply to the first solenoid valve 1 and the second solenoid valve 2 is disconnected.

[0053] When the fuel system is working, the flight control unit 17 controls the fuel pump 6 to open through the fuel controller 7, pressurizes the fuel system, and the fuel in the pressurized fuel tank 16 flows through the oil filter 8 and the flow meter 9 to the engine pump 10, and then flows to the front of the third solenoid valve 11.

[0054] When the turbojet engine 18 starts working, the ECU 19 supplies power to the engine pump 10 and the third solenoid valve 11. Fuel from fuel tank 1 flows into the pressurized fuel tank 16 through the fuel pump 6. The fuel in the pressurized fuel tank 16 is pressurized a second time by the engine pump 10 and then flows into the turbojet engine 18 through the third solenoid valve 11. At this time, the fuel consumed is the fuel in fuel tank 1, and the center of gravity of the entire engine moves backward as fuel is consumed.

[0055] The flow meter 9 sends the current flow rate value to the fuel controller 7 in real time. The flight control unit 17 calculates the current remaining fuel in fuel tank 1 in real time. When the fuel in fuel tank 1 is about to run out, the flight control unit 17 controls the first solenoid valve 1 to open through the fuel controller 7, and fuel is supplied from fuel tank 1 and fuel tanks 2 to 5 together. After being pressurized by the fuel pump 6 and the engine pump 10, the fuel flows into the engine through the third solenoid valve 11. After the fuel in fuel tank 1 is exhausted, fuel is supplied from fuel tanks 2 to 5. At this time, the fuel consumed is the fuel in fuel tanks 2 to 5. The center of gravity of the entire aircraft moves backward as the fuel is consumed.

[0056] Similarly, the flight control unit 17 calculates the remaining fuel in tanks 2 to 5 in real time. When the fuel in tanks 2 to 5 is about to run out, the flight control unit 17 controls the second solenoid valve 2 to open through the fuel controller 7, and tanks 2 to 5 and tanks 6 to 9 start to supply fuel together. After being pressurized by the fuel pump 6 and the engine pump 10, the fuel flows into the turbojet engine 18 through the third solenoid valve 11. When the fuel in tanks 2 to 5 is exhausted, fuel is supplied from tanks 6 to 9. At this time, the fuel consumed is from tanks 6 to 9, and the center of gravity of the entire aircraft moves forward continuously as the fuel is consumed.

[0057] After the turbojet engine 18 stops working, the ECU 19 controls the engine pump 10 and the third solenoid valve 11 to de-energize, so that the fuel in the pressurized fuel tank 16 no longer flows into the turbojet engine 18. The flight control unit 17 controls the first solenoid valve 1, the second solenoid valve 2 and the fuel pump 6 to de-energize through the fuel controller 7, so that the fuel system stops working.

[0058] After the fuel system stops working, open the filler / extractor port 3, open the manual valve 4, open the first solenoid valve 1 and the second solenoid valve 2 through the external power supply, drain the remaining fuel through the filler / extractor port 3, close the filler / extractor port 3, and close the manual valve 4. The fuel system operation is now complete.

[0059] A method for managing the fuel sequence of the aforementioned high-stability supersonic target drone fuel system specifically includes the following steps:

[0060] Step 1: When the target drone takes off with boost, the first solenoid valve 1 and the second solenoid valve 2 are closed by the control module, and fuel is supplied to the fuel pump 6 through the No. 1 fuel tank. The mass of the front part of the target drone is reduced and the center of gravity of the target drone is moved backward, which effectively reduces the impact of boost separation on the stability of the whole aircraft.

[0061] Step 2: The flight control unit 17 calculates the current remaining fuel in fuel tank 1 based on the fuel consumption of the turbojet engine 18. When the current remaining fuel in fuel tank 1 is less than the preset minimum fuel level, the flight control unit 17 controls the first solenoid valve 1 to open and the second solenoid valve 2 to remain closed via the fuel controller 7. Fuel is first supplied to the fuel pump 6 through fuel tank 1 and fuel tanks 2 to 5. After the fuel in fuel tank 1 is consumed, fuel is supplied to the fuel pump 6 separately through fuel tanks 2 to 5 to control the target drone's center of gravity to shift backward, reducing the stability impact caused by the backward shift of the focus of supersonic flight.

[0062] Step 3: The flight control unit 17 calculates the current remaining fuel in tanks 2 to 5 based on the fuel consumption of the turbojet engine 18. When the current remaining fuel in tanks 2 to 5 is less than the preset minimum fuel level, the flight control unit 17 controls the second solenoid valve 2 to open through the fuel controller 7. First, fuel is supplied to the fuel pump 6 through tanks 2 to 5 and tanks 6 to 9. After the fuel in tanks 2 to 5 is consumed, fuel is supplied to the fuel pump 6 through tanks 6 to 9 alone until the target drone is recovered.

Claims

1. A high-stability supersonic target drone fuel system, characterized in that: It includes an engine oil tank, a first solenoid valve (1), a second solenoid valve (2), a pressurized oil tank (16), a fuel pump (6), an overflow valve (5), an engine pump (10), a monitoring module, and a control module; The target drone's fuel tanks comprise three sets of fuel tanks arranged sequentially from the nose to the tail along the longitudinal axis of symmetry of the target drone's fuselage. The first set of fuel tanks (13) consists of at least one tank, while the second set (14) and the third set (15) each consist of at least two tanks, connected in series within the same set. The first set of fuel tanks (13) is located in the forward section of the target drone's fuselage, while the second set (14) and the third set (15) are located in the fuel tanks in the middle of the target drone's fuselage, respectively before and after the theoretical center of mass of the target drone. The fuel inlets of the second set of fuel tanks (14) and the third set of fuel tanks (15) are connected to one end of the first solenoid valve (1) and the second solenoid valve (2), respectively. The fuel inlet of the first set of fuel tanks (13) and the first solenoid valve (1) are connected to... After the other end of the second solenoid valve (2) and one end of the overflow valve (5) are connected to each other, they are connected to the input end of the fuel pump (6); after the other end of the overflow valve (5) is connected to the overflow end of the pressurized fuel tank (16), it is connected to the other end of the first solenoid valve (1) and connected to the fuel filler / extractor (3) of the target machine; the output end of the fuel pump (6) is connected to one end of the pressurized fuel tank (16), and the other end of the pressurized fuel tank (16) is connected to the fuel port of the turbojet engine (18) through the engine pump (10). The pressurized fuel tank (16) is used to form the local fuel supply pressure environment required to supply fuel to the turbojet engine (18), and the engine pump (10) is used to perform secondary pressurization on the fuel input to the turbojet engine (18); The first monitoring terminal of the monitoring module is located on the overflow valve (5) to monitor the fuel pressure at the overflow valve (5) in real time. The second monitoring terminal is located between the pressurized fuel tank (16) and the engine pump (10) to monitor the amount of fuel consumed by the turbojet engine (18) in real time. The third monitoring terminal is located at the front turbine of the turbojet engine (18) to monitor the actual speed of the turbojet engine (18) in real time. The fourth monitoring terminal is located on the target drone body to monitor the actual acceleration of the target drone in real time. The input terminal of the control module is electrically connected to the output terminal of the monitoring module, and the control terminal is connected to the first solenoid valve. (1) The control terminals of the second solenoid valve (2), fuel pump (6) and engine pump (10) are electrically connected. The control module is used to control the start and stop of the fuel pump (6) and engine pump (10), control the opening and closing of the first solenoid valve (1) and the second solenoid valve (2) according to the amount of oil consumed by the turbojet engine (18), calculate the thrust change of the target machine according to the actual accelerometer (21), and control the speed of engine pump (10) and fuel pump (6) in real time according to the current speed and thrust change of turbojet engine (18), thereby adaptively adjusting the fuel supply flow and pressure of turbojet engine (18).

2. The high-stability supersonic target drone fuel system according to claim 1, characterized in that: The target drone's fuel tank includes nine fuel tanks arranged sequentially from the head to the tail along the longitudinal axis of symmetry of the target drone's fuselage. The nine fuel tanks are divided into three groups. The first group has one fuel tank (13), the second group (14) and the third group (15) each have four fuel tanks, and the four fuel tanks in the second and third groups are connected in series. The oil port of the last oil tank in the second and third groups of four oil tanks connected in series is connected to one end of the first solenoid valve (1) and the second solenoid valve (2), respectively.

3. A high-stability supersonic target drone fuel system according to claim 1 or 2, characterized in that: The monitoring module includes a pressure sensor (12), a flow meter (9), a speed sensor (20), and an accelerometer (21); The probe of the pressure sensor (12) is mounted on the overflow valve (5), and its output is electrically connected to the first input of the control module to monitor the pressure in the pressurized oil tank (16). The flow meter (9) is located between the pressurized oil tank (16) and the engine pump (10), and its output end is electrically connected to the second input end of the control module to obtain the amount of oil consumed by the turbojet engine (18) in real time. The speed sensor (20) is installed at the turbine inside the front end of the turbojet engine (18), and its output end is electrically connected to the third input end of the control module to monitor the actual speed of the turbojet engine (18) in real time. The accelerometer (21) is integrated inside the control module and is used to monitor the actual acceleration of the target machine in real time.

4. The high-stability supersonic target drone fuel system according to claim 3, characterized in that: The control module includes a fuel controller (7), a flight control unit (17), and an ECU (19) that are connected in sequence. The input terminal of the fuel controller (7) is electrically connected to the output terminals of the pressure sensor (12) and the flow meter (9), respectively, and the control terminal is electrically connected to the control terminals of the fuel pump (6), the first solenoid valve (1), and the second solenoid valve (2), respectively. The output end of the engine pump (10) is connected to the turbojet engine (18) through the third solenoid valve (11), the input end of the ECU (19) is electrically connected to the output end of the speed sensor (20), and the control end is electrically connected to the control end of the engine pump (10) and the third solenoid valve (11) respectively. The accelerometer (21) is integrated inside the flight control unit (17). The flight control unit (17) is used to control the opening and closing of the first solenoid valve (1) and the second solenoid valve (2) through the fuel controller (7) according to the amount of fuel consumed by the turbojet engine (18). It calculates the thrust change of the target drone according to the actual acceleration, controls the start and stop of the fuel pump (6) and the engine pump (10) through the fuel controller (7) and the ECU (19), and controls the speed of the fuel pump (6) and the engine pump (10) in real time through the fuel controller (7) and the ECU (19) according to the current speed and thrust change of the turbojet engine (18), thereby adaptively adjusting the fuel supply flow and pressure of the turbojet engine (18).

5. The high-stability supersonic target drone fuel system according to claim 1, characterized in that: The other end of the overflow valve (5) is connected to the oil filling / extraction port (3) of the target machine via a manual valve (4).

6. The high-stability supersonic target drone fuel system according to claim 5, characterized in that: The other end of the pressurized oil tank (16) is connected to the engine pump (10) via an oil filter (8).

7. The high-stability supersonic target drone fuel system according to claim 6, characterized in that: The pressurized oil tank (16) includes a metal outer shell and a vacuum soft oil bladder disposed inside the metal outer shell.

8. The high-stability supersonic target drone fuel system according to claim 7, characterized in that: The first group of oil tanks (13), the second group of oil tanks (14) and the third group of oil tanks (15) are all polyurethane rubber film split soft oil tanks.

9. A fuel sequence management method for a high-stability supersonic target drone fuel system according to any one of claims 1-8, characterized in that, Includes the following steps: Step 1: When the target drone takes off with a boost, the first solenoid valve (1) and the second solenoid valve (2) are closed by controlling the control module, and fuel is supplied to the fuel pump (6) through the first set of fuel tanks (13); Step 2: The control module calculates the current remaining fuel in the first fuel tank (13) based on the fuel consumption of the turbojet engine (18). When the current remaining fuel in the first fuel tank (13) is less than the preset minimum fuel level, the control module controls the first solenoid valve (1) to open. First, fuel is supplied to the fuel pump (6) through the first fuel tank (13) and the second fuel tank (14). After the fuel in the first fuel tank (13) is consumed, fuel is supplied to the fuel pump (6) through the second fuel tank (14) alone. Step 3: The control module calculates the current remaining fuel in the second fuel tank (14) based on the fuel consumption of the turbojet engine (18). When the current remaining fuel in the second fuel tank (14) is less than the preset minimum fuel level, the control module controls the second solenoid valve (2) to open. First, fuel is supplied to the fuel pump (6) through the second fuel tank (14) and the third fuel tank (15). After the fuel in the second fuel tank (14) is consumed, fuel is supplied to the fuel pump (6) through the third fuel tank (15) alone.

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