Self-adaptive supersonic speed target drone fuel system and control method thereof

Abstract

The invention belongs to the field of target drone fuel oil systems, and particularly relates to a self-adaptive supersonic speed target drone fuel oil system and a control method thereof. The system comprises a machine body oil tank, a first electromagnetic valve, an overflow valve, a pressurization oil tank, a fuel pump, an engine pump, a monitoring module and a control module. The body fuel tank comprises a main fuel tank and an auxiliary fuel tank which are arranged in a fuel tank in the middle of the target drone body and located in front of and behind the theoretical mass center of the target drone respectively. The pressurization oil tank is additionally arranged in the fuel oil cabin, fuel oil in the engine body oil tank enters the pressurization oil tank for pressure maintaining after being pressurized by the fuel oil pump, and then oil is supplied to the engine from the pressurization oil tank, so that stable oil supply to the engine is achieved by establishing a local pressure environment instead of a large pressure environment of the whole fuel oil cabin, and therefore when a fuel oil system works, the fuel oil can be stably supplied to the engine. The oil supply flow and pressure are controlled in a closed-loop mode in real time through the control system according to the engine state.

Description

Technical Field

[0001] This invention relates to a target drone fuel system, and more specifically to an adaptive supersonic target drone fuel system and its control 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, the main power source for existing supersonic target drones is turbojet engines. Supersonic target drones have a large flight speed range, and the thrust of turbojet engines varies greatly accordingly. The fuel system adaptively adjusts the fuel supply flow and pressure according to the thrust changes of turbojet engines.

[0004] Most existing supersonic target drone fuel systems use bleed air pressurization to pressurize the fuel. For target drones with flat cross-sections and large-area blended wing-body layouts, which have very limited pressure resistance, using bleed air pressurization would greatly increase the difficulty of structural design. At the same time, because supersonic target drones have a wide speed range and a large range of speed variations, existing supersonic target drone fuel systems cannot match the fuel supply flow and pressure required for turbojet engines to operate in real time. Summary of the Invention

[0005] The purpose of this invention is to solve the technical problem that the bleed air pressurization method used in existing target drone fuel systems requires high structural strength of the fuel tank and is not suitable for target drones with large-area blended wing-body configurations. Instead, this invention provides an adaptive supersonic target drone fuel system and its control method.

[0006] To achieve the above objectives, the technical solution adopted by the present invention is as follows:

[0007] An adaptive supersonic target drone fuel system, characterized by:

[0008] It includes the engine block fuel tank, the first solenoid valve, the overflow valve, the pressurized fuel tank, the fuel pump, the engine pump, the monitoring module, and the control module;

[0009] The airframe fuel tanks include a main fuel tank and an auxiliary fuel tank located in the fuel compartment in the middle of the target drone's fuselage. The main fuel tank and the auxiliary fuel tank are located in front of and behind the theoretical center of mass of the target drone, respectively.

[0010] The fuel inlet of the main fuel tank and one end of the first solenoid valve are both connected to the input end of the fuel pump and to the fuel filler / sucker of the target machine. The other end of the first solenoid valve is connected to the fuel inlet of the auxiliary fuel tank.

[0011] The pressurized fuel tank is located in the fuel compartment in the middle of the target drone's fuselage, and is located after the auxiliary fuel tank. One end of the pressurized fuel tank is connected to the output end of the fuel pump, one end of the overflow valve is connected to the input end of the fuel pump, and the other end is connected to one end of the first solenoid valve and the overflow end of the pressurized fuel tank, respectively, to release pressure when the pressurized fuel tank is overpressurized. The fuel pump is used to pressurize and maintain the pressure of the fuel input into the pressurized fuel tank.

[0012] The pressurized fuel tank is used to create the local fuel supply pressure environment required to supply fuel to the turbojet engine. Its other end is connected to the fuel port of the turbojet engine through the engine pump, which is used to repressurize the fuel input to the turbojet engine.

[0013] The first monitoring end of the monitoring module is set at the overflow end of the pressurized oil tank to monitor the pressure at the overflow end of the pressurized oil tank in real time. The second monitoring end is set between the pressurized oil tank and the engine pump to monitor the amount of oil 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.

[0014] 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 fuel pump, and the engine pump, respectively. It is used to control the start and stop of the engine pump and the fuel pump, and to control the opening and closing of the first solenoid valve according to the amount of fuel consumed by the turbojet engine. At the same time, it controls the speed of the engine pump and the fuel pump in real time according to the current speed of the turbojet engine, thereby adaptively adjusting the fuel supply flow and pressure of the turbojet engine.

[0015] Furthermore, the engine pump has two output ends, and the oil ports of the turbojet engine include the ignition oil port and the main oil port;

[0016] Furthermore, the two output ends of the engine pump are connected to the ignition port and main fuel port of the turbojet engine through the second solenoid valve and the third solenoid valve, respectively. The control ends of the second solenoid valve and the third solenoid valve are electrically connected to the control end of the control module. The control system is used to control the second solenoid valve to open during ignition, supply fuel to the turbojet engine through the ignition port, and to control the second solenoid valve to automatically close after ignition. At the same time, it controls the third solenoid valve to automatically open after ignition, supply fuel to the turbojet engine through the main fuel port.

[0017] Furthermore, the monitoring module includes a pressure sensor, a flow meter, a speed sensor, and an accelerometer. The probe of the pressure sensor is located at the overflow end of the pressurized oil tank, and its output is electrically connected to the first input of the control module for real-time monitoring of the pressure in the pressurized oil tank. The flow meter is located between the pressurized oil tank and the engine pump, and its output is electrically connected to the second input of the control module for real-time monitoring of the amount of oil input to the engine pump input. The speed sensor is located at the turbine inside the front end of the turbojet engine, and its output is electrically connected to the third input of the control module for real-time monitoring of the actual speed of the turbojet engine. The accelerometer is integrated inside the control module for real-time monitoring of the actual acceleration of the target drone.

[0018] Furthermore, the control module includes a fuel controller, a flight control unit, and an ECU connected in sequence. 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 first solenoid valve and the fuel pump, respectively. The input terminal of the ECU is electrically connected to the output terminal of the speed sensor, and the control terminal is electrically connected to the control terminals of the engine pump, the second solenoid valve, and the third solenoid valve, respectively. An accelerometer is integrated inside the flight control unit. The flight control unit is used to control the opening and closing of the first solenoid valve through the fuel controller based on the amount of fuel consumed by the turbojet engine. At the same time, it calculates the thrust change of the target drone based on the actual acceleration, controls the start and stop of the fuel pump and the engine pump through the fuel controller and the ECU, and controls the speed of the fuel pump and the engine pump in real time through the fuel controller and the 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.

[0019] Furthermore, a manual valve is also provided between one end of the overflow valve and the first solenoid valve, and the overflow end of the pressurized oil tank is located between the manual valve and the overflow valve.

[0020] Furthermore, the output end of the pressurized oil tank is connected to the engine pump via an oil filter.

[0021] Furthermore, the pressurized oil tank includes a metal outer shell and a vacuum soft oil bladder disposed within the metal outer shell.

[0022] Furthermore, both the main fuel tank and the auxiliary fuel tank are polyurethane rubber film split flexible fuel tanks.

[0023] Furthermore, this invention also provides a control method for the above-mentioned adaptive supersonic target drone fuel system, which is characterized by including the following steps:

[0024] Step 1: The control module starts the operation of the fuel pump, engine pump, and monitoring module.

[0025] Step 2: The fuel in the main fuel tank is pressurized once by the fuel pump and sent to the pressurized fuel tank for pressure maintenance. Then, it is pressurized a second time by the engine pump and sent to the turbojet engine. At the same time, the monitoring module monitors the current amount of fuel consumed by the turbojet engine in real time and sends the data to the control module to obtain the current remaining amount of fuel in the main fuel tank.

[0026] Step 3: The control module determines in real time whether the current remaining fuel level in the main fuel tank is lower than the preset minimum fuel level. If so, the first solenoid valve is opened to supply fuel to the fuel pump through both the main fuel tank and the auxiliary fuel tank. If not, the first solenoid valve is kept closed.

[0027] Further, step 2 specifically involves the following steps: When the turbojet engine starts on the ground, the control module controls the second solenoid valve to open, and then the fuel pump pressurizes the fuel in the main fuel tank once and sends it to the pressurized fuel tank for pressure maintenance. After being pressurized a second time by the engine pump, it is sent to the ignition port of the turbojet engine. When the turbojet engine reaches a steady state, the control module controls the third solenoid valve to open and the second solenoid valve to close. The fuel is then pressurized a second time by the engine pump and sent to the main fuel port of the turbojet engine, and the turbojet engine operates normally. At the same time, the monitoring module monitors the current fuel consumption of the turbojet engine in real time and sends the data to the control module to obtain the current remaining fuel level in the main fuel tank.

[0028] The beneficial effects of this invention are:

[0029] 1. This invention adds a pressurized fuel tank to the fuel tank. The fuel in the engine tank is pressurized by the fuel pump and then enters the pressurized fuel tank for pressure maintenance. The fuel is then supplied to the engine from the pressurized fuel tank. This achieves a stable fuel supply to the engine by establishing a local pressure environment to replace the large pressure environment of the entire fuel tank. This makes it easier to control the fuel supply flow and pressure in real time through the control system based on the engine status when the fuel system is working.

[0030] 2. This invention possesses the capability for automatic ground starting of a turbojet engine. Currently, most target drones rely on ground fuel tanks for fuel supply during the ground starting phase of the turbojet engine. After the engine reaches a steady state, ground personnel must manually disconnect the ground-connected fuel line, posing a safety hazard. This invention adds an ignition fuel line to the fuel tank, connecting it to the turbojet engine's ignition port. By installing a solenoid valve at the front end of the engine's ignition port to control the on / off state of the ignition fuel line, automatic ground starting of the turbojet engine is achieved. Attached Figure Description

[0031] Figure 1 This is a structural schematic diagram of an embodiment of the present invention.

[0032] In the diagram: 1-Main fuel tank, 2-Auxiliary fuel tank, 3-First solenoid valve, 4-Add / Extract fuel port, 5-Fuel pump, 6-Overflow valve, 7-Manual valve, 8-Fuel controller, 9-Pressurized fuel tank, 10-Pressure sensor, 11-Fuel filter, 12-Flow meter, 13-Flight control unit, 14-Engine pump, 15-Second solenoid valve, 16-Third solenoid valve, 17-Turbojet engine, 18-Accelerometer, 19-ECU, 20-Speed ​​sensor. Detailed Implementation

[0033] To make the objectives, advantages, and features of the present invention clearer, the following detailed description of an adaptive supersonic target drone fuel system and its control method, in conjunction with the accompanying drawings and specific embodiments, is provided. 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; furthermore, the structures shown in the drawings are often part of the actual structure.

[0034] See Figure 1 This embodiment of an adaptive supersonic target drone fuel system mainly includes a fuselage fuel tank, a first solenoid valve 3, an overflow valve 6, a pressurized fuel tank 9, a fuel pump 5, a monitoring module, and a control module. Specifically, the fuselage fuel tank includes a main fuel tank 1 and an auxiliary fuel tank 2 located in the fuel compartment in the middle of the target drone's fuselage. Both the main fuel tank 1 and the auxiliary fuel tank 2 are separate flexible fuel tanks made of polyurethane rubber film, and both are kept in an atmospheric pressure environment.

[0035] Specifically, the main fuel tank 1 is positioned before the theoretical center of mass of the target drone, and the auxiliary fuel tank 2 is positioned after the theoretical center of mass of the target drone. The fuel inlet of the main fuel tank 1 and one end of the first solenoid valve 3 are both connected to the input end of the fuel pump 5 through a resistant hose, and are also connected to the fuel filler / sucker port 4 of the target drone through the resistant hose, so as to facilitate adding or sucking fuel to the main fuel tank 1 and the auxiliary fuel tank 2 through the fuel filler / sucker port 4 of the target drone. The other end of the first solenoid valve 3 is connected to the fuel inlet of the auxiliary fuel tank 2 through a resistant hose.

[0036] The pressurized fuel tank 9 specifically includes a metal outer shell and a vacuum soft fuel bladder housed 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 9 is located within the metal shell of the fuel tank in the middle of the target aircraft fuselage, and is situated after the auxiliary fuel tank 2. One end of the pressurized fuel tank 9 is connected to the output end of the fuel pump 5 via a resistant hose. The input end of the fuel pump 5 is connected to one end of the first solenoid valve 3 via a resistant hose in series with the overflow valve 6 and the manual valve 7. The overflow end of the pressurized fuel tank 9 is connected between the overflow valve 6 and the manual valve 7 via a resistant hose. The main function of the fuel pump 5 is to pressurize the fuel input into the pressurized fuel tank 9. The main function of the pressurized fuel tank 9 is to create the local fuel supply pressure environment required for supplying fuel to the turbojet engine 17. The main function of the overflow valve 6 is to release pressure when the pressurized fuel tank 9 is overpressurized, allowing fuel to return from the pressurized fuel tank 9 to the main fuel circuit via the overflow valve 6 and the manual valve 7.

[0037] The other end of the pressurized fuel tank 9 is connected to one end of the fuel filter 11 via an oil-resistant hose. The main function of the fuel filter 11 is to filter impurities in the fuel. The other end of the fuel filter 11 is connected to one end of the flow meter 12 via an oil-resistant hose. The other end of the flow meter 12 is connected to the input end of the engine pump 14 via an oil-resistant hose. The main function of the engine pump 14 is to repressurize the fuel input to the turbojet engine 17.

[0038] In this embodiment, the engine pump 14 has two output terminals, and the oil ports of the turbojet engine 17 are designated as the ignition port and the main oil port. The two output terminals of the engine pump 14 are connected to one end of the second solenoid valve 15 and the third solenoid valve 16 via oil-resistant hoses, respectively. The other ends of the second solenoid valve 15 and the third solenoid valve 16 are connected to the ignition port and the main oil port of the turbojet engine 17 via oil-resistant hoses, respectively. The control terminals of the second solenoid valve 15 and the third solenoid valve 16 are electrically connected to the control terminal of the control module, thereby controlling the second solenoid valve 15 to open during ignition to supply oil to the turbojet engine 17 through the ignition port, and controlling the second solenoid valve 15 to automatically close after ignition, while controlling the third solenoid valve 16 to automatically open after ignition to supply oil to the turbojet engine 17 through the main oil port.

[0039] The first monitoring end of the monitoring module is set at the overflow end of the pressurized oil tank 9 to monitor the pressure at the overflow end of the pressurized oil tank 9 in real time. The second monitoring end is set between the pressurized oil tank 9 and the engine pump 14 to monitor the amount of oil consumed by the turbojet engine 17 in real time. The third monitoring end is set at the front turbine of the turbojet engine 17 to monitor the actual speed of the turbojet engine 17 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, so that the thrust change of the target drone can be calculated by the subsequent control module.

[0040] Specifically, the monitoring module in this embodiment includes a pressure sensor 10, a flow meter 12, a speed sensor 20, and an accelerometer 18. The probe of the pressure sensor 10 is located at the overflow end of the pressurized fuel tank 9, and its output end is electrically connected to the input end of the fuel controller 8 to monitor the pressure in the pressurized fuel tank 9 in real time. The flow meter 12 is located between the oil filter 11 and the engine pump 14, and its output end is electrically connected to the input end of the fuel controller 8 to monitor the amount of fuel input to the input end of the engine pump 14 in real time. The speed sensor 20 is located at the turbine inside the front end of the turbojet engine 17, and its output end is electrically connected to the input end of the ECU 19 to monitor the actual speed of the turbojet engine 17 in real time. The accelerometer 18 is integrated inside the control module to monitor the actual acceleration of the target machine in real time.

[0041] 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 3, the second solenoid valve 15, the third solenoid valve 16, the fuel pump 5, and the engine pump 14, respectively. It is used to control the opening and closing of the first solenoid valve 3, the second solenoid valve 15, and the third solenoid valve 16, as well as the start and stop of the engine pump 14 and the fuel pump 5. At the same time, it controls the speed of the engine pump 14 and the fuel pump 5 in real time according to the current speed of the turbojet engine 17, thereby adaptively adjusting the fuel supply flow and pressure of the turbojet engine 17.

[0042] Specifically, the control module in this embodiment mainly includes a fuel controller 8, a flight control unit 13, and an ECU 19; the input terminal of the fuel controller 8 is electrically connected to the output terminals of the pressure sensor 10 and the flow meter 12, and the control terminal is electrically connected to the control terminals of the first solenoid valve 3 and the fuel pump 5; the control terminal of the flight control unit 13 is electrically connected to the fuel controller 8, and the accelerometer 18 is integrated inside the flight control unit 13; 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 14, the second solenoid valve 15, and the third solenoid valve 16, respectively.

[0043] Before the fuel system is activated, open the manual valve 7 and open the first solenoid valve 3 via an external power source, so that the entire fuel system is in a connected state.

[0044] Air is extracted from the soft fuel bladder and fuel line through the filler / extractor port 4. After the soft fuel bladder is evacuated to a vacuum, fuel is added through the filler / extractor port 4. During the filling process, the first solenoid valve 3 and the manual valve 7 are kept open throughout. After the filling is completed, the filler / extractor port 4 is closed, the manual valve 7 is closed, and the power supply to the first solenoid valve 3 is disconnected.

[0045] Air is extracted from the soft fuel bladder and fuel line through the filler / extractor port 4. After the soft fuel bladder is evacuated to a vacuum, fuel is added through the filler / extractor port 4. During the filling process, the first solenoid valve 3 and the manual valve 7 are kept open throughout. After the filling is completed, the filler / extractor port 4 is closed, the manual valve 7 is closed, and the power supply to the first solenoid valve 3 is disconnected.

[0046] When the turbojet engine 17 is working normally, the fuel in the main fuel tank 1 flows into the pressurized fuel tank 9 through the fuel pump 5. After being pressurized twice, the fuel in the pressurized fuel tank 9 flows into the main fuel port of the turbojet engine 17 through the oil filter 11 and the third solenoid valve 16. The fuel controller 8 controls the speed of the fuel pump 5 and the engine pump 14 in real time according to the current speed of the turbojet engine 17 to adjust the fuel supply pressure and fuel supply flow.

[0047] When the fuel in the main fuel tank 1 is about to run out, the fuel controller 8 controls the first solenoid valve 3 to open, and the main fuel tank 1 and the auxiliary fuel tank 2 start to supply fuel together. After being pressurized by the fuel pump 5, the fuel enters the pressurized fuel tank 9 to maintain pressure. A local pressure environment is established in the pressurized fuel tank 9. After being pressurized a second time by the engine pump 14, the fuel flows into the turbojet engine 17 through the third solenoid valve 16. After the fuel in the main fuel tank 1 is exhausted, the auxiliary fuel tank 2 supplies fuel separately.

[0048] After the turbojet engine 17 stops working, the ECU 19 energizes the engine pump 14 and the third solenoid valve 16, and the fuel in the pressurized fuel tank 9 no longer flows into the turbojet engine 17. The flight control unit 13 energizes the first solenoid valve 3 and the fuel pump 5 through the fuel controller 8, and the fuel system stops working.

[0049] After the fuel system stops working, open the filler / extractor port 4, open the manual valve 7, open the first solenoid valve 3 through the external power supply, drain the remaining fuel through the filler / extractor port 4, close the filler / extractor port 4, and close the manual valve 7. The fuel system operation is now complete.

[0050] This embodiment of a control method for an adaptive supersonic target drone fuel system specifically includes the following steps:

[0051] Step 1: The control module starts the operation of fuel pump 5, engine pump 14 and monitoring module;

[0052] Step 2: The fuel in the main fuel tank 1 is pressurized once by the fuel pump 5 and sent to the pressurized fuel tank 9 for pressure maintenance. Then, it is pressurized a second time by the engine pump 14 and sent to the turbojet engine 17. At the same time, the current amount of fuel consumed by the turbojet engine 17 is monitored in real time by the monitoring module and sent to the control module to obtain the current remaining amount of fuel in the main fuel tank 1.

[0053] Step 3: When the control module determines that the current remaining fuel level in the main fuel tank 1 is lower than the preset minimum fuel level, it controls the first solenoid valve 3 to open, so that fuel is supplied to the fuel pump 5 through the main fuel tank 1 and the auxiliary fuel tank 2.

Claims

1. An adaptive supersonic target drone fuel system, characterized in that: comprising a body oil tank, a first electromagnetic valve (3), an overflow valve (6), a pressurized oil tank (9), a fuel pump (5), an engine pump (14), a monitoring module and a control module; the body oil tank comprises a main oil tank (1) and an auxiliary oil tank (2) arranged in the fuel cabin of the middle part of the target drone body, the main oil tank (1) and the auxiliary oil tank (2) are respectively located before and after the theoretical center of mass of the target drone; the oil port of the main oil tank (1) and one end of the first electromagnetic valve (3) are both connected with the input end of the fuel pump (5), and are both connected with the oil filling / extracting port (4) of the target drone, the other end of the first electromagnetic valve (3) is connected with the oil port of the auxiliary oil tank (2); the pressurized oil tank (9) is arranged in the fuel cabin of the middle part of the target drone body and is located after the auxiliary oil tank (2); one end of the pressurized oil tank (9) is connected with the output end of the fuel pump (5), one end of the overflow valve (6) is connected with the input end of the fuel pump (5), and the other end is respectively connected with one end of the first electromagnetic valve (3) and the overflow end of the pressurized oil tank (9), for pressure relief when the pressurized oil tank (9) is overpressure, the fuel pump (5) is used for pressurizing and pressure maintaining the fuel input into the pressurized oil tank (9); the other end of the pressurized oil tank (9) is connected with the oil port of the turbojet engine (17) through the engine pump (14), the pressurized oil tank (9) is used for forming a local oil supply pressure environment required for oil supply to the turbojet engine (17), and the engine pump (14) is used for secondary pressurizing the fuel input into the turbojet engine (17); the first monitoring end of the monitoring module is arranged at the overflow end of the pressurized oil tank (9) and is used for monitoring the pressure of the overflow end of the pressurized oil tank (9) in real time, the second monitoring end is arranged between the pressurized oil tank (9) and the engine pump (14) and is used for monitoring the oil consumption of the turbojet engine (17) in real time, the third monitoring end is arranged at the front end turbine of the turbojet engine (17) and is used for monitoring the actual speed of the turbojet engine (17) in real time, and the fourth monitoring end is arranged on the target drone body and is used for monitoring the actual acceleration of the target drone in real time; the input end of the control module is electrically connected with the output end of the monitoring module, the control end is electrically connected with the control end of the first electromagnetic valve (3), the fuel pump (5) and the engine pump (14), respectively, for controlling the opening and closing of the first electromagnetic valve (3) according to the oil consumption of the turbojet engine (17), calculating the thrust change of the target drone according to the actual acceleration, controlling the start and stop of the engine pump (14) and the fuel pump (5), and controlling the speed of the engine pump (14) and the fuel pump (5) in real time according to the current speed of the turbojet engine (17) and the thrust change, so as to adaptively adjust the oil supply flow and pressure of the turbojet engine (17).

2. The adaptive supersonic target drone fuel system according to claim 1, characterized in that: the engine pump (14) is provided with two output ends, and the oil port of the turbojet engine (17) comprises an ignition oil port and a main oil port. ​ ​ ​ ​ ​ ​ The two outputs of the engine pump (14) are connected with the ignition oil port and the main oil port of the turbojet engine (17) through the second electromagnetic valve (15) and the third electromagnetic valve (16) respectively, and the control ends of the second electromagnetic valve (15) and the third electromagnetic valve (16) are electrically connected with the control end of the control module respectively; The control system is used for controlling the second electromagnetic valve (15) to open at the ignition time, supplying oil for the turbojet engine (17) through the ignition oil port, and automatically closing the second electromagnetic valve (15) after the ignition is completed, while automatically opening the third electromagnetic valve (16) to supply oil for the turbojet engine (17) through the main oil port.

3. The adaptive supersonic target aircraft fuel system according to claim 2, characterized in that: The monitoring module comprises a pressure sensor (10), a flow meter (12), a rotational speed sensor (20) and an accelerometer (18); The probe of the pressure sensor (10) is arranged at the overflow end of the pressurized oil tank (9), and the output end thereof is electrically connected with the first input end of the control module, for monitoring the pressure in the pressurized oil tank (9) in real time; The flow meter (12) is arranged between the pressurized oil tank (9) and the engine pump (14), and the output end thereof is electrically connected with the second input end of the control module, for monitoring the oil quantity input to the input end of the engine pump (14) in real time; The rotational speed sensor (20) is arranged at the internal turbine of the front end of the turbojet engine (17), and the output end thereof is electrically connected with the third input end of the control module, for monitoring the actual rotational speed of the turbojet engine (17) in real time; The accelerometer (18) is integrated in the control module, for monitoring the actual acceleration of the target aircraft in real time.

4. The adaptive supersonic target aircraft fuel system according to claim 3, characterized in that: The control module comprises a fuel controller (8), a flight control unit (13) and an ECU (19) which are electrically connected in sequence; The input end of the fuel controller (8) is electrically connected with the output end of the pressure sensor (10) and the flow meter (12) respectively, and the control end thereof is electrically connected with the control end of the first electromagnetic valve (3) and the fuel pump (5) respectively; The input end of the ECU (19) is electrically connected with the output end of the rotational speed sensor (20), and the control end thereof is electrically connected with the control end of the engine pump (14), the second electromagnetic valve (15) and the third electromagnetic valve (16) respectively; The accelerometer (18) is integrated in the flight control unit (13); the flight control unit (13) is used for controlling the opening and closing of the first electromagnetic valve (3) through the fuel controller (8) according to the oil quantity consumed by the turbojet engine (17), calculating the thrust change of the target aircraft according to the actual acceleration, controlling the start and stop of the fuel pump (5) and the engine pump (14) through the fuel controller (8) and the ECU (19), and controlling the rotational speed of the fuel pump (5) and the engine pump (14) through the fuel controller (8) and the ECU (19) according to the current rotational speed of the turbojet engine (17) and the thrust change in real time, so as to adaptively adjust the oil supply flow and pressure of the turbojet engine (17).

5. The adaptive supersonic target drone fuel system according to any one of claims 1-4, characterized in that: A manual valve (7) is further arranged between the overflow valve (6) and one end of the first electromagnetic valve (3), and the overflow end of the pressurized fuel tank (9) is located between the manual valve (7) and the overflow valve (6).

6. The adaptive supersonic target drone fuel system according to claim 5, characterized in that: The output end of the pressurized fuel tank (9) is connected with the engine pump (14) through an oil filter (11).

7. The adaptive supersonic target drone fuel system according to claim 6, characterized in that: The pressurized fuel tank (9) comprises a metal shell and a vacuum soft fuel bag arranged in the metal shell.

8. The adaptive supersonic target drone fuel system according to claim 7, characterized in that: The main fuel tank (1) and the auxiliary fuel tank (2) are both polyurethane rubber film split soft fuel tanks.

9. A control method of the self-adapting supersonic target drone fuel system according to any one of claims 1-8, characterized in that, The method comprises the following steps: Step 1: Start the fuel pump (5), the engine pump (14) and the monitoring module by the control module; Step 2: Pressurize the fuel in the main fuel tank (1) once by the fuel pump (5), then send the fuel into the pressurized fuel tank (9) for pressure maintaining, and then pressurize the fuel again by the engine pump (14) and send the fuel into the turbojet engine (17); at the same time, monitor the current fuel consumption of the turbojet engine (17) by the monitoring module and send the fuel consumption into the control module to obtain the current remaining fuel amount of the main fuel tank (1); Step 3: If the current remaining fuel amount of the main fuel tank (1) is lower than the preset minimum fuel amount, control the first electromagnetic valve (3) to open and supply fuel to the fuel pump (5) by the main fuel tank (1) and the auxiliary fuel tank (2); if not, control the first electromagnetic valve (3) to keep closed.

10. The control method of the adaptive supersonic target drone fuel system according to claim 9, characterized in that: Step 2 specifically comprises: when the turbojet engine (17) starts on the ground, control the second electromagnetic valve (15) to open by the control module, then pressurize the fuel in the main fuel tank (1) once by the fuel pump (5), send the fuel into the pressurized fuel tank (9) for pressure maintaining, and then pressurize the fuel again by the engine pump (14) and send the fuel into the ignition oil port of the turbojet engine (17); when the turbojet engine (17) works to a steady state, control the third electromagnetic valve (16) to open and the second electromagnetic valve (15) to close by the control module, pressurize the fuel again by the engine pump (14) and send the fuel into the main oil port of the turbojet engine (17), and the turbojet engine (17) works normally; at the same time, monitor the current fuel consumption of the turbojet engine (17) by the monitoring module and send the fuel consumption into the control module to obtain the current remaining fuel amount of the main fuel tank (1).

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