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

Abstract

The invention belongs to the field of target drone fuel oil systems, and particularly relates to a high-stability supersonic target drone fuel oil system and an oil sequence management method thereof. The system comprises a machine body oil tank, a first electromagnetic valve, a second electromagnetic valve, a pressurization oil tank, a fuel pump, an overflow valve, an engine pump, a monitoring module and a control module. The engine body oil tank comprises three groups of oil tanks arranged in sequence; the first group of oil tanks are arranged at the front cabin section of the target drone body, and the second group of oil tanks and the third group of oil tanks are respectively arranged in the fuel oil cabin in the middle of the target drone body and are respectively positioned in front of and behind the theoretical mass center of the target drone. According to the invention, the first group of oil tanks are arranged at the front cabin section of the fuselage, and the fuel system preferentially consumes the fuel of the first group of oil tanks to adjust the forward movement of the center of mass caused by boosting separation, so that the stability of the target aircraft after boosting separation is ensured to be within a controllable range. And meanwhile, the arrangement position of the first group number oil tank is front of the mass center, so that the mass center adjustment of the whole aircraft can be completed by only occupying a very small space of a front cabin section.

Description

TECHNICAL FIELD

[0001] The present application relates to a target aircraft fuel system, in particular to a high-stability supersonic target aircraft fuel system and an oil sequence management method thereof. BACKGROUND

[0002] The target aircraft refers to a kind of aircraft as training target flying object, which simulates target flying object to achieve training purpose by using remote control or pre-set flight path and mode, and it is a kind of unmanned aerial vehicle.

[0003] At present, the existing target aircraft is mainly launched by ground boost, which can cause large forward movement of the mass center of the target aircraft after boost separation, affecting the stability of the target aircraft after boost separation. At the same time, when the target aircraft flies at supersonic speed, the focal point of the target aircraft moves backward with the increase of flight speed, which can easily affect the stability of the supersonic flight segment of the target aircraft. SUMMARY

[0004] The present application aims to solve the technical problems that the existing target aircraft can cause large forward movement of the mass center of the target aircraft after boost separation, which can easily affect the stability of the target aircraft after boost separation, and when the target aircraft flies at supersonic speed, the focal point of the target aircraft moves backward with the increase of flight speed, which can easily affect the stability of the supersonic flight segment of the target aircraft, and provides a high-stability supersonic target aircraft fuel system and an oil sequence management method thereof.

[0005] To achieve the above-mentioned purpose, the technical solution adopted by the present application is as follows:

[0006] A high-stability supersonic target aircraft fuel system, which is characterized in that:

[0007] It comprises a body oil tank, a first electromagnetic valve, a second electromagnetic valve, a pressurized oil tank, a fuel pump, an overflow valve, an engine pump, a monitoring module and a control module.

[0008] The body oil tank comprises three groups of oil tanks arranged in sequence from the nose to the tail along the longitudinal symmetry axis of the target aircraft fuselage. The number of the first group of oil tanks is at least one, and the number of the second group and the third group of oil tanks is at least two. The multiple oil tanks in the same group are connected in sequence. The first group of oil tanks is arranged in the front cabin section of the target aircraft fuselage, and the second group and the third group of oil tanks are arranged in the fuel cabin in the middle of the target aircraft fuselage, respectively located before and after the theoretical center of mass of the target aircraft.

[0009] The oil ports of the second group and the third group of oil tanks are connected with one end of the first electromagnetic valve and the second electromagnetic valve respectively. The oil port of the first group of oil tanks, the other end of the first electromagnetic valve and the second electromagnetic valve, and one end of the overflow valve are connected with each other and connected with the input end of the fuel pump. The other end of the overflow valve is connected with the overflow end of the pressurized oil tank, and the other end of the first electromagnetic valve is connected with the oil extraction port of the target aircraft.

[0010] The output end of the fuel pump is connected with one end of the pressurized oil tank, and the other end of the pressurized oil tank is connected with the oil inlet of the turbojet engine through the engine pump, the pressurized oil tank is used for forming a local fuel supply pressure environment required for supplying fuel to the turbojet engine, and the engine pump is used for re-pressurizing the fuel input to the turbojet engine;

[0011] The first monitoring end of the monitoring module is arranged on the overflow valve and is used for monitoring the fuel pressure at the overflow valve in real time, the second monitoring end is arranged between the pressurized oil tank and the engine pump and is used for monitoring the oil consumption of the turbojet engine in real time, the third monitoring end is arranged at the front end turbine of the turbojet engine and is used for monitoring the actual rotating speed of the turbojet engine in real time, and the fourth monitoring end is arranged on the target aircraft body and is used for monitoring the actual acceleration of the target aircraft in real time;

[0012] 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 ends of the first electromagnetic valve, the second electromagnetic valve, the fuel pump and the engine pump, the control module is used for controlling the start and stop of the fuel pump and the engine pump, the opening and closing of the first electromagnetic valve and the second electromagnetic valve are controlled according to the obtained oil consumption of the turbojet engine, the thrust change of the target aircraft is calculated according to the actual acceleration, and the rotating speed of the engine pump and the fuel pump is controlled in real time according to the current rotating speed of the turbojet engine and the thrust change, so that the fuel supply flow and pressure of the turbojet engine are adaptively adjusted.

[0013] Further, the aircraft oil tank comprises nine oil tanks arranged in sequence from the nose to the tail along the longitudinal symmetry axis of the target aircraft body, the nine oil tanks are divided into three groups, the number of the first group of oil tanks is one, the number of the second group of oil tanks and the third group of oil tanks is four, and the four oil tanks of the second group and the third group are sequentially connected in series.

[0014] The oil inlets of the last one of the four oil tanks of the second group and the third group in series are connected with one end of the first electromagnetic valve and the second electromagnetic valve respectively.

[0015] Further, the monitoring module comprises a pressure sensor, a flow meter, a rotating speed sensor and an accelerometer.

[0016] The probe of the pressure sensor is arranged on the overflow valve, and the output end thereof is electrically connected with the first input end of the control module and is used for monitoring the pressure in the pressurized oil tank.

[0017] The flow meter is arranged between the pressurized oil tank and the engine pump, the output end thereof is electrically connected with the second input end of the control module, and is used for obtaining the oil consumption of the turbojet engine in real time.

[0018] The rotating speed sensor is arranged at the front end internal turbine of the turbojet engine, the output end thereof is electrically connected with the third input end of the control module, and is used for monitoring the actual rotating speed of the turbojet engine in real time.

[0019] The accelerometer is integrated in the inside of the control module, and is used for monitoring the actual acceleration of the target machine in real time.

[0020] Further, the control module comprises a fuel controller, a flight control unit and an ECU which are electrically connected in sequence.

[0021] The input end of the fuel controller is electrically connected with the output end of the pressure sensor and the flowmeter respectively, and the control end is electrically connected with the control end of the fuel pump, the first electromagnetic valve and the second electromagnetic valve respectively.

[0022] The output end of the engine pump is connected with the turbojet engine through the third electromagnetic valve, the input end of the ECU is electrically connected with the output end of the speed sensor, and the control end is electrically connected with the control end of the engine pump and the third electromagnetic valve respectively.

[0023] The accelerometer is integrated in the inside of the flight control unit, the flight control unit is used for controlling the opening and closing of the first electromagnetic valve and the second electromagnetic valve through the fuel controller according to the oil consumption of the turbojet engine, calculating the thrust change of the target machine according to the actual acceleration, controlling the start and stop of the fuel pump and the engine pump through the fuel controller and the ECU, and controlling the speed of the fuel pump and the engine pump through the fuel controller and the ECU according to the current speed of the turbojet engine and the thrust change in real time, so as to adaptively adjust the oil supply flow and pressure of the turbojet engine.

[0024] Further, the other end of the overflow valve is connected with the oil adding / extracting port of the target machine through the manual valve.

[0025] Further, the other end of the pressurized oil tank is connected with the engine pump through the oil filter.

[0026] Further, the pressurized oil tank comprises a metal shell and a vacuum soft oil bag arranged in the metal shell.

[0027] Further, the first group of oil tanks, the second group of oil tanks and the third group of oil tanks are all polyurethane rubber film split soft oil tanks.

[0028] Meanwhile, the application also provides an oil sequence management method of the high-stability supersonic target machine fuel system, which is characterized by comprising the following steps:

[0029] Step 1, when the target machine is launched by boosting, the first electromagnetic valve and the second electromagnetic valve are closed through the control module, and the fuel pump is supplied with oil through the first group of oil tanks;

[0030] Step 2, the current residual oil amount of the first group of oil tanks is calculated through the control module according to the oil consumption of the turbojet engine, when the current residual oil amount of the first group of oil tanks is less than the preset minimum oil amount, the first electromagnetic valve is opened through the control module, the fuel pump is supplied with oil through the first group of oil tanks and the second group of oil tanks together, and when the oil in the first group of oil tanks is consumed, the fuel pump is supplied with oil through the second group of oil tanks alone.

[0031] Step 3, the control module calculates the current remaining oil quantity of the second group of oil tanks according to the acquired oil consumption of the turbojet engine, when the current remaining oil quantity of the second group of oil tanks is less than the preset minimum oil quantity, the control module controls the second electromagnetic valve to open, the second group of oil tanks and the third group of oil tanks supply oil to the fuel pump together, and when the fuel in the second group of oil tanks is consumed, the third group of oil tanks supplies oil to the fuel pump alone.

[0032] The beneficial effects of the present application are:

[0033] 1. The present application has the ability to adjust the stability of the target machine after boost separation. The first group of oil tanks is arranged in the front cabin of the fuselage, and after the engine works, the fuel system preferentially consumes the fuel of the first group of oil tanks to adjust the forward movement of the center of mass caused by boost separation, ensuring that the stability of the target machine after boost separation is within a controllable range. At the same time, since the first group of oil tanks is arranged in front of the center of mass, only a small space in the front cabin is needed to complete the adjustment of the center of mass of the whole machine.

[0034] 2. The present application has the ability to adjust the stability of supersonic flight. The existing supersonic target machine will cause a large amount of rear movement of the focal point during supersonic flight, which will increase the stability of the target machine, thereby reducing the handling and stability characteristics of the target machine and affecting the flight performance of the target machine. The present application arranges two groups of oil tanks in the middle of the fuselage, wherein the second group of oil tanks is in front of the theoretical center of mass of the target machine, and the third group of oil tanks is behind the theoretical center of mass of the target machine. When the target machine starts cruising, the electromagnetic valve of the third group of oil tank oil circuit is closed, the fuel of the second group of oil tanks is preferentially consumed, and the rear movement of the center of mass of the target machine is controlled, thereby reducing the influence of stability caused by fuel consumption. BRIEF DESCRIPTION OF DRAWINGS

[0035] Figure 1 is a schematic diagram of the arrangement structure of three groups of oil tanks and a pressurized oil tank in an embodiment of the high-stability supersonic target machine fuel system of the present application;

[0036] Figure 2 is a schematic diagram of the structure of an embodiment of the high-stability supersonic target machine fuel system of the present application.

[0037] In the figure: 1-first electromagnetic valve, 2-second electromagnetic valve, 3-oil filling / extracting port, 4-hand valve, 5-overflow valve, 6-fuel pump, 7-fuel controller, 8-oil filter, 9-flow meter, 10-engine pump, 11-third electromagnetic valve, 12-pressure sensor, 13-first group of oil tanks, 14-second group of oil tanks, 15-third group of oil tanks, 16-pressurized oil tank, 17-flight control unit, 18-turbojet engine, 19-ECU, 20-rotational speed sensor, 21-accelerometer. DETAILED DESCRIPTION

[0038] In order to make the purposes, advantages and features of the present application more clear, the following will make further detailed description of the high-stability supersonic target drone fuel system and oil sequence management method thereof of the present application in combination with the drawings and specific embodiments. The advantages and features of the present application will be more clear according to the following specific embodiments. It should be noted that: the drawings all adopt very simplified forms and all use non-precise proportions, only for the purpose of facilitating and clearly assisting the description of the embodiments of the present application; secondly, the structures shown in the drawings are often part of the actual structures.

[0039] The high-stability supersonic target drone fuel system of the present embodiment specifically comprises a body oil tank, a first electromagnetic valve 1, a second electromagnetic 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.

[0040] Specifically, the body oil tank in the present embodiment comprises three groups of oil tanks arranged in sequence from the nose to the tail along the longitudinal symmetry axis of the target drone fuselage; the number of the first group of oil tanks 13 is at least one, and the number of the second group of oil tanks 14 and the third group of oil tanks 15 is at least two, and the multiple oil tanks in the same group are connected in sequence by oil-resistant hoses.

[0041] Specifically, the first group of oil tanks 13 is arranged in the front cabin section of the target drone fuselage, and the second group of oil tanks 14 and the third group of oil tanks 15 are arranged in the fuel cabin in the middle of the target drone fuselage, and the second group of oil tanks 14 is located before the theoretical center of mass of the target drone, and the third group of oil tanks 15 is located after the theoretical center of mass of the target drone.

[0042] Referring to Figure 1 In a preferred embodiment of the present application, the body oil tank comprises nine oil tanks arranged in sequence from the nose to the tail along the longitudinal symmetry axis of the target drone fuselage, which are No. 1 oil tank to No. 9 oil tank, and the nine oil tanks are divided into three groups, the number of the first group of oil tanks 13 is one, and the number of the second group of oil tanks 14 and the third group of oil tanks 15 is four, i.e. No. 2-5 oil tank is the second group of oil tanks 14, and No. 6-9 oil tank is the third group of oil tanks 15, and No. 2-5 oil tank of the second group and No. 6-9 oil tank of the third group are connected in sequence; the oil port of No. 5 oil tank is the oil port of the second group of oil tanks 14, and the oil port of No. 9 oil tank is the oil port of the third group of oil tanks 15.

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

[0044] The oil port of the second group and the third group of oil tanks 15 is connected with one end of the first electromagnetic valve 1 and the second electromagnetic valve 2 through oil-resistant hoses respectively, and the oil port of the first group of oil tanks 13, the other end of the first electromagnetic valve 1 and the second electromagnetic valve 2, one end of the overflow valve 5 are connected with each other through oil-resistant hoses, and then connected with the input end of the fuel pump 6 through an oil-resistant hose; the other end of the overflow valve 5 is connected with the overflow end of the pressurized oil tank 16 through an oil-resistant hose, and then connected with the other end of the first electromagnetic valve 1 through an oil-resistant hose to the oil adding / extracting port 3 of the target machine. At the same time, a manual valve 4 is arranged between the other end of the overflow valve 5 and the oil adding / extracting port 3 of the target machine, which can facilitate manual control of the on-off of the oil circuit.

[0045] The pressurized oil tank 16 specifically includes a metal shell and a vacuum soft oil bag arranged in the metal shell. The metal shell is specifically an aluminum alloy shell in this embodiment, which mainly functions to bear the pressure of the oil bag after being pressurized. The pressurized oil tank 16 is arranged in the fuel cabin in the middle of the target machine body and is located after the No. 9 oil tank. One end of the pressurized oil tank 16 is connected with the output end of the fuel pump 6 through an oil-resistant hose, and the other end is connected with one end of the oil filter 8 through an oil-resistant hose. The main function of the oil filter 8 is to filter impurities in the fuel. The other end of the oil filter 8 is connected with one end of the flow meter 9 through an oil-resistant hose. The other end of the flow meter 9 is connected with the input end of the engine pump 10 through an oil-resistant hose. The main function of the engine pump 10 is to pressurize the fuel input to the turbojet engine 18 twice. The output end of the engine pump 10 is connected with the turbojet engine 18 through the third electromagnetic valve 11.

[0046] The first monitoring end of the monitoring module is arranged at the overflow valve 5, which is used to monitor the fuel pressure at the overflow valve 5, so as to obtain the fuel pressure in the pressurized oil tank 16. The second monitoring end is arranged between the oil filter 8 and the engine pump 10, which is used to record the oil consumption of the turbojet engine 18, so as to facilitate subsequent calculation of the remaining oil quantity of each oil tank. The third monitoring end is arranged at the front end turbine of the turbojet engine 18, which is used to monitor the actual rotating speed of the turbojet engine 18 in real time. The fourth monitoring end is arranged on the target machine body, which is used to monitor the actual acceleration of the target machine in real time.

[0047] Specifically, in this embodiment, the monitoring module includes a pressure sensor 12, a flow meter 9, a rotating speed sensor 20 and an accelerometer 21. The probe of the pressure sensor 12 is arranged on the overflow valve 5, and the output end thereof is electrically connected with the first input end of the control module, which is used to monitor the pressure in the pressurized oil tank 16. The flow meter 9 is arranged between the oil filter 8 and the engine pump 10, and the output end thereof is electrically connected with the second input end of the control module, which is used to record the oil consumption of the turbojet engine 18. The rotating speed sensor 20 is arranged at the internal turbine at the front end of the turbojet engine 18, and the output end thereof is electrically connected with the third input end of the control module, which is used to monitor the actual rotating speed of the turbojet engine 18 in real time. The accelerometer 21 is integrated in the control module, which is used to monitor the actual acceleration of the target machine in real time.

[0048] The control end of the control module is connected with the control end of the first electromagnetic valve 1, the second electromagnetic valve 2, the third electromagnetic valve 11, the fuel pump 6 and the engine pump 10 respectively, for controlling the opening and closing of the first electromagnetic valve 1, the second electromagnetic valve 2 and the third electromagnetic valve 11, and the start and stop of the fuel pump 6 and the engine pump 10, and simultaneously controlling the rotation speed of the engine pump 10 and the fuel pump 6 according to the current rotation speed of the turbojet engine 18 in real time, so as to adaptively adjust the fuel supply flow and pressure of the turbojet engine 18.

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

[0050] The accelerometer 21 is integrated in the flight control unit 17, the flight control unit 17 is used for controlling the opening and closing of the first electromagnetic valve 1 and the second electromagnetic valve 2 through the fuel controller 7 according to the obtained oil consumption of the turbojet engine 18, controlling the start and stop of the fuel pump 6 and the engine pump 10 through the fuel controller 7 and the ECU 19 according to the actual acceleration of the target machine, and controlling the rotation speed of the fuel pump 6 and the engine pump 10 through the fuel controller 7 and the ECU 19 in real time according to the current rotation speed and the thrust change of the turbojet engine 18, so as to adaptively adjust the fuel supply flow and pressure of the turbojet engine 18.

[0051] Before the fuel system works, the manual valve 4 is opened, the first electromagnetic valve 1 and the second electromagnetic valve 2 are opened through the external power supply, and the whole fuel system is in a communication state.

[0052] All the air in the oil tank and the oil pipe is extracted through the oil filling / extraction port 3, and after being extracted to vacuum, fuel is filled through the oil filling / extraction port 3. The first electromagnetic valve 1, the second electromagnetic valve 2 and the manual valve 4 are kept open during the filling process, and after the filling is completed, the oil filling / extraction port 3 is closed, the manual valve 4 is closed, and the power supply of the first electromagnetic valve 1 and the second electromagnetic valve 2 is disconnected.

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

[0054] When the turbojet engine 18 starts to work, the ECU 19 supplies power to the engine pump 10 and the third electromagnetic valve 11, the fuel in the No. 1 fuel tank flows into the pressurized fuel tank 16 through the fuel pump 6, and the fuel in the pressurized fuel tank 16 flows into the turbojet engine 18 through the engine pump 10 and the third electromagnetic valve 11 after being pressurized twice by the engine pump 10, at this time, the fuel consumed is the fuel in the No. 1 fuel tank, and the center of mass of the whole aircraft constantly moves backward with the consumption of the fuel.

[0055] The flowmeter 9 sends the current flow value to the fuel controller 7 in real time, and the current remaining fuel in the No. 1 fuel tank is calculated by the flight control unit 17 in real time, when the fuel in the No. 1 fuel tank is about to be consumed, the flight control unit 17 controls the first electromagnetic valve 1 to open through the fuel controller 7, and the fuel in the No. 1 fuel tank and the fuel in the No. 2 to No. 5 fuel tanks begin to supply fuel together, and the fuel flows into the engine through the third electromagnetic valve 11 after being pressurized by the fuel pump 6 and the engine pump 10, after the fuel in the No. 1 fuel tank is consumed, the fuel is supplied by the No. 2 to No. 5 fuel tanks, at this time, the fuel consumed is the fuel in the No. 2 to No. 5 fuel tanks, and the center of mass of the whole aircraft constantly moves backward with the consumption of the fuel.

[0056] Similarly, the remaining fuel in the No. 2 to No. 5 fuel tanks is calculated by the flight control unit 17 in real time, when the fuel in the No. 2 to No. 5 fuel tanks is about to be consumed, the flight control unit 17 controls the second electromagnetic valve 2 to open through the fuel controller 7, and the No. 2 to No. 5 fuel tanks and the No. 6 to No. 9 fuel tanks begin to supply fuel together, and the fuel flows into the turbojet engine 18 through the third electromagnetic valve 11 after being pressurized by the fuel pump 6 and the engine pump 10, after the fuel in the No. 2 to No. 5 fuel tanks is consumed, the fuel is supplied by the No. 6 to No. 9 fuel tanks, at this time, the fuel consumed is the fuel in the No. 6 to No. 9 fuel tanks, and the center of mass of the whole aircraft constantly moves forward with the consumption of the fuel.

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

[0058] After the fuel system stops working, the add / drain port 3 is opened, the manual valve 4 is opened, the first electromagnetic valve 1 and the second electromagnetic valve 2 are opened through an external power supply, the remaining fuel is discharged through the add / drain port 3, and then the add / drain port 3 is closed, the manual valve 4 is closed, and the fuel system is completed.

[0059] A fuel sequence management method of the high-stability supersonic target aircraft fuel system, specifically comprising the following steps:

[0060] Step 1, when the target aircraft takes off with boost, the first electromagnetic valve 1 and the second electromagnetic valve 2 are controlled to be closed by the control module, and the fuel pump 6 is supplied with fuel by the No. 1 fuel tank, the mass of the front part of the target aircraft is reduced, and the center of mass of the target aircraft moves backward, effectively reducing the impact of boost separation on the stability of the whole aircraft.

[0061] Step 2, the flight control unit 17 calculates the current remaining oil quantity of the No. 1 oil tank according to the oil consumption of the turbojet engine 18, when the current remaining oil quantity of the No. 1 oil tank is less than the preset minimum oil quantity, the flight control unit 17 controls the first electromagnetic valve 1 to open and the second electromagnetic valve 2 to keep closed through the fuel controller 7, first supplies oil to the fuel pump 6 through the No. 1 oil tank and the No. 2 to No. 5 oil tanks together, and then supplies oil to the fuel pump 6 through the No. 2 to No. 5 oil tanks alone after the oil in the No. 1 oil tank is consumed, controls the target mass center to move backward, and reduces the stability influence caused by the focus point moving backward due to supersonic flight.

[0062] Step 3, the flight control unit 17 calculates the current remaining oil quantity of the No. 2 to No. 5 oil tanks according to the oil consumption of the turbojet engine 18, when the current remaining oil quantity of the No. 2 to No. 5 oil tanks is less than the preset minimum oil quantity, the flight control unit 17 controls the second electromagnetic valve 2 to open through the fuel controller 7, first supplies oil to the fuel pump 6 through the No. 2 to No. 5 oil tanks and the No. 6 to No. 9 oil tanks together, and then supplies oil to the fuel pump 6 through the No. 6 to No. 9 oil tanks alone after the oil in the No. 2 to No. 5 oil tanks is consumed, until the target is recovered.

Claims

1. A high-stability supersonic target drone fuel system, characterized in that: it comprises a body oil tank, a first electromagnetic valve (1), a second electromagnetic 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 body oil tank comprises three groups of oil tanks arranged in sequence from the nose to the tail along the longitudinal symmetry axis of the target drone fuselage; the first group of oil tanks (13) is at least one in number, the second group of oil tanks (14) and the third group of oil tanks (15) are both at least two in number, and the oil tanks in the same group are connected in series; the first group of oil tanks (13) is arranged in the front cabin section of the target drone fuselage, the second group of oil tanks (14) and the third group of oil tanks (15) are arranged in the fuel cabin in the middle of the target drone fuselage, and are located before and after the theoretical center of mass of the target drone respectively; the oil ports of the second group of oil tanks (14) and the third group of oil tanks (15) are connected with one end of the first electromagnetic valve (1) and the second electromagnetic valve (2) respectively, the oil port of the first group of oil tanks (13), the other end of the first electromagnetic valve (1) and the second electromagnetic valve (2), and one end of the overflow valve (5) are connected with each other and connected with the input end of the fuel pump (6); the other end of the overflow valve (5) is connected with the overflow end of the pressurized oil tank (16) and then connected with the other end of the first electromagnetic valve (1) and connected to the oil filling / extracting port (3) of the target drone; the output end of the fuel pump (6) is connected with one end of the pressurized oil tank (16), the other end of the pressurized oil tank (16) is connected with the oil port of the turbojet engine (18) through the engine pump (10), the pressurized oil tank (16) is used to form a local fuel supply pressure environment required for fuel supply to the turbojet engine (18), and the engine pump (10) is used to pressurize the fuel input to the turbojet engine (18) for the second time; the first monitoring end of the monitoring module is arranged on the overflow valve (5) for real-time monitoring of the fuel pressure at the overflow valve (5), the second monitoring end is arranged between the pressurized oil tank (16) and the engine pump (10) for real-time monitoring of the oil consumption of the turbojet engine (18), the third monitoring end is arranged at the front turbine of the turbojet engine (18) for real-time monitoring of the actual speed of the turbojet engine (18), and the fourth monitoring end is arranged on the target drone fuselage for real-time monitoring of the actual acceleration of the target drone; 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 (1), the second electromagnetic valve (2), the fuel pump (6) and the engine pump (10) respectively, the control module is used to control the start and stop of the fuel pump (6) and the engine pump (10), control the opening and closing of the first electromagnetic valve (1) and the second electromagnetic valve (2) according to the obtained oil consumption of the turbojet engine (18), simultaneously calculate the thrust change of the target drone according to the actual accelerometer (21), and control the speed of the engine pump (10) and the fuel pump (6) according to the current speed of the turbojet engine (18) and the thrust change in real time, so as to adaptively adjust the fuel supply flow and pressure of the turbojet engine (18). ​ ​ 2. The high-stability supersonic target drone fuel system according to claim 1, characterized in that: the body fuel tank comprises nine fuel tanks arranged along the longitudinal symmetry axis of the target drone fuselage from the nose to the tail, and the nine fuel tanks are divided into three groups, the first group of fuel tanks (13) has one fuel tank, the second group of fuel tanks (14) and the third group of fuel tanks (15) each have four fuel tanks, and the four fuel tanks of the second group and the third group are connected in series. The oil outlet of the last fuel tank in the four fuel tanks of the second group and the third group is connected with one end of the first electromagnetic valve (1) and the second electromagnetic valve (2) respectively.

3. The high-stability supersonic target drone fuel system according to claim 1 or 2, characterized in that: the monitoring module comprises a pressure sensor (12), a flow meter (9), a rotational speed sensor (20) and an accelerometer (21); the probe of the pressure sensor (12) is arranged on the overflow valve (5), and the output end thereof is electrically connected with the first input end of the control module, for monitoring the pressure in the pressurized fuel tank (16); the flow meter (9) is arranged between the pressurized fuel tank (16) and the engine pump (10), and the output end thereof is electrically connected with the second input end of the control module, for acquiring the oil consumption of the turbojet engine (18) in real time; the rotational speed sensor (20) is arranged at the internal turbine of the front end of the turbojet engine (18), 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 (18) in real time; the accelerometer (21) is integrated in the control module, for monitoring the actual acceleration of the target drone in real time.

4. The high-stability supersonic target drone fuel system according to claim 3, characterized in that: the control module comprises a fuel controller (7), a flight control unit (17) and an ECU (19) which are electrically connected in sequence; the input ends of the fuel controller (7) are electrically connected with the output ends of the pressure sensor (12) and the flow meter (9) respectively, and the control ends thereof are electrically connected with the control ends of the fuel pump (6), the first electromagnetic valve (1) and the second electromagnetic valve (2) respectively; the output end of the engine pump (10) is connected with the turbojet engine (18) through the third electromagnetic valve (11), the input end of the ECU (19) is electrically connected with the output end of the rotational speed sensor (20), and the control ends thereof are electrically connected with the control ends of the engine pump (10) and the third electromagnetic valve (11) respectively; the accelerometer (21) is integrated in the flight control unit (17), and the flight control unit (17) is used for controlling the opening and closing of the first electromagnetic valve (1) and the second electromagnetic valve (2) through the fuel controller (7) according to the acquired oil consumption of the turbojet engine (18), calculating the thrust change of the target drone according to the actual acceleration, controlling the start and stop of the fuel pump (6) and the engine pump (10) through the fuel controller (7) and the ECU (19), and controlling the rotational speed of the fuel pump (6) and the engine pump (10) through the fuel controller (7) and the ECU (19) according to the current rotational speed of the turbojet engine (18) and the thrust change in real time, so as to adaptively adjust 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 with the target drone's oil filling / drain port (3) through the hand valve (4).

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

7. The high-stability supersonic target drone fuel system according to claim 6, characterized in that: The pressurized fuel tank (16) comprises a metal shell and a vacuum soft fuel bag arranged in the metal shell.

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

9. A method for managing the order of the fuel in the high-stability supersonic drone fuel system according to any one of claims 1 to 8, characterized in that, Comprising the following steps: Step 1, when the target drone takes off with boost, the first electromagnetic valve (1) and the second electromagnetic valve (2) are closed by the control module, and the first group of fuel tanks (13) supply oil to the fuel pump (6); Step 2, the control module calculates the current remaining oil quantity of the first group of fuel tanks (13) according to the obtained oil consumption of the turbojet engine (18), and when the current remaining oil quantity of the first group of fuel tanks (13) is less than the preset minimum oil quantity, the first electromagnetic valve (1) is opened by the control module, the first group of fuel tanks (13) and the second group of fuel tanks (14) supply oil to the fuel pump (6) together, and when the fuel in the first group of fuel tanks (13) is consumed, the second group of fuel tanks (14) supply oil to the fuel pump (6) alone; Step 3, the control module calculates the current remaining oil quantity of the second group of fuel tanks (14) according to the obtained oil consumption of the turbojet engine (18), and when the current remaining oil quantity of the second group of fuel tanks (14) is less than the preset minimum oil quantity, the second electromagnetic valve (2) is opened by the control module, the second group of fuel tanks (14) and the third group of fuel tanks (15) supply oil to the fuel pump (6) together, and when the fuel in the second group of fuel tanks (14) is consumed, the third group of fuel tanks (15) supply oil to the fuel pump (6) alone.

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