Fuel conveying device and flight system

Abstract

The utility model provides a fuel conveying device and a flight system. The fuel conveying device comprises a control device, an oil pump and an oil storage device. Wherein the control device is connected with the oil pump, the oil pump is connected with an aircraft oil tank through a first oil way, and a three-way valve is further arranged on the first oil way; the oil pump is further connected with the oil storage device through a second oil way. The control device is used for controlling the oil pump to rotate forwards and controlling the three-way valve to be powered off, and air in the first oil way and air in the second oil way are exhausted. The control device is used for controlling the oil pump to rotate forwards and controlling the three-way valve to be powered on, and refueling is conducted on the aircraft oil tank from the oil storage device. The control device is further used for controlling the oil pump to rotate reversely and controlling the three-way valve to be powered on, and oil is pumped from the aircraft oil tank to the oil storage device. According to the invention, manual operation is reduced, and the working efficiency is improved.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft refueling, and in particular to a fuel delivery device and a flight system. Background Art

[0002] Unmanned target drones are commonly used for simulated flight to provide imaginary targets for training. They can be operated remotely or on a pre-set flight path, and fall under the category of unmanned aircraft.

[0003] In drone applications, refueling and oil extraction are essential. Prior to now, these operations were mostly manual. This required a significant amount of preparation time and a large number of personnel for handling tasks, resulting in low efficiency. Utility Model Content

[0004] In view of this, an object of the present application is to provide a fuel delivery device and a flight system to overcome the problems in the prior art.

[0005] In a first aspect, an embodiment of the present application provides a fuel delivery device, the fuel delivery device comprising:

[0006] A control device, an oil pump, and an oil storage device; wherein the control device is connected to the oil pump, and the oil pump is connected to the aircraft fuel tank via a first oil circuit, wherein the first oil circuit is further provided with a three-way valve; and the oil pump is further connected to the oil storage device via a second oil circuit;

[0007] The control device is used to control the oil pump to rotate forward and control the three-way valve to lose power, thereby exhausting the air in the first oil circuit and the second oil circuit;

[0008] The control device is used to control the forward rotation of the oil pump and the power supply of the three-way valve to refuel the aircraft fuel tank from the oil storage device;

[0009] The control device is further used to control the oil pump to reverse and control the three-way valve to be energized, so as to pump oil from the aircraft oil tank to the oil storage device.

[0010] In some technical solutions of the present application, the fuel delivery device further includes a selection switch;

[0011] The selection switch is used to select the manual mode or the automatic mode of the control device;

[0012] In manual mode, the control device controls the exhaust of air from the first oil circuit and the second oil circuit, controls the oil pump to refuel the aircraft fuel tank from the fuel storage device, or controls the oil pump to pump fuel from the aircraft fuel tank to the fuel storage device according to user input operations at each stage;

[0013] In the automatic mode, the control device automatically controls the oil pump to discharge air from the first oil circuit and the second oil circuit, controls the oil pump to refuel the aircraft fuel tank from the oil storage device, or controls the oil pump to pump fuel from the aircraft fuel tank to the oil storage device according to preset control parameters.

[0014] In some technical solutions of the present application, the control parameters include weight parameters and pressure parameters;

[0015] In the automatic mode, the control device automatically controls the oil pump to refuel the aircraft fuel tank from the oil storage device or to pump oil from the aircraft fuel tank to the oil storage device according to preset control parameters, including:

[0016] In the automatic mode, the control device automatically controls the oil pump to refuel the aircraft fuel tank from the oil storage device according to the weight parameter of the weighing sensor and the pressure parameter of the pressure sensor;

[0017] In the automatic mode, the control device automatically controls the oil pump to pump oil from the aircraft oil tank to the oil storage device according to the pressure parameter of the pressure sensor.

[0018] In some technical solutions of the present application, when the selection switch points to the manual control circuit, the manual module of the control device is selected;

[0019] The manual control circuit includes an oil pumping button SB1, an exhaust button SB2, a refueling button SB3, a stop button SB4, an oil pumping relay KM1, an exhaust relay KM2 and a refueling relay KM3; wherein, SB1, SB2 and SB3 are all interlocking buttons, each including two normally open sub-buttons and two normally closed sub-buttons.

[0020] In some technical solutions of the present application, the above-mentioned SB1 is a normally open contact and also includes normally closed contacts SB1_1 and SB1_2; the above-mentioned SB2 is a normally open contact and also includes normally closed contacts SB2_1 and SB2_2; the above-mentioned SB3 is a normally open contact and also includes normally closed contacts SB3_1 and SB3_2.

[0021] In some technical solutions of the present application, when the selection switch points to the automatic control circuit, the automatic module of the control device is selected;

[0022] The automatic control circuit includes an air detector, a weighing sensor, a pressure sensor and a touch screen display; the air detector, the pressure sensor and the touch screen display are all connected to the control device.

[0023] In some technical solutions of the present application, the air detector is provided in the first oil circuit and the second oil circuit, and the air detector is connected to the control device;

[0024] The air detector is used to detect whether there is air in the first oil circuit and the second oil circuit;

[0025] When air exists in the first oil circuit or the second oil circuit, a shutdown signal is sent to the control device;

[0026] The control device is used to stop the operation of the oil pump according to the shutdown signal and issue an alarm.

[0027] In some technical solutions of the present application, the weighing sensor is used to determine the weight of the oil in the oil storage device and send the weight of the oil in the oil storage device to the control device;

[0028] The pressure sensor is used to determine the pressure in the aircraft fuel tank and send the pressure in the aircraft fuel tank to the control device.

[0029] In some technical solutions of the present application, the above-mentioned touch screen display is used to display the refueling status and the oil pumping status; and is also used to generate control parameters in the automatic mode according to the user's operation.

[0030] In a second aspect, an embodiment of the present application provides a flight system, comprising: a fuel delivery device and an aircraft as described above.

[0031] The technical solutions provided by the embodiments of the present application may have the following beneficial effects:

[0032] The fuel delivery device in this application includes: a control device, an oil pump, and an oil storage device. The control device is connected to the oil pump, which is connected to an aircraft fuel tank via a first oil circuit, which is also provided with a three-way valve. The oil pump is also connected to the oil storage device via a second oil circuit. The control device is used to control the forward rotation of the oil pump and to de-energize the three-way valve to expel air from the first and second oil circuits. The control device is used to control the forward rotation of the oil pump and to energize the three-way valve to transfer fuel from the oil storage device to the aircraft fuel tank. The control device is also used to control the reverse rotation of the oil pump and to energize the three-way valve to pump fuel from the aircraft fuel tank to the oil storage device. This application reduces manual operations and improves work efficiency.

[0033] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, preferred embodiments are given below and described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following is a brief introduction to the drawings required for use in the embodiments. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without creative work.

[0035] Figure 1 shows an overall schematic diagram of a fuel delivery device provided in an embodiment of the present application;

[0036] Figure 2 A schematic diagram of a fuel delivery device provided in an embodiment of the present application is shown;

[0037] Figure 3 A schematic diagram showing a mode selection provided by an embodiment of the present application is shown;

[0038] Figure 4 A schematic diagram of a manual control circuit provided in an embodiment of the present application is shown;

[0039] Figure 5 A schematic diagram of an oil pumping circuit provided in an embodiment of the present application is shown;

[0040] Figure 6 A schematic diagram of an exhaust circuit provided in an embodiment of the present application is shown;

[0041] Figure 7 A schematic diagram of a refueling circuit provided in an embodiment of the present application is shown;

[0042] Figure 8 A schematic diagram of an automatic control circuit provided in an embodiment of the present application is shown. DETAILED DESCRIPTION

[0043] In order to make the purpose, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. It should be understood that the drawings in the present application only serve the purpose of illustration and description and are not used to limit the scope of protection of the present application. In addition, it should be understood that the schematic drawings are not drawn to scale. The flowcharts used in this application illustrate the operations implemented according to some embodiments of the present application. It should be understood that the operations of the flowcharts can be implemented out of sequence, and steps without logical context can be reversed or implemented simultaneously. In addition, those skilled in the art, under the guidance of the contents of this application, can add one or more other operations to the flowchart, or remove one or more operations from the flowchart.

[0044] In addition, the described embodiments are only a part of the embodiments of the present application, rather than all of the embodiments. The components of the embodiments of the present application generally described and shown in the drawings here can be arranged and designed in various configurations. Therefore, the following detailed description of the embodiments of the present application provided in the drawings is not intended to limit the scope of the claimed application, but merely represents selected embodiments of the present application. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without making creative work are within the scope of protection of the present application.

[0045] It should be noted that the term "comprising" will be used in the embodiments of the present application to indicate the existence of the features declared thereafter, but does not exclude the addition of other features.

[0046] Unmanned target drones are commonly used for simulated flight to provide imaginary targets for training. They can be operated remotely or on a pre-set flight path, and fall under the category of unmanned aircraft.

[0047] In drone applications, refueling and oil extraction are essential. Prior to now, these operations were mostly manual. This required a significant amount of preparation time and a large number of personnel for handling tasks, resulting in low efficiency.

[0048] Based on this, the embodiments of the present application provide a fuel delivery device and a flight system. Some implementation methods of the present application are described in detail below. Unless there is a conflict, the following embodiments and features in the embodiments can be combined with each other.

[0049] like Figure 1As shown, the fuel delivery device includes: a control device, an oil pump and an oil storage device; wherein the control device is connected to the oil pump, and the oil pump is connected to the aircraft fuel tank through a first oil circuit, and a three-way valve is also provided on the first oil circuit; the oil pump is also connected to the oil storage device through a second oil circuit;

[0050] The control device is used to control the oil pump to rotate forward and control the three-way valve to lose power, thereby exhausting the air in the first oil circuit and the second oil circuit;

[0051] The control device is used to control the forward rotation of the oil pump and the power supply of the three-way valve to refuel the aircraft fuel tank from the oil storage device;

[0052] The control device is further used to control the oil pump to reverse and control the three-way valve to be energized, so as to pump oil from the aircraft oil tank to the oil storage device.

[0053] The fuel delivery device also includes a selection switch;

[0054] The selection switch is used to select the manual mode or the automatic mode of the control device;

[0055] In manual mode, the control device controls the exhaust of air from the first oil circuit and the second oil circuit, controls the oil pump to refuel the aircraft fuel tank from the fuel storage device, or controls the oil pump to pump fuel from the aircraft fuel tank to the fuel storage device according to user input operations at each stage;

[0056] In the automatic mode, the control device automatically controls the oil pump to discharge air from the first oil circuit and the second oil circuit, controls the oil pump to refuel the aircraft fuel tank from the oil storage device, or controls the oil pump to pump fuel from the aircraft fuel tank to the oil storage device according to preset control parameters.

[0057] 4. The control parameters include weight parameters and pressure parameters;

[0058] In the automatic mode, the control device automatically controls the oil pump to refuel the aircraft fuel tank from the oil storage device or to pump oil from the aircraft fuel tank to the oil storage device according to preset control parameters, including:

[0059] In the automatic mode, the control device automatically controls the oil pump to refuel the aircraft fuel tank from the oil storage device according to the weight parameter of the weighing sensor and the pressure parameter of the pressure sensor;

[0060] In the automatic mode, the control device automatically controls the oil pump to pump oil from the aircraft oil tank to the oil storage device according to the pressure parameter of the pressure sensor.

[0061] When the selection switch points to the manual control circuit, the manual module of the control device is selected;

[0062] The manual control circuit includes an oil pumping button SB1, an exhaust button SB2, a refueling button SB3, a stop button SB4, an oil pumping relay KM1, an exhaust relay KM2 and a refueling relay KM3; wherein, SB1, SB2 and SB3 are all interlocking buttons, each including two normally open sub-buttons and two normally closed sub-buttons.

[0063] The SB1 is a normally open contact and also includes normally closed contacts SB1_1 and SB1_2; the SB2 is a normally open contact and also includes normally closed contacts SB2_1 and SB2_2; the SB3 is a normally open contact and also includes normally closed contacts SB3_1 and SB3_2.

[0064] When the selection switch is directed to the automatic control circuit, the automatic module of the control device is selected;

[0065] The automatic control circuit includes an air detector, a weighing sensor, a pressure sensor and a touch screen display; the air detector, the pressure sensor and the touch screen display are all connected to the control device.

[0066] The air detector is arranged on the first oil circuit and the second oil circuit, and the air detector is connected to the control device;

[0067] The air detector is used to detect whether there is air in the first oil circuit and the second oil circuit;

[0068] When air exists in the first oil circuit or the second oil circuit, a shutdown signal is sent to the control device;

[0069] The control device is used to stop the operation of the oil pump according to the shutdown signal and issue an alarm.

[0070] The weighing sensor is used to determine the weight of the oil in the oil storage device and send the weight of the oil in the oil storage device to the control device;

[0071] The pressure sensor is used to determine the pressure in the aircraft fuel tank and send the pressure in the aircraft fuel tank to the control device.

[0072] The touch screen display is used to display the refueling status and the oil pumping status; and is also used to generate control parameters in the automatic mode according to the user's operation.

[0073] When implementing it, Figure 2As shown, the load cell can be selected from a scale (a universal wheel mobile push-pull 500 kg electronic scale, a thickened high-precision industrial scale, or a 1-2-3 ton logistics scale). The fuel dispenser includes a fuel pump for bidirectional oil pumping and control of fueling / extraction modes; two air sensors for detecting air in the fuel line; and a pressure sensor for monitoring the tank pressure, including vacuum and full fuel status. The fuel pump and an air sensor are located in the main body box, while a three-way fuel valve, an air sensor, and a pressure sensor are located in the fuel gun box.

[0074] Figure 3 This is the schematic diagram for selecting manual / automatic mode: The selector switch is a three-position, two-throw switch. When the switch is in the manual position, the manual circuit is energized, allowing the dispenser to be controlled via the mechanical buttons. When the switch is in the automatic control position, the automatic system circuit is energized, allowing the system to be controlled automatically via the touch screen.

[0075] In an optional embodiment, if Figure 4 As shown, when the selector switch is in manual mode, manual circuit VCC is energized. Button SB1 is the oil pumping button, button SB2 is the exhaust button, and button SB3 is the refueling button. Buttons SB1, SB2, and SB3 are interlocked buttons, each with two normally open and two normally closed positions. SB4 is the stop button. KM1 is the first relay, serving as the oil pumping relay. KM2 is the second relay, serving as the exhaust relay. KM3 is the third relay, serving as the refueling relay.

[0076] Pressing the SB1 button closes the normally open contact of SB1, and the normally closed contacts of SB1_1 and SB1_2 open. The first relay's VCC flows through the normally open contact of SB1, the normally closed contact of SB2_1, and the normally closed contact of SB3_1, energizing the coil of the KM1 relay. Once KM1 is energized, the normally open auxiliary contact of KM1_1 closes, causing the first relay of KM1 to self-lock. This energizes the oil pumping relay.

[0077] like Figure 5 As shown, when the first relay KM1 is energized, the normally open auxiliary point of KM1_2 is closed, reversing the fuel pump circuit. When the first relay KM1 is energized, the normally open auxiliary point of KM1_3 is closed, energizing the three-way valve V1. This connects the aircraft fuel tank to the fuel pump line, and the refueling machine begins pumping fuel. When the first relay KM1 is energized, the normally open auxiliary point of KM1_4 is closed, and the fuel pumping indicator light L1 illuminates steadily, indicating fuel pumping.

[0078] When the fuel tank is completely pumped out and the tank is in a vacuum state, pressing the vent button SB2 closes the normally open contact of SB2 and opens the normally closed contact of SB2_1. The coil of the first relay KM1 loses power due to the disconnection of SB2_1. The normally open auxiliary contact of KM1_2 disconnects, de-energizing the fuel pump. The normally open auxiliary contact of KM1_3 disconnects the three-way valve V1, closing the aircraft fuel tank line. The normally open auxiliary contact of KM1_4 disconnects the fuel pump indicator light, turning it off. After the normally open contact of SB2 closes, the second relay VCC energizes the coil of the KM2 relay via the normally closed contact of SB2, the normally closed contact of SB1_1, and the normally closed contact of SB3_2.

[0079] like Figure 6 As shown, the coil of the second relay KM2 is energized, the normally open auxiliary point of KM2_1 is closed, and the coil of KM2 is self-locking and always energized. The normally open auxiliary point of the second relay KM2_2 is closed, energizing the fuel pump M and starting to rotate. Simultaneously, the normally open auxiliary point of KM2_3 is closed, causing the fuel pump to reverse direction and begin forward rotation. Because the three-way valve is de-energized, the oil circuit is forced back into the fuel tank through the three-way valve. This ensures that the refueling line is filled with oil before it reaches the aircraft fuel tank, venting any air in the line and preventing it from entering the aircraft fuel tank during refueling. The normally open auxiliary point of KM2_4 is closed, and the exhaust indicator light L2 is energized and illuminated, indicating exhaust.

[0080] When exhaust is complete, press SB3. SB3's normally open contact closes, SB3_2's normally closed contact opens, and the coil of the second relay, KM2, loses power due to the disconnection of SB3_2. KM2_2's normally open auxiliary contact opens, de-energizing the oil pump. KM2_3's normally open auxiliary contact opens, disconnecting the reversing direction signal. KM2_4's normally open auxiliary contact opens, de-energizing the exhaust indicator light, L1. After SB3's normally open contact closes, VCC of the third relay energizes through SB3's normally open contact, SB1_2's normally closed contact, and SB2_2's normally closed contact, energizing the coil of the KM3 relay.

[0081] like Figure 7 As shown: the coil of the third relay KM3 is energized, the normally open auxiliary point of KM3_1 is closed, and the coil of the KM3 relay is self-locking and always energized. The normally open auxiliary point of the third relay KM3_2 is closed, and the oil pump M is energized and starts to rotate. At the same time, the normally open auxiliary point of KM3_3 is closed, causing the oil pump to reverse direction and start forward rotation. At the same time, the normally open auxiliary point of KM3_4 is closed, and the three-way valve is energized, so that the oil circuit connects to the aircraft fuel tank through the three-way valve. The aircraft fuel tank begins to be refueled. Figure 5 As shown, after the normally open auxiliary point of KM3_1 is closed, the indicator light L3 is energized and always on, serving as a refueling indicator light.

[0082] When the refueling reaches the specified mass, press button SB4, SB4's normally closed contact opens, and the coil of the third relay KM3 is de-energized. The normally open auxiliary point of the third relay KM3_2 is disconnected, and the fuel pump M is de-energized and stops rotating. At the same time, the normally open auxiliary point of KM3_3 is disconnected. At the same time, the normally open auxiliary point of KM3_4 is disconnected, and the three-way valve is de-energized, closing the aircraft fuel tank pipeline. Figure 5 As shown, after the normally open auxiliary point of KM3_1 is disconnected, the indicator light L3 is powered off and goes out.

[0083] In an optional embodiment, as shown in FIG. Figure 8 As shown, the automatic control section primarily includes a weighing sensor, a touchscreen display, air detectors 1 and 2, a pressure sensor, an oil pump M, and a three-way valve V1. When the selector switch is set to automatic mode, the automatic control main control board receives power. The main control board uses the touchscreen display to set the relevant command parameters for the fuel dispenser (for example, after the refueling quality is determined). After the operator selects automatic refueling mode via the touchscreen, the intelligent fuel dispenser automatically begins pumping, venting, and refueling. When the refueling quality is reached, the intelligent fuel dispenser automatically stops refueling and issues an audible and visual alarm to notify the operator. The operating principles of each component are as follows:

[0084] The load cell uses a standard load cell with RS232 communication capabilities. This allows the mass of the kerosene in the barrel to be transmitted to the main control board. The main control board, equipped with an RS232 communication interface, receives the data transmitted by the load cell and converts it into a TTL level, sending it to the main MCU.

[0085] The touchscreen display is an LCD with touch input capabilities. This facilitates parameter input, mode selection, and status display for the intelligent dispenser. The touchscreen also includes RS232 communication, allowing command parameters to be transmitted to the main MCU control board and displaying MCU data status on the display, facilitating human-machine interaction.

[0086] The pressure sensor has a ±0.1 MPa range and outputs a 4-20 mA signal. This converts the fuel tank pressure into a current signal and transmits it to the MCU. The main control board (MCU) converts the 4-20 mA signal into a 0-3.3 V voltage signal. This is then converted to a digital signal via the MCU's analog-to-digital converter, allowing real-time monitoring of the fuel tank pressure.

[0087] Air detectors are installed at the fuel pump inlet and the aircraft fuel tank, respectively, to detect the presence of oil in the pipelines and determine whether air has entered the fuel inlet pipe and the aircraft fuel tank during refueling. When air enters the fuel inlet pipe, the air detectors input a switching signal, which is converted to a TTL signal through isolation and transmitted to the main control MCU. The main control board MCU then performs the corresponding processing.

[0088] The main MCU utilizes a 32-bit ARM Cortex-M3 core controller, offering high performance, low power consumption, a rich peripheral set, and powerful interrupt control capabilities. This controller features 64KB of Flash memory and 20KB of SRAM, along with up to 37 general-purpose input / output channels to meet the system's application needs. It also features a USART serial port to meet system communication requirements.

[0089] The system's minimum power supply is 3.3V. A 100nF ceramic capacitor is connected to pin 7, with a 10K resistor in series to act as a power-on reset circuit. The clock circuit uses an 8M passive crystal oscillator, with a 22pF capacitor connected in parallel to the pin, and the clock signal is connected to pins 5 / 6 of the MCU.

[0090] The switching output circuit controls external oil pumps, three-way valves, and other oil circuit power control components. The main control MCU connects to Darlington chip Q2 via three universal channels, converting TTL signals into operating voltages for the working relays to control the operation of the oil pump and three-way valve, and outputting a reversing signal.

[0091] In this application, when the function selector switch is set to automatic mode, the intelligent fuel dispenser enters automatic refueling mode. At this point, the intelligent fuel dispenser's main control board (MCU) and touchscreen display are powered, and the load cell is connected to the main control board (MCU) via a communication cable. The operator enters a predetermined amount of kerosene to be added on the touchscreen and clicks the start command. The intelligent fuel dispenser then automatically begins pumping, venting, and refueling. When the fuel mass reaches the input value, the intelligent fuel dispenser automatically stops, stopping refueling to meet the aircraft's refueling needs.

[0092] When the function selector switch is turned to manual mode, the operator must actually operate and complete the operations of pumping oil, exhausting, and refueling. After completing each process, the operator selects the next process operation button to finally complete the refueling of the aircraft.

[0093] It should be noted that similar numbers and letters represent similar items in the following figures. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. In addition, the terms "first", "second", "third", etc. are only used to distinguish the description and are not to be understood as indicating or implying relative importance.

[0094] Finally, it should be noted that the above-described embodiments are only specific implementation methods of the present application, which are used to illustrate the technical solutions of the present application, rather than to limit them. The scope of protection of the present application is not limited thereto. Although the present application has been described in detail with reference to the above-described embodiments, those skilled in the art should understand that any person skilled in the art can modify or easily conceive of changes to the technical solutions described in the above-described embodiments within the technical scope disclosed in the present application, or perform equivalent replacements for some of the technical features thereof. However, these modifications, changes, or replacements do not deviate from the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present application. They should all be included in the scope of protection of the present application. Therefore, the scope of protection of the present application shall be subject to the scope of protection of the claims.

Claims

1. A fuel delivery device, characterized in that: The fuel delivery device includes: a control device, an oil pump, and an oil storage device; wherein the control device is connected to the oil pump, and the oil pump is connected to the aircraft fuel tank via a first oil circuit, and a three-way valve is also provided on the first oil circuit; the oil pump is also connected to the oil storage device via a second oil circuit; The control device is used to control the oil pump to rotate forward and control the three-way valve to lose power, thereby exhausting the air in the first oil circuit and the second oil circuit; The control device is used to control the forward rotation of the oil pump and the power supply of the three-way valve to refuel the aircraft fuel tank from the oil storage device; The control device is further used to control the oil pump to reverse and control the three-way valve to be energized, so as to pump oil from the aircraft oil tank to the oil storage device.

2. The fuel delivery device according to claim 1, characterized in that The fuel delivery device also includes a selection switch; The selection switch is used to select the manual mode or the automatic mode of the control device; In manual mode, the control device controls the exhaust of air from the first oil circuit and the second oil circuit, controls the oil pump to refuel the aircraft fuel tank from the fuel storage device, or controls the oil pump to pump fuel from the aircraft fuel tank to the fuel storage device according to user input operations at each stage; In the automatic mode, the control device automatically controls the oil pump to discharge air from the first oil circuit and the second oil circuit, controls the oil pump to refuel the aircraft fuel tank from the oil storage device, or controls the oil pump to pump fuel from the aircraft fuel tank to the oil storage device according to preset control parameters.

3. The fuel delivery device according to claim 2, characterized in that The control parameters include weight parameters and pressure parameters; In the automatic mode, the control device automatically controls the oil pump to refuel the aircraft fuel tank from the oil storage device or to pump oil from the aircraft fuel tank to the oil storage device according to preset control parameters, including: In the automatic mode, the control device automatically controls the oil pump to refuel the aircraft fuel tank from the oil storage device according to the weight parameter of the weighing sensor and the pressure parameter of the pressure sensor; In the automatic mode, the control device automatically controls the oil pump to pump oil from the aircraft oil tank to the oil storage device according to the pressure parameter of the pressure sensor.

4. The fuel delivery device according to claim 2, characterized in that When the selection switch points to the manual control circuit, the manual module of the control device is selected; The manual control circuit includes an oil pumping button SB1, an exhaust button SB2, a refueling button SB3, a stop button SB4, an oil pumping relay KM1, an exhaust relay KM2 and a refueling relay KM3; wherein, SB1, SB2 and SB3 are all interlocking buttons, each including two normally open sub-buttons and two normally closed sub-buttons.

5. The fuel delivery device according to claim 1, characterized in that The SB1 is a normally open contact and also includes normally closed contacts SB1_1 and SB1_2; the SB2 is a normally open contact and also includes normally closed contacts SB2_1 and SB2_2; the SB3 is a normally open contact and also includes normally closed contacts SB3_1 and SB3_2.

6. The fuel delivery device according to claim 2, characterized in that When the selection switch is directed to the automatic control circuit, the automatic module of the control device is selected; The automatic control circuit includes an air detector, a weighing sensor, a pressure sensor and a touch screen display; the air detector, the pressure sensor and the touch screen display are all connected to the control device.

7. The fuel delivery device according to claim 6, characterized in that The air detector is arranged on the first oil circuit and the second oil circuit, and the air detector is connected to the control device; The air detector is used to detect whether there is air in the first oil circuit and the second oil circuit; When air exists in the first oil circuit or the second oil circuit, a shutdown signal is sent to the control device; The control device is used to stop the operation of the oil pump according to the shutdown signal and issue an alarm.

8. The fuel delivery device according to claim 6, characterized in that The weighing sensor is used to determine the weight of the oil in the oil storage device and send the weight of the oil in the oil storage device to the control device; The pressure sensor is used to determine the pressure in the aircraft fuel tank and send the pressure in the aircraft fuel tank to the control device.

9. The fuel delivery device according to claim 6, characterized in that The touch screen display is used to display the refueling status and the oil pumping status; and is also used to generate control parameters in the automatic mode according to the user's operation.

10. A flight system, characterized in that: include: A fuel delivery device and an aircraft according to any one of claims 1 to 9.

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