One-key starting method of piston engine unmanned aerial vehicle

Abstract

The invention discloses a one-key starting method of a piston engine unmanned aerial vehicle. According to the invention, the starting process is integrated into one button operation, and the flight control system automatically completes the steps of fuel supply, preheating, ignition and the like, so that the operation process is greatly simplified, the takeoff preparation time is shortened, the starting efficiency is improved, and the unmanned aerial vehicle can be put into task execution more quickly. According to the one-key starting method, the starting process is automated, human errors are avoided, the starting success rate is increased, the engine fault risk is reduced, and the reliability of the unmanned aerial vehicle is improved. The system monitors engine state parameters such as the rotating speed, the oil pressure, the water temperature and the oil temperature in real time and judges whether starting conditions such as the preheating temperature and the accelerator position are met or not. And if abnormal conditions such as fault warning and insufficient preheating time are found, the flight control system can stop a starting program and give an alarm, so that the engine is prevented from being started in an abnormal state, the starting safety is improved, and the safety of personnel and equipment is guaranteed.

Description

Technical Field

[0001] The invention belongs to the technical field of unmanned aerial vehicle starting, and in particular relates to a one-button starting method for a piston engine unmanned aerial vehicle. Background Art

[0002] In the current market, piston engines are widely used as power in low-speed and low-altitude areas, with the characteristics of low fuel consumption, low cost, and reliable operation. The structure and working principle of aviation piston engines are basically the same as those of existing common automobile engines. Both rely on the combustion and explosion of gas in the cylinder to push the piston to do work. Therefore, many aviation piston engines are developed based on existing mature automobile engines. This leads to many accessories on aviation piston engines being used in automobiles, and the working principle of the control system has the shadow of automobile engines. For example, it is impossible to monitor any status information of the engine before the engine is enabled.

[0003] However, in order to take off according to normal procedures, the startup process of traditional aviation piston engines is relatively complicated, and it is necessary to follow the warm-up procedure to make the engine oil temperature, gearbox oil temperature and coolant temperature rise to the specified range. As a result, it takes a long time for the drone to reach the state of take-off permission, affecting the quickness of startup. Summary of the invention

[0004] The purpose of the present invention is to provide a one-key starting method for a piston engine drone in order to solve the above-mentioned problem.

[0005] The technical solution adopted by the present invention is as follows: a one-key starting method for a piston engine drone, the method comprising the following steps: S1: Receive the engine one-key start command sent by the ground station.

[0006] S2: Send a command to turn on the onboard fuel shut-off valve.

[0007] S3: After a period of time (no more than 1 second), send a command to turn on the onboard fuel pump.

[0008] S4: After a certain period of time (depending on the time it takes for the fuel in the tank to be supplied to the engine fuel inlet and reach a predetermined pressure), a power system enable signal is sent.

[0009] S5: Monitor whether the engine start conditions are met, including: Whether the engine throttle control is in the slow-speed state; Whether the fuel pressure at the engine inlet is within the predetermined range; Whether the engine oil temperature, gearbox oil temperature, engine coolant temperature, and engine fuel temperature are higher than the starting threshold value; Check whether there are engine and propeller failure alarms.

[0010] If any of the conditions are not met, the one-key start procedure ends and a failure reason prompt message is sent to the ground station.

[0011] S6: Monitor the preheating status; if the preheating does not work, proceed to the next step; if the preheating has worked, monitor whether there is a preheating fault alarm; if there is a preheating fault alarm, end the one-key start program and send a failure reason prompt message to the ground station; if there is no preheating fault alarm, execute this loop.

[0012] S7: Send a brake command; after a period of time (depending on the time from the aircraft sending the brake command to the actuator executing the command to reaching the preset brake pressure), check whether the brake pressure reaches the preset value.

[0013] S8: Send an engine start command.

[0014] S9: Monitor whether the lubricating oil pressure is established within the predetermined time; monitor whether the speed exceeds the starter disengagement speed or is approaching the restricted use time. If any of the conditions is met, a starter disengagement command is sent, whichever comes first; monitor whether the speed reaches the idle speed within the predetermined time and stabilizes within the allowable range; monitor whether the idle speed sliding oil pressure is within the predetermined range.

[0015] If all the above monitoring conditions are met, a warm-up command will be sent after a period of time, that is, the throttle will be increased to a predetermined control amount; the engine oil temperature, gearbox oil temperature, and engine coolant temperature will be monitored to see if they are higher than the operating threshold value.

[0016] S10: If all three conditions are met, the one-key start ends, and a successful start prompt message is sent to the ground station, after which the one-key start process of the entire piston engine drone ends. The start process is integrated into a button operation, and the flight control system automatically completes the fuel supply, preheating, ignition and other steps, which greatly simplifies the operation process, shortens the takeoff preparation time, improves the start efficiency, and enables the drone to be put into mission execution faster. The one-key start method automates the start process, avoids human errors, improves the start success rate, reduces the risk of engine failure, and improves the reliability of the drone. At the same time, in the start method, the flight control system monitors the engine status parameters in real time, such as speed, oil pressure, water temperature, oil temperature, etc., and determines whether the start conditions are met, such as preheating temperature, throttle position, etc. If an abnormal situation is found, such as a fault alarm, insufficient preheating time, etc., the flight control system will stop the start program and issue a warning, avoiding the engine from starting in an abnormal state, improving the start safety, and ensuring the safety of personnel and equipment. The one-key start method can avoid excessive impact on the engine during cold start by accurately controlling the engine start process, such as preheating time, throttle control, etc., thereby extending the engine life. In addition, real-time monitoring of engine status parameters and timely adjustments can avoid problems such as engine overheating or poor lubrication, further extending engine life and reducing maintenance costs.

[0017] In a preferred embodiment, in step S1, the command is sent via a remote control or a ground control station and includes a signal to start the engine. After receiving the command, the flight control system will start the one-key start program and execute subsequent steps. The command can be sent using a wireless communication protocol, such as a 433MHz or 2.4GHz frequency band, and has a data encryption function to ensure the security and reliability of the command. The command data packet includes information such as a start command and a security code. After receiving the command, the flight control system will verify the security code and confirm the validity of the command.

[0018] In a preferred embodiment, in step S2, a command is sent to turn on the onboard fuel shut-off valve, and after a period of time (no more than 1 second), a command is sent to turn on the onboard fuel pump. The fuel shut-off valve is located in the fuel line and is used to control the flow of fuel to the engine. After the fuel shut-off valve is turned on, the fuel begins to flow into the engine. The fuel pump is used to transport fuel from the fuel tank to the engine. The interval time is to ensure that the fuel pump is started after the fuel shut-off valve is fully opened to avoid fuel backflow. The fuel pump can be started by an electric pump or a mechanical pump, and is equipped with a pressure sensor to monitor the fuel pressure in real time to ensure a stable fuel supply. The power of the electric pump is several hundred watts, while the mechanical pump is driven by the engine speed. The pressure range monitored by the fuel pressure sensor is 0-6bar, with an accuracy of 0.1bar.

[0019] In a preferred embodiment, in step S3, the fuel shut-off valve is located in the fuel pipeline to control the flow of fuel to the engine. After the fuel shut-off valve is turned on, the fuel begins to flow into the engine. The fuel pump is used to transport the fuel from the fuel tank to the engine. The interval time is to ensure that the fuel pump is started after the fuel shut-off valve is fully opened to avoid fuel backflow. The fuel pump can be started by an electric pump or a mechanical pump, and equipped with a pressure sensor to monitor the fuel pressure in real time to ensure a stable fuel supply. The power of the electric pump is several hundred watts, while the mechanical pump is driven by the engine speed. The pressure range monitored by the fuel pressure sensor is 0-6bar with an accuracy of 0.1bar.

[0020] In a preferred embodiment, in step S4, the signal activates the engine control unit (ECU) and other related systems to prepare for the engine start. The interval time depends on the design of the fuel system, and the engine can only be started after the fuel pressure is stable. The ECU is responsible for controlling the engine's ignition, fuel injection, air intake and other processes, and monitors the engine status in real time to ensure the safe operation of the engine. The control strategy of the ECU can be adjusted according to the engine type and operating status, such as idle speed control, throttle control, fault diagnosis, etc.

[0021] In a preferred embodiment, in step S5, the throttle controls the engine speed, and the speed in the slow-speed state is 600-800 rpm; The preset range of fuel pressure is 2-3 bar, with an accuracy of 0.1 bar; The startup threshold is 20-30℃ with an accuracy of 1℃.

[0022] In a preferred embodiment, in step S6, the preheating system is used to heat the engine to a starting temperature. The preheating time depends on the ambient temperature and the engine power, and takes from tens of seconds to several minutes. During the preheating process, it is necessary to monitor the preheating temperature and preheating time, and ensure that the preheating system operates normally. The monitoring range of the preheating temperature is 20-60°C, with an accuracy of 1°C.

[0023] In a preferred embodiment, in step S7, the interval depends on the time from when the aircraft sends a braking command to when the actuator executes the command until a predetermined braking pressure is reached.

[0024] In a preferred embodiment, in step S8, parameters such as engine speed, oil pressure, water temperature, etc. need to be monitored during the startup process to ensure that the engine starts normally.

[0025] Monitor whether the speed exceeds the starter disengagement speed or approaches the restricted usage time. If either condition is met, a starter disengagement command is sent, whichever comes first.

[0026] Starter disengagement speed: refers to the speed at which the engine can continue to run on its own power without the need for the starter to provide power after the engine speed reaches a certain value. This speed depends on the engine power and starting status.

[0027] Limited use time: refers to the continuous working time of the starter to avoid overheating and damage to the starter. This time depends on the type and power of the starter. For example, a starter with a larger power can be used for a longer time. For example, the starter limited use time may be 15-20 seconds.

[0028] Speed ​​monitoring: Real-time monitoring of engine speed to ensure it reaches the starter disengagement speed or approaches the limit of use time.

[0029] Starter disengagement command: When the engine speed reaches the starter disengagement speed or approaches the limited usage time, the flight control system sends a command to disconnect the starter circuit and the starter stops working.

[0030] In a preferred embodiment, in step S9, the monitoring of the idle speed needs to ensure that the engine speed is stable within a predetermined range and meets a certain cumulative time. The monitoring of the idle speed oil pressure needs to ensure that the engine lubrication system works normally. The starter disengagement speed is higher than 500rpm, and the cumulative time is 5 to 10 seconds. The monitoring range of the idle speed is 600-800rpm, the cumulative time is 30 to 60 seconds, and the swing tolerance is 10-20rpm. The monitoring range of the idle speed oil pressure is 1-2bar, and the accuracy is 0.1bar.

[0031] In summary, due to the adoption of the above technical solution, the beneficial effects of the present invention are: 1. In the present invention, the startup process is integrated into a button operation, and the flight control system automatically completes the steps of fuel supply, preheating, ignition, etc., which greatly simplifies the operation process, shortens the takeoff preparation time, improves the startup efficiency, and enables the UAV to be put into mission execution faster. The one-button startup method automates the startup process, avoids human errors, improves the startup success rate, reduces the risk of engine failure, and improves the reliability of the UAV.

[0032] 2. In the present invention, the flight control system in the one-button start method monitors the engine status parameters in real time, including speed, oil pressure, water temperature, oil temperature, etc., and determines whether the start conditions are met, including preheating temperature, throttle position, etc. If an abnormal situation is found, including a fault alarm, insufficient preheating time, etc., the flight control system will stop the start program and issue a warning, thereby avoiding the engine from starting under abnormal conditions, improving the start safety, and ensuring the safety of personnel and equipment. The one-button start method can avoid excessive impact on the engine during cold start by accurately controlling the engine start process, including preheating time, throttle control, etc., thereby extending the service life of the engine. In addition, real-time monitoring of engine status parameters and timely adjustment can avoid problems such as engine overheating or poor lubrication, further extending the engine life and reducing maintenance costs.

[0033] 3. In the present invention, the startup process is simplified, the take-off preparation time is shortened, the availability of the UAV is improved, the UAV can perform tasks faster, and the delay or cancellation of tasks caused by startup problems is reduced. This improves the mission execution efficiency of the UAV and enables it to better meet the needs of various application scenarios. The one-button startup method of the piston engine UAV simplifies the startup process, improves safety, prolongs the engine life, and improves the availability of the UAV through automation, intelligence, and precise control, which has brought great impetus to the development and application of UAVs. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 The figure is a flow chart of the method of the present invention. DETAILED DESCRIPTION

[0035] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0036] Reference Figure 1 , A one-button starting method for a piston engine drone, the method comprising the following steps: S1: Receive the engine one-key start command sent by the ground station.

[0037] S2: Send a command to turn on the onboard fuel shut-off valve.

[0038] S3: After a period of time (no more than 1 second), send a command to turn on the onboard fuel pump.

[0039] S4: After a certain period of time (depending on the time it takes for the fuel in the tank to be supplied to the engine fuel inlet and reach a predetermined pressure), a power system enable signal is sent.

[0040] S5: Monitor whether the engine start conditions are met, including: Whether the engine throttle control amount is in the slow-speed state; Whether the fuel pressure at the engine inlet is within the predetermined range; Whether the engine oil temperature, gearbox oil temperature, engine coolant temperature, and engine fuel temperature are higher than the starting threshold value; Check whether there are engine and propeller failure alarms.

[0041] If any of the conditions are not met, the one-key start procedure ends and a failure reason prompt message is sent to the ground station.

[0042] S6: Monitor the preheating status; if the preheating does not work, proceed to the next step; if the preheating has worked, monitor whether there is a preheating fault alarm; if there is a preheating fault alarm, end the one-key start program and send a failure reason prompt message to the ground station; if there is no preheating fault alarm, execute this loop.

[0043] S7: Send a brake command; after a period of time (depending on the time from the aircraft sending the brake command to the actuator executing the command to reaching the preset brake pressure), check whether the brake pressure reaches the preset value.

[0044] S8: Send an engine start command.

[0045] S9: Monitor whether the lubricating oil pressure is established within the predetermined time; monitor whether the speed exceeds the starter disengagement speed or is approaching the restricted use time. If any of the conditions is met, a starter disengagement command is sent, whichever comes first; monitor whether the speed reaches the idle speed within the predetermined time and stabilizes within the allowable range; monitor whether the idle speed sliding oil pressure is within the predetermined range.

[0046] If all the above monitoring conditions are met, a warm-up command will be sent after a period of time, that is, the throttle will be increased to a predetermined control amount; the engine oil temperature, gearbox oil temperature, and engine coolant temperature will be monitored to see if they are higher than the operating threshold value.

[0047] S10: If all three conditions are met, the one-key start is completed, and a successful start prompt message is sent to the ground station, after which the one-key start process of the entire piston engine drone is completed.

[0048] In step S1, the command is sent through the remote control or ground control station and contains a signal to start the engine. After receiving the command, the flight control system will start the one-button start program and execute the subsequent steps. The command can be sent using a wireless communication protocol, such as the 433MHz or 2.4GHz frequency band, and has a data encryption function to ensure the security and reliability of the command. The command data packet contains information such as the start command and the security code. After receiving the command, the flight control system will verify the security code and confirm the validity of the command.

[0049] In step S2, a command is sent to turn on the onboard fuel shut-off valve, and after a period of time (no more than 1 second), a command is sent to turn on the onboard fuel pump. The fuel shut-off valve is located in the fuel line and is used to control the flow of fuel to the engine. After the fuel shut-off valve is turned on, the fuel begins to flow into the engine. The fuel pump is used to transport fuel from the fuel tank to the engine. The interval is to ensure that the fuel pump is started after the fuel shut-off valve is fully opened to avoid fuel backflow. The fuel pump can be started by an electric pump or a mechanical pump, and is equipped with a pressure sensor to monitor the fuel pressure in real time to ensure a stable fuel supply. The power of the electric pump is several hundred watts, while the mechanical pump is driven by the engine speed. The pressure range monitored by the fuel pressure sensor is 0-6bar with an accuracy of 0.1bar.

[0050] In step S3, the fuel shut-off valve is located in the fuel line and is used to control the flow of fuel to the engine. After the fuel shut-off valve is turned on, the fuel starts to flow into the engine. The fuel pump is used to transport the fuel from the fuel tank to the engine. The interval time is to ensure that the fuel pump is started after the fuel shut-off valve is fully opened to avoid fuel backflow. The fuel pump can be started by an electric pump or a mechanical pump, and is equipped with a pressure sensor to monitor the fuel pressure in real time to ensure a stable fuel supply. The power of the electric pump is several hundred watts, while the mechanical pump is driven by the engine speed. The pressure range monitored by the fuel pressure sensor is 0-6bar with an accuracy of 0.1bar.

[0051] In step S4, the signal activates the engine control unit (ECU) and other related systems to prepare for the engine start. The interval time depends on the design of the fuel system, and the engine can only be started after the fuel pressure is stable. The ECU is responsible for controlling the engine's ignition, fuel injection, air intake and other processes, and monitors the engine status in real time to ensure the safe operation of the engine. The control strategy of the ECU can be adjusted according to the engine type and operating status, such as idle speed control, throttle control, fault diagnosis, etc.

[0052] In step S5, the throttle controls the engine speed, and the speed in the slow-speed state is 600-800 rpm; The preset range of fuel pressure is 2-3 bar, with an accuracy of 0.1 bar; The start threshold is 20-30℃, with an accuracy of 1℃ In step S6, the preheating system is used to heat the engine to the starting temperature. The preheating time depends on the ambient temperature and the engine type, and takes from tens of seconds to more than ten minutes. During the preheating process, it is necessary to monitor the preheating temperature and preheating time, and ensure that the preheating system operates normally. The monitoring range of the preheating temperature is 20-60℃, with an accuracy of 1℃.

[0053] In step S7, the interval depends on the time from when the aircraft sends a braking command to when the actuator executes the command until the predetermined braking pressure is reached.

[0054] In step S8, during the startup process, parameters such as engine speed, oil pressure, and water temperature need to be monitored to ensure that the engine starts normally; Monitor whether the speed exceeds the starter disengagement speed or approaches the restricted usage time. If either condition is met, a starter disengagement command is sent, whichever comes first.

[0055] Starter disengagement speed: refers to the speed at which the starter no longer provides power after the engine speed reaches a certain value, and the engine continues to run on its own power. The speed depends on the engine type and starting status.

[0056] Limited use time: refers to the continuous working time of the starter to avoid overheating and damage to the starter. This time depends on the type and power of the starter. For example, a starter with a larger power can be used for a longer time. For example, the starter limited use time may be 15-20 seconds.

[0057] Speed ​​monitoring: Real-time monitoring of engine speed to ensure it reaches the starter disengagement speed or approaches the limit of use time.

[0058] Starter disengagement command: When the engine speed reaches the starter disengagement speed or approaches the limited usage time, the flight control system sends a command to disconnect the starter circuit and the starter stops working.

[0059] In step S9, the monitoring of the idle speed needs to ensure that the engine speed is stable within a predetermined range and meets a certain cumulative time. The monitoring of the idle speed oil pressure needs to ensure that the engine lubrication system works normally. The starter disengagement speed is higher than 500rpm, and the cumulative time is 5 to 10 seconds. The monitoring range of the idle speed is 600-800rpm, the cumulative time is 30 to 60 seconds, and the swing tolerance is 10-20rpm. The monitoring range of the idle speed oil pressure is 1-2bar, and the accuracy is 0.1bar.

[0060] In the present invention, the operation is simplified and the efficiency is improved: The traditional startup process requires the pilot to perform multiple steps, which is time-consuming, labor-intensive and error-prone. The one-button startup method integrates the startup process into one button operation, and the flight control system automatically completes the fuel supply, preheating, ignition and other steps, which greatly simplifies the operation process, shortens the takeoff preparation time, improves the startup efficiency, and enables the drone to be put into mission execution faster.

[0061] In the present invention, the difficulty of operation and human error are reduced: UAV pilots may lack experience in operating aircraft engines and are prone to operating errors during the startup process, such as improper throttle control, insufficient preheating time, etc., which may lead to engine startup failure or damage. The one-button startup method automates the startup process, avoids human errors, improves the startup success rate, reduces the risk of engine failure, and improves the reliability of the UAV.

[0062] In the present invention, real-time monitoring and safety assurance are achieved: In the one-button start method, the flight control system monitors the engine status parameters in real time, such as speed, oil pressure, water temperature, oil temperature, etc., and determines whether the start conditions are met, such as preheating temperature, throttle position, etc. If an abnormal situation is found, such as a fault alarm, insufficient preheating time, etc., the flight control system will stop the start procedure and issue a warning, avoiding the engine from starting in an abnormal state, improving the start safety, and ensuring the safety of personnel and equipment.

[0063] In the present invention, the engine life is extended: The one-button start method can avoid excessive impact on the engine during cold start by accurately controlling the engine start process, such as preheating time, throttle control, etc., thereby extending the engine life. In addition, real-time monitoring of engine status parameters and timely adjustment can avoid problems such as engine overheating or poor lubrication, further extending the engine life and reducing maintenance costs.

[0064] In the present invention, the UAV usability is improved: The one-key start method simplifies the start-up process, shortens the take-off preparation time, improves the UAV usability, enables it to perform tasks faster, and reduces task delays or cancellations caused by start-up problems. This improves the task execution efficiency of the UAV, enabling it to better meet the needs of various application scenarios.

[0065] In summary, the one-button start method of piston engine drones simplifies the startup process, improves safety, extends engine life and increases drone availability through automation, intelligence and precise control, which has brought great impetus to the development and application of drones.

[0066] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the term "comprises" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprises a ..." do not exclude the existence of other identical elements in the process, method, article or device including the elements.

[0067] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit the same. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that the technical solutions described in the aforementioned embodiments may still be modified, or some of the technical features may be replaced by equivalents. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A one-button starting method for a piston engine drone, characterized in that: The method comprises the following steps: S1: Receive the engine one-key start command sent by the ground station; S2: Send a command to connect the onboard fuel shut-off valve; S3: After a period of time, no more than 1 second, a command is sent to turn on the onboard fuel pump; S4: after a certain period of time, which depends on the time when the fuel in the fuel tank is supplied to the fuel inlet of the engine and reaches a predetermined pressure, a power system enable signal is sent; S5: Monitor whether the engine start conditions are met, including: whether the engine throttle control is in the slow state; whether the engine inlet fuel pressure is within the preset range; whether the engine lubricating oil temperature, gearbox lubricating oil temperature, engine coolant temperature, and engine fuel temperature are higher than the start threshold value; whether the engine and propeller fault alarms appear; If any of the conditions are not met, the one-key start procedure ends and a failure reason prompt message is sent to the ground station; S6: monitor the preheating status; if the preheating does not work, proceed to the next step; if the preheating has worked, monitor whether there is a preheating fault alarm; if there is a preheating fault alarm, end the one-key start program and send a failure reason prompt message to the ground station; if there is no preheating fault alarm, execute this loop; S7: Send a brake command; after a period of time, which depends on the time from when the aircraft sends the brake command to when the actuator executes the command until the predetermined brake pressure is reached, check whether the brake pressure reaches the predetermined value; S8: Sending an engine start command; S9: monitor whether the lubricating oil pressure is established within a predetermined time; monitor whether the speed exceeds the starter disengagement speed or approaches the restricted use time, and if any of the conditions is met, send a starter disengagement command, whichever comes first; monitor whether the speed reaches the idle speed within a predetermined time and stabilizes within the allowable range; monitor whether the oil pressure at idle speed is within a predetermined range; If the above monitoring conditions are met, a warm-up command is sent after a period of time, that is, the throttle is increased to a predetermined control amount; the engine oil temperature, gearbox oil temperature, and engine coolant temperature are monitored to see if they are higher than the working threshold value; S10: If all three conditions are met, the one-key start is completed, and a successful start prompt message is sent to the ground station, after which the one-key start process of the entire piston engine drone is completed.

2. A one-key start method for a piston engine drone as claimed in claim 1, characterized in that: In step S1, the instruction is sent through the remote control or the ground control station and includes a signal for starting the engine; after receiving the instruction, the flight control system will start the one-key start program and execute subsequent steps; the instruction is sent using a wireless communication protocol and has a data encryption function to ensure the security and reliability of the instruction; the instruction data packet includes a start instruction and a security code information. After receiving the instruction, the flight control system will verify the security code and confirm the validity of the instruction.

3. The one-key starting method for a piston engine drone according to claim 1, characterized in that: In step S2, a command is sent to turn on the onboard fuel shut-off valve, and after a period of time, a command is sent to turn on the onboard fuel pump; the fuel shut-off valve is located in the fuel pipeline and is used to control the flow of fuel to the engine; after the fuel shut-off valve is turned on, the fuel begins to flow into the engine; the fuel pump is used to transport fuel from the fuel tank to the engine; the interval time is to ensure that the fuel pump is started after the fuel shut-off valve is fully opened to avoid fuel backflow; the fuel pump is started by an electric pump or a mechanical pump, and is equipped with a pressure sensor to monitor the fuel pressure in real time to ensure a stable fuel supply; the power of the electric pump is several hundred watts, and the mechanical pump is driven by the engine speed; the pressure range monitored by the fuel pressure sensor is 0-6bar, and the accuracy is 0.1bar.

4. The one-key starting method for a piston engine drone according to claim 1, characterized in that: In step S3, the fuel cut-off valve is located in the fuel pipeline and is used to control the flow of fuel to the engine; after the fuel cut-off valve is turned on, the fuel starts to flow into the engine; and the fuel pump is used to transport the fuel from the fuel tank to the engine.

5. The one-key starting method for a piston engine drone as claimed in claim 1, characterized in that: In step S4, the signal activates the engine control unit (ECU) and other related systems to prepare for the engine start; the interval time depends on the design of the fuel system to ensure that the engine can be started only after the fuel pressure is stable; The ECU is responsible for controlling the engine's ignition, fuel injection, and air intake processes, and monitors the engine status in real time to ensure safe engine operation; the ECU's control strategy is adjusted according to the engine type and operating status.

6. The one-key starting method for a piston engine drone according to claim 1, characterized in that: In step S5, the throttle controls the engine speed, and the speed in the slow-speed state is 600-800 rpm; The preset range of fuel pressure is 2-3 bar, with an accuracy of 0.1 bar; The startup threshold is -20℃ with an accuracy of 1℃.

7. The one-key starting method for a piston engine drone according to claim 1, characterized in that: In step S6, the preheating system is used to heat the engine to reach the starting temperature; the preheating time depends on the ambient temperature and the engine type, and takes tens of seconds to several minutes; the preheating temperature and preheating time need to be monitored during the preheating process, and the normal operation of the preheating system needs to be ensured; the monitoring range of the preheating temperature is 20-60°C, with an accuracy of 1°C.

8. The one-key starting method for a piston engine drone as claimed in claim 1, characterized in that: In step S7, the interval time depends on the time from when the aircraft sends a braking command to when the actuator executes the command until a predetermined braking pressure is reached.

9. The one-key starting method for a piston engine drone according to claim 1, characterized in that: In step S8, the engine speed, oil pressure, and water temperature parameters need to be monitored during the startup process to ensure that the engine starts normally; Monitor whether the speed exceeds the starter disengagement speed or approaches the limit time. If either condition is met, a starter disengagement command is sent, whichever comes first; Starter disengagement speed: refers to when the engine speed reaches a certain value, the starter no longer provides power, and the engine continues to run on its own power; Limiting the use time: refers to the continuous working time of the starter to avoid overheating and damage to the starter; Speed ​​monitoring: monitor the engine speed in real time to ensure it reaches the starter disengagement speed; Starter disengagement command: When the engine speed reaches the starter disengagement speed or approaches the limited usage time, the flight control system sends a command to disconnect the starter circuit and the starter stops working.

10. The one-key starting method for a piston engine drone according to claim 1, characterized in that: In step S9, the monitoring of the idle speed needs to ensure that the engine speed is stable within a predetermined range and meets a certain cumulative time; the monitoring of the idle glide oil pressure needs to ensure that the engine lubrication system works normally; the starter disengagement speed is higher than 500rpm, and the cumulative time is 5 to 10 seconds; the monitoring range of the idle speed is 600-800rpm, the cumulative time is 30 to 60 seconds, and the swing tolerance is 10-20rpm; the monitoring range of the idle glide oil pressure is 1-2bar, and the accuracy is 0.1bar.

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