One key start method for piston engine unmanned aerial vehicle

Abstract

The present invention discloses a one-button starting method for a piston engine UAV. In the present invention, the starting 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 operating process, shortens the takeoff preparation time, improves the starting efficiency, and enables the UAV to be put into mission execution more quickly. The one-button starting method automates the starting process, avoids human errors, improves the success rate of starting, reduces the risk of engine failure, and improves the reliability of the UAV. The system monitors the engine status parameters in real time, such as speed, oil pressure, water temperature, oil temperature, etc., and determines whether the starting 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 starting program and issue a warning, avoiding the engine starting in an abnormal state, improving the starting safety, and ensuring the safety of personnel and equipment.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of unmanned aerial vehicle starting, and particularly relates to a one-key starting method for a piston engine unmanned aerial vehicle. BACKGROUND

[0002] At present, piston engines are widely used in the low-speed and low-altitude field in the market, and have the characteristics of low fuel consumption, low cost and reliable work. The aviation piston engine and the existing common automobile engine are basically consistent in structure and working principle, and both rely on the combustion of gas in the cylinder to drive the piston to work, so many aviation piston engines are developed based on the existing mature automobile engines. This leads to the fact that many accessories on the aviation piston engine are for vehicles, and the working principle of the control system has the shadow of the automobile engine. For example, the engine cannot be monitored before being enabled.

[0003] However, in order to take off normally, the starting process of the traditional aviation piston engine is relatively complex, and the engine oil temperature, gear box oil temperature and cooling liquid temperature all need to be raised to the specified range according to the warm-up program. Therefore, the time for the unmanned aerial vehicle to reach the state of taking off permission is relatively long, which affects the quickness of starting. SUMMARY

[0004] The purpose of the application is to solve the above-mentioned problems, and provide a one-key starting method for a piston engine unmanned aerial vehicle.

[0005] The technical scheme adopted by the application is as follows: a one-key starting method for a piston engine unmanned aerial vehicle, the method comprising the following steps:

[0006] S1: receiving an engine one-key starting instruction sent by a ground station.

[0007] S2: sending an instruction to connect an on-board fuel cut-off valve.

[0008] S3: after a period of time (not more than 1 second), sending an instruction to connect an on-board fuel pump.

[0009] S4: after a period of time (depending on the time for the fuel tank to supply fuel to the engine fuel inlet and reach the predetermined pressure), sending a power system enable signal.

[0010] S5: monitoring whether the engine starting conditions are met, including:

[0011] whether the engine throttle control amount is in the slow vehicle state;

[0012] whether the engine inlet fuel pressure is in the predetermined range;

[0013] Engine oil temperature, gearbox oil temperature, engine coolant temperature, engine fuel temperature are higher than start threshold value or not;

[0014] Engine and propeller fault alarm appears or not.

[0015] If any condition is not met, end the one-key start procedure, and send the failure cause prompt information to the ground station.

[0016] S6: Monitor the preheating state; if the preheating is not working, proceed to the next step; if the preheating is working, monitor whether there is a preheating fault alarm; if there is a preheating fault alarm, end the one-key start procedure, and send the failure cause prompt information to the ground station; if there is no preheating fault alarm, execute this cycle.

[0017] S7: Send brake command; after a period of time (depending on the time from when the aircraft sends the brake command to the actuator executes the command to when the predetermined brake pressure is reached), check whether the brake pressure reaches the predetermined value.

[0018] S8: Send engine start command.

[0019] S9: Monitor whether the oil pressure is established within the predetermined time; monitor whether the rotation speed exceeds the starter disengagement rotation speed or approaches the limited use time, send the starter disengagement command if any condition is met, whichever comes first; monitor whether the rotation speed reaches the idle rotation speed within the predetermined time and is stable within the allowed range; monitor whether the oil pressure under idle is within the predetermined range.

[0020] If the above monitoring conditions are met, after a period of time, send the warm-up command, i.e. increase the throttle to the predetermined control amount; monitor whether the engine oil temperature, gearbox oil temperature, engine coolant temperature are higher than the working threshold value or not.

[0021] S10: If all three conditions are met, the one-key start ends, and a start success prompt information is sent to the ground station, and then the one-key start process of the entire piston engine unmanned aerial vehicle ends. The start process is integrated into a button operation, and the flight control system automatically completes the steps of fuel supply, preheating, ignition, etc., greatly simplifying the operation process, shortening the take-off preparation time, improving the start efficiency, and enabling the unmanned aerial vehicle to be put into task execution faster. The one-key start method automates the start process, avoids human errors, improves the start success rate, reduces the engine failure risk, and improves the reliability of the unmanned aerial vehicle. At the same time, in the start method, the flight control system monitors the engine state parameters in real time, such as the speed, oil pressure, water temperature, oil temperature, etc., and judges whether the start conditions are met, such as the preheating temperature, throttle position, etc. If abnormal conditions are found, such as fault alarms, insufficient preheating time, etc., the flight control system will stop the start program and issue a warning, avoiding the engine starting in an abnormal state, improving the start safety, and protecting the safety of personnel and equipment. The one-key start method can avoid excessive impact on the engine during cold start by precisely controlling the engine start process, such as preheating time, throttle control, etc., thereby prolonging the service life of the engine. In addition, real-time monitoring of engine state parameters and timely adjustment can avoid engine overheating or poor lubrication, further prolonging the engine life and reducing maintenance costs.

[0022] In a preferred embodiment, in step S1, the instruction is sent through a remote controller or a ground control station and contains a signal to start the engine. After receiving the instruction, the flight control system starts the one-key start program and executes the subsequent steps. The instruction can be sent using a wireless communication protocol, such as 433MHz or 2.4GHz frequency band, and has data encryption function to ensure the safety and reliability of the instruction. The instruction data packet contains start instruction, security code, etc. After receiving the instruction, the flight control system will verify the security code and confirm the validity of the instruction.

[0023] In a preferred embodiment, in step S2, the instruction is sent to turn on the on-board fuel cut-off valve, and after a certain interval (not more than 1 second), the instruction is sent to turn on the on-board fuel pump. The fuel cut-off valve is located in the fuel pipeline and is used to control the flow of fuel to the engine. After turning on the fuel cut-off valve, fuel begins to flow into the engine. The fuel pump is used to deliver fuel from the fuel tank to the engine. The interval time is to ensure that the fuel cut-off valve is fully opened before starting the fuel pump to avoid backflow of fuel. The start of the fuel pump can use an electric pump or a mechanical pump, and is equipped with a pressure sensor to monitor the fuel pressure in real time to ensure stable fuel supply. The power of the electric pump is several hundred watts, and the mechanical pump is driven by the engine speed. The fuel pressure sensor monitors the pressure in the range of 0-6bar with an accuracy of 0.1bar.

[0024] In a preferred embodiment, in step S3, a fuel shutoff valve is located in the fuel line to control the flow of fuel to the engine. After the fuel shutoff valve is turned on, fuel begins to flow into the engine. A fuel pump is used to deliver fuel from the tank to the engine. The interval time is to ensure that the fuel pump is started after the fuel shutoff valve is fully opened to avoid backflow of fuel. The start of the fuel pump can be an electric pump or a mechanical pump, and is equipped with a pressure sensor to monitor the fuel pressure in real time to ensure stable fuel supply. The power of the electric pump is several hundred watts, and the mechanical pump is driven by the engine speed. The fuel pressure sensor monitors the pressure in the range of 0-6bar with an accuracy of 0.1bar.

[0025] In a preferred embodiment, in step S4, the signal activates the engine control unit (ECU) and other related systems to prepare for engine start. The interval time depends on the design of the fuel system to ensure that the engine is started after the fuel pressure is stable. The ECU is responsible for controlling the ignition, fuel injection, air intake and other processes of the engine, and monitors the engine state in real time to ensure the safe operation of the engine. The control strategy of the ECU can be adjusted according to the type and operating state of the engine, such as idle control, throttle control, fault diagnosis, etc.

[0026] In a preferred embodiment, in step S5, the throttle controls the speed of the engine, and the speed in the slow vehicle state is 600-800rpm;

[0027] The predetermined range of fuel pressure is 2-3bar with an accuracy of 0.1bar;

[0028] The start threshold is 20-30℃ with an accuracy of 1℃.

[0029] In a preferred embodiment, 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 engine power, which takes tens of seconds to several minutes. The preheating temperature and preheating time need to be monitored during the preheating process to ensure the normal operation of the preheating system. The monitoring range of the preheating temperature is 20-60℃ with an accuracy of 1℃.

[0030] In a preferred embodiment, in step S7, the interval time depends on the time from the aircraft sending the brake command to the actuator executing the command to reaching the predetermined brake pressure.

[0031] In a preferred embodiment, in step S8, during the start process, the engine speed, oil pressure, water temperature and other parameters need to be monitored to ensure the normal start of the engine.

[0032] The speed is monitored to see if it exceeds the starter disengagement speed or is close to the limit of use time. If either condition is met, the starter disengagement command is sent, and the first one to arrive is used.

[0033] Start motor disengagement speed: refers to the engine speed at which the engine can continue to operate on its own power without the need for the starter motor to provide power. This speed depends on the engine power and starting state.

[0034] Limited use time: refers to the continuous working time of the starter motor to avoid overheating and damage. This time depends on the type and power of the starter motor, for example, a larger power starter motor can be used for a longer time. For example, the limited use time of the starter motor may be 15-20 seconds.

[0035] Speed monitoring: real-time monitoring of engine speed to ensure that it reaches the starter motor disengagement speed or is close to the limited use time.

[0036] Starter motor disengagement command: when the engine speed reaches the starter motor disengagement speed or is close to the limited use time, the flight control system sends a command to disconnect the starter motor circuit, and the starter motor stops working.

[0037] In a preferred embodiment, the monitoring of the idle speed in step S9 requires that the engine speed be stabilized within a predetermined range and meet a certain cumulative time. The monitoring of the idle down oil pressure requires that the engine lubrication system be working properly. The starter motor disengagement speed is higher than 500 rpm, and the cumulative time is 5-10 seconds. The monitoring range of the idle speed is 600-800 rpm, the cumulative time is 30-60 seconds, and the swing tolerance is 10-20 rpm. The monitoring range of the idle down oil pressure is 1-2 bar, and the accuracy is 0.1 bar.

[0038] In summary, due to the adoption of the above technical solutions, the beneficial effects of the present application are:

[0039] 1、In the present application, the starting process is integrated into a button operation, and the flight control system automatically completes the steps of fuel supply, preheating, ignition, etc., greatly simplifying the operation process, shortening the takeoff preparation time, improving the starting efficiency, and enabling the unmanned aerial vehicle to be put into task execution faster. The one-key starting method automates the starting process, avoids human errors, improves the starting success rate, reduces the engine failure risk, and improves the reliability of the unmanned aerial vehicle.

[0040] 2、In the present application, the engine state parameters are monitored in real time by the flight control system in the one-key starting method, including speed, oil pressure, water temperature, oil temperature, etc., and the starting conditions are judged, including preheating temperature, throttle position, etc. If abnormal conditions are found, including fault alarm, insufficient preheating time, etc., the flight control system will stop the starting program and issue a warning, avoiding the engine starting in an abnormal state, improving the starting safety and protecting the safety of personnel and equipment. The one-key starting method can avoid excessive impact on the engine during cold start by accurately controlling the engine starting process, including preheating time, throttle control, etc., thereby prolonging the service life of the engine. In addition, real-time monitoring of engine state parameters and timely adjustment can avoid engine overheating or poor lubrication, further prolonging the engine life and reducing maintenance costs.

[0041] 3、In the present application, the starting process is simplified, the take-off preparation time is shortened, the usability of the unmanned aerial vehicle is improved, the unmanned aerial vehicle can execute tasks faster, and the task delay or cancellation caused by starting problems is reduced. This improves the task execution efficiency of the unmanned aerial vehicle, making it better meet the needs of various application scenarios. The one-key starting method of the piston engine unmanned aerial vehicle realizes the simplification of the starting process, the improvement of safety, the prolongation of the engine life and the improvement of the usability of the unmanned aerial vehicle through automation, intelligence and precise control, which brings great impetus to the development and application of unmanned aerial vehicles. BRIEF DESCRIPTION OF DRAWINGS

[0042] Figure 1 The method flowchart of the present application. DETAILED DESCRIPTION

[0043] In order to make the purpose, technical scheme and advantages of the present application more clear, the present application is further described in detail below in combination with the drawings and examples. It should be understood that the specific examples described herein are only used to explain the present application and do not limit the present application.

[0044] Reference Figure 1 ,

[0045] A one-key starting method of a piston engine unmanned aerial vehicle, the method comprising the following steps:

[0046] S1: receiving the engine one-key starting instruction sent by the ground station.

[0047] S2: sending the instruction to turn on the on-board fuel cut-off valve.

[0048] S3: after a period of time (not more than 1 second), sending the instruction to turn on the on-board fuel pump.

[0049] S4: after a period of time (depending on the time for the fuel tank to supply fuel to the engine fuel inlet and reach the predetermined pressure), sending the power system enable signal.

[0050] S5: Monitor if the engine start conditions are met, including:

[0051] Whether the engine throttle control is in the idle state;

[0052] Whether the engine inlet fuel pressure is within a predetermined range;

[0053] Whether the engine oil temperature, gearbox oil temperature, engine coolant temperature, and engine fuel temperature are higher than the start threshold;

[0054] Whether there is an engine and propeller fault alarm.

[0055] If any condition is not met, end the one-key start procedure and send a failure reason prompt message to the ground station.

[0056] S6: Monitor the preheating state; if the preheating is not working, proceed to the next step; if the preheating is working, monitor whether there is a preheating fault alarm; if there is a preheating fault alarm, end the one-key start procedure and send a failure reason prompt message to the ground station; if there is no preheating fault alarm, execute this cycle.

[0057] S7: Send brake command; after a period of time (depending on the time from when the aircraft sends the brake command to the actuator executes the command to when the predetermined brake pressure is reached), check whether the brake pressure reaches the predetermined value.

[0058] S8: Send engine start command.

[0059] S9: Monitor whether the oil pressure is established within a predetermined time; monitor whether the speed exceeds the starter disengagement speed or approaches the limited use time, send the starter disengagement command if either condition is met, whichever comes first; monitor whether the speed reaches the idle speed within a predetermined time and stabilizes within the allowed range; monitor whether the oil pressure at idle is within a predetermined range.

[0060] If all the above monitoring conditions are met, after a period of time, send the warm-up command, i.e., increase the throttle to a predetermined control amount; monitor whether the engine oil temperature, gearbox oil temperature, and engine coolant temperature are higher than the working threshold.

[0061] S10: If all three conditions are met, the one-key start is completed, and a start success prompt message is sent to the ground station, after which the one-key start procedure of the entire piston engine UAV is completed.

[0062] In step S1, the instruction is sent through a remote control or ground control station and contains a signal to start the engine. After receiving the instruction, the flight control system starts the one-key start program and executes the subsequent steps. The instruction can be sent using a wireless communication protocol, such as 433MHz or 2.4GHz frequency band, with data encryption function to ensure the safety and reliability of the instruction. The instruction data packet contains start instruction, security code and other information. After receiving the instruction, the flight control system verifies the security code and confirms the validity of the instruction.

[0063] In step S2, the instruction is sent to turn on the on-board fuel cut-off valve, and after a certain interval (not more than 1 second), the instruction is sent to turn on the on-board fuel pump. The fuel cut-off valve is located in the fuel pipeline and is used to control the flow of fuel to the engine. After turning on the fuel cut-off valve, 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 cut-off valve is fully opened before starting the fuel pump to avoid backflow of fuel. The start of the fuel pump can use an electric pump or a mechanical pump, and is equipped with a pressure sensor to monitor the fuel pressure in real time, ensuring stable fuel supply. The power of the electric pump is several hundred watts, and the mechanical pump is driven by the engine speed. The fuel pressure sensor monitors the pressure range of 0-6bar with an accuracy of 0.1bar.

[0064] 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 turning on the fuel cut-off valve, 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 cut-off valve is fully opened before starting the fuel pump to avoid backflow of fuel. The start of the fuel pump can use an electric pump or a mechanical pump, and is equipped with a pressure sensor to monitor the fuel pressure in real time, ensuring stable fuel supply. The power of the electric pump is several hundred watts, and the mechanical pump is driven by the engine speed. The fuel pressure sensor monitors the pressure range of 0-6bar with an accuracy of 0.1bar.

[0065] In step S4, the signal activates the engine control unit (ECU) and other related systems to prepare for engine start. The interval time depends on the design of the fuel system, ensuring that the fuel pressure is stable before starting the engine. The ECU is responsible for controlling the ignition, fuel injection, intake process of the engine, and monitoring the engine state in real time to ensure the safe operation of the engine. The control strategy of the ECU can be adjusted according to the type and operating state of the engine, such as idle control, throttle control, fault diagnosis, etc.

[0066] In step S5, the throttle controls the speed of the engine, and the speed in the slow vehicle state is 600-800rpm;

[0067] The predetermined range of fuel pressure is 2-3bar with an accuracy of 0.1bar;

[0068] Start threshold: 20-30°C, precision: 1°C

[0069] In step S6, the preheating system is used to heat the engine to reach the start temperature. The preheating time depends on the ambient temperature and the engine type, which takes tens of seconds to tens of minutes. The preheating temperature and preheating time need to be monitored during the preheating process to ensure the normal operation of the preheating system. The monitoring range of the preheating temperature is 20-60°C, and the precision is 1°C.

[0070] In step S7, the interval time depends on the time from the aircraft sending the brake command to the actuator executing the command to reaching the predetermined brake pressure.

[0071] In step S8, the engine speed, oil pressure, water temperature and other parameters need to be monitored during the start process to ensure the normal start of the engine.

[0072] The speed is monitored to see if it exceeds the starter disengagement speed or approaches the limit use time. If either condition is met, the starter disengagement command is sent, whichever comes first.

[0073] Starter disengagement speed: refers to the engine speed at which the starter no longer provides power, and the engine continues to run on its own power. This speed depends on the engine type and start state.

[0074] Limit use time: refers to the continuous working time of the starter to avoid overheating and damage. This time depends on the type and power of the starter, for example, a larger power starter can be used for a longer time. For example, the starter limit use time may be 15-20 seconds.

[0075] Speed monitoring: real-time monitoring of engine speed to ensure it reaches the starter disengagement speed or approaches the limit use time.

[0076] Starter disengagement command: when the engine speed reaches the starter disengagement speed or approaches the limit use time, the flight control system sends a command to disconnect the starter circuit, and the starter stops working.

[0077] In step S9, the idle speed monitoring needs to ensure that the engine speed is stable within the predetermined range and meets a certain cumulative time. The idle down oil pressure monitoring needs to ensure that the engine lubrication system is working properly. The starter disengagement speed is higher than 500 rpm, and the cumulative time is 5-10 seconds. The monitoring range of the idle speed is 600-800 rpm, the cumulative time is 30-60 seconds, and the swing tolerance is 10-20 rpm. The monitoring range of the idle down oil pressure is 1-2 bar, and the precision is 0.1 bar.

[0078] In the present application, the operation is simplified and the efficiency is improved: the traditional starting process needs the pilot to operate multiple steps, which is time-consuming, laborious and prone to error. The one-key starting method integrates the starting process into one button operation, and the flight control system automatically completes the fuel supply, preheating, ignition and other steps, greatly simplifying the operation process, shortening the take-off preparation time and improving the starting efficiency, so that the UAV can be put into task execution faster.

[0079] In the present application, the operation difficulty and human error are reduced: the UAV pilot may lack experience in operating aviation engines, and is prone to operation errors during the starting process, such as improper throttle control, insufficient preheating time, etc., which may cause engine starting failure or damage. The one-key starting method automates the starting process, avoids human errors, improves the starting success rate, reduces the risk of engine failure, and improves the reliability of the UAV.

[0080] In the present application, real-time monitoring and safety guarantee are realized: in the one-key starting method, the flight control system monitors the engine state parameters in real time, such as speed, oil pressure, water temperature, oil temperature, etc., and judges whether the starting conditions are met, such as preheating temperature, throttle position, etc. If abnormal conditions are found, such as fault alarm, insufficient preheating time, etc., the flight control system will stop the starting program and issue a warning, avoiding the engine starting in an abnormal state, improving the starting safety, and ensuring the safety of personnel and equipment.

[0081] In the present application, the engine life is extended: the one-key starting method precisely controls the engine starting process, such as preheating time, throttle control, etc., which can avoid excessive impact on the engine during cold start, thereby extending the service life of the engine. In addition, real-time monitoring of engine state parameters and timely adjustment can avoid problems such as engine overheating or poor lubrication, further extending the service life of the engine and reducing maintenance costs.

[0082] In the present application, the usability of the UAV is improved: the one-key starting method simplifies the starting process, shortens the take-off preparation time, and improves the usability of the UAV, so that it can execute tasks faster and reduce task delays or cancellations due to starting problems. This improves the task execution efficiency of the UAV and better meets the needs of various application scenarios.

[0083] In summary, the one-key starting method of the piston engine UAV realizes the simplification of the starting process, the improvement of safety, the extension of the engine life and the improvement of the usability of the UAV through automation, intelligentization and precise control, which brings great impetus to the development and application of UAVs.

[0084] It is to be noted that, in the present text, relational terms such as first and second and the like can be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises", "comprising", "has", "having", "includes", "including", or any other variation thereof are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can include other elements not expressly listed or even inherent to such process, method, article, or apparatus. An element proceeded by "comprises... a", "has... a", "includes... a", or "has... a" does not, without more constraints, preclude the existence of additional identical elements in the process, method, article, or apparatus that comprises the element.

[0085] The above examples are merely intended to illustrate the technical solutions of the present application, but not to limit it; even though the present application has been described in detail with reference to the foregoing examples, those of ordinary skill in the art should understand that they can still make modifications to the technical solutions recorded in the foregoing examples, or make equivalent replacements to some of the technical features; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. A one-button start method for a piston engine drone, characterized by: The method comprises the following steps: S1: Receive the engine one-key start command sent by the ground station; S2: Send a command to turn on the fuel shut-off valve on the aircraft; S3: After a certain period of time, send a command to turn on the onboard fuel pump, the interval time shall not exceed 1 second; S4: After a certain interval, a power system enable signal is sent. The interval time depends on the time it takes for the fuel in the fuel tank to be supplied to the engine fuel inlet and reach a predetermined pressure. S5: Monitor whether engine start conditions are met, including: whether the engine throttle control is in the idle state; whether the engine inlet fuel pressure is within a predetermined range; whether the engine oil temperature, gearbox oil temperature, engine coolant temperature, and engine fuel temperature are above the start threshold; and whether there are engine and propeller fault alarms. If any of the conditions are not met, the one-key start program will be terminated and a failure reason prompt message will be 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 certain interval, check whether the brake pressure reaches the predetermined value. The interval time 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; 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 limit time; if either condition 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 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; S10: If all three conditions are met, the one-key start is completed, and a startup success prompt message is sent to the ground station, after which the one-key start process of the entire piston engine drone is completed.

2. The one-button start method for a piston engine drone according to claim 1, characterized in that: In step S1, a command is sent via a remote control or a ground control station and includes a signal to start the engine. Upon receiving the command, the flight control system initiates a one-button start procedure and executes subsequent steps. The command is sent using a wireless communication protocol and has a data encryption function to ensure the security and reliability of the command. The command data packet includes a start command and a security code. Upon receiving the command, the flight control system verifies the security code and confirms the validity of the command.

3. The one-button start method for a piston engine drone according to claim 1, characterized in that: In steps S2 and S3, 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 line and is used to control the flow of fuel to the engine. After the fuel shut-off valve is turned on, 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 shut-off valve is fully opened before the fuel pump is started to prevent 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 fuel pressure sensor monitors a pressure range of 0-6 bar with an accuracy of 0.1 bar.

4. The one-button start method for a piston engine drone according to claim 1, characterized in that: In step S4, the interval time depends on the design of the fuel system to ensure that the engine can only be started after the fuel pressure is stable; the ECU is responsible for controlling the engine's ignition, fuel injection, and 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.

5. The one-button start 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 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°C with an accuracy of 1°C.

6. The one-button start 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 its starting temperature; the preheating time depends on the ambient temperature and the engine type; the preheating temperature and preheating time need to be monitored during the preheating process to ensure the normal operation of the preheating system; the monitoring range of the preheating temperature is 20-60°C, with an accuracy of 1°C.

7. The one-button start method for a piston engine drone according to claim 1, characterized in that: In step S9, the engine speed, oil pressure, and water temperature parameters need to be monitored during the startup process to ensure that the engine starts normally; 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; Limit usage time: avoid overheating and damage to the starter; Speed ​​monitoring: Real-time monitoring of engine speed 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.

8. The one-button start 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 operates normally; 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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