Hybrid power control method, hybrid power controller and aircraft

Abstract

The invention provides a hybrid power control method, a hybrid power controller and an aircraft, and the method comprises the steps: obtaining the state information of each controller in the aircraft, and determining whether each controller and a system bus are normal or not according to the state information; when all the controllers and the system bus are in the normal state and the starting instruction sent by the flight control unit is received, the starting instruction is executed; receiving a power demand signal sent by the flight control unit, and dynamically controlling an engine throttle valve of the aircraft and the rotating speed of a generator according to the power demand signal; and the real-time state information of the generator and the real-time state information of the engine are collected, and under the condition that the real-time state information of the generator or the real-time state information of the engine is abnormal, target abnormity processing operation is executed. In this way, accurate control over the power can be achieved, real-time detection and rapid processing of abnormal faults can be achieved, and the safety and stability of the aircraft can be ensured.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft, and particularly to a hybrid power control method, a hybrid power controller, and an aircraft. Background Art

[0002] The power systems of traditional aircraft are mainly pure battery-driven or fuel-driven. Although pure battery-driven is environmentally friendly and has flexible control, the endurance time is limited, making it difficult to meet the requirements of long-duration tasks such as inspection and logistics. The fuel-driven system has a high energy density but unstable power output, and the engine is heavy and has complex control, affecting flight safety and operability.

[0003] In related technologies, the use of a hybrid system in an aircraft can improve endurance and efficiency, and has higher environmental adaptability. However, the hybrid system is not precise enough in power control, and due to the interaction of multiple systems, there are certain defects in fault detection and handling, resulting in low stability and safety of the aircraft. Summary of the Invention

[0004] The present application provides a hybrid power control method, a hybrid power controller, and an aircraft, which can achieve precise and dynamic power control and comprehensive and real-time fault detection and handling, improving the stability and safety of the aircraft.

[0005] In a first aspect, an embodiment of the present application provides a hybrid power control method, which is applied to a hybrid power controller and includes:

[0006] Obtain the status information of each controller in the aircraft, and determine whether each controller and the system bus are normal according to the status information;

[0007] When each controller and the system bus are in a normal state and a start instruction sent by the flight control unit is received, execute the start instruction;

[0008] Receive the power demand signal sent by the flight control unit, and dynamically control the engine throttle and generator speed of the aircraft according to the power demand signal;

[0009] Collect the real-time status information of the generator and the real-time status information of the engine, and execute a target abnormal handling operation when there is an abnormality in the real-time status information of the generator or the real-time status information of the engine.

[0010] In a possible implementation manner, the obtaining the status information of each controller in the aircraft and determining whether each controller and the system bus are normal according to the status information includes:

[0011] Collect the status information of each controller in the aircraft through the system bus; the status information includes the connection status of each controller and the communication messages of each controller.

[0012] When the connection status of each controller in the aircraft is in the online state, determine that the system bus of the aircraft is normal.

[0013] When there is no fault code in the communication messages of each controller, determine that each controller in the aircraft is operating normally.

[0014] In a possible implementation manner, the dynamically controlling the engine throttle and the generator speed of the aircraft according to the power demand signal includes:

[0015] Generate an engine throttle opening control signal and a generator speed control signal according to the power demand signal.

[0016] Send the engine throttle opening control signal to the engine controller through the system bus, and send the generator speed control signal to the generator controller through the system bus.

[0017] In a possible implementation manner, the real-time status information of the generator includes at least one of generator speed, generator temperature, generator bus voltage, generator bus current, power generation power, and high-voltage status signal;

[0018] The real-time status information of the engine includes at least one of engine speed, cylinder head temperature, lubricating oil temperature, throttle position, lubricating oil pressure, fuel pressure, fuel quantity information, and ignition status.

[0019] In a possible implementation manner, the method further includes:

[0020] Output a low-open signal or a high-open signal according to the control instruction sent by the flight control unit, the real-time status information of the generator, and / or the real-time status information of the engine;

[0021] Wherein, the low-open signal is used to control the opening and closing of at least one of the generator cooling water pump, the generator cooling fan, the engine fuel pump, and the engine speed increaser lubricating pump; the high-open signal is used to wake up the generator controller or to control the opening and closing of the engine fuel cut-off valve.

[0022] In a possible implementation manner, the performing a target abnormal handling operation when there is an abnormality in the real-time status information of the generator or the real-time status information of the engine includes:

[0023] During the startup process of the aircraft, if there is an abnormality in the real-time status information of the generator or the real-time status information of the engine, an alarm signal is output, the startup of the aircraft is terminated, and the abnormality information is sent to the flight control unit;

[0024] During the operation of the aircraft, if the actual speed does not match the speed control command, or the actual torque does not match the torque control command, or there is real-time status information exceeding the preset threshold, an alarm signal is output.

[0025] In a second aspect, an embodiment of the present application provides a hybrid power controller, which includes a main control unit, a sampling unit, a communication interface unit, and a switch control unit, where,

[0026] The main control unit is configured to obtain the status information of each controller in the aircraft through the communication interface unit, and determine whether each controller and the system bus are normal according to the status information;

[0027] The main control unit is configured to execute the startup command when each controller and the system bus are in a normal state and a startup command sent by the flight control unit is received;

[0028] The main control unit is further configured to receive a power demand signal sent by the flight control unit through the communication interface unit, and dynamically control the engine throttle valve and the generator speed of the aircraft through the communication interface unit according to the power demand signal;

[0029] The main control unit is further configured to receive the real-time status information of the generator and the real-time status information of the engine collected by the sampling unit and the communication interface unit, and perform a target abnormality handling operation when there is an abnormality in the real-time status information of the generator or the real-time status information of the engine.

[0030] In a third aspect, an embodiment of the present application provides a hybrid power control device, including: a processor and a memory;

[0031] The memory stores computer execution instructions;

[0032] The processor executes the computer execution instructions stored in the memory to implement the hybrid power control method according to any one of the first aspects.

[0033] In a fourth aspect, an embodiment of the present application provides a computer-readable storage medium, in which computer execution instructions are stored, and when the computer execution instructions are executed, they are used to implement the hybrid power control method according to any one of the first aspects.

[0034] In a fifth aspect, an embodiment of the present application provides a computer program product, including a computer program which, when executed, implements the hybrid power control method according to any one of the first aspect.

[0035] In a sixth aspect, an embodiment of the present application provides a chip, on which a computer program is stored, and when the computer program is executed by the chip, it implements the hybrid power control method according to any one of the first aspect.

[0036] In a seventh aspect, an embodiment of the present application provides an aircraft, which includes the hybrid power controller according to any one of the second aspect.

[0037] The hybrid power control method, hybrid power controller and aircraft provided by the embodiments of the present application obtain the status information of each controller in the aircraft, and determine whether each controller and the system bus are normal according to the status information; when each controller and the system bus are in a normal state and a start instruction sent by the flight control unit is received, execute the start instruction; receive the power demand signal sent by the flight control unit, and dynamically control the engine throttle and generator speed of the aircraft according to the power demand signal; collect the real-time status information of the generator and the real-time status information of the engine, and when there is an abnormality in the real-time status information of the generator or the real-time status information of the engine, execute the target abnormality handling operation. In the present application, the hybrid power controller determines whether each controller and the system bus are normal through the status information of each controller, which can ensure that each component of the aircraft works in a normal state; after starting, according to the power demand signal issued by the flight control unit, dynamically control the engine throttle and generator speed to ensure accurate dynamic control of power; at the same time, by collecting the real-time status information of the generator and the engine, when there is an abnormality in the real-time status information, execute the corresponding target abnormality handling operation, which can realize real-time detection and rapid processing of abnormal faults, so as to ensure the safety and stability of the aircraft. Description of the Drawings

[0038] The drawings here are incorporated into the description and form a part of this description, showing the embodiments in line with the present application, and are used together with the description to explain the principles of the present application.

[0039] Figure 1 It is a schematic flowchart of a hybrid power control method provided by an embodiment of the present application;

[0040] Figure 2 It is a system architecture diagram of a hybrid power controller provided by an embodiment of the present application;

[0041] Figure 3 It is a schematic flowchart of another hybrid power control method provided by an embodiment of the present application;

[0042] Figure 4 A communication interaction schematic diagram of a hybrid power controller provided by an embodiment of the present application;

[0043] Figure 5 A data interaction schematic diagram between a main control unit and other controllers provided by an embodiment of the present application;

[0044] Figure 6 A structural schematic diagram of a hybrid power control device provided by an embodiment of the present application.

[0045] Through the above-mentioned drawings, specific embodiments of the present application have been shown, and more detailed descriptions will be provided later. These drawings and text descriptions are not intended to limit the scope of the concept of the present application in any way, but to illustrate the concept of the present application to those skilled in the art by referring to specific embodiments. Detailed implementation manners

[0046] To enable those skilled in the art to better understand the technical solutions of the present application, the present application will be further described in detail below with reference to the drawings and embodiments. It should be understood that the specific embodiments and drawings described herein are only used to explain the present application, rather than to limit the present application. It should be noted that the user information (including but not limited to user device information, user personal information, etc.) and data (including but not limited to data for analysis, stored data, displayed data, etc.) involved in the present application are all information and data authorized by the user or fully authorized by all parties, and the collection, use, and processing of relevant data need to comply with relevant laws, regulations, and standards, and corresponding operation entrances are provided for users to select authorization or rejection.

[0047] With the continuous development of manufacturing technology, the types and quantities of aircraft have been increasing, such as electric vertical take-off and landing (eVTOL) drones. In terms of power control, traditional power systems are mainly pure battery-driven and fuel-driven. Although pure battery-driven is environmentally friendly and has flexible control, its endurance time is limited and it is difficult to meet the requirements of long-term tasks such as inspection and logistics. The fuel-driven system has a high energy density but unstable power output, and the engine is heavy and the control is complex, which affects flight safety and operability.

[0048] In the related art, aircraft use hybrid systems to improve endurance and efficiency, and the hybrid systems have higher environmental adaptability. The hybrid system adopts a redundant power architecture, where the engine and the battery are backup to each other, ensuring that a single-point failure does not affect flight safety and, to a certain extent, can also improve the reliability of the overall aircraft system. However, since the hybrid system involves multiple systems such as fuel power and battery power, the overall power control of the aircraft is not precise enough. And due to the interaction of multiple systems, there are certain defects in the fault detection and handling of the aircraft, resulting in low stability and safety of the aircraft operation.

[0049] To solve the above technical problems, the present application provides a hybrid power control method, a hybrid power controller, and an aircraft. In the hybrid system of the aircraft, the Hybrid Control Unit (HCU) mainly involves the integrated optimization of the power system, energy management, and flight control. The hybrid power controller provided by the present application obtains the status information of each controller in the aircraft and determines whether each controller and the system bus are normal according to the status information; when each controller and the system bus are in a normal state and a start instruction sent by the flight control unit is received, the start instruction is executed; the power demand signal sent by the flight control unit is received, and the engine throttle and the generator speed of the aircraft are dynamically controlled according to the power demand signal; the real-time status information of the generator and the real-time status information of the engine are collected, and when there is an abnormality in the real-time status information of the generator or the real-time status information of the engine, a target abnormality handling operation is executed. In the present application, the hybrid power controller determines whether each controller and the system bus are normal through the status information of each controller, which can ensure that each component of the aircraft works in a normal state; after starting, according to the power demand signal sent by the flight control unit, the engine throttle and the generator speed are dynamically controlled to ensure precise dynamic control of power; at the same time, by collecting the real-time status information of the generator and the engine, when there is an abnormality in the real-time status information, the corresponding target abnormality handling operation is executed, which can realize real-time detection and rapid handling of abnormal faults, thus ensuring the safety and stability of the aircraft.

[0050] The following details the solutions shown in the present application through specific embodiments. It should be noted that the following several embodiments can exist independently or be combined with each other, and the same or similar content will not be repeated in different embodiments.

[0051] Figure 1 It is a schematic flowchart of a hybrid power control method provided by an embodiment of the present application. Please refer to Figure 1 and the hybrid power control method may include:

[0052] S101. Obtain the status information of each controller in the aircraft, and determine whether each controller and the system bus are normal according to the status information.

[0053] The execution subject of the embodiment of this application can be a hybrid power controller or a hybrid power control device arranged in the aircraft. The hybrid power control device can be realized by the combination of software and hardware. For the convenience of understanding, in the following, the execution subject is taken as an example of the hybrid power controller HCU for description.

[0054] Figure 2 It is a system architecture diagram of a hybrid power controller provided by an embodiment of this application. As Figure 2 shown, the hybrid power controller 20 can include a low-voltage power supply unit 21, a main control unit 22, a sampling unit 23, a switch control unit 24, and a communication interface unit 25. Among them, the low-voltage power supply unit 21 can be used to convert the input power supply (such as an input voltage of 18 to 36 volts, etc.) into various power supplies used for the low-voltage part on the HCU board to supply power to each functional module. The main control unit 22 can include a memory (such as a flash memory, a ferroelectric random access memory (FRAM), etc.), a processor, and peripheral circuits (such as a boot circuit and a reset circuit, etc.), and can be used to receive signals transmitted by other functional modules to implement functions such as data calculation, interface communication, algorithm processing, logic control, health management, and fault storage. The sampling unit 23 can be used for data sampling, specifically sampling analog quantities such as fuel quantity information, and after analog-to-digital conversion, transmitting digital signals to the main control unit 22. The switch control unit 24 can implement switch control of the generator and engine-related equipment according to the control command of the main control unit 22. The communication interface unit 25 is connected to the system bus to realize communication interaction between the main control unit and other units.

[0055] In the embodiments of the present application, each controller may refer to the controller of other subsystems in the aircraft, such as a Flight Control Computer (FCC), a Generator Control Unit (GCU), an Engine Control Unit (ECU), a Battery Management System (BMS) controller, etc. The status information may refer to specific information such as the connection status and operation status of each control. The system bus may refer to the communication bus of the entire aircraft, specifically, it may refer to a Controller Area Network (CAN) bus or an RS422 bus, etc. Of course, it may also be other types of system buses, and the embodiments of the present application do not limit this.

[0056] In this step, the Hybrid Control Unit (HCU) has a self-check function, that is, the HCU can obtain the status information of each controller in the aircraft through the system bus. For example, it can obtain the connection status of each controller, etc., and then determine whether each controller and the system bus are normal according to the status information. This self-check process can be performed before the aircraft starts. Of course, periodic self-checks can also be performed during startup and normal operation. The embodiments of the present application do not limit this. In the embodiments of the present application, by self-checking the aircraft, the HCU can ensure that each component of the aircraft works in a normal state and ensure the stability of the aircraft operation.

[0057] S102: When each controller and the system bus are in a normal state and a start command sent by the flight control unit is received, execute the start command.

[0058] In the embodiments of the present application, the flight control unit may also be referred to as a flight control computer, a main control computer (flight control computer or test fixture), etc., and can be used to control the flight of the aircraft. The start command may refer to the command issued by the flight control unit to control the aircraft to take off. During the self-check process, when the HCU detects that each controller and the system bus are in a normal state, if a start command sent by the flight control unit is received, the HCU can execute the start command and perform the start process.

[0059] S103: Receive the power demand signal sent by the flight control unit, and dynamically control the engine throttle and generator speed of the aircraft according to the power demand signal.

[0060] In the embodiments of the present application, the power demand signal may refer to the power demand instruction issued during the flight control process of the flight control unit. The engine throttle is a component that controls the intake air volume of the engine. The HCU adjusts the opening and closing degree of the engine throttle, thereby adjusting the air volume entering the engine, achieving the control of the combustion efficiency, and ensuring the precise control of the power output and the power output. The generator speed may refer to the rotational speed of the generator in the aircraft. By adjusting the generator speed, the HCU can ensure the accuracy of power control.

[0061] In this step, after receiving the power demand signal issued by the flight control unit, the HCU can calculate the corresponding engine throttle opening and generator speed according to the power demand signal, and then can dynamically control the engine throttle and the generator speed through control instructions to ensure that the power demand of the flight control unit is met, and the power control is more precise and more in line with the requirements of the actual usage scenario.

[0062] S104. Collect the real-time status information of the generator and the real-time status information of the engine, and perform a target abnormal handling operation when there is an abnormality in the real-time status information of the generator or the real-time status information of the engine.

[0063] In the embodiments of the present application, the real-time status information of the generator may refer to the real-time operating status information of the generator, which may specifically include the rotational speed, temperature, bus voltage, bus current, power generation power, and high-voltage status signal of the generator, etc. The real-time status information of the engine may refer to the real-time operating status information of the engine, which may specifically include the rotational speed, cylinder head temperature, lubricating oil temperature, throttle position, lubricating oil pressure, fuel pressure, fuel quantity information, and ignition status of the engine, etc. Of course, the real-time status information of the generator and the real-time status information of the engine may also include other more information, which may be specifically configured based on actual needs, and the embodiments of the present application do not limit this. The target abnormal handling operation may refer to the fault handling operation performed by the HCU for abnormal situations, which may specifically include outputting an alarm message, stopping takeoff, and stopping operation, etc. The embodiments of the present application also do not limit the specific type of the target abnormal handling operation.

[0064] In this step, the operation of the aircraft includes the starting (takeoff) stage and the flight stage. During the operation of the aircraft, the HCU can collect the real-time status information of the generator and the real-time status information of the engine in real time through the sampling unit and the communication interface unit. The main control unit makes real-time abnormal judgments on the real-time status information of the generator and the real-time status information of the engine. When it is determined that there is an abnormality in the real-time status information of the generator or the real-time status information of the engine, the HCU can perform the target abnormal handling operation, and specifically can perform the corresponding target abnormal handling operation according to different abnormal situations. In this way, the HCU can realize the real-time abnormal detection of the engine and the generator, and dispose of the abnormal situation in a timely manner, which can ensure the stability and safety of the aircraft operation.

[0065] The hybrid control method provided by the embodiment of the present application, the hybrid controller obtains the status information of each controller in the aircraft, and determines whether each controller and the system bus are normal according to the status information; when each controller and the system bus are in a normal state and a start instruction sent by the flight control unit is received, execute the start instruction; receive the power demand signal sent by the flight control unit, and dynamically control the engine throttle valve and the generator speed of the aircraft according to the power demand signal; collect the real-time status information of the generator and the real-time status information of the engine, and when there is an abnormality in the real-time status information of the generator or the real-time status information of the engine, perform the target abnormal handling operation. In this application, the hybrid controller determines whether each controller and the system bus are normal through the status information of each controller, which can ensure that each component of the aircraft works in a normal state; after starting, according to the power demand signal sent by the flight control unit, dynamically control the engine throttle valve and the generator speed to ensure accurate dynamic control of power; at the same time, by collecting the real-time status information of the generator and the engine, when there is an abnormality in the real-time status information, perform the corresponding target abnormal handling operation, which can realize the real-time detection and rapid processing of abnormal faults, so as to ensure the safety and stability of the aircraft.

[0066] Based on the above embodiments, Figure 3 is a schematic flowchart of another hybrid control method provided by the embodiment of the present application. Please refer to Figure 3 and this hybrid control method may include:

[0067] S301. Collect the status information of each controller in the aircraft through the system bus; the status information includes the connection status of each controller and the communication message of each controller.

[0068] S302. When the connection status of each controller in the aircraft is in the online state, it is determined that the system bus of the aircraft is normal; when there is no fault code in the communication messages of each controller, it is determined that each controller in the aircraft is operating normally.

[0069] In the embodiment of the present application, the connection status may refer to the communication connection status of each controller, specifically, it may refer to the online state of normal connection or the offline state of unable to connect, etc. The communication message may refer to the communication (test) message sent by each controller. During the self-check process of the HCU, the main control unit may obtain the status information of each controller in the aircraft through the communication interface unit based on the system bus. The status information may include the connection status of each controller and the communication messages of each controller. If the connection status of each controller in the aircraft is in the online state, the HCU may determine that the system bus communication is normal, and the HCU may communicate with each controller normally through the system bus. If there is no fault code in the communication messages of each controller in the aircraft, the HCU may determine that each controller in the aircraft is operating normally.

[0070] In the embodiment of the present application, the self-check of the HCU may include detecting the connection status and operating status of the controller, and may also include detecting whether the sensor exceeds the measurement range and whether the command sent by the actuator is normally feedback, etc. During the self-check process, the HCU may obtain the status information of each controller through the system bus, which may include the connection status of each controller and the communication messages of each controller. If each controller is in the online state, at this time the HCU may determine that the system bus is normal; if at least one controller is in the offline state, the HCU may determine whether there is a fault in the system bus by taking the minimum value of all controller offline values, etc. In addition, the HCU may determine whether each controller is operating normally according to the communication messages of each controller. If there is no fault code in the communication messages of each controller, the HCU may determine that each controller is operating normally and each component corresponding to each controller has no fault; if there is a fault code in the communication message of at least one controller, the HCU may determine that at least one controller is abnormal and may output an alarm signal.

[0071] In the embodiment of the present application, the HCU obtains the status information of each controller in the aircraft through the system bus and determines whether the system bus and each controller are operating normally according to the status information, so as to realize the self-check of each component of the aircraft, ensure that the engine, generator, battery, etc. are all in the normal state, and improve the stability and safety of the aircraft operation.

[0072] S303. When each controller and the system bus are in the normal state and a start command sent by the flight control unit is received, execute the start command.

[0073] In the embodiment of the present application, when each controller and the system bus are in a normal state, and the HCU receives a start command sent by the flight control unit, the HCU can execute the start command and perform corresponding start processes such as engine ignition.

[0074] S304. Receive the power demand signal sent by the flight control unit; generate an engine throttle opening control signal and a generator speed control signal according to the power demand signal.

[0075] S305. Send the engine throttle opening control signal to the engine controller through the system bus, and send the generator speed control signal to the generator controller through the system bus.

[0076] In the embodiment of the present application, during the operation of the aircraft, the HCU can receive the power demand signal sent by the flight control unit through the communication interface unit. The HCU converts the power demand of the flight control unit into the engine throttle opening and the generator speed according to the power demand signal, and then the HCU can generate an engine throttle opening control signal and a generator speed control signal. Specifically, the HCU can send the engine throttle opening control signal to the engine controller through the communication interface unit and based on the system bus, and send the generator speed control signal to the generator controller at the same time.

[0077] In the embodiment of the present application, the HCU converts the power demand signal of the flight control unit into the engine throttle opening and the generator speed, and realizes the control of the engine throttle opening based on the engine controller and the control of the generator speed based on the generator controller by generating control signals. In this way, by dynamically and precisely controlling the generator speed and the engine throttle opening, the HCU can achieve precise control of the power of the aircraft system, and ensure the stability and safety of the operation of the aircraft. System power control.

[0078] S306. Collect the real-time state information of the generator and the real-time state information of the engine.

[0079] In the embodiment of the present application, during the operation of the aircraft, the HCU can collect the real-time state information of the generator and the real-time state information of the engine through the sampling unit and the communication interface unit, and subsequent abnormal detection can be performed according to the real-time state information of the generator and the real-time state information of the engine.

[0080] In a possible implementation manner, the real-time state information of the generator includes at least one of the generator speed, generator temperature, generator bus voltage, generator bus current, power generation power, and high-voltage state signal; the real-time state information of the engine includes at least one of the engine speed, cylinder head temperature, lubricating oil temperature, throttle position, lubricating oil pressure, fuel pressure, fuel quantity information, and ignition state.

[0081] Exemplarily, Figure 4 FIG. is a schematic diagram of communication interaction of a hybrid power controller provided by an embodiment of the present application. As Figure 4 shown, the sampling unit 23 in the hybrid power controller 20 can acquire various analog quantity information, perform analog-to-digital conversion on the analog quantity information, generate digital information corresponding to the analog quantity information, and transmit the digital information to the main control unit 22. The main control unit 22 can also communicate with the flight control unit, engine controller, generator controller, battery management system, fuel quantity sensor, etc. through the communication interface unit 25 to realize data exchange between the HCU and each controller. The main control unit 22 can also control the opening and closing of the generator cooling water pump, engine fuel pump, etc. through the switch control unit.

[0082] Specifically, the real-time information of the generator collected by the HCU can include at least one of the generator speed, generator temperature, generator bus voltage, generator bus current, power generation power, and high-voltage state signal; the real-time information of the engine collected by the HCU can include at least one of the engine speed, cylinder head temperature, lubricating oil temperature, throttle position, lubricating oil pressure, fuel pressure, fuel quantity information, and ignition state. Of course, the real-time signals of the generator and the real-time information of the engine can also include other information, which can be specifically determined according to actual needs, and the embodiments of the present application do not limit this.

[0083] Exemplarily, Figure 5 FIG. is a schematic diagram of data interaction between the main control unit and other controllers provided by an embodiment of the present application. As Figure 5 shown, the main control unit is respectively communicatively connected to and performs data interaction with the flight control unit, generator controller, engine controller, and battery management system to realize high-reliability data transmission and real-time sharing between the hybrid power system and other systems, and ensure the safety and stability of the operation of the aircraft.

[0084] S307. Output a low-opening signal or a high-opening signal according to the control instruction sent by the flight control unit, the real-time state information of the generator, and / or the real-time state information of the engine.

[0085] In an embodiment of the present application, a low-open signal is used to control the opening and closing of at least one of a generator cooling water pump, a generator cooling fan, an engine fuel pump, and an engine speed increaser lubricating pump; a high-open signal is used to wake up a generator controller or to control the opening and closing of an engine fuel cut-off valve.

[0086] In an embodiment of the present application, the HCU can output a low-open signal or a high-open signal through a switch control unit according to at least one of a control instruction issued by a flight control unit, real-time generator status information, and real-time engine status information. Among them, the low-open signal can be used to control the opening and closing of at least one of a generator cooling water pump, a cooling fan, a fuel pump, and a speed increaser lubricating pump; the high-open signal can be used to wake up a generator controller or to control the opening and closing of an engine fuel cut-off valve. Exemplarily, when the temperature of the generator in the real-time generator status information collected by the HCU is greater than a first temperature threshold (such as 60 or 70 degrees Celsius, etc.), the HCU can output a low-open signal to turn on the generator cooling water pump; when the temperature of the generator is less than a second temperature threshold (such as less than 50 or 40 degrees Celsius, etc.), the HCU can output a low-open signal to turn off the generator cooling water pump.

[0087] In an embodiment of the present application, the HCU outputs a low-open signal or a high-open signal through a switch control unit according to at least one of a control instruction of the flight control unit, real-time generator status information, and engine status information, so as to implement corresponding switch control functions, which can further ensure the safety and stability of the flight vehicle operation.

[0088] S308. During the start-up process of the flight vehicle, if there is an abnormality in the real-time generator status information or the real-time engine status information, an alarm signal is output, the start-up of the flight vehicle is terminated, and an abnormal information is sent to the flight control unit.

[0089] In an embodiment of the present application, during the start-up process of the flight vehicle, if there is an abnormality in the real-time generator status information or the real-time engine status information collected by the HCU, such as abnormal generator speed, abnormal generator temperature, abnormal engine speed, or too low fuel quantity, etc., the HCU can output an alarm signal, specifically, the alarm signal can be output through means such as sound and light alarm, and at the same time, the start-up of the flight vehicle can be terminated to ensure the safety of the flight vehicle. In addition, the HCU can also send abnormal information to the flight control unit for subsequent abnormal handling.

[0090] S309. During the operation process of the flight vehicle, if the actual speed does not match the speed control instruction, or the actual torque does not match the torque control instruction, or there is real-time status information exceeding a preset threshold, an alarm signal is output.

[0091] In the embodiments of the present application, during the operation of the aircraft, if the rotational speed of the generator or the engine does not match the corresponding rotational speed control instruction, or the actual torque does not match the torque control instruction, or there is real-time status information exceeding a preset threshold, such as too high generator temperature, too high lubricating oil temperature, etc., the HCU can output an alarm signal to achieve real-time reminder under abnormal conditions.

[0092] In the embodiments of the present application, during the startup phase of the aircraft, when the HCU detects abnormalities in the real-time status information of the generator or the real-time status of the engine, it outputs an alarm signal, terminates the startup of the aircraft, and sends abnormal information to the flight control unit; during the operation of the aircraft, if there are abnormalities in the real-time status information of the generator or the real-time status of the engine, the HCU outputs an alarm signal. In this way, the HCU can perform corresponding target abnormal handling operations for abnormal faults, which can ensure the stability and safety of the aircraft operation.

[0093] It should be noted that after the HCU collects the real-time status information of the generator and the real-time status information of the engine, it can be displayed through the display module to achieve an intuitive display of the working status of the range extender power system. Correspondingly, in the event of an abnormality, the alarm signal can also be output through this display module.

[0094] In addition, during the operation of the HCU, if it receives a parking instruction sent by the flight control unit, it can control the rotational speed of the generator to zero, simultaneously reduce the throttle opening of the engine, and control the engine's ignition wire to ground to stop the engine.

[0095] The hybrid power controller provided in the embodiments of the present application can be applied to aircraft powered by engines, generators, and batteries, specifically referring to unmanned aircraft, etc. Based on the characteristics of the engine and the battery, the HCU can achieve reliable data transmission and real-time sharing between the hybrid power system and other systems such as the flight control system. Through the self-check process, it can ensure that the engine and the battery are working in a normal state, ensure that the operating state of the entire system meets the flight requirements, and at the same time, the HCU has high portability and scalability and can achieve data interaction with more systems; in addition, during the operation of the aircraft, it can collect the real-time status information of the generator and the real-time status information of the engine, and quickly perform corresponding target abnormal handling operations in the event of an abnormality, which can ensure the safety and reliability of the system.

[0096] Based on the above embodiments, the present application further provides a hybrid power controller, which includes a main control unit, a sampling unit, a communication interface unit, and a switch control unit. Among them,

[0097] The main control unit is used to obtain the status information of each controller in the aircraft through the communication interface unit, and determine whether each controller and the system bus are normal according to the status information;

[0098] The main control unit is configured to execute the start instruction when each controller and the system bus are in normal states and a start instruction sent by the flight control unit is received.

[0099] The main control unit is further configured to receive a power demand signal sent by the flight control unit through the communication interface unit, and dynamically control the engine throttle and the generator speed of the aircraft through the communication interface unit according to the power demand signal.

[0100] The main control unit is further configured to receive the real-time status information of the generator and the real-time status information of the engine collected by the sampling unit and the communication interface unit, and execute a target exception handling operation when there is an abnormality in the real-time status information of the generator or the real-time status information of the engine.

[0101] The hybrid power controller provided in the embodiment of the present application can execute the technical solutions shown in the above method embodiments, and its implementation principle and beneficial effects are similar, and will not be elaborated here.

[0102] Figure 6 It is a schematic structural diagram of a hybrid power control device provided in the embodiment of the present application. Please refer to Figure 6 , the hybrid power control device 60 may include: a memory 61 and a processor 62. Exemplarily, the memory 61 and the processor 62 are interconnected with each other through a bus 63.

[0103] The memory 61 is used to store program instructions;

[0104] The processor 62 is configured to execute the program instructions stored in the memory to implement the hybrid power control method shown in the above embodiments.

[0105] Figure 6 The hybrid power control device 60 shown can execute the technical solutions shown in the above method embodiments, and its implementation principle and beneficial effects are similar, and will not be elaborated here.

[0106] The embodiment of the present application provides a computer-readable storage medium, in which computer-executable instructions are stored, and when the computer-executable instructions are executed by a processor, they are used to implement the above hybrid power control method.

[0107] The embodiment of the present application may further provide a computer program product, including a computer program, and when the computer program is executed by a processor, the above hybrid power control method can be implemented.

[0108] The embodiment of the present application provides a chip, on which a computer program is stored, and when the computer program is executed by the chip, the above hybrid power control method is implemented.

[0109] An embodiment of the present application further provides an aircraft, and the aircraft includes the hybrid power controller of the above embodiment.

[0110] It should be noted that the processor mentioned in the embodiments of the present application may be a central processing unit (CPU), or may also be other general-purpose processors, digital signal processors (DSPs), application specific integrated circuits (ASICs), field programmable gate arrays (FPGAs) or other programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, etc. The general-purpose processor may be a microprocessor or the processor may also be any conventional processor, etc.

[0111] It should be understood that the memory mentioned in the embodiments of the present application may be a volatile memory or a non-volatile memory, or may include both volatile and non-volatile memories. Among them, the non-volatile memory may be a read-only memory (ROM), a programmable read-only memory (PROM), an erasable programmable read-only memory (EPROM), an electrically erasable programmable read-only memory (EEPROM), or a flash memory. The volatile memory may be a random access memory (RAM), which is used as an external cache. By way of example but not limitation, many forms of RAM are available, such as static random access memory (SRAM), dynamic random access memory (DRAM), synchronous dynamic random access memory (SDRAM), double data rate synchronous dynamic random access memory (DDR SDRAM), enhanced synchronous dynamic random access memory (ESDRAM), synch link dynamic random access memory (SLDRAM), and direct ram bus random access memory (DR RAM). It should be noted that when the processor is a general-purpose processor, DSP, ASIC, FPGA, or other programmable logic device, discrete gate or transistor logic device, discrete hardware component, the memory (storage module) is integrated in the processor. It should be noted that the memory described herein is intended to include but not be limited to these and any other suitable types of memory.

[0112] It should be understood that in various embodiments of the present application, the sequence numbers of the above processes do not mean the order of execution. The order of execution of each process should be determined by its function and internal logic, and should not constitute any limitation to the implementation process of the embodiments of the present application.

[0113] The embodiments of the present application are described with reference to the flowcharts and / or block diagrams of methods, devices (systems), and computer program products according to the embodiments of the present application. It should be understood that each process and / or block in the flowchart and / or block diagram, and the combination of processes and / or blocks in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to the processing unit of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing devices to generate a machine, so that the instructions executed by the processing unit of the computer or other programmable data processing devices generate for implementation in the processFigure 1 one process or multiple processes and / or blocks Figure 1 a device for the functions specified in one block or multiple blocks.

[0114] These computer program instructions can also be stored in a computer-readable memory that can direct a computer or other programmable data processing device to work in a specific manner, such that the instructions stored in the computer-readable memory produce a manufactured article including an instruction device that implements the functions in the process Figure 1 one process or multiple processes and / or blocks Figure 1 specified in one block or multiple blocks.

[0115] These computer program instructions can also be loaded onto a computer or other programmable data processing device, such that a series of operation steps are executed on the computer or other programmable device to produce a computer-implemented process, and thus the instructions executed on the computer or other programmable device provide steps for implementing the functions specified in the process Figure 1 one process or multiple processes and / or blocks Figure 1 specified in one block or multiple blocks.

[0116] Regarding each device and each module / unit included in the product described in the above embodiments, it can be a software module / unit, a hardware module / unit, or it can also be partly a software module / unit and partly a hardware module / unit. Each device and product can be applied to or integrated into a chip, a chip module, or a terminal device. Exemplarily, for each device and product applied to or integrated into a chip, each module / chip included therein can be implemented in a hardware manner such as a circuit, or at least part of the modules / units can be implemented in a software program manner, and the software program runs on a processor integrated inside the chip, and the remaining part of the modules / units can be implemented in a hardware manner such as a circuit.

[0117] In this application, the term "including" and its variations can refer to non-restrictive inclusion; the term "or" and its variations can refer to "and / or". In this application, terms such as "first" and "second" are used to distinguish similar objects and do not necessarily have to describe a specific order or sequence. In this application, "multiple" means two or more. "And / or" describes the association relationship of associated objects and indicates that there can be three relationships. For example, A and / or B can indicate: A exists alone, A and B exist simultaneously, and B exists alone. The character " / " generally indicates that the associated objects before and after are in an "or" relationship.

[0118] The above are only some embodiments of the present application. It should be noted that for those of ordinary skill in the art, without departing from the principle of the present application, several improvements and refinements can be made, and these improvements and refinements should also be regarded as the protection scope of the present application.

Claims

1. A hybrid control method, characterized in that, Applied to a hybrid controller, including: Obtain the status information of each controller in the aircraft, and determine whether each controller and the system bus are normal according to the status information; When each controller and the system bus are in a normal state and a start command sent by the flight control unit is received, execute the start command; Receive the power demand signal sent by the flight control unit, and dynamically control the engine throttle and generator speed of the aircraft according to the power demand signal; Collect the real-time status information of the generator and the real-time status information of the engine, and execute the target abnormal handling operation when there is an abnormality in the real-time status information of the generator or the real-time status information of the engine.

2. The method according to claim 1, wherein The obtaining the status information of each controller in the aircraft and determining whether each controller and the system bus are normal according to the status information includes: Collect the status information of each controller in the aircraft through the system bus; the status information includes the connection status of each controller and the communication message of each controller; When the connection status of each controller in the aircraft is in an online state, determine that the system bus of the aircraft is normal; When there is no fault code in the communication message of each controller, determine that each controller in the aircraft is operating normally.

3. The method according to claim 1, wherein The dynamically controlling the engine throttle and generator speed of the aircraft according to the power demand signal includes: Generate an engine throttle opening control signal and a generator speed control signal according to the power demand signal; Send the engine throttle opening control signal to the engine controller through the system bus, and send the generator speed control signal to the generator controller through the system bus.

4. The method according to claim 1, wherein The real-time status information of the generator includes at least one of generator speed, generator temperature, generator bus voltage, generator bus current, power generation power, and high-voltage status signal; The real-time status information of the engine includes at least one of engine speed, cylinder head temperature, lubricating oil temperature, throttle position, lubricating oil pressure, fuel pressure, fuel quantity information, and ignition status.

5. The method according to claim 1, wherein The method further includes: Output a low-open signal or a high-open signal according to the control command sent by the flight control unit, the real-time status information of the generator and / or the real-time status information of the engine; Among them, the low-open signal is used to control the opening and closing of at least one of the generator cooling water pump, generator cooling fan, engine fuel pump, and engine booster lubricating pump; the high-open signal is used to wake up the generator controller or to control the opening and closing of the engine fuel cut-off valve.

6. The method according to any one of claims 1 to 5, characterized in that, The executing the target abnormal handling operation when there is an abnormality in the real-time status information of the generator or the real-time status information of the engine includes: During the start-up process of the aircraft, if there is an abnormality in the real-time status information of the generator or the real-time status information of the engine, output an alarm signal and terminate the start-up of the aircraft, and send abnormal information to the flight control unit; During the operation of the aircraft, if the actual rotational speed does not match the rotational speed control command, or the actual torque does not match the torque control command, or there is real-time status information exceeding a preset threshold, an alarm signal is output.

7. A hybrid controller, characterized in that, The hybrid controller includes a main control unit, a sampling unit, a communication interface unit, and a switch control unit, where the main control unit is configured to obtain the status information of each controller in the aircraft through the communication interface unit, and determine whether each controller and the system bus are normal according to the status information; the main control unit is configured to execute the start command when each controller and the system bus are in a normal state and a start command sent by the flight control unit is received; the main control unit is further configured to receive the power demand signal sent by the flight control unit through the communication interface unit, and dynamically control the engine throttle and the generator rotational speed of the aircraft through the communication interface unit according to the power demand signal; the main control unit is further configured to receive the real-time status information of the generator and the real-time status information of the engine collected by the sampling unit and the communication interface unit, and perform a target abnormal handling operation when the real-time status information of the generator or the real-time status information of the engine is abnormal.

8. A hybrid control device, characterized in that, including: a processor, a memory; the memory stores computer execution instructions; the processor executes the computer execution instructions stored in the memory to implement the hybrid control method according to any one of claims 1 to 6.

9. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer execution instructions, which are used to implement the hybrid control method according to any one of claims 1 to 6 when the computer execution instructions are executed.

10. An aircraft, characterized in that, The aircraft includes the hybrid controller according to claim 7.

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