A control method and device for an aviation turbo-mix engine

Abstract

The application discloses a control method and device of an aviation turbine hybrid engine, realizes real-time identification and adaptive switching control of a power mode, and smooth transition of power output in a multi-mode switching process; a complete state monitoring and safety judgment closed loop is constructed, and the overall energy efficiency of a power system and the flight task matching capability are improved. Further, through optimization of a power mode switching strategy and a control algorithm, smooth switching of the aviation turbine hybrid engine power mode is realized, power interruption and fluctuation are avoided, and the stability and safety of flight are improved. Through closed loop design of a safety monitoring and emergency control mechanism, the system state is kept stable and controllable while an abnormality occurs, and complete data basis is provided for subsequent ground maintenance, remote diagnosis and flight safety evaluation.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aviation propulsion system control, in particular to a control method and device of an aviation turbo hybrid engine. BACKGROUND

[0002] The existing aviation turbo hybrid engine control technology still has many problems in actual application, which seriously restricts its performance and engineering application.

[0003] In terms of power mode and load switching, the traditional control algorithm has a lagging response in the engine operating condition conversion process, resulting in a power output interruption or fluctuation. This uneven switching not only affects the stability of flight, but also may pose a potential threat to flight safety, especially in the key stages of take-off, climb and acceleration. Low fuel efficiency is also a major shortcoming of current hybrid control systems. Due to the lack of accurate power distribution strategy, the cooperation between the turbine engine and the motor is not close enough, resulting in low efficiency of the hybrid system in some operating conditions, making it difficult to achieve the expected energy-saving effect, thereby causing waste of fuel resources. In addition, in terms of emission control, the existing algorithm usually fails to dynamically optimize and adjust the engine's emission characteristics under different operating conditions, resulting in incomplete combustion and large amount of pollutant emissions in some flight stages, making it difficult to meet the increasingly stringent environmental protection standards and carbon emission control requirements. Moreover, the existing control strategy has poor robustness in complex flight environments. In the face of highly dynamic changes in external conditions and system state fluctuations, the traditional control method is easily affected by disturbances, making it difficult to maintain stable control effect, resulting in system oscillation or performance degradation, thereby affecting the reliability and adaptability of the whole machine.

[0004] How to effectively improve the response speed and control accuracy of the aviation turbo hybrid engine under different operating conditions, realize smooth switching of power mode and load, improve fuel utilization efficiency, and reduce harmful emissions, and ensure efficient, stable and safe operation of the engine in complex flight environments, is a technical problem that needs to be solved in the field. SUMMARY

[0005] The present application provides a control method and device of an aviation turbo hybrid engine, which can realize real-time identification and adaptive switching control of power mode, as well as smooth switching of power mode and load, and improve the overall energy efficiency of the power system and the flight task matching ability.

[0006] The embodiment of the present application provides a control method of an aviation turbo hybrid engine, comprising:

[0007] identifying the power mode in which the engine currently locates according to the real-time collected key operating parameters of the engine, the power mode comprising a pure electric mode, a hybrid mode and a turbine independent mode;

[0008] determining that a preset power mode switching condition is met and generating a corresponding switching decision according to preset specific parameters corresponding to the current power mode;

[0009] controlling an actuator to adjust the output of the turbine engine and the motor according to the switching decision to realize the power mode switching;

[0010] real-time monitoring of the engine state, and if the switching fails, ending; if the switching succeeds, returning to the step of identifying the power mode in which the engine is currently located.

[0011] In an exemplary instance, if it is determined that the power mode switching condition is not met, the method further comprises: maintaining the current power mode and entering the step of real-time monitoring of the engine state.

[0012] In an exemplary instance, the method further comprises: after the power mode switching is completed and a stable running phase is entered, executing a power output optimization strategy; the power output optimization strategy is used to dynamically adjust the output power ratio of the turbine engine and the motor according to actual working conditions, so that the system always runs in an efficient area.

[0013] In an exemplary instance, the method further comprises: continuously performing the real-time monitoring of the engine running state, and when one or more key running parameters are detected to be abnormal, executing a preset safety protection mechanism to ensure the running safety and control stability of the system under complex working conditions.

[0014] In an exemplary instance, the determining that a preset power mode switching condition is met and generating a corresponding switching decision comprises:

[0015] analyzing whether the preset specific parameters corresponding to the current power mode exceed a set threshold;

[0016] when one or more key running parameters serving as the preset specific parameters exceed the threshold, determining whether the power mode switching condition is met, and generating the corresponding switching decision when the power mode switching condition is met.

[0017] In an exemplary instance, the controlling an actuator to adjust the output of the turbine engine and the motor according to the switching decision to realize the power mode switching comprises:

[0018] when it is determined that the power mode switching is needed, generating a set of ordered control instructions according to the relationship between the current mode and the target mode; and performing the power mode switching according to the generated ordered control instructions.

[0019] In an exemplary instance, the real-time monitoring of the engine state comprises:

[0020] Real-time monitoring is performed on the running state of the engine. If the monitoring result shows that the engine is abnormal, it is determined that the power mode switching in the current round fails, a protection mechanism is triggered, and abnormal information is stored, and the current process is ended. If the monitoring result shows that the engine is normal, it is determined that the power mode switching in the current round succeeds, the power mode state is updated, and the step of identifying the power mode in which the engine currently locates is returned to.

[0021] The embodiment of the application further provides a computer readable storage medium, which stores computer executable instructions, and the computer executable instructions are used for executing the control method of the aviation turbo hybrid engine.

[0022] The embodiment of the application further provides a computer device, which comprises a memory and a processor, wherein the memory stores instructions executable by the processor, and the instructions are used for executing the steps of the control method of the aviation turbo hybrid engine.

[0023] The embodiment of the application further provides a control device of an aviation turbo hybrid engine, which comprises an identification module, a judgment module, a processing module and a monitoring module.

[0024] The identification module is used for identifying the power mode in which the engine currently locates according to the key running parameters of the engine collected in real time, and the power mode comprises a pure electric mode, a hybrid mode and a turbo independent mode.

[0025] The judgment module is used for judging that the power mode switching condition set in advance is met and generating a corresponding switching decision according to the preset specific parameters corresponding to the current power mode.

[0026] The processing module is used for controlling the execution mechanism to adjust the outputs of the turbo engine and the motor according to the switching decision, so as to realize the power mode switching.

[0027] The monitoring module is used for monitoring the state of the engine in real time. If the switching fails, the current process is ended. If the switching succeeds, the identification module is returned.

[0028] In an exemplary example, the optimization module is further used for:

[0029] After the power mode switching is completed and a stable running stage is entered, a power output optimization strategy is executed. The power output optimization strategy is used for dynamically adjusting the output power ratio of the turbo engine and the motor according to the actual working condition, so that the system always runs in an efficient area.

[0030] In an exemplary example, the safety guarantee module is further used for:

[0031] The real-time monitoring of the engine operating state is continuously performed, and when one or more of the key operating parameters are detected to be abnormal, a preset safety protection mechanism is executed to ensure the operation safety and control stability of the system under complex working conditions.

[0032] The control method of the aviation turbo hybrid engine provided by the embodiment of the application realizes real-time identification and adaptive switching control of the power mode, and smooth transition of power output in the multi-mode switching process; a complete state monitoring and safety judgment closed loop is constructed, and the overall energy efficiency of the power system and the flight task matching capability are improved.

[0033] Further, by optimizing the power mode switching strategy and control algorithm, smooth switching of the aviation turbo hybrid engine power mode is realized, power interruption and fluctuation are avoided, and the flight stability and safety are improved.

[0034] Further, the safety monitoring and emergency control mechanism provided by the embodiment of the application adopts a closed loop design, maintains stable and controllable system state when an abnormality occurs, and provides complete data basis for subsequent ground maintenance, remote diagnosis and flight safety evaluation.

[0035] Other features and advantages of the present application will be set forth in the following description, and in part will become apparent to those skilled in the art from the description, or can be learned by practice of the present application. The objects and other advantages of the present application can be realized and achieved by the structure particularly pointed out in the specification, claims and drawings. BRIEF DESCRIPTION OF DRAWINGS

[0036] The accompanying drawings are intended to provide a further understanding of the technical solutions of the present application, and constitute a part of the specification, and are used together with the embodiments of the present application to explain the technical solutions of the present application, and do not constitute a limitation on the technical solutions of the present application.

[0037] Figure 1 A flowchart of the control method of the aviation turbo hybrid engine in the embodiment of the present application is shown in the figure;

[0038] Figure 2 A processing process diagram of the power mode switching embodiment in the embodiment of the present application is shown in the figure;

[0039] Figure 3 A schematic diagram of the control system architecture of the aviation turbo hybrid engine in the embodiment of the present application is shown in the figure;

[0040] Figure 4 A processing process diagram of the power output optimization control algorithm embodiment in the embodiment of the present application is shown in the figure;

[0041] Figure 5 A schematic diagram of the composition structure of the control device of the aviation turbo hybrid engine in the embodiment of the present application is shown in the figure. DETAILED DESCRIPTION

[0042] For the purpose of clarity, technical solutions and advantages of the present application will be described in detail below with reference to the drawings. It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other as long as there is no conflict.

[0043] In order to facilitate understanding of the present application, the present application will be described more fully below with reference to the relevant drawings. The embodiments of the present application are shown in the drawings. However, the present application can be implemented in many different forms, and is not limited to the embodiments described herein. On the contrary, the purpose of providing these embodiments is to make the disclosure of the present application more thorough and comprehensive.

[0044] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which the present application belongs. The terms used in the specification of the present application are only for the purpose of describing specific embodiments and are not intended to limit the present application.

[0045] It can be understood that the terms "first", "second" used in the present application are only for the purpose of description, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features limited by "first", "second" can be explicitly or implicitly included at least one of the features. In the description of the present application, the meaning of "a plurality of" is at least two, for example, two, three, etc., unless otherwise specifically limited.

[0046] It can be understood that "connection" in the following embodiments, if the connected circuits, modules, units, etc. have the transmission of electrical signals or data between each other, it should be understood as "electrically connected", "communicatively connected" and the like.

[0047] As used herein, the singular forms "a", "an" and "the" can include plural forms unless the context clearly indicates otherwise. It should also be understood that the term "comprises / comprising" or "has / have" specifies the presence of stated features, integers, steps, operations, components, parts, or combinations thereof, but does not exclude the presence or addition of one or more other features, integers, steps, operations, components, parts, or combinations thereof. At the same time, the term "and / or" used in the specification includes any and all combinations of the related listed items.

[0048] The steps shown in the flowchart of the drawings can be executed in a computer system such as a set of computer executable instructions. Also, although the logical order is shown in the flowchart, in some cases, the steps shown or described herein can be executed in an order different from that shown.

[0049] Figure 1 A flowchart of a control method for an aviation turbo-mixing engine in an embodiment of the present application is shown in FIG. 1, which can include the following steps: Figure 1

[0050] Step 100: Identify the current power mode of the engine according to the real-time collected key operating parameters of the engine. The power mode includes pure electric mode, hybrid mode and turbo independent mode.

[0051] In an exemplary example, step 100 can further include: collecting the key operating parameters of the engine in real time. In an embodiment, the key operating parameters of the engine can include, but are not limited to, such as: turbo speed, motor power, fuel flow, temperature, pressure, etc. In an embodiment, the key operating parameters can be collected by a sensor module, such as a speed sensor, a current detection module, a temperature / pressure sensor, etc. The collected data is transmitted to the engine's aviation controller (ECU) by a data bus (such as CAN or RS485, etc.) after analog-to-digital conversion (ADC) and filtering processing (optional). The ECU uniformly formats and normalizes the data as the basis for subsequent judgment. In an embodiment, the ECU can pre-process the received data, which can include but is not limited to filtering, amplification, analog-to-digital conversion, etc., to remove noise and interference and improve the accuracy and reliability of the data. Through this step, the engine operating conditions are comprehensively perceived, providing data basis for subsequent dynamic judgment of power mode and energy distribution.

[0052] ​In an exemplary embodiment, the identification of the current power mode of the engine is known to those skilled in the art, and the implementation process does not limit the protection scope of the present application. For example, for the pure electric mode, the characteristics are that only the motor provides propulsion, and the engine is in the off or idle state. At this time, the typical identification rules can include, for example: the flight phase is ground taxi, low-speed take-off, and short-time cruise; the flight load demand is low (such as < motor peak power x safety margin); the battery power is higher than the set SOC threshold (for example, > 70%); the turbine has not reached the starting temperature, or the current task does not require the engine to work; the current temperature and current of the motor are within the controllable range, etc. For the hybrid mode, the characteristics are that the motor and the turbine engine jointly provide power output, which is used for high-load or transition phase. At this time, the typical identification rules can include, for example: the flight phase is post-take-off climb, medium-altitude cruise or climb acceleration; the total load > single system supportable range (for example, > motor peak); the battery power is at a medium-high level (40%-70%), which can assist in output; the turbine has started and is in a steady-state output state; the motor temperature has not overloaded and still has auxiliary capacity, etc. For the turbine independent mode, the characteristics are that only the turbine engine provides power output, and the motor exits or is in standby state. At this time, the typical identification rules can include, for example: the battery power is low (such as SOC < 30%), and the motor cannot continuously supply energy; the motor temperature is high, which has triggered the protection or fault state; the flight is in high-power cruise, high-speed transition, and long-time working condition; the current task is the oil-driven safety redundancy mode, such as long-distance flight or emergency return, etc.

[0053] Step 101: According to the preset specific parameters corresponding to the current power mode, it is judged whether the power mode switching condition is met and the corresponding switching decision is generated.

[0054] In an exemplary embodiment, step 101 can include:

[0055] analyzing whether the preset specific parameters corresponding to the current power mode exceed the set threshold (such as whether the temperature is too high, whether the current is overloaded, and / or whether the load is out of limit, etc.);

[0056] When one or more key operating parameters considered as specific parameters exceed the threshold, it is judged whether the pre-set power mode switching condition is met, and the corresponding switching decision is generated when the power mode switching condition is met.

[0057] It should be noted that the preset parameters may differ for different power modes. For example, in pure electric mode, determining whether preset parameters exceed thresholds may include: whether the battery has sufficient charge, whether the motor temperature is too high, and whether the current load exceeds the motor's capacity. In hybrid mode, determining whether preset parameters exceed thresholds may include: whether the total load is still high, whether the battery is about to be depleted, whether the motor is overloaded, and whether the turbocharger is stable. In turbo-independent mode, determining whether preset parameters exceed thresholds may include: whether the battery has become usable again, whether the motor has cooled down, and whether the load has decreased to a level that the electric drive can handle.

[0058] Taking the current power mode as pure electric mode as an example, assuming the current flight phase is the initial climb, the key operating parameters collected are as follows: Battery SOC, currently 75%, the corresponding threshold for this key operating parameter is >70% for pure electric operation; Current load demand, currently 42kW, the corresponding threshold for this key operating parameter is the maximum motor load of 40kW; Motor temperature, currently 83℃, the corresponding threshold for this key operating parameter is 90℃; Lubricating oil temperature (used to determine whether the engine can start), currently 60℃, the corresponding threshold for this key operating parameter is 50℃. The system determines whether any specific parameter exceeds the set thresholds: SOC = 75%, higher than 70%; Motor temperature = 83℃, not exceeding the upper limit of 90℃; Current load = 42kW > maximum motor load of 40kW, this key operating parameter exceeds the predetermined threshold; Lubricating oil temperature = 60℃, higher than the engine start threshold of 50℃. In other words, one of the key operating parameters exceeding the predetermined threshold is the current load. In one embodiment, the power mode switching condition is assumed to be: the current load exceeds the motor's upper limit and the turbine preheats (oil temperature meets the standard), then the system switches to hybrid mode. Therefore, based on the current key operating parameters, the power mode switching condition is met, and a switching decision from pure electric to hybrid mode is generated.

[0059] In one embodiment, combined with Figure 2 , Figure 3 As shown, if the current mode is pure electric and the collected load is greater than the threshold, then switch to hybrid mode; otherwise, maintain the current pure electric mode. If the current mode is hybrid and the collected load is too low and below the threshold, then switch to pure electric mode; otherwise, maintain the current hybrid mode. If the current mode is turbo independent and the collected speed is less than the threshold, or the load is lower than the threshold, then switch to hybrid mode; otherwise, maintain turbo independent mode.

[0060] In an exemplary instance, if it is determined that the power mode switching condition is not met, the current power mode is maintained, and step 103 is entered.

[0061] Through steps 100 and 101, real-time acquisition and analysis of key operating parameters of the engine (such as load, battery power, temperature, speed, etc.) are achieved, the current power mode is accurately identified, and it is determined whether the switching condition is met according to the preset specific parameters and judgment rules, and the switching decision is generated in time. The system has dynamic perception and response ability to flight conditions, avoiding energy loss caused by static control.

[0062] Step 102: According to the switching decision, the controller controls the actuator to adjust the output of the turbine engine and the motor to realize power mode switching.

[0063] In an exemplary instance, when the controller determines that power mode switching is needed, it will generate a set of ordered control instructions according to the relationship between the current mode and the target mode, including motor power adjustment, fuel valve opening adjustment, ignition control, etc., to realize smooth transition between power sources. For example, if switching from pure electric mode to turbine independent mode, the control instruction sequence includes: starting the ignition device, slowly opening the fuel valve, warming up the ignition, establishing power output of the turbine, and reducing the output of the motor to exit; if switching from turbine mode to hybrid mode, the controller first activates the motor by power-on, gradually increases the output, realizes parallel operation with the turbine, and then dynamically optimizes the power distribution of the two. In an embodiment, the ECU can output PWM or analog signals to adjust the fuel solenoid valve and the input end of the motor controller (such as controlling the torque or output current). In an embodiment, interpolation or ramp function can be used to control the output to change gradually, preventing sudden changes.

[0064] In combination with FIGS. 1, 2, 3, and 4, Figure 2 , Figure 3 Taking switching from pure electric mode to hybrid mode as an example, the switching decision can include: the ECU first issues an instruction to slowly start the turbine engine, while gradually increasing the output torque of the motor, and after the turbine engine reaches a certain speed, gradually transitions the power output to the turbine engine and the motor working together, avoiding power interruption and fluctuations.

[0065] In an embodiment, when it is determined to switch the power mode, such as switching from the pure electric mode to the turbine mode, the switching decision can include: starting the ignition device, preparing the engine ignition → slowly opening the fuel valve, controlling the fuel supply speed of the combustion chamber → turbine ignition, establishing power output → gradually reducing the output power of the motor, entering standby state → gradually taking over the total power demand by the turbine output → switching is completed. For example, it is determined to switch from the hybrid mode to the independent mode, the switching decision can include: detecting low battery or motor protection state → sending control signals to gradually reduce the motor output power → the motor is cut off to enter the idle or sleep mode → the turbine maintains the original working state to increase the load ratio → the turbine independently provides all power output → the switching is completed. For example, it is determined to switch from the turbine mode to the hybrid mode, the switching decision can include: the motor is powered on and the output power is slowly increased → the turbine maintains the existing running state and maintains the basic load → the motor and the turbine work in parallel for a short time to achieve energy overloading → the motor / turbine power distribution ratio is gradually adjusted according to the load demand and energy saving target → the target distribution is reached and the hybrid mode is stably carried out.

[0066] In the embodiment of the application, according to the switching decision, the coordinated adjustment of the turbine and the motor output is controlled, the gradual conversion from one mode to another mode is realized, the power mutation and output fluctuation in the traditional switching are avoided, and the flight stability and ride comfort are improved.

[0067] Step 103: Real-time monitoring of the engine state, if the switching fails, end; if the switching succeeds, return to step 100.

[0068] In an exemplary example, step 103 can include:

[0069] Real-time monitoring of the running state of the engine, focusing on collecting key parameters such as turbine speed, oil temperature, fuel pressure, and power output. If the monitoring result shows that the engine has abnormal conditions such as abnormal speed, temperature overrun, and output failure, it is determined that the current power mode switching fails. At this time, the protection mechanism is triggered immediately, and emergency strategies such as power limitation, mode switching, and motor output disconnection are executed, and the abnormal information is stored in the local storage module for subsequent diagnosis and analysis, and the process is ended. If the monitoring result shows that the system is running normally, the power is output stably, and the parameters are stable, it is determined that the current switching succeeds, the mode state is updated, and the process returns to the working condition collection stage of step 100, and enters the next control cycle.

[0070] The real-time monitoring of the engine key operating parameters by step 103 provides a post-switch state monitoring and fault response mechanism to verify whether the engine state is normal after the power mode is switched; for example, the turbine speed is monitored to determine whether it reaches the stable operating speed range and whether the speed fluctuation is abnormal; for example, the oil temperature / exhaust temperature is monitored to determine whether it exceeds the upper limit of normal operation; for example, the output power / torque is monitored to determine whether it reaches the required level of the switching target; for example, the fuel pressure and motor current are monitored to determine whether there is a lack of pressure or output overcurrent safety hazard. In an embodiment, the actual collected value can be compared with the preset reasonable operating interval. If any of the following conditions exists, it is determined that the switching fails: the turbine speed does not reach the set stable lower limit (such as 60% of the rated speed); the engine temperature continues to rise beyond the warning threshold; the actual output power is much lower than the required power for the current flight task; the motor fails to access / exit the target mode; the system oscillates, and the parameter fluctuation is greater than the tolerance range. If the abnormality is confirmed, the protection mechanism is triggered and the fault is recorded, and the emergency handling process is immediately entered, such as recording abnormal information (including abnormal type, timestamp, and key parameter value) and storing; triggering the protection mechanism, such as reducing power operation, switching to the lowest risk mode (such as pure turbine), disconnecting the motor circuit, triggering an alarm (sent to the cockpit or ground test system), terminating the current switching process to avoid further deterioration, and the controller enters the end state. If the switching is successful, the next task phase is entered, such as stable output power, all temperature / pressure / speed parameters within the normal range, and power continuity meeting the flight requirements, then step 100 is returned, the current power mode state variable is updated, the working condition parameters are continuously collected, and the power control process of the next flight task phase is entered.

[0071] After the switching is executed, the engine operating state is monitored in real time in the embodiment of the application. If an abnormality (such as a speed that does not meet the standard, a temperature that is too high, etc.) is found, the switching is immediately terminated and the protection mechanism is triggered. If the switching is successful, the judgment process is re-entered to realize continuous circulation. Such processing improves the robustness and fault tolerance of the control system, and guarantees the stable and safe operation of the engine in complex flight environments. The embodiment of the application relies on a closed-loop control process to automatically switch the optimal power mode according to different flight phases (such as taxiing, climbing, cruising, etc.), which improves fuel efficiency, reduces emissions, prolongs system life, and reduces human intervention, thereby improving the intelligent level of the system.

[0072] The control method of the aviation turbo-hybrid engine provided by the embodiment of the application realizes real-time identification and adaptive switching control of the power mode, and smooth transition of power output during multi-mode switching; a complete state monitoring and safety judgment closed loop is constructed to improve the overall energy efficiency of the power system and the flight task matching ability.

[0073] In an exemplary instance, the control method of the aviation turbo hybrid engine provided by the embodiment of the application can further include step 104 after completing the power mode switching and entering the stable running phase:

[0074] The power output optimization strategy is executed. The power output optimization strategy is used to dynamically adjust the output power ratio of the turbo engine and the motor according to the actual working condition, so that the system always runs in the high-efficiency region, maximizes the fuel utilization rate and reduces the emission.

[0075] In an exemplary instance, the ECU selects the applicable optimization control algorithm for calculation based on the collected engine running parameters (including the current load demand, turbo speed, fuel consumption rate, motor efficiency, emission data and the like) and the preset target performance indicators (such as the lowest fuel consumption, emission compliance, torque response and the like), and generates control instructions (such as fuel valve opening adjustment, motor torque setting, power distribution strategy and the like) according to the algorithm output results, so as to implement the adjustment action through the actuator module, and ensure that the power system continuously runs in the high-efficiency and economic working condition interval.

[0076] In an embodiment, the control algorithm used can include but is not limited to, for example, a PID control algorithm, which is suitable for scenarios with small load changes or clear response targets, and which realizes proportional control of the power output of the turbo and the motor through error feedback adjustment; a fuzzy control algorithm, which is suitable for complex working conditions with nonlinearity, model uncertainty or multi-target coordination, and which realizes a more flexible output control strategy based on fuzzy rule base processing of input quantities. For example, in a low load working condition, the ECU determines that the motor can drive the aircraft alone, and thus preferentially distributes power to the motor to reduce fuel consumption; and in a high load working condition, the ECU calculates the optimal cooperative working point, and reasonably allocates the power output ratio of the turbo engine and the motor, so as to meet the power performance demand while avoiding system overload.

[0077] In the embodiment of the application, the smooth switching of the power mode of the aviation turbo hybrid engine is realized by optimizing the power mode switching strategy and the control algorithm, the power interruption and fluctuation are avoided, and the stability and safety of the flight are improved. The advanced power output optimization algorithm is used to reasonably allocate the power output of the turbo engine and the motor, so that the engine can work in the high-efficiency region under different working conditions, and the fuel efficiency is significantly improved, and the fuel consumption and operating cost are reduced.

[0078] In an exemplary instance, the control method of the aviation turbo hybrid engine provided by the embodiment of the application can further include step 105 while the power output optimization strategy is implemented:

[0079] Real-time monitoring of engine operating conditions is continuously performed, with focus on key operating parameters such as turbine speed, oil temperature, exhaust temperature, fuel pressure, motor current, etc., to ensure the safety and stability of the system under complex operating conditions. For example, when the ECU detects that one or more parameters are abnormal and exceed the limit, such as the turbine speed exceeding the preset safety upper limit, and / or the exhaust temperature rising sharply, exceeding the combustion stable interval, and / or the motor is continuously overloaded, the battery is overheated, etc. The ECU will immediately execute the built-in preset safety protection mechanism to automatically trigger the following measures: issue protection instructions, including power reduction, forced power-off, current limiting control, etc.; shut down high-risk systems (such as motor systems or auxiliary burners) to prevent the fault from expanding; record abnormal data, write related fault codes, abnormal parameters and time stamps into the storage module; enter protection mode or interrupt the current task to prevent further damage or safety accidents.

[0080] The safety monitoring and emergency control mechanism provided by the embodiments of the present application adopts a closed-loop design, maintains stable and controllable system state while an abnormality occurs, and provides complete data basis for subsequent ground maintenance, remote diagnosis and flight safety evaluation. The embodiments of the present application enhance the stability and safety of engine operation by real-time monitoring of engine operating parameters and triggering safety protection mechanisms, can effectively cope with complex flight environments and operating conditions, and prolong the service life of the engine. Moreover, the control algorithm has strong robustness and adaptability, can be flexibly adjusted and optimized according to different engine models and operating conditions, and has wide application prospects.

[0081] Figure 4 The process schematic diagram of one embodiment of the aviation turbo hybrid engine power output optimization method based on the dynamic control algorithm is as follows: Figure 4As shown, in this embodiment, after the engine completes the power mode switching and enters the stable running state, first, according to the actual flight working condition, the power output ratio of the turbine engine and the motor is dynamically adjusted to maximize fuel efficiency and optimize system stability. First, the sensor module collects the key parameters of the engine operation in real time, including but not limited to, such as: turbine speed, motor power and torque, fuel flow, exhaust temperature, motor current, battery voltage, etc. These data can be sent to the ECU through the high-speed data bus for subsequent control decision basis. After the ECU receives the original parameters, it performs preprocessing operations, including, such as filtering, amplification, normalization and analog-to-digital conversion, etc., to eliminate sampling noise and improve data stability. Subsequently, the control algorithm selection stage is entered. The ECU can automatically call the applicable control algorithm according to the complexity of the current working condition, such as, if the current load change is small and the environmental disturbance is low, the PID control algorithm is selected, the error is calculated and the motor / turbine output ratio is adjusted in real time through the set output target (such as target torque, fuel efficiency, etc.); if the current working condition has nonlinearity, multiple disturbances or multiple target requirements, the fuzzy control algorithm is selected, based on the fuzzy rule base and fuzzy logic reasoning mechanism, the power distribution ratio between the motor and the turbine is optimized to improve adaptability and control accuracy. After the control algorithm outputs the target control quantity, the ECU generates control instructions, which can include, such as fuel valve opening, motor torque target, current adjustment signal, etc., and sends these instructions to the actuator. The actuator adjusts the running state of the turbine and the motor according to the instructions to complete the actual power output adjustment. During the execution of the control instructions, the ECU also records and stores the historical running parameters and control behavior for subsequent optimization analysis. At the same time, the ECU monitors the actual output effect of the engine in real time, and compares the output result with the preset performance target (such as fuel efficiency, emission level, output stability, etc.). When it is judged that the current output has reached the optimization target, the current control strategy is maintained, and the engine enters the stable running state; if the target performance is not reached, return to the control algorithm to re-execute parameter analysis and control instruction generation, realizing closed-loop adaptive optimization. This embodiment can also be combined with a safety protection mechanism to further improve robustness, that is, when the ECU detects abnormality in key parameters (such as turbine temperature, motor current, battery status, etc.) during optimization execution, it can immediately trigger the safety control strategy, including limiting power output, disconnecting the faulty subsystem, issuing an alarm, and recording fault data, entering protection mode.

[0082] Through this embodiment, the aviation turbine hybrid engine can dynamically realize energy deployment between the turbine and the motor in different flight stages, ensuring that the power output meets the task requirements while effectively reducing fuel consumption and emissions, and enhancing the adaptability and fault protection capability of the system to complex working conditions.

[0083] Figure 3An embodiment of the control system architecture and signal flow of an aviation turbine hybrid engine is shown. In this embodiment, as shown in FIG. 1, the engine control system architecture includes an engine body, an engine controller (ECU), a ground test device, a sensor module, an ignition device, a fuel system, an oil system, a power supply system, an on-board battery, a master control network, a generator control unit (GCU), and various data and control channels. Figure 3

[0084] Figure 3 In this embodiment, the ECU, as the core control unit of the system, is connected to multiple peripheral components and modules through a data bus, an analog signal line, and a control channel, for receiving flight state information, monitoring engine operating parameters, performing power mode switching control, executing output power optimization strategies, and triggering a fault protection mechanism when necessary. Multiple key sensor modules are deployed in the system to collect key operating parameters of the engine, including a rotational speed sensor (magneto type) for collecting turbine shaft rotational speed N, an intake temperature sensor T2 (platinum resistance), an intake pressure P2 sensor (silicon piezoresistive type), an exhaust temperature T5 sensor (thermocouple), a nozzle main oil pressure P2p and start-up nozzle oil pressure Pap sensor for monitoring fuel injection state, a fuel temperature and pressure sensor, and a lubricating oil tank lubricating oil temperature To and lubricating oil pressure Po sensor.

[0085] The above analog signals are transmitted to the ECU for ADC conversion and digital filtering and other preprocessing operations. The processed digital data is interconnected with the ground test device through an RS422 bidirectional serial bus, realizing remote debugging, state monitoring, and system calibration.

[0086] The ECU performs format unification and normalization processing on all collected data, and identifies the current power mode (e.g., pure electric, hybrid, turbine independent) based on pre-set judgment logic. When mode switching is required, the ECU outputs switching control signals according to the determination results, such as controlling the ignition device to power on, controlling the fuel electric valve to open and close, and controlling the auxiliary electric fuel pump to start and stop.

[0087] The fuel system is composed of a fuel tank, a fuel temperature / pressure sensor, and an electric fuel pump. The fuel is supplied by the electric pump and enters the combustion chamber through the nozzle. The ECU can control the injection state based on the fuel pressure change and nozzle oil pressure monitoring results, and adjust the fuel injection amount according to the flight stage and load demand. Fuel-related instructions are issued to the electric fuel pump controller through the ECU.

[0088] The oil system is composed of an oil tank, an electric oil pump, and a temperature / pressure sensor, and is used to lubricate the rotating parts of the engine. The ECU can adjust the working state of the oil pump according to the real-time feedback of the oil temperature To and pressure Po.

[0089] ​The ignition system is composed of an ignition device and an ignition cable. The ECU sends an ignition control signal (ignition trigger instruction) to the ignition device when the engine starts or the power is switched to the turbine mode, completing the ignition starting process. The power supply for this part is provided by the 28V power bus.

[0090] Figure 3 The engine control system in the embodiment supports a dual power supply structure, including a main power supply line from an on-board battery and a master control power grid (28V bus). Some high-power modules (such as the GCU) generate a 600V power supply for the electric propulsion module by internally boosting the 28V input. In addition to providing power, the GCU also feeds back the motor control state and power output state to the ECU, enabling global energy management.

[0091] During normal operation of the engine, the ECU dynamically calls control algorithm modules (such as PID, fuzzy control, etc.) according to different flight task stages and load changes to generate control targets (fuel injection amount, motor torque, etc.), and adjusts the power distribution ratio between the turbine engine and the motor in real time through the above signal path.

[0092] In addition, when the ECU detects abnormality in key operating parameters of the engine (such as abnormal speed, temperature overrun, pressure drop, current abnormality, etc.), it will immediately trigger a safety protection mechanism, such as limiting power output, forcibly disconnecting some sub-modules (such as the motor), recording fault data, closing the fuel valve, etc. to ensure safe and stable operation of the system.

[0093] The engine control system provided by the embodiment realizes efficient, intelligent, and adaptive power control, ensuring the safety, economy, and sustainability of the flight task.

[0094] A computer-readable storage medium is provided, which stores computer-executable instructions for executing the control method of the aviation turbine hybrid engine according to any one of the preceding embodiments.

[0095] The application further provides a computer device, comprising a memory and a processor, wherein the memory stores instructions executable by the processor, for executing the steps of the control method of the aviation turbine hybrid engine according to any one of the preceding embodiments.

[0096] Figure 5 The control device for the aviation turbine hybrid engine in the embodiment is a schematic diagram of the component structure of the control device. The control device provided by the embodiment can be arranged in the ECU. As shown in the figure, it can include an identification module, a judgment module, a processing module, and a monitoring module. Figure 5

[0097] ​An identification module is configured to identify a current power mode of the engine according to real-time collected key operating parameters of the engine, the power mode including a pure electric mode, a hybrid mode and a turbo independent mode.

[0098] A judgment module is configured to judge that a power mode switching condition is met and generate a corresponding switching decision according to preset specific parameters corresponding to the current power mode.

[0099] A processing module is configured to control an actuator to adjust outputs of the turbo engine and the motor according to the switching decision, so as to realize power mode switching.

[0100] A monitoring module is configured to monitor the state of the engine in real time, and if the switching fails, the process ends; if the switching succeeds, the process returns to the identification module.

[0101] In an exemplary example, the method can further include:

[0102] A collection processing module is configured to collect key operating parameters of the engine in real time; after ADC conversion and filtering processing (optional) of the collected data, the data can be transmitted to a preprocessing module through a data bus (such as CAN or RS485, etc.).

[0103] The preprocessing module is configured to uniformly format and normalize the received data as a basis for subsequent judgment. In an embodiment, the preprocessing can include but is not limited to digital filtering, amplification, format conversion, etc., to remove noise and interference and improve the accuracy and reliability of the data.

[0104] In an embodiment, the collection module can be implemented by sensors such as a speed sensor, a current detection module, a temperature / pressure sensor, etc. to collect the key operating parameters.

[0105] In an exemplary example, the judgment module can be specifically configured to:

[0106] analyze whether the preset specific parameters corresponding to the current power mode exceed a set threshold (such as whether the temperature is too high, whether the current is overloaded, and / or whether the load is out of limit, etc.); when one or more key operating parameters considered as specific parameters exceed the threshold, it is judged whether the pre-set power mode switching condition is met, and a corresponding switching decision is generated when the power mode switching condition is met.

[0107] In an exemplary example, the judgment module can be further configured to judge that the power mode switching condition is not met, and then maintain the current power mode and enter the monitoring module.

[0108] In an exemplary example, the processing module is specifically configured to:

[0109] When determining that power mode switching is required, a set of ordered control instructions are generated according to the relationship between the current mode and the target mode, including motor power regulation, fuel valve opening degree regulation, ignition control, etc., to achieve smooth transition between power sources.

[0110] In an exemplary example, the monitoring module is specifically configured to:

[0111] The operating state of the engine is monitored in real time, and if the monitoring result shows that the engine has an abnormality, it is determined that the current power mode switching fails, a protection mechanism is triggered, and abnormal information is stored. If the monitoring result shows that the system is running normally, it is determined that the current switching is successful, the mode state is updated, and the recognition module returns to the next control cycle.

[0112] The control device of the aviation turbo hybrid engine provided by the embodiment of the application realizes real-time identification and adaptive switching control of the power mode, and smooth transition of power output in the multi-mode switching process; a complete state monitoring and safety judgment closed loop is constructed, and the overall energy efficiency and flight task matching capability of the power system are improved.

[0113] In an exemplary example, the control device of the aviation turbo hybrid engine provided by the embodiment of the application can further include an optimization module configured to:

[0114] After completing the power mode switching and entering the stable running stage, a power output optimization strategy is executed. The power output optimization strategy is used to dynamically adjust the output power ratio of the turbine engine and the motor according to the actual working condition, so that the system always runs in the high-efficiency region, and the fuel utilization rate is maximized and the emission is reduced.

[0115] In the embodiment of the application, by optimizing the power mode switching strategy and the control algorithm, smooth switching of the power mode of the aviation turbo hybrid engine is realized, power interruption and fluctuation are avoided, and the stability and safety of flight are improved. By using an advanced power output optimization algorithm, the power output of the turbine engine and the motor is reasonably distributed, so that the engine can work in the high-efficiency region under different working conditions, and the fuel efficiency is significantly improved, and the fuel consumption and operating cost are reduced.

[0116] In an exemplary example, the control device of the aviation turbo hybrid engine provided by the embodiment of the application can further include a safety guarantee module configured to:

[0117] While the power output optimization strategy is implemented, the operating state of the engine is continuously monitored in real time, and key operating parameters such as turbine speed, oil temperature, exhaust temperature, fuel pressure, motor current, etc. are focused on. When one or more of the key operating parameters are abnormal, a preset safety protection mechanism is executed to ensure the running safety and control stability of the system under complex working conditions.

[0118] The safety monitoring and emergency control mechanism provided by the embodiments of the present application adopts a closed loop design, maintains stable and controllable system state while an abnormality occurs, and provides complete data basis for subsequent ground maintenance, remote diagnosis and flight safety evaluation. The embodiments of the present application enhance the stability and safety of engine operation by monitoring engine operating parameters in real time and triggering a safety protection mechanism, can effectively cope with complex flight environments and working conditions, and prolong the service life of the engine. Moreover, the control algorithm has strong robustness and adaptability, can be flexibly adjusted and optimized according to different engine models and operating conditions, and has wide application prospects.

[0119] Although the embodiments disclosed in the present application are as above, the content described is only the embodiments adopted for the purpose of facilitating the understanding of the present application, and is not intended to limit the present application. Any person skilled in the art of the present application can make any modification and change in the form and details without departing from the spirit and scope of the present application. The patent protection scope of the present application shall be subject to the scope defined by the appended claims.

Claims

1. A control method of an aviation turbo-mix engine, characterized in that, Comprising: identifying the current power mode of the engine according to the real-time collected key operating parameters of the engine, the power mode including pure electric mode, hybrid mode and turbine independent mode; judging that the pre-set power mode switching condition is met and generating a corresponding switching decision according to the pre-set specific parameters corresponding to the current power mode; controlling the actuator to adjust the output of the turbine engine and the motor according to the switching decision to realize power mode switching, including: when it is determined that the power mode switching is needed, generating a set of ordered control instructions according to the relationship between the current power mode and the target mode; and executing the power mode switching according to the generated ordered control instructions; real-time monitoring the engine state, if the monitoring result shows that the engine has an abnormality, determining that the current power mode switching fails, triggering a protection mechanism and storing abnormal information, and ending the process; if the monitoring result shows that the engine is normal, determining that the current power mode switching succeeds, updating the power mode state, and returning to the step of identifying the current power mode of the engine; after completing the power mode switching and entering the stable running stage, executing a power output optimization strategy, which is used to dynamically adjust the output power ratio of the turbine engine and the motor according to the actual working condition, so that the system always runs in the high-efficiency area.

2. The control method according to claim 1, if it is judged that the power mode switching condition is not satisfied, further comprising: maintaining the current power mode and entering the step of real-time monitoring the engine state.

3. The control method according to claim 1, further comprising: continuously monitoring the engine operating state, and when one or more key operating parameters are detected to be abnormal, executing a pre-set safety protection mechanism to ensure the running safety and control stability of the system under complex working conditions.

4. The control method according to any one of claims 1 to 3, wherein The judging that the pre-set power mode switching condition is met and generating a corresponding switching decision, comprising: analyzing whether the pre-set specific parameters corresponding to the current power mode exceed the set threshold; when one or more key operating parameters as the pre-set specific parameters exceed the threshold, judging whether the power mode switching condition is met, and generating the corresponding switching decision when the power mode switching condition is met.

5. A computer readable storage medium storing computer executable instructions for executing the control method of the aviation turbine hybrid engine according to any one of claims 1-4.

6. A computer device comprising a memory and a processor, wherein, The memory stores the following instructions executable by the processor: steps for executing the control method of the aviation turbine hybrid engine according to any one of claims 1-4.

7. A control device of an aviation turbo-mix engine, characterized in that, Comprising: an identification module, a judgment module, a processing module and a monitoring module; wherein, the identification module is configured to identify the current power mode of the engine according to the real-time collected key operating parameters of the engine, the power mode including pure electric mode, hybrid mode and turbine independent mode; the judgment module is configured to judge that the pre-set power mode switching condition is met and generate a corresponding switching decision according to the pre-set specific parameters corresponding to the current power mode; the processing module is configured to control the actuator to adjust the output of the turbine engine and the motor according to the switching decision to realize power mode switching, including: when it is determined that the power mode switching is needed, generating a set of ordered control instructions according to the relationship between the current power mode and the target mode; The processing module is configured to control the adjusting of the output of the turbine engine and the motor by the actuator according to a switching decision to realize the power mode switching, including: when it is determined that the power mode switching is needed, generating a set of ordered control instructions according to the relationship between the current power mode and the target mode; and performing the power mode switching according to the generated ordered control instructions; The monitoring module is configured to monitor the engine state in real time, if the monitoring result shows that the engine is abnormal, it is determined that the current power mode switching fails, a protection mechanism is triggered and the abnormal information is stored, and the current process is ended; if the monitoring result shows that the engine is normal, it is determined that the current power mode switching succeeds, the power mode state is updated, and the step of identifying the current power mode of the engine is returned to. The optimization module is further configured to: After the power mode switching is completed and the system enters a stable running stage, a power output optimization strategy is executed; the power output optimization strategy is configured to dynamically adjust the output power ratio of the turbine engine and the motor according to the actual working condition, so that the system always runs in an efficient area.

8. The control device according to claim 7, further comprising a safety guarantee module configured to: continuously monitor the engine running state, and when one or more of the key running parameters are detected to be abnormal, a preset safety protection mechanism is executed to guarantee the running safety and control stability of the system under complex working conditions.

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