Starting oil supply rule control method and device for aerial unmanned engine

Abstract

The invention relates to the technical field of aero-engines, and discloses a starting oil supply rule control method and device for an unmanned aerial engine, and the method comprises the steps: obtaining the rotating speed and acceleration at a target moment and a historical moment, and judging whether a first switching condition is met or not; if yes, the inlet temperature of the power turbine at the target moment and the historical moment is obtained, and whether a second switching condition is met or not is judged; if yes, the fuel given quantity and the fuel feedback quantity are obtained, and whether a third switching condition is met or not is judged; if yes, judging whether a fourth switching condition is met or not based on the first time consumption, the second time consumption and the third time consumption; if yes, whether a fifth switching condition is met or not is judged based on the first time consumption, the second time consumption and the fourth time consumption; if yes, switching to a third starting stage in advance, and executing the oil supply rule of the third starting stage. Through multi-stage judgment, oil supply rules are timely and effectively switched, suspension protection is prevented from being triggered, and the starting success rate of the engine is increased.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engines, in particular to a starting fuel supply law control method and device for an aero-unmanned engine. BACKGROUND

[0002] The aero-unmanned engine is often started and used in harsh and changeable environments such as ice, sand, rain and snow, plateau, plain, high temperature and low temperature. In order to successfully start the engine in various environments, the starting fuel supply law is crucial. The starting process of the traditional aero-unmanned engine includes three stages, and different fuel supply laws are used in the three stages: no fuel supply in the first starting stage; given fuel flow control in the second starting stage; and given acceleration control in the third starting stage.

[0003] The traditional fuel supply law control method is to gradually go through the three stages of starting and gradually execute the corresponding fuel supply law as the compressor rotor speed increases during the starting process of the engine. However, the fuel supply law used in the second starting stage has poor environmental adaptability when the atmospheric environment changes. When facing harsh environments such as extreme cold and plateau, the acceleration is slow, so that the compressor rotor speed cannot reach the specified value within the specified time, triggering the starting suspension protection logic, and the engine cannot smoothly enter the third starting stage to execute the corresponding fuel supply law. Even if it can enter the third starting stage, it will also trigger the starting suspension protection logic due to the long starting time, resulting in engine shutdown and starting failure.

[0004] Therefore, how to control the switching of the fuel supply law to successfully start the engine in a complex and changeable atmospheric environment is a problem to be solved. SUMMARY

[0005] Therefore, the present application provides a starting fuel supply law control method and device for an aero-unmanned engine to solve the problem of successfully starting the engine by controlling the switching of the fuel supply law in a complex and changeable atmospheric environment.

[0006] In a first aspect, the present application provides a starting fuel supply law control method for an aero-unmanned engine, which comprises:

[0007] The rotational speed and acceleration of the target time and the historical time are obtained respectively, and it is judged whether the first switching condition is met. The target time and the historical time are both located in the second starting stage of the aero-unmanned engine, and the second starting stage represents the stage in which the compressor rotor speed of the aero-unmanned engine is located in the first preset interval;

[0008] When the first switching condition is met, the power turbine inlet temperature of the target time and the historical time is obtained respectively, and it is judged whether the second switching condition is met;

[0009] When the second switching condition is met, the fuel given amount and the fuel feedback amount are obtained, and it is determined whether the third switching condition is met;

[0010] When the third switching condition is met, the first time consumption of the starting first stage is obtained, the second time consumption and the third time consumption are determined, and based on the first time consumption, the second time consumption and the third time consumption, it is determined whether the fourth switching condition is met, the starting first stage indicating a stage in which the compressor rotor speed of the aviation unmanned engine is located in a second preset interval;

[0011] When the fourth switching condition is met, the fourth time consumption of the starting third stage is determined, and based on the first time consumption, the second time consumption and the fourth time consumption, it is determined whether the fifth switching condition is met, and when the fifth switching condition is met, the aviation unmanned engine is controlled to switch from the starting second stage to the starting third stage in advance, and the fuel supply rule of the starting third stage is executed.

[0012] The application realizes early identification of starting abnormality from the speed trend level by continuously monitoring the speed and acceleration change of the starting second stage, and further verifies the starting abnormality trend when there is a suspended trend in the speed in combination with the trend of the power turbine inlet temperature. When the engine has shown the starting suspension trend in the speed and temperature levels, the starting suspension caused by non-environmental factors such as fuel leakage is excluded through the fuel given amount and the feedback amount, and it is ensured that the subsequent fuel supply adjustment is based on normal fuel supply. When there is no significant leakage in the fuel system, it is verified from the time angle to ensure that the starting suspension protection logic is not triggered when the fuel supply rule of the starting third stage is switched in advance, and the engine starting success rate is improved. Through multi-level dynamic judgment, the starting suspension trend is accurately identified, the time when the starting second stage switches to the starting third stage in advance is determined, the fuel supply rule of the given acceleration control with stronger adaptability is switched in advance in the harsh environment such as extreme cold and high altitude, the starting suspension protection logic is avoided, the problem of poor adaptability of the traditional given fuel flow control is solved, the timely and effective switching of the fuel supply rule is realized, and the engine starting success rate is improved.

[0013] In an optional implementation, the historical time includes a first time and a second time, the first time being a previous time of the target time, and the second time being a previous time of the first time;

[0014] The speed and acceleration of the target time and the historical time are obtained respectively, and it is determined whether the first switching condition is met, including:

[0015] The first speed and the first acceleration of the target time, the second speed and the second acceleration of the first time, and the third speed and the third acceleration of the second time are obtained;

[0016] When the third acceleration, the second acceleration and the first acceleration increase in turn or the absolute value of the difference between the first speed and the third speed is less than a first threshold, it is determined that the first condition is met;

[0017] obtaining an initial acceleration of the starting second stage, calculating an acceleration difference between the initial acceleration and the first acceleration, and calculating an acceleration ratio of the acceleration difference and the initial acceleration;

[0018] determining that the second condition is met when the acceleration ratio is not less than a second threshold value;

[0019] determining that the first switching condition is met when the first condition and the second condition are met;

[0020] determining that the first switching condition is not met when the first condition and / or the second condition is not met.

[0021] The application ensures that the data covers a sufficient time span by collecting the rotation speed and acceleration of the three consecutive sampling periods of the target time, the first time and the second time, judges whether the first condition and the second condition are met according to the collected data, and accurately identifies the suspension risk of the starting second stage. Only when the first condition and the second condition are met at the same time, it is determined that the first switching condition is met, ensuring that only when there is a serious suspension trend, the next step is entered; otherwise, if any condition is not met, it is determined that the first switching condition is not met, avoiding excessive intervention in the normal starting process, which helps to improve the starting success rate of the engine.

[0022] In an optional embodiment, when the first switching condition is met, the power turbine inlet temperature of the target time and the historical time is obtained respectively to determine whether the second switching condition is met, comprising:

[0023] When the first switching condition is met, the first power turbine inlet temperature of the target time, the second power turbine inlet temperature of the first time and the third power turbine inlet temperature of the second time are obtained, and the first temperature acceleration of the target time, the second temperature acceleration of the first time and the third temperature acceleration of the second time are determined;

[0024] obtaining a starting maximum allowable temperature of the power turbine, and determining a third threshold value based on the starting maximum allowable temperature;

[0025] determining that the third condition is met when the third temperature acceleration, the second temperature acceleration and the first temperature acceleration increase in turn;

[0026] determining that the fourth condition is met when the first power turbine inlet temperature is less than the third threshold value;

[0027] determining that the second switching condition is met when the third condition and the fourth condition are met;

[0028] determining that the second switching condition is not met when the third condition and / or the fourth condition is not met.

[0029] The application further verifies the suspension trend from the temperature trend level by collecting the power turbine inlet temperature after meeting the first switching condition and judging whether the third condition and the fourth condition are met, and meanwhile avoids over-temperature shutdown after switching to the third stage. Only when the third condition and the fourth condition are met at the same time, it is determined that the second switching condition is met, which ensures the consistency of the temperature characteristics and the suspension trend and guarantees the thermal safety; otherwise, if any condition is not met, the judgment is terminated and the previous link is returned, which avoids blindly switching the fuel supply rule when the temperature characteristics do not support or there is a safety hazard, and improves the reliability of the engine starting control.

[0030] In an optional embodiment, judging whether the third switching condition is met comprises:

[0031] calculating a fuel difference value between the fuel given amount and the fuel feedback amount, and calculating an absolute value of a ratio of the fuel difference value to the fuel given amount;

[0032] when the absolute value is not greater than the fourth threshold value, it is determined that the third switching condition is met;

[0033] when the absolute value is greater than the fourth threshold value, it is determined that the third switching condition is not met.

[0034] The application judges whether the third switching condition is met based on the fuel given amount and the fuel feedback amount to identify whether significant fuel leakage occurs, ensures that the subsequent fuel supply rule switching is based on normal fuel supply, and effectively reduces the risk of starting failure and safety accidents caused by fuel leakage.

[0035] In an optional embodiment, determining the second time consumption and the third time consumption comprises:

[0036] obtaining the balance speed and the starting time of the second starting stage;

[0037] determining a time difference between the target time and the starting time as the second time consumption;

[0038] calculating a first speed difference value between the balance speed and the first speed, and determining a ratio of the first speed difference value to the first acceleration as the third time consumption.

[0039] The application obtains the balance speed and the starting time of the second starting stage to provide core parameters for subsequent time verification, determines the time difference between the target time and the starting time as the second time consumption, which intuitively reflects the time consumed from entering the second starting stage to the current target time, and determines the third time consumption based on the balance speed and the first speed, which quantifies the estimated time required to complete the remaining process of the second starting stage under the current acceleration state, and provides core data for the judgment of the fourth switching condition.

[0040] In an optional implementation, the determining whether the fourth switching condition is met based on the first time consumption, the second time consumption and the third time consumption comprises:

[0041] The first time threshold is determined based on the start suspension protection logic, and the fifth threshold is determined based on the first time threshold;

[0042] When the sum of the first time consumption, the second time consumption and the third time consumption is less than the fifth threshold, it is determined that the fourth switching condition is met;

[0043] When the sum of the first time consumption, the second time consumption and the third time consumption is not less than the first time threshold, it is determined that the fourth switching condition is not met.

[0044] The application determines whether the second stage of starting is timed out through the first time threshold. When the sum of the first time consumption, the second time consumption and the third time consumption is less than the fifth threshold, it indicates that the total time for completing the second stage of starting in the current state is sufficient, and the third stage of starting is switched in advance to effectively shorten the time consumption, and the start suspension protection logic is not triggered. If the sum of the three is not less than the first time threshold, it is still triggered that the start suspension protection logic is triggered due to the total time exceeding the limit even if the switching is advanced. By judging the timing of the oil supply rule switching, the starting success rate is effectively improved.

[0045] In an optional implementation, the fourth time consumption of the third stage of starting is determined, comprising:

[0046] The ground slow rotating speed and the preset acceleration of the third stage of starting are obtained;

[0047] The second rotating speed difference between the ground slow rotating speed and the first rotating speed is calculated, and the ratio between the second rotating speed difference and the preset acceleration is calculated;

[0048] The product of the ratio and the sixth threshold is determined as the fourth time consumption.

[0049] The application provides data for estimating the third stage time consumption through the ground slow rotating speed and the preset acceleration of the third stage of starting. The fourth time consumption is calculated based on the ground slow rotating speed, the second rotating speed and the sixth threshold, the gap from the current rotating speed to the final target rotating speed is quantified, the estimation of the fourth time consumption is more in line with the actual acceleration process, and core data is provided for the subsequent judgment of the fifth switching condition.

[0050] In an optional implementation, the determining whether the fifth switching condition is met based on the first time consumption, the second time consumption and the fourth time consumption comprises:

[0051] The second time threshold is determined based on the start suspension protection logic, and the seventh threshold is determined based on the second time threshold;

[0052] When the sum of the first time consumption, the second time consumption and the fourth time consumption is less than the seventh threshold, it is determined that the fifth switching condition is met;

[0053] When the sum of the first time consumption, the second time consumption and the fourth time consumption is not less than the seventh threshold value, it is determined that the fifth switching condition is not met.

[0054] The application determines the success or failure of starting by the second time threshold value corresponding to the starting suspension protection logic, and the seventh threshold value is set based on the second time threshold value. When the sum of the first time consumption, the second time consumption and the fourth time consumption is less than the seventh threshold value, it indicates that the total time consumption can be controlled within a safe range after switching into the starting third stage in advance, and the starting suspension protection logic can be avoided. If the sum of the three is not less than the seventh threshold value, it indicates that even if the starting third stage is switched into in advance, there is a risk of triggering the starting suspension protection logic. By judging the timing of the fuel supply law switching, the starting success rate is effectively improved.

[0055] In a second aspect, the application provides a starting fuel supply law control device of an aviation unmanned engine, which comprises:

[0056] A first judging module is configured to acquire the rotation speed and acceleration at a target time and a historical time respectively, and determine whether the first switching condition is met, the target time and the historical time are both located in a starting second stage of the aviation unmanned engine, and the starting second stage represents a stage in which the rotation speed of the compressor rotor of the aviation unmanned engine is located in a first preset interval;

[0057] A second judging module is configured to acquire the power turbine inlet temperature at the target time and the historical time respectively when the first switching condition is met, and determine whether the second switching condition is met;

[0058] A third judging module is configured to acquire the fuel given amount and the fuel feedback amount when the second switching condition is met, and determine whether the third switching condition is met;

[0059] A fourth judging module is configured to acquire the first time consumption in a starting first stage, determine the second time consumption and the third time consumption, and determine whether the fourth switching condition is met based on the first time consumption, the second time consumption and the third time consumption, the starting first stage represents a stage in which the rotation speed of the compressor rotor of the aviation unmanned engine is located in a second preset interval;

[0060] A control module is configured to determine the fourth time consumption in a starting third stage based on the first time consumption, the second time consumption and the fourth time consumption when the fourth switching condition is met, and determine whether the fifth switching condition is met, and control the aviation unmanned engine to switch from the starting second stage to the starting third stage and execute the fuel supply law of the starting third stage when the fifth switching condition is met.

[0061] In a third aspect, the present application provides a computer device, comprising a memory and a processor, which are communicatively connected with each other, and the memory stores computer instructions, and the processor executes the starting fuel supply law control method of the aviation unmanned engine according to the first aspect or any one of the corresponding embodiments.

[0062] In a fourth aspect, the present application provides a computer readable storage medium, which stores computer instructions for making a computer execute the starting fuel supply law control method of the aviation unmanned engine according to the first aspect or any one of the corresponding embodiments. BRIEF DESCRIPTION OF DRAWINGS

[0063] In order to more clearly illustrate the specific embodiments or prior art technical solutions of the present application, the drawings needed in the specific embodiments or prior art description will be briefly introduced as follows. Obviously, the drawings in the following description are some embodiments of the present application, and those skilled in the art can obtain other drawings according to these drawings without creative labor.

[0064] Figure 1 is a starting curve diagram of an aviation unmanned engine according to an embodiment of the present application;

[0065] Figure 2 is a flowchart of the starting fuel supply law control method of the aviation unmanned engine according to an embodiment of the present application;

[0066] Figure 3 is another starting curve diagram of an aviation unmanned engine according to an embodiment of the present application;

[0067] Figure 4 is a structural block diagram of the starting fuel supply law control device of the aviation unmanned engine according to an embodiment of the present application;

[0068] Figure 5 is a hardware structure diagram of the computer device according to an embodiment of the present application. DETAILED DESCRIPTION

[0069] In order to make the purpose, technical solutions and advantages of the embodiments of the present application more clear, the technical solutions of the embodiments of the present application will be described clearly and completely in combination with the drawings in the embodiments of the present application. Obviously, the described embodiments are some embodiments of the present application, but not all the embodiments. Based on the embodiments in the present application, all the other embodiments obtained by those skilled in the art without creative labor are within the protection scope of the present application.

[0070] Figure 1This is a schematic diagram of the start-up curve of an unmanned aircraft engine according to an embodiment of the present invention, such as... Figure 1 As shown, the horizontal axis (time) represents time, the vertical axis (ng) represents the compressor rotor speed, and numbers 1-4 represent start-up curves under different environments. The slope of the curve represents the compressor acceleration. The start-up process of a traditional unmanned aero-engine includes three stages:

[0071] (1) Start the first stage: Figure 1 The black line segment indicates that no oil is supplied during this stage, and the compressor is driven by the starter. The acceleration is almost the same in different environments.

[0072] (2) Start the second phase: the interval from the end of the first phase to 40%, corresponding to Figure 1 The red line segment in the diagram. 40% is typically the speed at which the turbine's torque and engine drag torque first reach equilibrium, which can be represented by n. bal This indicates that due to significant variations in starter motor performance and fuel line filling, a fuel supply pattern controlled by a given fuel flow rate is used. Using a fuel supply pattern controlled by a given acceleration could easily lead to overheating or suspension issues.

[0073] (3) Start the third stage: The condition for a normal transition from the second stage to the third stage is that ng reaches a specified value. Figure 1 For example, when ng reaches 40%, the fuel supply pattern changes from given fuel flow control to given acceleration control, corresponding to... Figure 1 The blue line segment in the image.

[0074] Figure 1 The No. 1 starting curve in the figure represents engine starting at normal temperature, with similar acceleration in the second and second stages of starting. However, with changes in the atmospheric environment, especially in harsh environments such as extreme cold and high altitudes, the drawback of the fuel supply pattern with given fuel flow control having poor environmental adaptability gradually becomes apparent. As shown in the figure, the acceleration of starting curves 1-4 gradually decreases in the second stage of starting, resulting in a prolonged starting time even though the engine can enter the third stage of starting. During the starting process, a starting suspension protection logic is set. When suspension occurs, this protection logic is triggered, which will enter the shutdown state control and control the engine to stop to protect the engine. Assume that the starting suspension protection logic has two triggering conditions: Condition 1: ng < 40% after ng enters the starting state for more than 35 seconds; Condition 2: ng < 75% after ng enters the starting state for more than 65 seconds. Here, 75% is the idle speed on the ground, which can be represented by n. idl This indicates that condition 2 is also a marker for successful startup. If ng reaches 75% within 65 seconds of entering the startup state, the startup is considered successful. The startup suspension protection logic is triggered when any of the above triggering conditions are met. Figure 1As shown in start-up curve #4, if ng still does not reach 40% after 35 seconds of start-up, condition 1 is triggered, thus triggering the start-up suspension protection logic. Even if the startup can enter the third stage, condition 2 will still be triggered due to the extended start-up time, thus triggering the start-up suspension protection logic.

[0075] Therefore, it is evident that in harsh environments such as extreme cold and high altitudes, using traditional fuel supply control methods will trigger the starting suspension protection logic, leading to starting failure. Thus, this embodiment of the invention considers that the fuel supply pattern used in the third stage of starting is more adaptable to environmental changes. By acquiring parameters and performing multi-level judgments to predict the starting trend, it determines the timing for transitioning from the second stage to the third stage of starting ahead of schedule. This achieves timely and effective switching of the fuel supply pattern, avoids triggering suspension protection, and improves the engine starting success rate.

[0076] According to an embodiment of the present invention, a method for controlling the starting fuel supply pattern of an unmanned aircraft engine is provided. It should be noted that the steps shown in the flowchart in the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions. Furthermore, although a logical order is shown in the flowchart, in some cases, the steps shown or described may be executed in a different order than that shown here.

[0077] This embodiment provides a method for controlling the start-up fuel supply pattern of an unmanned aerial vehicle (UAV) engine, which can be used in the numerical control system of an UAV engine. Figure 2 This is a flowchart of a starting fuel supply control method for an unmanned aircraft engine according to an embodiment of the present invention, as shown below. Figure 2 As shown, the process includes the following steps:

[0078] Step S201: Obtain the rotational speed and acceleration at the target time and the historical time respectively, and determine whether the first switching condition is met. Both the target time and the historical time are in the second stage of the start-up of the unmanned aero-engine. The second stage of start-up means that the compressor rotor speed of the unmanned aero-engine is in the first preset range.

[0079] Specifically, the stage where the compressor rotor speed is within the first preset range (e.g., 15% to 40%), that is... Figure 1 The red line segment represents the second stage of starting, employing a fuel supply pattern controlled by a given fuel flow rate. Because this fuel supply pattern has poor environmental adaptability and is prone to triggering the starting suspension protection logic, it is necessary to identify the starting suspension trend in advance during this stage. Therefore, both the target time and the historical time must be within this stage. The engine speed and acceleration at the target time and the historical time are obtained respectively to determine whether the first switching condition is met, thus achieving early identification of starting anomalies from the perspective of engine speed trend.

[0080] Step S202, when the first switching condition is met, the power turbine inlet temperature at the target time and the historical time is obtained respectively, and it is judged whether the second switching condition is met.

[0081] Specifically, when the first switching condition is met, it indicates that there is a suspension trend in the compressor rotor speed, and another typical feature of the suspension in the second stage of starting is that the power turbine inlet temperature Tt45 rises slowly. Normally, Tt45 rises steadily with the fuel combustion process, and the acceleration is basically consistent; but when there is a risk of starting suspension, the Tt45 rising rate will slow down significantly. At the same time, since the fuel supply law of the third stage of starting adopts given acceleration control, the fuel supply flow will increase significantly, in order to avoid Tt45 exceeding the safety threshold due to the sudden increase of fuel quantity, resulting in over-temperature shutdown, it is necessary to ensure that Tt45 is at a low level before switching to the third stage of starting. Therefore, the power turbine inlet temperature at the target time and the historical time is obtained respectively, and it is judged whether the second switching condition is met, and the abnormal trend of starting is further verified from the trend of Tt45.

[0082] Step S203, when the second switching condition is met, the fuel given quantity and the fuel feedback quantity are obtained, and it is judged whether the third switching condition is met.

[0083] Specifically, when the second switching condition is met, it indicates that the engine has shown a starting suspension trend in terms of speed and temperature, but the cause of the suspension is not only extreme environment, but also abnormal fuel system (such as a large amount of fuel leakage). If there is fuel leakage, it will directly destroy the effectiveness of the fuel supply law, resulting in that the actual fuel quantity entering the combustion chamber does not match the control command, and at this time, switching the fuel supply law may exacerbate the risk of failure. Therefore, the fuel given quantity wf and the fuel feedback quantity wfdem are obtained, and it is judged whether the third switching condition is met, and further verification is made from the trend of fuel flow.

[0084] Step S204, when the third switching condition is met, the first time consumption of the first stage of starting is obtained, the second time consumption and the third time consumption are determined, and based on the first time consumption, the second time consumption and the third time consumption, it is judged whether the fourth switching condition is met, and the first stage of starting represents the stage in which the compressor rotor speed of the aviation unmanned engine is located in the second preset interval.

[0085] Specifically, when the third switching condition is met, it indicates that the fuel system is working normally, at this time, it is necessary to further verify from the time dimension whether the starting suspension protection logic is triggered. More specifically, the numerical control system can automatically count the first time consumption of the first stage of starting, which is the stage in which ng is located in the second preset interval (such as 0-15%), that is, the time spent for ng to rise from 0 to 15%. At the same time, the second time consumption and the third time consumption are determined, and it is judged whether the fourth switching condition is met based on the above three times.

[0086] Step S205, when the fourth switching condition is met, determine the fourth time consumption of the third stage, and judge whether the fifth switching condition is met based on the first time consumption, the second time consumption and the fourth time consumption, when the fifth switching condition is met, control the aviation unmanned engine to switch from the second starting stage to the third starting stage in advance, and execute the oil supply rule of the third starting stage.

[0087] Specifically, from the trigger condition of the starting suspension protection logic, it can be seen that meeting the fourth switching condition only indicates that condition 1 will not be triggered, and it is also necessary to judge whether condition 2 is triggered according to the fifth switching condition to evaluate whether the starting can be successful. When it is evaluated that the starting can be successful, the given acceleration control oil supply rule of the third starting stage is executed in advance by switching from the second starting stage to the third starting stage, so that the engine can be successfully started under any environment.

[0088] The application realizes early identification of starting abnormality from the trend of rotation speed by continuously monitoring the rotation speed and acceleration change of the second starting stage, and further verifies the starting abnormality trend by combining the trend of power turbine inlet temperature when the rotation speed has a suspension trend. When the engine has shown the starting suspension trend from the rotation speed and temperature levels, the starting suspension caused by non-environmental factors such as fuel leakage is excluded through the fuel given amount and feedback amount, so as to ensure that the subsequent oil supply adjustment is based on normal fuel supply. When there is no significant leakage in the fuel system, it is verified from the time angle to ensure that the starting suspension protection logic will not be triggered when switching to the oil supply rule of the third starting stage in advance, thereby improving the engine starting success rate. Through multi-level dynamic judgment, the starting suspension trend is accurately identified, the time when the second starting stage switches to the third starting stage is determined, the oil supply rule of the given acceleration control is switched to in advance in the harsh environment such as extreme cold and high altitude, the starting suspension protection logic is avoided, the problem of poor adaptability of the traditional given fuel flow control is solved, the oil supply rule is switched in time and effectively, and the engine starting success rate is improved.

[0089] An aviation unmanned engine starting oil supply rule control method is provided in the embodiment, which can be used in the numerical control system of the aviation unmanned engine described above, and the method specifically includes the following steps:

[0090] Step S301, the rotation speed and acceleration at the target time and the historical time are obtained respectively, and it is judged whether the first switching condition is met, the target time and the historical time are both located in the second starting stage of the aviation unmanned engine, the second starting stage represents the stage that the compressor rotor rotation speed of the aviation unmanned engine is located in the first preset interval, the historical time includes the first time and the second time, the first time is the last time of the target time, and the second time is the last time of the first time.

[0091] Specifically, the above step S301 includes:

[0092] In step S3011, the first rotational speed and the first acceleration at the target moment, the second rotational speed and the second acceleration at the first moment, and the third rotational speed and the third acceleration at the second moment are obtained.

[0093] Specifically, assuming that the target moment is a, the first moment is a-1, and the second moment is a-2, the target moment is at least the third sampling moment after entering the second starting stage. By obtaining the accelerations at three consecutive moments, as the basis for judging whether the acceleration is in a continuous downward trend, it is ensured that a sufficient time span is covered to identify a trend change rather than a transient fluctuation. Optionally, the moments can be selected according to actual conditions, but it is necessary to ensure that these moments are consecutive.

[0094] In step S3012, when the third acceleration, the second acceleration, and the first acceleration are sequentially increased or the absolute value of the difference between the first rotational speed and the third rotational speed is less than a first threshold value, it is determined that the first condition is met.

[0095] Specifically, assuming that the sampling period is t, which is generally 0.024s-0.1s, the first threshold value can be 0.2%xt. Optionally, 0.2% is only an example, which can be adjusted according to actual needs. When the third acceleration> the second acceleration> the first acceleration, i.e. a-2 >ngdot2 a-1 >ngdot2 a , it indicates that the acceleration is in a downward trend, reflecting that the rotational speed rising power is gradually weakened, which is a typical dynamic characteristic of the starting suspension. When the absolute value of the difference between the first rotational speed and the third rotational speed is less than the first threshold value, i.e. a -ng a-2 |<0.2%×t, it indicates that the rotational speed change is very small and almost stagnant, which reflects that the starting process is blocked and there may be a suspension risk. If any of the above conditions is met, it is considered that the first condition is met, i.e. there may be a suspension trend at this time. The suspension in extreme environment may be manifested as progressive acceleration weakness or sudden rotational speed stagnation, and double judgment is performed to improve the judgment accuracy.

[0096] In step S3013, the initial acceleration of the second starting stage is obtained, the acceleration difference between the initial acceleration and the first acceleration is calculated, and the acceleration ratio of the acceleration difference to the initial acceleration is calculated.

[0097] Specifically, the initial acceleration ngdot21 just entering the second starting stage is obtained, the acceleration difference between the initial acceleration and the first acceleration at the target moment is calculated, and the ratio of the acceleration difference to the initial acceleration is determined as the acceleration ratio, i.e. to quantify the attenuation ratio of the current acceleration compared with the initial state.

[0098] Step S3014, when the acceleration ratio is not less than the second threshold value, it is determined that the second condition is met.

[0099] Specifically, assuming that the second threshold value is 50%, which can be adjusted according to actual conditions, and generally takes a value of 40% to 70%. When the acceleration ratio is not less than the second threshold value, it indicates that the acceleration has decreased significantly at this time compared to just entering the second stage of starting, and the starting power is seriously insufficient, and the suspension risk is extremely high.

[0100] Step S3015, when the first condition and the second condition are met, it is determined that the first switching condition is met.

[0101] Specifically, if the first condition and the second condition are met at the same time, it is determined that the first switching condition is met. This indicates that the engine not only has a trend of acceleration decline or speed stagnation, but also the acceleration attenuation has reached a significant degree, and the starting suspension risk is high. It provides a reliable basis for whether to switch to the third stage of starting in advance, that is, to switch the fuel supply rule in advance.

[0102] Step S3016, when the first condition and / or the second condition is not met, it is determined that the first switching condition is not met.

[0103] Specifically, if the first condition and / or the second condition is not met, it is determined that the first switching condition is not met. This indicates that the engine speed rises normally, and there is no obvious starting failure risk. At this time, there is no need for early intervention, and the traditional fuel flow control oil supply rule is continued to be executed until the speed reaches n bal and naturally enters the third stage of starting.

[0104] Step S302, when the first switching condition is met, the power turbine inlet temperature at the target time and the historical time is obtained, and it is determined whether the second switching condition is met.

[0105] Specifically, the above step S302 includes:

[0106] Step S3021, when the first switching condition is met, the first power turbine inlet temperature at the target time, the second power turbine inlet temperature at the first time, and the third power turbine inlet temperature at the second time are obtained, and the first temperature acceleration at the target time, the second temperature acceleration at the first time, and the third temperature acceleration at the second time are determined.

[0107] Specifically, when the first switching condition is met, there is a suspension trend at the speed level at this time. Since the power turbine inlet temperature is a key indicator reflecting the combustion efficiency, its change trend is related to the speed suspension, and therefore it can assist in verifying the starting abnormality. The first power turbine inlet temperature Tt45 a at the target time a, the second power turbine inlet temperature Tt45a-1 , the third power turbine inlet temperature Tt45 at the second time a-2 a-2 . Each time, according to the Tt45 of the previous time, the temperature acceleration Tt45dot corresponding to each time is determined to quantify the change trend of Tt45.

[0108] Step S3022, the starting maximum allowable temperature of the power turbine is obtained, and the third threshold is determined based on the starting maximum allowable temperature.

[0109] Specifically, assuming that the starting maximum allowable temperature of the power turbine is Tt45 max , the result of Tt45 max -100℃ is taken as the third threshold. Optionally, the third threshold can be adjusted according to actual conditions, and generally not higher than Tt45 max -80℃.

[0110] Step S3023, when the third temperature acceleration, the second temperature acceleration and the first temperature acceleration increase in turn, it is determined that the third condition is met.

[0111] Specifically, when the third temperature acceleration > the second temperature acceleration > the first temperature acceleration, that is, Tt45dot2 a-2 > Tt45dot2 a-1 > Tt45dot2 a , it indicates that Tt45 rises very slowly, reflecting the decline of combustion efficiency, which is a typical feature of starting suspension in temperature dimension, and it is determined that the third condition is met.

[0112] Step S3024, when the first power turbine inlet temperature is less than the third threshold, it is determined that the fourth condition is met.

[0113] Specifically, if the current Tt45 is less than the third threshold, it is determined that the fourth condition is met, and it is ensured that when the third stage of starting is turned into in advance, Tt45 is in a safe range, so as to avoid the sudden increase of fuel flow when turning into the third stage, which leads to Tt45 over-temperature parking.

[0114] Step S3025, when the third condition and the fourth condition are met, it is determined that the second switching condition is met.

[0115] Specifically, if the third condition and the fourth condition are met at the same time, it is determined that the second switching condition is met, which further verifies the starting abnormal trend from the temperature dimension, and reduces the risk of misjudgment.

[0116] Step S3026, when the third condition and / or the fourth condition is not met, it is determined that the second switching condition is not met.

[0117] Specifically, if the third condition is not met, it indicates that the temperature acceleration does not show a decreasing trend, which means that the combustion state is normal; if the fourth condition is not met, there is an over-temperature risk in the early switching of the fuel supply law, and both cases are not suitable for switching to the third stage of the starting fuel supply law. At this time, return to step S301 to continue monitoring the next sampling time of the target time, realize dynamic tracking of the starting process, ensure timely intervention when there is a starting risk, and improve the engine starting success rate.

[0118] Step S303, when the second switching condition is met, the fuel given amount and the fuel feedback amount are obtained, and it is judged whether the third switching condition is met.

[0119] Specifically, the above step S303 includes:

[0120] Step S3031, calculate the fuel difference between the fuel given amount and the fuel feedback amount, and calculate the absolute value of the ratio of the fuel difference to the fuel given amount.

[0121] Specifically, the fuel given amount wf refers to the predetermined fuel flow, and the fuel feedback amount wfdem refers to the actual fuel flow supplied by the fuel system to the engine. Under normal circumstances, the error between the two is very small, but when the fuel leaks, the predetermined fuel supply will leak at some point, resulting in a significant reduction in the fuel entering the engine, thereby causing the starting suspension or fire risk. Therefore, by obtaining and calculating the fuel difference between the two, and calculating the absolute value of the ratio of the fuel difference to the fuel given amount, that is, To quantify the deviation of the fuel system, it is judged from the fuel flow stability whether the starting suspension is caused by fuel leakage.

[0122] Step S3032, when the absolute value is not greater than the fourth threshold, it is determined that the third switching condition is met.

[0123] Specifically, assuming that the fourth threshold is 15%, if the absolute value is not greater than the fourth threshold, the fuel is normal and no fuel leakage occurs, and it is determined that the third switching condition is met.

[0124] Step S3033, when the absolute value is greater than the fourth threshold, it is determined that the third switching condition is not met.

[0125] Specifically, if the absolute value is greater than the fourth threshold, there is significant fuel leakage, and even if the third stage of starting is switched in advance to increase fuel supply, the actual fuel will be insufficient to improve the acceleration performance, and the leakage risk may be exacerbated, so it is determined that the third switching condition is not met. At this time, return to step S301 to continue monitoring the next sampling time of the target time. By judging the fuel flow, invalid intervention is avoided when the fuel system is abnormal, the engine working safety is ensured, and the potential risk is reduced.

[0126] Step S304, when the third switching condition is met, a first time consumption of starting the first stage is obtained, a second time consumption and a third time consumption are determined, and whether the fourth switching condition is met is judged based on the first time consumption, the second time consumption and the third time consumption, and the starting the first stage means that the compressor rotor speed of the aviation unmanned engine is in the second preset interval.

[0127] Specifically, the step S304 includes:

[0128] Step S3041, the balance speed and the starting time of the starting the second stage are obtained.

[0129] Specifically, when the third switching condition is met, there is no significant leakage of the fuel system, and the feasibility of switching the oil supply rule in advance needs to be verified from the time dimension, and the core is to judge whether the starting suspension protection logic will be triggered. More specifically, the balance speed is obtained, that is, the speed at which the torque generated by the turbine and the engine resistance torque are first balanced, which is the judgment threshold for the traditional starting the second stage to enter the starting the third stage, which can be represented by n bal , and usually takes the value of 40%. At the same time, the time when the starting the second stage is just entered, that is, the starting time, is obtained.

[0130] Step S3042, the time difference between the target time and the starting time is determined as the second time consumption.

[0131] Specifically, the second time consumption t2 reflects the time consumed in the starting the second stage, and is a key parameter for evaluating whether the remaining time is sufficient.

[0132] Step S3043, the first speed difference between the balance speed and the first speed is calculated, and the ratio between the first speed difference and the first acceleration is determined as the third time consumption.

[0133] Specifically, the third time consumption is determined by the following formula (1), which represents the estimated remaining time required for the current acceleration to continue to accelerate to n bal , which is used to pre-judge the remaining time for completing the starting the second stage in the current state, and if the time is too long, the starting protection may be triggered, and the total time consumption needs to be shortened by switching the oil supply rule in advance.

[0134]

[0135] Wherein, t3 represents the third time consumption; n bal represents the balance speed; ng a represents the first speed of the target time a; ngdot2 a represents the first acceleration of the target time a.

[0136] Step S3044, the first time threshold is determined based on the starting suspension protection logic, and the fifth threshold is determined based on the first time threshold.

[0137] Specifically, the condition 1 for starting the suspension protection logic is that ng < n after more than 35s since ng enters the starting state bal where 35s is the first time threshold T1. The fifth threshold is 0.7*T1, which is a time margin parameter, and reserves a safety margin for early switching. Optionally, the first time threshold and 0.7 are only examples, and can be adjusted according to actual conditions, and the latter is generally selected within the interval of 0.6-0.8.

[0138] Step S3045, when the sum of the first time consumption, the second time consumption and the third time consumption is less than the fifth threshold, it is determined that the fourth switching condition is met.

[0139] Specifically, when the sum of the first time consumption, the second time consumption and the third time consumption is less than the fifth threshold, i.e. t1+t2+t3<0.7*T1, it represents the total estimated time for completing the second stage of starting according to the current state, and if it is less than the fifth threshold, it is determined that the fourth switching condition is met, which means that the remaining time is sufficient, and early switching can utilize the higher acceleration of the third stage of starting to shorten the total time consumption, avoid triggering the condition 1, and improve the starting success rate of the engine.

[0140] Step S3046, when the sum of the first time consumption, the second time consumption and the third time consumption is not less than the first time threshold, it is determined that the fourth switching condition is not met.

[0141] Specifically, if the sum of the above three times is not less than the first time threshold, i.e. t1+t2+t3≥T1, at this time, even if the third stage is switched in advance, the total time will exceed T1 to trigger the starting suspension protection logic 1, and early switching loses practical significance, so the engine continues to execute the fuel supply law controlled by the traditional given fuel flow until the speed reaches n bal and then naturally enters the third stage of starting.

[0142] Step S305, when the fourth switching condition is met, the fourth time consumption of the third stage of starting is determined, and based on the first time consumption, the second time consumption and the fourth time consumption, it is judged whether the fifth switching condition is met, and when the fifth switching condition is met, the aviation unmanned engine is controlled to switch from the second stage of starting to the third stage of starting in advance, and the fuel supply law of the third stage of starting is executed.

[0143] Specifically, the above step S305 includes:

[0144] Step S3051, the ground idle speed and the preset acceleration of the third stage of starting are obtained.

[0145] Specifically, the step S304 has verified the feasibility of the early switching of the fuel supply law by starting the condition 1 of the suspension protection logic, and the step S305 needs to further verify the possibility of the success of the starting based on the condition 2 of the protection logic. More specifically, the ground idle speed is obtained, which is the core parameter for evaluating whether the starting is successful, and can be expressed as n idl , and generally takes the value of 75%. At the same time, the fuel supply law of the third starting stage is given acceleration control, and the preset acceleration ngdot3 thereof is obtained.

[0146] The step S3052 calculates the second speed difference between the ground idle speed and the first speed, and the ratio between the second speed difference and the preset acceleration.

[0147] Specifically, the difference between the ground idle speed and the first speed at the target time is calculated, and the ratio between the difference and the preset acceleration of the third starting stage is calculated, that is, reflects the basic time for accelerating from the current speed to n idl according to the preset acceleration of the third starting stage, and is used for evaluating the time consumption of the third starting stage.

[0148] The step S3053 determines the product of the ratio and the sixth threshold value as the fourth time consumption.

[0149] Specifically, the sixth threshold value is 1.1, which represents a time margin coefficient and is used for compensating the transition time from the acceleration of the second starting stage to the preset acceleration of the third starting stage. Optionally, the sixth threshold value can be adjusted according to actual needs, and generally takes the value of 1.05-1.2. The product of the above ratio and the sixth threshold value is determined as the fourth time consumption t4, so that the time consumption estimation is more in line with the actual acceleration process, and the accuracy of the time judgment is improved.

[0150] The step S3054 determines the second time threshold value based on the starting suspension protection logic, and determines the seventh threshold value based on the second time threshold value.

[0151] Specifically, the condition 2 of the starting suspension protection logic is ng < n idl , wherein 65s is the second time threshold value T2. The seventh threshold value is 0.9*T2, which reserves a safety buffer for responding to sudden delays for the total time consumption. Optionally, the second time threshold value and 0.9 are only examples, and can be adjusted according to actual conditions.

[0152] The step S3055 determines that the fifth switching condition is met when the sum of the first time consumption, the second time consumption and the fourth time consumption is less than the seventh threshold value.

[0153] Specifically, assuming that the starting third stage is switched in advance from the target time a in the starting second stage, the engine increases the fuel supply amount, and thus the second time consumption obtained in step S3042 is the time consumed in the starting second stage. When the sum of the first time consumption, the second time consumption, and the fourth time consumption is less than the seventh threshold value, i.e., t1+t2+t4<0.9*T2, it represents that the total estimated time for completing the starting is too long after the switching of the fuel supply law, and if it is less than the seventh threshold value, it is determined that the fifth switching condition is satisfied, which indicates that there is sufficient time to reach n idl , and the starting success can be ensured.

[0154] In step S3056, when the sum of the first time consumption, the second time consumption, and the fourth time consumption is not less than the seventh threshold value, it is determined that the fifth switching condition is not satisfied.

[0155] Specifically, if the sum of the above three time consumptions is not less than the seventh threshold value, it is determined that the fifth switching condition is not satisfied, and at this time, even if the starting third stage is switched in advance to the fuel supply law of the given fuel flow control, the total time may be close to or exceed T2, and finally the condition 2 is triggered, and the starting fails. Therefore, the engine continues to execute the fuel supply law of the conventional given fuel flow control until the speed reaches n bal , and then naturally enters the starting third stage.

[0156] In some optional embodiments, when the fifth switching condition is satisfied, the starting third stage is switched in advance from the target time a in the starting second stage, and the fuel supply law of the given acceleration control with better environmental adaptability is switched to, so as to improve the starting success rate of the engine in various environments.

[0157] In some optional embodiments, Figure 3 is another starting curve diagram of an aviation unmanned engine according to an embodiment of the application, as Figure 3 shown, assuming that the time a satisfies all the above switching conditions, the starting third stage can be switched in advance at the time a, and the acceleration according to ngdot3 is performed, so as to avoid triggering the starting suspension protection logic, and finally the starting succeeds. Assuming that the time a1 satisfies the first switching condition-third switching condition, but does not satisfy the fourth switching condition, i.e., it is predicted that the starting third stage is switched in advance at the time a1, and the starting suspension protection logic 1 is still triggered, resulting in the failure of the starting.

[0158] The application realizes early identification of starting abnormality from the speed trend level by continuously monitoring the speed and acceleration change of the starting second stage, and further verifies the starting abnormality trend when the speed has a suspension trend in combination with the trend of the power turbine inlet temperature. When the engine has shown the starting suspension trend from the speed and temperature levels, the starting suspension caused by non-environmental factors such as fuel leakage is excluded through the fuel given amount and feedback amount, and the subsequent fuel supply adjustment is ensured to be based on the normal fuel supply. When there is no significant leakage in the fuel system, the time is verified to ensure that the starting suspension protection logic is not triggered when the fuel supply law of the starting third stage is switched to in advance, and the engine starting success rate is improved. Through multi-stage dynamic judgment, the starting suspension trend is accurately identified, the time when the starting second stage is switched to the starting third stage is determined, the fuel supply law of the given acceleration control which is more adaptive is switched to in advance in the harsh environment such as extreme cold and high altitude, the starting suspension protection logic is avoided to be triggered, the problem of poor adaptability of the traditional given fuel flow control is solved, the timely and effective switching of the fuel supply law is realized, and the engine starting success rate is improved.

[0159] In the embodiment, an aviation unmanned engine starting fuel supply law control device is also provided, which is used to realize the above-mentioned embodiments and preferred embodiments, and will not be described again. As used below, the term "module" can be a combination of software and / or hardware that realizes a predetermined function. Although the device described in the following embodiments is preferably realized in software, hardware, or a combination of software and hardware is also possible and is conceived.

[0160] The embodiment provides an aviation unmanned engine starting fuel supply law control device, as shown in the accompanying drawings, comprising: Figure 4

[0161] The first judgment module 401 is used to acquire the speed and acceleration of the target time and the historical time respectively, and judge whether the first switching condition is met, the target time and the historical time are both located in the starting second stage of the aviation unmanned engine, and the starting second stage represents the stage in which the compressor rotor speed of the aviation unmanned engine is located in the first preset interval.

[0162] The second judgment module 402 is used to acquire the power turbine inlet temperature of the target time and the historical time respectively when the first switching condition is met, and judge whether the second switching condition is met.

[0163] The third judgment module 403 is used to acquire the fuel given amount and the fuel feedback amount when the second switching condition is met, and judge whether the third switching condition is met.

[0164] ​The fourth determining module 404 is configured to, when the third switching condition is met, acquire a first time consumption of starting the first stage, determine a second time consumption and a third time consumption, and determine whether a fourth switching condition is met based on the first time consumption, the second time consumption and the third time consumption. The starting the first stage refers to a stage in which the compressor rotor speed of the aerial unmanned engine is located in the second preset interval.

[0165] The control module 405 is configured to, when the fourth switching condition is met, determine a fourth time consumption of starting the third stage, and determine whether a fifth switching condition is met based on the first time consumption, the second time consumption and the fourth time consumption. When the fifth switching condition is met, the aerial unmanned engine is controlled to switch from the starting the second stage to the starting the third stage in advance, and the fuel supply rule of the starting the third stage is executed.

[0166] In some optional embodiments, the historical time points include a first time point and a second time point. The first time point is a previous time point of the target time point, and the second time point is a previous time point of the first time point.

[0167] The first determining module 401 includes:

[0168] The first obtaining unit is configured to obtain a first speed and a first acceleration at the target time point, a second speed and a second acceleration at the first time point, and a third speed and a third acceleration at the second time point.

[0169] The first determining unit is configured to determine that the first condition is met when the third acceleration, the second acceleration and the first acceleration increase in sequence or an absolute value of a difference between the first speed and the third speed is less than a first threshold.

[0170] The first calculating unit is configured to acquire an initial acceleration of the starting the second stage, calculate an acceleration difference between the initial acceleration and the first acceleration, and calculate an acceleration ratio of the acceleration difference and the initial acceleration.

[0171] The second determining unit is configured to determine that the second condition is met when the acceleration ratio is not less than a second threshold.

[0172] The first condition determining unit is configured to determine that the first switching condition is met when the first condition and the second condition are met.

[0173] The second condition determining unit is configured to determine that the first switching condition is not met when the first condition and / or the second condition is not met.

[0174] In some optional embodiments, the second determining module 402 includes:

[0175] The second obtaining unit is configured to obtain the first power turbine inlet temperature at the target moment, the second power turbine inlet temperature at the first moment, and the third power turbine inlet temperature at the second moment, and determine the first temperature acceleration at the target moment, the second temperature acceleration at the first moment, and the third temperature acceleration at the second moment when the first switching condition is met.

[0176] The third obtaining unit is configured to obtain the start-up maximum allowable temperature of the power turbine, and determine the third threshold value based on the start-up maximum allowable temperature.

[0177] The third determining unit is configured to determine that the third condition is met when the third temperature acceleration, the second temperature acceleration, and the first temperature acceleration increase in sequence.

[0178] The fourth determining unit is configured to determine that the fourth condition is met when the first power turbine inlet temperature is less than the third threshold value.

[0179] The third condition determining unit is configured to determine that the second switching condition is met when the third condition and the fourth condition are met.

[0180] The fourth condition determining unit is configured to determine that the second switching condition is not met when the third condition and / or the fourth condition is not met.

[0181] In some optional embodiments, the third judging module 403 comprises:

[0182] The second calculating unit is configured to calculate a fuel difference value between the fuel given amount and the fuel feedback amount, and calculate an absolute value of a ratio of the fuel difference value to the fuel given amount.

[0183] The fifth condition determining unit is configured to determine that the third switching condition is met when the absolute value is not greater than the fourth threshold value.

[0184] The sixth condition determining unit is configured to determine that the third switching condition is not met when the absolute value is greater than the fourth threshold value.

[0185] In some optional embodiments, the fourth judging module 404 comprises:

[0186] The fourth obtaining unit is configured to obtain the balance rotating speed and the start moment of the start-up second stage.

[0187] The fifth determining unit is configured to determine a time difference between the target moment and the start moment as the second time consumption.

[0188] The third calculating unit is configured to calculate a first rotating speed difference value between the balance rotating speed and the first rotating speed, and determine a ratio between the first rotating speed difference value and the first acceleration as the third time consumption.

[0189] In some optional embodiments, the fourth judging module 404 comprises:

[0190] The sixth determining unit is configured to determine the first time threshold based on the start suspension protection logic, and determine the fifth threshold based on the first time threshold.

[0191] The seventh condition determining unit is configured to determine that the fourth switching condition is met when the sum of the first time consumption, the second time consumption and the third time consumption is less than the fifth threshold.

[0192] The eighth condition determining unit is configured to determine that the fourth switching condition is not met when the sum of the first time consumption, the second time consumption and the third time consumption is not less than the first time threshold.

[0193] In some optional embodiments, the control module 405 comprises:

[0194] The fifth obtaining unit is configured to obtain the ground idle speed and a preset acceleration of the start third stage.

[0195] The fourth calculating unit is configured to calculate a second speed difference between the ground idle speed and the first speed, and a ratio between the second speed difference and the preset acceleration.

[0196] The seventh determining unit is configured to determine a product of the ratio and the sixth threshold as the fourth time consumption.

[0197] In some optional embodiments, the control module 405 comprises:

[0198] The eighth determining unit is configured to determine the second time threshold based on the start suspension protection logic, and determine the seventh threshold based on the second time threshold.

[0199] The ninth condition determining unit is configured to determine that the fifth switching condition is met when the sum of the first time consumption, the second time consumption and the fourth time consumption is less than the seventh threshold.

[0200] The tenth condition determining unit is configured to determine that the fifth switching condition is not met when the sum of the first time consumption, the second time consumption and the fourth time consumption is not less than the seventh threshold.

[0201] Further function descriptions of the above-mentioned modules and units are the same as those of the corresponding embodiments, and will not be described here.

[0202] The start oil supply rule control device of the aviation unmanned engine in the embodiment is presented in the form of a functional unit. The unit herein refers to an ASIC (Application Specific Integrated Circuit, special-purpose integrated circuit) circuit, a processor and a memory executing one or more software or fixed programs, and / or other devices capable of providing the above functions.

[0203] The embodiment of the present application further provides a computer device having the aboveFigure 4 The starting oil supply law control device of the aerial unmanned engine.

[0204] Referring to Figure 5 Figure 5 is a structural schematic diagram of a computer device provided by an optional embodiment of the present application. As shown in Figure 5 , the computer device includes one or more processors 10, a memory 20, and interfaces for connecting various components, including high-speed interfaces and low-speed interfaces. Various components are communicatively connected to each other by using different buses, and can be installed on a common mainboard or in other manners as needed. The processor can process instructions executed within the computer device, including instructions stored in the memory or graphics information of a GUI stored in the memory for displaying on an external input / output device (such as a display device coupled to the interface). In some optional embodiments, multiple processors and / or multiple buses can be used with multiple memories and multiple memory, if needed. Similarly, multiple computer devices can be connected, each providing part of the necessary operations (for example, as a server array, a group of blade servers, or a multi-processor system). Figure 5 The processor 10 is taken as an example in the foregoing embodiment.

[0205] The processor 10 can be a central processor, a network processor, or a combination thereof. The processor 10 can further include a hardware chip. The hardware chip can be an application specific integrated circuit, a programmable logic device, or a combination thereof. The programmable logic device can be a complex programmable logic device, a field programmable logic gate array, a generic array logic, or any combination thereof.

[0206] The memory 20 stores instructions executable by the at least one processor 10, so that the at least one processor 10 executes the method shown in the foregoing embodiment.

[0207] The memory 20 can include a program storage area and a data storage area. The program storage area can store an operating system and application programs required by at least one function; and the data storage area can store data created according to the use of the computer device, and the like. In addition, the memory 20 can include a high-speed random access memory, and can further include a non-transitory memory, such as at least one magnetic disk storage device, a flash memory device, or other non-transitory solid-state memory device. In some optional embodiments, the memory 20 can optionally include a memory remotely arranged with respect to the processor 10, and these remote memories can be connected to the computer device by a network. Examples of the network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and a combination thereof.

[0208] ​The memory 20 can include a volatile memory, such as a random access memory, and / or a non-volatile memory, such as a flash memory, a hard disk, or a solid state disk. The memory 20 can also include a combination of the above-mentioned types of memories.

[0209] The computer device also includes a communication interface 30 for the computer device to communicate with other devices or communication networks.

[0210] The embodiments of the present application also provide a computer readable storage medium, and the method according to the embodiments of the present application can be implemented in hardware, firmware, or recorded in a storage medium, or stored in a remote storage medium or a non-transitory machine readable storage medium and downloaded to a local storage medium through network, so that the method described herein can be processed by such software on a storage medium using a general purpose computer, a special purpose processor, or programmable or special purpose hardware. The storage medium can be a disk, an optical disk, a read-only memory, a random access memory, a flash memory, a hard disk, or a solid state disk, etc. Further, the storage medium can also include a combination of the above-mentioned types of memories. It can be understood that the computer, the processor, the microprocessor controller, or the programmable hardware includes a storage component that can store or receive software or computer code, when the software or computer code is accessed and executed by the computer, the processor, or the hardware, the method shown in the above embodiments is implemented.

[0211] Part of the present application can be applied as a computer program product, for example, computer program instructions, when executed by a computer, through the operation of the computer, the method and / or technical solutions according to the present application can be invoked or provided. Those skilled in the art should understand that the form of computer program instructions in a computer readable medium includes but is not limited to source files, executable files, installation package files, etc. Correspondingly, the way of computer program instructions executed by computer includes but is not limited to: the computer directly executes the instructions, or the computer compiles the instructions and then executes the corresponding compiled program, or the computer reads and executes the instructions, or the computer reads and installs the instructions and then executes the corresponding installed program. Here, the computer readable medium can be any available computer readable storage medium or communication medium accessible to the computer.

[0212] Although the embodiments of the present application are described in conjunction with the accompanying drawings, various modifications and changes can be made by those skilled in the art without departing from the spirit and scope of the present application, and such modifications and changes fall within the scope defined by the appended claims.

Claims

1. A method for controlling the fuel supply law for starting an aeronautical engine without a pilot, characterized in that, The method comprises: respectively acquiring the rotation speed and acceleration of the target moment and the historical moment, judging whether the first switching condition is met, the target moment and the historical moment are both located in the second starting stage of the aviation unmanned engine, the second starting stage represents the stage in which the compressor rotor speed of the aviation unmanned engine is located in the first preset interval; when the first switching condition is met, respectively acquiring the power turbine inlet temperature of the target moment and the historical moment, judging whether the second switching condition is met; when the second switching condition is met, acquiring the fuel given quantity and the fuel feedback quantity, judging whether the third switching condition is met; when the third switching condition is met, acquiring the first time consumption of the first starting stage, determining the second time consumption and the third time consumption, and judging whether the fourth switching condition is met based on the first time consumption, the second time consumption and the third time consumption, the first starting stage represents the stage in which the compressor rotor speed of the aviation unmanned engine is located in the second preset interval; when the fourth switching condition is met, determining the fourth time consumption of the third starting stage, and judging whether the fifth switching condition is met based on the first time consumption, the second time consumption and the fourth time consumption, when the fifth switching condition is met, the aviation unmanned engine is controlled to be transferred from the second starting stage to the third starting stage in advance, and the fuel supply rule of the third starting stage is executed.

2. The method of claim 1, wherein, The historical moment comprises a first moment and a second moment, the first moment is the last moment of the target moment, and the second moment is the last moment of the first moment; The method comprises: acquiring the first rotation speed and the first acceleration of the target moment, the second rotation speed and the second acceleration of the first moment, and the third rotation speed and the third acceleration of the second moment; when the third acceleration, the second acceleration and the first acceleration increase in turn or the absolute value of the difference between the first rotation speed and the third rotation speed is less than a first threshold value, it is determined that the first condition is met; acquiring the initial acceleration of the second starting stage, calculating the acceleration difference between the initial acceleration and the first acceleration, and calculating the acceleration ratio of the acceleration difference and the initial acceleration; when the acceleration ratio is not less than a second threshold value, it is determined that the second condition is met; when the first condition and the second condition are met, it is determined that the first switching condition is met; when the first condition and / or the second condition are not met, it is determined that the first switching condition is not met.

3. The method of claim 2, wherein, The method comprises: when the first switching condition is met, acquiring the first power turbine inlet temperature of the target moment, the second power turbine inlet temperature of the first moment, and the third power turbine inlet temperature of the second moment, and determining the first temperature acceleration of the target moment, the second temperature acceleration of the first moment, and the third temperature acceleration of the second moment; acquiring a start maximum allowable temperature of the power turbine, determining a third threshold value based on the start maximum allowable temperature; determining that a third condition is met when the third temperature acceleration, the second temperature acceleration and the first temperature acceleration are sequentially increased; determining that a fourth condition is met when the first power turbine inlet temperature is less than the third threshold value; determining that the second switching condition is met when the third condition and the fourth condition are met; determining that the second switching condition is not met when the third condition and / or the fourth condition are not met.

4. The method of claim 1, wherein, The determining whether the third switching condition is met comprises: calculating a fuel difference value between the fuel given amount and the fuel feedback amount, and calculating an absolute value of a ratio of the fuel difference value to the fuel given amount; determining that the third switching condition is met when the absolute value is not greater than a fourth threshold value; determining that the third switching condition is not met when the absolute value is greater than the fourth threshold value.

5. The method of claim 2, wherein, The determining the second time consumption and the third time consumption comprises: acquiring an equilibrium rotating speed and a start time of the start second stage; determining a time difference between the target time and the start time as the second time consumption; calculating a first rotating speed difference value between the equilibrium rotating speed and the first rotating speed, and determining a ratio between the first rotating speed difference value and the first acceleration as the third time consumption.

6. The method of claim 1, wherein, The determining whether the fourth switching condition is met based on the first time consumption, the second time consumption and the third time consumption comprises: determining a first time threshold value based on a start suspension protection logic, and determining a fifth threshold value based on the first time threshold value; determining that the fourth switching condition is met when a sum of the first time consumption, the second time consumption and the third time consumption is less than the fifth threshold value; determining that the fourth switching condition is not met when the sum of the first time consumption, the second time consumption and the third time consumption is not less than the first time threshold value.

7. The method of claim 2, wherein, The determining a fourth time consumption of the start third stage comprises: acquiring a ground idle rotating speed and a preset acceleration of the start third stage; calculating a second rotating speed difference value between the ground idle rotating speed and the first rotating speed, and a ratio between the second rotating speed difference value and the preset acceleration; determining a product of the ratio and a sixth threshold value as the fourth time consumption.

8. The method of claim 6, wherein, The determining whether the fifth switching condition is met based on the first time consumption, the second time consumption and the fourth time consumption comprises: determining a second time threshold value based on the start suspension protection logic, and determining a seventh threshold value based on the second time threshold value; determining that the fifth switching condition is met when a sum of the first time consumption, the second time consumption and the fourth time consumption is less than the seventh threshold value; determining that the fifth switching condition is not met when the sum of the first time consumption, the second time consumption and the fourth time consumption is not less than the seventh threshold value.

9. A control device for starting fuel supply law of an aviation unmanned engine, characterized by, The device comprises: The first judging module is configured to acquire the rotation speed and the acceleration at a target time and a historical time, and judge whether a first switching condition is met, wherein the target time and the historical time are both located in a second starting stage of the aerial unmanned engine, and the second starting stage represents a stage in which the rotation speed of the compressor rotor of the aerial unmanned engine is located in a first preset interval. The second judging module is configured to acquire the power turbine inlet temperature at the target time and the historical time when the first switching condition is met, and judge whether a second switching condition is met. The third judging module is configured to acquire the fuel given amount and the fuel feedback amount when the second switching condition is met, and judge whether a third switching condition is met. The fourth judging module is configured to acquire a first time consumption of a first starting stage when the third switching condition is met, determine a second time consumption and a third time consumption, and judge whether a fourth switching condition is met based on the first time consumption, the second time consumption and the third time consumption, wherein the first starting stage represents a stage in which the rotation speed of the compressor rotor of the aerial unmanned engine is located in a second preset interval. The control module is configured to determine a fourth time consumption of a third starting stage when the fourth switching condition is met, judge whether a fifth switching condition is met based on the first time consumption, the second time consumption and the fourth time consumption, and control the aerial unmanned engine to be transferred from the second starting stage to the third starting stage in advance when the fifth switching condition is met, and execute a fuel supply rule of the third starting stage.

10. A computer device, comprising: The memory and the processor are communicatively connected, the memory stores computer instructions, and the processor executes the computer instructions to perform the starting fuel supply rule control method of the aerial unmanned engine according to any one of claims 1 to 8. ​

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