Method and device for determining control parameters of aviation piston engine

Abstract

The invention provides a method and a device for determining control parameters of an aviation piston engine. The method comprises the following steps: acquiring fluted disc data of the aviation piston engine; performing transformation processing on the fluted disc data to obtain a spectrogram; determining frequency data according to the spectrogram; according to the frequency data, the rotating speed and the rotating speed change rate of the aviation piston engine are determined; and according to the rotating speed and the rotating speed change rate, rotating speed control parameters of the aviation piston engine are determined. According to the method, the fluted disc data of the aviation piston engine are obtained and converted to obtain the spectrogram, then the frequency data are determined, and the rotating speed and the rotating speed change rate of the aviation piston engine are determined according to the frequency data. The rotating speed control parameters of the aviation piston engine are determined according to the rotating speed and the rotating speed change rate of the aviation piston engine, the rotating speed of the engine can be calculated more accurately, and the control effect on the aviation piston engine can be improved.

Description

Technical Field

[0001] The invention relates to the technical field of engines, and also to a method and a device for determining control parameters of an aviation piston engine. Background Art

[0002] An aviation piston engine is a power device that relies on the reciprocating motion of the piston in the cylinder to complete the thermodynamic cycle of the gas working fluid and ultimately convert the chemical energy in the fuel into mechanical energy. There are two ways for the crankshaft of an aviation piston engine to drive the propeller: direct drive and speed reduction drive after a reducer. The difference from automotive piston engines is that in order to reduce weight, aircraft generally do not have a flywheel, and the flywheel plays an important role in stabilizing the engine speed. Therefore, the speed of an aviation piston engine is directly determined by the combustion conditions in the cylinder and the propeller load, but the existing calculation of the speed of an aviation piston engine is not accurate enough, which will directly affect the control effect of the aviation piston engine. Summary of the invention

[0003] The technical problem to be solved by the present invention is to provide a method and a device for determining control parameters of an aviation piston engine, so as to improve the control effect of the aviation piston engine.

[0004] In order to solve the above technical problems, the technical solution of the present invention is as follows:

[0005] A first aspect of the present invention provides a method for determining control parameters of an aviation piston engine, comprising:

[0006] Get gear data of aviation piston engine;

[0007] Transforming the toothed disc data to obtain a frequency spectrum;

[0008] Determining frequency data according to the spectrum diagram;

[0009] Determining the rotation speed and the rotation speed change rate of the aviation piston engine according to the frequency data;

[0010] The speed control parameters of the aviation piston engine are determined according to the speed and the speed change rate.

[0011] Optionally, obtain gear data of an aviation piston engine, including:

[0012] The speed sensor installed at a preset position of the aviation piston engine is used to collect the speed data of the timing gear plate; the timing gear plate includes at least one missing tooth;

[0013] Obtaining speed data of the timing gear wheel in a preset time period;

[0014] The speed data of the timing gear wheel in the preset time period is preprocessed to obtain gear wheel data of the aviation piston engine.

[0015] Optionally, the toothed disc data is transformed to obtain a frequency spectrum, including:

[0016] Transform the toothed disc data according to a preset transformation method to obtain frequency and amplitude;

[0017] A spectrum diagram is obtained according to the frequency and the amplitude.

[0018] Optionally, determining frequency data according to the spectrum graph includes:

[0019] Determining an expected meshing frequency range based on the gear data;

[0020] Frequency data is determined based on the expected meshing frequency range and the frequency spectrum.

[0021] Optionally, determining the rotation speed of the aviation piston engine according to the frequency data includes:

[0022] According to the toothed disc data and the frequency data, the total number of teeth, the number of missing teeth and the frequency of missing teeth are obtained;

[0023] According to the total number of teeth, the number of missing teeth, the frequency of missing teeth and determining a rotational speed of the aviation piston engine;

[0024] Among them, RPM is the speed of the aviation piston engine, F is the missing tooth frequency, N is the total number of teeth, and M is the number of missing teeth.

[0025] Optionally, determining the speed change rate of the aviation piston engine according to the frequency data includes:

[0026] determining the instantaneous rotational speed of the tooth according to the frequency data;

[0027] determining an in-cylinder combustion event of the cylinder according to the instantaneous rotational speed of the tooth;

[0028] The speed change rate of the aviation piston engine is determined according to the in-cylinder combustion event of the cylinder.

[0029] Optionally, determining a speed control parameter of the aviation piston engine according to the speed and the speed change rate includes:

[0030] adjusting the throttle position, the ignition advance angle and the fuel injection amount according to the speed, the speed change rate and the preset speed threshold, to obtain an adjusted throttle position, an adjusted ignition advance angle and an adjusted fuel injection amount;

[0031] The speed control parameter of the aviation piston engine is determined according to the adjusted throttle position, the adjusted ignition advance angle and the adjusted fuel injection amount.

[0032] A second aspect of the present invention provides a device for determining control parameters of an aviation piston engine, comprising:

[0033] An acquisition module, used to acquire gear data of an aviation piston engine;

[0034] A processing module is used to transform the gear data to obtain a frequency spectrum; determine frequency data based on the frequency spectrum; determine the speed and speed change rate of the aviation piston engine based on the frequency data; and determine the speed control parameters of the aviation piston engine based on the speed and the speed change rate.

[0035] According to a third aspect of the present invention, a computing device is provided, comprising: a processor and a memory storing a computer program, wherein when the computer program is executed by the processor, the method according to the first aspect is executed.

[0036] A fourth aspect of the present invention provides a computer-readable storage medium storing instructions, which, when executed on a computer, causes the computer to execute the method described in the first aspect.

[0037] The above solution of the present invention includes at least the following beneficial effects:

[0038] The above scheme of the present invention obtains the gear data of the aviation piston engine and transforms it to obtain a spectrum diagram, and then determines the frequency data, and then determines the rotational speed and the rotational speed change rate of the aviation piston engine based on the frequency data. The rotational speed control parameters of the aviation piston engine are determined based on the rotational speed and the rotational speed change rate of the aviation piston engine. This can not only more accurately calculate the rotational speed of the engine, but also improve the control effect of the aviation piston engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0039] Figure 1 is a flow chart of a method for determining control parameters of an aviation piston engine in an embodiment of the present invention;

[0040] Figure 2 is a schematic diagram of the rotation speed data of an aviation piston engine in an embodiment of the present invention;

[0041] Figure 3 Schematic diagram of a spectrum diagram in an embodiment of the present invention.

[0042] Figure 4 It is a structural schematic diagram of a device for determining control parameters of an aviation piston engine in an embodiment of the present invention. DETAILED DESCRIPTION

[0043] The exemplary embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. Although the exemplary embodiments of the present invention are shown in the accompanying drawings, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided in order to enable a more thorough understanding of the present invention and to enable the scope of the present invention to be fully communicated to those skilled in the art.

[0044] like Figure 1 As shown, an embodiment of the present invention provides a method for determining control parameters of an aviation piston engine, comprising the following steps:

[0045] Step 101, obtaining gear data of an aviation piston engine;

[0046] Step 102, transforming the toothed disc data to obtain a frequency spectrum;

[0047] Step 103, determining frequency data according to the spectrum diagram;

[0048] Step 104, determining the rotation speed and rotation speed change rate of the aviation piston engine according to the frequency data;

[0049] Step 105: Determine a speed control parameter of the aviation piston engine according to the speed and the speed change rate.

[0050] The method for determining the control parameters of an aviation piston engine in an embodiment of the present invention obtains the gear data of the aviation piston engine and transforms it to obtain a spectrum diagram, thereby determining the frequency data, and then determining the rotational speed and the rotational speed change rate of the aviation piston engine based on the frequency data. The rotational speed control parameters of the aviation piston engine are determined based on the rotational speed and the rotational speed change rate of the aviation piston engine. This method can not only more accurately calculate the rotational speed of the engine, but also improve the control effect on the aviation piston engine.

[0051] In an optional embodiment of the present invention, step 101 includes:

[0052] Step 1011, using a speed sensor installed at a preset position of the aviation piston engine to collect speed data of a timing gear plate; the timing gear plate includes at least one missing tooth;

[0053] Specifically, an aviation piston engine is designed with a timing gear, which is composed of a number of small teeth and missing teeth. The timing gear is mainly used to control the precise timing of the various moving parts inside the engine to ensure that they can work in a coordinated and efficient manner; through the precise tooth shape and meshing relationship of the timing gear, the movement timing of key parts such as the piston, valve, ignition system, and fuel injection system can be accurately controlled.

[0054] A speed sensor is installed at a preset position of the aviation piston engine. The speed sensor can accurately detect the rotation of the timing gear. The installation position and angle of the speed sensor can be determined according to the specific structure of the timing gear and the operating characteristics of the engine. The speed sensor is used to collect the speed signal and the corresponding time point of the timing gear on the aviation piston engine, that is, the speed data, for subsequent calculations. Here, the speed sensor can be selected according to the specific situation, such as a Hall sensor or a photoelectric sensor, which can accurately capture the pulse signal (i.e., speed data) generated when the timing gear rotates.

[0055] Step 1012, obtaining the speed data of the timing gear wheel in a preset time period;

[0056] Specifically, the speed data of the timing gear can be obtained according to a preset period, such as once every 5 seconds or 30 seconds, which can be used in time for subsequent calculation of the speed and speed change rate, thereby improving the accuracy and timeliness of the control of the aviation piston engine.

[0057] Step 1013, pre-processing the rotation speed data of the timing gear in the preset time period to obtain gear data of the aviation piston engine.

[0058] Specifically, a digital filtering algorithm (such as mean filtering, median filtering, Kalman filtering, etc.) can be used to filter the speed data of the timing gear to remove noise and interference; then the preset standard data (or standard signal) can be used to verify the accuracy of the filtered speed data. If there is a deviation or error between the filtered speed data and the preset standard data, calibration is required. The calibration process includes adjusting the sensitivity of the speed sensor, the parameters when filtering the speed data of the timing gear, etc., to ensure the accuracy of the speed data.

[0059] In an optional embodiment of the present invention, step 102 includes:

[0060] Step 1021, transform the toothed disc data according to a preset transformation method to obtain frequency and amplitude;

[0061] Specifically, the preset transformation method can be and Where X[k] is the frequency obtained after the gear data is transformed, where k is the frequency index, ranging from 0 to N-1, and N is the length of the gear data. is a complex exponential function, where j is an imaginary unit (satisfying j 2 =-1), x[n] is the gear data, n is the time index, the value range is 0 to N-1, |X(k)| is the amplitude, Re(X(k))2 is the real part of X(k), Im(X(k)) 2 is the imaginary part of X(k). According to the formula of the above preset transformation method, the toothed disc data in the time domain can be transformed into the frequency and amplitude in the frequency domain.

[0062] Step 1022: Obtain a frequency spectrum diagram according to the frequency and the amplitude.

[0063] Specifically, the amplitude is used as the vertical axis and the frequency is used as the horizontal axis to obtain a spectrum diagram.

[0064] In an optional embodiment of the present invention, step 103 includes:

[0065] Step 1031, determining an expected meshing frequency range according to the gear data;

[0066] Specifically, the gear data also includes the number of normal teeth, the number of missing teeth, and the number of all teeth on the gear. A vibration sensor is used to collect vibration data of a gear (the number of normal teeth, the number of missing teeth, and the number of all teeth on the gear correspond to the number of normal teeth, the number of missing teeth, and the number of all teeth on the gear in the gear data) in different states, including vibration data of normal teeth and preset missing teeth, and the vibration data is converted from the time domain to the frequency domain to obtain a spectrum diagram, and then the spectrum diagram is obtained according to the gear speed, number of teeth, and Calculate the expected meshing frequency, where f m is the expected meshing frequency, Z is the total number of teeth on the gear, and p is the speed of the gear; a certain tolerance or fluctuation range is added to the expected meshing frequency, such as ±10%, to obtain the expected meshing frequency range (such as f m (1-10%) to f m (1+10%)) is used to determine the subsequent frequency data.

[0067] Step 1032: determining frequency data according to the expected meshing frequency range and the frequency spectrum.

[0068] Specifically, in the spectrum diagram, find the peak that matches the expected meshing frequency range, confirm that the frequency corresponding to the peak is the meshing frequency of the normal teeth, and the peak that increases abnormally or appears newly relative to the expected meshing frequency range is the frequency of the missing teeth. Here, the frequency data includes the frequency data of the missing teeth and the frequency data of other normal teeth, and the missing tooth frequency is lower than the normal tooth frequency, and the two frequencies are in a multiple relationship, which is the same as the ratio of the number of normal teeth to the number of missing teeth.

[0069] In an optional embodiment of the present invention, determining the rotation speed of the aviation piston engine according to the frequency data in step 104 includes:

[0070] Step 1041, obtaining the total number of teeth, the number of missing teeth and the frequency of missing teeth according to the toothed disc data and the frequency data;

[0071] Specifically, the sprocket data includes the number of normal teeth, the number of missing teeth and the number of all teeth on the sprocket, and the frequency data includes the missing tooth frequency. Therefore, the total number of teeth, the number of missing teeth and the missing tooth frequency can be obtained from the sprocket data and the frequency data for subsequent calculation of the rotation speed.

[0072] Step 1042: according to the total number of teeth, the number of missing teeth, the frequency of missing teeth and determining a rotational speed of the aviation piston engine;

[0073] Among them, RPM is the speed of the aviation piston engine, F is the missing tooth frequency, N is the total number of teeth, and M is the number of missing teeth.

[0074] Specifically, by inputting the total number of teeth, the number of missing teeth and the frequency of missing teeth into the formula, the rotational speed of the aviation piston engine can be calculated, providing a basis for the subsequent rotational speed control parameters of the aviation piston engine.

[0075] In an optional embodiment of the present invention, determining the speed change rate of the aviation piston engine according to the frequency data in step 104 includes:

[0076] Step 1043, determining the instantaneous rotation speed of the tooth according to the frequency data;

[0077] Specifically, the instantaneous speed can be calculated using the time difference between two adjacent teeth passing the sensor (ie, the time in the gear data), or the speed within a period of time can be averaged to obtain the average speed, ie, the instantaneous speed of the tooth.

[0078] Step 1044, determining a combustion event in the cylinder according to the instantaneous rotation speed of the tooth;

[0079] Specifically, the time point when the cylinder combustion event (such as ignition, combustion, etc.) occurs can be identified through the change in the instantaneous speed of the teeth. When the engine is working, the force (torque) on the crankshaft changes periodically. There is a certain relationship between this torque and the gas pressure generated by the combustion of fuel in the cylinder and the reciprocating inertia force generated by components such as the piston-connecting rod. When combustion occurs in the cylinder, the gas pressure rises sharply, driving the change in torque, and then causing the instantaneous speed of the crankshaft (or the instantaneous speed of the teeth) to change. Therefore, when the instantaneous speed of the teeth is inconsistent with the average speed of the teeth, it can be determined that a cylinder combustion event has occurred, and the time point when the event occurs facilitates the subsequent determination of the speed change rate of the aviation piston engine.

[0080] Step 1045, determining the speed change rate of the aviation piston engine according to the in-cylinder combustion event of the cylinder.

[0081] Specifically, after the combustion event in the cylinder is identified, the change in speed before and after the event is calculated. The speed change rate refers to the change in speed per unit time, which can be calculated by the following formula: Where V is the speed change rate, is the average rate of change of speed in Δt time (unit: r / min·s), multiplied by The purpose is to convert the rate of change into a percentage change in RPM. If the engine has multiple cylinders, the speed change rates of different cylinders under the same operating conditions can be compared.

[0082] In an optional embodiment of the present invention, step 105 includes:

[0083] Step 1051, adjusting the throttle position, the ignition advance angle and the fuel injection amount according to the speed, the speed change rate and the preset speed threshold, to obtain an adjusted throttle position, an adjusted ignition advance angle and an adjusted fuel injection amount;

[0084] Specifically, if the speed is within the preset speed threshold, and the speed change rate is greater than the preset speed change rate, the throttle position is reduced, the ignition time is advanced, the fuel injection pulse width is increased, etc. In a specific embodiment, if the preset speed threshold is 1500-2500 revolutions per minute (RPM), the actual calculated speed is 2000RPM, and the speed change rate is 50RPM per minute, in order to maintain stable engine operation, the throttle position can be slightly reduced (assuming that the current throttle opening is 50%, it can be gradually reduced to about 45%) to slow down the speed increase, slow down the acceleration speed, and avoid excessive speed; the ignition advance angle can be fine-tuned according to the recommended value of the engine manufacturer, for example, from the original 20° to about 22°, and the fuel injection pulse width or frequency is increased to increase the injection amount. It should be noted that the adjustments to the throttle position, ignition advance angle, and fuel injection amount should ensure compliance with the recommendations and guidelines of the engine manufacturer to improve safety during use.

[0085] Step 1052, determining the speed control parameters of the aviation piston engine according to the adjusted throttle position, the adjusted ignition advance angle and the adjusted fuel injection amount.

[0086] Specifically, the adjusted throttle position, the adjusted ignition advance angle and the adjusted fuel injection amount can be converted into speed control parameters suitable for aviation piston engines, thereby improving the control effect.

[0087] A specific embodiment of the method for determining the control parameters of an aviation piston engine according to an embodiment of the present invention includes:

[0088] Step 111, obtaining gear data of an aviation piston engine;

[0089] The timing gear on the aircraft piston engine is composed of a number of small teeth and missing teeth. The missing teeth serve as a mark to identify the position of the gear. The position of each tooth can be associated with the position of the piston, and then the piston top dead center position and engine speed can be calculated through the position of the tooth and the angle of rotation of the gear per unit time. The gear data with missing teeth of the aircraft piston engine is collected using a speed sensor installed on the aircraft piston engine. The gear data includes the time when the data is collected.

[0090] Step 112, transforming the toothed disc data to obtain a frequency spectrum;

[0091] The speed sensor collects data from the sprocket with missing teeth and records the time when the data is collected. After recording the data for a certain length of time, a frequency spectrum of the speed signal is obtained according to a preset transformation method.

[0092] Step 113, determining frequency data according to the spectrum diagram;

[0093] The frequency of missing teeth and other normal teeth can be obtained from the spectrum diagram, and the missing tooth frequency is lower than the normal tooth frequency. The two frequencies are in a multiple relationship, which is the same as the ratio of the number of normal teeth to the number of missing teeth. According to the frequency data of missing teeth or normal teeth, the speed of the aircraft piston engine can be calculated later.

[0094] Step 114, determining the speed and speed change rate of the aviation piston engine;

[0095] The speed change rate is the value of the engine speed change caused by the combined force of the force of the mixture on the piston in the cylinder and the resistance and friction of the engine load when a certain cylinder is burning. According to the missing teeth corresponding to the piston reaching the top dead center position in different cylinders, the gear disc data is grouped, and the gear disc data of the piston reaching the top dead center position in the same cylinder are spliced ​​together in time sequence to obtain a data group with the same number of cylinders. According to the preset transformation method, each group of data is processed separately to obtain a speed signal spectrum diagram for each group. The instantaneous speed displayed by each group of data can be obtained from the spectrum diagram. By comparing the instantaneous speeds of several groups, the contribution of the combustion in each cylinder to the speed can be analyzed, so that the combustion condition of each cylinder can be seen, and whether the injection or ignition parameters of the cylinder with poor combustion need to be modified.

[0096] Step 115, determining the speed control parameters of the aviation piston engine.

[0097] According to the speed and speed change rate of the aviation piston engine, the throttle position, ignition advance angle and fuel injection amount can be adjusted and then converted into the speed control parameters of the aviation piston engine (or the throttle position, ignition advance angle and fuel injection amount are adjusted and input into the electronic control unit of the aviation piston engine to control the aviation piston engine) as reference information for monitoring and controlling the operating status of the aviation piston engine.

[0098] The method for determining the control parameters of an aviation piston engine in an embodiment of the present invention, the data is derived from the data collected by the speed sensor, the data is processed, and then transformed in a preset transformation method, and the speed is determined according to the frequency and amplitude. The basis of the preset transformation method is that a periodic signal contains multiple frequency components, and any signal can be formed by adding multiple periodic functions. The data collected by the speed sensor is processed in a preset transformation method, and the corresponding speed parameters are obtained according to the frequency and amplitude; the data collected by the speed sensor is integrated, calculated and compared in combination with the gear position and the corresponding piston position to obtain the speed change rate value caused by the in-cylinder combustion, that is, the speed change rate caused by the in-cylinder combustion. Comparing the speed change rates caused by different in-cylinder combustion can be used to analyze the combustion condition.

[0099] Figure 2 It is the speed signal with missing teeth during one rotation of the crankshaft of an aviation piston engine (i.e. the gear data collected by the speed sensor). When the speed signal is collected by the speed sensor, the time value of each data point is recorded at the same time. After recording the data for a certain length of time, a preset transformation method is used to obtain the spectrum diagram of the speed signal. Figure 3 The frequency of normal teeth can be obtained from the spectrum diagram shown (such as the second peak is the frequency of normal teeth). The frequency value is divided by the number of teeth on the gear plate (missing teeth are converted to normal teeth according to the position size) to get the speed of the aviation piston engine. When the speed signal is collected by the speed sensor, the time value of each data point is recorded at the same time. After recording the speed signal data of the crankshaft for multiple revolutions, the following data processing is performed:

[0100] The same tooth number data after the top dead center of cylinder 1 in multiple cycles (until the top dead center of cylinder 2) are reorganized in chronological order. The tooth numbering method is as follows. For example, the third tooth after the top dead center of cylinder 1 is numbered 1#ATDC3. The speed signal spectrum of each tooth is obtained by using the preset transformation method. The signal frequency of the tooth can be obtained from the spectrum. Calculate the angle ratio of the tooth to the entire circumference, and then use the tooth frequency value multiplied by its angle ratio value to obtain the instantaneous speed of the tooth.

[0101] Calculate the instantaneous speed of each tooth after the top dead center of cylinders 2, 4, and 3 in multiple cycles (when the ignition order of the aviation piston engine is 1, 3, 4, and 2, the instantaneous speed of each tooth after the top dead center of cylinder 1 is calculated during implementation, and then the instantaneous speed of each tooth after the top dead center of cylinders 3, 4, and 2 is calculated).

[0102] Find the maximum instantaneous speed after the top dead center of each cylinder and its corresponding tooth number.

[0103] Compare the maximum instantaneous speed of each cylinder, find the value with the lowest maximum instantaneous speed, and judge whether it is reasonable. If it is reasonable, wait for the next round of calculation, otherwise compare the tooth number with the lowest maximum instantaneous speed of other cylinders, determine whether the combustion is too early or too late, and appropriately modify the injection timing, injection pulse width or ignition timing of the cylinder with the lowest maximum instantaneous speed. Then proceed to the next round of calculation.

[0104] The method for determining the control parameters of an aviation piston engine in an embodiment of the present invention transforms the collected data according to a preset transformation method, has higher tolerance for data errors and more accurate calculation results; the instantaneous speed of single-cylinder combustion can analyze the contribution of each cylinder combustion to the speed, and then compare the work done by each cylinder; the instantaneous speed of single-cylinder combustion can monitor the operating status of the aviation piston engine more precisely and detect cylinders with abnormal combustion in time; the instantaneous speed of single-cylinder combustion can provide a judgment basis for the fine control of the aviation piston engine.

[0105] like Figure 4 As shown, an embodiment of the present invention provides a device 200 for determining control parameters of an aviation piston engine, comprising:

[0106] The acquisition module 201 is used to acquire gear data of an aviation piston engine;

[0107] The processing module 202 is used to transform the gear data to obtain a frequency spectrum; determine frequency data based on the frequency spectrum; determine the speed and speed change rate of the aviation piston engine based on the frequency data; and determine the speed control parameters of the aviation piston engine based on the speed and the speed change rate.

[0108] Optionally, obtain gear data of an aviation piston engine, including:

[0109] The speed sensor installed at a preset position of the aviation piston engine is used to collect the speed data of the timing gear plate; the timing gear plate includes at least one missing tooth;

[0110] Obtaining speed data of the timing gear wheel in a preset time period;

[0111] The speed data of the timing gear wheel in the preset time period is preprocessed to obtain gear wheel data of the aviation piston engine.

[0112] Optionally, the toothed disc data is transformed to obtain a frequency spectrum, including:

[0113] Transform the toothed disc data according to a preset transformation method to obtain frequency and amplitude;

[0114] A spectrum diagram is obtained according to the frequency and the amplitude.

[0115] Optionally, determining frequency data according to the spectrum graph includes:

[0116] Determining an expected meshing frequency range based on the gear data;

[0117] Frequency data is determined based on the expected meshing frequency range and the frequency spectrum.

[0118] Optionally, determining the rotation speed of the aviation piston engine according to the frequency data includes:

[0119] According to the toothed disc data and the frequency data, the total number of teeth, the number of missing teeth and the frequency of missing teeth are obtained;

[0120] According to the total number of teeth, the number of missing teeth, the frequency of missing teeth and determining a rotational speed of the aviation piston engine;

[0121] Among them, RPM is the speed of the aviation piston engine, F is the missing tooth frequency, N is the total number of teeth, and M is the number of missing teeth.

[0122] Optionally, determining the speed change rate of the aviation piston engine according to the frequency data includes:

[0123] determining the instantaneous rotational speed of the tooth according to the frequency data;

[0124] determining an in-cylinder combustion event of the cylinder according to the instantaneous rotational speed of the tooth;

[0125] The speed change rate of the aviation piston engine is determined according to the in-cylinder combustion event of the cylinder.

[0126] Optionally, determining a speed control parameter of the aviation piston engine according to the speed and the speed change rate includes:

[0127] adjusting the throttle position, the ignition advance angle and the fuel injection amount according to the speed, the speed change rate and the preset speed threshold, to obtain an adjusted throttle position, an adjusted ignition advance angle and an adjusted fuel injection amount;

[0128] The speed control parameter of the aviation piston engine is determined according to the adjusted throttle position, the adjusted ignition advance angle and the adjusted fuel injection amount.

[0129] The device for determining the control parameters of an aviation piston engine in an embodiment of the present invention obtains the gear data of the aviation piston engine and transforms it to obtain a spectrum diagram, thereby determining the frequency data, and then determining the rotational speed and the rotational speed change rate of the aviation piston engine based on the frequency data. The rotational speed control parameters of the aviation piston engine are determined based on the rotational speed and the rotational speed change rate of the aviation piston engine, which can not only more accurately calculate the rotational speed of the engine, but also improve the control effect on the aviation piston engine.

[0130] It should be noted that the device is a device corresponding to the above method, and all implementations in the above method embodiment are applicable to the embodiment of the device and can achieve the same technical effect. This embodiment will not be repeated.

[0131] The embodiment of the present invention further provides a computing device, comprising: a processor, and a memory storing a computer program, wherein when the computer program is executed by the processor, the method described in any one of the above embodiments is executed. All implementations in the above method embodiments are applicable to the embodiments of the device, and can achieve the same technical effects. They will not be described in detail in this embodiment.

[0132] The embodiment of the present invention further provides a computer-readable storage medium on which instructions are stored. When the instructions are executed on a computer, the computer executes the method as described in any one of the above embodiments. All implementations in the above method embodiments are applicable to the embodiments of the device and can achieve the same technical effects. They will not be described in detail in this embodiment.

[0133] It should be noted that in the apparatus and method of the present invention, it is obvious that each component or each step can be decomposed and / or recombined. These decompositions and / or recombinations should be regarded as equivalent solutions of the present invention. In addition, the steps of performing the above series of processes can naturally be performed in chronological order according to the order of description, but do not necessarily need to be performed in chronological order. Some steps can be performed in parallel, crosswise or independently of each other.

[0134] It should be noted that, in the above-mentioned embodiments, the terms "include", "comprise" or any other variant thereof are intended to cover non-exclusive inclusion, so that the process, method, article or device including a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "include one..." do not exclude the existence of other identical elements in the process, method, article or device including the element. In addition, it should be pointed out that the scope of the methods and devices in the implementation of the above-mentioned embodiments is not limited to performing functions in the order shown or discussed, and may also include performing functions in a substantially simultaneous manner or in the opposite order according to the functions involved, for example, the described method may be performed in an order different from that described, and various steps may also be added, omitted, or combined. In addition, the features described with reference to certain examples may be combined in other examples.

[0135] The above is a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A method for determining control parameters of an aviation piston engine, characterized in that: include: Get gear data of aviation piston engine; Transforming the toothed disc data to obtain a frequency spectrum; Determining frequency data according to the spectrum diagram; Determining the rotation speed and the rotation speed change rate of the aviation piston engine according to the frequency data; The speed control parameters of the aviation piston engine are determined according to the speed and the speed change rate.

2. The method for determining the control parameters of an aviation piston engine according to claim 1, characterized in that: Get gear data of aviation piston engines, including: The speed sensor installed at a preset position of the aviation piston engine is used to collect the speed data of the timing gear plate; the timing gear plate includes at least one missing tooth; Obtaining speed data of the timing gear wheel in a preset time period; The speed data of the timing gear disk in the preset time period is preprocessed to obtain gear disk data of the aviation piston engine.

3. The method for determining the control parameters of an aviation piston engine according to claim 1, characterized in that: The gear data is transformed to obtain a frequency spectrum, including: Transform the toothed disc data according to a preset transformation method to obtain frequency and amplitude; A spectrum diagram is obtained according to the frequency and the amplitude.

4. The method for determining the control parameters of an aviation piston engine according to claim 1, characterized in that: Determining frequency data according to the spectrum diagram includes: Determining an expected meshing frequency range based on the gear data; Frequency data is determined based on the expected meshing frequency range and the frequency spectrum.

5. The method for determining the control parameters of an aviation piston engine according to claim 1, characterized in that: Determining the rotation speed of the aviation piston engine according to the frequency data includes: According to the toothed disc data and the frequency data, the total number of teeth, the number of missing teeth and the frequency of missing teeth are obtained; According to the total number of teeth, the number of missing teeth, the frequency of missing teeth and determining a rotational speed of the aviation piston engine; Among them, RPM is the speed of the aviation piston engine, F is the missing tooth frequency, N is the total number of teeth, and M is the number of missing teeth.

6. The method for determining the control parameters of an aviation piston engine according to claim 1, characterized in that: Determining the speed change rate of the aviation piston engine according to the frequency data includes: determining the instantaneous rotational speed of the tooth according to the frequency data; determining an in-cylinder combustion event of the cylinder according to the instantaneous rotational speed of the tooth; The speed change rate of the aviation piston engine is determined according to the in-cylinder combustion event of the cylinder.

7. The method for determining the control parameters of an aviation piston engine according to claim 1, characterized in that: Determining the speed control parameter of the aviation piston engine according to the speed and the speed change rate includes: adjusting the throttle position, the ignition advance angle and the fuel injection amount according to the speed, the speed change rate and the preset speed threshold, to obtain an adjusted throttle position, an adjusted ignition advance angle and an adjusted fuel injection amount; The speed control parameter of the aviation piston engine is determined according to the adjusted throttle position, the adjusted ignition advance angle and the adjusted fuel injection amount.

8. A device for determining control parameters of an aviation piston engine, characterized in that: include: An acquisition module, used to acquire gear data of an aviation piston engine; A processing module, used for transforming the toothed disc data to obtain a frequency spectrum; According to the frequency spectrum, frequency data is determined; according to the frequency data, the rotational speed and the rotational speed change rate of the aviation piston engine are determined; according to the rotational speed and the rotational speed change rate, the rotational speed control parameters of the aviation piston engine are determined.

9. A computing device, characterized in that include: A processor and a memory storing a computer program, wherein when the computer program is executed by the processor, the method according to any one of claims 1 to 7 is performed.

10. A computer-readable storage medium, characterized in that: Instructions are stored, and when the instructions are executed on a computer, the computer is caused to execute the method according to any one of claims 1 to 7.

Images