CN117559878A - Current control method and device of model airplane electronic speed regulator and electronic equipment - Google Patents
Current control method and device of model airplane electronic speed regulator and electronic equipment Download PDFInfo
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- CN117559878A CN117559878A CN202410046781.1A CN202410046781A CN117559878A CN 117559878 A CN117559878 A CN 117559878A CN 202410046781 A CN202410046781 A CN 202410046781A CN 117559878 A CN117559878 A CN 117559878A
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- 238000000034 method Methods 0.000 title claims abstract description 75
- 238000004364 calculation method Methods 0.000 claims abstract description 37
- 238000012545 processing Methods 0.000 claims abstract description 29
- 238000005070 sampling Methods 0.000 claims description 57
- 230000010354 integration Effects 0.000 claims description 15
- 238000004590 computer program Methods 0.000 claims description 5
- 230000008859 change Effects 0.000 description 10
- 238000001914 filtration Methods 0.000 description 8
- 238000012544 monitoring process Methods 0.000 description 8
- 230000008569 process Effects 0.000 description 7
- 238000010438 heat treatment Methods 0.000 description 6
- 230000006870 function Effects 0.000 description 5
- 230000002035 prolonged effect Effects 0.000 description 3
- 230000002159 abnormal effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000020169 heat generation Effects 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000003287 optical effect Effects 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004422 calculation algorithm Methods 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
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Classifications
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P29/00—Arrangements for regulating or controlling electric motors, appropriate for both AC and DC motors
- H02P29/02—Providing protection against overload without automatic interruption of supply
- H02P29/024—Detecting a fault condition, e.g. short circuit, locked rotor, open circuit or loss of load
- H02P29/027—Detecting a fault condition, e.g. short circuit, locked rotor, open circuit or loss of load the fault being an over-current
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P29/00—Arrangements for regulating or controlling electric motors, appropriate for both AC and DC motors
- H02P29/02—Providing protection against overload without automatic interruption of supply
- H02P29/024—Detecting a fault condition, e.g. short circuit, locked rotor, open circuit or loss of load
- H02P29/028—Detecting a fault condition, e.g. short circuit, locked rotor, open circuit or loss of load the motor continuing operation despite the fault condition, e.g. eliminating, compensating for or remedying the fault
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02P—CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS; CONTROLLING TRANSFORMERS, REACTORS OR CHOKE COILS
- H02P29/00—Arrangements for regulating or controlling electric motors, appropriate for both AC and DC motors
- H02P29/02—Providing protection against overload without automatic interruption of supply
- H02P29/032—Preventing damage to the motor, e.g. setting individual current limits for different drive conditions
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The embodiment of the application discloses a current control method and device of an electronic speed regulator of a model airplane and electronic equipment, wherein the method comprises the following steps: acquiring a current integral value calculation model and acquiring a plurality of key parameters; inputting the multiple key parameters into a current integral value calculation model for processing, and outputting a corresponding current integral value; comparing the current integral value with a preset current integral maximum threshold value under the condition that the current integral value is larger than zero to obtain a corresponding comparison result; and controlling to trigger a start instruction to execute a current protection operation based on the start instruction when the comparison result is that the present current integral value is greater than or equal to the preset current integral maximum threshold value.
Description
Technical Field
The invention relates to the technical field of computers, in particular to a current control method and device of an electronic speed regulator of a model airplane and electronic equipment.
Background
In the current electric model airplane market application, the current protection function is particularly important, and if the current protection value is set to be very high, the possibility of burning the electronic speed regulator is caused at a great risk; if the current protection value is set to be very small, false triggering protection can be performed with high probability, so that the operation experience of a user is affected. For an electric model airplane with less complex operability, the current protection function is less obvious; however, for some electric aeromodelling which needs to be operated with high difficulty and complexity, the current protection function is particularly important, so that the electronic speed regulator needs to be protected, and the probability of false triggering protection needs to be reduced.
How to effectively improve the operation experience and the service life of an electric model airplane so as to solve the problem of burning out an electronic speed regulator caused by large current due to locked rotor and frying in actual flight is a technical problem to be solved.
Disclosure of Invention
Based on this, it is necessary to provide a current control method, apparatus, storage medium, electronic device and computer program product for model airplane electronic speed regulator, which solve the problem of burnout of electronic speed regulator caused by high current in the prior art.
In a first aspect, embodiments of the present application provide a current control method of a model airplane electronic speed governor, the method including:
acquiring a current integral value calculation model and acquiring a plurality of key parameters;
inputting the key parameters into the current integral value calculation model for processing, and outputting a corresponding current integral value;
comparing the current integral value with a preset current integral maximum threshold value under the condition that the current integral value is larger than zero to obtain a corresponding comparison result;
and controlling to trigger a starting instruction to execute a current protection operation based on the starting instruction under the condition that the comparison result is that the current integral value is larger than or equal to the preset current integral maximum threshold value.
Preferably, the method further includes inputting the plurality of key parameters into the current integration value calculation model for processing, and outputting a corresponding current integration value, including:
reading the plurality of key parameters, wherein the plurality of key parameters at least comprise: the current integral value, a previous current integral value corresponding to the current integral value, a real-time sampling current value, a real-time sampling temperature value of a power MOS tube of the target model electronic speed regulator, a first constant related to the current value, a second constant related to the sampling temperature of the power MOS tube of the target model electronic speed regulator and a set initial current threshold;
and inputting the plurality of key parameters into the current integral value calculation model for processing, and outputting a corresponding current integral value.
Preferably, the method further comprises:
carrying out real-time sampling processing on the real-time sampling current value; and
and sampling the real-time sampling temperature value of the power MOS tube of the target model electronic speed regulator.
Preferably, the method further comprises:
in the case where it is determined that the present current integrated value is greater than zero, the present current integrated value is taken as an effective value.
Preferably, the method further comprises:
in the case where it is determined that the present current integrated value is smaller than or equal to zero, the present current integrated value is taken as an invalid value.
In a second aspect, embodiments of the present application provide a current control device for a model airplane electronic governor, the device comprising:
the acquisition module is used for acquiring the current integral value calculation model and acquiring a plurality of key parameters;
the calculation module is used for inputting the plurality of key parameters into the current integral value calculation model for processing and outputting a corresponding current integral value;
the comparison module is used for comparing the current integral value with a preset current integral maximum threshold value under the condition that the current integral value is larger than zero, so as to obtain a corresponding comparison result;
and the control module is used for controlling to trigger a starting instruction to execute current protection operation based on the starting instruction under the condition that the comparison result is that the current integral value is larger than or equal to the preset current integral maximum threshold value.
Preferably, the computing module is specifically configured to:
reading the plurality of key parameters, wherein the plurality of key parameters at least comprise: the current integral value, a previous current integral value corresponding to the current integral value, a real-time sampling current value, a real-time sampling temperature value of a power MOS tube of the target model electronic speed regulator, a first constant related to the current value and a second constant related to the sampling temperature of the power MOS tube of the target model electronic speed regulator;
and inputting the plurality of key parameters into the current integral value calculation model for processing, and outputting a corresponding current integral value.
Preferably, the method further comprises:
a sampling module for:
carrying out real-time sampling processing on the real-time sampling current value; and
and sampling the real-time sampling temperature value of the power MOS tube of the target model electronic speed regulator.
In a third aspect, embodiments of the present application provide a computer-readable storage medium storing a computer program for performing the above-described method steps.
In a fourth aspect, an embodiment of the present application provides an electronic device, including:
a processor;
a memory for storing executable instructions of the processor;
the processor is configured to read the executable instructions from the memory and execute the executable instructions to implement the method steps described above.
In a fifth aspect, embodiments of the present application provide a computer program product comprising a computer program which, when executed by a processor, implements the above-described method steps.
In the embodiment of the application, a current integral value calculation model is acquired and a plurality of key parameters are acquired; inputting the multiple key parameters into a current integral value calculation model for processing, and outputting a corresponding current integral value; comparing the current integral value with a preset current integral maximum threshold value under the condition that the current integral value is larger than zero to obtain a corresponding comparison result; and controlling to trigger a start instruction to execute a current protection operation based on the start instruction when the comparison result is that the present current integral value is greater than or equal to the preset current integral maximum threshold value. According to the current control method of the model airplane electronic speed regulator, the current integral value can be accurately calculated based on the current integral value calculation model, and under the condition that the current integral value is greater than or equal to the preset current integral maximum threshold value, the trigger starting instruction is controlled to execute the current protection operation based on the starting instruction; therefore, the phenomenon that the electronic speed regulator burns out caused by high current can be effectively avoided; in addition, the operation experience of the electric model aircraft can be effectively improved, and the service life of the electric model aircraft can be prolonged.
Drawings
Exemplary embodiments of the present invention may be more fully understood by reference to the following drawings. The accompanying drawings are included to provide a further understanding of embodiments of the application and are incorporated in and constitute a part of this specification, illustrate the invention and together with the embodiments of the application, and not constitute a limitation of the invention. In the drawings, like reference numerals generally refer to like parts or steps.
FIG. 1 is a flow chart of a method of current control of a model airplane electronic governor provided in accordance with an exemplary embodiment of the present application;
fig. 2 is a schematic structural diagram of a current control device 200 of a model airplane electronic speed governor according to an exemplary embodiment of the present application.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
It is noted that unless otherwise indicated, technical or scientific terms used herein should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs.
In addition, the terms "first" and "second" etc. are used to distinguish different objects and are not used to describe a particular order. Furthermore, the terms "comprise" and "have," as well as any variations thereof, are intended to cover a non-exclusive inclusion. For example, a process, method, system, article, or apparatus that comprises a list of steps or elements is not limited to only those listed steps or elements but may include other steps or elements not listed or inherent to such process, method, article, or apparatus.
The embodiments of the present application provide a current control method and apparatus for an electronic speed regulator of a model airplane, an electronic device and a computer readable medium, and the following description is made with reference to the accompanying drawings.
Referring to fig. 1, which is a flowchart illustrating a current control method of a model electronic speed regulator according to some embodiments of the present application, as shown in fig. 1, the current control method of a model electronic speed regulator may include the following steps:
step S101: a current integration value calculation model is acquired and a plurality of key parameters are acquired.
In the current control method of the model airplane electronic speed regulator provided by the embodiment of the application, the plurality of key parameters at least comprise: the method comprises the steps of a current integral value, a previous current integral value corresponding to the current integral value, a real-time sampling current value, a real-time sampling temperature value of a power MOS tube of a target model electronic speed regulator, a first constant related to the current value, a second constant related to the sampling temperature of the power MOS tube of the target model electronic speed regulator and a set initial current threshold value.
Step S102: and inputting the plurality of key parameters into a current integral value calculation model for processing, and outputting a corresponding current integral value.
In the current control method of the model airplane electronic speed regulator provided in the embodiment of the present application, the above current integral value calculation model may be processed by adopting a calculation model corresponding to the following formula (1), which is specifically described as follows:
formula (1);
in the above-mentioned formula (1),for the present current integral value->A previous current integration value corresponding to the present current integration value; />Is a first constant related to the current value; />A second constant related to the sampling temperature of the power MOS tube of the target model electronic speed regulator; />Sampling a current value in real time; />The temperature value is sampled in real time for a power MOS tube of the target model airplane electronic speed regulator; />Is the initial current threshold set.
The above-mentioned、/>Are all constant; all need to be set according to the actual power electronic speed regulator. If the current protection required by the actual application scene is more sensitive, the values of A and B can be set larger. For the actual electronic speed regulator, the developer or the user can flexibly adjust A, B and +_ according to the aspect of large actual influence factors>Specific values of (2).
Step S103: comparing the current integral value with a preset current integral maximum threshold value under the condition that the current integral value is larger than zero to obtain a corresponding comparison result;
step S104: and controlling to trigger a starting instruction to execute a current protection operation based on the starting instruction under the condition that the comparison result is that the current integral value is larger than or equal to the preset current integral maximum threshold value.
It should be noted that, the preset current integration maximum threshold in the above steps may be adjusted according to requirements of different application scenarios, which is not limited herein.
When the comparison result is that the current integral value is smaller than the preset current integral maximum threshold value, logic operation calculation is required to be performed again, and real-time sampling processing is continuously performed on the real-time sampling current value; and sampling the real-time sampling temperature value of the power MOS tube of the target model electronic speed regulator until the current integral value is greater than or equal to a preset current integral maximum threshold value, and controlling to trigger a starting instruction so as to execute current protection operation based on the starting instruction. For the logical operation process, the frequency of 10KHz is adopted for real-time monitoring. In this way, accurate and efficient monitoring can be performed at each point in time. The design not only increases the requirement on the data processing precision, but also requires the hardware equipment to have corresponding performance and response speed. In the process, advanced algorithm and precise hardware equipment are used to acquire current data of the model airplane electronic speed regulator in real time. As soon as these data reach or exceed a preset current integration maximum threshold value, the protection operation is started immediately. Such operations may include, but are not limited to, shutting down power, reducing motor speed, etc., to ensure that the model airplane electronic governor is not subjected to excessive current surges, thereby protecting and extending its useful life.
In addition, the real-time monitoring device has high stability and reliability. Even if facing the complex flying environment and various possible emergency conditions, the device can accurately and reliably execute the protection operation, and the safety and stable operation of the model airplane electronic speed regulator are ensured to the greatest extent.
In one possible implementation manner, the method includes the steps of inputting a plurality of key parameters into a current integral value calculation model for processing, and outputting a corresponding current integral value, and includes the following steps:
reading a plurality of key parameters, wherein the plurality of key parameters at least comprise: the method comprises the steps of a current integral value, a previous current integral value corresponding to the current integral value, a real-time sampling current value, a real-time sampling temperature value of a power MOS tube of a target model electronic speed regulator, a first constant related to the current value, a second constant related to the sampling temperature of the power MOS tube of the target model electronic speed regulator and a set initial current threshold value;
and inputting the plurality of key parameters into a current integral value calculation model for processing, and outputting a corresponding current integral value.
In one possible implementation manner, the current control method of the model airplane electronic speed regulator provided by the embodiment of the application further comprises the following steps:
carrying out real-time sampling treatment on the real-time sampling current value; and
and carrying out sampling processing on the real-time sampling temperature value of the power MOS tube of the target model airplane electronic speed regulator.
In the current control method of the model airplane electronic speed regulator, current sampling is achieved by connecting a high-precision current sampling resistor between a power supply and the model airplane electronic speed regulator. By measuring the voltage drop across the resistor, the current through the model airplane electronic governor can be calculated. The method has high precision and response speed, and can monitor the current consumption of the model airplane electronic speed regulator in real time. The sampling result shows that the temperature of the power MOS tube can be gradually increased along with the increase of the rotating speed of the motor. This is because the power MOS transistor in the electronic governor is a main power element and generates heat due to power loss. Generally, the temperature of the MOS transistor cannot exceed its maximum allowable temperature to prevent degradation or damage of its performance. By monitoring the temperature of the power MOS tube, the current of the real-time model airplane electronic speed regulator and the temperature of the power MOS tube are sampled in real time, so that the stability and reliability of the electronic speed regulator applied to more complex scenes can be improved.
It should be noted that the characteristics of the MOS transistor: the overcurrent capability is different at different temperatures. At high temperatures, the over-current capability of the MOS transistor may decrease. This is because the resistivity of the semiconductor material changes at high temperatures, thereby affecting the flow of current. In addition, the high temperature also causes an increase in thermal stress inside the MOS tube, which may cause changes in mechanical and electrical properties. These factors all affect the over-current capability of the MOS transistor.
In the current control method of the model airplane electronic speed regulator, which is provided by the embodiment of the application, the heating generated in the operation of the power MOS tube is combined, the temperature of the power MOS tube is monitored through a thermistor and other elements, and then the information is combined to calculate the overcurrent value.
In an electronic speed regulator, a power MOS transistor is one of the main power elements, and when it is switched in an on and off state, it generates heat along with energy conversion. The current control method of the model airplane electronic speed regulator provided by the embodiment of the application calculates the actual current value in the circuit by monitoring the heat generation process and the temperature change of the MOS tube, thereby obtaining the current integral value and better protecting the electronic speed regulator from current.
The specific implementation process is as follows:
and a thermistor is arranged beside the power MOS tube and used for monitoring the temperature change of the MOS tube. And measuring the voltage value of the thermistor, wherein the voltage value is in direct proportion to the temperature of the MOS tube. The heating power of the MOS tube can be calculated through a series of voltage values obtained through measurement, and the heating power is proportional to the square of the current in the circuit. According to the relation between the heating power and the current in the circuit, the actual current value of the circuit can be calculated.
In unmanned aerial vehicles, aeromodelling and other applications, an electronic governor is one of the vital components, which is responsible for controlling the rotational speed of the motor. If the electronic speed regulator fails, the motor may be out of control, thereby causing serious damage to the unmanned aerial vehicle or the model airplane. Therefore, the overcurrent protection provided by the current control method of the model airplane electronic speed regulator provided by the embodiment of the application is of great importance.
The current control method of the model airplane electronic speed regulator is realized by combining the current of the monitoring motor with the heat of the power MOS tube. When the current integral value exceeds a set threshold value, a current protection mechanism is triggered, and the electronic speed regulator is closed, so that the equipment is prevented from being damaged. This approach has higher reliability and robustness.
Of course, to ensure the accuracy of the over-current protection, an appropriate threshold value needs to be selected according to the performance and application requirements of the electronic governor. The maximum allowable current and voltage of the device need to be taken into account when selecting the threshold value to ensure that the protection circuit can trigger properly. In addition, to ensure the safety of the unmanned aerial vehicle or the model airplane, sufficient tests and verification are required to ensure that the overcurrent protection function can work normally under various conditions. For special applications such as unmanned aerial vehicles and aeromodelling, the current control method of the aeromodelling electronic speed regulator provided by the embodiment of the application can provide necessary protection for the electronic speed regulator so as to prevent the electronic speed regulator from faults such as overload or short circuit and the like, and ensure the reliability and the safety of a system.
In one possible implementation manner, the current control method of the model airplane electronic speed regulator provided by the embodiment of the application further comprises the following steps:
in the case where it is determined that the present current integrated value is greater than zero, the present current integrated value is taken as an effective value.
In the case where it is determined that the present current integrated value is greater than zero, the present current integrated value is taken as an effective value, and the next logic processing may be continued.
In one possible implementation manner, the current control method of the model airplane electronic speed regulator provided by the embodiment of the application further comprises the following steps:
in the case where it is determined that the present current integrated value is smaller than or equal to zero, the present current integrated value is taken as an invalid value.
In the case where it is determined that the present current integrated value is smaller than or equal to zero, the present current integrated value is taken as an invalid value, or it is determined that an error has occurred, and the sum of the current integrated values is not taken into consideration.
In the current control method of the model airplane electronic speed regulator provided by the embodiment of the application, the current of the model airplane electronic speed regulator with different power is different. If a uniform filter duration is used, it is difficult to ensure optimal current protection is achieved for all model airplane electronic governors. Therefore, through the operation calculation logic designed by the current control method of the model airplane electronic speed regulator, the most suitable filtering time length can be matched for the model airplane electronic speed regulators with different powers, so that high-precision current protection of each model airplane electronic speed regulator is realized.
The run calculation logic may be implemented by:
collecting data: firstly, installing a current detector at a current output port of each model electronic speed regulator, and collecting current data of each model electronic speed regulator in real time.
Data classification: the collected current data is classified according to power. For example, model airplane electronic speed regulators with power greater than 100W are classified into high power categories, and model airplane electronic speed regulators with power less than or equal to 100W are classified into low power categories.
Determining a filtering duration: for each power class, an appropriate filter duration is selected based on the characteristics of its current data. For the high-power model airplane electronic speed regulator, as the current change is faster, the shorter filtering time length can be selected to better reflect the current change condition; for a low-power model airplane electronic speed regulator, because the current change is slower, a longer filtering duration can be selected to reduce noise interference.
And (3) real-time control: and controlling the current output of the electronic speed regulator of each model airplane in real time according to the collected current data and the determined filtering time length. When the current is detected to exceed the preset threshold value, the rotating speed of the speed regulator is adjusted in time or the power supply is cut off so as to prevent overload or damage of the circuit.
Dynamic adjustment: in the running process of the equipment, the current change condition of each model airplane electronic speed regulator is monitored in real time, and the filtering time length is dynamically adjusted according to actual requirements. For example, when the current change of a model airplane electronic speed regulator is abnormal, the filtering time length of the model airplane electronic speed regulator can be adjusted to better reflect the current change condition.
Through the steps, the operation calculation logic designed by the current control method of the model airplane electronic speed regulator can be matched with the most proper filtering time length aiming at the model airplane electronic speed regulators with different powers, and high-precision current protection of each model airplane electronic speed regulator is realized. The logic can not only improve the reliability and stability of the equipment, but also prolong the service life of the equipment, reduce the probability of equipment damage and reduce the maintenance cost. Meanwhile, the logic has strong adaptability and expansibility, and can be widely applied to various model airplane electronic speed regulators.
The current control method of the model airplane electronic speed regulator provided by the embodiment of the application has the following advantages:
by monitoring the heating and temperature change of the power MOS tube, the actual current value in the circuit can be calculated more accurately, and the reliability of current protection is improved.
Compared with the traditional current protection method, the current control method of the model airplane electronic speed regulator combines the current value and the heating of the power MOS tube, so that the model airplane electronic speed regulator has more comprehensiveness and practicability.
The current control method of the model airplane electronic speed regulator provided by the embodiment of the application can also find out abnormal conditions in a circuit in time, such as MOS tube faults and the like, so that protection and maintenance can be performed in time.
In a word, the current control method of the model airplane electronic speed regulator provided by the embodiment of the application realizes more accurate and reliable monitoring and protection of the actual current value in the circuit by skillfully utilizing the heat generation of the power MOS tube and combining the actual current change. The current control method has practicability and innovation, and can provide powerful guarantee for the stable operation and reliability of the electronic speed regulator.
According to the current control method of the model airplane electronic speed regulator, the current integral value can be accurately calculated based on the current integral value calculation model, and under the condition that the current integral value is greater than or equal to the preset current integral maximum threshold value, the trigger starting instruction is controlled to execute the current protection operation based on the starting instruction; therefore, the phenomenon that the electronic speed regulator burns out caused by high current can be effectively avoided; in addition, the operation experience of the electric model aircraft can be effectively improved, and the service life of the electric model aircraft can be prolonged.
In the above embodiment, a current control method of a model airplane electronic speed regulator is provided, and correspondingly, the application also provides a current control device of the model airplane electronic speed regulator. The current control device of the model airplane electronic speed regulator provided by the embodiment of the application can implement the current control method of the model airplane electronic speed regulator, and the current control device of the model airplane electronic speed regulator can be realized in a mode of software, hardware or combination of software and hardware. For example, the current control device of the model airplane electronic speed regulator can comprise integrated or separate functional modules or units to perform the corresponding steps in the methods described above.
Referring to fig. 2, a schematic diagram of a current control device of a model airplane electronic speed governor according to some embodiments of the present application is shown. Since the apparatus embodiments are substantially similar to the method embodiments, the description is relatively simple, and reference is made to the description of the method embodiments for relevant points. The device embodiments described below are merely illustrative.
As shown in fig. 2, the current control device 200 of the model airplane electronic speed governor may include:
an acquisition module 201 for acquiring a current integration value calculation model and acquiring a plurality of key parameters;
the calculation module 202 is configured to input the plurality of key parameters into the current integration value calculation model for processing, and output a corresponding current integration value;
the comparison module 203 is configured to compare the current integration value with a preset current integration maximum threshold value to obtain a corresponding comparison result when the current integration value is greater than zero;
and the control module 204 is configured to control to trigger a start command to perform a current protection operation based on the start command, if the comparison result is that the current integrated value is greater than or equal to the preset current integrated maximum threshold.
In some implementations of the embodiments of the present application, the computing module 202 is specifically configured to:
reading a plurality of key parameters, wherein the plurality of key parameters at least comprise: the method comprises the steps of a current integral value, a previous current integral value corresponding to the current integral value, a real-time sampling current value, a real-time sampling temperature value of a power MOS tube of a target model electronic speed regulator, a first constant related to the current value, a second constant related to the sampling temperature of the power MOS tube of the target model electronic speed regulator and a set initial current threshold value;
and inputting the plurality of key parameters into a current integral value calculation model for processing, and outputting a corresponding current integral value.
In some implementations of the present embodiments, the current control device 200 of the model airplane electronic governor may further include:
a sampling module (not shown in fig. 2) for:
carrying out real-time sampling treatment on the real-time sampling current value; and
and carrying out sampling processing on the real-time sampling temperature value of the power MOS tube of the target model airplane electronic speed regulator.
In some implementations of the present embodiments, the current control device 200 of the model airplane electronic governor may further include:
a first processing module (not shown in fig. 2) for taking the present current integrated value as an effective value in the case where it is determined that the present current integrated value is greater than zero.
In some implementations of the present embodiments, the current control device 200 of the model airplane electronic governor may further include:
the second processing module (not shown in fig. 2) takes the present current integrated value as an invalid value in the case where it is determined that the present current integrated value is less than or equal to zero.
In some implementations of the embodiments of the present application, the current control device 200 of the model airplane electronic speed regulator provided by the embodiments of the present application has the same beneficial effects as the current control method of the model airplane electronic speed regulator provided by the foregoing embodiments of the present application due to the same inventive concept.
A third aspect of the present invention provides a computer readable storage medium having embodied therein a current control method program for a model airplane electronic governor, which when executed by a processor, implements the steps of the current control method for a model airplane electronic governor as described in any of the preceding claims.
The invention discloses a current control method, a device and a readable storage medium of a model airplane electronic speed regulator, which can accurately calculate a current integral value based on a current integral value calculation model, and control a trigger start instruction to execute current protection operation based on the start instruction under the condition that the current integral value is greater than or equal to a preset current integral maximum threshold value; therefore, the phenomenon that the electronic speed regulator burns out caused by high current can be effectively avoided; in addition, the operation experience of the electric model aircraft can be effectively improved, and the service life of the electric model aircraft can be prolonged.
In the several embodiments provided in this application, it should be understood that the disclosed apparatus and method may be implemented in other ways. The above described device embodiments are only illustrative, e.g. the division of the units is only one logical function division, and there may be other divisions in practice, such as: multiple units or components may be combined or may be integrated into another system, or some features may be omitted, or not performed. In addition, the various components shown or discussed may be coupled or directly coupled or communicatively coupled to each other via some interface, whether indirectly coupled or communicatively coupled to devices or units, whether electrically, mechanically, or otherwise.
The units described above as separate components may or may not be physically separate, and components shown as units may or may not be physical units; can be located in one place or distributed to a plurality of network units; some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.
In addition, each functional unit in each embodiment of the present invention may be integrated in one processing unit, or each unit may be separately used as one unit, or two or more units may be integrated in one unit; the integrated units may be implemented in hardware or in hardware plus software functional units.
Those of ordinary skill in the art will appreciate that: all or part of the steps for implementing the above method embodiments may be implemented by hardware related to program instructions, and the foregoing program may be stored in a computer readable storage medium, where the program, when executed, performs steps including the above method embodiments; and the aforementioned storage medium includes: a mobile storage device, a Read-Only Memory (ROM), a random access Memory (RAM, random Access Memory), a magnetic disk or an optical disk, or the like, which can store program codes.
Alternatively, the above-described integrated units of the present invention may be stored in a computer-readable storage medium if implemented in the form of software functional modules and sold or used as separate products. Based on such understanding, the technical solutions of the embodiments of the present invention may be embodied in essence or a part contributing to the prior art in the form of a software product stored in a storage medium, including several instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute all or part of the methods described in the embodiments of the present invention. And the aforementioned storage medium includes: a removable storage device, ROM, RAM, magnetic or optical disk, or other medium capable of storing program code.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present application, and not for limiting the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the embodiments, and are intended to be included within the scope of the claims and description.
Claims (10)
1. A method for controlling current of an electronic speed regulator of a model airplane, which is characterized by comprising the following steps:
acquiring a current integral value calculation model and acquiring a plurality of key parameters;
inputting the key parameters into the current integral value calculation model for processing, and outputting a corresponding current integral value;
comparing the current integral value with a preset current integral maximum threshold value under the condition that the current integral value is larger than zero to obtain a corresponding comparison result;
and controlling to trigger a starting instruction to execute a current protection operation based on the starting instruction under the condition that the comparison result is that the current integral value is larger than or equal to the preset current integral maximum threshold value.
2. The current control method according to claim 1, wherein inputting each of the plurality of key parameters into the current integration value calculation model for processing, outputting a corresponding present current integration value, comprises:
reading the plurality of key parameters, wherein the plurality of key parameters at least comprise: the current integral value, a previous current integral value corresponding to the current integral value, a real-time sampling current value, a real-time sampling temperature value of a power MOS tube of the target model electronic speed regulator, a first constant related to the current value, a second constant related to the sampling temperature of the power MOS tube of the target model electronic speed regulator and a set initial current threshold;
and inputting the plurality of key parameters into the current integral value calculation model for processing, and outputting a corresponding current integral value.
3. The current control method according to claim 2, characterized by further comprising:
carrying out real-time sampling processing on the real-time sampling current value; and
and sampling the real-time sampling temperature value of the power MOS tube of the target model electronic speed regulator.
4. The current control method according to claim 1, characterized by further comprising:
in the case where it is determined that the present current integrated value is greater than zero, the present current integrated value is taken as an effective value.
5. The current control method according to claim 1, characterized by further comprising:
in the case where it is determined that the present current integrated value is smaller than or equal to zero, the present current integrated value is taken as an invalid value.
6. A current control device for an electronic speed regulator of a model airplane, the device comprising:
the acquisition module is used for acquiring the current integral value calculation model and acquiring a plurality of key parameters;
the calculation module is used for inputting the plurality of key parameters into the current integral value calculation model for processing and outputting a corresponding current integral value;
the comparison module is used for comparing the current integral value with a preset current integral maximum threshold value under the condition that the current integral value is larger than zero, so as to obtain a corresponding comparison result;
and the control module is used for controlling to trigger a starting instruction to execute current protection operation based on the starting instruction under the condition that the comparison result is that the current integral value is larger than or equal to the preset current integral maximum threshold value.
7. The current control device according to claim 6, wherein,
the computing module is specifically configured to:
reading the plurality of key parameters, wherein the plurality of key parameters at least comprise: the current integral value, a previous current integral value corresponding to the current integral value, a real-time sampling current value, a real-time sampling temperature value of a power MOS tube of the target model electronic speed regulator, a first constant related to the current value, a second constant related to the sampling temperature of the power MOS tube of the target model electronic speed regulator and a set initial current threshold;
and inputting the plurality of key parameters into the current integral value calculation model for processing, and outputting a corresponding current integral value.
8. The current control device according to claim 7, further comprising:
a sampling module for:
carrying out real-time sampling processing on the real-time sampling current value; and
and sampling the real-time sampling temperature value of the power MOS tube of the target model electronic speed regulator.
9. A computer-readable storage medium, characterized in that the computer-readable storage medium stores a computer program for executing the current control method according to any one of the preceding claims 1 to 5.
10. An electronic device, the electronic device comprising:
a processor;
a memory for storing executable instructions of the processor;
the processor is configured to read the executable instructions from the memory and execute the executable instructions to implement the current control method of any one of the preceding claims 1 to 5.
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