CN118790480B - Timing control method and heating time design method of aircraft electric heating deicing system - Google Patents
Timing control method and heating time design method of aircraft electric heating deicing system Download PDFInfo
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Abstract
The application relates to a time sequence control method and a heating duration design method of an aircraft electric heating deicing system, and relates to the technical field of electric heating deicing. According to the application, the temperature supercooling factor is obtained by calculating a fixed relation between the ambient temperature and the temperature supercooling factor, the speed factor is obtained by calculating a fixed relation between the Reynolds number and the speed factor, and the icing influence factor is obtained by calculating a given fixed relation between the temperature supercooling factor, the speed factor and the icing influence factor, or a fixed relation between the temperature supercooling factor, the speed factor, the liquid water content LWC, the average volume diameter MVD of water drops and the icing influence factor, so that the icing influence factor is obtained by calculating a given fixed relation between the icing influence factor and the electric heating time in the electric heating period, and therefore, the electric heating time can be obtained quickly, the time sequence control of the electric heating deicing system is realized by combining the electric heating period, and the application can be suitable for the anti-icing requirements under different working conditions.
Description
Technical Field
The invention relates to the technical field of aircraft electric heating deicing, in particular to a time sequence control method and a heating duration design method of an aircraft electric heating deicing system.
Background
The icing of the aircraft can damage the original flow field, cause the increase of lift force reduction resistance, damage the stability and safety of flight operation and the like, brings great potential safety hazards to the flight safety, and becomes the key point of the current aviation industry research. In order to ensure flight safety, various deicing methods are developed, wherein the electrothermal deicing technology has the advantages of high operability, no damage to flight aerodynamic performance and the like, and becomes an important deicing method at present. The electric heating anti-icing system converts electric energy into heat energy through the electric heating element to heat the surface of the protective part, so that supercooled water drops which strike the surface of the aircraft are heated and evaporated, and further icing is avoided. Similarly, ice accumulation may occur in wind turbines, and wind turbines are also widely equipped with electrical heating systems.
However, how to realize the time sequence control of an aircraft electric heating deicing system applicable to different working conditions is still a problem to be solved.
Disclosure of Invention
The application aims to solve the technical problem of providing a time sequence control method and a heating duration design method for an aircraft electric heating deicing system, which have the characteristic of being capable of realizing time sequence control of the aircraft electric heating deicing system under different working conditions.
In a first aspect, an embodiment provides a method for controlling a time sequence of an aircraft electrical heating deicing system, including:
Obtaining an ambient temperature T and a Reynolds number R e;
Based on the formula Calculating a temperature supercooling factorBased on the formulaCalculating a speed factor; Wherein K represents the kelvin;
Based on the formula Calculating icing influencing factors; Wherein exp represents a natural exponential function;
Based on the formula Calculating an electrical heating cycleIn (2) the heating duration of；
Acquiring an electric heating period;
And realizing the time sequence control of the electric heating deicing system based on the electric heating period and the heating duration.
In one embodiment, the electrical heating cycle=120s。
In a second aspect, an embodiment provides a method for controlling a time sequence of an aircraft electrical heating deicing system, including:
Obtaining an ambient temperature T, a Reynolds number R e, a liquid water content LWC and a water drop average volume diameter MVD;
Based on the formula Calculating a temperature supercooling factorBased on the formulaCalculating a speed factor; Wherein K represents the kelvin;
Based on the formula Calculating icing influencing factors; Wherein exp represents a natural exponential function, A and B represent intermediate variables,，；
Based on the formulaCalculating an electrical heating cycleIn (2) the heating duration of；
Acquiring an electric heating period;
And realizing the time sequence control of the electric heating deicing system based on the electric heating period and the heating duration.
In one embodiment, the electrical heating cycle=120s。
In a third aspect, an embodiment provides a method for designing a heating duration in timing control of an aircraft electrical heating deicing system, including:
Design an electrical heating cycle based on a preset protection standard for an electrical heating deicing system In (2) the heating duration ofComprising:
calculating heating time length required by reaching preset protection standard of electric heating deicing system under different working conditions ；
Based on temperature supercooling factorAnd heating time periodFitting a first relationship to the relationship;
Based on a speed factor And heating time periodFitting a second relationship to the relationship;
based on the liquid water content LWC and the heating duration Fitting a third relationship to the relationship curve;
Based on the mean volume diameter MVD of the water drops and the heating time Fitting a fourth relationship to the relationship;
defining an icing influence factor based on the first, second, third and fourth relations ；
Based on icing influencing factorsCalculating an electrical heating cycleIn (2) the heating duration of。
In one embodiment, the temperature-based supercooling factorAnd heating time periodA first relationship, comprising:
；
Based on the speed factor And heating time periodA second relationship, comprising:
；
Based on the liquid water content LWC and the heating time A third relationship, comprising:
；
the average volume diameter MVD and the heating time length of the water drop A fourth relationship, comprising:
。
In one embodiment, the defining the icing factor based on the first, second, third, and fourth relationships includes:
。
in one embodiment, the method is based on icing influencing factors Calculating an electrical heating cycleIn (2) the heating duration ofComprising the following steps:
。
In one embodiment, the defining the icing factor based on the first, second, third, and fourth relationships includes:
；
wherein A and B are intermediate variables, ，。
In one embodiment, the method is based on icing influencing factorsCalculating an electrical heating cycleIn (2) the heating duration ofComprising the following steps:
。
The beneficial effects of the invention are as follows:
according to the application, the temperature supercooling factor is obtained by calculating a fixed relation between the ambient temperature and the temperature supercooling factor, the speed factor is obtained by calculating a fixed relation between the Reynolds number and the speed factor, and the icing influence factor is obtained by calculating a given fixed relation between the temperature supercooling factor, the speed factor and the icing influence factor, or a fixed relation between the temperature supercooling factor, the speed factor, the liquid water content LWC, the average volume diameter MVD of water drops and the icing influence factor, so that the icing influence factor is obtained by calculating a given fixed relation between the icing influence factor and the electric heating time in the electric heating period, and therefore, the electric heating time can be obtained quickly, the time sequence control of the electric heating deicing system is realized by combining the electric heating period, and the application can be suitable for the anti-icing requirements under different working conditions.
Drawings
FIG. 1 is a schematic flow chart of a method for designing heating duration in time sequence control of an aircraft electrical heating deicing system according to one embodiment of the present application;
FIG. 2 is a heating duration of one embodiment of the application And a temperature supercooling factorIs a schematic diagram of the relationship of (1);
FIG. 3 is a heating duration of one embodiment of the application And a velocity factorIs a schematic diagram of the relationship of (1);
FIG. 4 is a heating duration of one embodiment of the application A schematic diagram of the relationship between the water content LWC and the liquid state;
FIG. 5 is a heating duration of one embodiment of the application And average volume diameter of water drop schematic diagram of MVD relationship;
FIG. 6 is a heating duration of one embodiment of the application Schematic diagram of influencing factors;
FIG. 7 is a heating duration of one embodiment of the application And icing influencing factorIs a schematic diagram of the relationship of (1);
FIG. 8 is a heating duration of another embodiment of the present application And icing influencing factorIs a schematic diagram of the relationship of (1);
FIG. 9 is a flow chart of a method for controlling the timing of an aircraft electrical heating deicing system in accordance with one embodiment of the present application;
Fig. 10 is a flow chart of a timing control method of an aircraft electrical heating deicing system according to another embodiment of the present application.
Detailed Description
The application will be described in further detail below with reference to the drawings by means of specific embodiments. Wherein like elements in different embodiments are numbered alike in association. In the following embodiments, numerous specific details are set forth in order to provide a better understanding of the present application. However, one skilled in the art will readily recognize that some of the features may be omitted, or replaced by other elements, materials, or methods in different situations. In some instances, related operations of the present application have not been shown or described in the specification in order to avoid obscuring the core portions of the present application, and may be unnecessary to persons skilled in the art from a detailed description of the related operations, which may be presented in the description and general knowledge of one skilled in the art.
Furthermore, the described features, operations, or characteristics of the description may be combined in any suitable manner in various embodiments. Also, various steps or acts in the method descriptions may be interchanged or modified in a manner apparent to those of ordinary skill in the art. Thus, the various orders in the description and drawings are for clarity of description of only certain embodiments, and are not meant to be required orders unless otherwise indicated.
The numbering of the components itself, e.g. "first", "second", etc., is used herein merely to distinguish between the described objects and does not have any sequential or technical meaning. The term "coupled" as used herein includes both direct and indirect coupling (coupling), unless otherwise indicated.
For the purpose of illustrating the inventive concepts of the present application, a brief description of aircraft electrical heating deicing techniques is provided below.
Icing can be simultaneously affected by multiple parameters such as ambient temperature, water drop particle size, liquid water content, incoming flow speed and the like, the anti-icing requirements under different working conditions are different, the required electric heating time is different, but the current lack of knowledge on the heating time requirements under different environments is insufficient, and the design of electric heating time sequence is not studied deeply.
In view of this, the embodiment of the application provides a time sequence control method and a heating time length design method for an aircraft electric heating deicing system, and the heating time length is calculated based on a relation formula of the given influence factors of the electric heating time length and the heating time length, so that the time sequence control of the electric heating deicing system is realized by combining an electric heating period, and the method and the device can be suitable for anti-icing requirements under different working conditions.
For the sake of clarity, the following description will first be made of a method for designing a heating duration in the time sequence control of an aircraft electrical heating deicing system.
In one embodiment, the application provides a heating duration design method in the time sequence control of an aircraft electric heating deicing system, which comprises the following steps: design an electrical heating cycle based on a preset protection standard for an electrical heating deicing systemIn (2) the heating duration ofReferring to fig. 1, the method includes:
Step S10, calculating heating time length required by reaching preset protection standards of the electric heating deicing system under different working conditions 。
The following describes in detail an NACA 0012 airfoil as an example.
In general, the protection standard of the electric heating deicing system is set as follows: the temperature of the airfoil leading edge stagnation point is greater than 0 degrees celsius, namely 273.15K, after a heating cycle.
The specific calculation conditions are shown in table 1.
Table 1 calculation of the working conditions
，
Wherein V in table 1 represents the incoming flow rate.
Step S20, based on the temperature supercooling factorAnd heating time periodFitting the first relation to the relation.
Wherein the temperature supercooling factor; T represents the ambient temperature and K represents the Kelvin temperature. Referring to fig. 2, the heating time periodAnd temperature supercooling factorPositively correlated, as the ambient temperature decreases, the length of heating requiredAnd the improvement is continuous. Then a first relationship can be derived:
。
Step S30, based on the speed factor And heating time periodFitting a second relationship to the relationship.
Wherein the velocity factor; R e represents the Reynolds number. Referring to FIG. 3, the velocity factorThe higher the incoming flow velocity V, the greater the heating time period requiredThe larger. A second relationship can be derived:
。
Step S40, based on the liquid water content LWC and the heating time period Fitting a third relationship to the relationship.
Referring to fig. 4, the heating time periodPositively correlated with the liquid water content LWC, the higher the heating demand, the longer the heating time period requiredThe larger. A third relationship can be derived:
。
step S50, based on the average volume diameter MVD of the water drops and the heating time period Fitting a fourth relationship to the relationship of (c).
Referring to fig. 5, the heating time periodThe larger the water droplet mean volume diameter MVD, the higher the heating demand, the longer the heating time required, which is positively correlated with the water droplet mean volume diameter MVDThe larger. A fourth relationship can be obtained:
。
step S60, defining icing influence factors based on the first, second, third and fourth relations 。
Referring to fig. 6, it can be seen from the analysis of fig. 6 that the temperature supercooling factor change has an influence on the heating period of 13 to 69, the velocity factor has an influence on the heating period of 12 to 22, the liquid water content LWC has an influence on the heating period of 12 to 14.5, and the average volume diameter MVD of the water droplets has an influence on the heating period of 12.5 to 14. It can be seen that the liquid water content LWC has an influence of (14.5-12)/(69-13) = 0.0446, and the average volume diameter MVD of the water droplets has an influence of (14-12.5)/(69-13) = 0.0268, both of which are less than 5%, compared with the most significant speed factor.
In view of the above analysis, in one embodiment, since the influence of the liquid water content LWC and the average volume diameter MVD of the water droplets is small, compared with the temperature supercooling factor and the velocity factor, it is possible to define the icing influence factor for rapidly obtaining the heating time period in the electric heating cycle, which is negligibleThe method comprises the following steps:
。
In one embodiment, icing influencing factors may be defined for more precise heating durations and more tightly controlled durations The method comprises the following steps:
；
wherein A and B are intermediate variables, ，。
Step S70, based on icing influencing factorsCalculating an electrical heating cycleIn (2) the heating duration of。
Based on the above embodiment, in one embodiment, when the influence of the liquid water content LWC and the average volume diameter MVD of the water droplets is not taken into consideration, the obtained heating period isCan be expressed as:
。
in this case, the heating time period And icing influencing factorRefer to FIG. 7.
In one embodiment, the heating period is obtained when considering the influence of the liquid water content LWC and the average volume diameter MVD of the water dropletsCan be expressed as:
。
in this case, the heating time period And icing influencing factorRefer to FIG. 8.
In one embodiment, the electrical heating cycleCan be set to 120s, composed of=+At the time of heatingIn the case of (2), the power-off time period can be obtained。
Based on the embodiment, the control time sequence of the electric heating deicing system suitable for different working conditions can be obtained, so that the time sequence control is realized.
Based on the above design method, please refer to fig. 9, in one embodiment, the method for controlling the time sequence of the aircraft electric heating deicing system provided by the application includes:
In step S100, the ambient temperature T and the Reynolds number R e are obtained.
As will be appreciated by those skilled in the art, both the ambient temperature T and the reynolds number R e can be obtained directly based on an on-board sensor.
Step S200, based on the formulaCalculating a temperature supercooling factorBased on the formulaCalculating a speed factor. Wherein K represents the kelvin temperature.
Based on the acquired ambient temperature T and Reynolds number R e, the temperature supercooling factor is calculated by the ambient temperature TCan obtain the temperature supercooling factorBy Reynolds number R e and velocity factorCan obtain the velocity factor。
Step S300, based on the formulaCalculating icing influencing factors. Where exp represents a natural exponential function.
Based on temperature supercooling factorSpeed factorAnd icing influencing factorsCan quickly obtain icing influencing factorsThereby rapidly obtaining the icing factor。
Step S400, based on the formulaCalculating an electrical heating cycleIn (2) the heating duration of。
Based on icing influencing factorsAnd heating time periodCan quickly obtain the heating time lengthThereby rapidly obtaining the heating time length。
Step S500, an electrical heating cycle is acquired.
In one embodiment, the electrical heating cycleCan be set to 120s, composed of=+At the time of heatingIn the case of (2), the power-off time period can be obtained。
Step S600, the time sequence control of the electric heating deicing system is realized based on the electric heating period and the heating duration.
In the embodiment of steps S100 to S600, the heating period is due to the liquid water content LWC and the average volume diameter MVD of the water dropletsThe influence of the liquid water content LWC and the average volume diameter MVD of water drops is ignored, and the heating time length is obtained directly based on the ambient temperature T and the Reynolds number R e Therefore, the control time sequence of the electric heating deicing system is obtained rapidly, and the rapid control of the time sequence of the electric heating deicing system is realized.
Referring to fig. 10, in one embodiment, the method for controlling a time sequence of an aircraft electrical heating deicing system provided by the application includes:
In step S1000, the ambient temperature T, the reynolds number R e, the liquid water content LWC, and the average volume diameter MVD of the water droplets are obtained.
It will be appreciated by those skilled in the art that the ambient temperature T, reynolds number R e, liquid water content LWC, and average water droplet volume diameter MVD can all be obtained directly based on-board sensors.
Step S2000, based on formulaCalculating a temperature supercooling factorBased on the formulaCalculating a speed factor. Wherein K represents the kelvin temperature.
Based on the acquired ambient temperature T and Reynolds number R e, the temperature supercooling factor is calculated by the ambient temperature TCan obtain the temperature supercooling factorBy Reynolds number R e and velocity factorCan obtain the velocity factor。
Step S3000, based on formulaCalculating icing influencing factors. Wherein exp represents a natural exponential function, A and B represent intermediate variables,，。
Based on the ambient temperature T, the Reynolds number R e, the liquid water content LWC, the average volume diameter MVD of water drops and the icing influence factorCan quickly obtain icing influencing factorsThereby rapidly obtaining the icing factor。
Step S4000, based on the formulaCalculating an electrical heating cycleIn (2) the heating duration of。
Based on icing influencing factorsAnd heating time periodCan quickly obtain the heating time lengthThereby rapidly obtaining the heating time length。
Step S5000, an electric heating cycle is acquired.
In one embodiment, the electrical heating cycleCan be set to 120s, composed of=+At the time of heatingIn the case of (2), the power-off time period can be obtained。
And step S6000, realizing time sequence control of the electric heating deicing system based on the electric heating period and the heating duration.
In the embodiment of step S1000 to step S6000, the temperature supercooling factor is comprehensively consideredSpeed factorThe liquid water content LWC and the average volume diameter MVD of the water drops for the heating periodThe influence of the electric heating deicing system control time sequence can be obtained more accurately, the electric heating deicing system control time sequence can be obtained rapidly, and accurate and rapid control of the electric heating deicing system time sequence is realized.
An embodiment of the present application provides a computer readable storage medium having a program stored thereon, the stored program including a method capable of being loaded by a processor and processing any of the embodiments described above.
Those skilled in the art will appreciate that all or part of the functions of the various methods in the above embodiments may be implemented by hardware, or may be implemented by a computer program. When all or part of the functions in the above embodiments are implemented by means of a computer program, the program may be stored in a computer readable storage medium, and the storage medium may include: read-only memory, random access memory, magnetic disk, optical disk, hard disk, etc., and the program is executed by a computer to realize the above-mentioned functions. For example, the program is stored in the memory of the device, and when the program in the memory is executed by the processor, all or part of the functions described above can be realized. In addition, when all or part of the functions in the above embodiments are implemented by means of a computer program, the program may be stored in a storage medium such as a server, another computer, a magnetic disk, an optical disk, a flash disk, or a removable hard disk, and the program in the above embodiments may be implemented by downloading or copying the program into a memory of a local device or updating a version of a system of the local device, and when the program in the memory is executed by a processor.
The foregoing description of the invention has been presented for purposes of illustration and description, and is not intended to be limiting. Several simple deductions, modifications or substitutions may also be made by a person skilled in the art to which the invention pertains, based on the idea of the invention.
Claims (9)
1. A method for controlling the timing sequence of an aircraft electrical heating deicing system, comprising:
Obtaining an ambient temperature T and a Reynolds number R e;
Based on the formula Calculating a temperature supercooling factorBased on the formulaCalculating a speed factor; Wherein K represents the kelvin;
Based on the formula Calculating icing influencing factors; Wherein exp represents a natural exponential function;
Based on the formula Calculating an electrical heating cycleIn (2) the heating duration of；
Acquiring an electric heating period;
And realizing the time sequence control of the electric heating deicing system based on the electric heating period and the heating duration.
2. A method of timing control of an aircraft electrical heating deicing system as set forth in claim 1, wherein said electrical heating cycle=120s。
3. A method for controlling the timing sequence of an aircraft electrical heating deicing system, comprising:
Obtaining an ambient temperature T, a Reynolds number R e, a liquid water content LWC and a water drop average volume diameter MVD;
Based on the formula Calculating a temperature supercooling factorBased on the formulaCalculating a speed factor; Wherein K represents the kelvin;
Based on the formula Calculating icing influencing factors; Wherein exp represents a natural exponential function, A and B represent intermediate variables,，；
Based on the formulaCalculating an electrical heating cycleIn (2) the heating duration of；
Acquiring an electric heating period;
And realizing the time sequence control of the electric heating deicing system based on the electric heating period and the heating duration.
4. A method of timing control of an aircraft electrical heating deicing system as set forth in claim 3, wherein said electrical heating cycle=120s。
5. The design method of the heating time length in the time sequence control of the aircraft electric heating deicing system is characterized by comprising the following steps of:
Design an electrical heating cycle based on a preset protection standard for an electrical heating deicing system In (2) the heating duration ofComprising:
calculating heating time length required by reaching preset protection standard of electric heating deicing system under different working conditions ；
Based on temperature supercooling factorAnd heating time periodA first relationship, comprising:
；
Wherein, ；
Based on a speed factorAnd heating time periodA second relationship, comprising:
；
Wherein, Exp represents a natural exponential function;
based on the liquid water content LWC and the heating duration A third relationship, comprising:
；
Based on the mean volume diameter MVD of the water drops and the heating time A fourth relationship, comprising:
；
defining icing-affecting factors based on the first and second relationships Or defining the icing influence factor based on the first, second, third and fourth relations；
Based on icing influencing factorsCalculating an electrical heating cycleIn (2) the heating duration of。
6. The method for designing a heating time period in time sequence control of an aircraft electrical heating deicing system according to claim 5, wherein, in the case of defining the icing influence factor based on the first relational expression and the second relational expression, comprising:
。
7. The method for designing heating time length in time sequence control of aircraft electric heating deicing system according to claim 6, wherein said method is based on icing influence factor Calculating an electrical heating cycleIn (2) the heating duration ofComprising the following steps:
。
8. A method of designing a heating duration in time series control of an aircraft electrical heating deicing system as set forth in claim 5, wherein defining the icing influence factor based on the first relationship, the second relationship, the third relationship, and the fourth relationship comprises:
；
wherein A and B are intermediate variables, ，。
9. The method for designing heating duration in time sequence control of aircraft electrical heating deicing system according to claim 8, wherein said icing-based influencing factorCalculating an electrical heating cycleIn (2) the heating duration ofComprising the following steps:
。
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