CN108820227B - Predictive ice prevention and removal method utilizing graphene heating film - Google Patents
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- 238000010438 heat treatment Methods 0.000 title claims abstract description 123
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- 229910021389 graphene Inorganic materials 0.000 title claims abstract description 36
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- 238000012544 monitoring process Methods 0.000 claims abstract description 6
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- 238000000611 regression analysis Methods 0.000 claims description 5
- 238000012360 testing method Methods 0.000 claims description 4
- 238000005265 energy consumption Methods 0.000 abstract description 6
- 230000000737 periodic effect Effects 0.000 abstract description 4
- 238000013021 overheating Methods 0.000 description 10
- 238000012937 correction Methods 0.000 description 8
- 238000001514 detection method Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 4
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/20—Means for detecting icing or initiating de-icing
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Abstract
The invention discloses a predictive deicing prevention method by utilizing a graphene heating film, which aims to accurately deice and solve the problem of high deicing energy consumption of flight equipment and comprises the following steps: inputting the acquired current environmental parameter information into an icing prediction system to obtain a predicted temperature interval in the next flight state; judging whether the flight equipment is frozen or not, if so, starting a heating assembly to heat the flight equipment according to the type of a preset ice layer; and monitoring whether the flight equipment has an ice layer in the next flight state, and if so, adjusting the heating power of the heating assembly to eliminate the ice deposition of the flight equipment. The temperature interval in the next flight state is predicted by the icing prediction system so as to adjust the heating assembly, and the problem of high energy consumption of periodic heating or continuous heating is avoided when the icing problem of the flight equipment is prevented.
Description
Technical Field
The invention relates to the field of artificial intelligence, in particular to a predictive deicing method based on machine learning by using a graphene heating film as a heating element and using an extreme learning machine as a classification model.
Background
No matter in aviation or wind power generation or other engineering fields, this phenomenon of freezing can all produce very big influence to equipment normal operating, can cause efficiency to reduce, causes the incident even, causes certain injury. In terms of flight, icing on the wings of the aircraft can reduce the flight performance of the aircraft, change the flight characteristics, increase the weight of the aircraft, affect the normal operation of related systems, and the fallen ice layer can blow to the empennage of the aircraft along with airflow to damage the structure of the aircraft body and cause damage to the front edge of the empennage. The conventional electric heating deicing system generally adopts periodic heating or continuous heating, and an airplane icing sensor automatically switches on or off a power supply system after sensing an icing electric signal, but the method cannot accurately and timely deice the airplane, so that an ice layer cannot be timely removed, and the continuous heating has high energy consumption, resource consumption and low efficiency.
Disclosure of Invention
In order to solve the problem of high energy consumption for deicing flight equipment, the invention provides a predictive deicing prevention method by using a graphene heating film, which can prevent equipment from icing, eliminate accumulated ice in the shortest time even if icing occurs, improve deicing efficiency, ensure equipment safety, achieve an energy-saving effect and reduce loss.
In order to achieve the above object, the present invention provides a predictive ice prevention and removal method using a graphene heating film, which includes the steps of:
inputting the acquired current environmental parameter information into an icing prediction system to obtain a predicted temperature interval in the next flight state, wherein the icing prediction system is established based on historical flight environmental parameter data;
judging whether the flight equipment is frozen or not, if so, starting a heating assembly to heat the flight equipment according to the type of a preset ice layer; if not, judging whether the predicted temperature interval is within a preset icing threshold value, and if so, heating the flight equipment through a heating assembly;
and monitoring whether the flight equipment has an ice layer in the next flight state, and if so, adjusting the heating power of the heating assembly to eliminate the ice deposition of the flight equipment.
Preferably, the step of starting the heating assembly to heat the flying device according to the preset ice layer type comprises the following steps:
configuring different heating powers for the ice layer types;
and judging the type of the ice layer to which the ice is attached, and heating the flight equipment by adopting preset heating power according to the determined type of the ice layer.
Preferably, the environmental parameters include a plurality of time of flight, altitude of flight, temperature of flight, wind speed.
Preferably, the method for preventing and removing ice in a predictive manner using the graphene heating film further includes:
acquiring the heating temperature on the flight equipment;
and judging whether the heating temperature exceeds a preset threshold value, and if so, reducing the heating power of the heating assembly.
Preferably, the icing prediction system is established based on the environmental parameter data of the historical flight according to a stepwise regression analysis method and based on the environmental parameter data of the historical flight.
Preferably, the establishing according to the stepwise regression analysis method and based on the environmental parameter data of the historical flight comprises the following steps:
the environment parameter data comprises a plurality of independent variables of flight time, flight height, flight temperature and wind speed, the independent variables are subjected to significance test, and the independent variable with the highest significance is used as a first independent variable and introduced into a regression equation;
and on the basis of the first independent variable, continuously introducing other independent variables into the regression equation until the regression coefficient of the rest independent variables is zero, thus establishing the icing prediction system.
Preferably, the heating assembly comprises a graphene heating film embedded between a base layer and a skin of the flying apparatus.
Preferably, the heating assembly further comprises a thermal insulation layer disposed between the graphene heating film and the base layer.
Compared with the prior art, the method for preventing and removing ice by utilizing the prediction type graphene heating film has the following beneficial effects:
according to the method for predicting type ice prevention and removal by utilizing the graphene heating film, the temperature range in the next flight state is predicted by the icing prediction system so as to adjust the heating assembly, and the problem of high energy consumption of periodic heating or continuous heating is avoided when the icing problem of flight equipment is prevented. Meanwhile, the invention also realizes good control on the heating of the flight equipment by monitoring the ice layer and the heating temperature.
According to the method for preventing and removing ice by utilizing the prediction type of the graphene heating film, the extremely high thermal conductivity performance and the advantages of high strength and ultrathin performance of the graphene material are adopted, the graphene material can be tightly embedded into components such as a flight equipment skin, the uniform heating is ensured, the heating thickness is reduced, and the ice removing effect can be greatly improved.
Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention.
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The foregoing and/or additional aspects and advantages of the present invention will become apparent and readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings of which:
fig. 1 is a schematic view of an application scenario of predictive deicing using a graphene heating film according to an embodiment of the present invention;
fig. 2 is a schematic flow chart illustrating a method for predictive deicing prevention using a graphene heating film according to an embodiment of the present invention;
fig. 3 is a schematic structural diagram of a graphene film embedded between a base layer and a skin according to a predictive ice prevention and removal method using a graphene heating film according to an embodiment of the present invention.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative only and should not be construed as limiting the invention.
Referring to fig. 1, a method for preventing ice from being removed by using a graphene heating film according to an embodiment of the present invention is applied to an ice-removing heating system of flight equipment shown in fig. 1, as shown in figure 1, the anti-icing and heating system for the flight equipment comprises a sensor for collecting environmental parameters, a signal converter, an ice layer type detection system, an ice prediction system, a heating assembly, a heating controller, a correction controller and an overheating controller, wherein the sensor is arranged on the flight equipment and used for converting the collected environmental information into an electric signal, the signal converter is connected with the sensor and used for converting the collected environmental information into the electric signal, the ice layer type detection system is used for judging the type of ice, the ice prediction system is used for predicting the temperature information of the next flight state and is connected with the ice layer type detection system, the heating assembly is used for heating the flight equipment, the heating controller is connected with the ice prediction system, the correction controller is used for correcting the working state of the heating controller, the overheating controller is used for preventing overheating, wherein, the correction controller, the overheating controller and the ice layer type detection system are respectively connected with the signal converter.
In practice, in the flying process of an airplane, a sensor continuously monitors data, various signals in different forms are converted into electric signals through a signal converter, the electric signals are input into an icing prediction system, the space temperature of the parts which are easy to be iced, such as airplane wings, and the like in the next stage is predicted, and a heating controller is started to control a heating assembly to heat the parts, such as the airplane wings, and the like. Meanwhile, sensor signals are transmitted to the correction controller all the time, for example, whether an ice layer appears on the wing is monitored by the optical fiber sensor, when the ice layer appears, the heating power of the heating assembly controlled by the icing prediction system is insufficient, and the correction controller can adjust the working power of the heating assembly to eliminate accumulated ice as correction adjustment. The overheating controller is an overheating protection controller, when the temperature of the wing and other parts is too high, and the temperature signal of the sensor is transmitted to the overheating controller, the heating power of the heating assembly can be controlled, and deformation caused by high temperature is prevented.
In some embodiments, the heating controller, the correction controller and the overheating controller are all single-chip modules, and the model of a main control chip of the single-chip modules is STM32F103ZET 6.
Referring to fig. 2, the following description will be made by taking an example that a method for preventing ice from being predicted by using a graphene heating film according to an embodiment of the present invention is applied to an ice-preventing and heating system for flight equipment shown in fig. 1, where the method for preventing ice from being predicted by using a graphene heating film includes the following steps:
step S1: and inputting the acquired current environmental parameter information into an icing prediction system to obtain a predicted temperature interval in the next flight state, wherein the icing prediction system is established based on historical flight environmental parameter data.
In some embodiments, the icing prediction system is established based on the environmental parameter data of the historical flight according to a stepwise regression analysis method and based on the environmental parameter data of the historical flight, and specifically includes the following steps:
the environment parameter data comprises a plurality of independent variables of flight time, flight height, flight temperature and wind speed, the independent variables are subjected to significance test, and the independent variable with the highest significance is used as a first independent variable and introduced into a regression equation;
and on the basis of the first independent variable, continuously introducing other independent variables into the regression equation until the regression coefficient of the rest independent variables is zero, and thus establishing the icing prediction system.
In order to facilitate understanding of the icing prediction system establishment process, the following provides an example step of a stepwise regression analysis method, wherein, considering that the steps of introducing the independent variables are basically the same, the following explanation is given by taking the introduction of the first independent variable as an example. Specifically, assuming that the influence factors, i.e., the independent variables are four, which are X1, X2, X3 and X4, respectively, and there are n sets of historical environmental parameters used, which may correspond to flight time, flight altitude, flight temperature and wind speed, and meanwhile, for convenience of description, the relevant specific data are omitted here, and assuming that the introduced first independent variable is X4, see the historical environmental parameter data table of table one:
table-historical environmental parameter data table
| Numbering | Time of flight (X1) | Flying height (X2) | Flight temperature (X3) | Wind speed (X4) | Regression equation (Y) |
| 1 | * | * | * | * | * |
| 2 | * | * | * | * | * |
| 3 | * | * | * | * | * |
| 4 | * | * | * | * | * |
| ...... | ...... | ...... | ...... | ...... | ...... |
| n | * | * | * | * | * |
First, for four independent variables, the partial regression sum of squares is calculated according to the following formula
Wherein t is the number of transformation steps, and t is taken as 1.
By calculation, four μ s were comparediIt can be known which factor has the largest partial regression value, i.e. the value has the largest regression contribution to Y, and then the argument, i.e. X4, is selected as the priority;
secondly, for the significance test of the introduced factors, considering that the introduced first independent variable is X4, the statistic is calculated as follows:
in some embodiments, when F4(1) > F0.05(1, n-2), indicating that the contribution of the introduced factor X4 to the regression equation is significant, X4 should be introduced into the regression equation;
again, the Gaussian-Adam transform of the matrix R (0)
Carrying out matrix transformation by taking X4 as a principal element, wherein the transformation formula is as follows
a. Row and column of non-principal element
b. Principal element in the line (except principal element)
c. Principal element in column (except principal element)
d. Principal component
The transformation process requires proceeding in the order a → d. Recording the transformed matrix as R (1), (t ═ 1);
finally, the result of introducing X4 into the regression equation;
the standard regression coefficients, i.e. the regression coefficients found using the normalized data, are:
the standard form of the regression equation can be found, then the sum of the remaining squares
Where l is 1, indicating that the equation incorporates only one variable
The general regression coefficients are:
the constant term is:
the general form of the regression equation is:
it should be noted that the above is only the introduction of one independent variable, and the introduction of other independent variables is to continue to introduce other independent variables into the regression equation on the basis of the first independent variable, and if the regression coefficient of the remaining independent variables is zero, the icing prediction system is identified to be established, and therefore details are not repeated.
Step S2: judging whether the flight equipment is frozen or not, if so, starting a heating assembly to heat the flight equipment according to the type of a preset ice layer; if not, judging whether the predicted temperature interval is within a preset icing threshold value, and if so, heating the flight equipment through a heating assembly.
In some embodiments, the step of activating the heating assembly to heat the flying apparatus according to the preset ice layer type comprises the following steps:
configuring different heating powers for the ice layer types;
judging the type of the ice layer to which the ice is attached, and heating the flight equipment by adopting preset heating power according to the determined type of the ice layer.
Exemplarily, the ice layer types include rime, frost, and a plurality of ice layers divided according to a preset ice layer thickness.
Step S3: and monitoring whether the flight equipment has an ice layer in the next flight state, and if so, adjusting the heating power of the heating assembly to eliminate the ice deposition of the flight equipment.
In detail, whether the ice layer appears or not in the next flight state of the flight device is monitored by the optical fiber sensor.
In some embodiments, the method for preventing and killing ice using a graphene heating film further comprises:
acquiring the heating temperature on the flight equipment;
and judging whether the heating temperature exceeds a preset threshold value, and if so, reducing the heating power of the heating assembly.
Specifically, the heating temperature on the flight equipment is acquired by a temperature sensor.
It should be understood that the steps S2, S3 and the step of reducing the heating power of the heating assembly correspond to the heating controller connected to the icing prediction system, the correction controller for correcting the operation state of the heating controller and the overheating controller for preventing overheating as shown in fig. 1, respectively.
Referring to fig. 3, preferably, the heating assembly includes a graphene heating film embedded between a base layer and a skin of the flying apparatus.
In order to prevent heat from being conducted to the base layer and to improve the efficiency of heating, the heating assembly further includes an insulating layer disposed between the graphene heating film and the base layer.
Compared with the prior art, the method for preventing and removing ice by utilizing the prediction type graphene heating film has the following beneficial effects:
according to the method for predicting type ice prevention and removal by utilizing the graphene heating film, the temperature range in the next flight state is predicted by the icing prediction system so as to adjust the heating assembly, so that the problem of icing of flight equipment is solved, and the problem of high energy consumption caused by periodic heating or continuous heating is avoided. Meanwhile, the invention also realizes good control of the deicing process of the flight equipment by monitoring the ice layer and the heating temperature.
According to the method for preventing and removing ice by utilizing the prediction type of the graphene heating film, the extremely high thermal conductivity performance and the advantages of high strength and ultrathin performance of the graphene material are adopted, the graphene material can be tightly embedded into components such as a flight equipment skin, the uniform heating is ensured, the heating thickness is reduced, and the ice removing effect can be greatly improved.
The foregoing is only a partial embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and decorations can be made without departing from the principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.
Claims (4)
1. A method for preventing and removing ice through prediction of a graphene heating film is characterized by comprising the following steps:
inputting the acquired current environmental parameter information into an icing prediction system to obtain a predicted temperature interval in the next flight state, wherein the icing prediction system is established based on historical flight environmental parameter data, and the environmental parameters comprise a plurality of flight time, flight height, flight temperature and wind speed;
judging whether the flight equipment is frozen or not, if so, starting a heating assembly to heat the flight equipment according to the type of a preset ice layer; if not, judging whether the predicted temperature interval is within a preset icing threshold value, and if so, heating the flight equipment through a heating assembly;
monitoring whether an ice layer appears on the flight equipment in the next flight state, if so, adjusting the heating power of a heating assembly to eliminate the ice deposition of the flight equipment;
the method for heating the flying equipment by starting the heating assembly according to the type of the preset ice layer comprises the following steps:
configuring different heating powers for the ice layer types;
judging the type of the ice layer to which the ice is attached, and heating the flight equipment by adopting preset heating power according to the determined type of the ice layer;
the icing prediction system is established based on the environmental parameter data of the historical flight according to a stepwise regression analysis method and based on the environmental parameter data of the historical flight, and comprises the following steps:
the environment parameter data comprises a plurality of independent variables in flight time, flight height, flight temperature and wind speed, the independent variables are subjected to significance test, and the independent variable with the highest significance is used as a first independent variable and introduced into a regression equation;
and on the basis of the first independent variable, continuously introducing other independent variables into the regression equation until the regression coefficient of the rest independent variables is zero, thus establishing the icing prediction system.
2. The method for preventing and removing ice using a graphene heating film according to claim 1, wherein the method for preventing and removing ice using a graphene heating film further comprises:
acquiring the heating temperature on the flight equipment;
and judging whether the heating temperature exceeds a preset threshold value, and if so, reducing the heating power of the heating assembly.
3. The method of predictive anti-icing and deicing with graphene heating film according to claim 1, wherein said heating assembly comprises a graphene heating film embedded between a base layer and a skin of said flying apparatus.
4. The method of predictive anti-icing and deicing with graphene heating film according to claim 3, wherein said heating assembly further comprises an insulating layer disposed between said graphene heating film and said base layer.
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| WO2017114639A1 (en) * | 2015-12-29 | 2017-07-06 | fos4X GmbH | Method for predicting the accumulation of ice on a rotor blade of a wind turbine and the use thereof |
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| US7502717B2 (en) * | 2006-04-18 | 2009-03-10 | Honeywell International Inc. | Method for predicting air cycle machine turbine ice formation and shedding and journal bearing wear |
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|---|---|---|---|---|
| CN101411243B (en) * | 2004-06-10 | 2012-03-28 | 贝尔直升机泰克斯特龙公司 | Anti-icing system for radomes |
| CN102438903A (en) * | 2008-12-18 | 2012-05-02 | 佩尼贾尔斯航空航天有限公司 | Icing sensor system and method |
| CN102407942A (en) * | 2011-09-06 | 2012-04-11 | 中国商用飞机有限责任公司 | Icing condition detector |
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