CN114485254B - Uniform heat exchange control method for aircraft equipment - Google Patents
Uniform heat exchange control method for aircraft equipment Download PDFInfo
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- CN114485254B CN114485254B CN202210149477.0A CN202210149477A CN114485254B CN 114485254 B CN114485254 B CN 114485254B CN 202210149477 A CN202210149477 A CN 202210149477A CN 114485254 B CN114485254 B CN 114485254B
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- 238000000034 method Methods 0.000 title claims abstract description 21
- 230000001276 controlling effect Effects 0.000 description 8
- 238000009529 body temperature measurement Methods 0.000 description 6
- 230000000694 effects Effects 0.000 description 4
- 238000001816 cooling Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000112 cooling gas Substances 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000009776 industrial production Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000003208 petroleum Substances 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F28—HEAT EXCHANGE IN GENERAL
- F28F—DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION
- F28F27/00—Control arrangements or safety devices specially adapted for heat-exchange or heat-transfer apparatus
-
- 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
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/06—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned
- B64D13/08—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being conditioned the air being heated or cooled
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Health & Medical Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Pulmonology (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Temperature (AREA)
Abstract
The application belongs to the technical field of temperature regulation of airplane equipment, and particularly relates to a uniform heat exchange control method of airplane equipment. Comprising the following steps: step one, obtaining a uniform heat exchange system of a heat exchanger; arranging a plurality of temperature measuring points on the airplane equipment to be subjected to heat exchange, and acquiring the temperature of each temperature measuring point; and step three, determining the switching frequency of a pipeline switching unit of the uniform heat exchange system of the heat exchanger according to the temperature of each temperature measuring point. According to the method for controlling the uniform heat exchange of the airplane equipment, the pipeline switching unit of the uniform heat exchange system of the heat exchanger is used for realizing the switching of two states of the pipeline of the heat exchanger, the forward circulation of a medium is realized in one state, the reverse circulation of the medium is realized in the other state, the frequency of continuous switching of the two states is determined according to the temperature of each temperature measuring point on the airplane equipment to be subjected to heat exchange, and finally the double circulation of the medium of the heat exchanger is realized, so that the problem of nonuniform heat exchange of the heat exchanger is solved, and the heat exchange efficiency of the heat exchanger is improved.
Description
Technical Field
The application belongs to the technical field of temperature regulation of airplane equipment, and particularly relates to a uniform heat exchange control method of airplane equipment.
Background
A heat exchanger is a device that transfers a portion of the heat of a hot fluid to a cold fluid, also known as a heat exchanger. The heat exchanger plays an important role in chemical industry, petroleum, power, food and other industrial production, is an indispensable temperature regulating device on an aviation aircraft, and has application on environmental control systems, electronic equipment, skins and other equipment of the aircraft.
In the prior art, a medium for heating or cooling aircraft equipment in the heat exchanger generally adopts a single-cycle mode, and the heat exchange of the heat exchanger is uneven under the condition that the heat exchanger works for a long time in the mode, so that the heat exchange efficiency of the heat exchanger is reduced, and the effect of adjusting the temperature of the equipment is influenced.
It is therefore desirable to have a solution that overcomes or at least alleviates at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide a uniform heat exchange control method for aircraft equipment, which aims to solve at least one problem in the prior art.
The technical scheme of the application is as follows:
a method for controlling uniform heat exchange of aircraft equipment, comprising:
step one, obtaining a uniform heat exchange system of a heat exchanger, wherein the uniform heat exchange system of the heat exchanger comprises:
the heat exchanger comprises a heat exchange tube, wherein the heat exchange tube is provided with a first port and a second port;
a pipeline switching unit for realizing the switching between a first state and a second state, wherein,
in a first state, a first port of the heat exchange tube is connected with a medium inlet pipeline, and a second port of the heat exchange tube is connected with a medium outlet pipeline;
in the second state, the first port of the heat exchange tube is connected with a medium outlet pipeline, and the second port of the heat exchange tube is connected with a medium inlet pipeline;
arranging a plurality of temperature measuring points on the airplane equipment to be subjected to heat exchange, and acquiring the temperature of each temperature measuring point;
and step three, determining the switching frequency of a pipeline switching unit of the uniform heat exchange system of the heat exchanger according to the temperature of each temperature measuring point.
In at least one embodiment of the present application, the pipeline switching unit includes a first pipeline switching unit and a second pipeline switching unit, wherein,
the first pipeline switching unit comprises a first three-way valve and a first controller, wherein the first three-way valve is connected with a medium inlet pipeline through a first pipeline, is connected with a first port of the heat exchange pipe through a second pipeline and is connected with a second port of the heat exchange pipe through a third pipeline;
the first controller is used for controlling the first three-way valve, so that the first pipeline is communicated with the medium inlet pipeline in a first state, the second pipeline is communicated with the first port of the heat exchange pipe, the first pipeline is communicated with the medium inlet pipeline in a second state, and the third pipeline is communicated with the second port of the heat exchange pipe;
the second pipeline switching unit comprises a second three-way valve and a second controller, wherein the second three-way valve is connected with a medium outlet pipeline through a fourth pipeline, is connected with a first port of the heat exchange pipe through a fifth pipeline and is connected with a second port of the heat exchange pipe through a sixth pipeline;
the second controller is used for controlling the second three-way valve, so that the fourth pipeline is communicated with the medium outlet pipeline in the first state, the sixth pipeline is communicated with the second port of the heat exchange pipe, the fourth pipeline is communicated with the medium outlet pipeline in the second state, and the fifth pipeline is communicated with the first port of the heat exchange pipe.
In at least one embodiment of the present application, in step two, the aircraft device to be heat exchanged includes an aircraft skin and a cockpit instrument panel.
In at least one embodiment of the present application, in the second step, the arranging a plurality of temperature measurement points on the aircraft equipment to be heat exchanged, and obtaining the temperature of each temperature measurement point includes: dividing the surface of the airplane equipment to be subjected to heat exchange into a plurality of temperature areas, arranging a temperature measuring point in each temperature area, and acquiring the temperature of each temperature measuring point through a thermometer.
In at least one embodiment of the present application, in the second step, the arranging a plurality of temperature measurement points on the aircraft equipment to be heat exchanged, and obtaining the temperature of each temperature measurement point includes: a plurality of temperature measuring points are arranged on the surface of the airplane equipment to be subjected to heat exchange at equal intervals along the pipeline of the heat exchange pipe, and the temperature of each temperature measuring point is obtained through a thermometer.
In at least one embodiment of the present application, in the third step, the determining the switching frequency of the pipeline switching unit of the uniform heat exchange system of the heat exchanger according to the temperature of each temperature measuring point includes:
calculating the temperature difference delta T between each temperature measuring point and other temperature measuring points i ：
ΔT 1 ＝|T 1 -T 2 |+|T 1 -T 3 |+...+|T 1 -T n |
ΔT 2 ＝|T 2 -T 1 |+|T 2 -T 3 |+...+|T 2 -T n |
ΔT 3 ＝|T 3 -T 1 |+|T 3 -T 2 |+...+|T 3 -T n |
...
ΔT n ＝|T n -T 1 |+|T n -T 2 |+...+|T n -T n-1 |
Calculating the total difference Sigma delta T of the temperatures between each temperature measuring point and other temperature measuring points i ：
∑ΔT i ＝ΔT 1 +ΔT 2 +...+ΔT n
The switching frequency P of the pipeline switching unit of the uniform heat exchange system of the heat exchanger is determined to be:
P＝A∑ΔT i +C 1
wherein T is 1 、T 2 、T 3 ...T n A, C for the temperature of each temperature measuring point 1 Is constant.
In at least one embodiment of the present application, in the third step, the determining the switching frequency of the pipeline switching unit of the uniform heat exchange system of the heat exchanger according to the temperature of each temperature measuring point includes:
calculating the variance D of the temperature of each temperature measuring point T ：
The switching frequency P of the pipeline switching unit of the uniform heat exchange system of the heat exchanger is determined to be:
P＝BD T +C 2
wherein T is 1 、T 2 、T 3 ...T n For the temperature of each temperature measuring point,for the average value of the temperature of each temperature measuring point B, C 2 Is constant.
The application has at least the following beneficial technical effects:
according to the control method for uniform heat exchange of the aircraft equipment, the uniform heat exchange system of the heat exchanger is adopted to switch the heat exchanger pipelines, so that double circulation of heat exchanger media is realized, the switching frequency of the heat exchanger pipelines is reasonably determined, the problem of nonuniform heat exchange of the heat exchanger is solved, and the heat exchange efficiency of the heat exchanger is improved.
Drawings
FIG. 1 is a flow chart of a method for controlling uniform heat exchange of an aircraft device in accordance with one embodiment of the present application.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application become more apparent, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the application. The embodiments described below by referring to the drawings are illustrative and intended to explain the present application and should not be construed as limiting the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it should be understood that the terms "center," "longitudinal," "lateral," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, merely to facilitate describing the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the scope of the present application.
The application is described in further detail below with reference to fig. 1.
The application provides a uniform heat exchange control method of airplane equipment, which comprises the following steps:
s001, obtaining a uniform heat exchange system of the heat exchanger, wherein the uniform heat exchange system of the heat exchanger comprises:
the heat exchanger comprises a heat exchange tube, and the heat exchange tube is provided with a first port and a second port;
a pipeline switching unit for realizing the switching between a first state and a second state, wherein,
in the first state, a first port of the heat exchange tube is connected with a medium inlet pipeline, and a second port of the heat exchange tube is connected with a medium outlet pipeline;
in the second state, the first port of the heat exchange tube is connected with the medium outlet pipeline, and the second port of the heat exchange tube is connected with the medium inlet pipeline;
s002, arranging a plurality of temperature measuring points on the airplane equipment to be subjected to heat exchange, and acquiring the temperature of each temperature measuring point;
s003, determining the switching frequency of a pipeline switching unit of the uniform heat exchange system of the heat exchanger according to the temperature of each temperature measuring point.
According to the control method for uniform heat exchange of the aircraft equipment, the two states of the heat exchanger pipeline are switched through the pipeline switching unit of the uniform heat exchange system of the heat exchanger. The heat exchange tube of the heat exchanger is provided with two ports, wherein in one state, the first port of the heat exchange tube is connected with a medium inlet pipeline of the heat exchanger, the second port of the heat exchange tube is connected with a medium outlet pipeline of the heat exchanger, so that the positive circulation flow of a medium is realized, and in the other state, the first port of the heat exchange tube is connected with a medium outlet pipeline of the heat exchanger, and the second port of the heat exchange tube is connected with a medium inlet pipeline of the heat exchanger, so that the reverse circulation flow of the medium is realized. And determining the frequency of continuous switching of the two states according to the temperature of each temperature measuring point on the airplane equipment to be subjected to heat exchange, and finally realizing double circulation of the heat exchanger medium.
In a preferred embodiment of the present application, the pipe switching unit in the uniform heat exchange system of the heat exchanger may include a first pipe switching unit and a second pipe switching unit, wherein the first pipe switching unit includes a first three-way valve and a first controller, the first three-way valve is connected with the medium inlet pipe through a first pipe, connected with the first port of the heat exchange pipe through a second pipe, and connected with the second port of the heat exchange pipe through a third pipe; the first controller is used for controlling the first three-way valve, so that the first pipeline is communicated with the medium inlet pipeline in the first state, the second pipeline is communicated with the first port of the heat exchange tube, the first pipeline is communicated with the medium inlet pipeline in the second state, and the third pipeline is communicated with the second port of the heat exchange tube. The second pipeline switching unit comprises a second three-way valve and a second controller, wherein the second three-way valve is connected with a medium outlet pipeline through a fourth pipeline, is connected with a first port of the heat exchange pipe through a fifth pipeline and is connected with a second port of the heat exchange pipe through a sixth pipeline; the second controller is used for controlling the second three-way valve, so that the fourth pipeline is communicated with the medium outlet pipeline in the first state, the sixth pipeline is communicated with the second port of the heat exchange pipe, the fourth pipeline is communicated with the medium outlet pipeline in the second state, and the fifth pipeline is communicated with the first port of the heat exchange pipe.
In this embodiment, the first three-way valve has a valve a, a valve b and a valve c, and the second three-way valve has a valve d, a valve e and a valve f. In the first state, a valve a is opened through a first controller to enable a first pipeline to be communicated with a medium inlet pipeline, a valve b is opened to enable a second pipeline to be communicated with a first port of a heat exchange pipe, and a valve c is closed to enable the medium inlet pipeline to be communicated with the first port of the heat exchange pipe through the first pipeline and the second pipeline; and the valve d is opened through the second controller to enable the fourth pipeline to be communicated with the medium outlet pipeline, the valve f is opened to enable the sixth pipeline to be communicated with the second port of the heat exchange pipe, and the valve e is closed to enable the medium outlet pipeline to be communicated with the second port of the heat exchange pipe through the fourth pipeline and the sixth pipeline. In the second state, the valve a is opened through the first controller to enable the first pipeline to be communicated with the medium inlet pipeline, the valve c is opened to enable the third pipeline to be communicated with the second port of the heat exchange pipe, and the valve b is closed to enable the medium inlet pipeline to be communicated with the second port of the heat exchange pipe through the first pipeline and the third pipeline; and the valve d is opened through the second controller to enable the fourth pipeline to be communicated with the medium outlet pipeline, the valve e is opened to enable the fifth pipeline to be communicated with the first port of the heat exchange pipe, and the valve f is closed to enable the medium outlet pipeline to be communicated with the first port of the heat exchange pipe through the fourth pipeline and the fifth pipeline.
According to the control method for uniform heat exchange of the aircraft equipment, the uniform heat exchange system of the heat exchanger is applied to the aircraft equipment to be subjected to heat exchange, such as an aircraft skin, a cockpit instrument panel and the like. The heat exchanger can realize heat exchange through gas or liquid medium according to the type of the aircraft equipment to be heat exchanged, and the heat exchange medium can be cooling gas, fuel oil and the like according to the heat exchange requirement of the aircraft equipment to be heat exchanged, for example, the high-altitude deicing requirement of the aircraft skin and the cooling requirement of the cockpit electronic equipment. In a preferred embodiment of the present application, in step S002, a plurality of temperature measuring points on the aircraft device to be heat-exchanged are disposed on the surface of the aircraft device to be heat-exchanged, which is attached to the heat exchange tube of the heat exchanger, and each temperature measuring point may be disposed in a certain manner, for example, the surface of the aircraft device to be heat-exchanged is divided into a plurality of temperature areas, one temperature measuring point is disposed in each temperature area, the temperature of each temperature measuring point is measured by a thermometer, or a plurality of temperature measuring points are disposed directly on the surface of the aircraft device to be heat-exchanged at equal intervals along the pipeline of the heat exchange tube, and the temperature of each temperature measuring point is measured by a thermometer.
According to the method for controlling the uniform heat exchange of the aircraft equipment, the switching frequency of the pipeline switching unit of the uniform heat exchange system of the heat exchanger has a specific great influence on the heat exchange effect of the heat exchanger, and the switching frequency of the pipeline switching unit needs to be determined in a proper mode according to the specific type of the aircraft equipment to be subjected to heat exchange.
In one embodiment of the present application, in S003, determining a switching frequency of a pipe switching unit of a uniform heat exchange system of a heat exchanger according to a temperature of each temperature measurement point includes:
calculating the temperature difference delta T between each temperature measuring point and other temperature measuring points i ：
ΔT 1 ＝|T 1 -T 2 |+|T 1 -T 3 |+...+|T 1 -T n |
ΔT 2 ＝|T 2 -T 1 |+|T 2 -T 3 |+...+|T 2 -T n |
ΔT 3 ＝|T 3 -T 1 |+|T 3 -T 2 |+...+|T 3 -T n |
...
ΔT n ＝|T n -T 1 |+|T n -T 2 |+...+|T n -T n-1 |
Calculating the total difference Sigma delta T of the temperatures between each temperature measuring point and other temperature measuring points i ：
∑ΔT i ＝ΔT 1 +ΔT 2 +...+ΔT n
The switching frequency P of the pipeline switching unit of the uniform heat exchange system of the heat exchanger is determined to be:
P＝A∑ΔT i +C 1
wherein T is 1 、T 2 、T 3 ...T n A, C for the temperature of each temperature measuring point 1 Is constant.
In another embodiment of the present application, in S003, determining a switching frequency of a pipe switching unit of a uniform heat exchange system of a heat exchanger according to a temperature of each temperature measurement point includes:
calculating the variance D of the temperature of each temperature measuring point T ：
The switching frequency P of the pipeline switching unit of the uniform heat exchange system of the heat exchanger is determined to be:
P＝BD T +C 2
wherein T is 1 、T 2 、T 3 ...T n For the temperature of each temperature measuring point,for the average value of the temperature of each temperature measuring point B, C 2 Is constant.
The method for controlling the uniform heat exchange of the aircraft equipment provides a determination mode of the switching frequency of the pipeline switching unit of the uniform heat exchange system of two proper heat exchangers, the determination mode is respectively determined through the calculated difference and variance of the temperatures of all the temperature measuring points, the difference and variance of all the temperature measuring points can reflect the heat exchange effect of the aircraft equipment to be subjected to heat exchange, and all the parameters in the formula can be determined according to the actual conditions. In addition, in practical application, the switching frequency of the pipeline switching unit of the uniform heat exchange system of the heat exchanger can be determined in other proper modes according to different requirements.
The control method for the uniform heat exchange of the airplane equipment is provided with the uniform heat exchange system of the heat exchanger, and the pipeline switching unit of the uniform heat exchange system of the heat exchanger is used for switching the pipelines of the heat exchanger, so that the double circulation of heat exchanger media is realized, the switching frequency of the pipelines of the heat exchanger is reasonably determined, the problem of nonuniform heat exchange of the heat exchanger is solved, and the heat exchange efficiency of the heat exchanger is improved.
The foregoing is merely illustrative of the present application, and the present application is not limited thereto, and any changes or substitutions easily contemplated by those skilled in the art within the scope of the present application should be included in the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. A method for controlling uniform heat exchange of aircraft equipment, comprising:
step one, obtaining a uniform heat exchange system of a heat exchanger, wherein the uniform heat exchange system of the heat exchanger comprises:
the heat exchanger comprises a heat exchange tube, wherein the heat exchange tube is provided with a first port and a second port;
a pipeline switching unit for realizing the switching between a first state and a second state, wherein,
in a first state, a first port of the heat exchange tube is connected with a medium inlet pipeline, and a second port of the heat exchange tube is connected with a medium outlet pipeline;
in the second state, the first port of the heat exchange tube is connected with a medium outlet pipeline, and the second port of the heat exchange tube is connected with a medium inlet pipeline;
arranging a plurality of temperature measuring points on the airplane equipment to be subjected to heat exchange, and acquiring the temperature of each temperature measuring point;
step three, determining the switching frequency of a pipeline switching unit of the uniform heat exchange system of the heat exchanger according to the temperature of each temperature measuring point;
the determining the switching frequency of the pipeline switching unit of the uniform heat exchange system of the heat exchanger according to the temperature of each temperature measuring point comprises the following steps:
calculating the temperature difference delta T between each temperature measuring point and other temperature measuring points i ：
ΔT 1 ＝|T 1 -T 2 |+|T 1 -T 3 |+...+|T 1 -T n |
ΔT 2 ＝|T 2 -T 1 |+|T 2 -T 3 |+...+|T 2 -T n |
ΔT 3 ＝|T 3 -T 1 |+|T 3 -T 2 |+...+|T 3 -T n |
...
ΔT n ＝|T n -T 1 |+|T n -T 2 |+...+|T n -T n-1 |
Calculating the total difference Sigma delta T of the temperatures between each temperature measuring point and other temperature measuring points i ：
∑ΔT i ＝ΔT 1 +ΔT 2 +...+ΔT n
The switching frequency P of the pipeline switching unit of the uniform heat exchange system of the heat exchanger is determined to be:
P＝A∑ΔT i +C 1
wherein T is 1 、T 2 、T 3 ...T n A, C for the temperature of each temperature measuring point 1 Is constant.
2. The method for controlling uniform heat exchange of aircraft equipment according to claim 1, wherein the pipeline switching unit comprises a first pipeline switching unit and a second pipeline switching unit, wherein,
the first pipeline switching unit comprises a first three-way valve and a first controller, wherein the first three-way valve is connected with a medium inlet pipeline through a first pipeline, is connected with a first port of the heat exchange pipe through a second pipeline and is connected with a second port of the heat exchange pipe through a third pipeline;
the first controller is used for controlling the first three-way valve, so that the first pipeline is communicated with the medium inlet pipeline in a first state, the second pipeline is communicated with the first port of the heat exchange pipe, the first pipeline is communicated with the medium inlet pipeline in a second state, and the third pipeline is communicated with the second port of the heat exchange pipe;
the second pipeline switching unit comprises a second three-way valve and a second controller, wherein the second three-way valve is connected with a medium outlet pipeline through a fourth pipeline, is connected with a first port of the heat exchange pipe through a fifth pipeline and is connected with a second port of the heat exchange pipe through a sixth pipeline;
the second controller is used for controlling the second three-way valve, so that the fourth pipeline is communicated with the medium outlet pipeline in the first state, the sixth pipeline is communicated with the second port of the heat exchange pipe, the fourth pipeline is communicated with the medium outlet pipeline in the second state, and the fifth pipeline is communicated with the first port of the heat exchange pipe.
3. The method for uniform heat exchange control of an aircraft device according to claim 2, wherein in step two, the aircraft device to be heat exchanged comprises an aircraft skin and a cockpit instrument panel.
4. The method for controlling uniform heat exchange of aircraft equipment according to claim 3, wherein in the second step, a plurality of temperature measuring points are arranged on the aircraft equipment to be subjected to heat exchange, and acquiring the temperature of each temperature measuring point comprises: dividing the surface of the airplane equipment to be subjected to heat exchange into a plurality of temperature areas, arranging a temperature measuring point in each temperature area, and acquiring the temperature of each temperature measuring point through a thermometer.
5. The method for controlling uniform heat exchange of aircraft equipment according to claim 3, wherein in the second step, a plurality of temperature measuring points are arranged on the aircraft equipment to be subjected to heat exchange, and acquiring the temperature of each temperature measuring point comprises: a plurality of temperature measuring points are arranged on the surface of the airplane equipment to be subjected to heat exchange at equal intervals along the pipeline of the heat exchange pipe, and the temperature of each temperature measuring point is obtained through a thermometer.
6. The method for controlling uniform heat exchange of aircraft equipment according to claim 3, wherein in the third step, determining the switching frequency of the pipeline switching unit of the uniform heat exchange system of the heat exchanger according to the temperature of each temperature measuring point comprises:
calculating the variance D of the temperature of each temperature measuring point T ：
The switching frequency P of the pipeline switching unit of the uniform heat exchange system of the heat exchanger is determined to be:
P＝BD T +C 2
wherein T is 1 、T 2 、T 3 ...T n For the temperature of each temperature measuring point,for the average value of the temperature of each temperature measuring point B, C 2 Is constant.
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