CN113901590B - Large aircraft climate environment laboratory temperature rise and fall transient load analysis method - Google Patents

Large aircraft climate environment laboratory temperature rise and fall transient load analysis method Download PDF

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CN113901590B
CN113901590B CN202111358691.9A CN202111358691A CN113901590B CN 113901590 B CN113901590 B CN 113901590B CN 202111358691 A CN202111358691 A CN 202111358691A CN 113901590 B CN113901590 B CN 113901590B
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CN113901590A (en
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王彬文
成竹
吴敬涛
李闯勤
任战鹏
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AVIC Aircraft Strength Research Institute
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Abstract

The invention provides a method for analyzing the temperature rise and drop transient load of a large airplane in a climate environment laboratory, which relates to the technical field of airplanes and comprises the following steps: S1-S8: respectively establishing heat load models of air, a heat insulation plate, a terrace, compensation fresh air, a steel structure, a fan, illumination and an airplane; s9, establishing a refrigeration/heating system model; S10-S13, respectively establishing a temperature dynamic change equation of indoor air, a terrace and an airplane and an integral temperature dynamic change equation set; s14, setting relevant parameters; s15, solving a differential equation set and calculating the transient load. The analysis method solves the problems of lack of design or over-complex design of the laboratory for the accurate calculation of the heat load in the cooling and heating processes, and has the advantages of accurate calculation, reasonable design and low calculation complexity.

Description

Large aircraft climate environment laboratory temperature rise and fall transient load analysis method
Technical Field
The invention relates to the technical field of airplane design, in particular to a temperature rise and fall transient load analysis method for a large airplane climate environment laboratory.
Background
An aircraft (aeroplane) refers to a heavier-than-air aircraft that has one or more engines and a power plant that generates forward thrust or pull, generates lift from the fixed wings of the fuselage, and flies in the atmosphere. Airplanes can be classified into military and civil use according to their purpose. Military aircraft refers to aircraft used in various military fields, while civil aircraft refers to all non-military-purpose aircraft (such as passenger aircraft, cargo aircraft, agricultural aircraft, sports aircraft, ambulance aircraft, and research and development aircraft).
Of course, with the continuous development of aviation technology and the continuous improvement of airplane performance, the design requirement of airplane adapting to extreme weather is more and more, and generally, the airplane structure design should meet the following basic requirements: (1) the requirement of aerodynamic shape, in order to ensure that the airplane has the original good stability and maneuverability in aerodynamic, the wings, the empennage and the fuselage are not allowed to have excessive deformation, have enough strength and rigidity, and have light weight; (2) has sufficient rigidity (by rigidity is meant the ability of a structure or material to resist deformation) and takes other measures to avoid unacceptable aeroelastic and vibration problems.
To check whether the aircraft meets the above requirements, a relevant large climate laboratory needs to be established. The airplane environment laboratory is the first ultra-large type climate environment simulation facility capable of simulating typical climate environments such as high temperature, low temperature, solar radiation, temperature/humidity, rain, snow, freezing rain, icing and the like in China, is used for meeting the climate environment test of equipment such as full-size airplanes, missile weapon systems and the like, and fills the blank of the field of airplane climate environment test in China.
In a large aircraft climate environment laboratory, in order to simulate a temperature environment of-55 ℃ to +74 ℃, the aircraft climate environment laboratory is provided with a large refrigeration system and a large heating system, and a cold/heat carrying system is used for providing cold/heat for the laboratory. In order to efficiently transmit the cold quantity and the heat quantity of the secondary refrigerant to a laboratory, the laboratory is provided with a circulating air processing unit for adjusting the indoor air temperature, a heat exchanger and a circulating fan are arranged in the circulating air processing unit, the heat exchanger realizes the heat exchange between the air and the secondary refrigerant, and the circulating fan sends the processed air into the room. In order to ensure the stability of indoor pressure, the laboratory is provided with a fresh air processing unit, and after the fresh air processing unit dries outdoor air, fresh air is sent into the laboratory in a constant flow manner. In order to reduce the heat transfer between the air inside the laboratory and the outside air, the wall bodies and the suspended ceilings around the laboratory are all subjected to heat insulation treatment by adopting polyurethane heat insulation boards. In addition, the indoor terrace adopts a special concrete structure form, and the effects of large bearing capacity, heat insulation and sealing can be realized. The steel structure at the top of the laboratory is used for hoisting special simulation system devices, such as a solar irradiation system lamp array, a rain rack and the like. The top of the laboratory is provided with a high-power illuminating lamp for indoor illumination.
Aircraft environment laboratories are large in size and can accommodate a maximum of one large U.S. class C-5 transport (approximately 182 tons in mass), and these components are a significant thermal load on the cooling/heating system of the laboratory. Transient heat load of a super-large environment laboratory in a temperature rise/reduction process is related to capacity selection configuration of a refrigerating system and a heating system, and in order to avoid huge waste of capital or insufficient system capacity caused by over-design or under-design of capacities of the refrigerating system and the heating system of the laboratory, heat load of each component of the laboratory in the temperature rise/reduction process, especially transient load under the condition of load (large-scale transport machine), needs to be accurately calculated.
In the field of engineering application, a method for calculating the heat load comprises the following steps: (1) estimating the load by adopting empirical data, which is mainly used for estimating the heating and ventilation loads of common buildings and houses and is used for calculating the load of a boundary temperature point; (2) CFD simulation calculation is adopted.
The first method is based on a large amount of data as a reference basis, but an aircraft environmental laboratory does not have a large amount of historical reference data, and the result obtained by the method is invalid after the internal environment of the aircraft climate environmental laboratory changes; the second method has the problem of over-design, is too complex and has no practicability.
Disclosure of Invention
The technical problem solved by the invention is as follows: the accurate calculation of the thermal load in the cooling and heating processes in the aircraft climate environment laboratory is lack of design or too complex.
In order to solve the above problems, the present invention provides the following technical solutions:
the method for analyzing the temperature rise and fall transient load of the large airplane in the climate environment laboratory comprises the following steps:
s1, establishing an air heat load model taking the corrected temperature as a parameter, wherein the model formula is as follows:
Figure 100002_DEST_PATH_IMAGE002
in the formula:
Figure 100002_DEST_PATH_IMAGE004
for the purpose of the air transient load,
Figure 100002_DEST_PATH_IMAGE006
in order to be a model-modifying factor,
Figure 100002_DEST_PATH_IMAGE008
is the volume of the air in the room,
Figure 100002_DEST_PATH_IMAGE010
is the air density at normal temperature and pressure,
Figure 100002_DEST_PATH_IMAGE012
is the specific heat coefficient of the air,
Figure 100002_DEST_PATH_IMAGE014
for the numerical calculation of the current air temperature during the process,
Figure 100002_DEST_PATH_IMAGE016
calculating the air temperature at the previous moment in the process for the numerical value;
s2, considering the laboratory situation, setting the preconditions as: the temperature of the air outside the laboratory is not changed, and the temperature of the inner/outer surface of the heat-insulation plate is respectively the same as the temperature of the air inside and outside the laboratory, so that a heat load model of the heat-insulation plate is established;
s3, establishing a terrace heat load model:
Figure 100002_DEST_PATH_IMAGE018
in the formula:
Figure 100002_DEST_PATH_IMAGE020
in order to be the heat load of the terrace,
Figure 100002_DEST_PATH_IMAGE022
for strong convectionThe thermal coefficient of the material is as follows,
Figure 100002_DEST_PATH_IMAGE024
in order to provide a floor area for a laboratory,
Figure 100002_DEST_PATH_IMAGE026
for the numerical calculation of the current air temperature during the process,
Figure 100002_DEST_PATH_IMAGE028
the temperature of the top floor in the terrace;
s4, establishing a wind heat load compensation model according to the characteristic that the air supply temperature of the laboratory compensation fresh air is a constant value;
s5, establishing a steel structure heat load model, and setting the preconditions as follows: the initial air temperature in the steel structure and the laboratory is the same and the air temperature change rate in the steel structure and the laboratory is the same, and according to a heat calculation formula, the following steel structure transient heat load model is obtained:
Figure 100002_DEST_PATH_IMAGE030
in the formula:
Figure 100002_DEST_PATH_IMAGE032
for the transient load of the steel structure,
Figure 100002_DEST_PATH_IMAGE034
the mass of the steel structure is the weight of the steel structure,
Figure 100002_DEST_PATH_IMAGE036
is the specific heat coefficient of the steel material,
Figure 100002_DEST_PATH_IMAGE038
for numerically calculating the current steel structure temperature during the process,
Figure 100002_DEST_PATH_IMAGE040
for steel structures at a previous moment in the calculation of the value(ii) temperature;
s6, establishing a fan thermal load model, wherein the air temperature variation range of a laboratory is-55 to +74 ℃, and according to the characteristics that the air output of the laboratory fan is large under a high-temperature working condition and small under a low-temperature working condition, establishing the following variable working condition thermal load model:
Figure 100002_DEST_PATH_IMAGE042
in the formula:
Figure 100002_DEST_PATH_IMAGE044
in order to provide a thermal load for the fan,
Figure 100002_DEST_PATH_IMAGE046
in order to increase the number of the fans,
Figure 100002_DEST_PATH_IMAGE048
is the effective power of a single fan,
Figure 100002_DEST_PATH_IMAGE050
calculating the current air temperature for the value;
s7, establishing a lighting heat load model with a constant value;
s8, because the maximum load of the laboratory is a large-scale transport airplane with C5, in order to accurately calculate the heat load, an airplane heat load model is established according to the convection heat exchange principle:
Figure 100002_DEST_PATH_IMAGE052
in the formula:
Figure 100002_DEST_PATH_IMAGE054
in order to be a thermal load of the aircraft,
Figure 100002_DEST_PATH_IMAGE056
in order to obtain a convective heat transfer coefficient,
Figure 100002_DEST_PATH_IMAGE058
the surface area of the aircraft is,
Figure 100002_DEST_PATH_IMAGE060
for the numerical calculation of the current air temperature during the process,
Figure 100002_DEST_PATH_IMAGE062
is the temperature of the aircraft surface;
s9, establishing a refrigeration/heating system model, and establishing the following sectional type refrigeration/heating model according to the refrigeration/heating system working mode and refrigeration/heating application characteristics selected by a laboratory:
Figure 100002_DEST_PATH_IMAGE064
in the formula:
Figure 100002_DEST_PATH_IMAGE066
the cold/heat provided to the refrigeration/heating system,
Figure 100002_DEST_PATH_IMAGE068
as a coefficient of the margin, is,
Figure 100002_DEST_PATH_IMAGE070
calculating the current air temperature for the value;
s10, establishing an indoor air temperature dynamic change equation, and setting the preconditions as follows: the initial air temperature of the steel structure in the laboratory is the same as that of the air in the laboratory, and the change rate of the air temperature of the steel structure in the laboratory is the same as that of the air in the laboratory, and according to the heat balance principle, the following air temperature dynamic differential equation is established:
Figure 100002_DEST_PATH_IMAGE072
in the formula:
Figure 100002_DEST_PATH_IMAGE074
is air temperature versus time
Figure 100002_DEST_PATH_IMAGE076
The rate of change of (a) is,
Figure 100002_DEST_PATH_IMAGE078
is the temperature of the air in the room,
Figure 100002_DEST_PATH_IMAGE080
is the temperature of the top-layer terrace,
Figure 100002_DEST_PATH_IMAGE082
for the surface temperature of the aircraft as a load,
Figure 100002_DEST_PATH_IMAGE084
is the set point of the air temperature,
Figure 100002_DEST_PATH_IMAGE086
the cold/heat provided to the refrigeration/heating system,
Figure 100002_DEST_PATH_IMAGE088
in order to provide the thermal load of the insulation board,
Figure 100002_DEST_PATH_IMAGE090
in order to provide the heat load of the terrace,
Figure 100002_DEST_PATH_IMAGE092
in order to compensate for the heat load of the fresh air,
Figure 100002_DEST_PATH_IMAGE094
in order to provide a thermal load for the fan,
Figure 100002_DEST_PATH_IMAGE096
in order to illuminate the heat load,
Figure 100002_DEST_PATH_IMAGE098
which is indicative of the thermal load of the aircraft,
Figure 100002_DEST_PATH_IMAGE100
in order to obtain the quality of the air in the room,
Figure 100002_DEST_PATH_IMAGE102
、
Figure 100002_DEST_PATH_IMAGE104
the specific heat coefficients of air and a steel structure respectively,
Figure 100002_DEST_PATH_IMAGE106
the mass of the steel structure is the weight of the steel structure,
Figure 100002_DEST_PATH_IMAGE108
representing a dynamic variation function of air temperature;
s11, dividing the floor into 13 layers according to the concrete structure and weight of the laboratory floor, and respectively establishing floor temperature dynamic change equations for calculating the floor temperature change rates of the 1 st layer, the 2 nd to 12 th layers and the 13 th layer;
s12, establishing a temperature dynamic change equation of the airplane:
Figure 100002_DEST_PATH_IMAGE110
in the formula:
Figure 100002_DEST_PATH_IMAGE112
for aircraft temperature versus time
Figure 100002_DEST_PATH_IMAGE114
The rate of change of (a) is,
Figure 100002_DEST_PATH_IMAGE116
is the convective heat transfer coefficient between the air and the aircraft,
Figure 100002_DEST_PATH_IMAGE118
is the temperature of the air in the room,
Figure 100002_DEST_PATH_IMAGE120
the surface area of the aircraft is,
Figure 100002_DEST_PATH_IMAGE122
for the surface temperature of the aircraft as a load,
Figure 100002_DEST_PATH_IMAGE124
in order to be the mass of the aircraft,
Figure 100002_DEST_PATH_IMAGE126
is the specific heat coefficient of the aircraft,
Figure 100002_DEST_PATH_IMAGE128
representing a function of aircraft temperature dynamics;
s13, establishing an integral temperature dynamic change equation set:
Figure 100002_DEST_PATH_IMAGE130
in the formula:
Figure 100002_DEST_PATH_IMAGE132
in the form of a temperature rate-of-change matrix,
Figure 100002_DEST_PATH_IMAGE134
in the form of a temperature matrix, the temperature matrix,
Figure 100002_DEST_PATH_IMAGE136
in the form of an initial temperature matrix, the temperature,
Figure 100002_DEST_PATH_IMAGE138
it is the temperature of the air that is,
Figure 100002_DEST_PATH_IMAGE140
in order to obtain the temperature of each floor,
Figure DEST_PATH_IMAGE142
，
Figure DEST_PATH_IMAGE144
is the aircraft surface temperature;
Figure DEST_PATH_IMAGE146
is an initial temperature value;
s14, setting relevant parameters;
s15, substituting the parameters in step S14 into step S10, step S11, and step S12, respectively, obtaining the air temperature change rate, the floor-level layer temperature change rate, and the airplane temperature change rate, respectively, then importing the air temperature change rate, the floor-level layer temperature change rate, and the airplane temperature change rate into step S13 to obtain the temperature change rate of the entire laboratory under load, and then calculating the transient load.
In step S13, after the floor is divided into 13 layers, a floor temperature change equation with 13 dimensions is established, and since the dimension of the air temperature change equation in the laboratory is 1 dimension and the dimension of the airplane temperature change equation is 1 dimension, the dimension of the linear differential equation set formed by the combination is 15 dimensions.
Further, the thermal load model of the thermal insulation board in step S2 is:
Figure DEST_PATH_IMAGE148
in the formula:
Figure DEST_PATH_IMAGE150
in order to provide the thermal load of the insulation board,
Figure DEST_PATH_IMAGE152
is the heat transfer coefficient of the heat-insulating plate,
Figure DEST_PATH_IMAGE154
is the surface area of the heat-insulating plate in the laboratory,
Figure DEST_PATH_IMAGE156
is the thickness of the heat-preserving plate,
Figure DEST_PATH_IMAGE158
for the temperature of the current inner surface of the insulation board in the numerical calculation processThe temperature of the air is the same as that of the air,
Figure 100002_DEST_PATH_IMAGE160
the temperature of the outer surface of the current insulation board in the numerical calculation process is the same as the temperature of outdoor air.
The heat loss of the heat insulation plate in the laboratory is considered, the model is simplified through the precondition, the heat load model of the heat insulation plate is relatively simple, and the calculation process of the transient heat load is simplified while the time is met.
Further, in step S3, the strong convective heat transfer coefficient between the floor and the air is a variable linear parameter, and the functional relationship between the strong convective heat transfer coefficient and the air temperature is:
Figure 100002_DEST_PATH_IMAGE162
in the formula:
Figure 100002_DEST_PATH_IMAGE164
in order to have a strong convective heat transfer coefficient,
Figure 100002_DEST_PATH_IMAGE166
for the numerical calculation of the current air temperature during the process,
Figure 100002_DEST_PATH_IMAGE168
in order to fix the constant of 29.28,
Figure 100002_DEST_PATH_IMAGE170
is a linear factor and takes the value of 0.071.
The heat transfer mode of terrace and air in the laboratory is considered to be the form of strong convection heat transfer in the above content, combines the linear relation that the high low temperature performance evaluation test data of terrace reachs, more can laminate the reality of large-scale aircraft weather laboratory to the terrace heat load model that obtains is more superior than prior art.
Further, the model for compensating the wind heat load established in step S4 is:
Figure 100002_DEST_PATH_IMAGE172
in the formula:
Figure 100002_DEST_PATH_IMAGE174
in order to compensate for the heat load of the fresh air,
Figure 100002_DEST_PATH_IMAGE176
is the specific heat coefficient of the air,
Figure 100002_DEST_PATH_IMAGE178
in order to compensate for the mass of the fresh air,
Figure 100002_DEST_PATH_IMAGE180
for the purpose of numerically calculating the current air temperature,
Figure 100002_DEST_PATH_IMAGE182
to compensate for fresh air temperature.
The large-scale airplane climate laboratory compensates fresh air through a fresh air system, and the air supply temperature of the large-scale airplane climate laboratory is generally a constant value of minus 25 ℃. According to the characteristics of the fresh air system, the air supply temperature is used as a threshold value, the segmented heat load model is set, the calculation process of the fresh air transient heat load is simplified, the efficiency of the whole method is improved, and the method is more practical.
Further, in step S6, the effective power of the fan under the standard operating condition is:
Figure 100002_DEST_PATH_IMAGE184
in the formula:
Figure 100002_DEST_PATH_IMAGE186
the effective power of the fan is the effective power of the fan,
Figure 100002_DEST_PATH_IMAGE188
the air quantity of the fan is adopted,
Figure 100002_DEST_PATH_IMAGE190
is a pressure head of the fan,
Figure 100002_DEST_PATH_IMAGE192
the safety factor is.
Because the transient heat load change rate of the fan in the whole large-scale airplane climate laboratory is very low, the error of the final result generated by formula calculation with ideal use conditions is very little, the calculation time can be further saved, and the calculation complexity is simplified.
Further, in step S7, the lighting thermal load model formula is:
Figure 100002_DEST_PATH_IMAGE194
in the formula:
Figure 100002_DEST_PATH_IMAGE196
in order to illuminate the heat load,
Figure 100002_DEST_PATH_IMAGE198
is a constant.
For the setting of the lighting heat load model, since the instantaneous lighting heat load is constant throughout the large aircraft climate laboratory, it can be obtained directly by measurement, where it is reasonable and practical to use a constant value.
Preferably, the temperature dynamic change equations of the floor in step S11 are respectively:
the temperature change equation of the floor at the 1 st layer:
Figure 100002_DEST_PATH_IMAGE200
in the formula:
Figure 100002_DEST_PATH_IMAGE202
for top floor temperature versus time
Figure 100002_DEST_PATH_IMAGE204
The rate of change of (a) is,
Figure 100002_DEST_PATH_IMAGE206
is the temperature of the air in the room,
Figure 100002_DEST_PATH_IMAGE208
is the current temperature of the top floor level,
Figure 100002_DEST_PATH_IMAGE210
is the current temperature of the lower floor level,
Figure 100002_DEST_PATH_IMAGE212
in order to have a strong convective heat transfer coefficient,
Figure 100002_DEST_PATH_IMAGE214
as to the density of the terrace,
Figure 100002_DEST_PATH_IMAGE216
is the specific heat coefficient of the terrace,
Figure 100002_DEST_PATH_IMAGE218
the thickness of the terrace is the thickness of the terrace,
Figure 100002_DEST_PATH_IMAGE220
for the heat transfer coefficient of the terrace,
Figure 100002_DEST_PATH_IMAGE222
the temperature change function of the grade level of the layer 1 is shown,
temperature change equation of 2 nd to 12 th floor:
Figure 100002_DEST_PATH_IMAGE224
in the formula: integer number of
Figure 100002_DEST_PATH_IMAGE226
Value range ofEnclose as
Figure 100002_DEST_PATH_IMAGE228
，
Figure 100002_DEST_PATH_IMAGE230
For middle floor temperature versus time
Figure DEST_PATH_IMAGE231
The rate of change of (a) is,
Figure DEST_PATH_IMAGE233
is the current temperature of the upper floor,
Figure DEST_PATH_IMAGE235
is the current temperature of the intermediate floor level,
Figure DEST_PATH_IMAGE237
is the current temperature of the next floor level,
Figure DEST_PATH_IMAGE239
for the heat transfer coefficient of the terrace,
Figure DEST_PATH_IMAGE241
the thickness of the terrace is the thickness of the terrace,
Figure DEST_PATH_IMAGE243
as to the density of the terrace,
Figure DEST_PATH_IMAGE245
is the specific heat coefficient of the terrace,
the 13 th floor temperature change equation:
Figure DEST_PATH_IMAGE247
in the formula:
Figure DEST_PATH_IMAGE249
for insulating layer terrace temperature vs. time
Figure 100002_DEST_PATH_IMAGE250
The rate of change of (a) is,
Figure 100002_DEST_PATH_IMAGE252
is the current temperature of the 12 th floor,
Figure 100002_DEST_PATH_IMAGE254
is the current temperature of the 13 th floor,
Figure 100002_DEST_PATH_IMAGE256
for the heat transfer coefficient of the terrace,
Figure 100002_DEST_PATH_IMAGE258
the thickness of the terrace is the thickness of the terrace,
Figure 100002_DEST_PATH_IMAGE260
as to the density of the terrace,
Figure 100002_DEST_PATH_IMAGE262
is the specific heat coefficient of the terrace,
Figure 100002_DEST_PATH_IMAGE264
showing the temperature change function of the 13 th floor.
The above contents are set according to the actual conditions of a large-scale airplane climate environment laboratory, firstly, a laboratory terrace is of a special concrete structure and has the characteristics of large bearing capacity (containing 8% of a steel structure), heat insulation, heat preservation and sealing, the weight of the laboratory terrace reaches thousands of tons, the heat load is huge, secondly, the laboratory terrace is used for accurately simulating the heat transfer process between air and the terrace, the interior of the terrace and the loess layer at the bottom of the terrace, the heat transfer process inside the terrace is layered according to the heat convection, the heat transfer principle and the feasibility of numerical calculation, the heat transfer process is carried out on the interior of the terrace, and the heat load data can be obtained according to the actual conditions and aiming at the ground compared with the simple heat load calculation of a constant value.
Preferably, the setting procedure of the step S14 for the parameters is:
s14-1, setting target parameters: initial air temperature value
Figure 100002_DEST_PATH_IMAGE266
Outdoor air temperature
Figure 100002_DEST_PATH_IMAGE268
Target temperature rise/fall
Figure 100002_DEST_PATH_IMAGE270
；
S14-2, setting laboratory size: height
Figure 100002_DEST_PATH_IMAGE272
Width, width
Figure 100002_DEST_PATH_IMAGE274
Length, length
Figure 100002_DEST_PATH_IMAGE276
；
S14-3, setting air parameters: volume of air
Figure 100002_DEST_PATH_IMAGE277
Specific heat coefficient of air
Figure 100002_DEST_PATH_IMAGE278
Air density
Figure 100002_DEST_PATH_IMAGE279
Correction factor
Figure 100002_DEST_PATH_IMAGE280
；
S14-4, setting the parameters of the heat preservation plate: thickness of
Figure 100002_DEST_PATH_IMAGE281
Coefficient of heat transfer
Figure 100002_DEST_PATH_IMAGE282
；
S14-5, setting floor parameters: floor area
Figure 100002_DEST_PATH_IMAGE284
Specific heat coefficient
Figure 100002_DEST_PATH_IMAGE285
Density, density
Figure 100002_DEST_PATH_IMAGE286
Coefficient of heat transfer
Figure 100002_DEST_PATH_IMAGE287
；
S14-6, setting compensation fresh air parameters: compensating for fresh air quality
Figure 100002_DEST_PATH_IMAGE288
Compensating fresh air temperature
Figure 100002_DEST_PATH_IMAGE289
；
S14-7, setting steel structure parameters: quality of steel structure
Figure 100002_DEST_PATH_IMAGE290
Specific heat coefficient of steel material
Figure 100002_DEST_PATH_IMAGE291
；
S14-8, setting fan parameters: number of fans
Figure 100002_DEST_PATH_IMAGE292
Air quantity of fan
Figure 100002_DEST_PATH_IMAGE293
(ii) a Draught fan pressure head
Figure 100002_DEST_PATH_IMAGE294
(ii) a Factor of safety
Figure 100002_DEST_PATH_IMAGE295
；
S14-9, is providedDetermining airplane parameters: coefficient of convective heat transfer
Figure 100002_DEST_PATH_IMAGE296
Aircraft surface area
Figure 100002_DEST_PATH_IMAGE297
Specific heat coefficient of airplane
Figure 100002_DEST_PATH_IMAGE298
Aircraft mass
Figure 100002_DEST_PATH_IMAGE299
；
S14-10, setting refrigeration/heating parameters: margin coefficient
Figure 100002_DEST_PATH_IMAGE300
。
The multi-parameter settings enable the model to derive actual transient thermal load data from the laboratory environment.
Further preferably, in step S15, the differential equation set of S10 to S13 is solved by using the longguta numerical method, and after numerical calculation results of the air temperature, the temperature of each floor layer, and the aircraft temperature are obtained, the temperature data are used to determine the thermal load data of each component structure and load of the laboratory under the condition of load according to the thermal load model calculation of steps S1 to S8, and the longguta (rubber-Kutta) numerical method is a high-precision single-step algorithm widely applied to engineering, and includes a well-known eulerian method, which is used for numerically solving the differential equation, and has the advantages of high precision, convergence, and stability.
The invention has the beneficial effects that:
(1) the invention provides an air heat load calculation model considering temperature influence, wherein a model correction factor
Figure DEST_PATH_IMAGE301
Can correct the air quality change caused by temperature change in the temperature rise/fall process, solves the problem of large air transient load calculation deviation, and improves the air transientAccuracy of the state load calculation;
(2) aiming at different working conditions, the invention provides a variable-parameter terrace heat load model, in the step, as the adjusting range of a large-scale airplane climate environment laboratory is-55 ℃ to +74 ℃, in the temperature rising/reducing process of the laboratory, the strong convection heat exchange coefficient of air and a floor is a non-constant value, in order to simplify the analysis and calculation and not lose the accuracy, the linear variable-parameter terrace heat load model is established to solve the problem, thereby achieving the accurate calculation of the terrace transient load;
(3) the invention provides a variable working condition refrigerating/heating system model, which realizes dynamic simulation of cold/heat, and as the refrigerating capacity and the heating capacity of a laboratory under different test working conditions are different, and the working characteristics of the laboratory refrigerating/heating system under the variable working conditions are combined, a piecewise linear refrigerating/heating system model is established to solve the problem of dynamic application of cold/heat, thereby improving the calculation accuracy;
(4) the invention aims at the uniqueness of large bearing capacity and heat insulation of the laboratory floor structure, because the top layer of the terrace of the large airplane climate environment laboratory has strong convection heat exchange with air, the bottom terrace and the loess layer have heat insulation treatment, and the terrace is used as the maximum heat sink of the laboratory, in order to accurately calculate the heat load of the terrace, according to the characteristics of the terrace structure, the modeling of the heat transfer process of the terrace is carried out in a layered mode, the corresponding heat transfer equation comprises three forms, the temperature change equation of the top-layer terrace considers two factors of convective heat transfer with air and heat conduction with the lower-layer terrace, the temperature change equation of the middle-layer terrace considers heat conduction with the upper-layer terrace and the lower-layer terrace, the temperature change equation of the bottommost terrace only needs to consider heat conduction with the upper-layer terrace, a floor layered heat transfer interpolation model considering two modes of convective heat transfer and heat conduction is provided, and accurate simulation of the temperature reduction process of the terrace is achieved;
(5) aiming at the uniqueness that the laboratory floor structure has large bearing capacity and contains heat insulation, because the top layer of the terrace of the laboratory in the climate environment of a large airplane has strong heat convection with air, the heat insulation treatment is carried out between the bottommost terrace and the loess layer, the terrace is used as the maximum heat sink of the laboratory, and in order to accurately calculate the heat load of the terrace, the layered treatment is adopted for modeling the heat transfer process of the terrace according to the characteristics of the terrace structure, and the corresponding heat transfer equation comprises three forms: firstly, a top-layer terrace temperature change equation considers two factors of convective heat transfer with air and heat conduction with a lower-layer terrace, secondly, a middle-layer terrace temperature change equation considers heat conduction with an upper-layer terrace and a lower-layer terrace, and thirdly, a bottommost terrace temperature change equation only needs to consider heat conduction with the upper-layer terrace; a floor layered heat transfer interpolation model considering two modes of convection heat transfer and heat conduction is provided, and the accurate simulation of the floor cooling process is realized;
(6) the method of the invention considers that the aircraft climate environment laboratory has large volume and very large heat consumption, so that the energy can be saved to the maximum extent in the process of regulating and controlling the laboratory environment only by finely researching the heat change process of the aircraft climate environment laboratory, and the invention is used as a method for researching the temperature rising and falling transient load in the aircraft climate environment laboratory under the load (aircraft) state, and comprises a transient heat load model of all heat consumption generating sources (air in the environment, a heat insulation plate, a terrace with a special concrete structure containing 8 percent of stainless steel reinforcing ribs, an aircraft serving as a carrier, a fresh air system, an illuminating lamp and a steel structure), thereby being capable of obtaining the most practical transient load value according to the specific parameters of the aircraft climate environment laboratory, ensuring that the heat energy required by the temperature change in the aircraft climate environment laboratory can realize the datamation effect, the method has good popularization significance and prospect in the field of airplane design and manufacture.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The terminology used in the embodiments of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. As used in the examples of the present invention and the appended claims, the singular forms "a", "an", and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise, and "a plurality" typically includes at least two.
Examples
The embodiment relates to a temperature rise and fall transient load analysis method for a large aircraft climate environment laboratory, which specifically comprises the following steps:
s1, establishing an air heat load model taking the corrected temperature as a parameter, wherein the model formula is as follows:
Figure DEST_PATH_IMAGE302
in the formula:
Figure 469540DEST_PATH_IMAGE004
for the purpose of the air transient load,
Figure 386680DEST_PATH_IMAGE006
in order to be a model-modifying factor,
Figure 900838DEST_PATH_IMAGE008
is the volume of the air in the room,
Figure 296047DEST_PATH_IMAGE010
is the air density at normal temperature and pressure,
Figure DEST_PATH_IMAGE303
is the specific heat coefficient of the air,
Figure 907157DEST_PATH_IMAGE014
for the numerical calculation of the current air temperature during the process,
Figure 464041DEST_PATH_IMAGE016
for numerically calculating the air temperature at the previous moment in the process,
Figure 731074DEST_PATH_IMAGE006
the air quality change caused by temperature change in the temperature rising/lowering process can be corrected, and the problem of large air transient load calculation deviation is solved;
s2, considering the laboratory situation, assuming the conditions: 1) the ambient air temperature outside the laboratory chamber does not change; 2) the temperature of the inner/outer surface of the heat-insulation board is respectively the same as the air temperature inside and outside the laboratory, and the heat load model of the heat-insulation board is established as follows:
Figure 929974DEST_PATH_IMAGE148
in the formula:
Figure 395590DEST_PATH_IMAGE150
in order to provide the thermal load of the insulation board,
Figure 388954DEST_PATH_IMAGE152
is the heat transfer coefficient of the heat-insulating plate,
Figure 143284DEST_PATH_IMAGE154
is the surface area of the heat-insulating plate in the laboratory,
Figure 614716DEST_PATH_IMAGE156
is the thickness of the heat-preserving plate,
Figure 138102DEST_PATH_IMAGE158
the temperature of the inner surface of the current insulation board in the numerical calculation process is the same as the air temperature,
Figure 364684DEST_PATH_IMAGE160
the temperature of the outer surface of the current insulation board in the numerical calculation process is the same as the temperature of outdoor air;
s3, establish the heat load model of terrace, consider that the heat transfer mode of terrace and air in the laboratory is strong convection heat transfer form, the strong convection heat transfer coefficient between terrace and air is variable linear parameter in this method, and the functional relation between strong convection heat transfer coefficient and the air temperature is:
Figure 606309DEST_PATH_IMAGE162
in the formula:
Figure DEST_PATH_IMAGE304
in order to have a strong convective heat transfer coefficient,
Figure DEST_PATH_IMAGE305
for the numerical calculation of the current air temperature during the process,
Figure 615853DEST_PATH_IMAGE168
in order to fix the constant of 29.28,
Figure 67781DEST_PATH_IMAGE170
is a linear factor with the value of 0.071,
the heat load model of the terrace is:
Figure 402947DEST_PATH_IMAGE018
in the formula:
Figure 866289DEST_PATH_IMAGE020
in order to be the heat load of the terrace,
Figure 945104DEST_PATH_IMAGE022
in order to have a strong convective heat transfer coefficient,
Figure 443081DEST_PATH_IMAGE024
in order to provide a floor area for a laboratory,
Figure 11466DEST_PATH_IMAGE026
for the numerical calculation of the current air temperature during the process,
Figure 696525DEST_PATH_IMAGE028
the temperature of the top floor in the terrace;
s4, establishing a compensation fresh air heat load model, wherein the established compensation fresh air heat load model is as follows according to the characteristic that the air supply temperature of the compensation fresh air in the laboratory is a constant value:
Figure 579031DEST_PATH_IMAGE172
in the formula:
Figure 931514DEST_PATH_IMAGE174
in order to compensate for the heat load of the fresh air,
Figure 670800DEST_PATH_IMAGE176
is the specific heat coefficient of the air,
Figure 108735DEST_PATH_IMAGE178
in order to compensate for the mass of the fresh air,
Figure 529352DEST_PATH_IMAGE180
for the purpose of numerically calculating the current air temperature,
Figure DEST_PATH_IMAGE306
to compensate for fresh air temperature;
s5, establishing a steel structure heat load model, and setting the preconditions as follows: 1) the temperature of the steel structure is the same as the initial air temperature of the air in the laboratory; 2) the air temperature change rate in the steel structure and the laboratory is the same, and the following steel structure transient heat load model can be obtained according to a heat calculation formula:
Figure DEST_PATH_IMAGE307
in the formula:
Figure DEST_PATH_IMAGE308
for the transient load of the steel structure,
Figure 533080DEST_PATH_IMAGE034
the mass of the steel structure is the weight of the steel structure,
Figure 380950DEST_PATH_IMAGE036
is the specific heat coefficient of the steel material,
Figure 306181DEST_PATH_IMAGE038
for numerically calculating the current steel structure temperature during the process,
Figure DEST_PATH_IMAGE309
calculating the temperature of the steel structure at the previous moment in the process for the numerical value;
s6, establishing a fan thermal load model, wherein the effective power of the fan under the standard working condition is as follows:
Figure DEST_PATH_IMAGE310
in the formula:
Figure 327227DEST_PATH_IMAGE186
the effective power of the fan is the effective power of the fan,
Figure 123144DEST_PATH_IMAGE188
the air quantity of the fan is adopted,
Figure 407495DEST_PATH_IMAGE190
is a pressure head of the fan,
Figure 820022DEST_PATH_IMAGE192
in order to be a safety factor,
the air temperature variation range of the laboratory is-55 ℃ to +74 ℃, and according to the characteristics that the air output of a laboratory fan is large under a high-temperature working condition and small under a low-temperature working condition, the following variable working condition thermal load model is established:
Figure DEST_PATH_IMAGE311
in the formula:
Figure 644758DEST_PATH_IMAGE044
for heat load of fan，
Figure 826341DEST_PATH_IMAGE046
In order to increase the number of the fans,
Figure 750435DEST_PATH_IMAGE048
is the effective power of a single fan,
Figure 650258DEST_PATH_IMAGE050
calculating the current air temperature for the value;
s7, establishing a lighting heat load model with a constant value:
Figure 216368DEST_PATH_IMAGE194
in the formula:
Figure DEST_PATH_IMAGE312
in order to illuminate the heat load,
Figure DEST_PATH_IMAGE313
is a constant;
s8, because the maximum load of the laboratory is a large-scale transport airplane with C5, in order to accurately calculate the heat load, an airplane heat load model is established according to the convection heat exchange principle:
Figure 49195DEST_PATH_IMAGE052
in the formula:
Figure 206507DEST_PATH_IMAGE054
in order to be a thermal load of the aircraft,
Figure 593626DEST_PATH_IMAGE056
in order to obtain a convective heat transfer coefficient,
Figure 963427DEST_PATH_IMAGE058
the surface area of the aircraft is,
Figure 588444DEST_PATH_IMAGE060
for the numerical calculation of the current air temperature during the process,
Figure 385498DEST_PATH_IMAGE062
is the temperature of the aircraft surface;
and S9, establishing a refrigeration/heating system model. According to the working mode of a refrigerating and heating system and the characteristics of cold quantity/heat quantity application selected by a laboratory, the following sectional type cold quantity/heat quantity model is established:
Figure 994334DEST_PATH_IMAGE064
in the formula:
Figure 964564DEST_PATH_IMAGE066
the cold/heat provided to the refrigeration/heating system,
Figure 975246DEST_PATH_IMAGE068
as a coefficient of the margin, is,
Figure 677622DEST_PATH_IMAGE070
calculating the current air temperature for the value;
s10, establishing an indoor air temperature dynamic change equation, and assuming the conditions as follows: 1) the temperature of the steel structure is the same as the initial air temperature of the air in the laboratory; 2) the air temperature change rate in the steel structure and the laboratory is the same, and according to the assumption and the heat balance principle, the following air temperature dynamic differential equation is established:
Figure 773754DEST_PATH_IMAGE072
in the formula:
Figure 282096DEST_PATH_IMAGE074
is air temperature versus time
Figure 147284DEST_PATH_IMAGE076
The rate of change of (a) is,
Figure 286141DEST_PATH_IMAGE078
is the temperature of the air in the room,
Figure 603990DEST_PATH_IMAGE080
is the temperature of the top-layer terrace,
Figure 853706DEST_PATH_IMAGE082
for the surface temperature of the aircraft as a load,
Figure 838979DEST_PATH_IMAGE084
is the set point of the air temperature,
Figure 945476DEST_PATH_IMAGE086
the cold/heat provided to the refrigeration/heating system,
Figure 16200DEST_PATH_IMAGE088
in order to provide the thermal load of the insulation board,
Figure 804027DEST_PATH_IMAGE090
in order to provide the heat load of the terrace,
Figure 643807DEST_PATH_IMAGE092
in order to compensate for the heat load of the fresh air,
Figure 921205DEST_PATH_IMAGE094
in order to provide a thermal load for the fan,
Figure 213646DEST_PATH_IMAGE096
in order to illuminate the heat load,
Figure 805164DEST_PATH_IMAGE098
which is indicative of the thermal load of the aircraft,
Figure 499451DEST_PATH_IMAGE100
in order to obtain the quality of the air in the room,
Figure 151012DEST_PATH_IMAGE102
、
Figure 993066DEST_PATH_IMAGE104
the specific heat coefficients of air and a steel structure respectively,
Figure 388275DEST_PATH_IMAGE106
the mass of the steel structure is the weight of the steel structure,
Figure 937068DEST_PATH_IMAGE108
representing a dynamic variation function of air temperature;
s11, according to the concrete structure and the weight of laboratory terrace, divide into 13 layers with the terrace, establish the terrace temperature dynamic change equation that is used for calculating the 1 st floor, 2 nd ~12 th floor, 13 th floor terrace temperature rate of change respectively to the temperature dynamic change equation of the terrace through 3 kinds of forms calculates respectively, and the temperature dynamic change equation of terrace is respectively:
the temperature change equation of the floor at the 1 st layer:
Figure DEST_PATH_IMAGE314
in the formula:
Figure 759531DEST_PATH_IMAGE202
for top floor temperature versus time
Figure 26564DEST_PATH_IMAGE204
The rate of change of (a) is,
Figure DEST_PATH_IMAGE315
is the temperature of the air in the room,
Figure DEST_PATH_IMAGE316
is the current temperature of the top floor level,
Figure 756623DEST_PATH_IMAGE210
is the current temperature of the lower floor level,
Figure DEST_PATH_IMAGE317
in order to have a strong convective heat transfer coefficient,
Figure 956660DEST_PATH_IMAGE214
as to the density of the terrace,
Figure DEST_PATH_IMAGE318
is the specific heat coefficient of the terrace,
Figure 950024DEST_PATH_IMAGE218
the thickness of the terrace is the thickness of the terrace,
Figure 704353DEST_PATH_IMAGE220
for the heat transfer coefficient of the terrace,
Figure 441365DEST_PATH_IMAGE222
the temperature change function of the grade level of the layer 1 is shown,
temperature change equation of 2 nd to 12 th floor:
Figure DEST_PATH_IMAGE319
in the formula: integer number of
Figure 761488DEST_PATH_IMAGE226
Has a value range of
Figure 191332DEST_PATH_IMAGE228
，
Figure 901799DEST_PATH_IMAGE230
For middle floor temperature versus time
Figure DEST_PATH_IMAGE320
The rate of change of (a) is,
Figure DEST_PATH_IMAGE321
is the current temperature of the upper floor,
Figure 973660DEST_PATH_IMAGE235
is the current temperature of the intermediate floor level,
Figure 617131DEST_PATH_IMAGE237
is the current temperature of the next floor level,
Figure 952298DEST_PATH_IMAGE239
for the heat transfer coefficient of the terrace,
Figure 477957DEST_PATH_IMAGE241
the thickness of the terrace is the thickness of the terrace,
Figure 556772DEST_PATH_IMAGE243
as to the density of the terrace,
Figure DEST_PATH_IMAGE322
is the specific heat coefficient of the terrace,
the 13 th floor temperature change equation:
Figure DEST_PATH_IMAGE323
in the formula:
Figure DEST_PATH_IMAGE324
for insulating layer terrace temperature vs. time
Figure 789170DEST_PATH_IMAGE250
The rate of change of (a) is,
Figure 91975DEST_PATH_IMAGE252
is the current temperature of the 12 th floor,
Figure 42614DEST_PATH_IMAGE254
is the current temperature of the 13 th floor,
Figure 925119DEST_PATH_IMAGE256
for the heat transfer coefficient of the terrace,
Figure 277603DEST_PATH_IMAGE258
the thickness of the terrace is the thickness of the terrace,
Figure DEST_PATH_IMAGE325
as to the density of the terrace,
Figure 16889DEST_PATH_IMAGE262
is the specific heat coefficient of the terrace,
Figure 454823DEST_PATH_IMAGE264
representing the temperature change function of the 13 th floor;
s12, establishing a temperature dynamic change equation of the airplane:
Figure DEST_PATH_IMAGE326
in the formula:
Figure DEST_PATH_IMAGE327
for aircraft temperature versus time
Figure 609861DEST_PATH_IMAGE114
The rate of change of (a) is,
Figure 879168DEST_PATH_IMAGE116
is the convective heat transfer coefficient between the air and the aircraft,
Figure 461460DEST_PATH_IMAGE118
is the temperature of the air in the room,
Figure 386690DEST_PATH_IMAGE120
the surface area of the aircraft is,
Figure 610998DEST_PATH_IMAGE122
for the surface temperature of the aircraft as a load,
Figure 734812DEST_PATH_IMAGE124
is a planeThe amount of the compound (A) is,
Figure DEST_PATH_IMAGE328
is the specific heat coefficient of the aircraft,
Figure 19163DEST_PATH_IMAGE128
representing a function of aircraft temperature dynamics;
s13, establishing an integral temperature dynamic change equation set:
Figure DEST_PATH_IMAGE329
in the formula:
Figure 166110DEST_PATH_IMAGE132
in the form of a temperature rate-of-change matrix,
Figure 725268DEST_PATH_IMAGE134
in the form of a temperature matrix, the temperature matrix,
Figure 906850DEST_PATH_IMAGE136
in the form of an initial temperature matrix, the temperature,
Figure 362102DEST_PATH_IMAGE138
it is the temperature of the air that is,
Figure 996346DEST_PATH_IMAGE140
in order to obtain the temperature of each floor,
Figure 562457DEST_PATH_IMAGE142
，
Figure 598546DEST_PATH_IMAGE144
is the aircraft surface temperature;
Figure DEST_PATH_IMAGE330
is an initial temperature value;
s14, setting related parameters:
s14-1, setting target parameters: initial air temperature value
Figure DEST_PATH_IMAGE331
Outdoor air temperature
Figure 755858DEST_PATH_IMAGE268
Target temperature rise/fall
Figure DEST_PATH_IMAGE332
；
S14-2, setting laboratory size: height
Figure 939714DEST_PATH_IMAGE272
Width, width
Figure 43936DEST_PATH_IMAGE274
Length, length
Figure DEST_PATH_IMAGE333
；
S14-3, setting air parameters: volume of air
Figure 934532DEST_PATH_IMAGE277
Specific heat coefficient of air
Figure 731587DEST_PATH_IMAGE278
Air density
Figure DEST_PATH_IMAGE334
Correction factor
Figure 137160DEST_PATH_IMAGE280
；
S14-4, setting the parameters of the heat preservation plate: thickness of
Figure 45074DEST_PATH_IMAGE281
Coefficient of heat transfer
Figure 55755DEST_PATH_IMAGE282
；
S14-5, setting floor parameters: floor area
Figure 820449DEST_PATH_IMAGE284
Specific heat coefficient
Figure 916580DEST_PATH_IMAGE285
Density, density
Figure 362605DEST_PATH_IMAGE286
Coefficient of heat transfer
Figure DEST_PATH_IMAGE335
；
S14-6, setting compensation fresh air parameters: compensating for fresh air quality
Figure 227793DEST_PATH_IMAGE288
Compensating fresh air temperature
Figure 366650DEST_PATH_IMAGE289
；
S14-7, setting steel structure parameters: quality of steel structure
Figure 746816DEST_PATH_IMAGE290
Specific heat coefficient of steel material
Figure 996532DEST_PATH_IMAGE291
；
S14-8, setting fan parameters: number of fans
Figure 716226DEST_PATH_IMAGE292
Air quantity of fan
Figure 25985DEST_PATH_IMAGE293
(ii) a Draught fan pressure head
Figure 893447DEST_PATH_IMAGE294
(ii) a Factor of safety
Figure 946853DEST_PATH_IMAGE295
；
S14-9, setting airplane parameters: coefficient of convective heat transfer
Figure 521054DEST_PATH_IMAGE296
Aircraft surface area
Figure DEST_PATH_IMAGE336
Specific heat coefficient of airplane
Figure 1714DEST_PATH_IMAGE298
Aircraft mass
Figure 90893DEST_PATH_IMAGE299
；
S14-10, setting refrigeration/heating parameters: margin coefficient
Figure 947990DEST_PATH_IMAGE300
；
S15, solving a differential equation set and calculating the transient load: and (3) respectively substituting the parameters in the step (S14) into the steps (S10), (S11) and (S12), respectively calculating the air temperature change rate, the temperature change rate of each floor layer and the aircraft temperature change rate, introducing the air temperature change rate, the temperature change rate of each floor layer and the aircraft temperature change rate into the step (S13) to calculate the temperature change rate of the whole laboratory under the load condition, calculating the transient load, and calculating and determining the heat load data of each component structure and the load of the laboratory under the load condition according to the heat load models in the steps (S1-S8) by using the temperature data.
Examples of the experiments
The experimental example is a transient load calculation process under the condition of laboratory load of the climate environment of the large aircraft based on the embodiment:
the large aircraft climate environment laboratory is divided into a large chamber and a small chamber which are communicated with each other, and in the process of raising the temperature from minus 7 ℃ to plus 74 ℃ under the condition of carrying a large transport aircraft with the American grade C5, the parameters in the step S14 are firstly set:
s14-1, setting target parameters: initial air temperature value
Figure DEST_PATH_IMAGE338
Outdoor air temperature
Figure DEST_PATH_IMAGE340
Target temperature rise/fall
Figure DEST_PATH_IMAGE342
；
S14-2, setting laboratory size: height
Figure DEST_PATH_IMAGE344
Width (big room)
Figure DEST_PATH_IMAGE346
Length (big room)
Figure DEST_PATH_IMAGE348
(ii) a Width (Small chamber)
Figure DEST_PATH_IMAGE350
Length (cell)
Figure DEST_PATH_IMAGE352
；
S14-3, setting air parameters: volume of air
Figure DEST_PATH_IMAGE354
Specific heat coefficient of air
Figure DEST_PATH_IMAGE356
Air density
Figure DEST_PATH_IMAGE358
Correction factor
Figure DEST_PATH_IMAGE360
；
S14-4, setting the parameters of the heat preservation plate: thickness of
Figure DEST_PATH_IMAGE362
Coefficient of heat transfer
Figure DEST_PATH_IMAGE364
；
S14-5, setting floor parameters: specific heat coefficient
Figure DEST_PATH_IMAGE366
Density, density
Figure DEST_PATH_IMAGE368
Coefficient of heat transfer
Figure DEST_PATH_IMAGE370
Floor area
Figure DEST_PATH_IMAGE372
；
S14-6, setting compensation fresh air parameters: compensating for fresh air quality
Figure DEST_PATH_IMAGE374
Compensating fresh air temperature
Figure DEST_PATH_IMAGE376
；
S14-7, setting steel structure parameters: quality of steel structure
Figure DEST_PATH_IMAGE378
(ii) a Specific heat coefficient of steel material
Figure DEST_PATH_IMAGE380
；
S14-8, setting fan parameters: number of fans
Figure DEST_PATH_IMAGE382
Air quantity of fan
Figure DEST_PATH_IMAGE384
(ii) a Draught fan pressure head
Figure DEST_PATH_IMAGE386
(ii) a Factor of safety
Figure DEST_PATH_IMAGE388
；
S14-9, settingAirplane parameters: coefficient of convective heat transfer
Figure DEST_PATH_IMAGE390
Aircraft surface area
Figure DEST_PATH_IMAGE392
Aircraft mass
Figure DEST_PATH_IMAGE394
；
S14-10, setting refrigeration/heating parameters: margin coefficient
Figure DEST_PATH_IMAGE396
。
Establishing a differential equation set according to the steps S10-S13, and calculating a temperature matrix according to the Runge-Kutta numerical method adopted in the step S15;
calculating the heat load of each component according to the temperature change matrix and steps S1-S8, wherein the load calculation results of the partial temperature points are as follows:
laboratory air temperature (C degree) -710.0203074
Time (hrs) 0.00.40.71.18.4
Indoor air load (kW) -2812.9-1797-1255.3-803.4-148.6
Terrace load (kW) is 0.0-1420.1-2248.1-3015.4-4190
Steel structure load (kW) -3763.8-2548.3-1842.11-1218.7-258.1
The load (kW) of the heat-insulating board is 57.8-0.5-37.473.7-235.5
Fan load (kW) 700.9661.7639.1618.3540.0
Lighting load (kW) 9090909090
Compensating air load (kW) 0.0-267.5-436.8-603.1-1345.2
Aircraft load (kW) 0.0-445.3-637.4-722.0-180.7.

Claims (8)

1. The method for analyzing the temperature rise and fall transient load of the large airplane in the climate environment laboratory is characterized by comprising the following steps of:
s1, establishing an air heat load model taking the corrected temperature as a parameter, wherein the model formula is as follows:
Figure DEST_PATH_IMAGE002
in the formula:
Figure DEST_PATH_IMAGE004
for the purpose of the air transient load,
Figure DEST_PATH_IMAGE006
in order to be a model-modifying factor,
Figure DEST_PATH_IMAGE008
is the volume of the air in the room,
Figure DEST_PATH_IMAGE010
is the air density at normal temperature and pressure,
Figure DEST_PATH_IMAGE012
is the specific heat coefficient of the air,
Figure DEST_PATH_IMAGE014
for the numerical calculation of the current air temperature during the process,
Figure DEST_PATH_IMAGE016
calculating the air temperature at the previous moment in the process for the numerical value;
s2, considering the laboratory situation, setting the preconditions as: the temperature of the air outside the laboratory is not changed, and the temperature of the inner/outer surface of the heat-insulation plate is respectively the same as the temperature of the air inside and outside the laboratory, so that a heat load model of the heat-insulation plate is established;
s3, establishing a terrace heat load model:
Figure DEST_PATH_IMAGE018
in the formula:
Figure DEST_PATH_IMAGE020
in order to be the heat load of the terrace,
Figure DEST_PATH_IMAGE022
in order to have a strong convective heat transfer coefficient,
Figure DEST_PATH_IMAGE024
in order to provide a floor area for a laboratory,
Figure DEST_PATH_IMAGE026
for the numerical calculation of the current air temperature during the process,
Figure DEST_PATH_IMAGE028
the temperature of the top floor in the terrace;
s4, establishing a wind heat load compensation model according to the characteristic that the air supply temperature of the laboratory compensation fresh air is a constant value;
s5, establishing a steel structure heat load model, and setting the preconditions as follows: the initial air temperature in the steel structure and the laboratory is the same and the air temperature change rate in the steel structure and the laboratory is the same, and according to a heat calculation formula, the following steel structure transient heat load model is obtained:
Figure DEST_PATH_IMAGE030
in the formula:
Figure DEST_PATH_IMAGE032
for the transient load of the steel structure,
Figure DEST_PATH_IMAGE034
the mass of the steel structure is the weight of the steel structure,
Figure DEST_PATH_IMAGE036
is the specific heat coefficient of the steel material,
Figure DEST_PATH_IMAGE038
for numerically calculating the current steel structure temperature during the process,
Figure DEST_PATH_IMAGE040
calculating the temperature of the steel structure at the previous moment in the process for the numerical value;
s6, establishing a fan thermal load model, wherein the air temperature variation range of a laboratory is-55 to +74 ℃, and according to the characteristics that the air output of the laboratory fan is large under a high-temperature working condition and small under a low-temperature working condition, establishing the following variable working condition thermal load model:
Figure DEST_PATH_IMAGE042
in the formula:
Figure DEST_PATH_IMAGE044
in order to provide a thermal load for the fan,
Figure DEST_PATH_IMAGE046
in order to increase the number of the fans,
Figure DEST_PATH_IMAGE048
is the effective power of a single fan,
Figure DEST_PATH_IMAGE050
calculating the current air temperature for the value;
s7, establishing a lighting heat load model with a constant value;
s8, because the maximum load of the laboratory is a large-scale transport airplane with C5, in order to accurately calculate the heat load, an airplane heat load model is established according to the convection heat exchange principle:
Figure DEST_PATH_IMAGE052
in the formula:
Figure DEST_PATH_IMAGE054
in order to be a thermal load of the aircraft,
Figure DEST_PATH_IMAGE056
in order to obtain a convective heat transfer coefficient,
Figure DEST_PATH_IMAGE058
the surface area of the aircraft is,
Figure DEST_PATH_IMAGE060
for the numerical calculation of the current air temperature during the process,
Figure DEST_PATH_IMAGE062
is the temperature of the aircraft surface;
s9, establishing a refrigeration/heating system model, and establishing the following sectional type refrigeration/heating model according to the refrigeration/heating system working mode and refrigeration/heating application characteristics selected by a laboratory:
Figure DEST_PATH_IMAGE064
in the formula:
Figure DEST_PATH_IMAGE066
the cold/heat provided to the refrigeration/heating system,
Figure DEST_PATH_IMAGE068
is a great marginThe coefficient of the quantity is,
Figure DEST_PATH_IMAGE070
calculating the current air temperature for the value;
s10, establishing an indoor air temperature dynamic change equation, and setting the preconditions as follows: the initial air temperature of the steel structure in the laboratory is the same as that of the air in the laboratory, and the change rate of the air temperature of the steel structure in the laboratory is the same as that of the air in the laboratory, and according to the heat balance principle, the following air temperature dynamic differential equation is established:
Figure DEST_PATH_IMAGE072
in the formula:
Figure DEST_PATH_IMAGE074
is air temperature versus time
Figure DEST_PATH_IMAGE076
The rate of change of (a) is,
Figure DEST_PATH_IMAGE078
is the temperature of the air in the room,
Figure DEST_PATH_IMAGE080
is the temperature of the top-layer terrace,
Figure DEST_PATH_IMAGE082
for the surface temperature of the aircraft as a load,
Figure DEST_PATH_IMAGE084
is the set point of the air temperature,
Figure DEST_PATH_IMAGE086
the cold/heat provided to the refrigeration/heating system,
Figure DEST_PATH_IMAGE088
in order to provide the thermal load of the insulation board,
Figure DEST_PATH_IMAGE090
in order to provide the heat load of the terrace,
Figure DEST_PATH_IMAGE092
in order to compensate for the heat load of the fresh air,
Figure DEST_PATH_IMAGE094
in order to provide a thermal load for the fan,
Figure DEST_PATH_IMAGE096
in order to illuminate the heat load,
Figure DEST_PATH_IMAGE098
which is indicative of the thermal load of the aircraft,
Figure DEST_PATH_IMAGE100
in order to obtain the quality of the air in the room,
Figure DEST_PATH_IMAGE102
、
Figure DEST_PATH_IMAGE104
the specific heat coefficients of air and a steel structure respectively,
Figure DEST_PATH_IMAGE106
the mass of the steel structure is the weight of the steel structure,
Figure DEST_PATH_IMAGE108
representing a dynamic variation function of air temperature;
s11, according to the concrete structure and the weight of laboratory terrace, divide into 13 layers with the terrace, establish the terrace temperature dynamic change equation that is used for calculating the 1 st floor, 2~12 th floor, 13 th floor temperature rate of change respectively, the temperature dynamic change equation of terrace is respectively for in step S11:
the temperature change equation of the floor at the 1 st layer:
Figure DEST_PATH_IMAGE110
in the formula:
Figure DEST_PATH_IMAGE112
for top floor temperature versus time
Figure DEST_PATH_IMAGE114
The rate of change of (a) is,
Figure DEST_PATH_IMAGE116
is the temperature of the air in the room,
Figure DEST_PATH_IMAGE118
is the current temperature of the top floor level,
Figure DEST_PATH_IMAGE120
is the current temperature of the lower floor level,
Figure DEST_PATH_IMAGE122
in order to have a strong convective heat transfer coefficient,
Figure DEST_PATH_IMAGE124
as to the density of the terrace,
Figure DEST_PATH_IMAGE126
is the specific heat coefficient of the terrace,
Figure DEST_PATH_IMAGE128
the thickness of the terrace is the thickness of the terrace,
Figure DEST_PATH_IMAGE130
for the heat transfer coefficient of the terrace,
Figure DEST_PATH_IMAGE132
the temperature change function of the grade level of the layer 1 is shown,
temperature change equation of 2 nd to 12 th floor:
Figure DEST_PATH_IMAGE134
in the formula: integer number of
Figure DEST_PATH_IMAGE136
Has a value range of
Figure DEST_PATH_IMAGE138
，
Figure DEST_PATH_IMAGE140
For middle floor temperature versus time
Figure DEST_PATH_IMAGE141
The rate of change of (a) is,
Figure DEST_PATH_IMAGE143
is the current temperature of the upper floor,
Figure DEST_PATH_IMAGE145
is the current temperature of the intermediate floor level,
Figure DEST_PATH_IMAGE147
is the current temperature of the next floor level,
Figure DEST_PATH_IMAGE149
for the heat transfer coefficient of the terrace,
Figure DEST_PATH_IMAGE151
the thickness of the terrace is the thickness of the terrace,
Figure DEST_PATH_IMAGE153
as to the density of the terrace,
Figure DEST_PATH_IMAGE155
is the specific heat coefficient of the terrace,
the 13 th floor temperature change equation:
Figure DEST_PATH_IMAGE157
in the formula:
Figure DEST_PATH_IMAGE159
for insulating layer terrace temperature vs. time
Figure DEST_PATH_IMAGE160
The rate of change of (a) is,
Figure DEST_PATH_IMAGE162
is the current temperature of the 12 th floor,
Figure DEST_PATH_IMAGE164
is the current temperature of the 13 th floor,
Figure DEST_PATH_IMAGE166
for the heat transfer coefficient of the terrace,
Figure DEST_PATH_IMAGE168
the thickness of the terrace is the thickness of the terrace,
Figure DEST_PATH_IMAGE170
as to the density of the terrace,
Figure DEST_PATH_IMAGE172
is the specific heat coefficient of the terrace,
Figure DEST_PATH_IMAGE174
representing the temperature change function of the 13 th floor;
s12, establishing a temperature dynamic change equation of the airplane:
Figure DEST_PATH_IMAGE176
in the formula:
Figure DEST_PATH_IMAGE178
for aircraft temperature versus time
Figure DEST_PATH_IMAGE180
The rate of change of (a) is,
Figure DEST_PATH_IMAGE182
is the convective heat transfer coefficient between the air and the aircraft,
Figure DEST_PATH_IMAGE184
is the temperature of the air in the room,
Figure DEST_PATH_IMAGE186
the surface area of the aircraft is,
Figure DEST_PATH_IMAGE188
for the surface temperature of the aircraft as a load,
Figure DEST_PATH_IMAGE190
in order to be the mass of the aircraft,
Figure DEST_PATH_IMAGE192
is the specific heat coefficient of the aircraft,
Figure DEST_PATH_IMAGE194
representing a function of aircraft temperature dynamics;
s13, establishing an integral temperature dynamic change equation set:
Figure DEST_PATH_IMAGE196
in the formula:
Figure DEST_PATH_IMAGE198
in the form of a temperature rate-of-change matrix,
Figure DEST_PATH_IMAGE200
in the form of a temperature matrix, the temperature matrix,
Figure DEST_PATH_IMAGE202
in the form of an initial temperature matrix, the temperature,
Figure DEST_PATH_IMAGE204
it is the temperature of the air that is,
Figure DEST_PATH_IMAGE206
in order to obtain the temperature of each floor,
Figure DEST_PATH_IMAGE208
，
Figure DEST_PATH_IMAGE210
is the aircraft surface temperature;
Figure DEST_PATH_IMAGE212
is an initial temperature value;
s14, setting relevant parameters;
s15, substituting the parameters in step S14 into step S10, step S11, and step S12, respectively, obtaining the air temperature change rate, the floor-level layer temperature change rate, and the airplane temperature change rate, respectively, then importing the air temperature change rate, the floor-level layer temperature change rate, and the airplane temperature change rate into step S13 to obtain the temperature change rate of the entire laboratory under load, and then calculating the transient load.
2. The method for analyzing the transient load of the climate environment laboratory of the large aircraft as claimed in claim 1, wherein the thermal load model of the thermal insulation board in the step S2 is:
Figure DEST_PATH_IMAGE214
in the formula:
Figure DEST_PATH_IMAGE216
in order to provide the thermal load of the insulation board,
Figure DEST_PATH_IMAGE218
is the heat transfer coefficient of the heat-insulating plate,
Figure DEST_PATH_IMAGE220
is the surface area of the heat-insulating plate in the laboratory,
Figure DEST_PATH_IMAGE222
is the thickness of the heat-preserving plate,
Figure DEST_PATH_IMAGE224
the temperature of the inner surface of the current insulation board in the numerical calculation process is the same as the air temperature,
Figure DEST_PATH_IMAGE226
the temperature of the outer surface of the current insulation board in the numerical calculation process is the same as the temperature of outdoor air.
3. The method for analyzing the transient load of the climate environment laboratory of the large aircraft as claimed in claim 1, wherein the heat transfer coefficient of strong convection between the floor and the air in the step S3 is a variable linear parameter, and the function relationship between the heat transfer coefficient of strong convection and the air temperature is as follows:
Figure DEST_PATH_IMAGE228
in the formula:
Figure DEST_PATH_IMAGE230
in order to have a strong convective heat transfer coefficient,
Figure DEST_PATH_IMAGE232
for the numerical calculation of the current air temperature during the process,
Figure DEST_PATH_IMAGE234
in order to be a fixed constant, the number of the first and second electrodes,
Figure DEST_PATH_IMAGE236
is a linear factor.
4. The method for analyzing the transient load of the climate environment laboratory of the large aircraft as claimed in claim 1, wherein the model for compensating the wind-heat load established in step S4 is:
Figure DEST_PATH_IMAGE238
in the formula:
Figure DEST_PATH_IMAGE240
in order to compensate for the heat load of the fresh air,
Figure DEST_PATH_IMAGE242
is the specific heat coefficient of the air,
Figure DEST_PATH_IMAGE244
in order to compensate for the mass of the fresh air,
Figure DEST_PATH_IMAGE246
for the purpose of numerically calculating the current air temperature,
Figure DEST_PATH_IMAGE248
to compensate for fresh air temperature.
5. The method for analyzing the transient load of the climate environment laboratory of the large aircraft according to claim 1, wherein the effective power of the fan under the standard working condition in the step S6 is as follows:
Figure DEST_PATH_IMAGE250
in the formula:
Figure DEST_PATH_IMAGE252
the effective power of the fan is the effective power of the fan,
Figure DEST_PATH_IMAGE254
the air quantity of the fan is adopted,
Figure DEST_PATH_IMAGE256
is a pressure head of the fan,
Figure DEST_PATH_IMAGE258
the safety factor is.
6. The method for analyzing the transient load of the climate environment laboratory of the large aircraft as claimed in claim 1, wherein in step S7, the lighting heat load model formula is:
Figure DEST_PATH_IMAGE260
in the formula:
Figure DEST_PATH_IMAGE262
in order to illuminate the heat load,
Figure DEST_PATH_IMAGE264
is a constant.
7. The method for analyzing the temperature-rise and drop transient load of the climate environment laboratory of the large aircraft as claimed in claim 1, wherein the setting procedure of the step S14 for the parameters is as follows:
s14-1, setting target parameters: initial air temperature value
Figure DEST_PATH_IMAGE266
Outdoor air temperature
Figure DEST_PATH_IMAGE268
Target temperature rise/fall
Figure DEST_PATH_IMAGE270
；
S14-2, setting laboratory size: height
Figure DEST_PATH_IMAGE272
Width, width
Figure DEST_PATH_IMAGE274
Length, length
Figure DEST_PATH_IMAGE276
；
S14-3, setting air parameters: volume of air
Figure DEST_PATH_IMAGE277
Specific heat coefficient of air
Figure DEST_PATH_IMAGE278
Air density
Figure DEST_PATH_IMAGE279
Correction factor
Figure DEST_PATH_IMAGE280
；
S14-4, setting the parameters of the heat preservation plate: thickness of
Figure DEST_PATH_IMAGE281
Coefficient of heat transfer
Figure DEST_PATH_IMAGE282
；
S14-5, setting floor parameters: floor area
Figure DEST_PATH_IMAGE284
Specific heat coefficient
Figure DEST_PATH_IMAGE285
Density, density
Figure DEST_PATH_IMAGE286
Coefficient of heat transfer
Figure DEST_PATH_IMAGE287
；
S14-6, setting compensation fresh air parameters: compensating for fresh air quality
Figure DEST_PATH_IMAGE288
Compensating fresh air temperature
Figure DEST_PATH_IMAGE289
；
S14-7, setting steel structure parameters: quality of steel structure
Figure DEST_PATH_IMAGE290
Specific heat coefficient of steel material
Figure DEST_PATH_IMAGE291
；
S14-8, setting fan parameters: number of fans
Figure DEST_PATH_IMAGE292
Air quantity of fan
Figure DEST_PATH_IMAGE293
(ii) a Draught fan pressure head
Figure DEST_PATH_IMAGE294
(ii) a Factor of safety
Figure DEST_PATH_IMAGE295
；
S14-9, setting airplane parameters: coefficient of convective heat transfer
Figure DEST_PATH_IMAGE296
Aircraft surface area
Figure DEST_PATH_IMAGE297
Specific heat coefficient of airplane
Figure DEST_PATH_IMAGE298
Aircraft mass
Figure DEST_PATH_IMAGE299
；
S14-10, setting refrigeration/heating parameters: margin coefficient
Figure DEST_PATH_IMAGE300
。
8. The method for analyzing the transient load of the laboratory in the climate environment of the large aircraft as claimed in claim 1, wherein in step S15, the system of differential equations of S10 to S13 is solved by using a longguta numerical method, and after numerical calculation results of the air temperature, the temperature of each floor layer and the aircraft temperature are obtained, the temperature data are used to calculate and determine the thermal load data of each component structure and load of the laboratory under the condition of load according to the thermal load model of steps S1 to S8.
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