CN113901590A - 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

Info

Publication number
CN113901590A
CN113901590A CN202111358691.9A CN202111358691A CN113901590A CN 113901590 A CN113901590 A CN 113901590A CN 202111358691 A CN202111358691 A CN 202111358691A CN 113901590 A CN113901590 A CN 113901590A
Authority
CN
China
Prior art keywords
temperature
air
heat
laboratory
load
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN202111358691.9A
Other languages
Chinese (zh)
Other versions
CN113901590B (en
Inventor
王彬文
成竹
吴敬涛
李闯勤
任战鹏
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
AVIC Aircraft Strength Research Institute
Original Assignee
AVIC Aircraft Strength Research Institute
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by AVIC Aircraft Strength Research Institute filed Critical AVIC Aircraft Strength Research Institute
Priority to CN202111358691.9A priority Critical patent/CN113901590B/en
Publication of CN113901590A publication Critical patent/CN113901590A/en
Application granted granted Critical
Publication of CN113901590B publication Critical patent/CN113901590B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2119/00—Details relating to the type or aim of the analysis or the optimisation
    • G06F2119/08—Thermal analysis or thermal optimisation

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Theoretical Computer Science (AREA)
  • Geometry (AREA)
  • General Physics & Mathematics (AREA)
  • Computer Hardware Design (AREA)
  • General Engineering & Computer Science (AREA)
  • Evolutionary Computation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Pure & Applied Mathematics (AREA)
  • Mathematical Optimization (AREA)
  • Mathematical Analysis (AREA)
  • Computational Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Air Conditioning Control Device (AREA)

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 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 realize the transient heat load of 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
as a coefficient of the margin, 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 reduce the heat loss of the heat-insulation plate,
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
representing the thermal load of the aircraft on the load,
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, 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 DEST_PATH_IMAGE110
in the formula:
Figure DEST_PATH_IMAGE112
for aircraft temperature versus time
Figure DEST_PATH_IMAGE114
The rate of change of (a) is,
Figure DEST_PATH_IMAGE116
is the convective heat transfer coefficient between the air and the aircraft,
Figure DEST_PATH_IMAGE118
is the current temperature of the indoor air,
Figure DEST_PATH_IMAGE120
the surface area of the aircraft is,
Figure DEST_PATH_IMAGE122
as is the current aircraft surface temperature,
Figure DEST_PATH_IMAGE124
in order to be the mass of the aircraft,
Figure DEST_PATH_IMAGE126
is the specific heat coefficient of the aircraft,
Figure DEST_PATH_IMAGE128
representing a function of aircraft temperature dynamics;
s13, establishing an integral temperature dynamic change equation set:
Figure DEST_PATH_IMAGE130
in the formula:
Figure DEST_PATH_IMAGE132
in the form of a temperature rate-of-change matrix,
Figure DEST_PATH_IMAGE134
in the form of a temperature matrix, the temperature matrix,
Figure DEST_PATH_IMAGE136
in the form of an initial temperature matrix, the temperature,
Figure DEST_PATH_IMAGE138
it is the temperature of the air that is,
Figure DEST_PATH_IMAGE140
in order to obtain the temperature of each floor,
Figure DEST_PATH_IMAGE142
，
Figure DEST_PATH_IMAGE144
for 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
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_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 DEST_PATH_IMAGE162
in the formula:
Figure DEST_PATH_IMAGE164
in order to have a strong convective heat transfer coefficient,
Figure DEST_PATH_IMAGE166
for the numerical calculation of the current air temperature during the process,
Figure DEST_PATH_IMAGE168
in order to fix the constant of 29.28,
Figure 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 DEST_PATH_IMAGE172
in the formula:
Figure DEST_PATH_IMAGE174
in order to compensate for the transient load of the fresh air,
Figure DEST_PATH_IMAGE176
is the specific heat coefficient of the air,
Figure DEST_PATH_IMAGE178
in order to compensate for the mass of the fresh air,
Figure DEST_PATH_IMAGE180
for the purpose of numerically calculating the current air temperature,
Figure 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 DEST_PATH_IMAGE184
in the formula:
Figure DEST_PATH_IMAGE186
the effective power of the fan is the effective power of the fan,
Figure DEST_PATH_IMAGE188
the air quantity of the fan is adopted,
Figure DEST_PATH_IMAGE190
is a pressure head of the fan,
Figure 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 DEST_PATH_IMAGE194
in the formula:
Figure DEST_PATH_IMAGE196
in order to illuminate the heat load power,
Figure 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 DEST_PATH_IMAGE200
in the formula:
Figure DEST_PATH_IMAGE202
for top floor temperature versus time
Figure 468884DEST_PATH_IMAGE076
The rate of change of (a) is,
Figure DEST_PATH_IMAGE204
is the temperature of the air in the room,
Figure DEST_PATH_IMAGE206
is the current temperature of the top floor level,
Figure DEST_PATH_IMAGE208
is the current temperature of the lower floor level,
Figure DEST_PATH_IMAGE210
in order to have a strong convective heat transfer coefficient,
Figure DEST_PATH_IMAGE212
as to the density of the terrace,
Figure DEST_PATH_IMAGE214
is the specific heat coefficient of the terrace,
Figure DEST_PATH_IMAGE216
the thickness of the terrace is the thickness of the terrace,
Figure DEST_PATH_IMAGE218
for the heat transfer coefficient of the terrace,
Figure DEST_PATH_IMAGE220
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_IMAGE222
in the formula: integer number of
Figure DEST_PATH_IMAGE224
Has a value range of
Figure DEST_PATH_IMAGE226
，
Figure DEST_PATH_IMAGE228
For middle floor temperature versus time
Figure 792549DEST_PATH_IMAGE076
The rate of change of (a) is,
Figure DEST_PATH_IMAGE230
is the current temperature of the upper floor,
Figure DEST_PATH_IMAGE232
is the current temperature of the intermediate floor level,
Figure DEST_PATH_IMAGE234
is the current temperature of the next floor level,
Figure DEST_PATH_IMAGE236
for the heat transfer coefficient of the terrace,
Figure DEST_PATH_IMAGE238
the thickness of the terrace is the thickness of the terrace,
Figure DEST_PATH_IMAGE240
as to the density of the terrace,
Figure DEST_PATH_IMAGE242
is the specific heat coefficient of the terrace,
the 13 th floor temperature change equation:
Figure DEST_PATH_IMAGE244
in the formula:
Figure DEST_PATH_IMAGE246
for insulating layer terrace temperature vs. time
Figure DEST_PATH_IMAGE248
The rate of change of (a) is,
Figure DEST_PATH_IMAGE250
is the current temperature of the 12 th floor,
Figure DEST_PATH_IMAGE252
is the current temperature of the 13 th floor,
Figure DEST_PATH_IMAGE254
for the heat transfer coefficient of the terrace,
Figure DEST_PATH_IMAGE256
the thickness of the terrace is the thickness of the terrace,
Figure DEST_PATH_IMAGE258
as to the density of the terrace,
Figure DEST_PATH_IMAGE260
is the specific heat coefficient of the terrace,
Figure DEST_PATH_IMAGE262
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 DEST_PATH_IMAGE264
Outdoor air temperature
Figure DEST_PATH_IMAGE266
Target temperature rise/fall
Figure DEST_PATH_IMAGE268
；
S14-2, setting laboratory size: height
Figure DEST_PATH_IMAGE270
Width, width
Figure DEST_PATH_IMAGE272
Length, length
Figure DEST_PATH_IMAGE274
；
S14-3, setting air parameters: volume of air
Figure DEST_PATH_IMAGE275
Specific heat coefficient of air
Figure DEST_PATH_IMAGE276
Air density
Figure DEST_PATH_IMAGE277
Correction factor
Figure DEST_PATH_IMAGE278
；
S14-4, setting the parameters of the heat preservation plate: thickness of
Figure DEST_PATH_IMAGE279
Coefficient of heat transfer
Figure DEST_PATH_IMAGE280
；
S14-5, setting floor parameters: floor area
Figure DEST_PATH_IMAGE282
Specific heat coefficient
Figure DEST_PATH_IMAGE283
Density, density
Figure DEST_PATH_IMAGE284
Coefficient of heat transfer
Figure DEST_PATH_IMAGE285
；
S14-6, setting compensation fresh air parameters: compensating for fresh air quality
Figure DEST_PATH_IMAGE286
Compensating fresh air temperature
Figure DEST_PATH_IMAGE287
；
S14-7, setting steel structure parameters: quality of steel structure
Figure DEST_PATH_IMAGE288
Specific heat coefficient of steel material
Figure DEST_PATH_IMAGE289
；
S14-8, setting fan parameters: number of fans
Figure DEST_PATH_IMAGE290
Air quantity of fan
Figure DEST_PATH_IMAGE291
(ii) a Draught fan pressure head
Figure DEST_PATH_IMAGE292
(ii) a Factor of safety
Figure DEST_PATH_IMAGE293
；
S14-9, setting airplane parameters: coefficient of convective heat transfer
Figure DEST_PATH_IMAGE294
Aircraft surface area
Figure DEST_PATH_IMAGE295
Specific heat coefficient of airplane
Figure DEST_PATH_IMAGE296
Aircraft mass
Figure DEST_PATH_IMAGE297
；
S14-10, setting refrigeration/heating parameters: margin coefficient
Figure DEST_PATH_IMAGE298
。
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 883870DEST_PATH_IMAGE278
The air quality change caused by the temperature change in the temperature rising/reducing process can be corrected, the problem of large air transient load calculation deviation is solved, and the accuracy of air transient load calculation is improved;
(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_IMAGE299
in the formula:
Figure DEST_PATH_IMAGE300
for the purpose of the air transient load,
Figure 810238DEST_PATH_IMAGE278
in order to be a model-modifying factor,
Figure 890190DEST_PATH_IMAGE275
is the volume of the air in the room,
Figure DEST_PATH_IMAGE301
is the air density at normal temperature and pressure,
Figure 978231DEST_PATH_IMAGE276
is the specific heat coefficient of the air,
Figure DEST_PATH_IMAGE302
for the numerical calculation of the current air temperature during the process,
Figure DEST_PATH_IMAGE303
the air temperature at the previous moment in the process is calculated for the value,
Figure 42002DEST_PATH_IMAGE278
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 DEST_PATH_IMAGE304
in the formula:
Figure DEST_PATH_IMAGE305
in order to provide the thermal load of the insulation board,
Figure 519864DEST_PATH_IMAGE280
is the heat transfer coefficient of the heat-insulating plate,
Figure DEST_PATH_IMAGE306
is the surface area of the heat-insulating plate in the laboratory,
Figure 454322DEST_PATH_IMAGE279
is the thickness of the heat-preserving plate,
Figure DEST_PATH_IMAGE307
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_IMAGE308
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 DEST_PATH_IMAGE309
in the formula:
Figure DEST_PATH_IMAGE310
in order to have a strong convective heat transfer coefficient,
Figure DEST_PATH_IMAGE311
for the numerical calculation of the current air temperature during the process,
Figure DEST_PATH_IMAGE312
in order to fix the constant of 29.28,
Figure DEST_PATH_IMAGE313
is a linear factor with the value of 0.071,
the heat load model of the terrace is:
Figure DEST_PATH_IMAGE314
in the formula:
Figure DEST_PATH_IMAGE315
in order to be the heat load of the terrace,
Figure DEST_PATH_IMAGE316
in order to have a strong convective heat transfer coefficient,
Figure DEST_PATH_IMAGE317
in order to provide a floor area for a laboratory,
Figure DEST_PATH_IMAGE318
for the numerical calculation of the current air temperature during the process,
Figure DEST_PATH_IMAGE319
the temperature of the top floor in the terrace;
s4, establishing a fresh air heat load compensation model, wherein the fresh air heat load compensation model is established according to the characteristic that the air supply temperature of the laboratory compensation fresh air is a constant value:
Figure DEST_PATH_IMAGE320
in the formula:
Figure DEST_PATH_IMAGE321
in order to compensate for the transient load of the fresh air,
Figure DEST_PATH_IMAGE322
is the specific heat coefficient of the air,
Figure 385368DEST_PATH_IMAGE286
for supplementingThe quality of the fresh air is compensated for,
Figure DEST_PATH_IMAGE323
for the purpose of numerically calculating the current air temperature,
Figure DEST_PATH_IMAGE324
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_IMAGE325
in the formula:
Figure DEST_PATH_IMAGE326
for the transient load of the steel structure,
Figure DEST_PATH_IMAGE327
the mass of the steel structure is the weight of the steel structure,
Figure DEST_PATH_IMAGE328
is the specific heat coefficient of the steel material,
Figure DEST_PATH_IMAGE329
for numerically calculating the current steel structure temperature during the process,
Figure DEST_PATH_IMAGE330
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_IMAGE331
in the formula:
Figure DEST_PATH_IMAGE332
the effective power of the fan is the effective power of the fan,
Figure 15064DEST_PATH_IMAGE291
the air quantity of the fan is adopted,
Figure 17655DEST_PATH_IMAGE292
is a pressure head of the fan,
Figure 557352DEST_PATH_IMAGE293
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_IMAGE333
in the formula:
Figure DEST_PATH_IMAGE334
in order to realize the transient heat load of the fan,
Figure DEST_PATH_IMAGE335
in order to increase the number of the fans,
Figure DEST_PATH_IMAGE336
is the effective power of a single fan,
Figure DEST_PATH_IMAGE337
calculating the current air temperature for the value;
s7, establishing a lighting heat load model with a constant value:
Figure DEST_PATH_IMAGE338
in the formula:
Figure DEST_PATH_IMAGE339
in order to illuminate the heat load power,
Figure DEST_PATH_IMAGE340
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 DEST_PATH_IMAGE341
in the formula:
Figure DEST_PATH_IMAGE342
in order to be a thermal load of the aircraft,
Figure DEST_PATH_IMAGE343
in order to obtain a convective heat transfer coefficient,
Figure DEST_PATH_IMAGE344
the surface area of the aircraft is,
Figure DEST_PATH_IMAGE345
for the numerical calculation of the current air temperature during the process,
Figure DEST_PATH_IMAGE346
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 DEST_PATH_IMAGE347
in the formula:
Figure DEST_PATH_IMAGE348
the cold/heat provided to the refrigeration/heating system,
Figure 561430DEST_PATH_IMAGE298
as a coefficient of the margin, is,
Figure DEST_PATH_IMAGE349
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 DEST_PATH_IMAGE350
in the formula:
Figure DEST_PATH_IMAGE351
is air temperature versus time
Figure DEST_PATH_IMAGE352
The rate of change of (a) is,
Figure DEST_PATH_IMAGE353
is the temperature of the air in the room,
Figure DEST_PATH_IMAGE354
is the temperature of the top-layer terrace,
Figure DEST_PATH_IMAGE355
for the surface temperature of the aircraft as a load,
Figure DEST_PATH_IMAGE356
is the set point of the air temperature,
Figure DEST_PATH_IMAGE357
the cold/heat provided to the refrigeration/heating system,
Figure DEST_PATH_IMAGE358
in order to reduce the heat loss of the heat-insulation plate,
Figure DEST_PATH_IMAGE359
in order to provide the heat load of the terrace,
Figure DEST_PATH_IMAGE360
in order to compensate for the heat load of the fresh air,
Figure DEST_PATH_IMAGE361
in order to provide a thermal load for the fan,
Figure DEST_PATH_IMAGE362
in order to illuminate the heat load,
Figure DEST_PATH_IMAGE363
representing the thermal load of the aircraft on the load,
Figure DEST_PATH_IMAGE364
in order to obtain the quality of the air in the room,
Figure DEST_PATH_IMAGE365
、
Figure 757051DEST_PATH_IMAGE289
the specific heat coefficients of air and a steel structure respectively,
Figure 297753DEST_PATH_IMAGE288
the mass of the steel structure is the weight of the steel structure,
Figure DEST_PATH_IMAGE366
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_IMAGE367
in the formula:
Figure DEST_PATH_IMAGE368
for top floor temperature versus time
Figure 737962DEST_PATH_IMAGE352
The rate of change of (a) is,
Figure DEST_PATH_IMAGE369
is the temperature of the air in the room,
Figure DEST_PATH_IMAGE370
is the current temperature of the top floor level,
Figure DEST_PATH_IMAGE371
is the current temperature of the lower floor level,
Figure DEST_PATH_IMAGE372
in order to have a strong convective heat transfer coefficient,
Figure 617669DEST_PATH_IMAGE284
as to the density of the terrace,
Figure DEST_PATH_IMAGE373
is the specific heat coefficient of the terrace,
Figure DEST_PATH_IMAGE374
the thickness of the terrace is the thickness of the terrace,
Figure 877749DEST_PATH_IMAGE285
for the heat transfer coefficient of the terrace,
Figure DEST_PATH_IMAGE375
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_IMAGE376
in the formula: integer number of
Figure DEST_PATH_IMAGE377
Has a value range of
Figure DEST_PATH_IMAGE378
，
Figure DEST_PATH_IMAGE379
For middle floor temperature versus time
Figure 18880DEST_PATH_IMAGE352
The rate of change of (a) is,
Figure DEST_PATH_IMAGE380
is the current temperature of the upper floor,
Figure DEST_PATH_IMAGE381
is the current temperature of the intermediate floor level,
Figure DEST_PATH_IMAGE382
is the current temperature of the next floor level,
Figure DEST_PATH_IMAGE383
for the heat transfer coefficient of the terrace,
Figure DEST_PATH_IMAGE384
the thickness of the terrace is the thickness of the terrace,
Figure DEST_PATH_IMAGE385
as to the density of the terrace,
Figure DEST_PATH_IMAGE386
is the specific heat coefficient of the terrace,
the 13 th floor temperature change equation:
Figure DEST_PATH_IMAGE387
in the formula:
Figure DEST_PATH_IMAGE388
for insulating layer terrace temperature vs. time
Figure DEST_PATH_IMAGE248A
The rate of change of (a) is,
Figure 408535DEST_PATH_IMAGE250
is the current temperature of the 12 th floor,
Figure 445762DEST_PATH_IMAGE252
is the current temperature of the 13 th floor,
Figure 396400DEST_PATH_IMAGE254
for the heat transfer coefficient of the terrace,
Figure DEST_PATH_IMAGE390
the thickness of the terrace is the thickness of the terrace,
Figure DEST_PATH_IMAGE391
as to the density of the terrace,
Figure DEST_PATH_IMAGE392
is the specific heat coefficient of the terrace,
Figure 75643DEST_PATH_IMAGE262
representing the temperature change function of the 13 th floor;
s12, establishing a temperature dynamic change equation of the airplane:
Figure DEST_PATH_IMAGE393
in the formula:
Figure DEST_PATH_IMAGE394
for aircraft temperature versus time
Figure DEST_PATH_IMAGE395
The rate of change of (a) is,
Figure 506756DEST_PATH_IMAGE294
is the convective heat transfer coefficient between the air and the aircraft,
Figure DEST_PATH_IMAGE396
is the current temperature of the indoor air,
Figure DEST_PATH_IMAGE397
the surface area of the aircraft is,
Figure DEST_PATH_IMAGE398
as is the current aircraft surface temperature,
Figure 980462DEST_PATH_IMAGE297
in order to be the mass of the aircraft,
Figure DEST_PATH_IMAGE399
is the specific heat coefficient of the aircraft,
Figure DEST_PATH_IMAGE400
representing a function of aircraft temperature dynamics;
s13, establishing an integral temperature dynamic change equation set:
Figure DEST_PATH_IMAGE401
in the formula:
Figure DEST_PATH_IMAGE402
in the form of a temperature rate-of-change matrix,
Figure DEST_PATH_IMAGE403
in the form of a temperature matrix, the temperature matrix,
Figure DEST_PATH_IMAGE404
in the form of an initial temperature matrix, the temperature,
Figure DEST_PATH_IMAGE405
it is the temperature of the air that is,
Figure DEST_PATH_IMAGE406
in order to obtain the temperature of each floor,
Figure DEST_PATH_IMAGE407
，
Figure DEST_PATH_IMAGE408
is the aircraft surface temperature;
Figure DEST_PATH_IMAGE409
is an initial temperature value;
s14, setting related parameters:
s14-1, setting target parameters: initial air temperature value
Figure 556413DEST_PATH_IMAGE264
Outdoor air temperature
Figure DEST_PATH_IMAGE410
Target temperature rise/fall
Figure 242609DEST_PATH_IMAGE268
；
S14-2, setting laboratory size: height
Figure DEST_PATH_IMAGE411
Width, width
Figure 246337DEST_PATH_IMAGE272
Length, length
Figure 359786DEST_PATH_IMAGE274
；
S14-3, setting air parameters: volume of air
Figure 301329DEST_PATH_IMAGE275
Specific heat coefficient of air
Figure 791216DEST_PATH_IMAGE276
Air density
Figure 118292DEST_PATH_IMAGE277
Correction factor
Figure 402643DEST_PATH_IMAGE278
；
S14-4, setting the parameters of the heat preservation plate: thickness of
Figure 346328DEST_PATH_IMAGE279
Coefficient of heat transfer
Figure 374327DEST_PATH_IMAGE280
；
S14-5, setting floor parameters: floor area
Figure 821489DEST_PATH_IMAGE282
Specific heat coefficient
Figure 276741DEST_PATH_IMAGE283
Density, density
Figure 176564DEST_PATH_IMAGE284
Coefficient of heat transfer
Figure 8254DEST_PATH_IMAGE285
；
S14-6, setting compensation fresh air parameters: compensating for fresh air quality
Figure 326234DEST_PATH_IMAGE286
Compensating fresh air temperature
Figure 686808DEST_PATH_IMAGE287
；
S14-7, setting steel structure parameters: quality of steel structure
Figure 339506DEST_PATH_IMAGE288
Specific heat coefficient of steel material
Figure 974887DEST_PATH_IMAGE289
；
S14-8, setting fan parameters: number of fans
Figure 865482DEST_PATH_IMAGE290
Air quantity of fan
Figure 928116DEST_PATH_IMAGE291
(ii) a Draught fan pressure head
Figure 802531DEST_PATH_IMAGE292
(ii) a Factor of safety
Figure 241603DEST_PATH_IMAGE293
；
S14-9, setting airplane parameters: coefficient of convective heat transfer
Figure 517863DEST_PATH_IMAGE294
Aircraft surface area
Figure 485819DEST_PATH_IMAGE295
Specific heat coefficient of airplane
Figure 847531DEST_PATH_IMAGE296
Aircraft mass
Figure 575446DEST_PATH_IMAGE297
；
S14-10, setting refrigeration/heating parameters: margin coefficient
Figure 440634DEST_PATH_IMAGE298
；
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_IMAGE413
Outdoor air temperature
Figure DEST_PATH_IMAGE415
Target temperature rise/fall
Figure DEST_PATH_IMAGE417
；
S14-2, setting laboratory size: height
Figure DEST_PATH_IMAGE419
Width (big room)
Figure DEST_PATH_IMAGE421
Length (big room)
Figure DEST_PATH_IMAGE423
(ii) a Width (Small chamber)
Figure DEST_PATH_IMAGE425
Length (cell)
Figure DEST_PATH_IMAGE427
；
S14-3, setting air parameters: volume of air
Figure DEST_PATH_IMAGE429
Specific heat coefficient of air
Figure DEST_PATH_IMAGE431
Air density
Figure DEST_PATH_IMAGE433
Correction factor
Figure DEST_PATH_IMAGE435
；
S14-4, setting the parameters of the heat preservation plate: thickness of
Figure DEST_PATH_IMAGE437
Coefficient of heat transfer
Figure DEST_PATH_IMAGE439
；
S14-5, setting floor parameters: specific heat coefficient
Figure DEST_PATH_IMAGE441
Density, density
Figure DEST_PATH_IMAGE443
Coefficient of heat transfer
Figure DEST_PATH_IMAGE445
Floor area
Figure DEST_PATH_IMAGE447
；
S14-6, setting compensation fresh air parameters: compensating for fresh air quality
Figure DEST_PATH_IMAGE449
Compensating fresh air temperature
Figure DEST_PATH_IMAGE451
；
S14-7, setting steel structure parameters: quality of steel structure
Figure DEST_PATH_IMAGE453
(ii) a Specific heat coefficient of steel material
Figure DEST_PATH_IMAGE455
；
S14-8, setting fan parameters: number of fans
Figure DEST_PATH_IMAGE457
Air quantity of fan
Figure DEST_PATH_IMAGE459
(ii) a Draught fan pressure head
Figure DEST_PATH_IMAGE461
(ii) a Factor of safety
Figure DEST_PATH_IMAGE463
；
S14-9, setting airplane parameters: coefficient of convective heat transfer
Figure DEST_PATH_IMAGE465
Aircraft surface area
Figure DEST_PATH_IMAGE467
Aircraft mass
Figure DEST_PATH_IMAGE469
；
S14-10, setting refrigeration/heating parameters: margin coefficient
Figure DEST_PATH_IMAGE471
。
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 (9)

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 605740DEST_PATH_IMAGE001
in the formula:
Figure 991722DEST_PATH_IMAGE002
for the purpose of the air transient load,
Figure 771459DEST_PATH_IMAGE003
in order to be a model-modifying factor,
Figure 166668DEST_PATH_IMAGE004
is the volume of the air in the room,
Figure 981040DEST_PATH_IMAGE005
is the air density at normal temperature and pressure,
Figure 629934DEST_PATH_IMAGE006
is the specific heat coefficient of the air,
Figure 896967DEST_PATH_IMAGE007
for the numerical calculation of the current air temperature during the process,
Figure 95868DEST_PATH_IMAGE008
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 92642DEST_PATH_IMAGE009
in the formula:
Figure 86006DEST_PATH_IMAGE010
in order to be the heat load of the terrace,
Figure 840336DEST_PATH_IMAGE011
in order to have a strong convective heat transfer coefficient,
Figure 577348DEST_PATH_IMAGE012
in order to provide a floor area for a laboratory,
Figure 569574DEST_PATH_IMAGE013
for the numerical calculation of the current air temperature during the process,
Figure 999419DEST_PATH_IMAGE014
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 241044DEST_PATH_IMAGE015
in the formula:
Figure 516168DEST_PATH_IMAGE016
for the transient load of the steel structure,
Figure 487535DEST_PATH_IMAGE017
the mass of the steel structure is the weight of the steel structure,
Figure 822701DEST_PATH_IMAGE018
is the specific heat coefficient of the steel material,
Figure 551623DEST_PATH_IMAGE019
for numerically calculating the current steel structure temperature during the process,
Figure 99279DEST_PATH_IMAGE020
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 597256DEST_PATH_IMAGE021
in the formula:
Figure 368903DEST_PATH_IMAGE022
in order to realize the transient heat load of the fan,
Figure 319542DEST_PATH_IMAGE023
in order to increase the number of the fans,
Figure 529943DEST_PATH_IMAGE024
is the effective power of a single fan,
Figure 882427DEST_PATH_IMAGE025
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 824975DEST_PATH_IMAGE026
in the formula:
Figure 262910DEST_PATH_IMAGE027
in order to be a thermal load of the aircraft,
Figure 778467DEST_PATH_IMAGE028
in order to obtain a convective heat transfer coefficient,
Figure 251037DEST_PATH_IMAGE029
the surface area of the aircraft is,
Figure 364486DEST_PATH_IMAGE030
for the numerical calculation of the current air temperature during the process,
Figure 492979DEST_PATH_IMAGE031
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 717287DEST_PATH_IMAGE032
in the formula:
Figure 778784DEST_PATH_IMAGE033
the cold/heat provided to the refrigeration/heating system,
Figure 63135DEST_PATH_IMAGE034
as a coefficient of the margin, is,
Figure 803558DEST_PATH_IMAGE035
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 831557DEST_PATH_IMAGE036
in the formula:
Figure 13139DEST_PATH_IMAGE037
is air temperature versus time
Figure 202812DEST_PATH_IMAGE038
The rate of change of (a) is,
Figure 696110DEST_PATH_IMAGE039
is the temperature of the air in the room,
Figure 262221DEST_PATH_IMAGE040
is the temperature of the top-layer terrace,
Figure 563889DEST_PATH_IMAGE041
for the surface temperature of the aircraft as a load,
Figure 127726DEST_PATH_IMAGE042
is the set point of the air temperature,
Figure 514845DEST_PATH_IMAGE043
the cold/heat provided to the refrigeration/heating system,
Figure 884646DEST_PATH_IMAGE044
in order to reduce the heat loss of the heat-insulation plate,
Figure 775242DEST_PATH_IMAGE045
in order to provide the heat load of the terrace,
Figure 165772DEST_PATH_IMAGE046
in order to compensate for the heat load of the fresh air,
Figure 774608DEST_PATH_IMAGE047
in order to provide a thermal load for the fan,
Figure 948100DEST_PATH_IMAGE048
in order to illuminate the heat load,
Figure 958781DEST_PATH_IMAGE049
representing the thermal load of the aircraft on the load,
Figure 753169DEST_PATH_IMAGE050
in order to obtain the quality of the air in the room,
Figure 849301DEST_PATH_IMAGE051
、
Figure 560905DEST_PATH_IMAGE052
the specific heat coefficients of air and a steel structure respectively,
Figure 894934DEST_PATH_IMAGE053
the mass of the steel structure is the weight of the steel structure,
Figure 33791DEST_PATH_IMAGE054
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 617220DEST_PATH_IMAGE055
in the formula:
Figure 866935DEST_PATH_IMAGE056
for aircraft temperature versus time
Figure 180105DEST_PATH_IMAGE057
The rate of change of (a) is,
Figure 489864DEST_PATH_IMAGE058
is the convective heat transfer coefficient between the air and the aircraft,
Figure 560588DEST_PATH_IMAGE059
is the current temperature of the indoor air,
Figure 613994DEST_PATH_IMAGE060
the surface area of the aircraft is,
Figure 922616DEST_PATH_IMAGE061
is at presentThe temperature of the surface of the aircraft,
Figure 403276DEST_PATH_IMAGE062
in order to be the mass of the aircraft,
Figure 695717DEST_PATH_IMAGE063
is the specific heat coefficient of the aircraft,
Figure 880711DEST_PATH_IMAGE064
representing a function of aircraft temperature dynamics;
s13, establishing an integral temperature dynamic change equation set:
Figure 574997DEST_PATH_IMAGE065
in the formula:
Figure 226558DEST_PATH_IMAGE066
in the form of a temperature rate-of-change matrix,
Figure 271875DEST_PATH_IMAGE067
in the form of a temperature matrix, the temperature matrix,
Figure 994980DEST_PATH_IMAGE068
in the form of an initial temperature matrix, the temperature,
Figure 543773DEST_PATH_IMAGE069
it is the temperature of the air that is,
Figure 631815DEST_PATH_IMAGE070
in order to obtain the temperature of each floor,
Figure 898848DEST_PATH_IMAGE071
，
Figure 566590DEST_PATH_IMAGE072
is the aircraft surface temperature;
Figure 969889DEST_PATH_IMAGE073
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 228832DEST_PATH_IMAGE074
in the formula:
Figure 812523DEST_PATH_IMAGE075
in order to provide the thermal load of the insulation board,
Figure 549535DEST_PATH_IMAGE076
is the heat transfer coefficient of the heat-insulating plate,
Figure 72920DEST_PATH_IMAGE077
is the surface area of the heat-insulating plate in the laboratory,
Figure 502764DEST_PATH_IMAGE078
is the thickness of the heat-preserving plate,
Figure 72286DEST_PATH_IMAGE079
the temperature of the inner surface of the current insulation board in the numerical calculation process is the same as the air temperature,
Figure 612988DEST_PATH_IMAGE080
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 256459DEST_PATH_IMAGE081
in the formula:
Figure 591626DEST_PATH_IMAGE082
in order to have a strong convective heat transfer coefficient,
Figure 523810DEST_PATH_IMAGE083
for the numerical calculation of the current air temperature during the process,
Figure 602624DEST_PATH_IMAGE084
in order to be a fixed constant, the number of the first and second electrodes,
Figure 100602DEST_PATH_IMAGE085
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 200145DEST_PATH_IMAGE086
in the formula:
Figure 416362DEST_PATH_IMAGE087
in order to compensate for the transient load of the fresh air,
Figure 298868DEST_PATH_IMAGE088
is the specific heat coefficient of the air,
Figure 651352DEST_PATH_IMAGE089
in order to compensate for the mass of the fresh air,
Figure 921796DEST_PATH_IMAGE090
for the purpose of numerically calculating the current air temperature,
Figure 359731DEST_PATH_IMAGE091
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 780348DEST_PATH_IMAGE092
in the formula:
Figure 252917DEST_PATH_IMAGE093
the effective power of the fan is the effective power of the fan,
Figure 569629DEST_PATH_IMAGE094
the air quantity of the fan is adopted,
Figure 494860DEST_PATH_IMAGE095
is a pressure head of the fan,
Figure 719168DEST_PATH_IMAGE096
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 46244DEST_PATH_IMAGE097
in the formula:
Figure 157026DEST_PATH_IMAGE098
in order to illuminate the heat load power,
Figure 569553DEST_PATH_IMAGE099
is a constant.
7. The method for analyzing the transient load of the climate environment laboratory of the large aircraft as claimed in claim 1, wherein the temperature dynamic change equations of the terrace in the step S11 are respectively as follows:
the temperature change equation of the floor at the 1 st layer:
Figure 331972DEST_PATH_IMAGE100
in the formula:
Figure 841451DEST_PATH_IMAGE101
for top floor temperature versus time
Figure 296703DEST_PATH_IMAGE102
The rate of change of (a) is,
Figure 196526DEST_PATH_IMAGE103
is the temperature of the air in the room,
Figure 762637DEST_PATH_IMAGE104
is the current temperature of the top floor level,
Figure 267567DEST_PATH_IMAGE105
is the current temperature of the lower floor level,
Figure 893721DEST_PATH_IMAGE106
in order to have a strong convective heat transfer coefficient,
Figure 280840DEST_PATH_IMAGE107
as to the density of the terrace,
Figure 385062DEST_PATH_IMAGE108
is the specific heat coefficient of the terrace,
Figure 869133DEST_PATH_IMAGE109
the thickness of the terrace is the thickness of the terrace,
Figure 666188DEST_PATH_IMAGE110
for the heat transfer coefficient of the terrace,
Figure 275024DEST_PATH_IMAGE111
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 917357DEST_PATH_IMAGE112
in the formula: integer number of
Figure 928039DEST_PATH_IMAGE113
Has a value range of
Figure 895995DEST_PATH_IMAGE114
，
Figure 992127DEST_PATH_IMAGE115
For middle floor temperature versus time
Figure 766048DEST_PATH_IMAGE102
The rate of change of (a) is,
Figure 896815DEST_PATH_IMAGE116
is the current temperature of the upper floor,
Figure 35672DEST_PATH_IMAGE117
is the current temperature of the intermediate floor level,
Figure 619100DEST_PATH_IMAGE118
is the current temperature of the next floor level,
Figure 963756DEST_PATH_IMAGE119
for the heat transfer coefficient of the terrace,
Figure 949030DEST_PATH_IMAGE120
the thickness of the terrace is the thickness of the terrace,
Figure 258788DEST_PATH_IMAGE121
as to the density of the terrace,
Figure 532775DEST_PATH_IMAGE122
is the specific heat coefficient of the terrace,
the 13 th floor temperature change equation:
Figure 586181DEST_PATH_IMAGE123
in the formula:
Figure 425961DEST_PATH_IMAGE124
for insulating layer terrace temperature vs. time
Figure 906621DEST_PATH_IMAGE102
The rate of change of (a) is,
Figure 526959DEST_PATH_IMAGE125
is the current temperature of the 12 th floor,
Figure 384056DEST_PATH_IMAGE126
is the current temperature of the 13 th floor,
Figure 78343DEST_PATH_IMAGE127
for the heat transfer coefficient of the terrace,
Figure 729904DEST_PATH_IMAGE128
the thickness of the terrace is the thickness of the terrace,
Figure 368696DEST_PATH_IMAGE129
as to the density of the terrace,
Figure 763905DEST_PATH_IMAGE130
is the specific heat coefficient of the terrace,
Figure 312698DEST_PATH_IMAGE131
showing the temperature change function of the 13 th floor.
8. 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 400740DEST_PATH_IMAGE132
Outdoor air temperature
Figure 871035DEST_PATH_IMAGE133
Target temperature rise/fall
Figure 804356DEST_PATH_IMAGE134
；
S14-2, setting laboratory size: height ofDegree of rotation
Figure 473235DEST_PATH_IMAGE135
Width, width
Figure 325653DEST_PATH_IMAGE136
Length, length
Figure 814403DEST_PATH_IMAGE137
；
S14-3, setting air parameters: volume of air
Figure 816994DEST_PATH_IMAGE138
Specific heat coefficient of air
Figure 340380DEST_PATH_IMAGE006
Air density
Figure 331076DEST_PATH_IMAGE005
Correction factor
Figure 572702DEST_PATH_IMAGE003
；
S14-4, setting the parameters of the heat preservation plate: thickness of
Figure 113404DEST_PATH_IMAGE078
Coefficient of heat transfer
Figure 491296DEST_PATH_IMAGE076
；
S14-5, setting floor parameters: floor area
Figure 560883DEST_PATH_IMAGE139
Specific heat coefficient
Figure 24226DEST_PATH_IMAGE140
Density, density
Figure 368619DEST_PATH_IMAGE107
Coefficient of heat transfer
Figure 194493DEST_PATH_IMAGE110
；
S14-6, setting compensation fresh air parameters: compensating for fresh air quality
Figure 700560DEST_PATH_IMAGE089
Compensating fresh air temperature
Figure 916778DEST_PATH_IMAGE141
；
S14-7, setting steel structure parameters: quality of steel structure
Figure 799284DEST_PATH_IMAGE053
Specific heat coefficient of steel material
Figure 620609DEST_PATH_IMAGE052
；
S14-8, setting fan parameters: number of fans
Figure 297578DEST_PATH_IMAGE023
Air quantity of fan
Figure 735513DEST_PATH_IMAGE094
(ii) a Draught fan pressure head
Figure 421709DEST_PATH_IMAGE095
(ii) a Factor of safety
Figure 956595DEST_PATH_IMAGE096
；
S14-9, setting airplane parameters: coefficient of convective heat transfer
Figure 70045DEST_PATH_IMAGE058
Aircraft surface area
Figure 995276DEST_PATH_IMAGE060
Specific heat coefficient of airplane
Figure 547480DEST_PATH_IMAGE063
Aircraft mass
Figure 874556DEST_PATH_IMAGE062
；
S14-10, setting refrigeration/heating parameters: margin coefficient
Figure 158907DEST_PATH_IMAGE034
。
9. 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.
CN202111358691.9A 2021-11-17 2021-11-17 Large aircraft climate environment laboratory temperature rise and fall transient load analysis method Active CN113901590B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202111358691.9A CN113901590B (en) 2021-11-17 2021-11-17 Large aircraft climate environment laboratory temperature rise and fall transient load analysis method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202111358691.9A CN113901590B (en) 2021-11-17 2021-11-17 Large aircraft climate environment laboratory temperature rise and fall transient load analysis method

Publications (2)

Publication Number Publication Date
CN113901590A true CN113901590A (en) 2022-01-07
CN113901590B CN113901590B (en) 2022-03-01

Family

ID=79194358

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202111358691.9A Active CN113901590B (en) 2021-11-17 2021-11-17 Large aircraft climate environment laboratory temperature rise and fall transient load analysis method

Country Status (1)

Country Link
CN (1) CN113901590B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114237329A (en) * 2022-01-11 2022-03-25 中国飞机强度研究所 Temperature control system and control method for aircraft solar radiation test

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105260518A (en) * 2015-09-25 2016-01-20 天津大学 CFD simulation and system simulation model combination based airplane cabin environment control method
CN105281328A (en) * 2015-10-26 2016-01-27 上海交通大学 Static model and steady power flow analysis method of more electric aircraft electric system
US20170024496A1 (en) * 2015-07-22 2017-01-26 The Boeing Company Methods and apparatus to model thermal mixing for prediction of multi-stream flows
US20170101195A1 (en) * 2015-10-12 2017-04-13 Airbus Operations Sas Method for predicting temperatures which are tolerable by a component, a piece of equipment or an airplane structure
CN106934247A (en) * 2017-03-22 2017-07-07 上海理工大学 Based on the thermally equilibrated large space layering air-Conditioning Load Calculation Method in surface
CN108168893A (en) * 2017-12-13 2018-06-15 中国飞机强度研究所 A kind of interior aircraft engine running experience compensated with air system
CN111581720A (en) * 2020-04-30 2020-08-25 中国飞机强度研究所 Method for evaluating uncertainty of temperature data of all-round program control thermal test of aircraft
CN112307562A (en) * 2020-10-30 2021-02-02 泉州装备制造研究所 Method for assembling complex parts on large-scale airplane by combining thermal deformation and gravity deformation
CN113177321A (en) * 2021-05-10 2021-07-27 合肥工业大学 Air conditioner load modeling method based on heat exchange dynamic process

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20170024496A1 (en) * 2015-07-22 2017-01-26 The Boeing Company Methods and apparatus to model thermal mixing for prediction of multi-stream flows
CN105260518A (en) * 2015-09-25 2016-01-20 天津大学 CFD simulation and system simulation model combination based airplane cabin environment control method
US20170101195A1 (en) * 2015-10-12 2017-04-13 Airbus Operations Sas Method for predicting temperatures which are tolerable by a component, a piece of equipment or an airplane structure
CN105281328A (en) * 2015-10-26 2016-01-27 上海交通大学 Static model and steady power flow analysis method of more electric aircraft electric system
CN106934247A (en) * 2017-03-22 2017-07-07 上海理工大学 Based on the thermally equilibrated large space layering air-Conditioning Load Calculation Method in surface
CN108168893A (en) * 2017-12-13 2018-06-15 中国飞机强度研究所 A kind of interior aircraft engine running experience compensated with air system
CN111581720A (en) * 2020-04-30 2020-08-25 中国飞机强度研究所 Method for evaluating uncertainty of temperature data of all-round program control thermal test of aircraft
CN112307562A (en) * 2020-10-30 2021-02-02 泉州装备制造研究所 Method for assembling complex parts on large-scale airplane by combining thermal deformation and gravity deformation
CN113177321A (en) * 2021-05-10 2021-07-27 合肥工业大学 Air conditioner load modeling method based on heat exchange dynamic process

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
崔沈夷: "飞机地面空调的选用及其节能意义", 《暖通空调》 *
张昭、唐虎、成竹: ""军用飞机实验室气候环境试验项目分析"", 《装备环境工程》 *
杨志斌、成竹、任青梅: ""飞机结构三维温度场分析程序"", 《计算力学学报》 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114237329A (en) * 2022-01-11 2022-03-25 中国飞机强度研究所 Temperature control system and control method for aircraft solar radiation test

Also Published As

Publication number Publication date
CN113901590B (en) 2022-03-01

Similar Documents

Publication Publication Date Title
CN108830932B (en) Large-space building energy consumption prediction method based on EnergyPlus and CFD coupling
CN107208415A (en) It is particularly suitable for use in the heat-insulated shell of building
CN113901590B (en) Large aircraft climate environment laboratory temperature rise and fall transient load analysis method
CN106250621B (en) Train air conditioner energy consumption calculation system
CN107301276B (en) Method for calculating convection heat transfer load of large-space nozzle air supply layered air conditioner
CN110826221A (en) Method for decoupling indoor temperature field of building
CN113091262B (en) Data center temperature and humidity set value determination method based on model predictive control
CN111191907A (en) Comprehensive energy station energy efficiency evaluation method based on analytic hierarchy process
CN105674390A (en) Dynamic hydraulic balance adjusting method for centralized heating system
CN106871351A (en) A kind of frequency conversion air blowing control method of air-conditioning system
CN110162884A (en) Consider that the buried substation of pit heat cumulative effect assesses control method
CN106934247A (en) Based on the thermally equilibrated large space layering air-Conditioning Load Calculation Method in surface
CN115795607A (en) Annual energy consumption and thermal comfort coupling evaluation method for high and large space building
CN110082137B (en) Device and method for testing heat leakage load of different parts of refrigerator
CN108644955A (en) A kind of space humidity control method of floor radiant cooling composite permutation ventilating system
CN114154242A (en) Aircraft thermal management system optimization method and system
CN106765744B (en) The method for determining radiation cooling system radiant panel surface temperature variation when supplying water cooling
Jin et al. Dynamic variation in dew-point temperature of attached air layer of radiant ceiling cooling panels
CN208567008U (en) Air-conditioning Load Prediction system based on radiated time sequence method
CN111985026A (en) High-efficiency natural ventilation design method for building based on thermal stratification height
CN102306033A (en) Environmental temperature and humidity control system of integrated testing platform of controlled ecological life support system
CN108050670A (en) Air conditioning control method and air conditioner
Watkins et al. Quantifying the effects of climate change and risk level on peak load design in buildings
CN108253604A (en) The control method and air conditioner of air conditioner
CN109140667B (en) Intelligent setting method for air conditioner target

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant