CN113919083B - Large aircraft test steady-state load analysis method under multi-environmental-factor condition - Google Patents

Large aircraft test steady-state load analysis method under multi-environmental-factor condition Download PDF

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CN113919083B
CN113919083B CN202111519704.6A CN202111519704A CN113919083B CN 113919083 B CN113919083 B CN 113919083B CN 202111519704 A CN202111519704 A CN 202111519704A CN 113919083 B CN113919083 B CN 113919083B
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heat
load
calculating
test
water
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CN113919083A (en
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王彬文
强宝平
成竹
吴敬涛
李闯勤
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AVIC Aircraft Strength Research Institute
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    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/60—Testing or inspecting aircraft components or systems
    • 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

Abstract

The invention provides a method for analyzing steady-state load of a large airplane test under a multi-environment factor condition, which belongs to the technical field of airplane test and comprises the following steps: s1, setting parameters; s2, calculating the area of the insulation board of the airplane climate laboratory; s3, calculating the illumination load of the airplane climate laboratory; s4, calculating and compensating the fresh wind heat load; s5, calculating the heat load of the fan; s6, calculating the heat load of the heat insulation plate; s7, calculating the heat load of the solar radiation lamp array; s8, calculating the thermal load of the freezing rain/snowfall working condition; s9, calculating the heat load of the floor; s10, calculating the thermal load of the test piece object; and S11, calculating the heat load required by the refrigeration system. The method solves the problems that the calculation of the steady-state load of the large-scale airplane test is not perfect under the condition of multiple environmental factors and the design basis can not be provided for the model selection configuration of the refrigerating system at present, and has the advantages of comprehensive consideration of interference factors and accurate calculation.

Description

Large aircraft test steady-state load analysis method under multi-environmental-factor condition
Technical Field
The invention relates to the technical field of airplane testing, in particular to a steady-state load analysis method for a large airplane test under a multi-environment factor condition.
Background
The airplane climate environment laboratory is the first ultra-large airplane climate environment simulation facility capable of simulating typical climate environments such as high temperature, low temperature, solar irradiation, temperature/humidity, rain, snow, freezing rain, icing and the like in China, is used for meeting indoor climate environment tests of equipment such as airplanes, missile weapon systems and the like, and fills the gap in the field of airplane climate environment tests in China.
The airplane climate environment laboratory has a plurality of simulative environmental factors, and is designed with systems such as a refrigeration system, a heating system, a cold/heat carrying system, a circulating air processing unit, an air compensation system, a steam humidification system and the like for realizing cooling, heating and humidification of indoor air in order to reproduce various climate environments in the laboratory; meanwhile, a laboratory is designed with special environment simulation systems for solar irradiation, freezing rain, snowfall and the like, and various complex climate environment conditions can be simulated in an oversized space through independent operation or combined operation of all the systems in the laboratory.
The effective area of the solar irradiation simulation system of the airplane climate environment laboratory is 700 square meters, wherein the area of the full-spectrum lamp is 20 square meters, the area of the infrared lamp is 680 square meters, and the maximum irradiation intensity is 1120w/m2. The effective area of the freezing rain simulation system is 700 square meters, and the maximum rainfall intensity is 50.8 mm/h. The effective area of the snowing system is 700 square meters, and the maximum snowing intensity is 75 mm/h. When the environment simulation test working condition under the specific temperature condition is developed, a large amount of heat load is brought to a laboratory due to radiation heating of a large-area high-intensity irradiation lamp array and water phase change heat release in the high-intensity rainfall/snowfall process.
In order to reasonably configure the capacity of a refrigerating system and avoid over-design or under-design of the capacity of a laboratory refrigerating system, the steady-state heat load of an airplane climate laboratory needs to be accurately calculated under different tests/working conditions (solar irradiation, freezing rain and snowfall).
Disclosure of Invention
The invention solves the technical problems that:
at present, the calculation of the steady-state load of a large-scale airplane test under the condition of multiple environmental factors is not perfect, and a design basis cannot be provided for the model selection configuration of a refrigeration system.
In order to solve the problems, the technical scheme of the invention is as follows:
the method for analyzing the steady-state load of the large airplane test under the condition of multiple environmental factors comprises the following steps:
s1, setting corresponding parameters according to the test working conditions;
s2, on the basis that the ground in the aircraft climate laboratory is a concrete terrace, calculating the area of the insulation board in the aircraft climate laboratory by the following formula:
Figure DEST_PATH_IMAGE002
in the formula:
Figure DEST_PATH_IMAGE004
is the area of the insulation board inside the airplane climate laboratory,
Figure DEST_PATH_IMAGE006
is the altitude of the aircraft climate laboratory,
Figure DEST_PATH_IMAGE008
is the width of an aircraft climate laboratory,
Figure DEST_PATH_IMAGE010
length for an aircraft climate laboratory;
s3, calculating the illumination load of the airplane climate laboratory;
s4, calculating and compensating the fresh wind heat load;
s5, calculating the heat load of the fan;
s6, calculating the heat load of the heat insulation plate;
s7, calculating the heat load of the solar radiation lamp array: judging whether the test working condition is an irradiation working condition, if not, skipping the step and entering the step S8, if so, assuming that part of heat generated by the radiation lamp array is absorbed by air and part of heat is absorbed by an airplane, and calculating the heat load of the solar radiation lamp array according to the following formula:
Figure DEST_PATH_IMAGE012
in the formula:
Figure DEST_PATH_IMAGE014
in order to irradiate the effective thermal load of the lamp array,
Figure DEST_PATH_IMAGE016
for the number of full-spectrum lamps,
Figure DEST_PATH_IMAGE018
is the power of the full-spectrum lamp,
Figure DEST_PATH_IMAGE020
the coefficient of the heat absorption efficiency of the plane to the full spectrum,
Figure DEST_PATH_IMAGE022
for the effective area of the full spectrum lamp on the aircraft surface,
Figure DEST_PATH_IMAGE024
in order to be able to count the number of infrared lamps,
Figure DEST_PATH_IMAGE026
is the power of the infrared lamp and is,
Figure DEST_PATH_IMAGE028
the coefficient of heat absorption efficiency of the aircraft surface to the infrared lamp;
s8, calculating the thermal load of the freezing rain/snowfall working condition: judging whether the test working condition is a sleet/snowfall working condition, if not, skipping the step and entering the step S9, if yes, calculating the thermal load of the sleet/snowfall test according to the following formula:
Figure DEST_PATH_IMAGE030
in the formula:
Figure DEST_PATH_IMAGE032
the heat load generated for the freezing rain/snowfall test,
Figure DEST_PATH_IMAGE034
the quality of test water is shown;
Figure DEST_PATH_IMAGE036
is the specific heat coefficient of water and is,
Figure DEST_PATH_IMAGE038
the temperature of the water for the test is the temperature of the water,
Figure DEST_PATH_IMAGE040
is the latent heat coefficient of water;
Figure DEST_PATH_IMAGE042
is the specific heat coefficient of ice and,
Figure DEST_PATH_IMAGE044
is an indoor air temperature value;
s9, calculating the heat load of the floor, wherein the heat transfer process inside the floor and the air heat exchange process of the floor are simplified, and the calculation formula of the heat load of the floor is as follows:
Figure DEST_PATH_IMAGE046
in the formula:
Figure DEST_PATH_IMAGE048
in order to be the heat load of the terrace,
Figure DEST_PATH_IMAGE050
in order to have a strong convective heat transfer coefficient,
Figure DEST_PATH_IMAGE052
is the width of an aircraft climate laboratory,
Figure DEST_PATH_IMAGE054
is the length of the aircraft climate laboratory,
Figure DEST_PATH_IMAGE056
the temperature difference between the air and the floor;
s10, calculating the thermal load of the test piece object
Figure DEST_PATH_IMAGE058
Thermal load of test piece
Figure DEST_PATH_IMAGE059
Constant in steady state conditions;
and S11, calculating the heat load required by the refrigeration system.
Further, the corresponding parameters in step S1 include: indoor air temperature value
Figure 871387DEST_PATH_IMAGE044
Aircraft climate laboratory height
Figure DEST_PATH_IMAGE061
Aircraft climate laboratory width
Figure DEST_PATH_IMAGE063
Aircraft climate laboratory length
Figure DEST_PATH_IMAGE065
Power factor of lighting lamp
Figure DEST_PATH_IMAGE067
Specific heat coefficient of air
Figure DEST_PATH_IMAGE069
Compensating the fresh air quality
Figure DEST_PATH_IMAGE071
Number of full spectrum lamps
Figure DEST_PATH_IMAGE072
Full spectrum lamp power
Figure DEST_PATH_IMAGE073
Coefficient of heat absorption efficiency of the plane to the full spectrum
Figure DEST_PATH_IMAGE074
Effective area of full spectrum lamp on aircraft surface
Figure DEST_PATH_IMAGE075
Number of infrared lamps
Figure DEST_PATH_IMAGE076
Power of infrared lamp
Figure DEST_PATH_IMAGE077
Coefficient of heat absorption efficiency of aircraft surface to infrared lamp
Figure 245867DEST_PATH_IMAGE028
Thickness of the heat insulation board
Figure DEST_PATH_IMAGE079
Heat transfer coefficient of heat insulation board
Figure DEST_PATH_IMAGE081
Water consumption for test
Figure DEST_PATH_IMAGE083
Specific heat coefficient of water
Figure DEST_PATH_IMAGE085
Water temperature for test
Figure DEST_PATH_IMAGE087
Latent heat coefficient of water
Figure DEST_PATH_IMAGE089
Specific heat coefficient of ice
Figure DEST_PATH_IMAGE091
Strong convective heat transfer coefficient
Figure DEST_PATH_IMAGE093
Temperature difference between air and floor
Figure DEST_PATH_IMAGE095
。
Further, in step S3, the laboratory lighting load calculation formula is:
Figure DEST_PATH_IMAGE097
in the formula:
Figure DEST_PATH_IMAGE099
in order to illuminate a steady-state load,
Figure DEST_PATH_IMAGE101
is the power factor of the illuminating lamp,
Figure 623890DEST_PATH_IMAGE065
is the length of the aircraft climate laboratory,
Figure 335494DEST_PATH_IMAGE063
the width of an aircraft climate laboratory.
Further, in step S4, the calculation formula for compensating the fresh air heat load is:
Figure DEST_PATH_IMAGE103
in the formula:
Figure DEST_PATH_IMAGE105
in order to compensate for the steady state heat load of the fresh air,
Figure 731841DEST_PATH_IMAGE069
is the specific heat coefficient of the air,
Figure 277223DEST_PATH_IMAGE071
in order to compensate for the mass of the fresh air,
Figure 595071DEST_PATH_IMAGE044
is the indoor air temperature value and is,
Figure DEST_PATH_IMAGE107
in order to compensate for the temperature of the fresh air,
Figure 310699DEST_PATH_IMAGE107
the value was-25 ℃.
Further, in step S5, the calculation formula of the fan thermal load is:
Figure DEST_PATH_IMAGE109
in the formula:
Figure DEST_PATH_IMAGE111
in order to provide a thermal load for the fan,
Figure 561552DEST_PATH_IMAGE044
is the indoor air temperature value.
Further, in step S6, the calculation formula of the thermal load of the thermal insulation board is:
Figure DEST_PATH_IMAGE113
in the formula:
Figure DEST_PATH_IMAGE115
in order to provide the thermal load of the insulation board,
Figure DEST_PATH_IMAGE117
is the heat transfer coefficient of the heat-insulating plate,
Figure DEST_PATH_IMAGE119
is the area of the heat-insulating plate in the airplane climate laboratory,
Figure DEST_PATH_IMAGE121
is the area of the heat-insulating plate in the circulating air duct,
Figure DEST_PATH_IMAGE123
is the thickness of the heat preservation plate;
Figure DEST_PATH_IMAGE125
the temperature of the inner surface of the heat-insulation plate,
Figure DEST_PATH_IMAGE127
the temperature of the outer surface of the insulation board is taken as a constant value of 35 ℃.
Preferably, in step S8, the precondition of the thermal load calculation formula for the freezing rain/snowfall test is: the water for the freezing rain test is completely converted into ice, the water for the snowfall test is completely converted into snow, and the temperature of the ice/snow is finally the same as the temperature of the test air.
Preferably, in step S10, the test piece is thermally loaded
Figure 12256DEST_PATH_IMAGE059
The values of (A) are:
Figure DEST_PATH_IMAGE129
。
further preferably, in step S11, the calculation formula of the heat load required by the refrigeration system is:
Figure DEST_PATH_IMAGE131
in the formula:
Figure DEST_PATH_IMAGE133
in order to provide the thermal load required by the refrigeration system,
Figure 958346DEST_PATH_IMAGE099
in order to illuminate a steady-state load,
Figure 11753DEST_PATH_IMAGE105
the fresh air steady-state heat load is obtained;
Figure 382691DEST_PATH_IMAGE111
in order to provide a thermal load for the fan,
Figure 863351DEST_PATH_IMAGE115
in order to provide the thermal load of the insulation board,
Figure DEST_PATH_IMAGE134
in order to irradiate the thermal load of the lamp array,
Figure DEST_PATH_IMAGE135
the heat load generated for the freezing rain/snowfall test,
Figure DEST_PATH_IMAGE136
is the heat load of the terrace and is the heat load of the terrace,
Figure DEST_PATH_IMAGE137
the test piece is thermally loaded.
The invention has the beneficial effects that:
(1) the invention provides a modeling and calculating method of the heat load of an irradiation system under a steady state condition, and an accurate result of the steady state heat load of a solar irradiation system is obtained;
(2) the invention provides a calculation method and an equivalent model of the heat load of a freezing rain/snow system, which are used for accurately calculating the heat load related to heat exchange of the freezing rain/snow system;
(3) the invention establishes a calculation method and a model suitable for a climate laboratory, improves the calculation precision, and solves the problem of calculation of the heat load of the aircraft climate environment laboratory under the steady-state working condition under different environmental factors;
(4) the invention realizes the steady-state load data of the refrigerating system under different working conditions, realizes the checking of the refrigerating capacity of the refrigerating system and solves the problem of capacity selection configuration of a large-scale refrigerating system.
Drawings
FIG. 1 is a flow chart of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention clearer, the present invention will be described in further detail with reference to the accompanying drawings, and it is apparent that the described embodiments are only a part of the embodiments of the present invention, not all of the 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.
Example 1
The embodiment is as follows: under the condition that the test working condition in the airplane climate laboratory is the solar irradiation working condition with the temperature of 28 ℃, the method for analyzing the steady-state load of the large airplane test under the condition of multiple environmental factors comprises the following steps:
s1, setting corresponding parameters according to the solar irradiation working condition of 28 ℃, wherein the corresponding parameters comprise: indoor air temperature value
Figure DEST_PATH_IMAGE139
Aircraft climate laboratory height
Figure DEST_PATH_IMAGE141
Aircraft climate laboratory width
Figure DEST_PATH_IMAGE143
Length of airplane climate laboratory
Figure DEST_PATH_IMAGE145
Power factor of lighting lamp
Figure DEST_PATH_IMAGE147
Specific heat coefficient of air
Figure DEST_PATH_IMAGE149
Compensating the fresh air quality
Figure DEST_PATH_IMAGE151
Number of full spectrum lamps
Figure DEST_PATH_IMAGE153
The full spectrum lamp has a power of
Figure DEST_PATH_IMAGE155
Coefficient of heat absorption efficiency of the aircraft to the full spectrum lamp
Figure DEST_PATH_IMAGE157
Number of infrared lamps
Figure DEST_PATH_IMAGE159
Power of infrared lamp
Figure DEST_PATH_IMAGE161
Aircraft surface to infrared lampCoefficient of heat absorption efficiency
Figure DEST_PATH_IMAGE163
Thickness of the heat insulation board
Figure DEST_PATH_IMAGE165
Heat transfer coefficient of heat insulation board
Figure DEST_PATH_IMAGE167
Strong convective heat transfer coefficient
Figure DEST_PATH_IMAGE169
Temperature difference between air and floor
Figure DEST_PATH_IMAGE171
；
S2, on the basis that the ground in the aircraft climate laboratory is a concrete terrace, calculating the area of the insulation board in the aircraft climate laboratory by the following formula:
Figure 575699DEST_PATH_IMAGE002
in the formula:
Figure 167217DEST_PATH_IMAGE004
is the area of the insulation board inside the aircraft climate laboratory,
Figure 330345DEST_PATH_IMAGE006
is the altitude of the aircraft climate laboratory,
Figure 981907DEST_PATH_IMAGE008
is the width of an aircraft climate laboratory,
Figure 761644DEST_PATH_IMAGE010
length for an aircraft climate laboratory;
s3, calculating the illumination load of the airplane climate laboratory, wherein the calculation formula of the illumination load of the laboratory is as follows:
Figure 156853DEST_PATH_IMAGE097
in the formula:
Figure 502384DEST_PATH_IMAGE099
in order to illuminate a steady-state load,
Figure 324846DEST_PATH_IMAGE101
is the power factor of the illuminating lamp,
Figure 591879DEST_PATH_IMAGE065
is the length of the aircraft climate laboratory,
Figure 931725DEST_PATH_IMAGE063
width of the aircraft climate laboratory;
s4, calculating and compensating the fresh air heat load, wherein the calculation formula for compensating the fresh air heat load is as follows:
Figure 600604DEST_PATH_IMAGE103
in the formula:
Figure 593968DEST_PATH_IMAGE105
in order to compensate for the steady state heat load of the fresh air,
Figure 551559DEST_PATH_IMAGE069
is the specific heat coefficient of the air,
Figure 554150DEST_PATH_IMAGE071
in order to compensate for the mass of the fresh air,
Figure 77536DEST_PATH_IMAGE044
is the indoor air temperature value and is,
Figure 772959DEST_PATH_IMAGE107
in order to compensate for the temperature of the fresh air,
Figure 14585DEST_PATH_IMAGE107
the value is-25 ℃;
s5, calculating the heat load of the fan, wherein the calculation formula of the heat load of the fan is as follows:
Figure DEST_PATH_IMAGE172
in the formula:
Figure 696233DEST_PATH_IMAGE111
is a thermal load of the fan and is,
Figure 74125DEST_PATH_IMAGE044
is an indoor air temperature value;
s6, calculating the heat load of the heat-insulating plate, wherein the calculation formula of the heat load of the heat-insulating plate is as follows:
Figure DEST_PATH_IMAGE173
in the formula:
Figure 206029DEST_PATH_IMAGE115
in order to provide the thermal load of the insulation board,
Figure DEST_PATH_IMAGE174
is the heat transfer coefficient of the heat-insulating plate,
Figure 669371DEST_PATH_IMAGE119
is the area of the heat-insulating plate in the airplane climate laboratory,
Figure DEST_PATH_IMAGE175
is the area of the heat-insulating plate in the circulating air duct,
Figure 217027DEST_PATH_IMAGE123
is the thickness of the heat preservation plate;
Figure DEST_PATH_IMAGE176
the temperature of the inner surface of the heat-insulation plate,
Figure DEST_PATH_IMAGE177
taking a constant value of 35 ℃ for the temperature of the outer surface of the insulation board;
s7, calculating the heat load of the solar radiation lamp array: assuming that a part of the heat generated by the lamp array is absorbed by the air and a part is absorbed by the aircraft, the load of the lamp array is calculated by the formula:
Figure 855950DEST_PATH_IMAGE012
in the formula:
Figure 627597DEST_PATH_IMAGE014
in order to irradiate the effective thermal load of the lamp array,
Figure 578235DEST_PATH_IMAGE016
for the number of full-spectrum lamps,
Figure 726320DEST_PATH_IMAGE018
is the power of the full-spectrum lamp,
Figure DEST_PATH_IMAGE178
the coefficient of the heat absorption efficiency of the plane to the full spectrum,
Figure 78804DEST_PATH_IMAGE022
is the effective area of the full spectrum lamp on the aircraft surface,
Figure 427877DEST_PATH_IMAGE024
in order to be able to count the number of infrared lamps,
Figure 865811DEST_PATH_IMAGE026
is the power of the infrared lamp and is,
Figure 552007DEST_PATH_IMAGE028
the coefficient of heat absorption efficiency of the aircraft surface to the infrared lamp;
s8, skipping the step, and entering step S9;
s9, calculating the heat load of the floor, wherein the heat transfer process inside the floor and the heat exchange process of the air of the floor are simplified to obtain the floor heat load calculation formula:
Figure DEST_PATH_IMAGE179
in the formula:
Figure 959330DEST_PATH_IMAGE048
is the heat load of the terrace and is the heat load of the terrace,
Figure 72780DEST_PATH_IMAGE050
in order to have a strong convective heat transfer coefficient,
Figure 263590DEST_PATH_IMAGE052
is the width of an aircraft climate laboratory,
Figure 487898DEST_PATH_IMAGE054
is the length of the aircraft climate laboratory,
Figure 814974DEST_PATH_IMAGE056
the temperature difference between the air and the floor;
s10, calculating the thermal load of the test piece object
Figure 240270DEST_PATH_IMAGE058
Thermal load of test piece
Figure 652797DEST_PATH_IMAGE059
Constant in steady state case:
Figure DEST_PATH_IMAGE180
；
s11, calculating the heat load required by the refrigeration system, wherein the calculation formula of the heat load required by the refrigeration system is as follows:
Figure 884058DEST_PATH_IMAGE131
in the formula:
Figure 65641DEST_PATH_IMAGE133
in order to provide the thermal load required by the refrigeration system,
Figure 520893DEST_PATH_IMAGE099
in order to illuminate a steady-state load,
Figure 686295DEST_PATH_IMAGE105
is the steady-state heat load of the fresh air;
Figure 252406DEST_PATH_IMAGE111
in order to provide a thermal load for the fan,
Figure 554074DEST_PATH_IMAGE115
in order to provide the thermal load of the insulation board,
Figure 321173DEST_PATH_IMAGE134
in order to irradiate the thermal load of the lamp array,
Figure 442713DEST_PATH_IMAGE135
the heat load generated for the freezing rain/snowfall test,
Figure 812514DEST_PATH_IMAGE048
in order to be the heat load of the terrace,
Figure 968689DEST_PATH_IMAGE058
the test piece is thermally loaded.
Example 2
The embodiment is as follows: under the condition that the test working condition in the airplane climate laboratory is a freezing rain working condition with the temperature of minus 10 ℃, the method for analyzing the steady-state load of the large airplane test under the condition of multi-environment factors comprises the following steps:
s1, setting corresponding parameters according to the freezing rain condition that the test condition is-10 ℃, wherein the corresponding parameters comprise: indoor air temperature value
Figure DEST_PATH_IMAGE182
Aircraft climate laboratory height
Figure DEST_PATH_IMAGE184
Aircraft climate laboratory width
Figure DEST_PATH_IMAGE186
Length of airplane climate laboratory
Figure DEST_PATH_IMAGE188
Power factor of lighting lamp
Figure 500164DEST_PATH_IMAGE147
Specific heat coefficient of air
Figure 109000DEST_PATH_IMAGE149
Compensating the fresh air quality
Figure 423438DEST_PATH_IMAGE151
Thickness of the heat insulation board
Figure DEST_PATH_IMAGE190
And heat transfer coefficient of the heat-insulating board
Figure DEST_PATH_IMAGE192
Water consumption for test
Figure DEST_PATH_IMAGE194
Specific heat coefficient of water
Figure DEST_PATH_IMAGE196
Water temperature for test
Figure DEST_PATH_IMAGE198
Latent heat coefficient of water
Figure DEST_PATH_IMAGE200
Specific heat coefficient of ice
Figure DEST_PATH_IMAGE202
Strong convective heat transfer coefficient
Figure DEST_PATH_IMAGE204
Temperature difference between air and floor
Figure DEST_PATH_IMAGE206
。
S2, on the basis that the ground in the aircraft climate laboratory is a concrete terrace, calculating the area of the insulation board in the aircraft climate laboratory by the following formula:
Figure 309486DEST_PATH_IMAGE002
in the formula:
Figure 277442DEST_PATH_IMAGE004
is the area of the insulation board inside the airplane climate laboratory,
Figure 639153DEST_PATH_IMAGE006
is the altitude of the aircraft climate laboratory,
Figure 350757DEST_PATH_IMAGE008
is the width of an aircraft climate laboratory,
Figure 215945DEST_PATH_IMAGE010
is the length of the aircraft climate laboratory;
s3, calculating the illumination load of the airplane climate laboratory, wherein the calculation formula of the illumination load of the laboratory is as follows:
Figure DEST_PATH_IMAGE207
in the formula:
Figure 758397DEST_PATH_IMAGE099
in order to illuminate a steady-state load,
Figure 341825DEST_PATH_IMAGE101
is the power factor of the illuminating lamp,
Figure 857120DEST_PATH_IMAGE065
is the length of the aircraft climate laboratory,
Figure 780077DEST_PATH_IMAGE063
width of an aircraft climate laboratory;
s4, calculating and compensating the fresh air heat load, wherein the calculation formula for compensating the fresh air heat load is as follows:
Figure 89835DEST_PATH_IMAGE103
in the formula:
Figure 160559DEST_PATH_IMAGE105
in order to compensate for the steady state heat load of the fresh air,
Figure 745125DEST_PATH_IMAGE069
is the specific heat coefficient of the air,
Figure 584905DEST_PATH_IMAGE071
in order to compensate for the mass of the fresh air,
Figure 65565DEST_PATH_IMAGE044
is the indoor air temperature value and is,
Figure 764530DEST_PATH_IMAGE107
in order to compensate for the temperature of the fresh air,
Figure 356049DEST_PATH_IMAGE107
the value is-25 ℃;
s5, calculating the heat load of the fan, wherein the calculation formula of the heat load of the fan is as follows:
Figure 50335DEST_PATH_IMAGE172
in the formula:
Figure 170738DEST_PATH_IMAGE111
in order to provide a thermal load for the fan,
Figure 950475DEST_PATH_IMAGE044
is an indoor air temperature value;
s6, calculating heat loss of the heat load of the heat-insulation plate, wherein the calculation formula of the heat load of the heat-insulation plate is as follows:
Figure DEST_PATH_IMAGE208
in the formula:
Figure 876843DEST_PATH_IMAGE115
in order to provide the thermal load of the insulation board,
Figure 691215DEST_PATH_IMAGE174
is the heat transfer coefficient of the heat-insulating plate,
Figure 513677DEST_PATH_IMAGE119
is the area of the heat-insulating plate in the airplane climate laboratory,
Figure 921656DEST_PATH_IMAGE175
is the area of the heat-insulating plate in the circulating air duct,
Figure 120556DEST_PATH_IMAGE123
the thickness of the heat preservation plate;
Figure 789435DEST_PATH_IMAGE176
the temperature of the inner surface of the heat-insulation plate,
Figure 313957DEST_PATH_IMAGE177
taking a constant value of 35 ℃ for the temperature of the outer surface of the insulation board;
s7, skipping the step, and entering step S8;
s8, calculating the heat load generated under the freezing rain working condition, and the precondition is that: the water for the freezing rain test is completely converted into ice, the temperature of the ice is finally the same as the temperature of the test air, and the calculation formula of the freezing rain test heat load is as follows:
Figure 68287DEST_PATH_IMAGE030
in the formula:
Figure DEST_PATH_IMAGE209
for the thermal load generated by the freezing rain test,
Figure DEST_PATH_IMAGE210
the quality of test water is shown;
Figure DEST_PATH_IMAGE211
is the specific heat coefficient of water and is,
Figure DEST_PATH_IMAGE212
the temperature of the water for the test is the temperature of the water,
Figure 8561DEST_PATH_IMAGE040
is the latent heat coefficient of water;
Figure 938471DEST_PATH_IMAGE042
is the specific heat coefficient of the ice,
Figure 368315DEST_PATH_IMAGE044
is an indoor air temperature value;
s9, calculating the heat load of the floor, wherein the heat transfer process inside the floor and the air heat exchange process of the floor are simplified, and the calculation formula of the heat load of the floor is as follows:
Figure 609941DEST_PATH_IMAGE179
in the formula:
Figure 150643DEST_PATH_IMAGE048
in order to be the heat load of the terrace,
Figure 794114DEST_PATH_IMAGE050
in order to have a strong convective heat transfer coefficient,
Figure 129281DEST_PATH_IMAGE052
is the width of an aircraft climate laboratory,
Figure 264727DEST_PATH_IMAGE054
is the length of the aircraft climate laboratory,
Figure 343541DEST_PATH_IMAGE056
the temperature difference between the air and the floor;
s10, calculating the thermal load of the test piece object
Figure 841519DEST_PATH_IMAGE058
Thermal load of test piece
Figure 813498DEST_PATH_IMAGE059
Constant in steady state case:
Figure 764137DEST_PATH_IMAGE180
；
s11, calculating the heat load required by the refrigeration system, wherein the calculation formula of the heat load required by the refrigeration system is as follows:
Figure 646642DEST_PATH_IMAGE131
in the formula:
Figure 264705DEST_PATH_IMAGE133
in order to provide the thermal load required by the refrigeration system,
Figure 207254DEST_PATH_IMAGE099
in order to illuminate a steady-state load,
Figure 645188DEST_PATH_IMAGE105
the fresh air steady-state heat load is obtained;
Figure 472330DEST_PATH_IMAGE111
in order to provide a thermal load for the fan,
Figure 944899DEST_PATH_IMAGE115
in order to provide the thermal load of the insulation board,
Figure 58349DEST_PATH_IMAGE134
in order to irradiate the thermal load of the lamp array,
Figure 186842DEST_PATH_IMAGE135
the heat load generated for the freezing rain/snowfall test,
Figure 411150DEST_PATH_IMAGE048
is the heat load of the terrace and is the heat load of the terrace,
Figure 472647DEST_PATH_IMAGE058
the test piece is thermally loaded.
Example 3
The embodiment is as follows: under the condition that the test working condition in the airplane climate laboratory is a snowfall working condition with the temperature of-25 ℃, the method for analyzing the steady-state load of the large airplane test under the condition of multi-environment factors comprises the following steps:
s1, setting corresponding parameters according to the snowfall working condition of-25 ℃, wherein the corresponding parameters comprise: indoor air temperature value
Figure DEST_PATH_IMAGE214
Aircraft climate laboratory height
Figure 288156DEST_PATH_IMAGE184
Aircraft climate laboratory width
Figure 700683DEST_PATH_IMAGE186
Length of airplane climate laboratory
Figure 869627DEST_PATH_IMAGE188
Power factor of lighting lamp
Figure DEST_PATH_IMAGE215
Specific heat coefficient of air
Figure 51210DEST_PATH_IMAGE149
Compensating the fresh air quality
Figure 240883DEST_PATH_IMAGE151
Specific heat coefficient of air
Figure DEST_PATH_IMAGE216
Compensating the fresh air quality
Figure DEST_PATH_IMAGE217
Thickness of the heat insulation board
Figure DEST_PATH_IMAGE218
Heat transfer coefficient of heat insulation board
Figure DEST_PATH_IMAGE219
Water consumption for test
Figure DEST_PATH_IMAGE221
Specific heat coefficient of water
Figure DEST_PATH_IMAGE223
Water temperature for test
Figure DEST_PATH_IMAGE225
Latent heat coefficient of water
Figure DEST_PATH_IMAGE227
Specific heat coefficient of ice
Figure DEST_PATH_IMAGE229
Strong convective heat transfer coefficient
Figure DEST_PATH_IMAGE231
Temperature difference between air and floor
Figure 547230DEST_PATH_IMAGE206
；
S2, on the basis that the ground in the aircraft climate laboratory is a concrete terrace, calculating the area of the insulation board in the aircraft climate laboratory by the following formula:
Figure 113341DEST_PATH_IMAGE002
in the formula:
Figure 618272DEST_PATH_IMAGE004
is the area of the insulation board inside the airplane climate laboratory,
Figure 978846DEST_PATH_IMAGE006
is the altitude of the aircraft climate laboratory,
Figure 365965DEST_PATH_IMAGE008
is the width of an aircraft climate laboratory,
Figure 735766DEST_PATH_IMAGE010
is the length of the aircraft climate laboratory;
s3, calculating the illumination load of the airplane climate laboratory, wherein the calculation formula of the illumination load of the laboratory is as follows:
Figure 32886DEST_PATH_IMAGE097
in the formula:
Figure 829941DEST_PATH_IMAGE099
in order to illuminate a steady-state load,
Figure 438777DEST_PATH_IMAGE101
is the power factor of the illuminating lamp,
Figure 877849DEST_PATH_IMAGE065
is the length of the aircraft climate laboratory,
Figure 888530DEST_PATH_IMAGE063
width of an aircraft climate laboratory;
s4, calculating and compensating the fresh air heat load, wherein the calculation formula for compensating the fresh air heat load is as follows:
Figure DEST_PATH_IMAGE232
in the formula:
Figure 260081DEST_PATH_IMAGE105
in order to compensate for the steady state heat load of the fresh air,
Figure 356213DEST_PATH_IMAGE069
is the specific heat coefficient of the air,
Figure 67817DEST_PATH_IMAGE071
in order to compensate for the mass of the fresh air,
Figure 136267DEST_PATH_IMAGE044
is the indoor air temperature value and is,
Figure 275124DEST_PATH_IMAGE107
in order to compensate for the temperature of the fresh air,
Figure 858553DEST_PATH_IMAGE107
the value is-25 ℃;
s5, calculating the heat load of the fan, wherein the calculation formula of the heat load of the fan is as follows:
Figure 639427DEST_PATH_IMAGE172
in the formula:
Figure 624700DEST_PATH_IMAGE111
in order to provide a thermal load for the fan,
Figure 934459DEST_PATH_IMAGE044
is an indoor air temperature value;
s6, calculating heat loss of the heat load of the heat-insulation plate, wherein the calculation formula of the heat load of the heat-insulation plate is as follows:
Figure 146128DEST_PATH_IMAGE208
in the formula:
Figure 199535DEST_PATH_IMAGE115
in order to provide the thermal load of the insulation board,
Figure 39315DEST_PATH_IMAGE174
is the heat transfer coefficient of the heat-insulating plate,
Figure 723237DEST_PATH_IMAGE119
is the area of the heat-insulating plate in the airplane climate laboratory,
Figure 15678DEST_PATH_IMAGE175
is the area of the heat-insulating plate in the circulating air duct,
Figure 872776DEST_PATH_IMAGE123
is the thickness of the heat preservation plate;
Figure 567063DEST_PATH_IMAGE176
the temperature of the inner surface of the heat-insulation plate,
Figure 749782DEST_PATH_IMAGE127
taking a constant value of 35 ℃ for the temperature of the outer surface of the insulation board;
s7, skipping the step, the flow proceeds to step S8;
s8, calculating the heat load generated by the snowfall working condition, and the precondition is that: the water used for the snowfall test is completely converted into snow, the temperature of the snow is finally the same as the temperature of the test air, and the calculation formula of the thermal load of the snowfall test is as follows:
Figure DEST_PATH_IMAGE233
in the formula:
Figure 795099DEST_PATH_IMAGE209
in order to generate the thermal load for the snowfall test,
Figure 331253DEST_PATH_IMAGE210
the quality of test water is shown;
Figure DEST_PATH_IMAGE234
is the specific heat coefficient of water and is,
Figure 880046DEST_PATH_IMAGE212
the temperature of the water for the test is the temperature of the water,
Figure 499246DEST_PATH_IMAGE040
is the latent heat coefficient of water;
Figure 766280DEST_PATH_IMAGE042
is the specific heat coefficient of ice and,
Figure 965180DEST_PATH_IMAGE044
is an indoor air temperature value;
s9, calculating the heat load of the floor, wherein the heat transfer process inside the floor and the air heat exchange process of the floor are simplified, and the calculation formula of the heat load of the floor is as follows:
Figure DEST_PATH_IMAGE235
in the formula:
Figure 571742DEST_PATH_IMAGE048
is the heat load of the terrace and is the heat load of the terrace,
Figure 830685DEST_PATH_IMAGE050
in order to have a strong convective heat transfer coefficient,
Figure 991539DEST_PATH_IMAGE052
is the width of an aircraft climate laboratory,
Figure 728551DEST_PATH_IMAGE054
is the length of the aircraft climate laboratory,
Figure 251936DEST_PATH_IMAGE056
for air and floorThe temperature difference of (a);
s10, calculating the thermal load of the test piece object
Figure 947359DEST_PATH_IMAGE058
Thermal load of test piece
Figure 923406DEST_PATH_IMAGE059
Constant in steady state case:
Figure 464108DEST_PATH_IMAGE180
；
s11, calculating the heat load required by the refrigeration system, wherein the calculation formula of the heat load required by the refrigeration system is as follows:
Figure 107579DEST_PATH_IMAGE131
in the formula:
Figure 849270DEST_PATH_IMAGE133
in order to provide the thermal load required by the refrigeration system,
Figure 578192DEST_PATH_IMAGE099
in order to illuminate a steady-state load,
Figure 657007DEST_PATH_IMAGE105
is the steady-state heat load of the fresh air;
Figure 355317DEST_PATH_IMAGE111
in order to provide a thermal load for the fan,
Figure 861384DEST_PATH_IMAGE115
in order to provide the thermal load of the insulation board,
Figure 77602DEST_PATH_IMAGE134
in order to irradiate the thermal load of the lamp array,
Figure 225687DEST_PATH_IMAGE135
the heat load generated for the freezing rain/snowfall test,
Figure 578170DEST_PATH_IMAGE048
in order to be the heat load of the terrace,
Figure 520719DEST_PATH_IMAGE058
the test piece is thermally loaded.
Examples of the experiments
The heat load required by the refrigeration systems of the embodiments 1, 2 and 3 is calculated by the calculation formula of the heat load of the refrigeration systems, and the results are as follows:
table 1 example 1, example 2, and example 3 refrigeration system heat load statistics
Item Solar irradiation operating mode Freezing rain condition Snowfall conditions
Temperature (. degree.C.) 28 -10 -25
Lamp (kW) 50.0 50.0 50.0
New trend system (kW) 0.0 0.0 0.0
Draught fan (kW) 483.9 553.8 587.3
Thermal insulation board (kW) 20.3 132.6 176.9
Terrace (kW) 1134.0 793.8 680.4
Test piece (kW) 100.0 100.0 100.0
Irradiation system (kW) 2580.0 0.0 0.0
Snowing system (kW) 0.0 0.0 3630.6
Freezing rain system (kW) 0.0 3876.9 0.0
In total (kW) 4368.2 5417.2 5225.2

Claims (4)

1. The method for analyzing the steady-state load of the large airplane test under the condition of multiple environmental factors is characterized by comprising the following steps of:
s1, setting corresponding parameters according to the test working conditions;
s2, on the basis that the ground in the aircraft climate laboratory is a concrete terrace, calculating the area of the insulation board in the aircraft climate laboratory by the following formula:
Asurf＝2·Hr·Wr+2·Hr·Lr+Lr·Wr
in the formula: a. thesurfIs the area of the interior insulation board of the aircraft climate laboratory, HrHeight of aircraft climate laboratory, WrWidth of the aircraft climate laboratory, LrIs the length of the aircraft climate laboratory;
s3, calculating the illumination load of the airplane climate laboratory, wherein the calculation formula of the illumination load of the laboratory is as follows:
ql＝δ·Lr·Wr
in the formula: q. q of1For steady state load illumination, δ is lamp power factor, LrLength of aircraft climate laboratory, WrWidth of the aircraft climate laboratory;
s4, calculating and compensating the fresh air heat load, wherein the calculation formula for compensating the fresh air heat load is as follows:
Figure FDF0000016712360000011
in the formula: q. q.smaFor compensating steady-state heat load of fresh air，cpIs the specific heat coefficient of air, maTo compensate for fresh air quality, TaIs the indoor air temperature value, Ta0To compensate for fresh air temperature, Ta0The value is-25 ℃;
s5, calculating the heat load of the fan;
s6, calculating the heat load of the heat-insulating plate, wherein the calculation formula of the heat load of the heat-insulating plate is as follows:
Figure FDF0000016712360000012
in the formula: q. q ofsIs the thermal load of the insulation board, lambda is the heat transfer coefficient of the insulation board, AsurfIs the area of an internal insulation board of an airplane climate laboratory, Asurf_AHIs the area of the heat-insulating board in the circulating air duct hsIs the thickness of the heat preservation plate; t is0Is the temperature of the inner surface of the insulation board, TbTaking a constant value of 35 ℃ for the temperature of the outer surface of the heat-insulation plate;
s7, calculating the heat load of the solar radiation lamp array: judging whether the test working condition is an irradiation working condition, if not, skipping the step and entering the step S8, if so, assuming that part of heat generated by the radiation lamp array is absorbed by air and part of heat is absorbed by an airplane, and calculating the heat load of the solar radiation lamp array according to the following formula:
qsolar＝Nfull·ψfull·(1-ηfull)+Nrad·ψrad·(1-ηrad)
in the formula: q. q.ssolarFor the effective heat load of an array of radiation lamps, NfullNumber of full spectrum lamps, #fullIs the power of a full spectrum lamp, etafullIs the heat absorption efficiency coefficient of the plane to the full spectrum, Sa_fullEffective area of full spectrum lamp on aircraft surface, NradNumber of infrared lamps, #radPower of infrared lamps, ηradThe coefficient of heat absorption efficiency of the surface of the airplane to the infrared lamp;
s8, calculating the thermal load of the freezing rain/snowfall working condition: judging whether the test working condition is a sleet/snowfall working condition, if not, skipping the step and entering the step S9, if yes, calculating the thermal load of the sleet/snowfall test according to the following formula:
qsleet＝mwater·[Cp_water·(Twater-0)+hfs+Cp_ice·(273.15-Ta)]
in the formula: q. q.ssleetThermal load generated for freezing rain/snowfall test, mwaterThe quality of test water is shown; cp_waterIs the specific heat coefficient of water, TwaterWater temperature h for testfsIs the latent heat coefficient of water; cp_iceIs the specific heat coefficient of ice, TaIs an indoor air temperature value, and the precondition is as follows: the water for the freezing rain test is completely converted into ice, the water for the snowfall test is completely converted into snow, and the temperature of the ice/snow is finally the same as the temperature of the test air;
s9, calculating the heat load of the floor, wherein the heat transfer process inside the floor and the air heat exchange process of the floor are simplified, and the calculation formula of the heat load of the floor is as follows:
qc＝hc·Wr·Lr·ΔT
in the formula: q. q.scFor the thermal load of the floor, hcFor a strong convective heat transfer coefficient, WrWidth of the aircraft climate laboratory, LrThe length of an airplane climate laboratory, and delta T is the temperature difference between air and a terrace;
s10, calculating the thermal load q of the test piece objecttThermal load q of test piecetConstant in steady state conditions;
s11, calculating the heat load required by the refrigeration system, wherein the calculation formula of the heat load required by the refrigeration system is as follows:
Q＝ql+qma+qf+qs+qsolar+qsleet+qc+qt
in the formula: q is the heat load required by the refrigeration system, Q1For illuminating steady-state loads, qmaIs the steady-state heat load of the fresh air; q. q.sfFor thermal loading of the fan, qsIs the thermal load of the insulation board, qsolarFor thermal loading of the lamp array, qsleetThermal load generated for freezing rain/snowfall test, qcIs groundHeat load of the plateau, qtThe test piece is thermally loaded.
2. The method for analyzing the steady-state load of the large aircraft test under the multi-environment-factor condition as recited in claim 1, wherein the corresponding parameters in the step S1 include: indoor air temperature value TaAircraft climate laboratory height HrWidth W of airplane climate laboratoryrLength L of airplane climate laboratoryrPower factor delta of lighting lamp and specific heat coefficient c of airpCompensating the fresh air mass maNumber N of full spectrum lampsfullPower psi of full spectrum lampfullCoefficient eta of heat absorption efficiency of plane to full spectrumfullEffective area S of full spectrum lamp on aircraft surfacea_fullNumber N of infrared lampsradPower psi of infrared lampradCoefficient eta of heat absorption efficiency of aircraft surface to infrared lampradThickness h of the insulation boardsHeat transfer coefficient lambda of heat-insulating board and water consumption m for testwaterSpecific heat coefficient of water Cp_waterWater temperature T for testwaterLatent heat coefficient h of waterfsSpecific heat coefficient of ice Cp_iceStrong convective heat transfer coefficient hcAnd the temperature difference delta T between the air and the floor.
3. The method for analyzing the steady-state load of the large aircraft test under the multi-environment-factor condition as claimed in claim 1, wherein in the step S5, the calculation formula of the thermal load of the fan is as follows:
Figure FDF0000016712360000041
in the formula: q. q.sfFor thermal loading of the fan, TaIs the indoor air temperature value.
4. The method for analyzing the steady-state load of the large aircraft under the multi-environment-factor condition as claimed in claim 1, wherein in the step S10, the thermal load q of the test piece istThe values of (A) are: q. q.st＝100kw。
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