CN113553707B - Fairing temperature and humidity modeling method based on energy and mass conservation - Google Patents

Fairing temperature and humidity modeling method based on energy and mass conservation Download PDF

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CN113553707B
CN113553707B CN202110826872.3A CN202110826872A CN113553707B CN 113553707 B CN113553707 B CN 113553707B CN 202110826872 A CN202110826872 A CN 202110826872A CN 113553707 B CN113553707 B CN 113553707B
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孙成杰
柴毅
鄢利清
刘切
郭茂耘
唐树海
陈小龙
范林川
朱亚雄
施镇顺
方森林
赵立芬
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Chinese People's Liberation Army 63798
Chongqing University
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Abstract

The invention relates to a fairing temperature and humidity modeling method based on energy and mass conservation, and belongs to the technical field of temperature and humidity prediction. In the aspect of temperature and humidity modeling, a mathematical equation of temperature change in the fairing is established by utilizing energy conservation, a heat balance equation taking an enthalpy value as an air state change index is established by utilizing substance conservation, and a temperature and humidity prediction model is jointly established, so that the problem of low prediction accuracy caused by serious temperature and humidity coupling of the traditional temperature and humidity prediction model is solved.

Description

Fairing temperature and humidity modeling method based on energy and mass conservation
Technical Field
The invention belongs to the technical field of temperature and humidity prediction, and relates to a fairing temperature and humidity modeling method based on energy and mass conservation.
Background
In the transmitting task, the conditions that the air conditioning unit is shut down due to fluctuation of an external power grid caused by thunderstorm weather and the like, the air conditioning unit is stopped due to failure, the transmitting program is stopped due to some reason after an air conditioner connector falls off, and the like exist. These conditions make the air conditioner unable to provide a safe environment for the load. Therefore, after air supply is stopped, the change rule of the temperature and the humidity in the fairing is mastered, and the time when the temperature and the humidity exceed the limit is found, so that timely and effective rescue measures are taken before the safe time of the temperature and humidity range exceeding the load requirement, and the safety of high-value loads is ensured.
To this problem, the humiture prediction model in the radome fairing is urgently needed, realizes the humiture prediction to accurate quick.
Disclosure of Invention
In view of this, the present invention provides a fairing temperature and humidity modeling method based on energy and mass conservation. So as to realize accurate and quick fairing humiture prediction model. On the basis of analyzing a heat transfer mechanism and a humidity change mechanism of a fairing air-conditioning guarantee system in detail, the actual situation of simulated emission before emission is combined, and a fairing and an internal satellite thereof are equivalent to a whole body with a certain heat transfer coefficient, heat transfer area and heat capacity according to the certainty of thermodynamic parameters (heat capacity, external surface area and structure) of the fairing, namely a fairing assembly. And finally, establishing a temperature and humidity prediction model in the fairing based on the energy conservation and mass conservation laws and considering the influences of factors such as external environment temperature, wind speed, solar radiation and the like.
In order to achieve the purpose, the invention provides the following technical scheme:
a fairing temperature and humidity modeling method based on energy and mass conservation comprises the following steps:
s1: calculating the heat transfer coefficient of the enclosure structure of the enclosure wall of the fairing;
s2: calculating the mass of moisture-containing water vapor mixed in the wet air containing 1kg of dry air in the current fairing;
s3: calculating to obtain the specific volume of dry air according to the total pressure and the moisture content of the current fairing;
s4: calculating the constant-pressure specific heat capacity of the current wet air;
s5: calculating the enthalpy of the current humid air, i.e. the sum of the enthalpy of 1kg of dry air and the enthalpy of 0.001dkg water vapor;
s6: according to the law of conservation of energy, the change rate of the total energy in the fairing is equal to the energy entering the fairing in unit time minus the energy flowing out of the fairing in unit time in a heat dissipation mode, the change rate of the energy in the fairing is equal to (the heat entering the fairing + the heat dissipation amount of equipment in the fairing) - (the heat discharged from the fairing + the heat transfer amount from the interior of the fairing to the exterior of the fairing), a mathematical equation of the temperature change in the fairing is established, and the unit time is 1 min;
s7: judging whether the air obtains heat or loses heat according to the change of specific enthalpy of the air with certain mass in the treatment process; the increase of the specific enthalpy of the air indicates the heat gain in the air; a decrease in the specific enthalpy of air indicates a loss of heat in the air; the enthalpy value is used as the basis for measuring the cold quantity and the heat quantity of the air, and a heat balance equation is listed from the energy perspective;
s8: simultaneously solving a temperature change mathematical equation and a heat balance equation to obtain the temperature T of the humid air in the fairing n And enthalpy of humid air in the cowling
Figure BDA0003174056250000021
S9: and obtaining the relative humidity phi of the wet air in the fairing according to the moisture content and the enthalpy.
Optionally, in S6, the mathematical equation of the temperature change in the fairing is:
Figure BDA0003174056250000022
wherein, T n The temperature of air in the fairing is measured in units of ℃; t is sa The comprehensive temperature of the air outside the fairing contains factors of solar radiation and atmospheric long-wave radiation, and the unit is;
Figure BDA0003174056250000023
is the density of the humid air in the cowling, in kg/m 3 ；
Figure BDA0003174056250000024
The density of wet air supplied to the rocket fairing air conditioner is kg/m 3 ；
Figure BDA0003174056250000025
The constant pressure specific heat capacity of the wet air in the fairing is J/(kg.K);
Figure BDA0003174056250000026
the constant-pressure specific heat capacity of the wet air supplied by the rocket fairing air conditioner is represented by J/(kg.K); q f The heat dissipation capacity of the satellite in the fairing in unit time is 200W; m is a group of s 2200m for air supply quantity of rocket fairing air conditioner 3 H, i.e. 36.7m 3 Min; v is the internal air volume of the rocket fairing and the unit is m 3 (ii) a F is the area of the outer surface of the fairing in m 2 (ii) a k is the heat transfer coefficient of the enclosure wall of the fairing enclosure wall, and the unit is w/(m) 2 ·K)。
Optionally, in S7, the heat balance equation is:
Figure BDA0003174056250000027
wherein the content of the first and second substances,
Figure BDA0003174056250000028
is the enthalpy of the wet air in the fairing, KJ/kg;
Figure BDA0003174056250000029
the enthalpy of the wet air supplied to the cowling air conditioner is KJ/kg.
The invention has the beneficial effects that:
1. the invention relates to a fairing temperature and humidity modeling method based on energy and mass conservation, which is characterized in that a fairing and an internal satellite thereof are equivalent to a whole body with certain heat transfer coefficient, heat transfer area and heat capacity, namely a fairing assembly, according to the certainty of the thermodynamic parameters (heat capacity, external surface area and structure) of the fairing, and the problem that the fairing and the internal satellite are separately considered to cause a model to be complex when the traditional fairing is modeled is solved.
2. The invention relates to a fairing temperature and humidity modeling method based on energy and mass conservation, which is characterized in that an enthalpy value is adopted as an air index to establish a heat balance equation, a mathematical equation for temperature change of a fairing assembly is established in combination, and the influence of factors such as external environment temperature, wind speed and solar radiation is considered, so that a model for predicting the temperature and humidity in a fairing is established, and the problem of low accuracy of the traditional fairing temperature and humidity modeling method is effectively solved.
Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and claims thereof.
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For the purposes of promoting a better understanding of the objects, aspects and advantages of the invention, reference will now be made to the following detailed description taken in conjunction with the accompanying drawings in which:
FIG. 1 is a graph showing the variation of ambient temperature stability values in a cowling of an ambient 1 with the temperature of an air supply;
FIG. 2 is a graph showing the variation of the ambient humidity stability value in the cowling of the ambient 1 with the supply air temperature;
FIG. 3 is a graph of ambient temperature stability values within the cowling of ambient 2 as a function of supply air temperature;
fig. 4 is a graph showing changes in the ambient humidity stability value inside the cowling of the ambient 2 with changes in the supply air temperature.
Detailed Description
The embodiments of the present invention are described below with reference to specific embodiments, and other advantages and effects of the present invention will be easily understood by those skilled in the art from the disclosure of the present specification. The invention is capable of other and different embodiments and of being practiced or of being carried out in various ways, and its several details are capable of modification in various respects, all without departing from the spirit and scope of the present invention. It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present invention in a schematic way, and the features in the following embodiments and examples may be combined with each other without conflict.
Wherein the showings are for the purpose of illustrating the invention only and not for the purpose of limiting the same, and in which there is shown by way of illustration only and not in the drawings in which there is no intention to limit the invention thereto; to better illustrate the embodiments of the present invention, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; it will be understood by those skilled in the art that certain well-known structures in the drawings and descriptions thereof may be omitted.
The same or similar reference numerals in the drawings of the embodiments of the present invention correspond to the same or similar components; in the description of the present invention, it should be understood that if there is an orientation or positional relationship indicated by terms such as "upper", "lower", "left", "right", "front", "rear", etc., based on the orientation or positional relationship shown in the drawings, it is only for convenience of description and simplification of description, but it is not an indication or suggestion that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and therefore, the terms describing the positional relationship in the drawings are only used for illustrative purposes, and are not to be construed as limiting the present invention, and the specific meaning of the terms may be understood by those skilled in the art according to specific situations.
The embodiment is a fairing temperature and humidity modeling method based on energy and mass conservation, and according to the certainty of thermodynamic parameters (heat capacity, external surface area and structure) of a fairing, the fairing and an internal satellite thereof are equivalent to a whole body with certain heat transfer coefficient, heat transfer area and heat capacity, namely a fairing assembly, so that the problem that the fairing and the internal satellite are separated from each other to cause a model to be complex when the traditional fairing is modeled is solved. The enthalpy value is adopted as an air index to establish a heat balance equation, a mathematical equation for temperature change of a fairing assembly is established in combination with the enthalpy value, the influence of factors such as external environment temperature, wind speed and solar radiation is considered, a model for predicting the temperature and humidity in the fairing is established, and the problem of low accuracy of the traditional fairing temperature and humidity modeling method is effectively solved, and the method comprises the following steps:
1) calculating the heat transfer coefficient of the enclosure structure of the enclosure wall of the fairing;
the heat transfer coefficient of the enclosure wall of the fairing determines the amount of heat dissipated. The value of the heat transfer coefficient can be calculated by the following formula:
Figure BDA0003174056250000041
in the formula: k is the heat transfer coefficient of the building envelope, w/(m) 2 ·K)；D i Is the thickness of each layer of material, m; n is a radical of i Is the thermal conductivity of each layer material, w/(m.K); a is a n Is the indoor convective heat transfer coefficient, w/(m) 2 K), typically 8.7; a is w Is the outdoor convective heat transfer coefficient, w/(m.K), a w In relation to the external wind speed,
Figure BDA0003174056250000042
v 1 is the average wind speed outside the shroud.
2) Calculating the mass (moisture content) of the mixed water vapor in the wet air containing 1kg of dry air in the current fairing; the moisture content (or specific humidity) is the mass of water vapor mixed in a wet air containing 1kg of dry air.
Figure BDA0003174056250000043
In the formula: d is the moisture content of the humid air, g/kg; p ma The total pressure of the wet air is Pa; p v Is the partial pressure of water vapor, Pa; phi is the relative humidity of the humid air,%; p is s (T) is the water vapor saturation pressure, Pa, corresponding to the humid air temperature, T deg.C, which can be found by looking up a table of saturated water and saturated water vapor and can also be calculated from the fitted formula:
Figure BDA0003174056250000044
3) calculating to obtain the specific volume of dry air according to the total pressure and the moisture content of the current fairing;
the specific volume of the humid air is expressed as the total pressure P at a certain temperature T ma Next, the volume occupied by 1kg of dry air and 0.001dkg of water vapor, i.e., the specific volume of wet air of 1kg of dry air, can also be regarded as being the total pressure P ma And the specific volume of dry air calculated from the moisture content d, i.e.
Figure BDA0003174056250000045
In the formula: v is the specific volume of the humid air, m 3 /kg；R da Taking 287J/(kg. K) as the gas constant of the dry air; t is the temperature of the humid air, DEG C.
Since the specific volume of the humid air is defined on the basis of 1kg of dry air, the density of the humid air is:
Figure BDA0003174056250000051
in the formula: rho ma Density of moist air, kg/m 3 。
4) Calculating the constant-pressure specific heat capacity of the current humid air;
the constant-pressure specific heat capacity of the humid air can be determined according to the component x i And (3) calculating:
Figure BDA0003174056250000052
in the formula: c. C p,ma The constant pressure specific heat capacity of the wet air is J/(kg. K); x is the number of da 、x v The mass fractions of dry air and water vapor in the wet air respectively; c. C p,da The value of J/(kg. K), which is the constant pressure specific heat capacity of dry air, can be obtained by looking up the dry air thermophysical property table and can also be calculated from the fitted formula: c. C p,da ＝7×10 -4 T 2 +1.86×10 -2 T+1005；c p,v J/(kg. K), which is the constant pressure specific heat capacity of water vapor, can be obtained by looking up a table of the thermal physical properties of water vapor and can also be calculated from the fitted formula: c. C p,da ＝9×10 -5 T 3 +3.5×10 -3 T 2 +0.4873T+1854.3。
Figure BDA0003174056250000053
Wherein x da +x v ＝1
Therefore, there are:
Figure BDA0003174056250000054
5) calculating the enthalpy of the current wet air, i.e. the sum of the enthalpy of 1kg of dry air and the enthalpy of 0.001dkg water vapor;
the enthalpy of the humid air is the sum of the enthalpy of 1kg of dry air and the enthalpy of 0.001dkg water vapor, i.e.
Figure BDA0003174056250000055
In the formula: h ma Enthalpy for humid air, KJ/kg; h is da Enthalpy for dry air, KJ/kg; h is v KJ/kg is the enthalpy of the water vapor; t is the temperature of air, DEG C; r is latent heat of vaporization of water, and 2501KJ/kg is taken;
it can be seen that the enthalpy of the humid air includes both sensible heat and latent heat. Thus, the enthalpy of the air does not necessarily increase at elevated temperatures, but rather how the moisture content d varies. In the air treatment process, air is heated, humidified or cooled and dehumidified, and the air state change process can be generally regarded as a constant pressure process, so that the heat flow rate supplied to or removed from the air is only related to the enthalpy difference and the mass flow rate. Therefore, the enthalpy of the humid air can be regarded as the energy that the humid air has.
6) According to the law of conservation of energy, the rate of change of the total energy in the fairing is equal to the energy entering the fairing in unit time minus the energy of the fairing radiating outflow in unit time (1min is a unit), namely: the in-hood energy change rate (heat entering the hood + heat dissipation of the in-hood device) - (heat discharged from the inside of the hood + heat transfer from the inside of the hood to the outside of the hood) is calculated, and a mathematical equation of the temperature change in the fairing is established:
Figure BDA0003174056250000061
wherein, T n Is the air temperature in the fairing, DEG C; t is sa The comprehensive temperature (including solar radiation and atmospheric long-wave radiation factors) of air outside the fairing is at the temperature of DEG C;
Figure BDA0003174056250000062
is the density of the wet air in the cowling, kg/m 3 ；
Figure BDA0003174056250000063
Density of wet air supply kg/m for rocket fairing air conditioner 3 ；
Figure BDA0003174056250000064
The constant pressure specific heat capacity of the wet air in the fairing is J/(kg.K);
Figure BDA0003174056250000065
the constant pressure specific heat capacity of the wet air supplied to the rocket fairing air conditioner is J/(kg.K); q f The heat dissipation capacity of the satellite in the fairing in unit time is 200W; m s The air supply volume of the rocket fairing air conditioner is 2200m 3 H, i.e. 36.7m 3 Min; v is the inner air of rocket fairingProduct of m 3 (ii) a F is the area of the outer surface of the fairing, m 2 (ii) a k is the heat transfer coefficient of the enclosure wall of the fairing enclosure wall, w/(m) 2 ·K)。
7) And judging whether the air obtains heat or loses heat according to the change of specific enthalpy of a certain mass of air in the treatment process. The increase of the specific enthalpy of the air indicates the heat gain in the air; a decrease in the specific enthalpy of air indicates a loss of heat in the air. With the enthalpy as the basis for measuring the cold and heat of air, from the energy point of view, the following heat balance equation can be listed:
Figure BDA0003174056250000066
wherein, the first and the second end of the pipe are connected with each other,
Figure BDA0003174056250000067
is the enthalpy of the wet air in the fairing, KJ/kg;
Figure BDA0003174056250000068
the enthalpy of the wet air supplied by the air conditioner with the fairing is KJ/kg.
8) Simultaneously solving a temperature change mathematical equation and a heat balance equation to obtain the temperature T of the humid air in the fairing n And enthalpy of humid air in the cowling
Figure BDA0003174056250000069
9) And obtaining the relative humidity phi of the wet air in the fairing according to the moisture content and the enthalpy.
Fig. 1 shows that when an initial temperature of the environment inside the fairing is set at 32 c, an initial humidity of 60% and a combined temperature of the environment outside the fairing is set at 35 c. And when the temperature and humidity of the air supply of the fairing air conditioner are adjusted to be 20 ℃ and 40%, a curve graph of the environment temperature stable value in the fairing along with the change of the air supply temperature is formed.
Fig. 2 shows that when the initial temperature of the environment inside the fairing is set at 32 c, the initial humidity is 60% and the integrated temperature of the environment outside the fairing is set at 35 c. And when the temperature and humidity of the air supply of the fairing air conditioner are adjusted to be 20 ℃ and 40%, a curve chart of the environmental humidity stable value in the fairing along with the change of the air supply temperature is formed.
Fig. 3 shows that when the initial temperature of the environment inside the fairing is set at 32 c, the initial humidity is 60% and the integrated temperature of the environment outside the fairing is set at 35 c. And when the air supply humidity of the fairing air conditioner is 40% and the air supply temperature is increased from 11 ℃ to 30 ℃, the ambient temperature stability value in the fairing changes along with the air supply temperature.
Fig. 4 shows that when the initial temperature of the environment inside the fairing is set at 32 c, the initial humidity is 60% and the integrated temperature of the environment outside the fairing is set at 35 c. And when the air supply humidity of the fairing air conditioner is 40% and the air supply temperature is increased from 11 ℃ to 30 ℃, the stable value of the environmental humidity in the fairing is a curve chart changing along with the air supply temperature.
Finally, the above embodiments are only intended to illustrate the technical solutions of the present invention and not to limit the present invention, and although the present invention has been described in detail with reference to the preferred embodiments, it will be understood by those skilled in the art that modifications or equivalent substitutions may be made on the technical solutions of the present invention without departing from the spirit and scope of the technical solutions, and all of them should be covered by the claims of the present invention.

Claims (3)

1. A fairing temperature and humidity modeling method based on energy and mass conservation is characterized in that: the method comprises the following steps:
s1: calculating the heat transfer coefficient of the enclosure structure of the enclosure wall of the fairing;
s2: calculating the mass of moisture-containing water vapor mixed in the wet air containing 1kg of dry air in the current fairing;
s3: calculating to obtain the specific volume of dry air according to the total pressure and the moisture content of the current fairing;
s4: calculating the constant-pressure specific heat capacity of the current humid air;
s5: calculating the enthalpy of the current wet air, i.e. the sum of the enthalpy of 1kg of dry air and the enthalpy of 0.001dkg water vapor;
s6: according to the law of conservation of energy, the change rate of the total energy in the fairing is equal to the energy entering the fairing in unit time minus the energy flowing out of the fairing in unit time in a heat dissipation mode, the change rate of the energy in the fairing is equal to (the heat entering the fairing + the heat dissipation amount of equipment in the fairing) - (the heat discharged from the fairing + the heat transfer amount from the interior of the fairing to the exterior of the fairing), a mathematical equation of the temperature change in the fairing is established, and the unit time is 1 min;
s7: judging whether the air obtains heat or loses heat according to the change of specific enthalpy of the air with certain mass in the treatment process; the increase of the specific enthalpy of the air indicates the heat gain in the air; a decrease in the specific enthalpy of air indicates a loss of heat in the air; the enthalpy value is used as the basis for measuring the cold quantity and the heat quantity of the air, and a heat balance equation is listed from the energy perspective;
s8: simultaneously solving a temperature change mathematical equation and a heat balance equation to obtain the temperature T of the humid air in the fairing n And enthalpy of humid air in cowls
Figure FDA0003174056240000011
S9: and obtaining the relative humidity phi of the wet air in the fairing according to the moisture content and the enthalpy.
2. The fairing temperature and humidity modeling method based on energy and mass conservation of claim 1, wherein the fairing temperature and humidity modeling method comprises the following steps: in S6, the mathematical equation for the change in temperature in the cowling is:
Figure FDA0003174056240000012
wherein, T n The temperature of air in the fairing is measured in units of ℃; t is sa The comprehensive temperature of the air outside the fairing contains factors of solar radiation and atmospheric long-wave radiation, and the unit is;
Figure FDA0003174056240000013
is the density of the humid air in the cowling, in kg/m 3 ；
Figure FDA0003174056240000014
Wet air supply seal for rocket fairing air conditionerDegree in kg/m 3 ；
Figure FDA0003174056240000015
Is the constant-pressure specific heat capacity of the wet air in the fairing, and the unit is J/(kg.K);
Figure FDA0003174056240000016
the constant-pressure specific heat capacity of the wet air supplied by the rocket fairing air conditioner is represented by J/(kg. K); q f The heat dissipation capacity of the satellite in the fairing in unit time is 200W; m s The air supply volume of the rocket fairing air conditioner is 2200m 3 H, i.e. 36.7m 3 Min; v is the internal air volume of the rocket fairing and has the unit of m 3 (ii) a F is the area of the outer surface of the fairing in m 2 (ii) a k is the heat transfer coefficient of the enclosure wall of the fairing enclosure wall, and the unit is w/(m) 2 ·K)。
3. The fairing temperature and humidity modeling method based on energy and mass conservation as claimed in claim 2, wherein: in S7, the heat balance equation is:
Figure FDA0003174056240000021
wherein the content of the first and second substances,
Figure FDA0003174056240000022
is the enthalpy of the wet air in the fairing, KJ/kg;
Figure FDA0003174056240000023
the enthalpy of the wet air supplied to the cowling air conditioner is KJ/kg.
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适用于宽温度和压力范围的湿空气热力性质分段计算方法;袁智等;《动力工程学报》;20110715(第07期);全文 *

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