CN112861316B - Method for characterizing cold emission process by using supercritical carbon dioxide as working medium and computer program product - Google Patents

Method for characterizing cold emission process by using supercritical carbon dioxide as working medium and computer program product Download PDF

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CN112861316B
CN112861316B CN202110031081.1A CN202110031081A CN112861316B CN 112861316 B CN112861316 B CN 112861316B CN 202110031081 A CN202110031081 A CN 202110031081A CN 112861316 B CN112861316 B CN 112861316B
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carbon dioxide
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文键
李超龙
王超
王合久
秦会国
何春涛
杨向东
王斯民
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Beijing Machinery Equipment Research Institute
Xian Jiaotong University
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Xian Jiaotong University
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    • G06—COMPUTING; CALCULATING OR COUNTING
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    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
    • G—PHYSICS
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    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
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    • G06F2119/08—Thermal analysis or thermal optimisation
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
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Abstract

The invention provides a method and a computer program product for characterizing a cold emission process using supercritical carbon dioxide as a working medium. The method comprises the following steps: 1) Acquiring structural parameters, initial state parameters and preset working parameters of a cold emission system; 2) Calculating the rapid pressurization process of the high-pressure chamber; 3) Calculating the dynamic change process of the carbon dioxide state in the high-pressure chamber after the valve is opened; 4) And calculating the dynamic change process of the carbon dioxide state in the variable-volume low-pressure chamber and the motion variable of the aircraft until whether the displacement X or the speed v of the aircraft meets the preset emission requirement. By utilizing the method and the device, the dynamic change characteristic of the carbon dioxide state in the high-pressure chamber and the low-pressure chamber in the cold emission process and the incidence relation between the change characteristic and the aircraft motion can be quickly obtained, theoretical guidance is provided for the design and research and development of a cold emission system taking supercritical carbon dioxide as a working medium, and the cost and the period of the system research and development design are reduced.

Description

Method for characterizing cold emission process by using supercritical carbon dioxide as working medium and computer program product
Technical Field
The invention relates to the field of cold emission, in particular to a method for characterizing a cold emission process by using carbon dioxide as a working medium.
Background
The mode of launching missiles or launch vehicles without relying on their own engines is called cold launching. Steam ejection and gas steam ejection are common at present, but the ejection modes have some limitations, mainly:
1) A steam storage tank with a larger volume is required to be arranged, and the bomb carrying capacity space is compressed;
2) The ejection load is small, and when the ejection load reaches a certain degree and the load is continuously increased, the steam consumption and the energy are rapidly increased;
3) The ejection capability adjusting system is complex, and the reliability of the system is reduced. In view of this, various countries have continuously studied other ejection methods.
Compared with the traditional ejection working medium, the carbon dioxide has the advantages of low critical pressure, normal critical temperature, large internal energy per unit mass and the like, and is a potential high-quality ejection working medium. However, the dynamic change characteristics of the carbon dioxide in the high-pressure chamber and the low-pressure chamber during the ejection process and the relevant connection between the carbon dioxide and missile movement are still lack of understanding at present by taking the carbon dioxide as an ejection working medium.
The technical information described above is intended to facilitate a quick understanding of the objects and concepts of the present invention, and may contain information that does not form the prior art that is well known to those skilled in the art.
Disclosure of Invention
The main purposes of the invention are as follows: the method is used for calculating the dynamic change characteristic of the thermal state of carbon dioxide in a high-pressure chamber and a low-pressure chamber in the ejection process by taking the carbon dioxide as a cold emission working medium and the related quantitative relation between the change characteristic and the motion of an aircraft, so that the cold emission process is simplified and visually represented.
In order to achieve the above purpose, the invention provides the following scheme:
a method for characterizing a cold emission process using supercritical carbon dioxide as a working medium comprises the following steps:
1) Acquiring parameters:
acquiring structural parameters, initial state parameters and preset working parameters of a cold emission system; the initial state parameters comprise temperature T0 and pressure P0 in the initial carbon dioxide filling state in the high-pressure chamber of the cold emission system, and the preset working parameters comprise heating power W in the high-pressure chamber of the cold emission system, total heat Q ready to be input into the high-pressure chamber and valve set opening pressure P val ；
2) Calculating a rapid pressurization process of a high pressure chamber
Calculating the density rho 0 and the mass m0 of the filled carbon dioxide according to the pressure P0 and the temperature T0 of the carbon dioxide obtained in the step 1), and calculating the change of the specific internal energy u in the heating process by using the formula (1):
Figure GDA0003789498250000021
calculating the pressure P1 and the temperature T1 in the heated high-pressure chamber according to the density rho 0 and the specific internal energy u, and when the pressure P1 reaches the set opening pressure P of the valve val Stopping calculation;
3) Calculating dynamic change process of carbon dioxide state in high-pressure chamber after valve is opened
The pressure in the high-pressure chamber reaches the set opening pressure P of the valve val When the carbon dioxide enters the low-pressure chamber, the control valve is opened, and the high-pressure carbon dioxide flows to the low-pressure chamber; high pressure indoor satisfaction formula (2)
Figure GDA0003789498250000022
Low pressure indoor satisfaction formula (3)
Figure GDA0003789498250000023
Wherein t is time, W is high-pressure indoor heating power, U 1 、U 2 Is the thermodynamic energy of the high-pressure and low-pressure chambers, h out 、h in The enthalpy of the carbon dioxide flowing out of the high pressure chamber and into the low pressure chamber respectively,
Figure GDA0003789498250000024
is the flow of carbon dioxide out of the high pressure chamber and into the low pressure chamber; wherein
Figure GDA0003789498250000025
In the formula, m 1 、m 2 The mass of carbon dioxide in the high-pressure chamber and the low-pressure chamber, respectively, and further has h out ＝h in (ii) a Will be provided with
Figure GDA0003789498250000026
Figure GDA0003789498250000027
Are all abbreviated as
Figure GDA0003789498250000028
Then:
when the internal pressure ratio P3/P2 of the high-low pressure chamber does not exceed the critical value, calculating according to the formula (5)
Figure GDA0003789498250000029
Figure GDA00037894982500000210
When the internal pressure ratio P3/P2 of the high-low pressure chamber is higher than the critical value, the calculation is carried out by using the formula (6)
Figure GDA0003789498250000031
Figure GDA0003789498250000032
Wherein A1 is the cross-sectional area of the launch canister, C q Is the flow coefficient associated with the valve structure, and P3, P2 are the absolute pressures, ρ, in the high and low pressure chambers, respectively 1 Is the density of carbon dioxide in the high pressure chamber as it flows from the high pressure chamber into the low pressure chamber, and κ is the carbon dioxide adiabatic index;
calculating the specific internal energy u1 of carbon dioxide in the high-pressure chamber after the carbon dioxide flows into the low-pressure chamber from the high-pressure chamber and calculating the density rho 3 of the carbon dioxide in the high-pressure chamber after the carbon dioxide flows into the low-pressure chamber from the high-pressure chamber according to the formula (7);
Figure GDA0003789498250000033
further calculating the pressure P5 and the temperature T5 in the high-pressure chamber after the carbon dioxide flows into the low-pressure chamber from the high-pressure chamber according to the density rho 3 and the specific internal energy u 1;
4) Calculating dynamic change process of carbon dioxide state in variable-volume low-pressure chamber and aircraft motion variable
When the pressure in the low-pressure chamber is not enough to push the aircraft to move, calculating internal energy u2 in the low-pressure chamber and density rho 2 of carbon dioxide in the low-pressure chamber after the carbon dioxide flows into the low-pressure chamber from the high-pressure chamber by referring to equations (3) to (6), and further calculating to obtain pressure P6 and temperature T6 in the low-pressure chamber after the carbon dioxide flows into the low-pressure chamber from the high-pressure chamber;
when the pressure in the low-pressure chamber is enough to push the aircraft to move, the carbon dioxide in the low-pressure chamber expands, and the internal energy of the carbon dioxide in the low-pressure chamber is calculated according to the formula (8)
Figure GDA0003789498250000034
Aircraft motion is calculated by equation (9)
Figure GDA0003789498250000035
In formula (II) u' 2 To expand the internal energy of the low-pressure chamber, p 0 Is atmospheric pressure, G is aircraft gravity, F is the friction experienced by the aircraft, X is aircraft displacement, Δ E k Is the kinetic energy variation of the aircraft; m is the aircraft mass;
internal energy u 'in the expanded low-pressure chamber obtained by calculation' 2 Calculating the carbon dioxide density ρ 'in the low pressure chamber after expansion in combination with the aircraft displacement X of the expansion process' 2 Further calculating to obtain the pressure P4 and the temperature T4 in the variable-volume low-pressure chamber in the expansion process;
5) And (3) judging whether the displacement X or the speed v of the aircraft meets a preset launching requirement, and if not, continuing to calculate according to the steps 2) to 4).
Optionally, the structural parameters of the cold launching system in step 1) include a high-pressure chamber volume V1, a low-pressure chamber initial volume V2, a launching tube cross-sectional area A1, a launching tube stroke length L, a launching tube inclination angle θ, an aircraft mass M, and a valve area A2.
Optionally, the initial state parameters are acquired in step 1), specifically at the work site using a temperature sensor and a pressure sensor or in advance according to a pre-configured charging system.
Optionally, in step 3), the carbon dioxide adiabatic exponent κ takes a value of 1.3.
Optionally, in step 3), calculating according to equation (5) and equation (6), respectively
Figure GDA0003789498250000041
And taking the smaller one as a calculation result.
Correspondingly, the invention also provides computer equipment which comprises a processor and a memory, wherein the memory stores a plurality of programs, and the computer equipment is characterized in that the programs are loaded and run by the processor to realize the method for characterizing the cold emission process by using the supercritical carbon dioxide as a working medium.
Correspondingly, the invention also provides a computer-readable storage medium, which stores a plurality of programs, and is characterized in that the programs are loaded and run by a processor to realize the method for characterizing the cold emission process by using the supercritical carbon dioxide as the working medium.
The invention has the beneficial effects that:
by utilizing the method and the device, the dynamic change characteristic of the carbon dioxide state in the high-pressure and low-pressure chambers in the cold emission process and the incidence relation between the change characteristic and the aircraft motion can be quickly obtained, theoretical guidance is provided for the design and research and development of a cold emission system taking supercritical carbon dioxide as a working medium, and the cost and the period of the system research and development design are reduced.
Drawings
Fig. 1 is a simplified schematic diagram of a cold emission system.
FIG. 2 is a flow chart of one embodiment of the present invention.
FIG. 3 shows the calculated pressure results in the high and low pressure chambers according to one embodiment of the present invention.
Fig. 4 shows the calculated temperature results in the high and low pressure chambers according to an embodiment of the present invention.
FIG. 5 shows the results of acceleration, velocity, and displacement of an aircraft calculated according to an embodiment of the present invention.
The reference numbers are as follows:
wherein: 1. a high pressure chamber; 2. a valve; 3. a low pressure chamber; 4. a tray; 5. an aircraft; 6. launch the section of thick bamboo.
Detailed Description
The present invention will be described in further detail by way of examples with reference to the accompanying drawings.
As shown in fig. 1, a cold launching system with carbon dioxide as a launching medium. The low pressure chamber is filled with supercooled carbon dioxide liquid with the pressure of 3MPa and the temperature of 263.15K (-10 ℃) at the beginning, and the volume of the high pressure chamber is 0.002m 3 Initial volume of the low pressure chamber of 0.4m 3 Diameter of launch canister 0.3m, aircraft delivery stroke 6m, valve diameter 0.005m, valve opening pressure120MPa, 8000kW of heating power of the high-pressure chamber and 0.1s of heating time. The launch canister is vertical. The friction is 0.3 times of the gravity, and the mass of the aircraft is 600kg.
1) Acquiring parameters:
obtaining the volume of the high-pressure chamber to be 0.002m at the working site or in advance 3 Initial volume of the low pressure chamber of 0.4m 3 Emission tube cross-sectional area 7.0686 × 10 -4 m 2 The stroke length of the launching tube is 6m, the inclination angle of the launching tube is 90 degrees, the mass of the aircraft is 600kg, and the valve area is 1.963 multiplied by 10 -4 m 2 . A temperature sensor and a pressure sensor are utilized on a working site or a temperature 263.15K and a pressure 6MPa in the initial carbon dioxide filling state in the high-pressure chamber are obtained in advance according to a filling system. The power of the high-pressure chamber heating equipment is 800kW at a working site or obtained in advance, the total heat input into the high-pressure chamber is prepared to be 800kJ, and the valve is set to have the opening pressure of 120MPa.
2) Calculating a rapid pressurization process of a high pressure chamber
Calculating the density rho 0 and the mass m0 of the filled carbon dioxide by using the carbon dioxide pressure of 3MPa and the temperature 263.15K obtained in the step one, and calculating the change of the specific internal energy u in the heating process by using the formula (1):
Figure GDA0003789498250000051
the heated pressure P1 and temperature T1 are calculated from the density ρ 0 and the specific internal energy u, and the calculation is stopped when P1 reaches the valve-opening set pressure of 120MPa, as indicated by a reference point 1 in fig. 3.
3) Calculating dynamic change process of carbon dioxide state in high-pressure chamber after valve is opened
When the pressure in the high-pressure chamber reaches the valve opening pressure of 120MPa (indicated by a mark point 1 in figure 3), the valve opens the high-pressure carbon dioxide to flow to the low-pressure chamber. High pressure indoor use type (2)
Figure GDA0003789498250000052
Low-pressure indoor use type (3)
Figure GDA0003789498250000053
Wherein t is time, W is high-pressure indoor heating power, U 1 、U 2 Is the thermodynamic energy of the high-pressure and low-pressure chambers, h out 、h in The enthalpy of the carbon dioxide flowing out of the high pressure chamber and into the low pressure chamber respectively,
Figure GDA0003789498250000061
is the flow of carbon dioxide out of the high pressure chamber and into the low pressure chamber. Wherein
Figure GDA0003789498250000062
In the formula, m 1 、m 2 The mass of carbon dioxide in the high-pressure chamber and the low-pressure chamber, respectively, and further has h out ＝h in 。
Figure GDA0003789498250000063
Calculation using equation (5)
Figure GDA0003789498250000064
When the internal pressure ratio P3/P2 of the high-low pressure chamber is higher than a critical value,
Figure GDA0003789498250000065
calculation using equation (6)
Figure GDA0003789498250000066
In the formula, C q Is the flow coefficient related to the valve structure, in this example 0.61, P3, P2 are the absolute pressures in the high and low pressure chambers, rho 1 Is the density of carbon dioxide in the high-pressure chamber when it flows from the high-pressure chamber into the low-pressure chamber, and κ is the carbon dioxide adiabatic index, and may have a value of 1.3. In use mode(5) And equation (6) separately
Figure GDA0003789498250000068
And comparing and taking the smaller as a calculated value. Accordingly, the specific internal energy u1 of carbon dioxide in the high-pressure chamber after carbon dioxide flows from the high-pressure chamber into the low-pressure chamber and the density ρ 3 of carbon dioxide in the high-pressure chamber after carbon dioxide flows from the high-pressure chamber into the low-pressure chamber can be calculated by using the formula (7).
Figure GDA0003789498250000067
Further, the pressure P5 and the temperature T5 in the high-pressure chamber after the carbon dioxide flows from the high-pressure chamber into the low-pressure chamber can be calculated from the density ρ 3 and the specific internal energy u 1. The calculation results are shown in fig. 3 and 4.
4) Missile motion in dynamic change process for calculating carbon dioxide state in variable-volume low-pressure chamber
Along with the pressure in the flowing low-pressure chamber of carbon dioxide rises gradually, when the pressure in the low-pressure chamber is not enough to push the guided missile to move, similarly, formula (3) to formula (6) are used for calculating internal energy u2 in the low-pressure chamber and carbon dioxide density rho 2 in the low-pressure chamber after the carbon dioxide flows into the low-pressure chamber from the high-pressure chamber, and then the pressure P5 and the temperature T5 in the low-pressure chamber after the carbon dioxide flows into the low-pressure chamber from the high-pressure chamber can be calculated by the density rho 2 and the internal energy u 2.
When the pressure in the low-pressure chamber is enough to push the aircraft to move, the carbon dioxide in the low-pressure chamber expands, and the expansion work of the carbon dioxide is used for overcoming the gravity, the friction resistance and the atmospheric pressure of the aircraft to do work and increasing the kinetic energy of the aircraft. At this time, the internal energy of carbon dioxide in the low-pressure chamber is calculated by using the formula (8)
Figure GDA0003789498250000071
Aircraft motion can be calculated from equation (9)
Figure GDA0003789498250000072
In formula (II) u' 2 To expand the internal energy of the low-pressure chamber, p 0 Is atmospheric pressure, G is the aircraft weight, F is the friction experienced by the aircraft, X is the aircraft displacement, Δ E k Is the amount of kinetic energy variation of the aircraft.
Internal energy u 'in the expanded low-pressure chamber obtained by calculation' 2 Calculating the density rho 'of carbon dioxide in the expanded low-pressure chamber in combination with the displacement X of the expansion process' 2 Then the pressure P4 and temperature T4 of the carbon dioxide in the variable volume low pressure chamber during expansion can be calculated. The calculation results are shown in fig. 3 and 4.
5) And (3) judging whether the displacement X or the speed v of the aircraft meets a preset launching requirement, if not, continuing to calculate the motion of the aircraft according to the steps 2) to 4), wherein the calculation result is shown in fig. 5.
The embodiment allows the dynamic change characteristics of the carbon dioxide in the rapid pressurization process and the carbon dioxide state in the high-low pressure chamber in the ejection process to be calculated in a simplified mode with less storage space and calculation capacity, and particularly the correlation between the emission parameters input in the calculation and the motion of the aircraft can be conveniently seen.

Claims (7)

1. A method for characterizing a cold emission process using supercritical carbon dioxide as a working medium is characterized by comprising the following steps:
1) Acquiring parameters:
acquiring structural parameters, initial state parameters and preset working parameters of a cold emission system; the initial state parameters comprise temperature T0 and pressure P0 in the initial carbon dioxide filling state in the high-pressure chamber of the cold emission system, and the preset working parameters comprise heating power W in the high-pressure chamber of the cold emission system, total heat Q ready to be input into the high-pressure chamber and valve set opening pressure P val ；
2) Calculating a rapid pressurization process of a high pressure chamber
Calculating the density rho 0 and the mass m0 of the filled carbon dioxide according to the pressure P0 and the temperature T0 of the carbon dioxide obtained in the step 1), and calculating the change of the specific internal energy u in the heating process by using the formula (1):
Figure FDA0003789498240000011
calculating the pressure P1 and the temperature T1 in the heated high-pressure chamber according to the density rho 0 and the specific internal energy u, and when the pressure P1 reaches the set opening pressure P of the valve val Stopping calculation;
3) Calculating dynamic change process of carbon dioxide state in high-pressure chamber after valve is opened
The pressure in the high-pressure chamber reaches the set opening pressure P of the valve val When the carbon dioxide generator is started, the control valve is opened, and the high-pressure carbon dioxide flows to the low-pressure chamber; high pressure indoor satisfaction formula (2)
Figure FDA0003789498240000012
Low pressure indoor satisfaction formula (3)
Figure FDA0003789498240000013
Wherein t is time, W is high-pressure indoor heating power, U 1 、U 2 Is the thermodynamic energy of the high-pressure and low-pressure chambers, h out 、h in The enthalpy of the carbon dioxide flowing out of the high pressure chamber and into the low pressure chamber respectively,
Figure FDA0003789498240000014
is the flow of carbon dioxide out of the high pressure chamber and into the low pressure chamber; wherein
Figure FDA0003789498240000015
In the formula, m 1 、m 2 The carbon dioxide mass in the high-pressure chamber and the low-pressure chamber respectively, and then h out ＝h in (ii) a Will be provided with
Figure FDA0003789498240000016
Figure FDA0003789498240000021
Are all abbreviated as
Figure FDA0003789498240000022
Then:
when the internal pressure ratio P3/P2 of the high-low pressure chamber does not exceed the critical value, calculating according to the formula (5)
Figure FDA0003789498240000023
Figure FDA0003789498240000024
When the internal pressure ratio P3/P2 of the high-low pressure chamber is higher than the critical value, the calculation is carried out by using the formula (6)
Figure FDA0003789498240000025
Figure FDA0003789498240000026
Wherein A1 is the cross-sectional area of the launch canister, C q Is the flow coefficient associated with the valve structure, and P3, P2 are the absolute pressures, ρ, in the high and low pressure chambers, respectively 1 Is the density of carbon dioxide in the high pressure chamber as it flows from the high pressure chamber into the low pressure chamber, and κ is the carbon dioxide adiabatic index;
calculating the carbon dioxide specific internal energy u1 in the high-pressure chamber after the carbon dioxide flows into the low-pressure chamber from the high-pressure chamber and calculating the carbon dioxide density rho 3 in the high-pressure chamber after the carbon dioxide flows into the low-pressure chamber from the high-pressure chamber according to the formula (7);
Figure FDA0003789498240000027
further calculating the pressure P5 and the temperature T5 in the high-pressure chamber after the carbon dioxide flows into the low-pressure chamber from the high-pressure chamber according to the density rho 3 and the specific internal energy u 1;
4) Calculating dynamic change process of carbon dioxide state in variable-volume low-pressure chamber and aircraft motion variable
When the pressure in the low-pressure chamber is not enough to push the aircraft to move, calculating internal energy u2 in the low-pressure chamber and density rho 2 of carbon dioxide in the low-pressure chamber after the carbon dioxide flows into the low-pressure chamber from the high-pressure chamber by referring to equations (3) to (6), and further calculating to obtain pressure P6 and temperature T6 in the low-pressure chamber after the carbon dioxide flows into the low-pressure chamber from the high-pressure chamber;
when the pressure in the low-pressure chamber is enough to push the aircraft to move, the carbon dioxide in the low-pressure chamber expands, and the internal energy of the carbon dioxide in the low-pressure chamber is calculated according to the formula (8)
Figure FDA0003789498240000028
Aircraft motion is calculated by equation (9)
Figure FDA0003789498240000029
U 'in the formula' 2 To expand the internal energy of the low-pressure chamber, p 0 Is atmospheric pressure, G is aircraft gravity, F is the friction experienced by the aircraft, X is aircraft displacement, Δ E k Is the kinetic energy variation of the aircraft; m is the aircraft mass;
internal energy u 'in the expanded low-pressure chamber obtained by calculation' 2 Calculating the carbon dioxide density ρ 'in the low pressure chamber after expansion in combination with the aircraft displacement X of the expansion process' 2 Further calculating to obtain the pressure P4 and the temperature T4 in the variable-volume low-pressure chamber in the expansion process;
5) And (3) judging whether the displacement X or the speed v of the aircraft meets a preset launching requirement, and if not, continuing to calculate according to the steps 2) to 4).
2. The method for characterizing the cold emission process using supercritical carbon dioxide as the working medium according to claim 1, wherein the structural parameters of the cold emission system in step 1) comprise a high-pressure chamber volume V1, a low-pressure chamber initial volume V2, an emission tube cross-sectional area A1, an emission tube stroke length L, an emission tube inclination angle θ, an aircraft mass M and a valve area A2.
3. The method for characterizing the cold emission process using supercritical carbon dioxide as the working medium according to claim 1, wherein the initial state parameters are obtained in step 1), particularly at the working site by using a temperature sensor and a pressure sensor or in advance according to a pre-configured charging system.
4. The method for characterizing the cold emission process by using the supercritical carbon dioxide as the working medium according to claim 1, wherein the carbon dioxide adiabatic exponent k in the step 3) is 1.3.
5. The method for characterizing the cold emission process using supercritical carbon dioxide as the working medium according to claim 1, wherein in step 3), the calculation is performed according to the formula (5) and the formula (6)
Figure FDA0003789498240000031
The smaller one is taken as the calculation result.
6. A computer device comprising a processor and a memory, said memory storing programs, wherein said programs when loaded and executed by the processor implement the method of claim 1 for characterizing a cold emission process using supercritical carbon dioxide as a working medium.
7. A computer-readable storage medium, in which a plurality of programs are stored, which, when being loaded and executed by a processor, implement the method for characterizing a cold emission process using supercritical carbon dioxide as a working medium according to claim 1.
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