CN113255072A - Method for rapidly calculating heat transfer process of solid rocket engine cladding sleeve structure - Google Patents
Method for rapidly calculating heat transfer process of solid rocket engine cladding sleeve structure Download PDFInfo
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- 238000012546 transfer Methods 0.000 title claims abstract description 138
- 238000000034 method Methods 0.000 title claims abstract description 81
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Abstract
The invention discloses a method for quickly calculating a heat transfer process of a solid rocket engine coating sleeve structure, which comprises the following steps: the method comprises an input stage, a calculation and calculation process prompting stage, a calculation result display stage and a calculation data storage stage. And the input stage is used for inputting geometric parameters, physical parameters, initial boundary value conditions, heat transfer time and unit geometric parameter reference values of all layers of the cladding sleeve structure. And the calculation and calculation process prompt stage is used for calculating the heat transfer process according to the numerical values and conditions of the input stage and displaying the prompt of the calculation completion condition according to the actual calculation completion degree. And the calculation result display stage is used for displaying the calculated data cloud picture and the calculated data curve after the heat transfer is finished. And the calculation data storage stage is used for storing calculation result data. The method has the advantages of convenient use, simple operation, short calculation time, intuitive calculation result, low cost and high benefit.
Description
Technical Field
The invention relates to a method for quickly calculating a heat transfer process of a solid rocket engine cladding sleeve structure, and belongs to the technical field of solid rocket engines.
Background
The coating sleeve structure is positioned between the solid rocket engine shell and the explosive column, is an important structural component of the solid rocket engine, and plays an important role in structural integrity, working reliability and safety of the solid rocket engine. Firstly, for the adherence pouring type of the powder column, the coating sleeve has the function of firmly bonding the shell and the powder column. And secondly, the coating sleeve can play a role in stress buffering, and the adverse effect of loads such as external impact on the performance of the explosive column is reduced in the processes of loading, unloading, transportation, storage and the like of an engine. Finally, the coating sleeve plays a role in inhibiting combustion and protecting the shell and the explosive columns, the coating sleeve can reduce the heating capacity of the shell to ensure that the shell has enough rigidity and is not burnt through when the explosive columns are poured against the wall, and the coating sleeve can inhibit the heat transfer from high-temperature gas in gaps between the shell and the explosive columns to the explosive columns after ignition and prevent accidents such as inner ballistic performance change, fire leaping, detonation and the like caused by advanced thermal decomposition or combustion of the explosive columns on the side surfaces when the explosive columns are freely loaded.
For engine charging of the freely-filled explosive column, a gap is formed between the explosive column coating sleeve and the shell, high-temperature gas enters the gap after ignition, and a temperature difference is formed between the gap gas layer and the coating sleeve as well as the explosive column, so that the gas layer transfers heat to the coating sleeve and the explosive column, and if the thickness of the coating sleeve is insufficient, the explosive column is heated too high, so that the safety problem is caused, and the engine cannot work normally and reliably. The thickness design of the sheathing is therefore critical to safe and reliable operation of the engine. The calculation of the heat transfer process of the structure of the wrapping sleeve is the basis of the thickness design of the wrapping sleeve, and currently, for a design or simulation person, the heat transfer calculation of the wrapping sleeve generally needs to use mature commercial software, such as Fluent software, and the calculation accuracy is high. However, at the same time, the use of this software has at least the following inconveniences: (1) the software requires a user to have a certain basis and experience, and non-fluid or heat transfer professional design or simulation personnel need to spend a certain amount of time and energy to learn and master the use of the software; (2) the software needs complicated processes such as geometric model drawing, manual unit division, boundary condition setting, result post-processing and the like, and is not beneficial to simplifying the process; (3) the software is strong in universality, time is consumed for calculation, and calculation time is not saved for specific problems; (4) the method is not easy to be integrated into a solid rocket engine design simulation integrated platform. Therefore, the software is difficult to meet the urgent requirements of rapid design, optimization and simulation analysis of the solid rocket engine cladding sleeve structure.
Disclosure of Invention
The technical problem solved by the invention is as follows: the method for rapidly calculating the heat transfer process of the solid rocket engine cladding sleeve structure is convenient to use, simple to operate, short in calculation time, intuitive in calculation result, low in cost and high in benefit.
The technical scheme of the invention is as follows: a method for rapidly calculating a heat transfer process of a solid rocket engine cladding sleeve structure is characterized by comprising the following steps: an input stage, a calculation and calculation process prompting stage, a calculation result display stage and a calculation data storage stage;
the coating sleeve structure of the solid rocket engine is a four-layer structure and comprises a drug column layer, a coating sleeve layer, a fuel gas layer and a combustion chamber shell layer from inside to outside; each layer is hollow cylindrical; in the calculation process, each layer of the cladding sleeve structure is radially divided into a plurality of units, and any unit only belongs to one layer of the four-layer structure;
the input stage is as follows:
(1) inputting the geometric parameters, physical parameters and initial boundary value conditions of a combustion chamber shell layer, a fuel gas layer, a coating sleeve layer and a drug column layer in a coating sleeve structure; setting heat transfer time and setting a geometric parameter reference value of a unit;
and a calculation and calculation process prompt stage, which is specifically as follows:
(2) determining the unit number and unit radial thickness of each layer in the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the drug column layer according to the geometric parameters of the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the drug column layer determined in the step (1) and the set geometric parameter reference values of the units;
(3) determining the physical parameters, inner and outer surface radial coordinates, initial temperature and heat flux density of each unit in the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the explosive column layer according to the geometric parameters, the physical parameters and the initial boundary value conditions of the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the explosive column layer determined in the step (1) and the unit number and the unit radial thickness of each layer in the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the explosive column layer determined in the step (2);
(4) determining the heat transfer time step length and the total number M of the heat transfer time step length of the cladding sleeve structure according to the physical parameters and the radial coordinates of the inner surface and the outer surface of each unit in the combustion chamber shell layer, the fuel gas layer, the cladding sleeve layer and the drug column layer determined in the step (3);
(5) determining the temperature variation of each unit in the 1 st heat transfer time step of the coating structure according to the physical parameters, the radial coordinates of the inner surface and the outer surface, the initial temperature and the heat flux density of each unit in the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the explosive column layer determined in the step (3-4);
(6) recording the serial number of the current heat transfer time step as j (j is 1, 2, …, M), making j be 1, adding the temperature variation of each unit in the 1 st heat transfer time step of the cladding sleeve structure determined in the step (5) to the initial temperature of each unit determined in the step (3) to be used as the temperature of each unit corresponding to the jth heat transfer time step of the cladding sleeve structure;
(7) judging whether j is equal to the total number M of the heat transfer time step; if not, calculating the temperature variation of each unit in the j +1 th heat transfer time step of the coating sleeve structure according to the physical parameters, the radial coordinates of the inner and outer surfaces, the temperature and the heat flow density corresponding to the j heat transfer time step of the combustion chamber shell layer, the gas layer, the coating sleeve layer and the drug column layer, and adding the temperature variation to each unit corresponding to the j +1 th heat transfer time step of the coating sleeve structure to obtain the temperature of each unit corresponding to the j +1 th heat transfer time step of the coating sleeve structure; determining the calculation completion degree W according to the heat transfer time step sequence number j +1 and the total number M of the heat transfer time steps, and making j equal to j + 1; if so, stopping calculating to obtain the temperature of each unit of the cladding sleeve structure after the heat transfer time is over;
and a calculation result display stage, which is specifically as follows:
(8) displaying a temperature chart of each unit of the cladding sleeve structure after the heat transfer time is over;
the calculation data storage stage specifically comprises the following steps:
(9) and storing the temperature data of each unit of the cladding sleeve structure after the heat transfer time is over.
Further, the method for rapidly calculating the heat transfer process of the solid rocket engine cladding sleeve structure is characterized by comprising the following steps: the geometric dimension on combustion chamber shell layer, gas layer, cladding jacket layer, explosive column layer includes: the radial thickness of the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the explosive column layer and the radial coordinate of the inner side of the explosive column.
Further, the method for rapidly calculating the heat transfer process of the solid rocket engine cladding sleeve structure is characterized by comprising the following steps: the initial boundary value condition of combustion chamber shell layer, gas layer, cladding jacket layer, explosive column layer includes: initial temperature and heat flux density of the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the explosive column layer.
Further, the method for rapidly calculating the heat transfer process of the solid rocket engine cladding sleeve structure is characterized by comprising the following steps: physical property parameters including: the density, the heat conductivity coefficient and the constant pressure specific heat capacity of the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the explosive column layer.
Further, the method for rapidly calculating the heat transfer process of the solid rocket engine cladding sleeve structure is characterized by comprising the following steps: the length of heat transfer is: the total time required for heat transfer of the clad sleeve structure.
Further, the method for rapidly calculating the heat transfer process of the solid rocket engine cladding sleeve structure is characterized by comprising the following steps: the geometric parameter reference value of the unit refers to: a reference value for the radial thickness of the cell.
Compared with the prior art, the invention has the advantages that:
(1) the invention has convenient use and simple operation. Compared with commercial software Fluent, the method does not need operations such as geometric model drawing, manual division of units, result post-processing and the like, the calculation result is displayed visually, and the learning threshold is low;
(2) the invention has short calculation time and accurate and reliable result. Compared with commercial software Fluent, the calculation time is obviously reduced under the conditions of the same structure and the same initial value and the same unit size and time step length, and the calculation accuracy is equivalent;
(3) the invention has low cost and high benefit. Expensive commercial software does not need to be purchased, the integrated platform is convenient to integrate into a solid rocket engine design and simulation integrated platform, the intellectual property of self-developed software is possessed, the use is quick and convenient, the coating sleeve structure is favorable for quick design, simulation and optimization, the research and development period is shortened, the research and development cost is reduced, and the rapid propulsion of the aerospace army task is assisted.
Drawings
FIG. 1 is a schematic axial cross-sectional view of a solid rocket motor jacket structure.
FIG. 2 is a schematic cross-sectional view of radial units of a cladding sleeve structure of a solid rocket engine.
Detailed Description
The invention is described in further detail below with reference to the figures and specific embodiments.
The invention discloses a method for quickly calculating a heat transfer process of a coating sleeve structure of a solid rocket engine, which is used for establishing a method for quickly calculating the heat transfer process of the coating sleeve structure in a mode of freely filling grains in the solid rocket engine according to a basic principle of heat transfer science. The calculation method comprises the following steps: the method comprises an input stage, a calculation and calculation process prompting stage, a calculation result display stage and a calculation data storage stage. And the input stage is used for inputting geometric parameters, physical parameters, initial boundary value conditions, heat transfer time and unit geometric parameter reference values of all layers of the cladding sleeve structure. And the calculation and calculation process prompt stage is used for calculating the heat transfer process according to the numerical values and conditions of the input stage and displaying the prompt of the calculation completion condition according to the actual calculation completion degree. And the calculation result display stage is used for displaying the calculated data cloud picture and the calculated data curve after the heat transfer is finished. And the calculation data storage stage is used for storing calculation result data. The method has the advantages of convenient use, simple operation, short calculation time, intuitive calculation result, low cost and high benefit.
In the design stage of the coating sleeve structure scheme, when a scheme needs to be compared or optimized quickly, or when a solid rocket engine fails and a numerical simulation support fault recurrence test needs to be carried out on a possible coating sleeve structure quickly, the use of commercial software such as Fluent and the like usually consumes a long time and is not beneficial to ensuring the timely completion of tasks such as scheme design or fault recurrence and the like, so that the processing and calculating time can be greatly saved by adopting the quick calculation method disclosed by the invention, and the tasks can be completed quickly.
A method for rapidly calculating a heat transfer process of a solid rocket engine cladding sleeve structure is characterized by comprising the following steps: an input stage, a calculation and calculation process prompting stage, a calculation result display stage and a calculation data storage stage;
the solid rocket engine coating sleeve structure is a four-layer structure, as shown in fig. 1, an axial section view (a cylindrical coordinate system, the radial direction is r, the annular direction is theta, and the axial direction is z) of the coating sleeve structure is respectively a drug column layer, a coating sleeve layer, a gas layer and a combustion chamber shell layer from inside to outside; each layer is hollow cylindrical, and materials of each layer have corresponding physical parameters such as density, constant pressure specific heat capacity, heat conductivity coefficient and the like and dimensional parameters such as radial thickness and the like; after the solid rocket engine is ignited, the initial temperature of the gas layer is high, the initial temperature of the combustion chamber shell layer, the coating sleeve layer and the explosive column layer is low, and the gas layer transfers heat to the coating sleeve layer, the explosive column layer and the combustion chamber shell layer. The heat source is not provided in the heat transfer process, the heat convection process is not considered, only the heat conduction process is considered, and the physical property parameter and the radial thickness parameter are not changed in the heat transfer process; fig. 2 is a schematic cross-sectional view of a radial unit of a cladding sleeve structure of a solid rocket engine. In the calculation process, according to the characteristics that the axial size of the cladding sleeve structure is large and the annular direction has symmetry, the temperature at any moment is assumed to be a function of a radial position coordinate, namely, the cladding sleeve structure is simplified into a one-dimensional heat transfer problem, units are divided in the radial direction, any representative unit is taken, a heat transfer control equation in a discrete format is obtained according to the fact that the heat quantity difference flowing into and out of the unit is equal to the heat quantity required by the temperature change of the unit, and then a heat transfer calculation program is compiled;
in the input stage, the preferred scheme is as follows:
(1) inputting the geometric parameters, physical parameters and initial boundary value conditions of a combustion chamber shell layer, a fuel gas layer, a coating sleeve layer and a drug column layer in a coating sleeve structure; setting heat transfer time and setting a geometric parameter reference value of a unit; the preferred scheme is as follows:
the radial thicknesses of the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the explosive column layer in the input coating sleeve structure are respectively marked as hkt、hrq、hbf、hyzAnd inputting the radial coordinate r of the inner surface of the grain layernc(ii) a Setting heat transfer time t, setting geometric parameter reference value of unit, namely unit radial thickness reference value h*；
Wherein,
hktis the radial thickness of the combustion chamber shell layer, m;
hrqis the radial thickness of the gas layer, m;
hbfis the radial thickness of the cladding jacket layer, m;
hyzthe radial thickness of the grain layer is m;
rncis the radial coordinate m of the inner surface of the grain layer;
t is the heat transfer time of the coating sleeve, s;
h*is a unit radial thickness reference, m;
and a calculation and calculation process prompt stage, which is specifically as follows:
(2) determining the unit number and unit radial thickness of each layer in the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the drug column layer according to the geometric parameters of the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the drug column layer determined in the step (1) and the set geometric parameter reference values of the units; the preferred scheme is as follows:
the number of units in each layer is equal to the quotient of the radial thickness of each layer divided by the reference value of the radial thickness of the unit, and then the quotient is rounded up, i.e. the
nkt＝Ceiling(hkt/h*) (1)
nrq＝Ceiling(hrq/h*) (2)
nbf＝Ceiling(hbf/h*) (3)
nyz＝Ceiling(hyz/h*) (4)
Wherein,
nktthe number of the combustion chamber shell layer units is shown;
nrqthe number of the gas layer units;
nbfthe number of the coating units is;
nyzthe number of the explosive column layer units is shown;
ceiling () represents a Ceiling operation;
and the total number of the units is n, then
n＝nkt+nrq+nbf+nyz (5)
After the number of units and the total number of units in each layer are determined, the actual radial thickness h of any unit i (i is 1, 2, …, n) is determined according to which layer the unit i (i is 1, 2, …, n) belongs toi，
If i is not less than 1 and not more than nyzThen h isi＝hyz/nyz (6)
If n isyz+1≤i≤nyz+nbfThen h isi＝hbf/nbf (7)
If n isyz+nbf+1≤i≤nyz+nbf+nrqThen h isi＝hrq/nrq (8)
If n isyz+nbf+nrqI is more than or equal to +1 and less than or equal to n, then hi＝hkt/nkt (9)
Wherein,
hiis the radial thickness of any unit i (i ═ 1, 2, …, n), m;
it should be noted that the above method determines the actual total number of cells and the radial thickness by using the reference value of the radial thickness of the cells, and also determines the actual total number of cells and the radial thickness by setting the number of cells in each layer, and for convenience of description, only the former is described here;
(3) determining the physical parameters, inner and outer surface radial coordinates, initial temperature and heat flux density of each unit in the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the explosive column layer according to the geometric parameters, the physical parameters and the initial boundary value conditions of the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the explosive column layer determined in the step (1) and the unit number and the unit radial thickness of each layer in the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the explosive column layer determined in the step (2); the preferred scheme is as follows:
recording the densities of the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the explosive column layer as rhokt、ρrq、ρbf、ρyzRespectively has a thermal conductivity of kkt、krq、kbf、kyzThe specific heat capacity at constant pressure is Cpkt、Cprq、Cpbf、CpyzInitial temperatures are respectively Tkt、Trq、Tbf、TyzRecording the density, the thermal conductivity, the constant pressure specific heat capacity and the initial temperature of the unit i as rhoi、ki、Cpi、Ti (0)Then, it is determined which layer the unit i (i ═ 1, 2, …, n) belongs to, and the density, thermal conductivity, constant pressure specific heat capacity, initial temperature, and the layer density, thermal conductivity, constant pressure specific heat capacity, and initial temperature are equal, that is, they are equal to each other
If i is not less than 1 and not more than nyzThen ρi＝ρyz，ki＝kyz，Cpi＝Cpyz，Ti (0)＝Tyz (10)
If n isyz+1≤i≤nyz+nbfThen ρi＝ρbf，ki＝kbf，Cpi＝Cpbf，Ti (0)＝Tbf (11)
If n isyz+nbf+1≤i≤nyz+nbf+nrqThen ρi＝ρrq，ki＝krq，Cpi＝Cprq，Ti (0)＝Trq (12)
If n isyz+nbf+nrqI is more than or equal to +1 and less than or equal to n, then rhoi＝ρkt，ki＝kkt，Cpi＝Cpkt，Ti (0)＝Tkt (13)
Wherein,
ρktis the density of the combustion chamber shell layer, kg/m3；
ρrqIs the density of a gas layer, kg/m3；
ρbfIn order to coat the jacket layer density, kg/m3；
ρyzIs the density of the grain layer in kg/m3；
kktThe thermal conductivity of the combustion chamber shell layer is W/(m.K);
krqthe thermal conductivity of the gas layer is W/(m.K);
kbfthe thermal conductivity of the coating layer is W/(m.K);
kyzthe thermal conductivity of the grain layer is W/(m.K);
Cpktthe constant pressure specific heat capacity of a shell layer of the combustion chamber is J/(kg.K);
Cprqthe constant pressure specific heat capacity of the fuel gas layer is J/(kg. K);
Cpbfthe specific heat capacity of the cladding layer at constant pressure is J/(kg. K);
Cpyzthe constant pressure specific heat capacity of the grain layer is J/(kg.K);
Tktis the initial temperature of the combustion chamber shell layer, K;
Trqinitial temperature of the gas layer, K;
Tbfinitial temperature for coating jacket layer, K;
Tyzinitial temperature of the grain layer, K;
ρiis the density of unit i (i ═ 1, 2, …, n), kg/m3；
kiIs the thermal conductivity of unit i (i ═ 1, 2, …, n), W/(m · K);
Cpiis the constant pressure specific heat capacity of the unit i (i is 1, 2, …, n), J/(kg · K);
Ti (0)is the initial temperature of unit i (i ═ 1, 2, …, n), K;
it should be noted that the density, thermal conductivity, and specific heat capacity at constant pressure can be functions of temperature, and are all processed as constants for convenience of description;
let the radial coordinates of the inner and outer surfaces of element i (i ═ 1, 2, …, n) be riAnd ri+1Because of the continuity of the units, the radial coordinates of the outer surface of the unit i (i ═ 1, 2, …, n-1) and the radial coordinates of the inner surface of the unit i +1(i ═ 1, 2, …, n-1) are the same and are both ri+1The calculation methods of the radial coordinates of the inner and outer surfaces of the unit i (i is 1, 2, …, n) are respectively
Wherein,
riis the unit i (i ═ 1, 2, …, n) inner surface radial coordinate, m;
ri+1is the unit i (i ═ 1, 2, …, n) outer surface radial coordinate, m;
hjis the radial thickness of cell j (the range of cell number j depends on the summation operation), m;
it should be noted that the deformation of the structure of the coating sleeve caused by the temperature change is not considered in the calculation process, so that the radial coordinates of the inner surface and the outer surface of each unit are kept unchanged in the calculation process;
let q be the internal and external surface heat flux density of unit i (i ═ 1, 2, …, n), respectivelyiAnd q isi+1Because the units are continuous, the heat flow density on the outer surface of the unit i (i is 1, 2, …, n-1) is the same as that on the inner surface of the unit i +1(i is 1, 2, …, n-1), and both are qi+1Note that the heat flux density of the inner and outer surfaces of the clad structure is qncAnd q iswcThe heat flux density of the inner surface of the innermost unit of the grain layer, namely the unit 1, is
q1＝qnc (16)
The outer surface heat flux density of the outermost unit of the combustion chamber shell layer, namely the unit n is
qn+1＝qwc (17)
In the formula (16-17), the metal oxide,
qncthe heat flux density of the inner surface of the cladding sleeve structure is W/m2；
qwcThe heat flux density of the outer surface of the cladding sleeve structure is W/m2；
q1Is the heat flux density of the inner surface of the cell 1, W/m2；
qn+1Is the heat flux density of the outer surface of the unit n, W/m2；
It should be noted that the heat flux density inside and outside the solid rocket engine cladding sleeve structure is constant, so the heat flux density on the inner surface of the unit 1 and the heat flux density on the outer surface of the unit n are both kept constant in the calculation process, the total number of heat transfer time steps is recorded as M, and the heat flux density on the inner surface of the unit 1 and the heat flux density on the outer surface of the unit n are respectively recorded as q (j is 1, 2, …, M) heat transfer time steps1 (j)And q isn+1 (j)Then, then
q1 (j)＝q1＝qnc (18)
qn+1 (j)＝qn+1＝qwc (19)
Wherein,
q1 (j)surface heat flux density, W/M, for the jth (j ═ 1, 2, …, M) heat transfer time step cell 12；
qn+1 (j)The heat transfer time step n is the j (j is 1, 2, …, M) th heat transfer time step unit n outer surface heat flow density, W/M2；
(4) Determining the heat transfer time step length and the total number M of the heat transfer time step length of the cladding sleeve structure according to the physical parameters and the radial coordinates of the inner surface and the outer surface of each unit in the combustion chamber shell layer, the fuel gas layer, the cladding sleeve layer and the drug column layer determined in the step (3); the preferred scheme is as follows:
the heat transfer time step is denoted as Δ t, since for any unit i (i ═ 1, 2, …, n), the stability condition should be met
Δtki/(ρiCpi(ri+1-ri)2)≤0.5 (20)
Therefore, the minimum heat transfer time step satisfying the equation (20) is taken as the reference heat transfer time step Δ t*I.e. by
Δt*＝Min(0.5ρ1Cp1(r2-r1)2/k1，0.5ρ2Cp2(r3-r2)2/k2，…，0.5ρnCpn(rn+1-rn)2/kn)
(21)
The total number of heat transfer time steps is M, then
M＝Ceiling(t/Δt*) (22)
Thus, the actual heat transfer time step Δ t is
Δt＝t/M (23)
In the formula (20-23), the metal oxide,
Δ t is the actual heat transfer time step, abbreviated as heat transfer time step, s;
Δt*to a reference heat transfer time step, s;
min () represents the minimum value;
m is the total number of heat transfer time steps;
(5) determining the temperature variation of each unit in the 1 st heat transfer time step of the coating structure according to the physical parameters, the radial coordinates of the inner surface and the outer surface, the initial temperature and the heat flux density of each unit in the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the explosive column layer determined in the step (3-4); the preferred scheme is as follows:
referring to fig. 2, which is a schematic cross-sectional view of radial units of a jacket structure (cylindrical coordinate system, radial is r, circumferential is θ, axial is z), without loss of generality, for any unit i (i is 1, 2, …, n), the difference between the heat flow rate flowing into the outer surface and the heat flow rate flowing out of the inner surface of the unit i within the 1 st heat transfer time step is recorded as Δ Φi (1)The areas of the inner and outer surfaces are respectively marked as AiAnd Ai+1If the axial length of each unit is l and the central angle subtended by the arcs on the inner and outer surfaces of each unit is alpha, then
ΔΦi (1)＝Ai+1qi+1 (1)-Aiqi (1)＝αl(ri+1qi+1 (1)-riqi (1)) (24)
The difference between the amount of heat flowing into the outer surface of the unit i (i ═ 1, 2, …, n) and the amount of heat flowing out of the inner surface of the unit i (i ═ 1, 2, …, n) in the 1 st heat transfer time step Δ t is denoted as Qi (1)Then, then
Qi (1)＝ΔΦi (1)Δt＝Δtαl(ri+1qi+1 (1)-riqi (1)) (25)
According to the principle that the heat flow density on the adjacent cell interface is continuous, the heat flow density on the inner surface of the cell i (i-2, 3, …, n) is obtained by Fourier's law as
q1 (1)And q isn+1 (1)See formula (16) and formula (17);
note that the temperature change of unit i (i ═ 1, 2, …, n) in the 1 st heat transfer time step is Δ Ti (1)Then its temperature changes by Δ Ti (1)The required amount of heat is
The difference between the heat flow flowing into the outer surface of the unit and the heat flow flowing out of the inner surface of the unit in unit time is equal to the heat required by the temperature change of the unit, so that the heat exchange unit can obtain the heat exchange unit
Qi (1)＝miCpiΔTi (1) (28)
The united type (25-28) can obtain
In the formula (24-29), the metal oxide,
ΔΦi (1)is the difference, W, between the heat flow into the outer surface of unit i (i 1, 2, …, n) and the heat flow out of the inner surface of unit i (i 1, 2, …, n) in the 1 st heat transfer time step;
Aiis the surface area of the inner surface of unit i (i ═ 1, 2, …, n), m2；
Ai+1Is the outer surface area of unit i (i ═ 1, 2, …, n), m2；
qi (1)Is the surface heat flow density of unit i (i ═ 1, 2, …, n) in the 1 st heat transfer time step, W/m2；
qi+1 (1)Is the heat flow density of the outer surface of the unit i (i is 1, 2, …, n) in the 1 st heat transfer time step, W/m2；
Alpha is the central angle, rad, subtended by the inner and outer surface arcs of each unit;
l is the axial length of each unit, m;
Qi (1)is the difference between the amount of heat flowing into the outer surface of unit i (i ═ 1, 2, …, n) and out of the inner surface of unit i (i ═ 1, 2, …, n), J, within the 1 st heat transfer time step Δ t;
Ti (0)is the initial temperature of unit i (i ═ 1, 2, …, n), K;
Ti-1 (0)is the initial temperature of unit i-1(i ═ 2, 3, …, n), K;
Ti+1 (0)is the initial temperature of unit i +1(i ═ 1, 2, …, n-1), K;
ΔTi (1)is the temperature variation, K, of unit i (i ═ 1, 2, …, n) in the 1 st heat transfer time step;
miunit i (i ═ 1, 2, …, n) mass, kg;
Viis the unit i (i ═ 1, 2, …, n) volume, m3；
(6) Recording the serial number of the current heat transfer time step as j (j is 1, 2, …, M), making j be 1, adding the temperature variation of each unit in the 1 st heat transfer time step of the cladding sleeve structure determined in the step (5) to the initial temperature of each unit determined in the step (3) to be used as the temperature of each unit corresponding to the jth heat transfer time step of the cladding sleeve structure; the preferred scheme is as follows:
let the current heat transfer time step number be j (j is 1, 2, …, M), let j be 1, and let the temperature of the unit i (i is 1, 2, …, n) in the jth heat transfer time step be Ti (j)At the current heat transfer time step, i.e. Ti (1)Then, then
Wherein,
Ti (1)is the temperature, K, of unit i (i ═ 1, 2, …, n) in the 1 st heat transfer time step;
(7) judging whether j is equal to the total number M of the heat transfer time step; if not, calculating the temperature variation of each unit in the j +1 th heat transfer time step of the coating sleeve structure according to the physical parameters, the radial coordinates of the inner and outer surfaces, the temperature and the heat flow density corresponding to the j heat transfer time step of the combustion chamber shell layer, the gas layer, the coating sleeve layer and the drug column layer, and adding the temperature variation to each unit corresponding to the j +1 th heat transfer time step of the coating sleeve structure to obtain the temperature of each unit corresponding to the j +1 th heat transfer time step of the coating sleeve structure; determining the calculation completion degree W according to the heat transfer time step sequence number j +1 and the total number M of the heat transfer time steps; and let j equal j + 1; if so, stopping calculating to obtain the temperature of each unit of the cladding sleeve structure after the heat transfer time is over; the preferred scheme is as follows:
if j is equal to M, stopping calculation; if j<And M, similarly to the step (5), calculating the temperature variation delta T in the j +1 th heat transfer time step of each unit according to the physical parameters, the radial coordinates of the inner surface and the outer surface, the temperature corresponding to the j heat transfer time step and the heat flow density of each unit in the combustion chamber shell layer, the gas layer, the coating sleeve layer and the drug column layeri (j+1)The temperature T corresponding to the jth heat transfer time step of each uniti (j)To obtain the temperature T corresponding to the j +1 th heat transfer time step of each uniti (j+1)Determining the calculation completion degree W according to the current heat transfer time step sequence number j +1 and the total number M of the heat transfer time steps, and making j equal to j +1, namely
Wherein the heat flux density of the inner surface of the unit i (i is 2, 3, …, n) is
q1 (j+1)And q isn+1 (j+1)See formula (16) and formula (17);
the completion of the calculation is
W＝(j+1)/M*100％ (33)
Updating heat transfer time step sequence numbers
j＝j+1 (34)
In the formula (31-34), the metal oxide,
Ti (j+1)for the (j + 1) th heat transfer time stepTemperature of long internal unit i (i ═ 1, 2, …, n), K;
Ti-1 (1)is the temperature, K, of unit i-1(i ═ 2, 3, …, n) in the j +1 th heat transfer time step;
ΔTi (j+1)is the temperature variation, K, of unit i (i ═ 1, 2, …, n) in the (j + 1) th heat transfer time step;
qi (j+1)is the surface heat flow density of the unit i (i is 1, 2, …, n) in the j +1 th heat transfer time step, W/m2；
qi+1 (j+1)Is the heat flow density of the outer surface of the unit i (i is 1, 2, …, n) in the j +1 th heat transfer time step, W/m2；
And a calculation result display stage, which is specifically as follows:
(8) displaying a temperature chart of each unit of the cladding sleeve structure after the heat transfer time is finished; the preferred scheme is as follows:
after the calculation is finished, displaying a temperature curve of the cladding sleeve structure corresponding to the last heat transfer time step along the radial coordinate and a temperature cloud chart of the cladding sleeve structure;
in the stage of storing the calculation data, the preferred scheme is as follows:
(9) and storing the temperature data of each unit of the cladding sleeve structure after the heat transfer time is over. The preferred scheme is as follows:
and storing the temperature data of the cladding sleeve structure corresponding to the last heat transfer time step along the radial coordinate into a document such as Excel.
Preferably, the heat transfer working condition of a coating sleeve structure of a certain solid rocket engine is taken as an example, the heat transfer time is 0.1s, and the densities of a combustion chamber shell layer, a fuel gas layer, a coating sleeve layer and a drug column layer are respectively 1500kg/m3、1.225kg/m3、1390kg/m3、1780kg/m3The thermal conductivity is 0.42W/(mK), 0.0242W/(mK), 0.24W/(mK), 0.2W/(mK), the specific heat capacity under constant pressure is 1100J/(kg K), 1800J/(kg K), 1713J/(kg K), 3660J/(kg K), the initial temperature is 300K, 3000K, 300K, the thickness is 5mm, 1.2mm, 0.8mm, 10mm, the radial coordinate of the inner surface of the drug column layer is 130mm, and the radial coordinate is set asThe radial thickness of the unit is 10-4m, respectively carrying out Fluent software calculation and calculation of the calculation method of the invention on the same computer under the working conditions, wherein the result is as follows:
(1) after heat transfer is finished, the position with the maximum radial temperature difference of each unit is located at the center of a gas layer, the calculation result of Fluent software is 311.66K, the calculation result of the method is 310.96K, and the difference between the two is 0.22%;
(2) the single calculation and pre-and-post processing time of Fluent software is about 4h, the single calculation and pre-and-post processing time of the method is about 2min, and the time is shortened to about eight per thousand.
The invention has convenient use and simple operation. Compared with commercial software Fluent, the method does not need operations such as geometric model drawing, manual division of units, result post-processing and the like, the calculation result is displayed visually, and the learning threshold is low; the invention has short calculation time and accurate and reliable result. Compared with commercial software Fluent, the calculation time is obviously reduced under the conditions of the same structure and the same initial value and the same unit size and time step length, and the calculation accuracy is equivalent;
the invention has low cost and high benefit. Expensive commercial software does not need to be purchased, the integrated platform is convenient to integrate into a solid rocket engine design and simulation integrated platform, the intellectual property of self-developed software is possessed, the use is quick and convenient, the coating sleeve structure is favorable for quick design, simulation and optimization, the research and development period is shortened, the research and development cost is reduced, and the rapid propulsion of the aerospace army task is assisted.
Claims (6)
1. A method for rapidly calculating a heat transfer process of a solid rocket engine cladding sleeve structure is characterized by comprising the following steps: an input stage, a calculation and calculation process prompting stage, a calculation result display stage and a calculation data storage stage;
the coating sleeve structure of the solid rocket engine is a four-layer structure and comprises a drug column layer, a coating sleeve layer, a fuel gas layer and a combustion chamber shell layer from inside to outside; each layer is hollow cylindrical; in the calculation process, each layer of the cladding sleeve structure is radially divided into a plurality of units, and any unit only belongs to one layer of the four-layer structure;
the input stage is as follows:
(1) inputting the geometric parameters, physical parameters and initial boundary value conditions of a combustion chamber shell layer, a fuel gas layer, a coating sleeve layer and a drug column layer in a coating sleeve structure; setting heat transfer time and setting a geometric parameter reference value of a unit;
and a calculation and calculation process prompt stage, which is specifically as follows:
(2) determining the unit number and unit radial thickness of each layer in the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the drug column layer according to the geometric parameters of the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the drug column layer determined in the step (1) and the set geometric parameter reference values of the units;
(3) determining the physical parameters, inner and outer surface radial coordinates, initial temperature and heat flux density of each unit in the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the explosive column layer according to the geometric parameters, the physical parameters and the initial boundary value conditions of the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the explosive column layer determined in the step (1) and the unit number and the unit radial thickness of each layer in the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the explosive column layer determined in the step (2);
(4) determining the heat transfer time step length and the total number M of the heat transfer time step length of the cladding sleeve structure according to the physical parameters and the radial coordinates of the inner surface and the outer surface of each unit in the combustion chamber shell layer, the fuel gas layer, the cladding sleeve layer and the drug column layer determined in the step (3);
(5) determining the temperature variation of each unit in the 1 st heat transfer time step of the coating structure according to the physical parameters, the radial coordinates of the inner surface and the outer surface, the initial temperature and the heat flux density of each unit in the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the explosive column layer determined in the step (3-4);
(6) recording the serial number of the current heat transfer time step as j (j is 1, 2, …, M), making j be 1, adding the temperature variation of each unit in the 1 st heat transfer time step of the cladding sleeve structure determined in the step (5) to the initial temperature of each unit determined in the step (3) to be used as the temperature of each unit corresponding to the jth heat transfer time step of the cladding sleeve structure;
(7) judging whether j is equal to the total number M of the heat transfer time step; if not, calculating the temperature variation of each unit in the j +1 th heat transfer time step of the coating sleeve structure according to the physical parameters, the radial coordinates of the inner and outer surfaces, the temperature and the heat flow density corresponding to the j heat transfer time step of the combustion chamber shell layer, the gas layer, the coating sleeve layer and the drug column layer, and adding the temperature variation to each unit corresponding to the j +1 th heat transfer time step of the coating sleeve structure to obtain the temperature of each unit corresponding to the j +1 th heat transfer time step of the coating sleeve structure; determining the calculation completion degree W according to the heat transfer time step sequence number j +1 and the total number M of the heat transfer time steps, and making j equal to j + 1; if so, stopping calculating to obtain the temperature of each unit of the cladding sleeve structure after the heat transfer time is over;
and a calculation result display stage, which is specifically as follows:
(8) displaying a temperature chart of each unit of the cladding sleeve structure after the heat transfer time is over;
the calculation data storage stage specifically comprises the following steps:
(9) and storing the temperature data of each unit of the cladding sleeve structure after the heat transfer time is over.
2. The method for rapidly calculating the heat transfer process of the solid rocket engine jacket structure according to claim 1, wherein the method comprises the following steps: the geometric dimension on combustion chamber shell layer, gas layer, cladding jacket layer, explosive column layer includes: the radial thickness of the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the explosive column layer and the radial coordinate of the inner side of the explosive column.
3. The method for rapidly calculating the heat transfer process of the solid rocket engine jacket structure according to claim 1, wherein the method comprises the following steps: the initial boundary value condition of combustion chamber shell layer, gas layer, cladding jacket layer, explosive column layer includes: initial temperature and heat flux density of the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the explosive column layer.
4. The method for rapidly calculating the heat transfer process of the solid rocket engine jacket structure according to claim 1, wherein the method comprises the following steps: physical property parameters including: the density, the heat conductivity coefficient and the constant pressure specific heat capacity of the combustion chamber shell layer, the fuel gas layer, the coating sleeve layer and the explosive column layer.
5. The method for rapidly calculating the heat transfer process of the solid rocket engine jacket structure according to claim 1, wherein the method comprises the following steps: the length of heat transfer is: the total time required for heat transfer of the clad sleeve structure.
6. The method for rapidly calculating the heat transfer process of the solid rocket engine jacket structure according to claim 1, wherein the method comprises the following steps: the geometric parameter reference value of the unit refers to: a reference value for the radial thickness of the cell.
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