CN112507469B - Design method for heat insulation layer of combustion chamber of solid rocket engine - Google Patents

Design method for heat insulation layer of combustion chamber of solid rocket engine Download PDF

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CN112507469B
CN112507469B CN202110151057.1A CN202110151057A CN112507469B CN 112507469 B CN112507469 B CN 112507469B CN 202110151057 A CN202110151057 A CN 202110151057A CN 112507469 B CN112507469 B CN 112507469B
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insulation layer
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CN112507469A (en
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武泽平
王鹏宇
王文杰
杨家伟
文谦
李国盛
彭博
张为华
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Abstract

The invention provides a design method of a heat insulating layer of a combustion chamber of a solid rocket motor, which is characterized in that the length and the thickness of each heat insulating layer section are taken as design variables, and the minimum quality of the heat insulating layer is taken as a target to construct a target function; for the firstiSegment insulation layer, using optimization algorithm, searching foriOptimal length, thickness of the insulating layer of the segment, secondiThe quality of the insulating layer corresponding to the optimal length and thickness of the insulating layer section is taken as the secondiThe quality of the insulating layer of the segment also serves as the secondiAnd outputting the optimal design scheme corresponding to the section heat insulation layer. And if the mass difference corresponding to the two continuous sections of the heat insulation layers is smaller than a given threshold value, outputting the current number of the sections of the heat insulation layers and the optimal design scheme of each heat insulation layer section as a final heat insulation layer design scheme. The invention can reduce the passive weight as much as possible while ensuring the structural integrity of the engine, and realize the rapid and fine design of the heat insulating layer of the combustion chamber. The invention has higher robustness and design efficiencyAnd the precision is obviously improved.

Description

Design method for heat insulation layer of combustion chamber of solid rocket engine
Technical Field
The invention relates to the technical field of solid rocket engines, in particular to a design method of a heat insulation layer of a combustion chamber of a solid rocket engine.
Background
The solid rocket engine has the advantages of light and simple structure, convenient use and maintenance, high reliability, capability of being in a combat readiness state for a long time and the like. At present, solid rocket engines are widely applied to various tactical missiles, strategic missiles and space vehicles.
The high-temperature and high-pressure gas generated by propellant combustion in the combustion chamber of the solid rocket engine seriously threatens the structural integrity of the engine, so that the design of the heat insulating layer of the combustion chamber is one of important influence factors of the performance and the structural reliability of the engine, and the main task is to determine the thickness of the heat insulating layer and ensure the structural safety of the engine while reducing the negative weight as much as possible. According to the theoretical design, the heat insulating layer extends from the head part to the tail part from thin to thick with a certain slope, but the actual heat insulating layer is changed in steps due to factors such as process and production, and parameters such as the number of the steps, the thickness and the length of each step are determined according to the design scheme.
The currently common methods for designing the thickness of the heat insulating layer are as follows:
(1) based on the existing engine model, the existing design scheme with the closer operating condition is used. The method is simple and convenient, is easy to realize, and effectively avoids a complex operation process. The design method is based on the premise that the existing engine model with the design working condition close to that of the existing engine model has large limitation and poor robustness, and the design result can ensure the structural integrity but increase the passive weight.
(2) Based on a great deal of design experience and case data, parameters such as the number of the insulating layer steps and the thickness and the length of each step are manually corrected and set so as to meet the design requirements. Such methods are used in many applications in the industrial sector, and generally achieve better design results due to the accumulation of a large number of insulation layer design case experiences during the engine design process. The design method needs a large amount of design experience and case data support, needs an experienced engineer to participate, and has low manual iteration efficiency, thereby restricting the improvement of the design efficiency.
Disclosure of Invention
The invention provides a design method of a heat insulating layer of a combustion chamber of a solid rocket engine, aiming at the problems that the design of the heat insulating layer of the combustion chamber of the solid rocket engine in the prior art depends too much on an experience case, and has low efficiency, poor precision and the like.
In order to achieve the technical purpose, the invention adopts the following specific technical scheme:
the design method of the heat insulating layer of the combustion chamber of the solid rocket engine comprises the following steps:
constructing an objective function by taking the length and the thickness of each heat insulation layer segment as design variables and the minimum quality of the heat insulation layer as an objective;
for the firsttA segment of insulating layer, whereint=1,2,…,TUsing an optimization algorithm to search fortOptimal length, thickness of the insulating layer of the segment, secondtThe quality of the insulating layer corresponding to the optimal length and thickness of the insulating layer section is taken as the secondtThe quality of the insulating layer of the segment also serves as the secondtOutputting an optimal design scheme corresponding to the section heat insulation layer;
and if the mass difference corresponding to the two continuous sections of the heat insulation layers is smaller than a given threshold value, outputting the current number of the sections of the heat insulation layers and the optimal design scheme of each heat insulation layer section as a final heat insulation layer design scheme.
As a further limitation of the present invention, the objective function is constructed as follows:
Figure 590056DEST_PATH_IMAGE001
wherein the objective function
Figure 116852DEST_PATH_IMAGE002
The quality of the heat insulation layer;x t to design variables, expresstThe length of the section heat insulation layer is within the range of
Figure 520152DEST_PATH_IMAGE003
；
Figure 44674DEST_PATH_IMAGE004
Is shown astThe thickness of the segment insulation layer.
For the firsttThickness of the segmental insulation layer
Figure 2266DEST_PATH_IMAGE004
And determining the maximum exposure time of the heat insulating layer according to the maximum exposure time of the heat insulating layer in the fuel gas, wherein the calculation method comprises the following steps:
Figure 739278DEST_PATH_IMAGE005
wherein the content of the first and second substances,rfor the rate of ablation of the thermal insulation layer,t z to an axial positionzThe exposure time of the heat insulating layer is determined according to the charging configuration and the combustion time of the engine,
Figure 528242DEST_PATH_IMAGE006
the allowance of the thickness of the heat insulating layer,r、t z 、
Figure 285982DEST_PATH_IMAGE006
are given design parameters.
As a further limitation of the present invention, the constraint of the constructed objective function is: the thickness of two adjacent sections of heat insulation layers is not in phaseEtc. that is
Figure 262029DEST_PATH_IMAGE007
. Therefore, the heat insulation layer with the same thickness can be prevented from being divided into multiple sections, unnecessary calculation consumption is brought to optimization searching, and the optimization algorithm is driven to automatically search for the condition meeting the constraint by designing the constraint condition.
As a further limitation of the present invention, the optimization algorithm used is a differential evolution algorithm.
As a further limitation of the invention, thetThe optimal design scheme corresponding to the section heat insulation layer is obtained through the following steps:
(a) initialization: make the number of iterationsk=1, randomly generating an initial population;
(b) carrying out differential variation and intersection to generate new individual design variables:
(c) carrying out fitness evaluation on newly generated individual design variables, calculating the quality of the adiabatic layer corresponding to each individual design variable, adopting a constraint penalty factor for the individual design variables which do not meet the constraint condition, and adding 10 to the quality of the adiabatic layer6Processing, combining parent population and variant and cross individual design variables, then performing selection operation, and reserving the individual design variable which meets constraint conditions and corresponds to the minimum quality of the heat insulation layer as the current optimal solution;
(d) setting a convergence judgment condition, and outputting the current optimal solution as the second one when the convergence judgment condition is mettThe optimal design scheme corresponding to the section heat insulation layer; otherwise, let the number of iterationsk=k+1, go to step (b) for the next iteration.
Further, in step (d), the convergence determination condition is: continuousnThe quality of the heat insulating layer corresponding to the individual design variables reserved by the generation is not updated, whereinnGreater than 2; or number of iterationskReaching the set maximum number of iterationsK max 。
The invention has the following beneficial effects:
the method is based on an optimized numerical method, aims at the problems of efficiency and precision in the design of the heat insulation layer of the combustion chamber of the solid rocket engine, provides the optimal number of steps under the specified working condition by combining an optimization algorithm, provides the optimal length and thickness of each step, reduces the passive weight as far as possible while ensuring the structural integrity of the engine, and realizes the rapid and fine design of the heat insulation layer of the combustion chamber. The method does not need a large amount of design experience and case data support, avoids tedious and low-efficiency manual iteration, quickly and accurately calculates the design scheme of the heat insulation layer under the current working condition requirement, and realizes the design of the heat insulation layer of the solid rocket engine. Compared with the existing scheme and the manual adjustment method, the method has higher robustness, and the design efficiency and the precision are obviously improved.
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In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the structures shown in the drawings without creative efforts.
FIG. 1 is a flow chart of an embodiment of the present invention;
FIG. 2 is the local charge thickness in case 1;
FIG. 3 is a graph of the combustion thickness of the charge as a function of time for case 1;
FIG. 4 is the local charge thickness in case 2;
FIG. 5 is a graph of the combustion thickness of the charge as a function of time for case 2.
Detailed Description
In order to make the technical scheme and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The invention provides a simple, efficient and rapid design method for a heat insulation layer of a combustion chamber of a solid rocket engine, aiming at the problems that the design of the heat insulation layer of the combustion chamber of the solid rocket engine depends too much on experience cases, and the efficiency is low, the precision is poor and the like. By combining an optimization algorithm, the optimal number of steps under the specified working condition is given, the optimal length and thickness of each step are given, the passive weight is reduced as far as possible while the structural integrity of the engine is ensured, and the rapid and fine design of the heat insulation layer of the combustion chamber is realized. Compared with the existing scheme and the manual adjustment method, the method has higher robustness, and the design efficiency and the precision are obviously improved.
The invention adds the number of the segments of the heat insulating layer, takes the length and the thickness of each segment as design variables and the minimum quality of the heat insulating layer as an objective function aiming at the given number of the segments, and searches the optimal length and the thickness of the segment meeting the design requirements by using an optimization algorithm until the difference of the optimal structural quality corresponding to the number of the segments of the two adjacent heat insulating layers is less than a given threshold value, thereby completing the design of the heat insulating layer of the engine.
An embodiment of the invention provides a design method for a heat insulating layer of a combustion chamber of a solid rocket engine, which comprises the following steps:
first, according to design requirements, design parameters are given, wherein the design parameters comprise an ablation rate of the heat insulation layer, a density of the heat insulation layer, a thickness allowance of the heat insulation layer, a total length of the heat insulation layer, an outer diameter of an engine, a local charging thickness of a charging body, a low-temperature internal ballistic parameter, a convergence threshold value and the like.
And constructing an objective function by taking the length and the thickness of each heat insulation layer segment as design variables and the minimum quality of the heat insulation layer as an objective.
The constructed objective function is:
Figure 68311DEST_PATH_IMAGE008
wherein the objective function
Figure 711782DEST_PATH_IMAGE009
The quality of the heat insulation layer;x t to design variables, expresstThe length of the section heat insulation layer is within the range of
Figure 250210DEST_PATH_IMAGE010
；
Figure 244711DEST_PATH_IMAGE011
Is shown astThe thickness of the segment insulation layer.
For the firsttThickness of the segmental insulation layer
Figure 323526DEST_PATH_IMAGE011
And determining the maximum exposure time of the heat insulating layer according to the maximum exposure time of the heat insulating layer in the fuel gas, wherein the calculation method comprises the following steps:
Figure 149399DEST_PATH_IMAGE012
wherein the content of the first and second substances,rfor the rate of ablation of the thermal insulation layer,t z to an axial positionzThe exposure time of the heat insulating layer is determined according to the charging configuration and the combustion time of the engine,
Figure 655467DEST_PATH_IMAGE013
the allowance of the thickness of the heat insulating layer,r、t z 、
Figure 137264DEST_PATH_IMAGE013
are given design parameters.
The constraint conditions of the constructed objective function are as follows: the thicknesses of the two adjacent sections of heat insulating layers are not equal. Therefore, the heat insulation layer with the same thickness can be prevented from being divided into multiple sections, unnecessary calculation consumption is brought to optimization searching, and the optimization algorithm is driven to automatically search for the condition meeting the constraint by designing the constraint condition.
For the firsttA segment of insulating layer, whereint=1,2,…,TUsing an optimization algorithm to search fortOptimal length, thickness of the insulating layer of the segment, secondtThe quality of the insulating layer corresponding to the optimal length and thickness of the insulating layer section is taken as the secondtThe quality of the insulating layer of the segment also serves as the secondtOptimal design method corresponding to segment insulating layerOutputting the case;
and if the mass difference corresponding to the two continuous sections of the heat insulation layers is smaller than a given threshold value, outputting the current number of the sections of the heat insulation layers and the optimal design scheme of each heat insulation layer section as a final heat insulation layer design scheme.
Referring to fig. 1, an algorithm flow diagram according to an embodiment of the present invention is shown,
(1) initialization, number of segments of insulating layert=1
(2) Using an optimization algorithm to search fortOptimal length, thickness of the insulating layer of the segment, secondtThe quality of the insulating layer corresponding to the optimal length and thickness of the insulating layer section is taken as the secondtThe quality of the insulating layer of the segment also serves as the secondtOutputting an optimal design scheme corresponding to the section heat insulation layer;
(a) initialization: make the number of iterationsk=1, randomly generating an initial population;
(b) carrying out differential variation and intersection to generate new individual design variables;
the way in which differential variation generates new individuals is as follows:
Figure 223032DEST_PATH_IMAGE014
in the formula (I), the compound is shown in the specification,
Figure 575515DEST_PATH_IMAGE015
representing generation of differential variations
Figure 783643DEST_PATH_IMAGE016
A new individual design variable;
Figure 549474DEST_PATH_IMAGE017
is a scaling factor;
Figure 970091DEST_PATH_IMAGE018
、
Figure 708239DEST_PATH_IMAGE019
、
Figure 759372DEST_PATH_IMAGE020
designing variables for randomly selected individuals in a population;
Figure 684603DEST_PATH_IMAGE021
、
Figure 174490DEST_PATH_IMAGE022
、
Figure 501566DEST_PATH_IMAGE023
three random integers, for finding out the individual from the population, i.e. the second in the population
Figure 113813DEST_PATH_IMAGE021
、
Figure 791919DEST_PATH_IMAGE022
、
Figure 554339DEST_PATH_IMAGE023
Individual design variables.
The way in which new individuals are cross-generated is as follows:
Figure 939184DEST_PATH_IMAGE024
in the formula (I), the compound is shown in the specification,
Figure 660015DEST_PATH_IMAGE025
represents the second of cross generationiThe variation of the design of an individual body,
Figure 559838DEST_PATH_IMAGE026
represents the second of cross generation
Figure 453845DEST_PATH_IMAGE027
First of individual design variablesjDimension value taking;
Figure 489934DEST_PATH_IMAGE028
is indicative of the generation of a variationiThe variation of the design of an individual body,
Figure 381666DEST_PATH_IMAGE029
is indicative of the generation of a variation
Figure 972048DEST_PATH_IMAGE030
First of individual design variablesjDimension value taking;
Figure 341849DEST_PATH_IMAGE031
represents the second in the original populationiThe variation of the design of an individual body,
Figure 498024DEST_PATH_IMAGE032
represents the first in the original populationiFirst of individual design variablesjDimension value taking;
Figure 622975DEST_PATH_IMAGE033
indication interval
Figure 231811DEST_PATH_IMAGE034
A random number within;
Figure 670882DEST_PATH_IMAGE035
is the cross probability;
fromj=1 start, if the random number is less than the crossover probability, the second of the individual design variables generated by crossoverjWei Jie
Figure 884826DEST_PATH_IMAGE036
To (1) ajDimension value
Figure 852782DEST_PATH_IMAGE037
(ii) a If the random number is greater than the crossover probability, crossover the generated individual design variablesjWei Jie
Figure 214493DEST_PATH_IMAGE038
To (1) ajDimensional values, i.e.
Figure 988414DEST_PATH_IMAGE039
。
(c) Carrying out fitness evaluation on newly generated individual design variables, calculating the quality of the adiabatic layer corresponding to each individual design variable, adopting a constraint penalty factor for the individual design variables which do not meet the constraint condition, and adding 10 to the quality of the adiabatic layer6And (4) processing, combining the parent population with the variation and cross individual design variables, then performing selection operation, and reserving the individual design variable which meets the constraint condition and corresponds to the minimum quality of the heat insulation layer as the current optimal solution.
Selecting operation, the method is as follows:
Figure 119181DEST_PATH_IMAGE040
in the formula (I), the compound is shown in the specification,
Figure 523618DEST_PATH_IMAGE041
is shown askFirst in the +1 generation populationiIndividual design variables;
Figure 107046DEST_PATH_IMAGE042
is shown askSecond in sub-optimal iterationiA number of cross individual design variables;
Figure 560024DEST_PATH_IMAGE043
is shown askGeneration group the firstiIndividual design variables;
Figure 810877DEST_PATH_IMAGE044
、
Figure 120635DEST_PATH_IMAGE045
respectively representing individual design variables
Figure 519255DEST_PATH_IMAGE046
、
Figure 572662DEST_PATH_IMAGE047
The quality of the corresponding heat insulating layer;
(d) and (3) convergence judgment: if continuous 10 generations of insuranceThe quality of the heat insulating layer corresponding to the remained individual design variables is not updated or the iteration times are not updatedkReaching the set maximum number of iterationsK max Then the current optimal solution is output
Figure 678021DEST_PATH_IMAGE048
As a firsttThe optimal design scheme corresponding to the section heat insulation layer; otherwise, let the number of iterationsk=k+1, go to step (b) for the next iteration.
(3) Remember the currenttThe quality of the heat insulating layer corresponding to the number of the segments of the heat insulating layer is the current optimal solution, namely
Figure 361944DEST_PATH_IMAGE049
If, ift=1, go to step (5); otherwise, turning to the step (4);
(4) and (3) convergence judgment: if the quality difference of the heat insulating layers corresponding to the two continuous heat insulating layer sections is less than a given threshold value
Figure 654385DEST_PATH_IMAGE050
I.e. by
Figure 777061DEST_PATH_IMAGE051
Outputting the current number of sections and the optimal design scheme as the final design scheme of the heat insulation layer; otherwise, turning to the step (5);
(5) recording the quality of the heat insulating layer corresponding to the number of the segments of the heat insulating layer
Figure 799244DEST_PATH_IMAGE052
，t= t And +1, turning to the step (2) for next iteration.
Two implementation cases are given by taking the design of the heat insulating layer of the combustion chamber of a solid rocket engine of a certain model as an example, and the specific steps are as follows:
(1) initializing the number of insulating layer segments according to given calculation conditionst=1；
(2) Solving the optimal heat insulation layer quality under the current section of heat insulation layer by using a differential evolution algorithm;
(3) note the bookRecording the optimum thermal insulation layer quality of the thermal insulation layer of the current section iftIf not 1, returning to the step
Figure 450805DEST_PATH_IMAGE053
Solving the optimal heat insulation layer quality of the next section of heat insulation layer;
(4) and (4) convergence judgment, if the convergence judgment condition is met, namely the quality difference of the optimal heat insulation layers corresponding to the two continuous heat insulation layer segments is smaller than a given threshold value, outputting the current optimal design scheme, and otherwise, returning to the step after the optimal heat insulation layer quality of the previous section of heat insulation layer is updated
Figure 761701DEST_PATH_IMAGE054
。
Case 1:
the thickness of the engine charge given in case 1 is shown in FIG. 2, the combustion thickness of the charge as a function of time is shown in FIG. 3, and the ablation rate of the insulating layer
Figure 156910DEST_PATH_IMAGE055
Density of heat insulating layer
Figure 908966DEST_PATH_IMAGE056
The allowance of the thickness of the heat insulating layer
Figure 262586DEST_PATH_IMAGE057
Outer diameter of engine
Figure 529620DEST_PATH_IMAGE058
。
From the results of the calculation in case 1, it can be seen that the quality of the heat insulating layer structure gradually decreases as the number of heat insulating layer sections gradually increases. And the quality difference is less than a given threshold value 1 when the number of segments is 6 and 7
Figure 790837DEST_PATH_IMAGE059
Therefore, the optimal length and thickness of each segment at the number of segments of 7 is used as the final design, as shown in table 2.
The quality of the thermal insulation layer of each thermal insulation layer of the obtained case 1 is shown in table 1:
TABLE 1
Figure 459716DEST_PATH_IMAGE060
The design results for case 1, as shown in table 2:
TABLE 2
Figure 984238DEST_PATH_IMAGE061
Case 2:
case 2 is a dual burn rate engine insulation design, the thickness of the given engine charge is shown in FIG. 4, the thickness of the primary and secondary charges burn over time is shown in FIG. 5, and the rate of insulation ablation
Figure 676250DEST_PATH_IMAGE062
Density of heat insulating layer
Figure 678841DEST_PATH_IMAGE063
The allowance of the thickness of the heat insulating layer
Figure 467806DEST_PATH_IMAGE064
Outer diameter of engine
Figure 959967DEST_PATH_IMAGE065
。
From the calculation results of case 2, it can be seen that the quality difference is less than the given threshold 1 when the number of segments is 4 and 5
Figure 201593DEST_PATH_IMAGE066
Therefore, the optimal length and thickness of each segment at 5 segments is used as the final design, as shown in table 4.
The quality of the thermal insulation layer for each thermal insulation layer of example 2 was obtained as shown in table 3:
TABLE 3
Figure 7874DEST_PATH_IMAGE067
The design results for case 2, as shown in table 4:
TABLE 4
Figure 385766DEST_PATH_IMAGE068
The method is applied to the design of the heat insulating layer of the combustion chamber under various different design working conditions, compared with the prior art, the method does not need a large amount of design experience and case data support, the manual participation process is less, the design speed is high, the structural integrity of the design result can be ensured under the condition of high-temperature and high-pressure gas, the design automation degree and efficiency are high, and the design requirement is met.
In summary, although the present invention has been described with reference to the preferred embodiments, it should be understood that various changes and modifications can be made by those skilled in the art without departing from the spirit and scope of the invention.

Claims (10)

1. The design method of the heat insulating layer of the combustion chamber of the solid rocket engine is characterized by comprising the following steps:
(1) constructing an objective function by taking the length and the thickness of each heat insulation layer segment as design variables and the minimum quality of the heat insulation layer as an objective;
(2) initialization, number of segments of insulating layert=1；
(3) Using an optimization algorithm to search fortOptimal length, thickness of the insulating layer of the segment, secondtThe quality of the insulating layer corresponding to the optimal length and thickness of the insulating layer section is taken as the secondtThe quality of the insulating layer of the segment also serves as the secondtOutputting an optimal design scheme corresponding to the section heat insulation layer;
(4) remember the currenttThe quality of the heat insulating layer corresponding to the number of the segments of the heat insulating layer is the current optimal solution, namely
Figure 677849DEST_PATH_IMAGE001
If, ift=1, turnGo to step (6); otherwise, turning to the step (5);
(5) and (3) convergence judgment: if the quality difference of the heat insulating layers corresponding to the two continuous heat insulating layer sections is less than a given threshold value
Figure 905568DEST_PATH_IMAGE002
I.e. by
Figure 471678DEST_PATH_IMAGE003
Outputting the current number of the heat insulation layer sections and the optimal design scheme of each heat insulation layer section as a final heat insulation layer design scheme; otherwise, turning to the step (6);
(6) recording the quality of the heat insulating layer corresponding to the number of the segments of the heat insulating layer
Figure 38926DEST_PATH_IMAGE004
，t=tAnd +1, turning to the step (3) for next iteration.
2. The solid rocket engine combustion chamber insulation design process of claim 1 wherein the objective function constructed in step (1) is:
Figure 602762DEST_PATH_IMAGE005
wherein the objective function
Figure 989881DEST_PATH_IMAGE006
The quality of the heat insulation layer;x t to design variables, expresstThe length of the section heat insulation layer is within the range of
Figure 625262DEST_PATH_IMAGE007
；
Figure 843754DEST_PATH_IMAGE008
Is shown astThe thickness of the segment insulation layer.
3. The method for designing a thermal insulation layer for a combustion chamber of a solid rocket engine as recited in claim 2, wherein in the step (1), the first steptThickness of the segmental insulation layer
Figure 640808DEST_PATH_IMAGE008
According to the firsttThe maximum exposure time of the heat insulating layer in the fuel gas is determined by the following calculation method:
Figure 515224DEST_PATH_IMAGE009
wherein the content of the first and second substances,rfor the rate of ablation of the thermal insulation layer,t z to an axial positionzThe exposure time of the heat insulating layer is determined according to the charging configuration and the combustion time of the engine,
Figure 688716DEST_PATH_IMAGE010
the allowance of the thickness of the heat insulating layer,r、t z 、
Figure 902660DEST_PATH_IMAGE010
are given design parameters.
4. The method for designing a solid rocket engine combustion chamber insulation layer according to claim 2 wherein the constraints of the objective function in step (1) are: the thickness of two adjacent sections of insulating layer being unequal, i.e.
Figure 136195DEST_PATH_IMAGE011
。
5. The method for designing a solid rocket engine combustion chamber insulation layer according to claim 2, 3 or 4 wherein the optimization algorithm in step (3) is a differential evolution algorithm.
6. According to claimThe method for designing the heat insulating layer of the combustion chamber of the solid rocket engine is characterized in that in the step (3), the first steptThe optimal design scheme corresponding to the section heat insulation layer is obtained through the following steps:
(a) initialization: make the number of iterationsk=1, randomly generating an initial population;
(b) carrying out differential variation and intersection to generate new individual design variables:
(c) carrying out fitness evaluation on newly generated individual design variables, calculating the quality of the adiabatic layer corresponding to each individual design variable, adopting a constraint penalty factor for the individual design variables which do not meet the constraint condition, and adding 10 to the quality of the adiabatic layer6Processing, combining parent population and variant and cross individual design variables, then performing selection operation, and reserving the individual design variable which meets constraint conditions and corresponds to the minimum quality of the heat insulation layer as the current optimal solution;
(d) setting a convergence judgment condition, and outputting the current optimal solution as the second one when the convergence judgment condition is mettThe optimal design scheme corresponding to the section heat insulation layer; otherwise, let the number of iterationsk=k+1, go to step (b) for the next iteration.
7. The method of designing a solid rocket engine combustion chamber insulation layer according to claim 6 wherein in step (3) (b), the differential variation generates new individual design variables in the following manner:
Figure 560223DEST_PATH_IMAGE012
wherein the content of the first and second substances,
Figure 271827DEST_PATH_IMAGE013
representing generation of differential variations
Figure 402594DEST_PATH_IMAGE014
A new individual design variable;
Figure 541451DEST_PATH_IMAGE015
is a scaling factor;
Figure 328142DEST_PATH_IMAGE016
、
Figure 843437DEST_PATH_IMAGE017
、
Figure 828710DEST_PATH_IMAGE018
variables were designed for randomly selected individuals in the population.
8. The method of designing a solid rocket engine combustion chamber insulation layer according to claim 6 wherein in step (3) (b), the new individual design variables are generated in a crossed manner as follows:
Figure 466365DEST_PATH_IMAGE019
in the formula (I), the compound is shown in the specification,
Figure 537089DEST_PATH_IMAGE020
represents the second of cross generation
Figure 856075DEST_PATH_IMAGE021
First of individual design variables
Figure 899117DEST_PATH_IMAGE022
Dimension value taking;
Figure 379777DEST_PATH_IMAGE023
is indicative of the generation of a variation
Figure 937798DEST_PATH_IMAGE021
First of individual design variables
Figure 122791DEST_PATH_IMAGE022
Dimension value taking;
Figure 817078DEST_PATH_IMAGE024
represents the first in the original population
Figure 734218DEST_PATH_IMAGE021
First of individual design variables
Figure 779535DEST_PATH_IMAGE022
Dimension value taking;
Figure 378006DEST_PATH_IMAGE025
indication interval
Figure 192378DEST_PATH_IMAGE026
A random number within;
Figure 280420DEST_PATH_IMAGE027
is the cross probability.
9. The method for designing a thermal insulation layer for a combustion chamber of a solid rocket engine as recited in claim 6, wherein in step (3) (d), the convergence determination condition is: continuousnThe quality of the heat insulating layer corresponding to the individual design variables reserved by the generation is not updated, whereinnGreater than 2; or number of iterationskReaching the set maximum number of iterationsK max 。
10. The solid rocket engine combustion chamber insulation design process of claim 9 wherein in step (3) (d),nequal to 10.
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