CN112597600B - Method, device and equipment for setting charging configuration of solid rocket engine - Google Patents

Method, device and equipment for setting charging configuration of solid rocket engine Download PDF

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CN112597600B
CN112597600B CN202110186648.2A CN202110186648A CN112597600B CN 112597600 B CN112597600 B CN 112597600B CN 202110186648 A CN202110186648 A CN 202110186648A CN 112597600 B CN112597600 B CN 112597600B
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configuration
combustion surface
surface calculation
cavity
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CN112597600A (en
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武泽平
彭博
王东辉
张为华
李国盛
杨家伟
张士峰
江振宇
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National University of Defense Technology
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    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/10—Shape or structure of solid propellant charges
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/24—Charging rocket engines with solid propellants; Methods or apparatus specially adapted for working solid propellant charges
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    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
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Abstract

The application relates to a method, a device and equipment for setting a charging configuration of a solid rocket engine, wherein the method comprises the following steps: establishing a charge configuration component library in a combustion surface calculation program, and carrying out parametric modeling on common characteristic shapes of the solid rocket engine; decomposing and judging the complete charging configuration of the solid rocket engine, and determining an outer contour configuration assembly and a cavity configuration assembly required by the complete charging; carrying out parameterization setting on each configuration component, judging whether the Boolean attribute of the configuration component is Boolean increase or Boolean decrease, and determining the axial position, the radial position, the shape and the number of the configuration components; discretizing the combustion surface calculation domain in the combustion surface calculation program and introducing Boolean corresponding
Figure 925810DEST_PATH_IMAGE001
The function corresponding to a Boolean subtraction
Figure 603916DEST_PATH_IMAGE002
A function; judging the position of the charge profile in a combustion surface calculation program; judging the position of the charge cavity in a combustion surface calculation program; in the combustion surface calculation program, according to
Figure 631914DEST_PATH_IMAGE001
Function sum
Figure 220022DEST_PATH_IMAGE002
And determining a charge column part, a cavity part and a charge initial burning surface of the complex three-dimensional charge. The design efficiency is high.

Description

Method, device and equipment for setting charging configuration of solid rocket engine
Technical Field
The application relates to the technical field of aircraft engine design, in particular to a method, a device and equipment for setting a charging configuration of a solid rocket engine.
Background
The solid rocket engine is one of the important power systems of space vehicles such as missiles, rockets and the like. Solid rocket engines are one of the important tasks in engine design through selection of the shape of the propellant and adjustment of the structure to suit the specific needs of the engine and the aircraft mission. Because the inner trajectory curve is consistent with the variation trend of the combustion surface area of the explosive column, a designer reasonably designs the variation relation of the combustion surface along with the transition of the thickness of the explosive column by continuously adjusting the geometric configuration of the explosive column, and a thrust scheme meeting the tactical performance requirement is obtained. Meanwhile, the internal boundary geometry of the solid rocket engine varies with the structure of the grain, so that the generation of a computational grid and the determination of boundary conditions related to the grain geometry are difficult, and accurate grain three-dimensional geometric representation is the basis of combustion surface calculation.
The currently common combustion surface calculation methods include: computer graphics based combustion surface calculation and discrete method based charge combustion surface calculation. However, in the process of implementing the invention, the inventor finds that the traditional method for calculating the combustion surface of the solid rocket engine still has the technical problem of low design efficiency of the loading configuration.
Disclosure of Invention
In view of the above, there is a need to provide a simple, efficient and fast method for setting a charge configuration of a solid rocket engine, a device for setting a charge configuration of a solid rocket engine, a computer device and a computer-readable storage medium.
In order to achieve the above purpose, the embodiment of the invention adopts the following technical scheme:
in one aspect, an embodiment of the present invention provides a method for setting a charging configuration of a solid rocket engine, including the steps of:
establishing a charge configuration component library in a combustion surface calculation program, and carrying out parametric modeling on common characteristic shapes of the solid rocket engine;
decomposing and judging the complete charging configuration of the solid rocket engine, and determining an outer contour configuration assembly and a cavity configuration assembly required by the complete charging;
carrying out parameterization setting on each configuration component, judging whether the Boolean attribute of the configuration component is Boolean increase or Boolean decrease, and determining the axial position, the radial position, the shape and the number of the configuration components;
discretizing the combustion surface calculation domain in the combustion surface calculation program and introducing Boolean corresponding
Figure 470430DEST_PATH_IMAGE001
The function corresponding to a Boolean subtraction
Figure 938452DEST_PATH_IMAGE002
A function;
judging the position of the charge profile in a combustion surface calculation program;
judging the position of the charge cavity in a combustion surface calculation program;
in the combustion surface calculation program, according to
Figure 753961DEST_PATH_IMAGE001
Function sum
Figure 432067DEST_PATH_IMAGE002
And determining a charge column part, a cavity part and a charge initial burning surface of the complex three-dimensional charge.
In another aspect, there is provided a solid rocket engine charge configuration setting device comprising:
the parameterization module is used for establishing a charging configuration component library in a combustion surface calculation program and carrying out parameterization modeling on common characteristic shapes of the solid rocket engine;
the assembly determination module is used for decomposing and judging the complete charging configuration of the solid rocket engine and determining an outer contour configuration assembly and a cavity configuration assembly which are required by the complete charging;
the Boolean judgment module is used for carrying out parameterization setting on each configuration component, judging whether the Boolean attribute of the configuration component is Boolean increase or Boolean decrease, and determining the axial position, the radial position, the shape and the number of the configuration component;
a discrete processing module for discretizing the combustion surface calculation domain in the combustion surface calculation program and introducing Boolean corresponding
Figure 99547DEST_PATH_IMAGE001
The function corresponding to a Boolean subtraction
Figure 546709DEST_PATH_IMAGE002
A function;
the contour position module is used for judging the charge contour position in the combustion surface calculation program;
the cavity position module is used for judging the position of the charge cavity in the combustion surface calculation program;
a configuration determining module for determining the configuration of the combustion surface in accordance with
Figure 267540DEST_PATH_IMAGE001
Function sum
Figure 308308DEST_PATH_IMAGE002
And determining a charge column part, a cavity part and a charge initial burning surface of the complex three-dimensional charge.
In yet another aspect, a computer apparatus is provided, comprising a memory storing a computer program and a processor, the processor implementing the steps of the above-described method for setting a charging configuration of a solid rocket engine when executing the computer program.
In yet another aspect, a computer-readable storage medium is provided, having stored thereon a computer program which, when being executed by a processor, carries out the steps of the above-mentioned method for setting a charge configuration of a solid rocket engine.
One of the above technical solutions has the following advantages and beneficial effects:
according to the method, the device and the equipment for setting the charging configuration of the solid rocket engine, through a charging configuration modularization method, complex three-dimensional charging is decomposed into a series of simple combinations of characteristic shapes in the combustion surface calculation process, such as wing-shaped characteristics, wedge-shaped characteristics, star-shaped characteristics and the like, and then the characteristic shapes are combined through Boolean operation to obtain the complete charging configuration. Compared with the traditional charging configuration design method, the method is relatively simple and convenient, the position and the geometric parameters of each configuration only need to be determined manually, the overall characteristics do not need to be set manually, the parts can be modified in the modification of the initial configuration of the charging, the overall workload is greatly reduced, and the charging configuration design efficiency is greatly improved.
Drawings
FIG. 1 is a schematic flow diagram of a method for setting a charging configuration for a solid rocket engine according to one embodiment;
FIG. 2 is a schematic representation of characteristic shapes of several common grains in one embodiment; wherein, (a) is a cylinder, (b) is a semi-ellipsoid, (c) is a wing, (d) is a circular truncated cone, (e) is a star-shaped inner hole, and (f) is a stress release groove;
FIG. 3 is a diagram of a custom build, in one embodiment; wherein, (a) is a self-defined characteristic section, and (b) is a characteristic molding body;
FIG. 4 is a schematic flow chart illustrating the application of the charge configuration setting method described above in one embodiment;
FIG. 5 is a schematic diagram of a complex three-dimensional winged-column charge configuration in one embodiment;
FIG. 6 is a three-dimensional schematic view of a complex three-dimensional wing shaped charge in one embodiment;
FIG. 7 is a schematic diagram of a complex three-dimensional wing-shaped charge assembly method configuration in one embodiment;
FIG. 8 is a schematic diagram illustrating the calculation results of the transition of a complex three-dimensional wing-shaped charge combustion surface in one embodiment; wherein, (a) is a combustion surface-thickness curve, and (b) is a grain volume-thickness curve;
FIG. 9 is a schematic diagram of a dual star shaped charge configuration in one embodiment;
FIG. 10 is a three-dimensional schematic diagram of a dual star hole charge in one embodiment;
FIG. 11 is a schematic diagram of a two-star hole charge modular approach configuration in one embodiment;
FIG. 12 is a graph illustrating the calculation of the shift of the dual star holes charge combustion surface in one embodiment; (a) is a combustion surface-thickness curve, and (b) is a grain volume-thickness curve;
FIG. 13 is a schematic block diagram of a solid rocket engine charge configuration setting device according to an embodiment.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the present application is described in further 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 present application and are not intended to limit the present application. It will be understood that when an element is referred to as being "connected" to another element, it can be directly connected to the other element and integrated therewith or intervening elements may be present, i.e., indirectly connected to the other element.
Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein in the description of the present application is for the purpose of describing particular embodiments only and is not intended to be limiting of the application. As used herein, the term "and/or" includes any and all combinations of one or more of the associated listed items.
In addition, the technical solutions in the embodiments of the present invention may be combined with each other, but it must be based on the realization of those skilled in the art, and when the technical solutions are contradictory or cannot be realized, such a combination of technical solutions should be considered to be absent and not within the protection scope of the present invention.
In the traditional method for calculating the combustion surface of the solid rocket engine, computer graphics based combustion surface calculation is used for modeling the combustion surface at the initial moment through CAD software, a new combustion surface shape is manually drawn along with the combustion surface, and through the circulation, the shape of the charge at each moment and a corresponding combustion surface curve can be obtained, so that the engine performance simulation is performed. Such a method is most used in industrial production because it is highly visible and can visually express the change of a figure.
The method is based on discrete method medicine-loading combustion surface calculation, and specifically comprises the following steps:
firstly, carrying out charge initialization, establishing a three-dimensional model of the charge column through parameterized modeling software, and introducing the discretization of the model surface into a combustion surface calculation program. In a combustion surface calculation program, a combustion surface calculation domain of the whole charge is subjected to grid division, and then combustion surface transition solving is carried out by using different methods, wherein the common combustion surface transition calculation method comprises the following steps:
one is the minimum distance function method: and calculating the distance from each grid node inside the charge to the initial combustion surface, namely a minimum distance function, selecting all points with the minimum distance function value equal to the burned thickness according to the charge parallel layer transition rule to form the combustion surface with the burned thickness, and calculating the combustion surface area on the basis.
Secondly, an interface tracking method: the combustion surface of the engine is regarded as a free boundary in a flow field, and the change rule of the combustion surface is calculated by tracking the change of the combustion interface of the solid propellant. Currently, a Level Set method is used more. Setting the propellant internal area as Kt) The outer region is N: (t) The interface between the two parts, i.e. the combustion surface, is denoted by Γ: (t). Additionally, a symbol distance function from any point in space to the burning surface is set as h: (x,t) If h is: (x,t) At K: (t) Is a distance from the combustion surface, in N: (t) Where is the inverse of the distance to the combustion surface, in Γ (b) ((m))t) The upper is 0. According to this definition, the function h (x,t) The point with a value of 0 is the position of the combustion surface, so that the tracking of the combustion surface progression is changed to solve the function h (per time h)x,t) Solution of = 0.
The defects of the currently used combustion surface calculation method are as follows:
profile settings for engine charges based on computer graphics combustion surface calculations require definition of geometry and location, require manual settings for different charge configurations, and are not versatile. And for the medicine type with a complex structure, the molding process is very complicated.
Although the minimum distance function method and the interface tracking method can automatically shift the combustion surface in the operation process, the initial charge setting is relatively complicated. For complex three-dimensional charging, the accurate modeling characteristic of initial charging needs to be manually established, and the process of constructing the initial combustion surface is complex. Although the geometric parameters of the charge configuration can be rapidly modified through a parametric modeling means, a new shape needs to be manually established again after the charge configuration is changed, and the universality is poor.
In order to solve the technical problem of low design efficiency of the loading configuration in the traditional solid rocket engine combustion surface calculation method, the embodiment of the invention provides the following technical scheme:
referring to fig. 1, in one embodiment, the present invention provides a method for setting a charge configuration of a solid rocket engine, including the following steps S11 to S17:
and S11, establishing a charge configuration component library in the combustion surface calculation program, and carrying out parametric modeling on the common characteristic shapes of the solid rocket engine.
In the process of carrying out parametric modeling on characteristic shapes commonly used by a solid rocket engine, the adopted geometric parameters comprise length, radius, thickness, height, wing inclination angle, major semi-axis, minor semi-axis, star edge semi-angle, star hole angle fraction and/or star angle number. The common characteristic shape of the solid rocket engine is parameterized and modeled, so that a simple characteristic shape can be obtained by modifying a small amount of parameters. For example, modifying the length and diameter may result in cylindrical features, and for example, modifying the length, thickness, height, and wing pitch may result in airfoil features, and the like. The definitions and geometrical parameters of several common characteristic forms of grains in the field are shown in table 1, and the drawings corresponding to the characteristic forms of grains in table 1 are shown in fig. 2.
TABLE 1
Figure 139998DEST_PATH_IMAGE003
It will be appreciated that in addition to the above features, other simple feature assemblies may be customized to meet the needs of a rapid charge build to achieve a complete or continually complete library of charge configuration assemblies for actual charge configuration needs.
Meanwhile, for the characteristic configuration of the revolving body, the characteristic section is defined by using the point set coordinates in the two-dimensional plane, so that the corresponding revolving body model can be obtained, and the user-defined model can be conveniently and rapidly constructed, as shown in fig. 3.
And S12, carrying out decomposition judgment on the complete charging configuration of the solid rocket engine, and determining an outer contour configuration assembly and a cavity configuration assembly required by the complete charging.
It will be appreciated that for different charge configurations of a given solid rocket engine design, a full charge configuration decomposition decision can be made so that the two major components required to form a full charge configuration can be determined in the established charge configuration component library: an outer contour configuration component and a cavity configuration component.
And S13, carrying out parameterization setting on each configuration component, judging whether the Boolean attribute of the configuration component is Boolean increase or Boolean decrease, and determining the axial position, the radial position, the shape and the number of the configuration component.
It can be understood that after the type of the charge type assembly is determined, each determined configuration assembly can be parameterized according to the design requirement of a charge configuration assembly library, and further the boolean attribute of each determined configuration assembly can be judged. The boolean attribute includes two types, boolean increase or boolean decrease. And then determining information such as axial position, radial position, shape and number of each configuration component.
S14, discretizing the combustion surface calculation domain in the combustion surface calculation program and introducing Boolean corresponding
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The function corresponding to a Boolean subtraction
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A function.
Introducing Boolean correspondence
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The function corresponding to a Boolean subtraction
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Functions, which are defined as:
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Figure 122177DEST_PATH_IMAGE007
thus, each grid node in the domain can be calculated by calculating the combustion surface
Figure 996593DEST_PATH_IMAGE004
Function sum
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The value of the function, in the combustion surface calculation domain, represents the initial configuration of the charge.
And S15, judging the charge contour position in the combustion surface calculation program. The method comprises the following specific steps:
respectively calculating the position relation between each grid node and each outer contour configuration component in the combustion surface calculation domain;
setting a contour judgment logic based on the position relation; the outline judgment logic is as follows: for any mesh node, if the mesh node is located in any outer contour configuration component, the mesh node
Figure 351405DEST_PATH_IMAGE008
Otherwise of mesh nodes
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；
Computing all grid nodes
Figure 946652DEST_PATH_IMAGE004
Value of function, extraction
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Obtaining the positions in the charging profile by all grid nodes;
in the calculation program of obtaining combustion surface by using dichotomy solution
Figure 929968DEST_PATH_IMAGE008
And
Figure 599984DEST_PATH_IMAGE009
the interface therebetween.
It will be appreciated that for any point within the surface calculation domain, the positional relationship to each outer contour configuration component is calculated, and if the point is located within any outer contour configuration component, then the point is calculated
Figure 324358DEST_PATH_IMAGE008
Else the point is
Figure 839653DEST_PATH_IMAGE009
. Computing all grid nodes
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Function, all
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The set of grid nodes is the position in the charging contour, and finally the combustion surface calculation domain is obtained through the dichotomy
Figure 143092DEST_PATH_IMAGE008
And
Figure 462078DEST_PATH_IMAGE009
the interface therebetween.
And S16, judging the position of the charge cavity in the combustion surface calculation program. The method comprises the following specific steps:
respectively calculating the position relation between each grid node and each cavity configuration component in the combustion surface calculation domain;
based on the positional relationship, setDetermining a cavity judgment logic; the cavity judgment logic is as follows: for any grid node, if the grid node is located in any cavity configuration component, the grid node
Figure 206918DEST_PATH_IMAGE010
Otherwise of mesh nodes
Figure 953157DEST_PATH_IMAGE011
；
Extraction of
Figure 511177DEST_PATH_IMAGE012
Obtaining the positions outside the charge cavity by all grid nodes;
in the calculation program of obtaining combustion surface by using dichotomy solution
Figure 633854DEST_PATH_IMAGE010
And
Figure 469086DEST_PATH_IMAGE011
the interface therebetween.
It will be appreciated that for any point within the surface calculation domain, the positional relationship to each cavity configuration element is calculated, and if the point is located within any cavity configuration element, then that point is calculated
Figure 386226DEST_PATH_IMAGE010
Else the point is
Figure 962701DEST_PATH_IMAGE011
. Computing all grid nodes
Figure 498856DEST_PATH_IMAGE013
Function, all
Figure 313228DEST_PATH_IMAGE011
The set of grid nodes is the position outside the charge cavity, and finally the combustion surface calculation domain is obtained by the dichotomy
Figure 666849DEST_PATH_IMAGE010
And
Figure 199462DEST_PATH_IMAGE011
the interface therebetween.
S17, in the fuel surface calculation program, based on
Figure 804886DEST_PATH_IMAGE004
Function sum
Figure 473765DEST_PATH_IMAGE005
And determining a charge column part, a cavity part and a charge initial burning surface of the complex three-dimensional charge.
It can be understood that if a certain mesh node is satisfied
Figure 998287DEST_PATH_IMAGE008
And is
Figure 392097DEST_PATH_IMAGE011
And then, the node is positioned in the range of the charge grain, and all the node sets meeting the condition represent the charge grain part of the complex three-dimensional charge. In the same way, all satisfy
Figure 394688DEST_PATH_IMAGE008
And is
Figure 449232DEST_PATH_IMAGE010
The set of nodes of (a) represents the cavity portion of the complex three-dimensional charge. The interface between the cavity and the charge column is the initial burning surface of charge.
According to the solid rocket engine charging configuration setting method, through a charging configuration modularization method, the complex three-dimensional charging is decomposed into a series of combinations of simple characteristic shapes in the combustion surface calculation process, such as wing-shaped characteristics, wedge-shaped characteristics, star-shaped characteristics and the like, and then the characteristic shapes are combined through Boolean operation to obtain the complete charging configuration. Compared with the traditional charging configuration design method, the method is relatively simple and convenient, the position and the geometric parameters of each configuration only need to be determined manually, the overall characteristics do not need to be set manually, the parts can be modified in the modification of the initial configuration of the charging, the overall workload is greatly reduced, and the charging configuration design efficiency is greatly improved.
Referring to fig. 4, in one embodiment, to more intuitively and fully describe the above-described method for setting a charge configuration of a solid rocket engine, the following two embodiments are given below by taking a complex three-dimensional winged-shaped charge and a double star-shaped charge as examples. It should be noted that the two embodiments given in this specification are only illustrative and are not the only limitations of the specific embodiments of the present invention, and those skilled in the art can rapidly design other different charging configurations by using the above-mentioned method for setting the charging configuration of the solid rocket engine in the spirit of the embodiments provided by the present invention.
Case 1: complex three-dimensional winged-cylindrical charge:
a complex three-dimensional winged-cylindrical charge configuration is shown in figure 5 and a three-dimensional schematic is shown in figure 6.
1) Analyzing fig. 6, the contour portion of the grain is composed of two semi-ellipsoids and a cylinder, and both ends are cut flat. The inner bore portion is formed by three cylinders, a stress relief groove and two wing shapes.
2) The position and geometry of the individual components are set according to the charge configuration diagram, as shown in table 2.
3) Dividing charge computational domain grids, calculating for each grid
Figure 20022DEST_PATH_IMAGE004
Function sum
Figure 261647DEST_PATH_IMAGE005
A function.
4) The charge configuration calculations are shown in fig. 7, and a comparison of fig. 6 shows that the results are highly consistent.
5) The results of calculations based on the charge configuration for the face-to-thickness curve and the charge volume-to-thickness curve are shown in figure 8.
TABLE 2 Complex three-dimensional Airfoil shaped Charge Assembly configuration setting Table
Figure 67929DEST_PATH_IMAGE014
Case 2: double star shaped charge:
a two star shaped charge configuration is shown in fig. 9, and a three dimensional schematic is shown in fig. 10.
1) As can be seen from the analysis of FIG. 10, the contour of the double-star-hole charge-configured grain is composed of a cylindrical section and two semi-ellipsoids, and a part of two ends of the cylindrical section is cut off; the inner hole of the star-hole component is formed by two star-hole component configurations and a cylinder.
2) The position and geometry of each assembly was set according to the charge configuration diagram, as shown in table 3.
3) Dividing charge computational domain grids, calculating for each grid
Figure 117925DEST_PATH_IMAGE004
Function sum
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A function.
4) By passing
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Function sum
Figure 57565DEST_PATH_IMAGE005
The function determines the charge column part and the cavity part, the result is shown in fig. 11, and the goodness of fit is high compared with the actual model of fig. 10.
5) The charge combustion face displacement calculation results are shown in fig. 12.
TABLE 3 configuration setting table for double star hole charging assembly
Figure 962067DEST_PATH_IMAGE015
The example results show that the invention obviously simplifies the manual operation, ensures that the precision of the grain is basically consistent with the manual three-dimensional modeling result, and fully proves the effectiveness of the invention.
Compared with the best technology in the prior art, the invention has the advantages that: 1. the explosive charging setting is quickly and simply realized during the combustion surface calculation, the complexity of manual operation is reduced, and the efficiency of the explosive charging design process is improved. 2. The invention has good universality, can adapt to various shapes of the explosive column and is beneficial to the automatic operation of a computer. The method is applied to combustion surface calculation of various different configurations, and compared with the existing method, the method is simple and convenient in manual operation, high in setting speed, high in automation degree and reliable in calculation result performance.
It should be understood that although the steps in the flowcharts of fig. 1 and 4 are shown in order as indicated by the arrows, the steps are not necessarily performed in order as indicated by the arrows. The steps are not performed in the exact order shown and described, and may be performed in other orders, unless explicitly stated otherwise. Moreover, at least a portion of the steps of fig. 1 and 4 may include multiple sub-steps or multiple stages that are not necessarily performed at the same time, but may be performed at different times, and the order of performance of the sub-steps or stages is not necessarily sequential, but may be performed in turn or alternately with other steps or at least a portion of the sub-steps or stages of other steps.
Referring to fig. 13, in another aspect, there is provided a solid rocket engine charge configuration setting apparatus 100, including a parameterization module 13, an assembly determination module 15, a boolean judgment module 17, a discretization processing module 19, a contour position module 21, a cavity position module 23, and a configuration determination module 25. The parameterization module 13 is used for establishing a charging configuration component library in a combustion surface calculation program and carrying out parameterization modeling on characteristic shapes commonly used by the solid rocket engine. The assembly determination module 15 is used for carrying out decomposition judgment on the complete charging configuration of the solid rocket engine and determining an outer contour configuration assembly and a cavity configuration assembly required by the complete charging. The Boolean judgment module 17 is used for carrying out parameterization setting on each configuration component, judging whether the Boolean attribute of the configuration component is Boolean increase or Boolean decrease, and determining the axial position, the radial position, the shape and the number of the configuration component. The discrete processing module 19 is used for discretizing the combustion surface calculation domain in the combustion surface calculation program and introducing Boolean corresponding
Figure 733714DEST_PATH_IMAGE004
The function corresponding to a Boolean subtraction
Figure 215511DEST_PATH_IMAGE005
A function. The profile position module 21 is used to determine the charge profile position in the combustion surface calculation program. The cavity position module 23 is used to determine the charge cavity position in the combustion surface calculation program. The configuration determining module 25 is used in the combustion surface calculating program according to
Figure 737497DEST_PATH_IMAGE004
Function sum
Figure 355560DEST_PATH_IMAGE005
And determining a charge column part, a cavity part and a charge initial burning surface of the complex three-dimensional charge.
According to the solid rocket engine charging configuration setting device 100, through cooperation of all modules, a charging configuration modularization method is utilized, complex three-dimensional charging is decomposed into a series of simple combinations of characteristic shapes in the combustion surface calculation process, such as wing-shaped characteristics, wedge-shaped characteristics, star-shaped characteristics and the like, and then the characteristic shapes are combined through Boolean operation to obtain a complete charging configuration. Compared with the traditional charging configuration design method, the method is relatively simple and convenient, the position and the geometric parameters of each configuration only need to be determined manually, the overall characteristics do not need to be set manually, the parts can be modified in the modification of the initial configuration of the charging, the overall workload is greatly reduced, and the charging configuration design efficiency is greatly improved.
In one embodiment, the modules of the solid rocket engine charge configuration setting apparatus 100 may also be used to implement the corresponding steps or substeps added in the embodiments of the solid rocket engine charge configuration setting method.
For specific limitations of the solid rocket engine charge configuration setting apparatus 100, reference may be made to the corresponding limitations of the solid rocket engine charge configuration setting method above, and details thereof are not repeated here. The various modules in the solid rocket engine charge configuration setting apparatus 100 described above may be implemented in whole or in part by software, hardware, and combinations thereof. The modules may be embedded in hardware or independent from a device with specific data processing function, or may be stored in a memory of the device in software, so that a processor may invoke and execute operations corresponding to the modules, where the device may be, but is not limited to, a computer device or a computing system for designing a solid rocket engine.
In still another aspect, a computer device is provided, which includes a memory and a processor, the memory stores a computer program, and the processor executes the computer program to implement the following steps: establishing a charge configuration component library in a combustion surface calculation program, and carrying out parametric modeling on common characteristic shapes of the solid rocket engine; decomposing and judging the complete charging configuration of the solid rocket engine, and determining an outer contour configuration assembly and a cavity configuration assembly required by the complete charging; carrying out parameterization setting on each configuration component, judging whether the Boolean attribute of the configuration component is Boolean increase or Boolean decrease, and determining the axial position, the radial position, the shape and the number of the configuration components; discretizing the combustion surface calculation domain in the combustion surface calculation program and introducing Boolean corresponding
Figure 829267DEST_PATH_IMAGE004
The function corresponding to a Boolean subtraction
Figure 408147DEST_PATH_IMAGE005
A function; judging the position of the charge profile in a combustion surface calculation program; judging the position of the charge cavity in a combustion surface calculation program; in the combustion surface calculation program, according to
Figure 94343DEST_PATH_IMAGE004
Function sum
Figure 832492DEST_PATH_IMAGE005
Function, determining the charge portion of a complex three-dimensional chargeA branch, a cavity part and a charge initial combustion surface.
In one embodiment, the processor when executing the computer program may also implement the additional steps or substeps of the various embodiments of the method for setting a charge configuration for a solid rocket engine described above.
In yet another aspect, there is also provided a computer readable storage medium having a computer program stored thereon, the computer program when executed by a processor implementing the steps of: establishing a charge configuration component library in a combustion surface calculation program, and carrying out parametric modeling on common characteristic shapes of the solid rocket engine; decomposing and judging the complete charging configuration of the solid rocket engine, and determining an outer contour configuration assembly and a cavity configuration assembly required by the complete charging; carrying out parameterization setting on each configuration component, judging whether the Boolean attribute of the configuration component is Boolean increase or Boolean decrease, and determining the axial position, the radial position, the shape and the number of the configuration components; discretizing the combustion surface calculation domain in the combustion surface calculation program and introducing Boolean corresponding
Figure 945941DEST_PATH_IMAGE004
The function corresponding to a Boolean subtraction
Figure 277697DEST_PATH_IMAGE005
A function; judging the position of the charge profile in a combustion surface calculation program; judging the position of the charge cavity in a combustion surface calculation program; in the combustion surface calculation program, according to
Figure 767584DEST_PATH_IMAGE004
Function sum
Figure 360239DEST_PATH_IMAGE005
And determining a charge column part, a cavity part and a charge initial burning surface of the complex three-dimensional charge.
In one embodiment, the computer program, when executed by the processor, further implements additional steps or substeps of the above-described method for setting a charge configuration of a solid rocket engine.
It will be understood by those skilled in the art that all or part of the processes of the methods of the embodiments described above can be implemented by hardware related to instructions of a computer program, which can be stored in a non-volatile computer-readable storage medium, and when executed, can include the processes of the embodiments of the methods described above. Any reference to memory, storage, database, or other medium used in the embodiments provided herein may include non-volatile and/or volatile memory, among others. Non-volatile memory can include read-only memory (ROM), Programmable ROM (PROM), Electrically Programmable ROM (EPROM), Electrically Erasable Programmable ROM (EEPROM), or flash memory. Volatile memory can include Random Access Memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in a variety of forms, such as Static RAM (SRAM), Dynamic RAM (DRAM), Synchronous DRAM (SDRAM), Double Data Rate SDRAM (DDRSDRAM), Enhanced SDRAM (ESDRAM), synchronous link DRAM (Synchlink) DRAM (SLDRAM), Rambus DRAM (RDRAM), and interface DRAM (DRDRAM).
The technical features of the above embodiments can be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the above embodiments are not described, but should be considered as the scope of the present specification as long as there is no contradiction between the combinations of the technical features.
The above examples only express several embodiments of the present application, and the description thereof is more specific and detailed, but not construed as limiting the scope of the invention. It should be noted that, for those skilled in the art, various changes and modifications can be made without departing from the spirit of the present application, and all of them fall within the scope of the present application. Therefore, the protection scope of the present patent should be subject to the appended claims.

Claims (7)

1. A method for setting a charging configuration of a solid rocket engine is characterized by comprising the following steps:
establishing a charge configuration component library in a combustion surface calculation program, and carrying out parametric modeling on common characteristic shapes of the solid rocket engine;
decomposing and judging the complete charging configuration of the solid rocket engine, and determining an outer contour configuration assembly and a cavity configuration assembly required by the complete charging;
carrying out parameterization setting on each configuration component, judging whether the Boolean attribute of the configuration component is Boolean increase or Boolean decrease, and determining the axial position, the radial position, the shape and the number of the configuration component;
discretizing the combustion surface calculation domain in the combustion surface calculation program, introducing Boolean corresponding
Figure 226545DEST_PATH_IMAGE001
The function corresponding to a Boolean subtraction
Figure 568927DEST_PATH_IMAGE002
A function;
judging the position of a charging profile in the combustion surface calculation program;
judging the position of a charge cavity in the combustion surface calculation program;
in the combustion surface calculation program, according to the
Figure 108493DEST_PATH_IMAGE001
Function and the
Figure 958637DEST_PATH_IMAGE002
Determining a charge column part, a cavity part and a charge initial burning surface of the complex three-dimensional charge;
the method of Boolean corresponds to
Figure 329575DEST_PATH_IMAGE003
The function is defined as:
Figure 544656DEST_PATH_IMAGE004
corresponding to a Boolean subtraction
Figure 899414DEST_PATH_IMAGE005
The function is defined as:
Figure 22091DEST_PATH_IMAGE006
；
the step of judging the charge profile position in the combustion surface calculation program comprises the following steps:
respectively calculating the position relation between each grid node and each outer contour configuration component in the combustion surface calculation domain;
setting a contour judgment logic based on the position relation; the contour judgment logic is as follows: for any of the mesh nodes, if the mesh node is located within any of the outer contour configuration components, the mesh node' s
Figure 716377DEST_PATH_IMAGE007
Otherwise, the mesh node
Figure 164676DEST_PATH_IMAGE008
；
Computing all grid nodes
Figure 678834DEST_PATH_IMAGE001
Value of function, extraction
Figure 605202DEST_PATH_IMAGE007
Obtaining the positions in the charging profile by all the grid nodes;
the combustion surface calculation program is obtained by solving through a dichotomy
Figure 216312DEST_PATH_IMAGE007
And
Figure 773195DEST_PATH_IMAGE008
an interface therebetween;
the step of judging the position of the charge cavity in the combustion surface calculation program comprises the following steps:
respectively calculating the position relation between each grid node and each cavity configuration component in the combustion surface calculation domain;
setting cavity judgment logic based on the position relation; the cavity judgment logic is as follows: for any of the grid nodes, if the grid node is located within any of the cavity-configured components, the grid node' s
Figure 72852DEST_PATH_IMAGE009
Otherwise, the mesh node
Figure 68490DEST_PATH_IMAGE010
；
Extraction of
Figure 471789DEST_PATH_IMAGE010
Obtaining the position outside the charging cavity by all the grid nodes;
the combustion surface calculation program is obtained by solving through a dichotomy
Figure 996311DEST_PATH_IMAGE009
And
Figure 547378DEST_PATH_IMAGE010
the interface therebetween.
2. A solid-rocket engine charge configuration setting method as recited in claim 1, wherein in said combustion surface calculation program, said method is based on said
Figure 284390DEST_PATH_IMAGE001
Function and the
Figure 604513DEST_PATH_IMAGE002
A process for determining a charge portion of a complex three-dimensional charge, comprising:
extracting the fuel surface calculation program satisfying
Figure 299937DEST_PATH_IMAGE007
And is
Figure 275983DEST_PATH_IMAGE011
The node set formed by all grid nodes obtains the charge column part of the complex three-dimensional charge.
3. A solid-rocket engine charge configuration setting method as recited in claim 1, wherein in said combustion surface calculation program, said method is based on said
Figure 347844DEST_PATH_IMAGE001
Function and the
Figure 522474DEST_PATH_IMAGE002
A process for determining a cavity portion of a complex three-dimensional charge, comprising:
extracting the fuel surface calculation program satisfying
Figure 857640DEST_PATH_IMAGE007
And is
Figure 619185DEST_PATH_IMAGE012
And obtaining the cavity part of the complex three-dimensional charge by a node set formed by all grid nodes.
4. A method of setting a solid rocket engine charge configuration according to claim 1 wherein the process of determining a charge initiation face comprises:
determining an interface between the charge portion and the cavity portion as the charge initiating face.
5. A solid-rocket engine charge configuration setting method as recited in claim 1, wherein said geometric parameters used in the process of parametric modeling the characteristic features commonly used in solid-rocket engines include length, radius, thickness, height, wing pitch angle, major semi-axis, minor semi-axis, star half angle, star-hole angle fraction and/or star angle number.
6. A solid rocket engine charge configuration setting device, comprising:
the parameterization module is used for establishing a charging configuration component library in a combustion surface calculation program and carrying out parameterization modeling on common characteristic shapes of the solid rocket engine;
the assembly determination module is used for decomposing and judging the complete charging configuration of the solid rocket engine and determining an outer contour configuration assembly and a cavity configuration assembly which are required by the complete charging;
the Boolean judgment module is used for carrying out parameterization setting on each configuration component, judging whether the Boolean attribute of the configuration component is Boolean increase or Boolean decrease, and determining the axial position, the radial position, the shape and the number of the configuration component;
a discrete processing module for discretizing the combustion surface calculation domain in the combustion surface calculation program and introducing Boolean corresponding
Figure 494737DEST_PATH_IMAGE001
The function corresponding to a Boolean subtraction
Figure 461556DEST_PATH_IMAGE005
A function;
the outline position module is used for judging the charge outline position in the combustion surface calculation program;
the cavity position module is used for judging the position of a charge cavity in the combustion surface calculation program;
a configuration determination module for determining, in the combustion surface calculation program, a configuration based on the
Figure 29940DEST_PATH_IMAGE001
Function and the
Figure 511737DEST_PATH_IMAGE002
Determining a charge column part, a cavity part and a charge initial burning surface of the complex three-dimensional charge;
the method of Boolean corresponds to
Figure 128664DEST_PATH_IMAGE001
The function is defined as:
Figure 277885DEST_PATH_IMAGE013
corresponding to a Boolean subtraction
Figure 954854DEST_PATH_IMAGE005
The function is defined as:
Figure 923947DEST_PATH_IMAGE014
the outline position module is also used for respectively calculating the position relation between each grid node and each outline configuration component in the combustion surface calculation domain;
setting a contour judgment logic based on the position relation; the contour judgment logic is as follows: for any of the mesh nodes, if the mesh node is located within any of the outer contour configuration components, the mesh node' s
Figure 406881DEST_PATH_IMAGE007
Otherwise, the mesh node
Figure 348292DEST_PATH_IMAGE008
；
Computing all grid nodes
Figure 992900DEST_PATH_IMAGE001
Value of function, extraction
Figure 216333DEST_PATH_IMAGE007
Obtaining the positions in the charging profile by all the grid nodes;
the combustion surface calculation program is obtained by solving through a dichotomy
Figure 175062DEST_PATH_IMAGE007
And
Figure 298876DEST_PATH_IMAGE008
an interface therebetween;
the cavity position module is also used for respectively calculating the position relation between each grid node and each cavity configuration component in the combustion surface calculation domain;
setting cavity judgment logic based on the position relation; the cavity judgment logic is as follows: for any of the grid nodes, if the grid node is located within any of the cavity-configured components, the grid node' s
Figure 848806DEST_PATH_IMAGE015
Otherwise, the mesh node
Figure 995754DEST_PATH_IMAGE016
；
Extraction of
Figure 820490DEST_PATH_IMAGE016
Obtaining the position outside the charging cavity by all the grid nodes;
the combustion surface calculation program is obtained by solving through a dichotomy
Figure 533231DEST_PATH_IMAGE015
And
Figure 722904DEST_PATH_IMAGE016
the interface therebetween.
7. A computer apparatus comprising a memory and a processor, the memory storing a computer program, wherein the processor when executing the computer program performs the steps of a method of setting a charge configuration for a solid rocket engine according to any one of claims 1 to 5.
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