Automatic pushing method and system for combustion surface of grain of solid rocket engine

Abstract

The invention relates to the technical field of solid rocket engine design, and discloses a solid rocket engine grain combustion surface automatic pushing method and system.The method comprises the steps that a grain model is segmented on the basis of preset solid engine grain model geometric symmetry parameters, and a minimum symmetric unit grain model is obtained; extracting a plurality of inner molded surfaces of the minimum symmetric unit grain model, and jointing the plurality of inner molded surfaces to obtain an initial burning surface; taking the initial burning surface as an offset object of the geometry, and offsetting the initial burning surface based on a preset offset parameter to obtain a thickened curved surface geometry; and after the thickened curved surface geometry is removed from the minimum symmetric unit grain model, original model reduction is carried out, the solid engine grain model after combustion surface pushing is obtained, the efficiency and precision of the combustion surface pushing process are improved, the research and development cost is reduced, and the research and development time is shortened.

Description

Technical Field

[0001] The present invention relates to the technical field of solid rocket engine design, and in particular to a method and system for automatically advancing the burning surface of a solid rocket engine grain. Background Art

[0002] As the propulsion system for solid rockets, solid rocket motors play a vital role in their operation. When designing their interior ballistics, shifting the grain's burning surface is a critical step, as changes in the grain's burning surface directly affect the engine's combustion characteristics and thrust output, ultimately determining the solid rocket's flight performance.

[0003] The traditional method of moving the combustion surface of the grain mainly relies on establishing a core mold model in 3D software. This modeling method itself has a certain degree of complexity and requires the operator to have high 3D modeling skills and rich experience. After the core mold model is established, it is "offset" to achieve the movement of the combustion surface. However, in actual operation, there are many problems in the process of selecting several offset lengths. After each "offset" operation, the model needs to be checked and adjusted to ensure that it conforms to the actual combustion surface movement. If there is a deviation, the modeling and operation must be repeated, which greatly increases the time cost of the entire work.

[0004] Due to the complexity of modeling and offset operations, as well as the need for continuous trial and error adjustments, completing a single grain combustion surface movement simulation can take a long time. In today's rapidly developing aerospace industry, time costs are a factor that cannot be ignored. This inefficient method clearly cannot meet the rapid iteration and optimization requirements of modern solid rocket engine designs. Traditional methods also have significant shortcomings in terms of accuracy. Due to the lack of precision in the selection of offset lengths, the final combustion surface movement results deviate from the actual situation. This lack of precision can mislead the interior ballistic design of the solid rocket engine, thereby affecting the performance and safety of the entire solid rocket. Summary of the Invention

[0005] In view of this, the present invention provides a method and system for automatically advancing the burning surface of a solid rocket motor grain to solve the problem of how to improve the efficiency and accuracy of advancing the burning surface of a solid rocket motor grain.

[0006] In a first aspect, the present invention provides a method for automatically advancing the burning surface of a solid rocket motor grain, the method comprising:

[0007] The grain model is divided based on the preset geometric symmetry parameters of the solid motor grain model to obtain the minimum symmetric unit grain model;

[0008] Extracting multiple inner surfaces of the minimum symmetrical unit grain model and joining the multiple inner surfaces to obtain an initial burning surface;

[0009] Taking the initial burning surface as an offset object of a geometric body, offsetting the initial burning surface based on preset offset parameters to obtain a thickened curved surface geometric body;

[0010] After removing the thickened surface geometry from the minimum symmetric unit grain model, the original model is restored to obtain the solid motor grain model after the combustion surface is moved.

[0011] The method for automatically shifting the burning surface of a solid rocket engine grain provided by an embodiment of the present invention divides the grain model based on geometric symmetry parameters. It only needs to process the minimum symmetric unit grain model instead of operating the entire complex grain model, which greatly reduces the amount of calculation and the complexity of modeling and improves the efficiency of modeling. When processing the minimum symmetric unit grain model, its multiple internal surfaces are accurately extracted and joined to obtain the initial burning surface, which can accurately reflect the starting state of the grain combustion and provide an accurate basis for subsequent burning surface shifting simulation. The initial burning surface is used as the offset object and the offset is performed based on the preset offset parameters. The thickened curved surface geometry is obtained by shifting the surface geometry. This method can more realistically simulate the movement of the burning surface of the grain during the combustion process. The changing law of the burning surface during the combustion of the grain is taken into account, so that the simulation results are closer to the actual combustion process. After the thickened geometry is removed from the minimum symmetric unit grain model, the original model is restored to obtain the solid motor grain model after the burning surface is shifted. This can intuitively display the shape of the grain after a certain combustion time. Through accurate automatic movement simulation of the burning surface, the combustion situation of the grain can be displayed in advance on the computer, which improves the efficiency and accuracy of the burning surface movement process and reduces R&D costs and time.

[0012] In an optional embodiment, the method further includes: recording the combustion area, charge mass, charge volume and center of mass position during the automatic movement process.

[0013] The combustion area is directly related to the engine combustion chamber pressure and thrust. Recording it can calculate parameters such as combustion chamber pressure and engine thrust; the grain mass is used to calculate the remaining mass of the propellant, and the grain volume is used to calculate the combustion surface, or to calculate the grain mass. The center of mass position is crucial to the flight stability of the rocket. Recording its changes can timely adjust the flight attitude control strategy to prevent instability during flight. By recording these data, a basis is provided for the operating parameter control of the solid rocket engine. By analyzing these data at different stages, designers can also optimize the shape and size of the grain and improve the overall performance of the engine.

[0014] In an optional embodiment, the offset parameters include: initial offset thickness, offset thickness interval and number of offsets, wherein the initial offset thickness is less than the preset drug column thickness, and the offset thickness interval*number of offsets ≤ the preset drug column thickness.

[0015] By reasonably setting these three parameters, the embodiment of the present invention can simulate the movement of the combustion surface in stages and at fixed distances, accurately restore the changes in the combustion surface during the combustion of the grain, and improve the simulation accuracy. Different combinations of initial offset thickness, offset thickness interval and offset number can adapt to a variety of grain structures and combustion characteristics, meeting diverse simulation needs.

[0016] In an optional embodiment, the combustion area is calculated according to the following formula:

[0017]

[0018] Where i represents the number of offsets, A represents the burning area, V represents the volume of the grain, and w represents the offset thickness interval.

[0019] The formula provided in this embodiment of the present invention takes into account the number of offsets, which represents the progression of the grain's burning surface. This number can reflect the dynamic changes in the burning surface over time or over the combustion process, facilitating tracking of changes in the burning area throughout the combustion process. The calculation also incorporates the grain volume V, taking into account the fundamental properties of the grain itself. Grains of varying volumes have different initial conditions. This formula allows the calculation of the burning area to be correlated with the grain's own characteristics, making the calculation more realistic. The offset thickness interval w is a customizable parameter that precisely controls the quantification of the burning surface's progression, ensuring that the calculated results more closely meet the simulation's accuracy requirements and facilitating more accurate analysis of the combustion process.

[0020] In an optional embodiment, the geometric symmetry parameter is determined according to the wing distribution of the charge.

[0021] The wing distribution of the grain is its important geometric feature. The embodiment of the present invention determines the symmetry parameters based on this, can accurately find the minimum symmetry unit, simplify the modeling process, reduce the amount of calculation, and at the same time will not miss key structural information. The wing distribution affects the combustion surface changes and airflow distribution during the combustion of the grain. Determining the symmetry parameters based on it for simulation can more realistically reflect the combustion conditions of the grain in actual work, making the simulation results more reliable.

[0022] In a second aspect, the present invention provides a method and system for automatically advancing the burning surface of a solid rocket motor grain, the system comprising:

[0023] A model segmentation module is used to segment the grain model based on the preset geometric symmetry parameters of the solid motor grain model to obtain the minimum symmetric unit grain model;

[0024] An initial burning surface acquisition module is used to extract multiple inner surfaces of the minimum symmetrical unit grain model and to join the multiple inner surfaces to obtain an initial burning surface;

[0025] a thickened curved surface geometry acquisition module, configured to use the initial burning surface as an offset object of a geometry, and offset the initial burning surface based on preset offset parameters to obtain a thickened curved surface geometry;

[0026] The model restoration model is used to remove the thickened surface geometry from the minimum symmetric unit grain model and then restore the original model to obtain the solid motor grain model after the combustion surface is moved.

[0027] In one embodiment, the system further comprises: a data recording module for recording the burning area, charge mass, charge volume and center of mass position during the automatic movement process.

[0028] In a third aspect, the present invention provides a computer device comprising: a memory and a processor, the memory and the processor being communicatively connected to each other, the memory storing computer instructions, and the processor executing the computer instructions to execute the method for automatically advancing the burning surface of a solid rocket engine grain according to the first aspect or any corresponding embodiment thereof.

[0029] In a fourth aspect, the present invention provides a computer-readable storage medium having computer instructions stored thereon, the computer instructions being used to enable a computer to execute the method for automatically advancing the burning surface of a solid rocket engine propellant according to the first aspect or any corresponding embodiment thereof.

[0030] In a fifth aspect, the present invention provides a computer program product comprising computer instructions for causing a computer to execute the method for automatically advancing the burning surface of a solid rocket motor grain according to the first aspect or any corresponding embodiment thereof. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0032] Figure 1 1 is a flow chart of a method for automatically advancing the burning surface of a solid rocket motor grain according to an embodiment of the present invention;

[0033] Figure 2 is a schematic diagram of a wing-column type grain model according to an embodiment of the present invention;

[0034] Figure 3 According to an embodiment of the present invention Figure 2 The 1 / 16 medicine column model of the traditional Chinese medicine column model is a schematic diagram of the minimum symmetric unit medicine column model;

[0035] Figure 4 is a schematic diagram of an initial combustion surface according to an embodiment of the present invention;

[0036] Figure 5 Column (a) is a schematic diagram of the corresponding thickened surface geometry after 6 shifts with a preset offset thickness;

[0037] Figure 5 Column (b) in the figure shows the thickened surface geometry from Figure 3 Schematic diagram of the state after the minimum symmetric unit of the grain model is removed;

[0038] Figure 5 Column (c) is as follows Figure 2 The grain model shown corresponds to the states of the six shifts of the burning surface.

[0039] Figure 6 1 is a flow chart of another method for automatically advancing the burning surface of a solid rocket motor grain according to an embodiment of the present invention;

[0040] Figure 7 is a schematic diagram of derived data according to an embodiment of the present invention;

[0041] Figure 8 2 is a structural block diagram of a method system for automatically advancing the burning surface of a solid rocket motor grain according to an embodiment of the present invention;

[0042] Figure 9 Schematic diagram of the hardware structure of a computer device according to an embodiment of the present invention. DETAILED DESCRIPTION

[0043] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without making creative efforts shall fall within the scope of protection of the present invention.

[0044] In order to solve the problem of low efficiency and precision in moving the burning surface of a conventional solid rocket motor grain, an embodiment of the present invention provides a method for automatically moving the burning surface of a solid rocket motor grain. Figure 1 FIG. 1 is a flow chart of a method for automatically moving the burning surface of a solid rocket motor grain according to an embodiment of the present invention. Figure 1 As shown, the process includes the following steps:

[0045] Step S101, dividing the grain model based on preset geometric symmetry parameters of the solid motor grain model to obtain a minimum symmetric unit grain model;

[0046] Specifically, the embodiment of the present invention divides the grain model based on geometric symmetry parameters, and only needs to process the minimum symmetric unit grain model, without having to operate the entire complex grain model, which greatly reduces the amount of calculation and the complexity of modeling, and improves the efficiency of modeling. The geometric symmetry parameters are determined according to the wing distribution of the grain. In one example, the wing column type grain model with 8 wings at the front and 8 wings at the rear (such as Figure 2 As shown in the figure, the drug column model is divided into 1 / 16 drug column models (as shown in the figure) Figure 3 shown).

[0047] The wing distribution of the grain is its important geometric feature. The embodiment of the present invention is determined based on the wing distribution of the grain based on the geometric symmetry parameters, which can accurately find the minimum symmetry unit, simplify the modeling process, reduce the amount of calculation, and at the same time will not miss key structural information. The wing distribution affects the combustion surface changes and airflow distribution during the combustion of the grain. Determining the symmetry parameters based on it for simulation can more realistically reflect the combustion conditions of the grain in actual work, making the simulation results more reliable.

[0048] Step S102: extract multiple inner surfaces of the minimum symmetrical unit charge model, and join the multiple inner surfaces to obtain an initial burning surface.

[0049] Specifically, when processing the minimum symmetrical unit charge model, the embodiment of the present invention accurately extracts and joins multiple inner surfaces to obtain the initial combustion surface, such as Figure 4 As shown in the figure, the initial burning surface can accurately reflect the starting state of the grain combustion, providing an accurate basis for the subsequent burning surface advancement simulation and avoiding the loss of accuracy caused by simplifying the model.

[0050] Step S103, using the initial burning surface as an offset object of the geometric body, and offsetting the initial burning surface based on preset offset parameters to obtain a thickened curved surface geometric body;

[0051] Specifically, the offset parameters in the embodiment of the present invention include: initial offset thickness, offset thickness interval and offset times, wherein the initial offset thickness is less than the preset grain thickness (e.g. 0.01 mm), and the offset thickness interval * offset times ≤ preset grain thickness. The initial offset thickness represents the first displacement distance when the burning surface starts to move, and is less than the preset grain thickness, and is used to set the starting change amount. The offset thickness interval is a fixed distance for each displacement of the burning surface, and together with the offset times, determines the final total displacement of the burning surface. The offset times: the total number of times the burning surface performs an offset operation, multiplied by the offset thickness interval is less than or equal to the preset grain thickness, and can flexibly control the precision of the burning surface displacement process. By reasonably setting these three parameters, the displacement of the burning surface can be simulated in stages and at a fixed distance, accurately restoring the changes in the burning surface during the combustion of the grain, and improving the simulation accuracy. Different combinations of initial offset thickness, offset thickness interval and offset times can adapt to a variety of grain structures and combustion characteristics, and meet diverse simulation needs.

[0052] The initial burning surface is used as the offset object, and the offset is performed based on the preset offset parameters to obtain the thickened surface geometry. This method can more realistically simulate the movement of the burning surface of the grain during the combustion process, taking into account the changing law of the burning surface during the combustion of the grain, making the simulation results closer to the actual combustion process.

[0053] Step S104 , removing the thickened curved surface geometry from the minimum symmetrical unit grain model and restoring the original model to obtain a solid motor grain model after the combustion surface is shifted.

[0054] Specifically, the thickened curved surface geometry of the embodiment of the present invention is removed from the minimum symmetrical unit grain model and the original model is restored. The resulting solid engine grain model after the combustion surface is moved can display the shape of the grain after a certain combustion time, and intuitively reflect the gradual change of the combustion surface over time. This helps researchers analyze the changes in various parameters during the grain combustion process and provides a reliable basis for engine design and performance optimization.

[0055] In one embodiment, based on Figure 3 The 1 / 16 grain model and Figure 4 The initial burning surface in the process of moving the burning surface, such as Figure 5 As shown, Figure 5 Column (a) shows the corresponding thickened surface geometry after 6 shifts with the preset offset thickness, and column (b) shows the corresponding thickened surface geometry after 6 shifts with the preset offset thickness. Figure 3 The state after the minimum symmetric unit of the grain model is removed, (c) is listed as Figure 2 The shown grain model corresponds to the states of the six shifts in the burning surface.

[0056] The automatic movement of the burning surface of the solid rocket motor grain provided by the embodiment of the present invention can display the combustion status of the grain in advance on a computer through accurate automatic movement simulation of the burning surface, thereby improving the efficiency and accuracy of the burning surface movement process and reducing research and development costs and time.

[0057] In one embodiment, after the burning surface is moved, Figure 6 As shown, it also includes:

[0058] Step S105, recording the burning area, grain mass, grain volume and center of mass position during the automatic movement process.

[0059] Specifically, the data is recorded for the combustion area, grain mass, grain volume, and center of mass position corresponding to the offset thickness of the automatic displacement process and the displacement of the combustion surface. The combustion area is directly related to the engine's combustion chamber pressure and thrust. Recording it can be used to calculate parameters such as combustion chamber pressure and engine thrust. The grain mass is used to calculate the remaining mass of the propellant, and the grain volume is used to calculate the combustion surface or the grain mass. The center of mass position is crucial to the rocket's flight stability. Recording its changes can timely adjust the flight attitude control strategy to prevent instability during flight. By recording this data, a basis for controlling the operating parameters of the solid rocket engine is provided. By analyzing this data at different stages, it can also be used to optimize the shape and size of the grain and improve the overall performance of the engine.

[0060] In practical applications, the above process can be implemented with the help of existing three-dimensional model design software. In the embodiment of the present invention, CATIA (Computer Aided Three-dimensional Interactive Application) software is used as an example. After the grain model is segmented by the software and the minimum symmetrical unit grain model is obtained, the "Join" function in the "Wireframe and Surface Design" of CATIA is used to select the initial burning surface of the grain for joining. A new geometric body is created in CATIA as the thickened curved surface geometric body; the "Macro" function in CATIA is used to record the following burning surface shifting operations:

[0061] 1. Define the created thickened surface geometry as a work object, click the "Thick Surface" function, select the initial combustion surface joined in step 2 as the "Object to Offset", and enter an initial "Offset Thickness". The initial "Offset Thickness" should be smaller than the grain thickness, for example 0.01mm;

[0062] 2. Use the "Remove" function to remove the thickened surface geometry from the segmented grain model;

[0063] 3. Use the "Mirror" and "Circular Array" functions to restore the complete grain model and end macro recording;

[0064] 4. Open the recorded "macro", edit the VBA language in the recorded macro program, write a For loop for the "offset thickness", set the offset thickness interval, and realize the automatic displacement of the burning surface through the For loop.

[0065] In one embodiment, the thickness of the grain is 500.25 mm, and the offset thickness interval is 0.5 mm, and the For loop is automatically executed 1000 times, that is, the grain is shifted backward 1000 times at 0.5 mm intervals, for a total shift of 500 mm. The For loop code is as follows:

[0066]

[0067] Furthermore, open the recorded "macro", edit the VBA language in the recorded macro program, write a program to export data to a spreadsheet file, obtain the mass and volume of the grain column moving the burning surface, and calculate the burning area using the following formula:

[0068]

[0069] Where i represents the number of offsets, A represents the burning area, V represents the volume of the grain, and w represents the offset thickness interval.

[0070] The formula provided in this embodiment of the present invention takes into account the number of offsets, which represents the progression of the grain's burning surface. This number can reflect the dynamic changes in the burning surface over time or over the combustion process, facilitating tracking of changes in the burning area throughout the combustion process. The calculation also incorporates the grain volume V, taking into account the fundamental properties of the grain itself. Grains of varying volumes have different initial conditions. This formula allows the calculation of the burning area to be correlated with the grain's own characteristics, making the calculation more realistic. The offset thickness interval w is a customizable parameter that precisely controls the quantification of the burning surface's progression, ensuring that the calculated results more closely meet the simulation's accuracy requirements and facilitating more accurate analysis of the combustion process.

[0071] The data acquisition code written in the embodiment of the present invention is as follows:

[0072]

[0073]

[0074] The exported data table is as follows Figure 7 shown.

[0075] In the embodiment of the present invention, the grain is divided according to the symmetry of the grain model, the "join" function of CATIA is used to select the initial combustion surface, CATIA modeling and the "macro" function are used to move the combustion surface, and VBA language is used for secondary development to achieve automatic movement of the combustion surface of the solid rocket motor grain at specified intervals and automatic acquisition of relevant data, thereby improving the efficiency and accuracy of the combustion surface movement.

[0076] This embodiment also provides a method and system for automatically advancing the burning surface of a solid rocket motor grain. This system is used to implement the above-mentioned embodiments and preferred implementations, and details already described will not be repeated. As used below, the term "module" may refer to a combination of software and / or hardware that implements a predetermined function. Although the devices described in the following embodiments are preferably implemented in software, implementation using hardware, or a combination of software and hardware, is also possible and contemplated.

[0077] The embodiment of the present invention provides a method and system for automatically moving the burning surface of a solid rocket motor grain. Figure 8 Shown, including:

[0078] The model segmentation module 801 is used to extract multiple inner surfaces of the minimum symmetrical unit grain model and to join the multiple inner surfaces to obtain an initial burning surface;

[0079] An initial burning surface acquisition module 802 is configured to use the initial burning surface as an offset object of a geometric body, and offset the initial burning surface based on preset offset parameters to obtain a thickened curved surface geometric body;

[0080] The thickened surface geometry acquisition module 803 is used to add the lateral moment of inertia of the propellant and the lateral moment of inertia of the solid part to obtain an evaluation result of the lateral moment of inertia of the liquid rocket upper stage;

[0081] The model restoration model 804 is used to remove the thickened surface geometry from the minimum symmetrical unit grain model and then restore the original model to obtain the solid motor grain model after the combustion surface is moved.

[0082] In some optional embodiments, the above system also includes: a data recording module for recording the combustion area, charge mass, charge volume and center of mass position corresponding to the offset thickness of the moving burning surface during the automatic movement process.

[0083] In some optional embodiments, the offset parameters in the initial combustion surface acquisition module 802 include: initial offset thickness, offset thickness interval and number of offsets, wherein the initial offset thickness is less than the preset grain thickness, and the offset thickness interval * number of offsets ≤ the preset grain thickness.

[0084] In some optional embodiments, the combustion area is calculated according to the following formula:

[0085]

[0086] Where i represents the number of offsets, A represents the burning area, V represents the volume of the grain, and w represents the offset thickness interval.

[0087] In some optional embodiments, the geometric symmetry parameters in the model segmentation module 801 are determined according to the wing distribution of the charge.

[0088] The further functional description of each of the above modules and units is the same as that of the above corresponding embodiments and will not be repeated here.

[0089] The method and device for automatically advancing the burning surface of a solid rocket engine grain in this embodiment is presented in the form of a functional unit, where the unit refers to an ASIC (Application Specific Integrated Circuit) circuit, a processor and memory that executes one or more software or fixed programs, and / or other devices that can provide the above functions.

[0090] The embodiment of the present invention also provides a computer device having the above Figure 8 The solid rocket motor grain combustion surface automatic advancement method system shown.

[0091] See also Figure 9 , Figure 9 is a schematic diagram of the structure of a computer device provided by an optional embodiment of the present invention, such as Figure 9 As shown, the computer device includes: one or more processors 10, memory 20, and interfaces for connecting various components, including high-speed interfaces and low-speed interfaces. Various components utilize different buses to communicate with each other and can be installed on a common mainboard or installed in other ways as needed. The processor can process the instructions executed in the computer device, including instructions stored in the memory or on the memory to display the graphical information of the GUI on an external input / output device (such as, a display device coupled to the interface). In some optional embodiments, if necessary, multiple processors and / or multiple buses can be used together with multiple memories and multiple memories. Equally, multiple computer devices can be connected, and each device provides part of the necessary operations (for example, as a server array, a group of blade servers, or a multi-processor system). Figure 9 A processor 10 is taken as an example.

[0092] The processor 10 may be a central processing unit, a network processor, or a combination thereof. The processor 10 may further include a hardware chip. The hardware chip may be an application-specific integrated circuit, a programmable logic device, or a combination thereof. The programmable logic device may be a complex programmable logic device, a field programmable gate array, a general purpose array logic, or any combination thereof.

[0093] The memory 20 stores instructions that can be executed by at least one processor 10, so as to enable at least one processor 10 to execute the method shown in the above embodiment.

[0094] The memory 20 may include a program storage area and a data storage area, wherein the program storage area may store an operating system and application programs required for at least one function; the data storage area may store data created based on the use of the computer device, etc. In addition, the memory 20 may include a high-speed random access memory, and may also include a non-transient memory, such as at least one disk storage device, a flash memory device, or other non-transient solid-state storage device. In some optional embodiments, the memory 20 may optionally include a memory remotely located relative to the processor 10, and these remote memories may be connected to the computer device via a network. Examples of the above-mentioned network include, but are not limited to, the Internet, an intranet, a local area network, a mobile communication network, and combinations thereof.

[0095] The memory 20 may include a volatile memory, such as a random access memory; the memory may also include a non-volatile memory, such as a flash memory, a hard disk or a solid-state drive; the memory 20 may also include a combination of the above types of memory.

[0096] The computer device further includes a communication interface 30 for the computer device to communicate with other devices or a communication network.

[0097] The embodiment of the present invention also provides a computer-readable storage medium. The above-mentioned method according to the embodiment of the present invention can be implemented in hardware, firmware, or implemented as a computer code that can be recorded in a storage medium, or implemented as a computer code that is originally stored in a remote storage medium or a non-temporary machine-readable storage medium and downloaded through a network and will be stored in a local storage medium, so that the method described herein can be stored in such software processing on a storage medium using a general-purpose computer, a dedicated processor, or programmable or dedicated hardware. Among them, the storage medium can be a magnetic disk, an optical disk, a read-only storage memory, a random access memory, a flash memory, a hard disk or a solid-state drive, etc.; further, the storage medium can also include a combination of the above-mentioned types of memory. It can be understood that a computer, a processor, a microprocessor controller or programmable hardware includes a storage component that can store or receive software or computer code. When the software or computer code is accessed and executed by a computer, a processor or hardware, the method shown in the above embodiment is implemented.

[0098] A portion of the present invention may be applied as a computer program product, such as a computer program instruction, which, when executed by a computer, can call or provide the method and / or technical solution according to the present invention through the operation of the computer. Those skilled in the art should understand that the form in which the computer program instruction exists in a computer-readable medium includes, but is not limited to, a source file, an executable file, an installation package file, etc. Accordingly, the way in which the computer program instruction is executed by the computer includes, but is not limited to: the computer directly executes the instruction, or the computer compiles the instruction and then executes the corresponding compiled program, or the computer reads and executes the instruction, or the computer reads and installs the instruction and then executes the corresponding installed program. Here, the computer-readable medium may be any available computer-readable storage medium or communication medium that can be accessed by the computer.

[0099] Although the embodiments of the present invention have been described with reference to the accompanying drawings, those skilled in the art may make various modifications and variations without departing from the spirit and scope of the present invention. Such modifications and variations are all within the scope defined by the appended claims.

Claims

1. A method for automatically moving the burning surface of a solid rocket motor grain, characterized in that: include: The grain model is divided based on the preset geometric symmetry parameters of the solid motor grain model to obtain the minimum symmetric unit grain model; Extracting multiple inner surfaces of the minimum symmetrical unit grain model and joining the multiple inner surfaces to obtain an initial burning surface; Taking the initial burning surface as an offset object of a geometric body, offsetting the initial burning surface based on preset offset parameters to obtain a thickened curved surface geometric body; After removing the thickened surface geometry from the minimum symmetric unit grain model, the original model is restored to obtain the solid motor grain model after the combustion surface is moved.

2. The method according to claim 1, characterized in that Also includes: Record the burning area, grain mass, grain volume and center of mass position during the automatic movement process.

3. The method according to claim 2, characterized in that The offset parameters include: initial offset thickness, offset thickness interval and offset times, wherein the initial offset thickness is less than the preset grain thickness, and the offset thickness interval*offset times≤preset grain thickness.

4. The method according to claim 3, characterized in that The burning area is calculated according to the following formula: Where i represents the number of offsets, A represents the burning area, V represents the volume of the grain, and w represents the offset thickness interval.

5. The method according to claim 1, wherein The geometric symmetry parameters are determined based on the wing distribution of the grain.

6. A method and system for automatically moving the burning surface of a solid rocket motor grain, characterized in that: The system comprises: A model segmentation module is used to segment the grain model based on the preset geometric symmetry parameters of the solid motor grain model to obtain the minimum symmetric unit grain model; An initial burning surface acquisition module is used to extract multiple inner surfaces of the minimum symmetrical unit grain model and to join the multiple inner surfaces to obtain an initial burning surface; a thickened curved surface geometry acquisition module, configured to use the initial burning surface as an offset object of a geometry, and offset the initial burning surface based on preset offset parameters to obtain a thickened curved surface geometry; The model restoration model is used to remove the thickened surface geometry from the minimum symmetric unit grain model and then restore the original model to obtain the solid motor grain model after the combustion surface is moved.

7. The system according to claim 6, characterized in that Also includes: The data recording module is used to record the burning area, grain mass, grain volume and center of mass position during the automatic movement process.

8. A computer device, characterized in that: include: A memory and a processor, wherein the memory and the processor are communicatively connected to each other, the memory stores computer instructions, and the processor executes the method for automatically advancing the burning surface of a solid rocket engine grain according to any one of claims 1 to 5 by executing the computer instructions.

9. A computer-readable storage medium, characterized in that The computer-readable storage medium stores computer instructions, which are used to enable a computer to execute the method for automatically advancing the burning surface of a solid rocket motor grain according to any one of claims 1 to 5.

10. A computer program product, characterized in that The method comprises computer instructions for causing a computer to execute the method for automatically advancing the burning surface of a solid rocket motor grain according to any one of claims 1 to 5.

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