Balanced rotating speed estimation method and device of projectile and storage medium

Abstract

Embodiments of the present specification provide a method and device for estimating the equilibrium rotation speed of a projectile and a storage medium, wherein the method comprises: constructing a projectile geometric model according to preset projectile data and a preset tail wing angle; performing steady calculation according to preset working condition data based on the projectile geometric model to obtain surface flow field data and spatial flow field data; obtaining the average value of the center of pressure or the center of mass coordinates on each tail wing of the projectile and the average value of the center of pressure or the center of mass distance from the projectile axis radius according to the surface flow field data; obtaining the average value of the speed according to the spatial flow field data, the average value of the center of pressure or the center of mass coordinates and the average value of the center of pressure or the center of mass distance from the projectile axis radius; and obtaining the equilibrium rotation speed of the projectile according to the average value of the center of pressure or the center of mass distance from the projectile axis radius, the average value of the speed and the preset tail wing angle. The data acquisition accuracy and the calculation efficiency can be improved at the same time, so that the equilibrium rotation speed calculation result is more accurate.

Description

TECHNICAL FIELD

[0001] The present document relates to the field of aerodynamics, and in particular to a method and device for estimating the equilibrium rotation speed of a projectile, and a storage medium. BACKGROUND

[0002] The equilibrium rotation speed of a projectile with a set-back fin determines the stability and shooting accuracy of the projectile.

[0003] The prior art mainly estimates the equilibrium rotation speed of a projectile with a set-back fin by an engineering estimation method based on fin geometric parameters and incoming flow parameters, or an interpolation calculation method based on CFD numerical calculation to obtain rolling moment coefficients at different rolling angular velocities.

[0004] However, the engineering estimation method in the prior art needs to use prior knowledge, such as a nonlinear correction coefficient related to the shape, a compressibility correction coefficient related to the flow, a friction drag coefficient of a flat plate, etc. These prior data cannot cover all states, resulting in a large error in the estimated value of the equilibrium rotation speed. The interpolation calculation method uses non-steady flow field calculation, which needs to carry out non-steady flow field calculation at a constant rolling angular velocity, and needs a long time and low calculation efficiency. SUMMARY

[0005] In view of the above solutions, the present application aims to provide a method and device for estimating the equilibrium rotation speed of a projectile, and a storage medium, to solve at least one of the above technical problems.

[0006] In a first aspect, one or more embodiments of the present specification provide a method for estimating the equilibrium rotation speed of a projectile with a set-back fin, comprising:

[0007] constructing a projectile geometric model according to preset projectile data and a preset set-back fin angle;

[0008] based on the projectile geometric model, performing steady calculation according to preset working condition data to obtain surface flow field data and spatial flow field data;

[0009] obtaining the average value of the center of pressure or the center of mass coordinates on each fin of the projectile and the average value of the center of pressure or the center of mass distance from the projectile axis radius according to the surface flow field data;

[0010] obtaining the average value of the velocity according to the spatial flow field data, the average value of the center of pressure or the center of mass coordinates, and the average value of the center of pressure or the center of mass distance from the projectile axis radius; and

[0011] obtaining the equilibrium rotation speed of the projectile according to the average value of the center of pressure or the center of mass distance from the projectile axis radius, the average value of the velocity, and the preset set-back fin angle.

[0012] Further, the projectile geometric model is meshed to obtain a computational fluid dynamics mesh;

[0013] Set the height and speed of the projectile according to the preset working condition data; and

[0014] According to the height and speed of the projectile, surface flow field data and spatial flow field data of the projectile are determined using a computational fluid dynamics grid.

[0015] Furthermore, based on the surface flow field data, the coordinates of the pressure center or the centroid of each tail fin on the projectile are extracted; and

[0016] According to the coordinates of the pressure center or the centroid of each tail fin, an average value of the coordinates of the pressure center or the centroid and an average value of the radius of the pressure center or the centroid from the missile axis are obtained.

[0017] Furthermore, an isosurface value is obtained based on the spatial flow field data and an average value of the radius from the pressure center or the centroid to the projectile axis;

[0018] Obtaining an isoline value based on the isosurface value and the average value of the pressure center or centroid coordinates; and

[0019] According to the isosurface value and the isoline value, an average value of the velocity on the isoline is obtained.

[0020] Furthermore, the calculation formula of the equilibrium rotation speed of the projectile is as follows:

[0021] ω x = u * *sin(δ) / r*

[0022] Among them, ω x Indicates the equilibrium speed;

[0023] x represents the coordinate axis;

[0024] u * Indicates the average speed;

[0025] δ represents the tail wing cant angle; and

[0026] r* represents the average value of the radius from the compression center or centroid to the projectile axis.

[0027] In a second aspect, an embodiment of the present application provides a device for estimating a balanced rotational speed of a projectile having an oblique tail fin, comprising:

[0028] A construction module, used for constructing a projectile geometric model according to preset projectile data and preset tail fin tilt angle;

[0029] A data acquisition module is used to perform steady calculations based on the projectile geometric model and preset working condition data to obtain surface flow field data and spatial flow field data;

[0030] A first calculation module is used to obtain the average value of the coordinates of the pressure center or the centroid on each tail fin of the projectile and the average value of the radius of the pressure center or the centroid from the projectile axis based on the surface flow field data;

[0031] A second calculation module is configured to obtain an average velocity value based on the spatial flow field data, an average value of the pressure center or the centroid coordinates, and an average value of the radius of the pressure center or the centroid from the projectile axis; and

[0032] The third calculation module is used to obtain the equilibrium rotation speed of the projectile according to the average value of the radius of the pressure center or the centroid from the projectile axis, the average speed and the preset tail fin tilt angle.

[0033] Furthermore, the data acquisition module is configured to:

[0034] Meshing the projectile geometric model to obtain a computational fluid dynamics grid;

[0035] Set the height and speed of the projectile according to the preset working condition data; and

[0036] According to the height and speed of the projectile, surface flow field data and spatial flow field data of the projectile are determined using a computational fluid dynamics grid.

[0037] Furthermore, the first computing module is configured to:

[0038] Extracting the center of pressure or center of shape coordinates of each tail fin on the projectile based on the surface flow field data; and

[0039] According to the coordinates of the pressure center or the centroid of each tail fin, an average value of the coordinates of the pressure center or the centroid and an average value of the radius of the pressure center or the centroid from the missile axis are obtained.

[0040] Furthermore, the second computing module is configured to:

[0041] Obtaining an isosurface value based on the spatial flow field data and an average value of the radius from the pressure center or the centroid to the projectile axis;

[0042] Obtaining an isoline value based on the isosurface value and the average value of the pressure center or centroid coordinates; and

[0043] According to the isosurface value and the isoline value, an average value of the velocity on the isoline is obtained.

[0044] In a third aspect, an embodiment of the present application provides a storage medium for storing computer-executable instructions, characterized in that when the computer-executable instructions are executed, the steps of the method for estimating the equilibrium rotational speed of a projectile with an oblique tail fin described in any one of the first aspects are implemented.

[0045] Compared with the existing technology, this application can at least achieve the following technical effects:

[0046] The application can estimate the balanced rotating speed of the oblique tail fin projectile geometric model under any working condition, improve the acquisition accuracy of the data source, and only needs to carry out a steady calculation on the oblique tail fin projectile geometric model, thereby improving the calculation efficiency and the result accuracy. BRIEF DESCRIPTION OF DRAWINGS

[0047] In order to more clearly illustrate the technical solutions in the one or more embodiments of the present specification or the prior art, the drawings needed to be used in the embodiment or prior art description will be briefly introduced as follows. Obviously, the drawings in the following description are only some embodiments described in the present specification, and other drawings can be obtained by those skilled in the art without creative labor.

[0048] Figure 1 A balanced rotating speed estimation method flow chart of a projectile with an oblique tail fin is provided for one or more embodiments of the present specification.

[0049] Figure 2 A geometric model diagram of an oblique tail fin projectile is provided for one or more embodiments of the present specification.

[0050] Figure 3 A balanced rotating speed estimation device structural schematic diagram of a projectile with an oblique tail fin is provided for one or more embodiments of the present specification. DETAILED DESCRIPTION

[0051] In order to make the person skilled in the art better understand the technical solutions in the one or more embodiments of the present specification, the technical solutions in the one or more embodiments of the present specification will be clearly and completely described below in combination with the drawings in the one or more embodiments of the present specification. Obviously, the described embodiments are only some embodiments of the present specification, not all embodiments. Based on the one or more embodiments of the present specification, all other embodiments obtained by those skilled in the art without creative labor should belong to the protection scope of the present document.

[0052] Currently, there are mainly two methods for estimating the balance rotation speed of a rotating projectile. One is an engineering estimation method based on the geometric parameters of the tail wing and the flow parameters, and the other is an interpolation calculation method based on the rolling moment coefficient at different rolling angular velocities obtained by CFD numerical calculation. The engineering estimation method is fast, and only the shape parameters and corresponding working condition parameters are needed to carry out the calculation, but the error is large, about 10%, and prior knowledge is also needed, such as the nonlinear correction coefficient related to the shape, the compressibility correction coefficient related to the flow, the friction resistance coefficient of the flat plate, etc. The coefficients obtained from public data cannot cover all states, so the engineering estimation method cannot be used in some working conditions due to large errors; the interpolation method has higher calculation accuracy, and the error is less than 10%, but the interpolation method needs to carry out more unsteady flow field calculations at constant rolling angular velocities. The interpolation method needs at least two unsteady calculations to estimate the balance rotation speed, and one unsteady flow field needs about 1 / 2 times of the calculation time of a steady flow field, which is equivalent to carrying out more than 20 steady calculations.

[0053] In view of the above technical problems, the present application provides a balance rotation speed estimation method for a projectile with a skew tail wing, as shown in Figure 1 The specific steps are as follows:

[0054] Step S1, constructing a projectile geometric model according to preset projectile data and preset tail wing skew angle.

[0055] In the embodiment of the present application, the preset projectile data includes the length, diameter, head shape, number and size of the tail wing, etc. of the projectile. A suitable three-dimensional coordinate system (such as Cartesian coordinate system) is selected to determine the origin (usually the geometric center or tail of the projectile); then the main part of the projectile is drawn using a geometric modeling software according to the basic size data of the projectile. According to the preset number, size and skew angle of the tail wing, etc., the tail wing is added to the tail of the projectile. The skew angle of the tail wing can ensure that each tail wing is skewed at the preset angle to ensure the stability of the projectile during flight. Finally, the measurement tool of the geometric modeling software is used to verify whether the size of the projectile and the skew angle of the tail wing meet the preset data, and the adjustment is made as needed until the design requirements are met. Finally, a well-constructed projectile geometric model is obtained.

[0056] Step S2, based on the projectile geometric model, performing steady calculation according to preset working condition data to obtain surface flow field data and spatial flow field data.

[0057] In the embodiment of the present application, the projectile geometric model is meshed to obtain a computational fluid dynamics mesh; the height and speed of the projectile are set according to the preset working condition data; and the surface flow field data and spatial flow field data of the projectile are determined by using the computational fluid dynamics mesh according to the height and speed of the projectile.

[0058] Specifically, the projectile geometry model is meshed using mesh generation software to generate a computational fluid dynamics mesh file. Then, a suitable CFD solver is selected and the generated mesh is imported. Collect and prepare all necessary operating condition data, set the operating condition data for the projectile, including height and speed data, for example: select the case of 5000 meters in height and 1000 m / s in speed to estimate the balance speed. Perform CFD steady-state calculation under the given operating condition, start the solution process, monitor the convergence, and adjust the iteration parameters as necessary until a stable solution is obtained. After the calculation converges, extract the surface flow field data (such as pressure distribution, temperature, etc.) and spatial flow field data (such as velocity field, temperature field, pressure field, velocity components in each direction, etc.).

[0059] Step S3, according to the surface flow field data, the average value of the pressure center or centroid coordinates on each fin of the projectile and the average value of the pressure center or centroid distance from the projectile axis radius are obtained.

[0060] In the embodiments of the present application, according to the surface flow field data, the pressure center or centroid coordinates of each fin on the projectile are extracted; and according to the pressure center or centroid coordinates of each fin, the average value of the pressure center or centroid coordinates and the average value of the pressure center or centroid distance from the projectile axis radius are obtained.

[0061] Specifically, in the post-processing software Tecplot, first, identify the fin area, extract the pressure center or centroid coordinates (X, Y, Z) on each fin, the coordinate X axis coincides with the projectile axis, as shown in Figure 2 , both forward and backward; the coordinate Y axis and the coordinate Z axis are perpendicular to the coordinate X axis. Among them, the pressure center is the equivalent point of the aerodynamic force acting on the object, which is usually calculated by integrating the pressure distribution; the centroid is the "geometric center" of the geometric body, which is obtained by calculating the centroid of the geometric shape. Secondly, the X axis of the pressure center or centroid coordinates of each fin is summed up, and then divided by the number of fins to obtain the average value of the pressure center or centroid coordinates. According to the coordinates or direction of the projectile axis, the distance from each fin pressure center or centroid to the projectile axis is calculated; the distances are summed up, and then according to the data of the fin, the average value of the pressure center or centroid distance from the projectile axis radius is obtained.

[0062] For example: if you have 4 fins, and the pressure center coordinates of each fin are (x1, y1, z1), (x2, y2, z2), (x3, y3, z3) and (x4, y4, z4) respectively, then the average coordinates are ((x1+x2+x3+x4) / 4, if the distances from the pressure centers of the 4 fins to the projectile axis are d1, d2, d3 and d4 respectively, then the average radius is (d1+d2+d3+d4) / 4.

[0063] Step S4, according to the spatial flow field data, the average value of the pressure center or centroid coordinates and the average value of the pressure center or centroid distance from the projectile axis radius, the average value of the velocity is obtained.

[0064] In the embodiment of the present application, an isosurface value is obtained according to the space flow field data and the average value of the distance between the center of pressure or the centroid and the radius of the projectile axis, an isocline value is obtained according to the isosurface value and the average value of the coordinates of the center of pressure or the centroid, and an average value of the velocity on the isocline is obtained according to the isosurface value and the isocline value.

[0065] Specifically, using the space flow field data, an isosurface is generated by setting the distance from the projectile axis equal to the average value of the radius of the center of pressure or the centroid by using the post-processing software Tecplot. The isosurface refers to a surface with equal values of a specific variable (such as velocity, pressure, etc.), that is, an isosurface formed by the variable (such as velocity, pressure, etc.) in the flow field. An isocline is generated on the isosurface by setting the x coordinate equal to the average value of the x coordinate of the center of pressure or the centroid. The isocline value refers to a line on the isosurface with equal values of the variable in a specific direction (such as a direction perpendicular to the isosurface). Finally, the velocity data of each point on the isocline is extracted, and the average value of the velocity is obtained according to the velocity data of each point.

[0066] In step S5, the equilibrium rotating speed of the projectile is obtained according to the average value of the distance between the center of pressure or the centroid and the radius of the projectile axis, the average value of the velocity, and a preset tail wing oblique angle.

[0067] In the embodiment of the present application, the average value of the velocity u * is multiplied by the sine value of the tail wing oblique angle δ, and the obtained product is divided by the average value r* of the distance between the center of pressure or the centroid and the radius of the projectile axis, to obtain the equilibrium rotating speed.

[0068] ω x = u * *sin(δ) / r*

[0069] wherein ω x represents the equilibrium rotating speed;

[0070] x represents a coordinate;

[0071] u * represents the average value of the velocity;

[0072] δ represents the tail wing oblique angle;

[0073] r* represents the average value of the distance between the center of pressure or the centroid and the radius of the projectile axis;

[0074] The application can estimate the balance rotating speed without prior knowledge, is suitable for any inclined tail fin projectile model and any working condition, and has a larger working condition application range than the engineering estimation method. The application uses the processing result of the static flow field in the inclined tail fin projectile model, has more reliable flow field data basis than the engineering estimation method, and has higher result precision. In the application, only one steady CFD calculation is needed for the inclined tail fin projectile model, the calculation time is less than that of the interpolation calculation method, and the balance rotating speed can be estimated more quickly.

[0075] The application embodiment provides a balance rotating speed estimation device of a projectile with an inclined tail fin, as shown in the accompanying drawings, comprising: Figure 3

[0076] The construction module 101 is configured to construct a projectile geometric model according to preset projectile data and a preset tail fin inclination angle.

[0077] The data acquisition module 102 is configured to obtain surface flow field data and spatial flow field data by performing steady calculation according to preset working condition data based on the projectile geometric model.

[0078] The first calculation module 103 is configured to obtain the average value of the center of pressure or the center of mass coordinates of each tail fin of the projectile and the average value of the center of pressure or the center of mass distance from the projectile axis radius according to the surface flow field data.

[0079] The second calculation module 104 is configured to obtain the average value of the velocity according to the spatial flow field data, the average value of the center of pressure or the center of mass coordinates, and the average value of the center of pressure or the center of mass distance from the projectile axis radius.

[0080] The third calculation module 105 is configured to obtain the balance rotating speed of the projectile according to the average value of the center of pressure or the center of mass distance from the projectile axis radius, the average value of the velocity, and the preset tail fin inclination angle.

[0081] Further, the data acquisition module is configured to:

[0082] perform grid division on the projectile geometric model to obtain a computational fluid dynamics grid;

[0083] set the height and speed of the projectile according to preset working condition data; and

[0084] determine the surface flow field data and the spatial flow field data of the projectile by using the computational fluid dynamics grid according to the height and speed of the projectile.

[0085] Further, the first calculation module is configured to:

[0086] extract the center of pressure or the center of mass coordinates of each tail fin of the projectile according to the surface flow field data; and

[0087] ​According to the pressure center or centroid coordinates of each tail wing, an average value of the pressure center or centroid coordinates and an average value of the pressure center or centroid distance from the projectile axis radius are obtained.

[0088] Further, the second calculation module is configured to:

[0089] According to the space flow field data and the average value of the pressure center or centroid distance from the projectile axis radius, an isosurface value is obtained.

[0090] According to the isosurface value and the average value of the pressure center or centroid coordinates, an isocline value is obtained; and

[0091] According to the isosurface value and the isocline value, an average value of the velocity on the isocline is obtained.

[0092] The embodiment of the present application provides a storage medium for storing computer executable instructions, which, when executed, implement the steps of the balance rotating speed estimation method of the projectile with an inclined tail wing in any one of the above-mentioned embodiments.

[0093] It should be noted that the embodiment of the storage medium in the present specification and the embodiment of the balance rotating speed estimation method of the projectile in the present specification are based on the same inventive concept, and therefore the specific implementation of this embodiment can be referred to the foregoing implementation of the corresponding balance rotating speed estimation method of the projectile, and the repeated parts will not be described herein.

[0094] The above describes specific embodiments of the present specification. Other embodiments are within the scope of the appended claims. In some cases, the acts or steps recited in the claims can be performed in an order other than that in the embodiments and still achieve desirable results. Additionally, the processes depicted in the figures do not necessarily require the particular order shown or sequential order in order to achieve the desired results. In some implementations, multitasking and parallel processing can be advantageous or possible.

[0095] In the 1930s, it was clear to distinguish whether an improvement in a technology was in hardware (e.g., improvement in circuit structure of diodes, transistors, switches, etc.) or in software (e.g., improvement in method flow). However, as technology has evolved, many improvements in method flow today can be considered as direct improvements in hardware circuit structure. Designers almost always obtain the corresponding hardware circuit structure by programming the improved method flow into the hardware circuit. Therefore, it cannot be said that an improvement in a method flow cannot be implemented using hardware entity modules. For example, a programmable logic device (PLD) (e.g., a field programmable gate array (FPGA)) is an integrated circuit whose logic function is determined by user programming of the device. A digital system is "integrated" on a PLD by the designer programming it, rather than by asking a chip manufacturer to design and fabricate a custom integrated circuit chip. Moreover, instead of manually fabricating integrated circuit chips, this programming is now mostly implemented using "logic compiler" software, which is similar to software compilers used in program development, and the original code before compilation is written in a specific programming language, which is called a hardware description language (HDL), and there are many HDLs, such as ABEL (Advanced Boolean Expression Language), AHDL (Altera Hardware Description Language), Confluence, CUPL (Cornell University Programming Language), HDCal, JHDL (Java Hardware Description Language), Lava, Lola, MyHDL, PALASM, RHDL (Ruby Hardware Description Language), etc., and the most commonly used are VHDL (Very-High-Speed Integrated Circuit Hardware Description Language) and Verilog. Those skilled in the art should be aware that only a little logical programming of the method flow in the above-mentioned hardware description languages and programming into an integrated circuit can easily obtain a hardware circuit that implements the logical method flow.

[0096] The controller can be implemented in any suitable way, for example, the controller can take the form of a microprocessor or processor and a computer readable medium storing computer readable program code, such as software or firmware, executable by the (micro)processor, logic gates, switches, an application specific integrated circuit (ASIC), a programmable logic controller and an embedded microcontroller, examples of which include but are not limited to the following microcontrollers: ARC 625D, Atmel AT91SAM, Microchip PIC18F26K20 and Silicone Labs C8051F320, the memory controller can also be implemented as part of the control logic of the memory. Those skilled in the art will also know that, in addition to implementing the controller in pure computer readable program code, it is also possible to implement the controller in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers and embedded microcontrollers, etc. to perform the same functions by logically programming the method steps. Such a controller can therefore be considered as a hardware component, and the means included therein for performing various functions can also be considered as structures within the hardware component. Alternatively, the means for performing various functions can even be considered as both a software module implementing the method and a structure within the hardware component.

[0097] The systems, apparatuses, modules or units illustrated by the above embodiments can be specifically implemented by computer chips or entities, or by products with certain functions. A typical implementation device is a computer. Specifically, the computer can be, for example, a personal computer, a laptop computer, a cellular phone, a camera phone, a smart phone, a personal digital assistant, a media player, a navigation device, an email device, a game console, a tablet computer, a wearable device, or a combination of any of these devices.

[0098] For the sake of description, the above apparatuses are described in functional division and are described respectively. Of course, the functions of the units can be implemented in the same or multiple software and / or hardware when implementing the embodiments of the present specification.

[0099] Those skilled in the art will appreciate that one or more embodiments of the specification can be provided as a method, a system or a computer program product. Therefore, one or more embodiments of the specification can take the form of a complete hardware embodiment, a complete software embodiment, or an embodiment combining software and hardware aspects. Moreover, the specification can take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to magnetic disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0100] This specification is described with reference to the flowcharts and / or block diagrams of the methods, devices (systems), and computer program products according to the embodiments of this specification. It should be understood that each process and / or block in the flowchart and / or block diagram, as well as the combination of processes and / or blocks in the flowchart and / or block diagram, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to produce a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowchart and / or block diagram. Figure 1 a process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0101] These computer program instructions may also be stored in a computer readable memory that can direct a computer or other programmable data processing device to work in a specific manner, so that the instructions stored in the computer readable memory produce an article of manufacture comprising an instruction device, which implements the process Figure 1 a process or multiple processes and / or boxes Figure 1 The function specified in one or more boxes.

[0102] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operational steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing the instructions executed on the computer or other programmable device for implementing the process. Figure 1 a process or multiple processes and / or boxes Figure 1 A step that specifies a function in one or more boxes.

[0103] In a typical configuration, a computing device includes one or more processors (CPUs), input / output interfaces, network interfaces, and memory.

[0104] Memory may include non-permanent storage in a computer-readable medium, random access memory (RAM) and / or non-volatile memory in the form of read-only memory (ROM) or flash RAM. Memory is an example of a computer-readable medium.

[0105] Computer-readable media includes permanent and non-permanent, movable and non-movable media that can be implemented by any method or technology to store information. The information can be computer-readable instructions, data structures, program modules or other data. Examples of computer storage media include, but are not limited to, phase change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technologies, compact disc read-only memory (CD-ROM), digital versatile disc (DVD) or other optical storage, magnetic cassette, magnetic tape, magnetic disk storage or other magnetic storage devices, or any other non-transmission medium that can be used to store information accessible to a computing device. According to the definition herein, computer-readable media does not include transitory media such as modulated data signals and carriers.

[0106] It should also be noted that the terms "comprising", "containing", or any other variant thereof are intended to cover non-exclusive inclusion, such that processes, methods, articles or devices that include a series of elements not only include those elements, but also include other elements not explicitly listed, or inherent to such processes, methods, articles or devices. Without more limitations, the element defined by the statement "comprising a" does not exclude the presence of additional identical elements in the process, method, article or device that includes the element.

[0107] One or more embodiments of the present specification can be described in the general context of computer-executable instructions being executed by a computer, such as program modules. Generally, program modules include routines, programs, objects, components, data structures, and the like that perform particular tasks or implement particular abstract data types. One or more embodiments of the present specification can also be practiced in a distributed computing environment, in which tasks are performed by remote processing devices connected through a communication network. In a distributed computing environment, program modules can be located in local and remote computer storage media, including storage devices.

[0108] Each embodiment in the present specification is described in a progressive manner, and the same or similar parts between each embodiment can be referred to each other, and each embodiment focuses on the difference from other embodiments. In particular, for system embodiments, since they are basically similar to method embodiments, the description is relatively simple, and the relevant parts can be referred to the part of the method embodiment.

[0109] The above merely provides the example of the present document and is not intended to limit the present document. For those skilled in the art, the present document can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. within the spirit and principle of the present document shall be included in the scope of claims of the present document.

Claims

1. A method of estimating the spin rate of a projectile having a canted tail fin, characterized by The method comprises the following steps: constructing a projectile geometric model according to preset projectile data and a preset tail wing skew angle; performing steady calculation according to preset working condition data based on the projectile geometric model to obtain surface flow field data and spatial flow field data; obtaining average values of pressure center or centroid coordinates and average values of pressure center or centroid radii from the projectile axis on each tail wing of the projectile according to the surface flow field data; obtaining a velocity average value according to the spatial flow field data, the average values of pressure center or centroid coordinates and the average values of pressure center or centroid radii from the projectile axis; obtaining a balance rotating speed of the projectile according to the average values of pressure center or centroid radii from the projectile axis, the velocity average value and the preset tail wing skew angle; wherein the velocity average value is obtained according to the spatial flow field data, the average values of pressure center or centroid coordinates and the average values of pressure center or centroid radii from the projectile axis, and the velocity average value comprises the following steps: obtaining an isosurface value according to the spatial flow field data and the average values of pressure center or centroid radii from the projectile axis; obtaining an isocline value according to the isosurface value and the average values of pressure center or centroid coordinates; obtaining an average value of velocities on the isocline according to the isosurface value and the isocline value.

2. The method according to claim 1, wherein the steady calculation based on the projectile geometric model according to preset working condition data to obtain surface flow field data and spatial flow field data comprises the following steps: performing mesh division on the projectile geometric model to obtain computational fluid dynamics mesh; setting the height and speed of the projectile according to preset working condition data; and determining the surface flow field data and the spatial flow field data of the projectile by using the computational fluid dynamics mesh according to the height and speed of the projectile.

3. The method according to claim 1, wherein the average values of pressure center or centroid coordinates and the average values of pressure center or centroid radii from the projectile axis on each tail wing of the projectile according to the surface flow field data comprise the following steps: extracting the pressure center or centroid coordinates of each tail wing on the projectile according to the surface flow field data; and obtaining the average values of pressure center or centroid coordinates and the average values of pressure center or centroid radii from the projectile axis according to the pressure center or centroid coordinates of each tail wing.

4. The method according to claim 1, wherein the balance rotating speed of the projectile is calculated according to the following formula: x represents a coordinate axis; δ represents a tail wing skew angle; and r* represents the average values of pressure center or centroid radii from the projectile axis. ω x = u * *sin(δ) / r* where ω x represents the equilibrium rotational speed; The method comprises the following steps: u * represents the average value of the speed; constructing a projectile geometric model according to preset projectile data and a preset tail wing skew angle by using a constructing module; obtaining surface flow field data and spatial flow field data by performing steady calculation according to preset working condition data based on the projectile geometric model by using a data acquisition module; 5. A device for estimating the equilibrium rotation speed of a projectile having a dihedral fin, characterized in that obtaining average values of pressure center or centroid coordinates and average values of pressure center or centroid radii from the projectile axis on each tail wing of the projectile according to the surface flow field data by using a first calculating module; obtaining a velocity average value according to the spatial flow field data, the average values of pressure center or centroid coordinates and the average values of pressure center or centroid radii from the projectile axis by using a second calculating module; obtaining a balance rotating speed of the projectile according to the average values of pressure center or centroid radii from the projectile axis, the velocity average value and the preset tail wing skew angle by using a third calculating module. ​ ​ ​ The second calculation module is configured to: obtain an isosurface value according to the space flow field data and the average value of the distance between the pressure center or the centroid and the radius of the projectile axis; obtain an isocline value according to the isosurface value and the average value of the pressure center or the centroid coordinate; obtain an average value of the velocity on the isocline according to the isosurface value and the isocline value.

6. The apparatus of claim 5, wherein The data acquisition module is configured to: divide the projectile geometric model into a computational fluid dynamics grid; set the height and the speed of the projectile according to preset working condition data; and determine the surface flow field data and the space flow field data of the projectile by using the computational fluid dynamics grid according to the height and the speed of the projectile.

7. The apparatus of claim 5, wherein The first calculation module is configured to: extract the pressure center or the centroid coordinate of each tail fin on the projectile according to the surface flow field data; and obtain the average value of the pressure center or the centroid coordinate and the average value of the distance between the pressure center or the centroid and the radius of the projectile axis according to the pressure center or the centroid coordinate of each tail fin.

8. A storage medium for storing computer-executable instructions, comprising: The computer executable instructions, when executed, implement the steps of the balance rotating speed estimation method of the projectile with inclined tail fins according to any one of claims 1-4.

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