A method, device, equipment and storage medium for simulating arc ground effect

Abstract

The present disclosure provides a method, an apparatus, a device, and a storage medium for simulating an arc ground effect, relating to the field of aerospace engineering. The method includes: setting a reference system that moves uniformly in a set direction; respectively determining a relative motion speed of a supersonic aircraft in the reference system, a horizontal motion speed and a sinking motion speed of a flat ground directly below the supersonic aircraft in the reference system; and performing dynamic simulation according to the relative motion speed of the supersonic aircraft in the reference system, the horizontal motion speed and the sinking motion speed of the flat ground in the reference system to determine the aerodynamic characteristics of the supersonic aircraft. The present disclosure can be applicable to simulating supersonic, large-curvature, and long-distance arc ground effects, and improving the calculation efficiency in the numerical simulation process.

Description

Technical Field

[0001] The present invention relates to the field of aerospace engineering, and in particular, to a method, device, equipment and storage medium for simulating arc ground effect. Background Art

[0002] In the existing numerical studies of ground effect, since the near-ground flight speed of near-ground aircraft is small and the orbital curvature is small, meeting the principle of flat ground hypothesis, it can be processed according to flat ground. Usually, the near-ground aircraft is selected as the reference system, and the ground and the distant air have the same speed as the flight speed but in the opposite direction relative to the near-ground aircraft.

[0003] When studying the process of near-ground electromagnetic launch vehicle and rocket separation, due to the lack of lift surface of the rocket and its insufficient lift relative to gravity, in order to quickly increase the vertical height difference, the concept of an arc-shaped long orbit is proposed. The curvature of the arc-shaped long orbit is much larger than that of the earth, and the rocket flies at supersonic speed, and its flight speed is much greater than that of the near-ground aircraft. As a result, within a unit time, the distance flown by the supersonic aircraft represented by the rocket is not a small amount relative to the flight orbit. Therefore, for a moving object such as a supersonic aircraft with supersonic speed, large curvature and long distance, it cannot be processed according to flat ground, nor can the supersonic aircraft itself be selected as the reference system.

[0004] In order to numerically simulate the motion process of supersonic aircraft, the prior art usually sets the ground as an arc-shaped ground and selects the ground absolute reference system as the reference system. When calculating using this method, the calculation domain needs to include the complete path flown by the supersonic aircraft and the entire arc-shaped ground. Assuming that the supersonic aircraft flies at a speed of 408 m / s and the separation time between the carrier and the supersonic aircraft is 1 s, when calculating in this way, the calculation domain is large, resulting in a huge increase in the number of calculation grids, low calculation efficiency and time consumption. Moreover, since the orbital curvature of the supersonic aircraft is much larger than the earth's curvature and the speed of the supersonic aircraft is much faster than that of the near-ground aircraft, the arc ground effect in this process cannot be ignored. Therefore, there is an urgent need for a method suitable for simulating the arc ground effect of supersonic speed, large curvature and long distance, so as to improve the calculation efficiency in the numerical simulation process. Summary of the Invention

[0005] The purpose of the embodiments of this article is to provide a method, device, equipment and storage medium for simulating arc ground effect, so as to improve the calculation efficiency in the numerical simulation process.

[0006] To achieve the above purpose, on the one hand, the embodiments of this article provide a method for simulating arc ground effect, and the method includes:

[0007] Set a reference system moving uniformly along a set direction;

[0008] Determine the relative motion speed of the supersonic aircraft in the reference frame, as well as the horizontal motion speed and the sinking motion speed of the flat ground directly below the supersonic aircraft in the reference frame;

[0009] Perform dynamic simulation based on the relative motion speed of the supersonic aircraft in the reference frame, the horizontal motion speed and the sinking motion speed of the flat ground in the reference frame, so as to determine the aerodynamic characteristics of the supersonic aircraft.

[0010] Preferably, the motion speed of the reference frame is the same as the initial speed of the supersonic aircraft and remains unchanged.

[0011] Preferably, the determining the relative motion speed of the supersonic aircraft in the reference frame includes:

[0012] Determine the aerodynamic force of the supersonic aircraft according to the flow control equation;

[0013] Determine the relative motion speed of the supersonic aircraft in the reference frame according to the aerodynamic force of the supersonic aircraft and the motion speed of the reference frame.

[0014] Preferably, the determining the horizontal motion speed of the flat ground directly below the supersonic aircraft in the reference frame includes:

[0015] The horizontal motion speed of the flat ground in the reference frame is equal in magnitude and opposite in direction to the motion speed of the reference frame.

[0016] Preferably, the determining the sinking motion speed of the flat ground directly below the supersonic aircraft in the reference frame includes:

[0017] Determine the absolute horizontal displacement of the supersonic aircraft according to the relative motion speed of the supersonic aircraft in the reference frame and the motion speed of the reference frame;

[0018] Determine the sinking height of the flat ground directly below the supersonic aircraft according to the absolute horizontal displacement of the supersonic aircraft and the radius of curvature of the arc-shaped ground;

[0019] Calculate the sinking motion speed of the flat ground in the reference frame according to the sinking height of the flat ground.

[0020] Preferably, the calculating the sinking motion speed of the flat ground in the reference frame according to the sinking height of the flat ground includes:

[0021] Take the derivative of the sinking height of the flat ground with respect to time, and calculate the sinking motion speed of the flat ground through the following formula:

[0022]

[0023] wherein, v ground is the sinking motion speed of the flat ground in the reference frame, h is the sinking height of the flat ground, x is the absolute horizontal displacement of the supersonic aircraft, R is the curvature radius of the arc ground, v is the motion speed of the reference frame, and v missile_r is the relative motion speed of the supersonic aircraft.

[0024] Preferably, performing dynamic simulation based on the relative motion speed of the supersonic aircraft in the reference frame, the horizontal motion speed and the sinking motion speed of the flat ground in the reference frame to determine the aerodynamic characteristics of the supersonic aircraft, including:

[0025] Generating a file for controlling the motion of the supersonic aircraft and a file for controlling the motion of the flat ground according to the relative motion speed of the supersonic aircraft in the reference frame, the horizontal motion speed and the sinking motion speed of the flat ground in the reference frame;

[0026] Establishing a three-dimensional model of the computational domain including the supersonic aircraft and the flat ground in the simulation software;

[0027] Controlling the motion of the supersonic aircraft and the flat ground respectively by using the file for controlling the motion of the supersonic aircraft and the file for controlling the motion of the flat ground to perform dynamic simulation;

[0028] Determining the aerodynamic characteristics of the supersonic aircraft according to the dynamic simulation process.

[0029] On the other hand, an embodiment of the present invention provides a device for simulating the arc ground effect, and the device includes:

[0030] A reference frame establishing module: setting a reference frame moving uniformly along a set direction;

[0031] A speed determining module: respectively determining the relative motion speed of the supersonic aircraft in the reference frame, and the horizontal motion speed and the sinking motion speed of the flat ground located directly below the supersonic aircraft in the reference frame;

[0032] A dynamic simulation module: performing dynamic simulation according to the relative motion speed of the supersonic aircraft in the reference frame, the horizontal motion speed and the sinking motion speed of the flat ground in the reference frame to determine the aerodynamic characteristics of the supersonic aircraft.

[0033] In another aspect, embodiments of the present disclosure further provide a computer device, including a memory, a processor, and a computer program stored on the memory. When the computer program is run by the processor, it executes the instructions of any one of the above methods.

[0034] In another aspect, embodiments of the present disclosure further provide a computer-readable storage medium, on which a computer program is stored. When the computer program is run by a processor of a computer device, it executes the instructions of any one of the above methods.

[0035] As can be seen from the technical solutions provided by the embodiments of the present disclosure above, after establishing a reference system moving at a uniform speed in the horizontal direction, the relative motion speed of the supersonic aircraft is determined through the reference system, and the arc-shaped ground is divided into several flat ground segments located directly below the supersonic aircraft. During the movement of the supersonic aircraft, the arc-shaped ground is simulated by dividing the ground into a stepped-like sinking manner, enabling the use of a limited computational domain to follow the supersonic aircraft for dynamic simulation. On the premise of a limited computational domain, the number of computational grids is limited and the computational efficiency is higher.

[0036] To make the above and other purposes, features, and advantages of the present disclosure more obvious and understandable, the following specifically enumerates preferred embodiments and, in conjunction with the accompanying drawings, makes the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] To more clearly illustrate the technical solutions in the embodiments of the present disclosure or in the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present disclosure. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0038] Figure 1 FIG. shows a schematic flowchart of a method for simulating the arc-shaped ground effect provided by an embodiment of the present disclosure;

[0039] Figure 2 FIG. shows the relative motion situation of a supersonic aircraft and a flat ground under the uniform motion of a reference system provided by an embodiment of the present disclosure;

[0040] Figure 3 FIG. shows a schematic diagram of the steps for determining the relative motion speed of a supersonic aircraft in a reference system provided by an embodiment of the present disclosure;

[0041] Figure 4 FIG. shows a schematic diagram of the steps for determining the sinking motion speed of a flat ground in a reference system provided by an embodiment of the present disclosure;

[0042] Figure 5 FIG. shows a schematic diagram of the steps for performing dynamic simulation provided by an embodiment of the present disclosure;

[0043] Figure 6 Shows the division diagram of the computational domain provided by the embodiments herein;

[0044] Figure 7 Shows the pressure contour map of the motion of a supersonic aircraft with an initial velocity of 1.5 Mach numbers from 0.01 s to 0.9 s under Fluent simulation provided by the embodiments herein;

[0045] Figure 8 Shows the curve graph of the position change of the supersonic aircraft relative to the reference system during motion provided by the embodiments herein;

[0046] Figure 9 Shows the schematic diagram of the module structure of a device for simulating the arc ground effect provided by the embodiments herein;

[0047] Figure 10 Shows the schematic diagram of the structure of the computer device provided by the embodiments herein.

[0048] Description of the reference signs in the drawings:

[0049] 100, Establish reference system module;

[0050] 200, Velocity determination module;

[0051] 300, Dynamic simulation module;

[0052] 1002, Computer device;

[0053] 1004, Processor;

[0054] 1006, Memory;

[0055] 1008, Driving mechanism;

[0056] 1010, Input / output module;

[0057] 1012, Input device;

[0058] 1014, Output device;

[0059] 1016, Presentation device;

[0060] 1018, Graphical user interface;

[0061] 1020, Network interface;

[0062] 1022, Communication link;

[0063] 1024, Communication bus. Detailed implementation manners

[0064] Next, the technical solutions in the embodiments of this article will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of this article. Obviously, the described embodiments are only a part of the embodiments of this article, rather than all the embodiments. Based on the embodiments in this article, all other embodiments obtained by those of ordinary skill in the art without creative work belong to the scope of protection of this article.

[0065] In the prior art, the ground is usually set as an arc-shaped ground, and the reference system is selected as the absolute ground reference system. When calculating a supersonic aircraft using this method, the calculation domain needs to include the complete path flown by the supersonic aircraft and the entire arc-shaped ground. Suppose the supersonic aircraft is flying at a speed of 408 m / s, and the separation time between the carrier and the supersonic aircraft is 1 s. When calculating in this way, the calculation domain is large, resulting in a huge increase in the number of calculation grids, low calculation efficiency, and time consumption. Moreover, since the orbital curvature of the supersonic aircraft is much larger than the curvature of the earth, and the speed of the supersonic aircraft is much faster than that of a near-earth aircraft, the arc-shaped ground effect in this process cannot be ignored.

[0066] To solve the above problems, the embodiments of this article provide a method for simulating the arc-shaped ground effect. Figure 1 It is a schematic diagram of the steps of a method for simulating the arc-shaped ground effect provided by the embodiments of this article. This specification provides the method operation steps as described in the embodiments or flowcharts, but based on routine or non-creative labor, there may be more or fewer operation steps. The order of steps listed in the embodiments is only one way among the execution orders of numerous steps and does not represent the only execution order. When the actual system or device product executes, it can be executed in the order of the method shown in the embodiments or the drawings, or executed in parallel.

[0067] Referring to Figure 1 , the method may include the following steps:

[0068] S101: Set a reference system moving uniformly along a set direction;

[0069] S102: Determine the relative motion speed of the supersonic aircraft in the reference system, and the horizontal motion speed and sinking motion speed of the flat ground directly below the supersonic aircraft in the reference system, respectively;

[0070] S103: Perform dynamic simulation according to the relative motion speed of the supersonic aircraft in the reference system, the horizontal motion speed and sinking motion speed of the flat ground in the reference system, to determine the aerodynamic characteristics of the supersonic aircraft.

[0071] Referring to Figure 2, after establishing a reference frame moving uniformly along a set direction, the relative motion speed of the supersonic aircraft is determined through the reference frame, and the arc-shaped ground is divided into several flat grounds with changing heights directly below the supersonic aircraft. During the movement of the supersonic aircraft, by dividing the ground into a stepped-like sinking manner to simulate the arc-shaped ground, it enables the use of a limited computational domain to follow the supersonic aircraft for dynamic simulation, avoiding the situation in the prior art where, with the ground as the absolute reference frame, the computational domain is too large, resulting in an explosive increase in the number of computational grids and low computational efficiency. In the embodiments of this article, the supersonic aircraft can be any aircraft with a flight speed greater than 340 m / s, such as a supersonic aircraft, a missile, a shell, etc. The specific type of the supersonic aircraft is not limited in this article.

[0072] Preferably, the motion speed of the reference frame can be the same as the initial speed of the supersonic aircraft and remain unchanged, then the set direction is the direction of the initial speed of the supersonic aircraft. The magnitude and direction of the motion speed of the reference frame are not specifically limited in this article. The motion speed of the reference frame is the convective motion speed of the reference frame. When the motion speed of the reference frame is the same as the initial speed of the supersonic aircraft, the reference frame only has translational motion and remains unchanged, without changing with the supersonic aircraft. In this reference frame, the relative speed of any point in space including the supersonic aircraft and the flat ground at any moment can be obtained. Due to the use of the flat ground approximation, for supersonic flow, the computational domain can be restricted near the supersonic aircraft. It is like taking a flow field photo for each physical moment following the supersonic aircraft. In the given moving reference frame, the horizontal supersonic relative motion of the arc-shaped ground is transformed into the horizontal supersonic relative motion of the flat ground, and at the same time, the sinking speed of the flat ground and the relative motion speed of the supersonic aircraft are limited, ensuring the computational speed throughout the process.

[0073] Refer to Figure 3 , in the embodiments of this article, the determination of the relative motion speed of the supersonic aircraft in the reference frame includes the following sub-steps:

[0074] S1021: Determine the aerodynamic force of the supersonic aircraft according to the flow control equation;

[0075] S1022: Determine the relative motion speed of the supersonic aircraft in the reference frame according to the aerodynamic force of the supersonic aircraft and the motion speed of the reference frame.

[0076] In the embodiments of this article, the following flow control equation is established based on the arbitrary Arbitrary Lagrangian-Eulerian (ALE) method in the reference frame:

[0077]

[0078] Among them, ρ is the air density, u is the velocity vector of any spatial point, us is the grid deformation velocity vector, Γ is the diffusion coefficient, and S φ is the source term of the flux φ, S is the control volume boundary, V is the control volume, and n is the normal vector of the control volume boundary. is the Hamiltonian operator.

[0079] In some embodiments, to ensure the adaptability of the solution of the ALE flow control equation, the following boundary conditions need to be established: the lower arc-shaped ground is approximately replaced by a flat ground, and the boundary conditions of the flat ground are determined according to the horizontal movement speed and the sinking movement speed of the flat ground in the reference frame; the upper and front airflows are given according to the free incoming flow, and the rear is given according to the supersonic outlet. Under the above boundary conditions, by solving the flow control equations (continuity equation, momentum equation, and energy equation), the aerodynamic force of the supersonic aircraft can be obtained.

[0080] The specific forms of the symbols in the flow control equations are shown in Table 1:

[0081]

[0082] Table 1

[0083] where u is the velocity vector, μ is the gas viscosity coefficient, T is the gas temperature, k is the thermal conductivity, c is the specific heat capacity at constant pressure, S T is the energy source term, and S i is the source term such as body force, is the pressure gradient.

[0084] In some embodiments, when the movement speed of the reference frame is the same as the initial speed of the supersonic aircraft, the relative initial speed of the supersonic aircraft in the reference frame is 0. The supersonic aircraft starts to move at the initial speed. At any m-th moment, the aerodynamic force of the supersonic aircraft is known, and the acceleration of the supersonic aircraft can be obtained through the following formula:

[0085]

[0086] where F m is the aerodynamic force of the supersonic aircraft at the m-th moment, M is the mass of the supersonic aircraft, and a m is the acceleration of the supersonic aircraft at the m-th moment.

[0087] The relative movement speed of the supersonic aircraft at the mΔt moment can be obtained through the following formula:

[0088]

[0089] where, is the relative movement speed of the supersonic aircraft at the m-th moment, is the relative motion speed of the supersonic aircraft at time mΔt, and Δt is the motion time of the supersonic aircraft from time m to time mΔt.

[0090] Since the relative initial velocity of the supersonic aircraft is 0 and the acceleration is known. Therefore, at the initial motion of the supersonic aircraft, that is, at time 0, is 0, and after knowing , the relative motion speed of the supersonic aircraft at any time can be obtained by the iterative solution method according to formula (3).

[0091] Referring to Figure 2 and Figure 4 , in some embodiments, the motion of the flat ground directly below the supersonic aircraft is decomposed into horizontal motion and sinking motion. Among them, the horizontal motion speed of the flat ground is equal in magnitude and opposite in direction to the motion speed of the reference frame. Determining the sinking motion speed of the flat ground in the reference frame includes the following sub-steps:

[0092] S1023: Determine the absolute horizontal displacement of the supersonic aircraft according to the relative motion speed of the supersonic aircraft in the reference frame and the motion speed of the reference frame;

[0093] S1024: Determine the sinking height of the flat ground directly below the supersonic aircraft according to the absolute horizontal displacement of the supersonic aircraft and the radius of curvature of the arc-shaped ground;

[0094] S1025: Calculate the sinking motion speed of the flat ground in the reference frame according to the sinking height of the flat ground.

[0095] After solving the relative motion speed of the supersonic aircraft at any time, the relative displacement of the supersonic aircraft at any time can be obtained through the following formula

[0096]

[0097] According to the relative displacement of the supersonic aircraft and the motion speed of the reference frame, the absolute horizontal displacement of the supersonic aircraft can be calculated through the following formula:

[0098]

[0099] where x is the absolute horizontal displacement of the supersonic aircraft and v is the motion speed of the reference frame.

[0100] According to the absolute horizontal displacement of the supersonic aircraft and the radius of curvature of the arc-shaped ground, the sinking height of the flat ground directly below the supersonic aircraft can be calculated through the following formula:

[0101]

[0102] Where h is the subsidence height of the flat ground and R is the radius of curvature of the arc ground. When the arc ground is the earth's surface,

[0103] Derive the subsidence height of the flat ground with respect to time, and calculate the subsidence velocity v of the flat ground through the following formula ground :

[0104]

[0105] Refer to Figure 5 , in some embodiments, step S103 includes the following sub-steps:

[0106] S1031: Generate a file for controlling the movement of the supersonic aircraft and a file for controlling the movement of the flat ground according to the relative movement speed of the supersonic aircraft in the reference system, the horizontal movement speed and the subsidence movement speed of the flat ground in the reference system;

[0107] S1032: Establish a three-dimensional model of the computational domain including the supersonic aircraft and the flat ground in the simulation software;

[0108] S1033: Use the file of the movement of the supersonic aircraft and the file of the movement of the flat ground to control the movement of the supersonic aircraft and the flat ground respectively, and perform dynamic simulation;

[0109] S1034: Determine the aerodynamic characteristics of the supersonic aircraft according to the dynamic simulation process.

[0110] According to the obtained relative movement speed of the supersonic aircraft, the horizontal movement speed and the subsidence movement speed of the flat ground, write the Motion_missile.c file for controlling the movement of the supersonic aircraft and the Motion_ground.c file for controlling the movement of the flat ground by the wing.

[0111] Refer to Figure 6 , establish a three-dimensional model of the computational domain including the supersonic aircraft and the flat ground in CATIA. In the ICEM mesh generation software, to ensure the mesh quality near the supersonic aircraft, establish a cylindrical Interior near the supersonic aircraft, divide the computational domain into Body1 and Body2, and save the generated mesh as Missile.msh.

[0112] Perform dynamic simulation through Fluent, read the above-mentioned grid file Missile.msh and the previously established boundary conditions in Fluent, and solve the flow control equation through Fluent steady solution mode to obtain the initial field Flow_ini.dat for unsteady calculation iteration. Switch to Fluent unsteady solution mode, read the initial field Flow_ini.dat, compile and load Motion_ground.c file and Motion_missile.c file, and start solving the flow control equation and six-degree-of-freedom dynamic equation.

[0113] The unsteady solution uses the following settings: the characteristic time is calculated as L is the characteristic length, usually the length of the supersonic vehicle, v 0 is the initial velocity, the internal iteration time can be ΔT=0.01T, and the number of internal iteration steps can be set to 30, wherein the internal iteration time and the number of internal iteration steps can be set according to actual needs. This article does not limit the specific values ​​of the internal iteration time and the number of internal iteration steps. Including the vicinity of the body1 area of ​​the supersonic aircraft and the flat ground, the mesh is updated by Fluent elastic deformation and local mesh reconstruction to generate a dynamic simulation model and determine the aerodynamic characteristics of the supersonic aircraft. Among them, Fluent determines the aerodynamic characteristics of the supersonic aircraft by one or more of the following methods: FVM (finite volume method), FDM (finite difference method), FEM (finite element method), particle method or LBM (discrete lattice Boltzmann method). Such as Figure 7 , showing the dynamic simulation model of a supersonic aircraft with an initial velocity of Ma = 1.5 from 0.01s to 0.9s, such as Figure 8 , showing the changes in the position of the supersonic aircraft itself and the curved ground relative to the reference system during the movement of a supersonic aircraft with an initial velocity of .

[0114] Based on the above-described method for simulating an arc ground effect, an embodiment of the present invention further provides a device for simulating an arc ground effect. The device may include a system (including a distributed system), software (application), module, component, server, client, etc. using the method described in the embodiment of the present invention and a device in combination with necessary implementation hardware. Based on the same innovative concept, the device in one or more embodiments provided in the embodiment of the present invention is as described in the following embodiments. Since the implementation scheme and method for solving the problem of the device are similar, the implementation of the specific device in the embodiment of the present invention can refer to the implementation of the aforementioned method, and the repetitions will not be repeated. As used below, the term "unit" or "module" can be a combination of software and / or hardware that implements a predetermined function. Although the device described in the following embodiments is preferably implemented in software, the implementation of hardware, or a combination of software and hardware, is also possible and conceived.

[0115] Specifically, Figure 9 FIG. 282 is a schematic diagram of a module structure of an embodiment of a device for simulating an arc ground effect provided by an embodiment of the present invention. Referring to Figure 9 As shown in FIG. 283, a device for simulating an arc ground effect provided by an embodiment of the present invention includes: a reference system establishment module 100, a speed determination module 200, and a dynamic simulation module 300.

[0116] The reference system establishment module 100: sets a reference system that moves uniformly in the horizontal direction;

[0117] The speed determination module 200: respectively determines the relative motion speed of the supersonic aircraft in the reference system, and the horizontal motion speed and the sinking motion speed of the flat ground directly below the supersonic aircraft in the reference system;

[0118] The dynamic simulation module 300: performs dynamic simulation according to the relative motion speed of the supersonic aircraft in the reference system, the horizontal motion speed and the sinking motion speed of the flat ground in the reference system, so as to determine the aerodynamic characteristics of the supersonic aircraft.

[0119] In an embodiment of the present invention, referring to Figure 10 As shown in FIG. 292, a computer device 1002 is further provided. The computer device 1002 may include one or more processors 1004, such as one or more central processing units (CPUs) or graphics processing units (GPUs), and each processing unit may implement one or more hardware threads. The computer device 1002 may further include any memory 1006 for storing any kind of information such as code, settings, data, etc. In a specific embodiment, a computer program stored on the memory 1006 and executable on the processor 1004, when the computer program is run by the processor 1004, may execute the instructions according to the above method. Non-limitingly, for example, the memory 1006 may include any one or a combination of the following: any type of RAM, any type of ROM, flash memory devices, hard disks, optical discs, etc. More generally, any memory may use any technology to store information. Further, any memory may provide volatile or non-volatile retention of information. Further, any memory may represent a fixed or removable component of the computer device 1002. In one case, when the processor 1004 executes the associated instructions stored in any memory or combination of memories, the computer device 1002 may perform any operation of the associated instructions. The computer device 1002 further includes one or more drive mechanisms 1008 for interacting with any memory, such as a hard disk drive mechanism, an optical disc drive mechanism, etc.

[0120] The computer device 1002 may further include an input / output module 1010 (I / O) for receiving various inputs (via the input device 1012) and for providing various outputs (via the output device 1014). A specific output mechanism may include a presentation device 1016 and an associated graphical user interface 1018 (GUI). In other embodiments, the input / output module 1010 (I / O), the input device 1012, and the output device 1014 may not be included, and it may only be a computer device in the network. The computer device 1002 may further include one or more network interfaces 1020 for exchanging data with other devices via one or more communication links 1022. One or more communication buses 1024 couple the components described above together.

[0121] The communication link 1022 may be implemented in any manner, for example, via a local area network, a wide area network (e.g., the Internet), a point-to-point connection, etc., or any combination thereof. The communication link 1022 may include any combination of hardwired links, wireless links, routers, gateway functions, name servers, etc. governed by any protocol or combination of protocols.

[0122] Corresponding to Figures 1-5 In accordance with the method in [the relevant part], embodiments herein further provide a computer-readable storage medium having a computer program stored thereon, and when the computer program is run by a processor, it executes the steps of the above method.

[0123] Embodiments herein further provide a computer-readable instruction, wherein when the processor executes the instruction, the program therein causes the processor to execute the method as Figures 1 to 5 shown.

[0124] It should be understood that in various embodiments herein, the magnitudes of the sequence numbers of the above processes do not imply the order of execution. The order of execution of each process should be determined by its function and internal logic, and should not constitute any limitation to the implementation process of the embodiments herein.

[0125] It should also be understood that in the embodiments herein, the term "and / or" is merely a description of the association relationship of associated objects, indicating that three relationships may exist. For example, A and / or B may represent: A exists alone, A and B exist simultaneously, and B exists alone. Additionally, the character " / " herein generally represents an "or" relationship between the associated objects before and after.

[0126] Those of ordinary skill in the art can realize that the units and algorithm steps of the examples described in combination with the embodiments disclosed herein can be implemented by electronic hardware, computer software, or a combination of the two. To clearly illustrate the interchangeability of hardware and software, the composition and steps of the examples have been generally described according to functions in the above description. Whether these functions are executed in a hardware or software manner depends on the specific application and design constraints of the technical solution. Professional technicians can use different methods to implement the described functions for each specific application, but such implementation should not be considered to exceed the scope of this article.

[0127] Those skilled in the art can clearly understand that for the convenience and conciseness of description, the specific working processes of the systems, devices, and units described above can refer to the corresponding processes in the foregoing method embodiments and will not be elaborated herein.

[0128] In the several embodiments provided in this article, it should be understood that the disclosed systems, devices, and methods can be implemented in other ways. For example, the device embodiments described above are merely illustrative. For example, the division of the units is only a logical function division. In actual implementation, there may be other division methods. For example, multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. In addition, the displayed or discussed couplings or direct couplings or communication connections to each other can be indirect couplings or communication connections through some interfaces, devices, or units, and can also be in the form of electrical, mechanical, or other connections.

[0129] The units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they can be located in one place or distributed to multiple network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of the embodiments in this article.

[0130] In addition, the functional units in the various embodiments of this article can be integrated into one processing unit, or each unit can exist physically alone, or two or more units can be integrated into one unit. The above integrated units can be implemented in the form of hardware or in the form of software functional units.

[0131] When the integrated unit is implemented in the form of a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on such an understanding, the technical solution herein, in essence, or the part that contributes to the prior art, or all or part of the technical solution can be embodied in the form of a software product. The computer software product is stored in a storage medium and includes several instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute all or part of the steps of the methods described in the various embodiments herein. The foregoing storage medium includes: various media that can store program codes, such as USB flash drives, mobile hard disks, read-only memories (ROMs), random access memories (RAMs), magnetic disks, or optical discs.

[0132] Specific embodiments are applied herein to elaborate on the principles and implementation manners of this article. The description of the above embodiments is only used to help understand the method and its core idea herein; at the same time, for those of ordinary skill in the art, according to the idea herein, there will be changes in the specific implementation manners and application scopes. In summary, the content of this specification should not be construed as a limitation to this article.

Claims

1. A method for simulating the curved ground effect, characterized in that, the method includes: setting a reference frame moving uniformly in a set direction; respectively determining the relative motion speed of a supersonic aircraft in the reference frame, and the horizontal motion speed and sinking motion speed of a flat ground directly below the supersonic aircraft in the reference frame; performing dynamic simulation according to the relative motion speed of the supersonic aircraft in the reference frame, the horizontal motion speed and sinking motion speed of the flat ground in the reference frame to determine the aerodynamic characteristics of the supersonic aircraft; wherein, the motion speed of the reference frame is the same as the initial speed of the supersonic aircraft and remains unchanged; the determining of the relative motion speed of the supersonic aircraft in the reference frame includes: determining the aerodynamic force of the supersonic aircraft according to the flow control equation; determining the relative motion speed of the supersonic aircraft in the reference frame according to the aerodynamic force of the supersonic aircraft and the motion speed of the reference frame; the determining of the horizontal motion speed of the flat ground directly below the supersonic aircraft in the reference frame includes: the horizontal motion speed of the flat ground in the reference frame is equal in magnitude and opposite in direction to the motion speed of the reference frame; the determining of the sinking motion speed of the flat ground directly below the supersonic aircraft in the reference frame includes: determining the absolute horizontal displacement of the supersonic aircraft according to the relative motion speed of the supersonic aircraft in the reference frame and the motion speed of the reference frame; determining the sinking height of the flat ground directly below the supersonic aircraft according to the absolute horizontal displacement of the supersonic aircraft and the curvature radius of the curved ground; calculating the sinking motion speed of the flat ground in the reference frame according to the sinking height of the flat ground; the performing of dynamic simulation according to the relative motion speed of the supersonic aircraft in the reference frame, the horizontal motion speed and sinking motion speed of the flat ground in the reference frame to determine the aerodynamic characteristics of the supersonic aircraft includes: generating a file for controlling the motion of the supersonic aircraft and a file for controlling the motion of the flat ground according to the relative motion speed of the supersonic aircraft in the reference frame, the horizontal motion speed and sinking motion speed of the flat ground in the reference frame; establishing a three-dimensional model of the computational domain including the supersonic aircraft and the flat ground in the simulation software; using the file for controlling the motion of the supersonic aircraft and the file for controlling the motion of the flat ground to control the motion of the supersonic aircraft and the flat ground respectively and perform dynamic simulation; determining the aerodynamic characteristics of the supersonic aircraft according to the dynamic simulation process.

2. The method according to claim 1, characterized in that, the calculating of the sinking motion speed of the flat ground in the reference frame according to the sinking height of the flat ground includes: taking the derivative of the sinking height of the flat ground with respect to time, and calculating the sinking motion speed of the flat ground through the following formula: Among them, v ground is the sinking speed of the flat ground in the reference frame, h is the sinking height of the flat ground, x is the absolute horizontal displacement of the supersonic aircraft, R is the curvature radius of the arc ground, v is the moving speed of the reference frame, v missile_r is the relative moving speed of the supersonic aircraft.

3. A device for simulating the curved ground effect, characterized in that, The device performs dynamic simulation by using the method for simulating the arc ground effect as described in any one of claims 1-2. The device includes: A reference system establishment module: setting up a reference system moving at a uniform speed along a set direction; A speed determination module: respectively determining the relative motion speed of the supersonic aircraft in the reference system, and the horizontal motion speed and the sinking motion speed of the flat ground directly below the supersonic aircraft in the reference system; A dynamic simulation module: performing dynamic simulation according to the relative motion speed of the supersonic aircraft in the reference system, the horizontal motion speed and the sinking motion speed of the flat ground in the reference system, so as to determine the aerodynamic characteristics of the supersonic aircraft.

4. A computer device, including a memory, a processor, and a computer program stored on the memory, characterized in that when the computer program is run by the processor, it executes the instructions of the method as described in any one of claims 1-2.

5. A computer-readable storage medium, on which a computer program is stored, characterized in that when the computer program is run by the processor of the computer device, it executes the instructions of the method as described in any one of claims 1-2.

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