Method, device and equipment for determining parameters of launch ship baffle

Abstract

The present invention provides a method, device and equipment for determining the parameters of a launch ship baffle, and relates to the technical field of rocket launch analysis. The method for determining the parameters of a launch ship baffle includes: obtaining a three-dimensional model of the baffle when the rocket is launched at a preset launch altitude; meshing the three-dimensional model of the baffle to obtain a plurality of unit grids; performing numerical simulation calculations on the plurality of unit grids to obtain simulation calculation results; the simulation calculation results include the temperature and pressure of each unit grid in the three-dimensional model of the baffle; optimizing the parameters of the baffle based on the simulation calculation results to obtain target parameters, and the target parameters include: the target height, target width and target thickness of the baffle. The solution of the present invention can accurately simulate and analyze the temperature and pressure of the baffle impacted by the heat flow at a preset launch altitude, providing theoretical and data support for the parameters when designing the baffle.

Description

Technical Field

[0001] The present invention relates to the technical field of launch ships, and in particular to a method, device and equipment for determining parameters of a launch ship baffle. Background Art

[0002] Setting a baffle at the outlet of the guide chute on the launch ship can effectively reduce the speed of the lateral jet after the rocket is launched, and to a certain extent suppress the impact of the heat flow, thereby providing protection for other equipment on the launch ship; the current guide chute of the sea launch ship is generally arranged horizontally, that is, the rocket jet tail flame is perpendicular to the launch ship after passing through the guide chute. There is no design for the longitudinal arrangement of the guide chute and the setting of a baffle at the outlet of the guide chute; analyzing the pressure and temperature on the baffle can provide theoretical and data support for the design of the baffle; during the rocket launch process, as the launch altitude increases, the pressure and temperature on the baffle are constantly changing, so when to take the pressure and temperature as the design pressure and temperature of the baffle is a problem that needs to be studied and solved. Summary of the Invention

[0003] The present invention provides a method, device and equipment for determining the parameters of a launch ship's baffle. By simulating and analyzing the temperature and pressure on the baffle at a preset launch altitude, theoretical and data support are provided for the parameters in the baffle design, thereby ensuring that the baffle can block the heat flow generated during rocket launch and reduce the impact force on other equipment on the launch ship.

[0004] In order to solve the above technical problems, the technical solutions of the present invention are as follows:

[0005] An embodiment of the present invention provides a method for determining parameters of a launch vessel spoiler, comprising:

[0006] Obtain a three-dimensional model of the baffle when the rocket is launched at a preset launch altitude;

[0007] Meshing the baffle three-dimensional model to obtain a plurality of unit grids;

[0008] Performing numerical simulation calculations on the plurality of unit grids to obtain simulation calculation results, wherein the simulation calculation results include the temperature and pressure of each unit grid in the baffle three-dimensional model;

[0009] According to the simulation calculation results, the parameters of the baffle are optimized to obtain target parameters, which include: a target height, a target width, and a target thickness of the baffle.

[0010] Optionally, the baffle three-dimensional model is meshed to obtain a plurality of unit meshes, including:

[0011] The baffle three-dimensional model is meshed within a preset calculation domain to obtain a discretized numerical calculation unit mesh, and the inlet boundary and wall boundary of the baffle three-dimensional model are set.

[0012] Optionally, the method for determining the parameters of the launch vessel baffle further includes:

[0013] The numerical calculation unit grid is subjected to structured grid encryption processing to obtain an encrypted numerical calculation unit grid.

[0014] Optionally, numerical simulation calculations are performed on the plurality of unit grids to obtain simulation calculation results, including:

[0015] Determine the mathematical model corresponding to the numerical simulation calculation process;

[0016] According to the mathematical model, a numerical simulation calculation is performed on each unit grid in the three-dimensional model to obtain the simulation calculation result.

[0017] Optionally, determining a mathematical model corresponding to the numerical simulation calculation process includes:

[0018] The mathematical model corresponding to the numerical simulation calculation process is determined based on the jet temperature, jet velocity, jet pressure of the nozzle during rocket launch and the preset altitude during launch.

[0019] Optionally, the mathematical model includes:

[0020]

[0021] Where ρ represents the fluid density; u i represents the velocity component; μ represents the dynamic viscosity; μ t represents turbulent viscosity; σ k The turbulent Prandtl number represents the turbulent kinetic energy k; σ ∈ The turbulent Prandtl number represents the turbulent energy dissipation rate ∈; P k represents the turbulent kinetic energy generation term; G h (ρ, T, P) represents the highly turbulent kinetic energy generated due to the change in rocket altitude; C1 and C2 represent constant terms.

[0022] Optionally, according to the simulation calculation results, the parameters of the baffle are optimized to obtain target parameters, including:

[0023] According to the temperature and pressure of each unit grid, the temperature cloud map and pressure cloud map at the time of rocket launch are obtained;

[0024] According to the temperature cloud map, the pressure cloud map and the preset safety factor, the parameters of the baffle are optimized to obtain the target parameters.

[0025] An embodiment of the present invention further provides a device for determining parameters of a launch vessel spoiler, comprising:

[0026] An acquisition module is used to obtain a three-dimensional model of a baffle when the rocket is launched at a preset launch altitude;

[0027] a processing module configured to mesh the three-dimensional model of the baffle to obtain a plurality of unit grids; perform numerical simulation calculations on each of the plurality of unit grids to obtain simulation calculation results, wherein the simulation calculation results include the temperature and pressure of each unit grid in the three-dimensional model of the baffle; and optimize parameters of the baffle based on the simulation calculation results to obtain target parameters, wherein the target parameters include a target height, a target width, and a target thickness of the baffle.

[0028] An embodiment of the present invention further provides a computing device, comprising: a processor and a memory storing a computer program, wherein the computer program executes the method described above when executed by the processor.

[0029] An embodiment of the present invention further provides a computer-readable storage medium storing instructions, which, when executed on a computer, enable the computer to execute the method described above.

[0030] The above solution of the present invention includes at least the following beneficial effects:

[0031] The method for determining the parameters of the launch ship baffle described in the present invention obtains a three-dimensional model of the baffle when a rocket is launched at a preset launch altitude; grids the three-dimensional model of the baffle to obtain multiple unit grids; performs numerical simulation calculations on the multiple unit grids to obtain simulation calculation results; the simulation calculation results include the temperature and pressure of each unit grid in the three-dimensional model of the baffle; based on the simulation calculation results, the parameters of the baffle are optimized to obtain target parameters, and the target parameters include: target height, target width and target thickness of the baffle; the above-mentioned scheme of the present invention simulates and analyzes the temperature and pressure on the baffle at the preset launch altitude to provide theoretical and data support for the parameters when designing the baffle, thereby ensuring that the baffle can block the heat flow generated during rocket launch and reduce the impact force borne by other equipment on the launch ship. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] Figure 1 is a flow chart of a method for determining parameters of a launch vessel baffle of the present invention;

[0033] Figure 2 An optional embodiment of the method for determining parameters of a launch vessel baffle of the present invention provides a schematic diagram of the distribution structure of the baffle, the launch platform, and the nozzle;

[0034] Figure 3 A temperature cloud map drawn based on temperature data obtained by three-dimensional numerical simulation is provided in an optional embodiment of the method for determining parameters of a launch vessel baffle of the present invention;

[0035] Figure 4 A pressure cloud diagram drawn based on pressure data obtained by three-dimensional numerical simulation is provided in an optional embodiment of the method for determining parameters of a launch vessel baffle of the present invention;

[0036] Figure 5 A schematic block diagram of a module of a device for determining parameters of a launch vessel baffle according to the present invention.

[0037] Description of reference numerals:

[0038] 21. Baffle; 22. Launch pad; 23. Nozzle. DETAILED DESCRIPTION

[0039] Exemplary embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present invention are shown in the accompanying drawings, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided to enable a more thorough understanding of the present invention and to fully convey the scope of the present invention to those skilled in the art.

[0040] like Figure 1 As shown, an embodiment of the present invention provides a method for determining parameters of a launch vessel spoiler, comprising:

[0041] Step 11, obtaining a three-dimensional model of the baffle when the rocket is launched at a preset launch altitude;

[0042] Step 12, meshing the baffle three-dimensional model to obtain a plurality of unit grids;

[0043] Step 13, performing numerical simulation calculations on the plurality of unit grids to obtain simulation calculation results; the simulation calculation results include the temperature and pressure of each unit grid in the baffle three-dimensional model;

[0044] Step 14: Optimize the parameters of the baffle according to the simulation calculation results to obtain target parameters, which include: a target height, a target width, and a target thickness of the baffle.

[0045] In this embodiment, it should be noted that Figure 2As shown, since the baffle 21 is fixed in actual application, when simulating and analyzing the impact of the heat flow generated by the nozzle 23 on the baffle during the rocket launch process (the impact of the heat flow on the baffle is mainly reflected in the temperature and pressure distribution on the baffle), only the impact of the heat flow generated by the rocket at different launch altitudes on the baffle is considered; here, the launch altitude of the rocket is changed by changing the height of the launch platform 22;

[0046] In this embodiment, the three-dimensional model of the baffle can be established by CAD software or other professional geometric modeling software based on pre-set parameters of the baffle; the parameters of the baffle may include: height, width and thickness of the baffle;

[0047] By dividing the established three-dimensional model of the baffle into grids, and performing three-dimensional numerical simulation calculations on each unit grid obtained after the division within the calculation range defined by the thermal flow field formed by the heat flux ejected from the tail of the nozzle during rocket launch, the temperature and pressure corresponding to each unit grid at different launch altitudes are determined; further, based on the obtained temperature and pressure, the design parameters of the baffle are optimized to obtain the optimal target parameters, thereby ensuring that the baffle can block the heat flux generated during rocket launch and reduce the impact of the heat flux generated during rocket launch on the temperature and pressure of other equipment on the launch ship; the present invention establishes a three-dimensional model of the baffle, and through three-dimensional numerical simulation calculations at a preset launch altitude and within the defined flow field calculation range, provides a reliable evaluation and optimization method for the parameter design of the baffle, and at the same time provides strong technical support for the practical application of the baffle in rocket launch.

[0048] In an optional embodiment of the present invention, step 12 may include:

[0049] Step 121 : Meshing the baffle three-dimensional model within a preset calculation domain to obtain a discretized numerical calculation unit grid, and setting the inlet boundary and wall boundary of the baffle three-dimensional model.

[0050] In this embodiment, since a thermal flow field may be generated around the entire baffle during rocket launch, the three-dimensional model of the baffle may be meshed to facilitate numerical simulation calculations by a computer. Specifically, the three-dimensional model of the baffle is discretized into a series of nodes within the continuous preset computational domain to obtain a discretized numerical computation unit grid, where each computation unit grid represents a tiny area. Here, the size and density of a single computation unit grid may be determined based on the geometry, accuracy, and computational domain range of the baffle, thereby ensuring a balance between accuracy and computational efficiency in subsequent numerical simulation calculations.

[0051] In this embodiment, meshing software such as ANSYS Fluent or ICEM CFD can be used to mesh the three-dimensional model of the baffle. Specifically, the three-dimensional model of the baffle is imported into the meshing software, and the three-dimensional model of the baffle is meshed according to the set meshing parameters, such as mesh size and mesh type (structured or unstructured), to generate the unit mesh required for the numerical simulation calculation.

[0052] In an optional embodiment of the present invention, step 121 may further include:

[0053] Step 122 : performing structured grid encryption processing on the numerical calculation unit grid to obtain an encrypted numerical calculation unit grid.

[0054] In this embodiment, to further improve the calculation accuracy, the numerical calculation unit grid is subjected to structured grid encryption processing. Specifically, the grid is encrypted in key areas of the baffle, such as the jet impact area, to ensure that the fluid dynamic characteristics of the area can be accurately simulated. Preferably, the grid size and distribution can be adjusted to ensure that the encrypted grid can accurately reflect the local geometric characteristics of the baffle.

[0055] In an optional embodiment of the present invention, step 13 may include:

[0056] Step 131, determining a mathematical model corresponding to the numerical simulation calculation process;

[0057] Step 132: Perform numerical simulation calculation on each unit grid in the three-dimensional model according to the mathematical model to obtain the simulation calculation result.

[0058] In this embodiment, based on the set simulation parameters and the flow characteristics of the airflow ejected from the nozzle during rocket launch, a mathematical model corresponding to the subsequent numerical simulation calculation process can be determined and fitted; further, by performing numerical simulation calculations using the determined mathematical model, the pressure and temperature corresponding to each calculation unit grid corresponding to the baffle three-dimensional model under different set simulation parameters can be obtained, and then the thermal flow field distribution, pressure distribution and temperature distribution of the baffle three-dimensional model under different set simulation parameters can be determined, further providing designers with more accurate aerodynamic characteristic data to optimize parameter information during baffle design.

[0059] In an optional embodiment of the present invention, the setting of simulation parameters may include the above-mentioned step 131, which may specifically include:

[0060] Step 1311, determining a mathematical model corresponding to the numerical simulation calculation process according to the jet temperature, jet velocity, jet pressure of the nozzle during rocket launch and the preset altitude during launch.

[0061] Specifically, the mathematical model may include:

[0062]

[0063] Where ρ represents the fluid density; u i represents the velocity component; μ represents the dynamic viscosity; μ t represents turbulent viscosity; σ k The turbulent Prandtl number represents the turbulent kinetic energy k; σ ∈ The turbulent Prandtl number represents the turbulent energy dissipation rate ∈; P k represents the turbulent kinetic energy generation term; G h (ρ, T, P) represents the highly turbulent kinetic energy generated due to the change in rocket altitude; C1 and C2 represent constant terms.

[0064] Here, μ t =C μ ρk 2 / ∈;

[0065] Among them, C μ represents an empirical constant that adjusts the relationship between turbulent viscosity and turbulent kinetic energy and dissipation rate, represents the jet velocity component u i The sum of the partial derivatives in all directions, i.e. the jet velocity divergence; represents the jet velocity component u i In direction x j The sum of the partial derivatives on represents the rate of change of the jet velocity in the spatial direction, that is, the velocity gradient; is the symmetric part of the velocity gradient, indicating that the gradients of the velocity field in both directions are equal;

[0066] here, Wherein, T represents the jet temperature; T0 is the set reference temperature; P represents the jet pressure, and P0 is the set jet pressure; is the square of the velocity divergence, which represents the velocity gradient in the flow field; here, the influence of the rocket launch altitude is reflected by ρ (the higher the altitude, the lower the density).

[0067] In an optional embodiment of the present invention, step 132 may include:

[0068] Step 1321, setting initial conditions: according to the initial parameters of the rocket launch, set the initial temperature, velocity, pressure, etc. of each unit grid;

[0069] Import the three-dimensional baffle model into numerical simulation software, such as ANSYS Fluent, and perform the following operations: set boundary conditions, which may include an inlet, an outlet, and a wall surface (here, corresponding boundary conditions can be set according to the actual conditions of the nozzle outlet and inlet); input parameters such as the preset launch altitude, jet temperature, jet velocity, and jet pressure during rocket launch; discretize the mathematical model using the finite element method or the finite difference method; apply an iterative algorithm to solve the discretized equation system until convergence conditions are reached, and thereby obtain temperature and pressure data for each unit grid in the three-dimensional baffle model;

[0070] Since the preset altitude at rocket launch has an important influence on the jet characteristics, the jet characteristics at different preset altitudes can be considered during the numerical simulation process; here, the parameters in the mathematical model (such as gravitational acceleration, atmospheric pressure, etc.) can be adjusted according to different preset altitudes (h1, h2, h3...) to ensure the accuracy and stability of the simulation calculation results.

[0071] In an optional embodiment of the present invention, step 14 may include:

[0072] Step 141, obtaining a temperature cloud map and a pressure cloud map during rocket launch based on the temperature and pressure of each unit grid;

[0073] Step 142 : Optimize the parameters of the baffle according to the temperature cloud map, the pressure cloud map, and a preset safety factor to obtain the target parameters.

[0074] In this embodiment, a temperature cloud map and a pressure cloud map are drawn during rocket launch based on the temperature and pressure of each unit grid, and the temperature and pressure distribution of each part of the baffle are analyzed. Here, the cloud map can be drawn using existing drawing software, such as FLUENT or ANSYS Fluent, etc., and a suitable coordinate system and view direction are set during drawing to ensure that the temperature and pressure distribution of the rocket and the surrounding environment can be clearly displayed. The cloud map drawing function in the existing drawing software is used to map the temperature and pressure data to the grid on the surface of the rocket to generate a temperature cloud map (such as Figure 3 as shown) and pressure cloud diagram (as shown) Figure 4 and adjust the color and transparency of the cloud map to make the temperature and pressure distribution more intuitive;

[0075] By observing the temperature cloud map, we can identify areas with higher temperatures on the baffle surface and focus on the temperature changes in these areas. By observing the pressure cloud map, we can identify areas with higher pressure on the baffle surface and analyze the pressure distribution in these areas. Based on the temperature and pressure distribution analysis results and the preset safety factors, we can optimize the baffle's target height, width, thickness and other parameters. Specifically:

[0076] Adjust the height of the baffle to effectively withstand the heat and pressure generated during rocket launch; adjust the width of the baffle to ensure that its coverage area can meet the needs of rocket launch; adjust the thickness of the baffle to improve its strength and stability to adapt to different temperature and pressure environments;

[0077] By simulating the scene during rocket launch and drawing temperature and pressure cloud maps based on the temperature and pressure obtained after simulation calculation, the temperature and pressure distribution of each part of the baffle are analyzed, and the parameters of the baffle are optimized based on the preset safety factor, thereby improving the safety and stability of the rocket during launch.

[0078] like Figure 5 As shown, an embodiment of the present invention further provides a device 50 for determining parameters of a launch vessel baffle, comprising:

[0079] An acquisition module 51 is used to acquire a three-dimensional model of a baffle when the rocket is launched at a preset launch altitude;

[0080] The processing module 52 is configured to mesh the three-dimensional model of the baffle to obtain a plurality of unit grids; perform numerical simulation calculations on each of the plurality of unit grids to obtain simulation calculation results, wherein the simulation calculation results include the temperature and pressure of each unit grid in the three-dimensional model of the baffle; and optimize the parameters of the baffle based on the simulation calculation results to obtain target parameters, wherein the target parameters include a target height, a target width, and a target thickness of the baffle.

[0081] Optionally, the processing module 52 is configured to perform grid division on the baffle three-dimensional model to obtain a plurality of unit grids, including:

[0082] The baffle three-dimensional model is meshed within a preset calculation domain to obtain a discretized numerical calculation unit mesh, and the inlet boundary and wall boundary of the baffle three-dimensional model are set.

[0083] Optionally, the processing module 52 is further configured to:

[0084] The numerical calculation unit grid is subjected to structured grid encryption processing to obtain an encrypted numerical calculation unit grid.

[0085] Optionally, the processing module 52 is configured to perform numerical simulation calculations on the plurality of unit grids to obtain simulation calculation results, including:

[0086] Determine the mathematical model corresponding to the numerical simulation calculation process;

[0087] According to the mathematical model, a numerical simulation calculation is performed on each unit grid in the three-dimensional model to obtain the simulation calculation result.

[0088] Optionally, the processing module 52 is used to determine a mathematical model corresponding to the numerical simulation calculation process, including:

[0089] The mathematical model corresponding to the numerical simulation calculation process is determined based on the jet temperature, jet velocity, jet pressure of the nozzle during rocket launch and the preset altitude during launch.

[0090] Optionally, the mathematical model includes:

[0091]

[0092] Where ρ represents the fluid density; u i represents the velocity component; μ represents the dynamic viscosity; μ t represents turbulent viscosity; σ k The turbulent Prandtl number represents the turbulent kinetic energy k; σ ∈ The turbulent Prandtl number represents the turbulent energy dissipation rate ∈; P k represents the turbulent kinetic energy generation term; G h (ρ, T, P) represents the highly turbulent kinetic energy generated due to the change in rocket altitude; C1 and C2 represent constant terms.

[0093] Optionally, the processing module 52 is configured to optimize the parameters of the baffle according to the simulation calculation results to obtain target parameters, including:

[0094] According to the temperature and pressure of each unit grid, the temperature cloud map and pressure cloud map at the time of rocket launch are obtained;

[0095] According to the temperature cloud map, the pressure cloud map and the preset safety factor, the parameters of the baffle are optimized to obtain the target parameters.

[0096] It should be noted that this device is a device corresponding to the above-mentioned embodiment of the method for determining the parameters of the launch ship baffle. All implementation methods in the above-mentioned method embodiment are applicable to the embodiment of this device and can achieve the same technical effect.

[0097] An embodiment of the present invention further provides a computing device comprising: a processor and a memory storing a computer program, wherein the computer program, when executed by the processor, performs the method described in the above embodiment. All implementations of the above method embodiments are applicable to this embodiment and can achieve the same technical effects.

[0098] The present invention also provides a computer-readable storage medium storing instructions that, when executed on a computer, cause the computer to execute the method described in the above embodiment. All implementations of the above method embodiments are applicable to this embodiment and can achieve the same technical effects.

[0099] Those skilled in the art will appreciate that the units and algorithm steps of each example described in conjunction with the embodiments disclosed herein can be implemented in electronic hardware, or a combination of computer software and electronic hardware. Whether these functions are performed in hardware or software depends on the specific application and design constraints of the technical solution. Professionals and technicians can use different methods to implement the described functions for each specific application, but such implementation should not be considered beyond the scope of the present invention.

[0100] Those skilled in the art will clearly understand that, for the convenience and brevity of description, the specific working processes of the systems, devices and units described above can refer to the corresponding processes in the aforementioned method embodiments and will not be repeated here.

[0101] In the embodiments provided by the present invention, it should be understood that the disclosed 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 merely a logical function division. In actual implementation, there may be other division methods, such as multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. In addition, the mutual coupling or direct coupling or communication connection shown or discussed can be through some interface, indirect coupling or communication connection of devices or units, which can be electrical, mechanical or other forms.

[0102] The units described as separate components may or may not be physically separate, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed across multiple network units. Some or all of these units may be selected to achieve the purpose of this embodiment according to actual needs.

[0103] In addition, each functional unit in each embodiment of the present invention may be integrated into one processing unit, or each unit may exist physically separately, or two or more units may be integrated into one unit.

[0104] If the functions are implemented in the form of software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, or the part that contributes to the prior art, or part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions for enabling a computer device (which can be a personal computer, server, or network device, etc.) to execute all or part of the steps of the method described in each embodiment of the present invention. The aforementioned storage medium includes various media that can store program code, such as a USB flash drive, a mobile hard drive, ROM, RAM, a magnetic disk, or an optical disk.

[0105] In addition, it should be noted that, in the apparatus and method of the present invention, it is obvious that each component or each step can be decomposed and / or recombined. These decompositions and / or recombinations should be regarded as equivalent schemes of the present invention. Moreover, the steps of performing the above-mentioned series of processing can naturally be performed in chronological order according to the order of description, but it is not necessary to perform them in chronological order, and some steps can be performed in parallel or independently of each other. For those of ordinary skill in the art, it will be understood that all or any steps or components of the method and apparatus of the present invention can be implemented in any computing device (including processors, storage media, etc.) or a network of computing devices in hardware, firmware, software or a combination thereof, which can be achieved by those of ordinary skill in the art using their basic programming skills after reading the description of the present invention.

[0106] Therefore, the purpose of the present invention can also be achieved by running a program or a group of programs on any computing device. The computing device can be a well-known general-purpose device. Therefore, the purpose of the present invention can also be achieved simply by providing a program product containing program code that implements the method or device. That is to say, such a program product also constitutes the present invention, and the storage medium storing such a program product also constitutes the present invention. Obviously, the storage medium can be any well-known storage medium or any storage medium developed in the future. It should also be pointed out that in the device and method of the present invention, it is obvious that each component or each step can be decomposed and / or recombined. These decompositions and / or recombinations should be regarded as equivalent schemes of the present invention. In addition, the steps of performing the above-mentioned series of processing can naturally be performed in chronological order according to the order of description, but do not necessarily need to be performed in chronological order. Certain steps can be performed in parallel or independently of each other.

[0107] The above is a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention. These improvements and modifications should also be regarded as within the scope of protection of the present invention.

Claims

1. A method for determining the parameters of a launch ship spoiler, characterized in that: include: Obtain a three-dimensional model of the baffle when the rocket is launched at a preset launch altitude; Meshing the baffle three-dimensional model to obtain a plurality of unit grids; Performing numerical simulation calculations on the plurality of unit grids to obtain simulation calculation results, wherein the simulation calculation results include the temperature and pressure of each unit grid in the baffle three-dimensional model; Optimizing the parameters of the baffle according to the simulation calculation results to obtain target parameters, wherein the target parameters include: a target height, a target width, and a target thickness of the baffle; The baffle three-dimensional model is meshed to obtain a plurality of unit meshes, including: The baffle three-dimensional model is meshed within a preset computational domain to obtain a discretized numerical computation unit grid, and an inlet boundary and a wall boundary of the baffle three-dimensional model are set. Specifically, the baffle three-dimensional model is discretized into a series of nodes within the continuous preset computational domain to obtain a discretized numerical computation unit grid, wherein each discretized numerical computation unit grid represents a micro-region; the size and density of a single discretized numerical computation unit grid are determined according to the geometric shape, accuracy, and computational domain of the baffle; performing structured mesh encryption processing on the numerical calculation unit grid to obtain an encrypted numerical calculation unit grid; specifically, performing mesh encryption in the jet impact area of ​​the baffle to obtain an encrypted numerical calculation unit grid, and adjusting the mesh size and distribution to ensure that the encrypted grid accurately reflects the local geometric characteristics of the baffle; Numerical simulation calculations are performed on the plurality of unit grids to obtain simulation calculation results, including: Determine the mathematical model corresponding to the numerical simulation calculation process; Performing numerical simulation calculations on each unit grid in the three-dimensional model according to the mathematical model to obtain the simulation calculation results; Determine the mathematical model corresponding to the numerical simulation calculation process, including: Determine the mathematical model corresponding to the numerical simulation calculation process based on the jet temperature, jet velocity, jet pressure of the nozzle during rocket launch and the preset altitude during launch; The mathematical model includes: ； ； in, represents the fluid density; represents the velocity component; represents dynamic viscosity; represents the turbulent viscosity; The turbulent Prandtl number represents the turbulent kinetic energy k; represents the turbulent energy dissipation rate The turbulent Prandtl number; represents the turbulent kinetic energy generation term; represents the high turbulence kinetic energy generation term caused by the change of rocket altitude; C1 and C2 represent constant terms; in, ; ; represents an empirical constant that adjusts the relationship between turbulent viscosity and turbulent kinetic energy and dissipation rate, represents the velocity gradient; is the symmetric part of the velocity gradient, indicating that the gradients of the velocity field in both directions are equal; ; Wherein, T represents the jet temperature; T0 is the set reference temperature; P represents the jet pressure, and P0 is the set jet pressure; is the square of the velocity divergence, which represents the velocity gradient in the flow field.

2. The method for determining the parameters of the launch ship spoiler according to claim 1, characterized in that: Based on the simulation results, the parameters of the baffle are optimized to obtain target parameters, including: According to the temperature and pressure of each unit grid, the temperature cloud map and pressure cloud map at the time of rocket launch are obtained; According to the temperature cloud map, the pressure cloud map and the preset safety factor, the parameters of the baffle are optimized to obtain the target parameters.

3. A device for determining parameters of a launch ship spoiler, characterized in that: include: An acquisition module is used to obtain a three-dimensional model of a baffle when the rocket is launched at a preset launch altitude; a processing module configured to mesh the baffle three-dimensional model to obtain a plurality of unit grids; and perform numerical simulation calculations on each of the plurality of unit grids to obtain simulation calculation results, wherein the simulation calculation results include the temperature and pressure of each unit grid in the baffle three-dimensional model; Optimizing the parameters of the baffle according to the simulation calculation results to obtain target parameters, wherein the target parameters include: a target height, a target width, and a target thickness of the baffle; The baffle three-dimensional model is meshed to obtain a plurality of unit meshes, including: The baffle three-dimensional model is meshed within a preset computational domain to obtain a discretized numerical computation unit grid, and an inlet boundary and a wall boundary of the baffle three-dimensional model are set. Specifically, the baffle three-dimensional model is discretized into a series of nodes within the continuous preset computational domain to obtain a discretized numerical computation unit grid, wherein each discretized numerical computation unit grid represents a micro-region; the size and density of a single discretized numerical computation unit grid are determined according to the geometric shape, accuracy, and computational domain of the baffle; performing structured mesh encryption processing on the numerical calculation unit grid to obtain an encrypted numerical calculation unit grid; specifically, performing mesh encryption in the jet impact area of ​​the baffle to obtain an encrypted numerical calculation unit grid, and adjusting the mesh size and distribution to ensure that the encrypted grid accurately reflects the local geometric characteristics of the baffle; Numerical simulation calculations are performed on the plurality of unit grids to obtain simulation calculation results, including: Determine the mathematical model corresponding to the numerical simulation calculation process; Performing numerical simulation calculations on each unit grid in the three-dimensional model according to the mathematical model to obtain the simulation calculation results; Determine the mathematical model corresponding to the numerical simulation calculation process, including: Determine the mathematical model corresponding to the numerical simulation calculation process based on the jet temperature, jet velocity, jet pressure of the nozzle during rocket launch and the preset altitude during launch; The mathematical model includes: ； ； in, represents the fluid density; represents the velocity component; represents dynamic viscosity; represents the turbulent viscosity; The turbulent Prandtl number represents the turbulent kinetic energy k; represents the turbulent energy dissipation rate The turbulent Prandtl number; represents the turbulent kinetic energy generation term; represents the high turbulence kinetic energy generation term caused by the change of rocket altitude; C1 and C2 represent constant terms; in, ; ; represents an empirical constant that adjusts the relationship between turbulent viscosity and turbulent kinetic energy and dissipation rate, represents the velocity gradient; is the symmetric part of the velocity gradient, indicating that the gradients of the velocity field in both directions are equal; ; Wherein, T represents the jet temperature; T0 is the set reference temperature; P represents the jet pressure, and P0 is the set jet pressure; is the square of the velocity divergence, which represents the velocity gradient in the flow field.

4. A computing device, characterized in that include: A processor and a memory storing a computer program, wherein when the computer program is executed by the processor, the method according to any one of claims 1 to 2 is performed.

5. A computer-readable storage medium, characterized in that: The device stores instructions, which, when executed on a computer, enable the computer to execute the method according to any one of claims 1 to 2.

Images