Method, device and equipment for determining parameters of flow baffle of launching ship

Abstract

The invention provides a method, a device and equipment for determining parameters of a flow baffle of a launching ship, and relates to the technical field of rocket launching analysis. The method for determining the parameters of the flow baffle of the launching ship comprises the following steps: acquiring a three-dimensional model of the flow baffle when a rocket is launched at a preset launching height; performing grid division on the three-dimensional model of the flow baffle to obtain a plurality of unit grids; performing numerical simulation calculation on the plurality of unit grids to obtain simulation calculation results; the simulation calculation result comprises the temperature and the pressure of each unit grid in the three-dimensional model of the flow baffle; according to the simulation calculation result, parameters of the flow baffle are optimized, target parameters are obtained, and the target parameters comprise the target height, the target width and the target thickness of the flow baffle. According to the scheme provided by the invention, the temperature and pressure of the flow baffle impacted by heat flow can be accurately simulated and analyzed at the preset emission height, and theoretical and data support is provided for parameters during design of the flow baffle.

Description

Technical Field

[0001] The present invention relates to the technical field of launching ships, and in particular to a method, a device and equipment for determining parameters of a baffle of a launching ship. 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 guide chute of the current offshore 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, and 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, 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 baffle, which simulates and analyzes the temperature and pressure on the baffle at a preset launch altitude, so as to provide theoretical and data support for the parameters of 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 solution of the present invention is as follows:

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

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

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

[0008] Performing numerical simulation calculations on the plurality of unit grids respectively to obtain simulation calculation results; 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 the wall boundary of the baffle three-dimensional model are set.

[0012] Optionally, the method for determining the parameters of the launch ship 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 respectively to obtain simulation calculation results, including:

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

[0016] According to the mathematical model, 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 according to 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 the 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 generation term caused by the change of 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 when the rocket is launched 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 ship baffle, comprising:

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

[0027] A processing module is used to mesh the three-dimensional model of the baffle to obtain a plurality of unit grids; perform 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; and optimize 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.

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

[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 baffle of a launch ship described in the present invention obtains a three-dimensional model of the baffle when a rocket is launched at a preset launch altitude; meshes the three-dimensional model of the baffle to obtain a plurality of unit grids; performs numerical simulation calculations on the plurality of unit grids respectively 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; according to the simulation calculation results, the parameters of the baffle are optimized to obtain target parameters, and the target parameters include: the target height, target width and target thickness of the baffle; the above scheme of the present invention simulates and analyzes the temperature and pressure on the baffle at the preset launch altitude, so as 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 the rocket launch and reduce the impact force borne by other equipment on the launch ship. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0033] Figure 2 An optional embodiment of the method for determining the parameters of the launch ship 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 diagram drawn according to temperature data obtained by three-dimensional numerical simulation is provided in an optional embodiment of the method for determining parameters of a launch ship baffle of the present invention;

[0035] Figure 4 A pressure cloud diagram drawn according to pressure data obtained by three-dimensional numerical simulation is provided in an optional embodiment of the method for determining parameters of a launch ship 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 of the present invention.

[0037] Description of reference numerals:

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

[0039] The exemplary embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. Although the 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. On the contrary, these embodiments are provided in order to enable a more thorough understanding of the present invention and to enable the scope of the present invention to be fully communicated 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 ship baffle, comprising:

[0041] Step 11, obtaining a three-dimensional model of a 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 meshes;

[0043] Step 13, performing numerical simulation calculations on the plurality of unit grids respectively 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, optimizing the parameters of the baffle plate 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 plate.

[0045] In this embodiment, it should be noted that Figure 2As shown, since the baffle plate 21 is set at a fixed position in actual applications, when simulating and analyzing the impact of the heat flow generated by the nozzle 23 on the baffle plate during rocket launch (the impact of the heat flow on the baffle plate is mainly reflected in the distribution of temperature and pressure on the baffle plate), only the impact of the heat flow generated by the rocket at different launch altitudes on the baffle plate 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 baffle three-dimensional model can be established by CAD software or other professional geometric modeling software according to the pre-set parameters of the baffle; the parameters of the baffle may include: the height, width and thickness of the baffle;

[0047] The established three-dimensional model of the baffle is gridded, and within the calculation range defined by the thermal flow field formed by the heat flow ejected from the tail of the nozzle during rocket launch, a three-dimensional numerical simulation calculation is performed on each unit grid obtained after the division to determine the temperature and pressure corresponding to each unit grid at different launch altitudes; further, according to 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 flow generated during rocket launch and reduce the influence of the heat flow generated during rocket launch on the temperature and pressure of other equipment on the launch ship; the present invention provides a reliable evaluation and optimization method for the parameter design of the baffle by establishing a three-dimensional model of the baffle and performing three-dimensional numerical simulation calculations at a preset launch altitude and within the defined flow field calculation range, 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 mesh, and setting an inlet boundary and a wall boundary of the baffle three-dimensional model.

[0050] In this embodiment, since a thermal flow field may be generated around the entire baffle when the rocket is launched, in order to facilitate the computer to perform numerical simulation calculations, the three-dimensional model of the baffle may be gridded. Specifically, the three-dimensional model of the baffle is discretized into a series of nodes in the continuous preset calculation domain to obtain a discretized numerical calculation unit grid, each calculation unit grid representing a tiny area; here, the size and density of a single calculation unit grid may be determined according to the geometric shape, accuracy and calculation domain range of the baffle, thereby ensuring a balance between the accuracy and calculation efficiency of subsequent numerical simulation calculations;

[0051] In this embodiment, meshing software such as ANSYS Fluent or ICEM CFD can be used to mesh the baffle three-dimensional model. Specifically, the baffle three-dimensional model is imported into the meshing software, and the baffle three-dimensional model is meshed according to the set meshing parameters, such as mesh size, mesh type (structured or unstructured), etc., 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, in order to further improve the calculation accuracy, the numerical calculation unit grid is subjected to structured grid encryption processing. Specifically, the grid is encrypted in the key area 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, according to the set simulation parameters and the flow characteristics of the airflow ejected from the nozzle during rocket launch, the mathematical model corresponding to the subsequent numerical simulation calculation process can be determined and fitted; further, by performing numerical simulation calculations with 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 step 131, which may specifically include:

[0060] Step 1311, according to the jet temperature, jet velocity, jet pressure of the nozzle when the rocket is launched and the preset height when launching, determine the mathematical model corresponding to the numerical simulation calculation process.

[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 the 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 generation term caused by the change of 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 regulates 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 greater the altitude, the smaller 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 baffle three-dimensional model into numerical simulation software, such as ANSYS Fluent, and perform the following operations: set boundary conditions, which may include an inlet, an outlet, a wall, etc. (here, the corresponding boundary conditions can be set according to the actual conditions of the nozzle outlet and the inlet); input the parameters such as the preset launch height, the jet temperature, the jet velocity, and the jet pressure during rocket launch, discretize the mathematical model using the finite element method or the finite difference method, and solve the discretized equation group using an iterative algorithm until the convergence condition is reached, thereby obtaining the temperature and pressure data of each unit grid in the baffle three-dimensional 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 when the rocket is launched according to the temperature and pressure of each unit grid;

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

[0074] In this embodiment, according to the temperature and pressure of each unit grid, the temperature cloud map and pressure cloud map during rocket launch are drawn to analyze the temperature and pressure distribution of each part of the baffle; here, the cloud map can be drawn by 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 As shown in the figure), 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, find out the areas with higher temperature on the baffle surface, and focus on the temperature changes in these areas; by observing the pressure cloud map, find out the areas with higher pressure on the baffle surface, and analyze the pressure distribution in these areas; according to the temperature and pressure distribution analysis results, combined with the preset safety factor, optimize the parameters such as the target height, width and thickness of the baffle, 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 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 launch.

[0078] like Figure 5 As shown, an embodiment of the present invention further provides a device 50 for determining parameters of a launch ship 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 used to mesh the three-dimensional model of the baffle to obtain a plurality of unit grids; perform 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; and optimize 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.

[0081] Optionally, the processing module 52 is used 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 the wall boundary of the baffle three-dimensional model are set.

[0083] Optionally, the processing module 52 is further used for:

[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 used to perform numerical simulation calculations on the plurality of unit grids respectively to obtain simulation calculation results, including:

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

[0087] According to the mathematical model, 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 according to 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 the 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 generation term caused by the change of rocket altitude; C1 and C2 represent constant terms.

[0093] Optionally, the processing module 52 is used 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 when the rocket is launched 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 method embodiment for determining the parameters of the launch ship baffle, and 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] The embodiment of the present invention further provides a computing device, including: a processor, a memory storing a computer program, and when the computer program is executed by the processor, the method described in the above embodiment is executed. All implementations in the above method embodiment are applicable to this embodiment and can achieve the same technical effect.

[0098] In an embodiment of the present invention, a computer-readable storage medium is further provided, which stores instructions, and when the instructions are executed on a computer, the computer executes the method described in the above embodiment. All implementations in the above method embodiment are applicable to this embodiment, and can also achieve the same technical effect.

[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. Professional and technical personnel can use different methods to implement the described functions for each specific application, but such implementation should not be considered to be beyond the scope of the present invention.

[0100] Those skilled in the art can 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 only schematic. For example, the division of the units is only a logical function division. There may be other division methods in actual implementation, such as multiple units or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the mutual coupling or direct coupling or communication connection shown or discussed can be through some interfaces, 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 separated, and the components shown as units may or may not be physical units, that is, they may be located in one place or distributed on multiple network units. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.

[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 the 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, including several instructions for a computer device (which can be a personal computer, server, or network device, etc.) to perform 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 codes, such as USB flash drives, mobile hard disks, ROM, RAM, magnetic disks, or optical disks.

[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 is 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 device. Therefore, the purpose of the present invention can also be achieved by simply providing a program product containing a 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 it is not necessary to perform them in chronological order. Some 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 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 a baffle when the rocket is launched at a preset launch altitude; Meshing the baffle three-dimensional model to obtain a plurality of unit meshes; Performing numerical simulation calculations on the plurality of unit grids respectively to obtain simulation calculation results; the simulation calculation results include the temperature and pressure of each unit grid in the baffle three-dimensional model; 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.

2. The method for determining the parameters of the launch ship baffle according to claim 1, characterized in that: 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 calculation domain to obtain a discretized numerical calculation unit mesh, and the inlet boundary and the wall boundary of the baffle three-dimensional model are set.

3. The method for determining the parameters of the launch ship baffle according to claim 2, characterized in that: Also includes: The numerical calculation unit grid is subjected to structured grid encryption processing to obtain an encrypted numerical calculation unit grid.

4. The method for determining the parameters of the launch ship baffle according to claim 1, characterized in that: 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; According to the mathematical model, numerical simulation calculation is performed on each unit grid in the three-dimensional model to obtain the simulation calculation result.

5. The method for determining the parameters of the launch ship baffle according to claim 4, characterized in that: Determine the mathematical model corresponding to the numerical simulation calculation process, including: The mathematical model corresponding to the numerical simulation calculation process is determined according to the jet temperature, jet velocity, jet pressure of the nozzle during rocket launch and the preset altitude during launch.

6. The method for determining the parameters of the launch ship baffle according to claim 5, characterized in that: The mathematical model includes: Where ρ represents the fluid density; u i represents the velocity component; μ represents the dynamic viscosity; μ t represents the 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 generation term caused by the change of rocket altitude; C1 and C2 represent constant terms.

7. The method for determining the parameters of the launch ship baffle according to claim 1, characterized in that: According to the simulation calculation 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 when the rocket is launched 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.

8. A device for determining the parameters of a launch ship spoiler, characterized in that: include: An acquisition module, used to acquire a three-dimensional model of a baffle when the rocket is launched at a preset launch altitude; A processing module, used for meshing the baffle three-dimensional model to obtain a plurality of unit grids; performing numerical simulation calculations on the plurality of unit grids respectively to obtain simulation calculation results; the simulation calculation results include the temperature and pressure of each unit grid in the baffle three-dimensional model; 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.

9. 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 7 is performed.

10. A computer-readable storage medium, characterized in that: Instructions are stored, and when the instructions are executed on a computer, the computer is caused to execute the method according to any one of claims 1 to 7.

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