Magnetic levitation propulsion dynamics calculation method, device, equipment and medium

Abstract

The invention discloses a magnetic levitation propulsion dynamics calculation method and device, equipment and a medium, an electromagnetic propulsion booster dynamics model and an electromagnetic propulsion booster aerodynamic model are established, a real-time exchange database is established based on Fluent UDF, the electromagnetic propulsion booster dynamics model and the electromagnetic propulsion booster aerodynamic model are subjected to data exchange, and a real-time simulation result is obtained. Carrying out dynamic calculation by using an electromagnetic propulsion booster dynamic model to obtain displacement data of the booster, converting the displacement data into an aerodynamic load of the booster, and solving a dynamic equation based on the aerodynamic load of the booster, the preset electromagnetic force, the shoe rail acting force and the structural parameters to obtain the displacement of the next time step. Under the condition that all time steps are completed, a dynamic response curve of the whole operation process is generated, the defect that a traditional interpolation method cannot reflect dynamic reaction is overcome based on a Fluent UDF database dynamic interaction and step-by-step start-stop control strategy, and synchronous accurate solution of aerodynamic loads and structural responses is achieved.

Description

Technical Field

[0001] The present application relates to the field of load calculation technology, and more specifically, to a method, device, equipment, and medium for calculating magnetic levitation propulsion dynamics. Background Art

[0002] During operation, the booster's speed constantly fluctuates, accompanied by strong vibrations, causing its attitude to dynamically change. These changes in speed and attitude directly affect the aerodynamic and electromagnetic loads acting on the booster; these loads, in turn, significantly influence the booster's dynamic response characteristics. The coupling between dynamic response and aerodynamic / electromagnetic loads is particularly strong under high-speed operation. Accurately calculating the system's dynamic response throughout operation is not only a key foundation for guiding the design of each subsystem, but also a core prerequisite for ensuring the safe operation of the entire system.

[0003] Currently, dynamic calculations that simulate the full-range dynamic response of a booster primarily consider the combined effects of aerodynamic and electromagnetic loads. A commonly used implementation method in the industry is: First, through theoretical calculations, wind tunnel tests, or numerical simulations, the aerodynamic loads of the booster at different operating speeds and attitude angles, as well as the electromagnetic loads at different operating speeds and magnetic track spacings, are pre-calculated. The calculated aerodynamic and electromagnetic load data are then organized into a multidimensional interpolation table. Finally, during dynamic calculations, the current aerodynamic and electromagnetic loads are obtained in real time through table lookup and interpolation based on state parameters such as the current speed, attitude angle, and magnetic track spacing, and are then input into the dynamics model as external excitation.

[0004] While the aforementioned load input method based on a preset interpolation table can simulate the dynamic response process to a certain extent, it has significant shortcomings: First, the interpolation point coverage and adaptability are limited. The key state parameter points such as speed and attitude required for interpolation calculations are pre-selected discrete points. This selection method cannot fully cover all possible operating conditions. In particular, during rapid speed changes or transient processes within a specific speed range, the interpolation points may not accurately capture the complex dynamic response characteristics within that range. Second, it ignores the dynamic reaction of the load. Existing methods generally use a "steady" assumption when calculating aerodynamic loads. This approach completely ignores the dynamic reaction effects of the actual motion of the booster on the surrounding flow field, meaning it fails to reflect the reaction of the dynamic response to the aerodynamic loads. Therefore, there is a fundamental gap between the aerodynamic load input provided by the interpolation method and the actual unsteady aerodynamic loads of the booster, which are affected by its own dynamic response feedback, resulting in reduced accuracy in the dynamic calculations. This directly affects the reliability of the system design and the accuracy of the operational safety assessment. Summary of the Invention

[0005] The purpose of this application is to provide a method, device, equipment and medium for calculating the dynamics of magnetic levitation propulsion in order to overcome the existing technical defects. By solving the aerodynamic and dynamic coupling problem, the aerodynamic loads that change during operation are calculated in real time, so that the consideration of the aerodynamic loads during the operation of the magnetic levitation electromagnetic propulsion booster is closer to the actual situation, and the calculated aerodynamic loads and dynamic responses are also more accurate.

[0006] The purpose of this application is achieved through the following technical solutions: In a first aspect, the present application proposes a method for calculating magnetic levitation propulsion dynamics, the method comprising: Establish the dynamic model of electromagnetic propulsion booster and the aerodynamic model of electromagnetic propulsion booster respectively; A real-time exchange database is established based on Fluent UDF, enabling data exchange between the electromagnetic propulsion booster dynamics model and the electromagnetic propulsion booster aerodynamics model; The electromagnetic propulsion booster dynamics model is used to perform dynamics calculations to obtain the booster displacement data; The electromagnetic propulsion booster aerodynamic model is used to convert the displacement data into aerodynamic loads on the booster; The electromagnetic propulsion booster dynamics model is used to solve the dynamic equations based on the booster's aerodynamic load, preset electromagnetic force, shoe rail force, and structural parameters to obtain the displacement of the next time step; When all time steps are completed, a dynamic response curve for the entire run is generated.

[0007] In one possible implementation, the dynamic model of the electromagnetic propulsion booster is established using the multi-body dynamics software Simpack. The steps of establishing the dynamic model of the electromagnetic propulsion booster include: Based on the mass, center of gravity coordinates and moment of inertia around the main axis of the booster, reference points for all electromagnetic loads, aerodynamic loads and shoe rail loads are established in the booster space, and the spatial three-dimensional coordinate parameters of all reference points are given; Force elements are created at each reference point. The force elements include aerodynamic force, electromagnetic force, and shoe rail force. The electromagnetic force is applied through an interpolation table, and the aerodynamic load reads the aerodynamic calculation result file through the substitution variable function.

[0008] In one possible implementation, the steps of establishing an aerodynamic model of an electromagnetic propulsion booster include: Import the booster's 3D geometry model through the fluid simulation software Fluent; Use grid pre-processing software to build the external flow field calculation grid for the three-dimensional geometric model; A three-dimensional unsteady calculation method is used, and the turbulence model is set as the SST k-ω model; The computational domain boundary is set as the pressure outlet boundary, the track surface is set as the no-slip wall, and the booster surface is set as the moving wall. The initial condition is set as the initial velocity of the booster equal to zero, and the motion of the booster in the flow field is simulated using the overlapping grid and moving grid coupling strategy.

[0009] In a possible implementation, the six-degree-of-freedom motion speed of the moving wall is determined by using a user-defined function to read displacement data output by dynamics calculation in real time.

[0010] In one possible implementation, the step of converting displacement data into aerodynamic loads of the booster using an electromagnetic propulsion booster aerodynamic model includes: In each time step, the displacement data is read from the real-time exchange database. The displacement data contains the three-dimensional position coordinates of each reference point on the booster surface in the current time step and the previous time step. Calculate the displacement difference of each reference point and calculate the moving speed of the booster surface; The booster surface moving speed is set as the booster wall boundary condition through the DEFINE_CG_MOTION module of Fluent UDF; Perform iterative calculation of the three-dimensional unsteady flow field, use the f_loop(f_all,thread) function to traverse the surface grid cells, and combine the F_CENTROID(x,f_all,thread) function to extract the pressure center coordinates; Based on the pressure distribution and the pressure center coordinates, the six-degree-of-freedom aerodynamic load vector is calculated by integration.

[0011] In a possible implementation, the steps after calculating the six-degree-of-freedom aerodynamic load vector further include: Write the aerodynamic load vector into a text file in the real-time exchange database and update the file content in overwrite mode.

[0012] In one possible implementation, the kinetic equation is: ,in 、 、 are the mass, damping and stiffness of the booster system, is the displacement of the system, For speed, is the acceleration, The external force acting on the system.

[0013] In a second aspect, the present application proposes a magnetic levitation propulsion dynamics calculation device, the device comprising: A construction module is used to establish a dynamic model of an electromagnetic propulsion booster and an aerodynamic model of an electromagnetic propulsion booster respectively; The data exchange module is used to establish a real-time exchange database based on Fluent UDF, enabling data exchange between the electromagnetic propulsion booster dynamic model and the electromagnetic propulsion booster aerodynamic model; A calculation module, used to perform dynamic calculations using an electromagnetic propulsion booster dynamics model to obtain displacement data of the booster; A conversion module for converting displacement data into aerodynamic loads on the booster using an electromagnetic propulsion booster aerodynamic model; A solver module is used to use the electromagnetic propulsion booster dynamics model to solve the dynamic equations based on the booster's aerodynamic loads and preset electromagnetic forces, shoe rail forces, and structural parameters to obtain the displacement of the next time step; The generation module is used to generate the dynamic response curve of the entire operation process when all time steps are completed.

[0014] In a third aspect, the present application also proposes a computer device, which includes a processor and a memory, wherein a computer program is stored in the memory, and the computer program is loaded and executed by the processor to implement the magnetic levitation propulsion dynamics calculation method as described in any one of the first aspects.

[0015] In a fourth aspect, the present application further proposes a computer-readable storage medium, in which a computer program is stored. The computer program is loaded and executed by a processor to implement the magnetic levitation propulsion dynamics calculation method as described in any one of the first aspects.

[0016] The above-mentioned main solution of this application and its various further options can be freely combined to form multiple solutions, all of which are solutions that can be adopted and protected by this application. Moreover, in this application, (non-conflicting options) can also be freely combined with each other and with other options. After understanding the solution of this application, those skilled in the art will understand that there are many combinations based on existing technology and common knowledge, all of which are technical solutions to be protected by this application, and this is not an exhaustive list.

[0017] The present application discloses a magnetic levitation propulsion dynamics calculation method, apparatus, equipment and medium, establishes an electromagnetic propulsion booster dynamics model and an electromagnetic propulsion booster aerodynamic model, establishes a real-time exchange database based on Fluent UDF, enables the electromagnetic propulsion booster dynamics model and the electromagnetic propulsion booster aerodynamic model to exchange data, uses the electromagnetic propulsion booster dynamics model to perform dynamic calculations to obtain the booster's displacement data, converts the displacement data into the booster's aerodynamic load, solves the dynamic equation based on the booster's aerodynamic load and preset electromagnetic force, shoe rail force and structural parameters to obtain the displacement of the next time step, generates a dynamic response curve for the entire operation process when all time steps are completed, and solves the problem of traditional interpolation method's inability to reflect dynamic reaction based on the Fluent UDF database dynamic interaction and step-by-step start-stop control strategy, thereby achieving the synchronous and accurate solution of aerodynamic load and structural response. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following is a brief introduction to the drawings required for use in the embodiments. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without creative work.

[0019] Figure 1 A flow chart of a magnetic levitation propulsion dynamics calculation method proposed in an embodiment of the present application is shown.

[0020] Figure 2 The figure shows a coupling calculation flow chart proposed in an embodiment of the present application.

[0021] Figure 3 A schematic diagram of the interaction between Fluent and Simpack software proposed in an embodiment of the present application based on the start-stop control law in coupled calculations is shown.

[0022] Figure 4 The graph showing the change of aerodynamic drag during the entire operation of the booster obtained by coupling calculation is shown.

[0023] Figure 5 The graph of aerodynamic lift variation during the entire booster operation obtained by coupling calculation is shown.

[0024] Figure 6 The aerodynamic pitch moment variation curve of the booster throughout the entire operation obtained by coupling calculation.

[0025] Figure 7 A graph showing the change of booster operating speed over time obtained through coupling calculation is shown.

[0026] Figure 8The graph showing the change in vertical displacement of the center of the suspension magnet with time during the operation of the booster obtained by coupling calculation is shown. DETAILED DESCRIPTION

[0027] The following describes the implementation methods of the present application through specific examples. The present application can also be implemented or applied through other different specific implementation methods. The details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that the following embodiments and features in the embodiments can be combined with each other unless they conflict.

[0028] Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making any creative work shall fall within the scope of protection of this application.

[0029] In the existing technology, the interpolation calculation method can reflect the effect of aerodynamic load on dynamic response during operation to a certain extent. However, the selection of interpolation speed points may ignore the dynamic response characteristics within some speed ranges. In addition, the aerodynamic load in the interpolation calculation method adopts a steady-state calculation, which cannot reflect the reaction of dynamic response to aerodynamic load. In summary, there is a gap between the consideration of aerodynamic load by the existing interpolation calculation method and the actual situation.

[0030] In order to solve the problems in the prior art, the embodiments of the present application propose a method, device, equipment and medium for calculating the dynamics of magnetic levitation propulsion, which can overcome the limitations of aerodynamic load data in the aerodynamic interpolation calculation method, introduce the fluid-solid coupling concept into the dynamics calculation of magnetic levitation electromagnetic propulsion, and calculate the aerodynamic load that changes during operation in real time through the aerodynamic and dynamic coupling solution. This makes the consideration of the aerodynamic load during the operation of the magnetic levitation electromagnetic propulsion booster closer to the actual situation, and the calculated aerodynamic load and dynamic response are also more accurate. It is described in detail below.

[0031] Please refer to Figure 1 , Figure 1 A schematic flow chart of a magnetic levitation propulsion dynamics calculation method proposed in an embodiment of the present application is shown, and the method includes: Step S1: Establish an electromagnetic propulsion booster dynamic model and an electromagnetic propulsion booster aerodynamic model respectively.

[0032] The aerodynamic model was established with the help of the fluid simulation software Fluent. By importing the three-dimensional geometric model of the booster, the external flow field grid was established for it using mesh pre-processing software. A strategy combining overlapping grids and dynamic grids was adopted, and aerodynamic calculations were performed in combination with the three-dimensional unsteady calculation method and the SST k-ω turbulence model. At the same time, the corresponding boundary conditions and initial conditions were set to simulate the movement of the booster in the flow field.

[0033] The dynamic model of the electromagnetic propulsion booster is established using the multi-body dynamics software Simpack. The steps for establishing the dynamic model of the electromagnetic propulsion booster include: Based on the mass, center of gravity coordinates and moment of inertia around the main axis of the booster, reference points for all electromagnetic loads, aerodynamic loads and shoe rail loads are established in the booster space, and the spatial three-dimensional coordinate parameters of all reference points are given; Force elements are created at each reference point. The force elements include aerodynamic force, electromagnetic force, and shoe rail force. The electromagnetic force is applied through an interpolation table, and the aerodynamic load reads the aerodynamic calculation result file through the substitution variable function.

[0034] First, the initial dynamic model framework of the booster is constructed based on basic parameters such as the booster's mass, center of gravity coordinates, and moment of inertia about the main axis. Subsequently, the application points of all electromagnetic, aerodynamic, and shoe rail loads are determined on the booster's spatial model, and the spatial three-dimensional coordinate parameters of these load reference points are given to ensure the accuracy of the load application locations. Furthermore, corresponding force elements are created at each load reference point, covering aerodynamic, electromagnetic, and shoe rail force elements.

[0035] Among them, the electromagnetic force is applied using an interpolation table to quickly and accurately obtain the magnitude of the electromagnetic force according to different working states and parameter conditions; and the aerodynamic load is dynamically read by the aerodynamic load result file generated by the aerodynamic calculation software Fluent with the help of Simpack's substitution variable function, realizing real-time updating and application of the aerodynamic load in the dynamic model, thereby completing the establishment of the electromagnetic propulsion booster dynamic model.

[0036] The steps to establish the aerodynamic model of the electromagnetic propulsion booster include: Import the booster's 3D geometry model through the fluid simulation software Fluent; Use grid pre-processing software to build the external flow field calculation grid for the three-dimensional geometric model; A three-dimensional unsteady calculation method is used, and the turbulence model is set as the SST k-ω model; The computational domain boundary is set as the pressure outlet boundary, the track surface is set as the no-slip wall, and the booster surface is set as the moving wall.

[0037] The initial condition is set as the initial velocity of the booster equal to zero, and the motion of the booster in the flow field is simulated using the overlapping grid and moving grid coupling strategy.

[0038] First, the 3D geometric model of the booster was imported into the fluid simulation software Fluent. Using professional mesh pre-processing software, the imported 3D model was used to generate the high-quality mesh required for external flow field calculations. The quality of the mesh directly affects the accuracy and efficiency of aerodynamic calculations. When setting up the aerodynamic calculations in Fluent, a 3D unsteady calculation method was employed to capture the time-varying characteristics of the flow field, ensuring that the calculation results reflect the complex aerodynamic behavior of the booster in actual motion. The SST k-ω model was also selected as the turbulence model, which offers high accuracy for near-wall and separated flows and can effectively simulate the turbulent characteristics of the complex flow field around the booster.

[0039] Regarding boundary conditions, the computational domain's outlet boundary is defined as a pressure outlet boundary to simulate the pressure environment surrounding the fluid as it exits the computational domain. The track surface is set as a no-slip wall, conforming to the physical condition of zero velocity on a solid surface in actual flow. The booster surface is set as a moving wall, with its six-degree-of-freedom velocity calculated from the dynamics calculation using a user-defined function (UDF). This enables data exchange between the aerodynamic and dynamic models, allowing the aerodynamic calculation to be dynamically adjusted based on the booster's actual motion state.

[0040] The initial condition is set to zero skid velocity, meaning the booster is initially stationary. To effectively simulate the booster's complex motion within the flow field, a coupled strategy combining overlapping and moving meshes is employed. Overlapping meshing can handle complex geometries and large-scale motion, while moving meshing accommodates the booster's shape changes and position shifts during motion. This combination ensures the computational mesh accurately tracks the booster's motion.

[0041] The six-degree-of-freedom motion speed of the moving wall is determined by a user-defined function that reads the displacement data output by the dynamic calculation in real time.

[0042] The data storage module acquires structural displacement data Δx, and then calculates the velocity of each degree of freedom according to the formula v = Δx / Δt (the ratio of structural displacement to time step). These velocity data are then applied to the boundary conditions on the booster wall. This real-time data interaction allows the aerodynamic model to dynamically adjust based on the dynamic calculation results, thereby more accurately simulating the complex motion of the booster during actual operation.

[0043] Step S2: establishing a real-time exchange database based on Fluent UDF, so that the electromagnetic propulsion booster dynamic model and the electromagnetic propulsion booster aerodynamic model can exchange data; A real-time exchange database, based on Fluent UDF, ensures data exchange between the electromagnetic propulsion booster dynamics model and the aerodynamics model. This database stores the six-degree-of-freedom aerodynamic loads and structural displacements of each component in the form of read-write text files and is continuously updated during the calculation process.

[0044] Step S3: Using the electromagnetic propulsion booster dynamics model to perform dynamics calculations to obtain the booster displacement data.

[0045] The dynamic model is used to calculate and obtain the displacement data of the booster, which is then stored in the real-time exchange database.

[0046] Step S4: using the electromagnetic propulsion booster aerodynamic model to convert the displacement data into the aerodynamic load of the booster.

[0047] The aerodynamic model reads displacement data from the database and converts it into aerodynamic loads. Specifically, the model uses a Fluent UDF to read the displacement data and the DEFINE_CG_MOTION module to convert the displacements into velocity boundary conditions for the booster wall. Then, through iterative calculations of the unsteady flow field, combined with the f_loop and F_CENTROID functions, the pressure center coordinates are extracted. Finally, the six-degree-of-freedom aerodynamic load vector is obtained based on the integral of the pressure distribution and output to the database.

[0048] The steps for converting displacement data into aerodynamic loads on the booster using the electromagnetic propulsion booster aerodynamic model include: In each time step, the displacement data is read from the real-time exchange database. The displacement data contains the three-dimensional position coordinates of each reference point on the booster surface in the current time step and the previous time step. Calculate the displacement difference of each reference point and calculate the moving speed of the booster surface; The booster surface moving speed is set as the booster wall boundary condition through the DEFINE_CG_MOTION module of Fluent UDF; Perform iterative calculation of the three-dimensional unsteady flow field, use the f_loop(f_all,thread) function to traverse the surface grid cells, and combine the F_CENTROID(x,f_all,thread) function to extract the pressure center coordinates; Based on the pressure distribution and the pressure center coordinates, the six-degree-of-freedom aerodynamic load vector is calculated by integration.

[0049] At each time step, displacement data is read from the real-time exchange database. This data contains the three-dimensional position coordinates of each reference point on the booster surface between the current and previous time steps. The displacement difference between each reference point is calculated, and the booster surface velocity is calculated using the formula v = Δx / Δt, where Δx is the structural displacement data and Δt is the time step. The calculated booster surface velocity is set as the booster wall boundary condition using the DEFINE_CG_MOTION module in the Fluent UDF to ensure that the aerodynamic calculations accurately reflect the booster's motion.

[0050] Next, an iterative calculation of the three-dimensional unsteady flow field is performed. During this process, the f_loop(f_all,thread) function is used to traverse the grid cells on the booster surface, and the pressure center coordinates of each grid cell are extracted in combination with the f_centroid(x,f_all,thread) function. Based on the pressure distribution of the flow field and the extracted pressure center coordinates, the six-degree-of-freedom aerodynamic load vector is calculated by integration, including aerodynamic drag, lift, side force, and torque about each axis. Finally, the calculated aerodynamic load results are output to the data storage module for reading and use by Simpack dynamic calculations.

[0051] Step S5: Using the electromagnetic propulsion booster dynamics model, the dynamics equation is solved based on the booster's aerodynamic load, preset electromagnetic force, shoe rail force, and structural parameters to obtain the displacement of the next time step.

[0052] The electromagnetic propulsion booster dynamics model is used for calculations to predict the displacement of the next time step. Specifically, the Simpack software is started according to the control law to solve the system dynamics equations. The dynamics calculation reads the aerodynamic load vector from the real-time exchange database and combines it with the preset electromagnetic load interpolation table, the shoe rail force, and the structural parameters (such as mass, damping, stiffness, etc.) to solve the dynamics equations through the numerical integration method, thereby calculating the six-degree-of-freedom displacement of the booster in the next time step. The calculated displacement data is then output to the real-time exchange database. After completing the calculation of the time step, Simpack suspends the calculation and enters a waiting state until it receives the start signal to start the calculation of the next time step.

[0053] The kinetic equation is: ,in 、 、 are the mass, damping and stiffness of the booster system, is the displacement of the system, For speed, is the acceleration, The external force acting on the system.

[0054] A dynamic calculation method for a high-speed magnetic levitation electromagnetic propulsion system based on aerodynamic-dynamic coupling simulation was established, which realized the real-time coupling calculation of aerodynamic loads and structural dynamic responses, and significantly improved the accuracy and reliability of the dynamic simulation of the high-speed magnetic levitation electromagnetic propulsion system.

[0055] Step S6: When all time steps are completed, a dynamic response curve of the entire operation process is generated.

[0056] Finally, through the post-processing function of the dynamics software, the displacement and other dynamic response parameters of each component are organized into a complete dynamic response curve, providing comprehensive data support for analyzing the dynamic performance of the booster.

[0057] In one possible implementation, in order to ensure the accuracy and reliability of the coupled calculation, the present invention adopts a multi-software coupled calculation method and designs a step-by-step calculation start-stop control technology based on parameter identification: Because Simpack continuously updates files during calculations, only the results from the final step are retained. Therefore, Simpack's post-processing scripting function is executed at the end of each time step to output the six-degree-of-freedom displacements and other key dynamic response parameters of each component to the data storage module. After the calculation is completed, this data is compiled to form a complete dynamic response curve over time.

[0058] The entire calculation process is discretized into multiple smaller time steps, and the calculation order of "dynamics first, then aerodynamics" is adopted. For the dynamic calculation module, active and pending digital signal parameters are set. When the computer recognizes the activation parameter, the Simpack solver starts and performs dynamic response solution; after the solution is completed, the parameter state changes from active to pending, and the dynamic calculation stops and enters the pending state. The aerodynamic calculation module uses the Fluent custom function function to set the sleep time between each time step. After completing the aerodynamic load solution, the pneumatic module enters the stop state, at which time the dynamic module performs the dynamic load solution; when the aerodynamic calculation stop time reaches the sleep time, the pneumatic module restarts and enters the calculation of the next time step.

[0059] At each time step, the aerodynamic calculation reads the six-degree-of-freedom displacement output from the dynamics calculation from the database and uses the ratio of this displacement to the time step length as the velocity condition. After a certain number of internal iterations reach convergence, the six-degree-of-freedom aerodynamic loads on the booster are calculated and output to the database. Subsequently, a control law is set to pause the aerodynamic calculation and wait for the start signal to proceed to the next time step.

[0060] The steps after calculating the six-degree-of-freedom aerodynamic load vector also include: Write the aerodynamic load vector into a text file in the real-time exchange database and update the file content in overwrite mode.

[0061] After calculating the six-degree-of-freedom aerodynamic load vector, write the result to a text file in the real-time exchange database, and update the file content in an overwrite manner. This operation ensures that the latest aerodynamic load vector obtained each time can be read by Simpack and used for subsequent dynamic calculations. To read the aerodynamic load vector into the text file of the real-time exchange database, it is necessary to output the aerodynamic load vector to the text file through a Fluent custom function. Then overwrite and update the file content, which involves the way the file is written. It is necessary to ensure that the original file content is overwritten each time it is written, rather than appended. At the same time, the file format and content structure must also be considered to ensure that Simpack can read it correctly.

[0062] Figure 2 The coupled calculation flow chart proposed in the embodiment of the present application is shown. The coupled calculation is mainly achieved by real-time output and reading of the aerodynamic loads solved by the aerodynamic simulation subsystem and the dynamic response solved by the structural dynamics simulation subsystem. The entire process is as follows: In the aerodynamics simulation subsystem, the background mesh and component mesh are first divided, and overlapping interfaces and customized mesh motion are set. Next, the unsteady Navier-Stokes equations are solved, and internal iterations are performed to determine whether the convergence criteria are met. If not, iterations continue; if so, the aerodynamic loads are output to the database. In the structural dynamics simulation subsystem, the system dynamics model receives load inputs through the database, solves the multibody dynamics equations, and writes the output dynamic results to the database. The database acts as an intermediary, storing and transmitting aerodynamic loads and dynamic results, enabling data exchange between the two subsystems. Through this real-time output and reading method, the aerodynamics simulation subsystem and the structural dynamics simulation subsystem cooperate with each other to form a closed-loop coupled simulation process.

[0063] Figure 3 This figure shows the interaction between Fluent and Simpack software in a coupled calculation based on the start-stop control law, as proposed in an embodiment of the present application. Because the entire calculation process is discretized into multiple time steps, both software programs need to pause the calculation after each time step to exchange data.

[0064] Fluent solves the Navier-Stokes equations and outputs aerodynamic forces. After each calculation step, Fluent enters a sleep state, waiting for Simpack to complete the dynamics calculations. Fluent's start and stop are controlled by the configured sleep time. During this sleep period, Fluent pauses its calculations, allowing Simpack to read the aerodynamic force data output by Fluent and perform the dynamics calculations.

[0065] Simpack solves the dynamic equations and outputs the dynamic response. After each calculation step, Simpack pauses the calculation to wait for Fluent to update the aerodynamic data. Simpack's start and stop are controlled by parameter identification. Simpack starts or pauses the calculation when it detects a specific parameter change (for example, a start / stop control parameter changes from 0 to 1).

[0066] During the coupled calculation process, the two software programs are synchronized using a start / stop control parameter. After Fluent completes the aerodynamic calculation and outputs the results, it sets the start / stop control parameter from 0 to 1, triggering Simpack to begin the dynamic calculation. After Simpack completes the dynamic calculation and outputs the dynamic response, it sets the start / stop control parameter from 1 to 0, instructing Fluent to restart and proceed to the next aerodynamic calculation.

[0067] The interaction method based on the start-stop control law ensures that the calculations of the two software can be carried out in an orderly manner within each time step, and the necessary data interaction is carried out after the calculation is completed, thereby realizing efficient coupling between Fluent and Simpack.

[0068] Figure 4 A graph showing the change in aerodynamic drag over the entire booster's operation, derived from coupled calculations, shows time (in seconds) on the horizontal axis and aerodynamic drag (in Newtons) on the vertical axis. The graph shows that aerodynamic drag gradually increases from 0 to 4 seconds, with the overall trend showing a smooth curve.

[0069] Figure 5 The figure shows the aerodynamic lift variation curve for the entire booster operation, obtained from coupled calculations, with the vertical upward direction being the positive direction. The horizontal axis represents time (in seconds), and the vertical axis represents aerodynamic lift (in Newtons). The figure shows that aerodynamic lift exhibits a gradual increase from time 0 to 4 seconds. The curve is relatively flat initially, but gradually increases over time, reaching a peak near 4 seconds.

[0070] Figure 6This graph shows the change in aerodynamic pitching moment over the entire booster's operation, calculated using coupled calculations. The positive direction is defined as the direction that causes the booster to tilt upward. The horizontal axis represents time (in seconds), and the vertical axis represents the aerodynamic pitching moment (in Newton-meters). The graph shows a gradual increase in the aerodynamic pitching moment from 0 to 4 seconds. The curve is relatively flat initially, but the rate of increase accelerates over time, reaching a particularly high value near 4 seconds.

[0071] Figure 7 A graph showing the booster's operating speed versus time, obtained from coupled calculations, is shown. The horizontal axis represents time (in seconds) and the vertical axis represents the booster's operating speed (in meters per second). The graph shows that the booster's speed exhibits a smooth and continuous upward trend from 0 to 4 seconds. Initially, the speed increases relatively slowly, then gradually accelerates, ultimately reaching a high operating speed near 4 seconds.

[0072] Figure 8 A graph showing the vertical displacement of the center of the levitation magnet over time during booster operation, obtained using coupled calculations, is shown. The horizontal axis represents time (in seconds) and the vertical axis represents vertical displacement (in meters). The graph shows that the vertical displacement of the levitation magnet exhibits significant fluctuations between 0 and 4 seconds. Initially, the displacement fluctuations are large, then gradually decrease and stabilize. This indicates that during the initial stages of booster operation, the levitation magnet experiences significant vertical disturbances. However, over time, the system gradually reaches equilibrium, and the fluctuations in vertical displacement decrease.

[0073] In summary, this application incorporates the changing characteristics of aerodynamic loads into dynamic calculations, which can solve the aerodynamic loads and dynamic responses of the entire booster movement process in real time, and can analyze the complex dynamic responses of the booster to determine the suspension stability and operational safety.

[0074] Compared with the prior art, the embodiments of the present application have the following beneficial effects: First, the accuracy of aerodynamic load input in electromagnetic propulsion system dynamics simulations has been effectively improved. By overcoming the limitations of aerodynamic load data in aerodynamic interpolation calculations and calculating the constantly changing aerodynamic loads during operation in real time, the consideration of aerodynamic loads during the operation of a magnetically levitated electromagnetic propulsion booster is more realistic.

[0075] Second, a real-time coupled aerodynamic and dynamic calculation method was established, incorporating fluid-structure coupling into the dynamics calculations of magnetic levitation electromagnetic propulsion. This innovative approach overcomes the limitations of traditional interpolation calculations and can more accurately simulate the actual operation of electromagnetic propulsion boosters.

[0076] A possible implementation of a magnetic levitation propulsion dynamics calculation device is provided below. The device is used to execute the various execution steps and corresponding technical effects of the magnetic levitation propulsion dynamics calculation method shown in the above embodiments and possible implementations. The device includes: A construction module is used to establish a dynamic model of an electromagnetic propulsion booster and an aerodynamic model of an electromagnetic propulsion booster respectively; The data exchange module is used to establish a real-time exchange database based on Fluent UDF, enabling data exchange between the electromagnetic propulsion booster dynamic model and the electromagnetic propulsion booster aerodynamic model; A calculation module, used to perform dynamic calculations using an electromagnetic propulsion booster dynamics model to obtain displacement data of the booster; A conversion module for converting displacement data into aerodynamic loads on the booster using an electromagnetic propulsion booster aerodynamic model; A solver module is used to use the electromagnetic propulsion booster dynamics model to solve the dynamic equations based on the booster's aerodynamic loads and preset electromagnetic forces, shoe rail forces, and structural parameters to obtain the displacement of the next time step; The generation module is used to generate the dynamic response curve of the entire operation process when all time steps are completed.

[0077] This preferred embodiment provides a computer device that can implement the steps in any embodiment of the magnetic levitation propulsion dynamics calculation method provided in the embodiments of the present application. Therefore, the beneficial effects of the magnetic levitation propulsion dynamics calculation method provided in the embodiments of the present application can be achieved. Please refer to the previous embodiments for details and will not be repeated here.

[0078] Those skilled in the art will appreciate that all or part of the steps in the various methods of the above embodiments can be accomplished through instructions, or by controlling related hardware through instructions. The instructions can be stored in a computer-readable storage medium and loaded and executed by a processor. To this end, an embodiment of the present application provides a storage medium storing a plurality of instructions that can be loaded by a processor to execute the steps of any of the embodiments of the magnetic levitation propulsion dynamics calculation method provided in the embodiments of the present application.

[0079] The storage medium may include a read-only memory (ROM), a random access memory (RAM), a magnetic disk or an optical disk, etc.

[0080] Since the instructions stored in the storage medium can execute the steps in any embodiment of the magnetic levitation propulsion dynamics calculation method provided in the embodiments of the present application, the beneficial effects that can be achieved by any magnetic levitation propulsion dynamics calculation method provided in the embodiments of the present application can be achieved. Please refer to the previous embodiments for details and will not be repeated here.

[0081] The above description is only a preferred embodiment of the present application and is not intended to limit the present application. Any modifications, equivalent replacements and improvements made within the spirit and principles of the present application should be included in the scope of protection of the present application.

Claims

1. A method for calculating magnetic levitation propulsion dynamics, characterized in that: The method comprises: Establish the dynamic model of electromagnetic propulsion booster and the aerodynamic model of electromagnetic propulsion booster respectively; A real-time exchange database is established based on Fluent UDF, enabling data exchange between the electromagnetic propulsion booster dynamics model and the electromagnetic propulsion booster aerodynamics model; The electromagnetic propulsion booster dynamics model is used to perform dynamics calculations to obtain the booster displacement data; The electromagnetic propulsion booster aerodynamic model is used to convert the displacement data into aerodynamic loads on the booster; The electromagnetic propulsion booster dynamics model is used to solve the dynamic equations based on the booster's aerodynamic load, preset electromagnetic force, shoe rail force, and structural parameters to obtain the displacement of the next time step; When all time steps are completed, a dynamic response curve for the entire run is generated.

2. The magnetic levitation propulsion dynamics calculation method according to claim 1, characterized in that: The dynamic model of the electromagnetic propulsion booster is established using the multi-body dynamics software Simpack. The steps for establishing the dynamic model of the electromagnetic propulsion booster include: Based on the mass, center of gravity coordinates and moment of inertia around the main axis of the booster, reference points for all electromagnetic loads, aerodynamic loads and shoe rail loads are established in the booster space, and the spatial three-dimensional coordinate parameters of all reference points are given; Force elements are created at each reference point. The force elements include aerodynamic force, electromagnetic force, and shoe rail force. The electromagnetic force is applied through an interpolation table, and the aerodynamic load reads the aerodynamic calculation result file through the substitution variable function.

3. The magnetic levitation propulsion dynamics calculation method according to claim 1, characterized in that: The steps to establish the aerodynamic model of the electromagnetic propulsion booster include: Import the booster's 3D geometry model through the fluid simulation software Fluent; Use grid pre-processing software to build the external flow field calculation grid for the three-dimensional geometric model; A three-dimensional unsteady calculation method is used, and the turbulence model is set as the SST k-ω model; The computational domain boundary is set as the pressure outlet boundary, the track surface is set as the no-slip wall, and the booster surface is set as the moving wall. The initial condition is set as the initial velocity of the booster equal to zero, and the motion of the booster in the flow field is simulated using the overlapping grid and moving grid coupling strategy.

4. The magnetic levitation propulsion dynamics calculation method according to claim 3, characterized in that: The six-degree-of-freedom motion speed of the moving wall is determined by a user-defined function that reads the displacement data output by the dynamic calculation in real time.

5. The magnetic levitation propulsion dynamics calculation method according to claim 1, characterized in that: The steps for converting displacement data into aerodynamic loads on the booster using the electromagnetic propulsion booster aerodynamic model include: In each time step, the displacement data is read from the real-time exchange database. The displacement data contains the three-dimensional position coordinates of each reference point on the booster surface in the current time step and the previous time step. Calculate the displacement difference of each reference point and calculate the moving speed of the booster surface; The booster surface moving speed is set as the booster wall boundary condition through the DEFINE_CG_MOTION module of Fluent UDF; Perform iterative calculation of the three-dimensional unsteady flow field, use the f_loop(f_all,thread) function to traverse the surface grid cells, and combine the F_CENTROID(x,f_all,thread) function to extract the pressure center coordinates; Based on the pressure distribution and the pressure center coordinates, the six-degree-of-freedom aerodynamic load vector is calculated by integration.

6. The magnetic levitation propulsion dynamics calculation method according to claim 5, characterized in that: The steps after calculating the six-degree-of-freedom aerodynamic load vector also include: Write the aerodynamic load vector into a text file in the real-time exchange database and update the file content in overwrite mode.

7. The magnetic levitation propulsion dynamics calculation method according to claim 1, characterized in that: The kinetic equation is: ,in 、 、 are the mass, damping and stiffness of the booster system, is the displacement of the system, For speed, is the acceleration, The external force acting on the system.

8. A magnetic levitation propulsion dynamics calculation device, characterized in that: The device comprises: A construction module is used to establish a dynamic model of an electromagnetic propulsion booster and an aerodynamic model of an electromagnetic propulsion booster respectively; The data exchange module is used to establish a real-time exchange database based on Fluent UDF, enabling data exchange between the electromagnetic propulsion booster dynamic model and the electromagnetic propulsion booster aerodynamic model; A calculation module, used to perform dynamic calculations using an electromagnetic propulsion booster dynamics model to obtain displacement data of the booster; A conversion module for converting displacement data into aerodynamic loads on the booster using an electromagnetic propulsion booster aerodynamic model; A solver module is used to use the electromagnetic propulsion booster dynamics model to solve the dynamic equations based on the booster's aerodynamic loads and preset electromagnetic forces, shoe rail forces, and structural parameters to obtain the displacement of the next time step; The generation module is used to generate the dynamic response curve of the entire operation process when all time steps are completed.

9. A computer device, characterized in that: The computer device includes a processor and a memory, wherein a computer program is stored in the memory, and the computer program is loaded and executed by the processor to implement the magnetic levitation propulsion dynamics calculation method according to any one of claims 1 to 7.

10. A computer-readable storage medium, characterized in that The storage medium stores a computer program, which is loaded and executed by a processor to implement the magnetic levitation propulsion dynamics calculation method according to any one of claims 1 to 7.

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