A dynamic simulation method for hydrogen-oxygen mixture under thermal and electromagnetic composite field

Abstract

This invention belongs to the field of aerospace engine technology and relates to a method for simulating the dynamics of a hydrogen-oxygen mixture in a thermal-electromagnetic composite field. The method comprises the following steps: 1) reading data and meshing the simulation area; 2) using unsteady detonation combustion simulation to obtain particle state distribution parameters and aerodynamic thrust; 3) using the particle state distribution parameters as initial input conditions, using particle mesh units and the Monte Carlo collision method to simulate the thermodynamic distribution parameters and electromagnetic thrust; and 4) summing the aerodynamic thrust and electromagnetic thrust to obtain the engine thrust. This invention utilizes a weak coupling simulation method to simulate the dynamics of a hydrogen-oxygen mixture in a thermal-electromagnetic composite field, providing a reference for numerical simulation of particle dynamics in complex field environments.

Description

Technical Field

[0001] The invention belongs to the technical field of aerospace engines, and in particular relates to a dynamic simulation method of a hydrogen-oxygen mixture under a thermal-electromagnetic composite field. Background Art

[0002] With the successive launch of new space exploration missions, the performance requirements for aerospace engines are becoming increasingly demanding. As we all know, current aerospace engines can be divided into two types: chemical propulsion and electric propulsion. Chemical propulsion primarily relies on converting the heat released by the chemical reaction of the working fluid into its backward kinetic energy, which in turn generates thrust. This is characterized by high thrust but low specific impulse. Electric propulsion, on the other hand, relies on converting the working fluid's kinetic energy into electrical energy. Compared to chemical propulsion, electric propulsion offers significantly higher specific impulse but lower thrust.

[0003] In practical applications, aerospace engines need to take into account both the thrust and specific impulse performance of the engine in order to support the smooth implementation of certain special space missions. As a result, some new engine technology concepts involving the combined effects of multiple physical fields have emerged to obtain higher thrust and specific impulse.

[0004] Currently, in the development of aerospace engines, in order to better reflect the impact of the combined effects of physical fields on engine performance, in addition to hardware development and experimental verification, the use of numerical simulation methods to explore engine operating mechanisms and assist in the development of new technologies has become a hot topic of research. Simulation research on pure chemical propulsion or electric propulsion has been very in-depth, but dynamic simulation research on new engine technologies that involve multiple physical fields is very lacking, and the corresponding simulation methods are also very immature, making simulation difficult to implement. Summary of the Invention

[0005] The purpose of the present invention is to provide a method for simulating the dynamics of hydrogen-oxygen mixed gases under a thermal-electromagnetic composite field. The weak coupling simulation method is used to realize the dynamics simulation of hydrogen-oxygen mixed gases under a thermal-electromagnetic composite field, providing a reference for the numerical simulation of particle dynamics in complex field environments.

[0006] In order to achieve the above object, the technical solution adopted by the present invention is:

[0007] A method for simulating the dynamics of a hydrogen-oxygen mixture under a thermal-electromagnetic composite field comprises the following steps:

[0008] 1) Read grid data, boundary data, initial field data, thermodynamic reaction data, pressure data, temperature data, particle density data, velocity data, and component distribution data; and mesh the simulation area;

[0009] 2) using all the data read in step 1) as input, performing an unsteady simulation of the hydrogen-oxygen detonation combustion reaction in the engine to obtain particle state distribution parameters and aerodynamic thrust;

[0010] 3) Using the particle state distribution parameters from step 2) as initial input conditions, using particle grid units and the Monte Carlo collision method, simulate the plasma flow pattern inside the engine to obtain thermodynamic distribution parameters and electromagnetic thrust;

[0011] 4) The aerodynamic thrust of step 2) and the electromagnetic thrust of step 3) are summed to obtain the thrust of the engine.

[0012] Furthermore, the specific process of step 2) is:

[0013] 2.1) Initialize all the data read in step 1) and assign initial values to each grid in the simulation area;

[0014] 2.2) Solve the compressible equations for the hydrogen-oxygen chemical reaction kinetics during hydrogen-oxygen detonation combustion to obtain density distribution parameters, particle velocity distribution parameters, pressure distribution parameters, total energy distribution parameters, component distribution parameters, and temperature distribution parameters;

[0015] 2.3) The aerodynamic thrust F is obtained based on the density distribution parameters, particle velocity distribution parameters, pressure distribution parameters, total energy distribution parameters, component distribution parameters, and temperature distribution parameters obtained above.

[0016] Furthermore, the step 2.2) includes the following steps:

[0017] 2.2.1) Set the computation time and use the operator splitting method to solve the coupled compressible equations within one time step;

[0018] 2.2.2) Update all data read in step 1) and process them according to step 2.1), then proceed to the next time step and continue solving according to step 2.2.1) until the set calculation time is completed, and output the final density parameters, velocity parameters, pressure parameters, temperature parameters, and component distribution parameters.

[0019] Furthermore, in step 2.2.1), the compressible equations include a continuity equation, a momentum equation, a total energy equation, and a component equation;

[0020] The continuity equation is

[0021] The momentum equation is

[0022] The total energy equation is

[0023] The component equation is

[0024] Where: ρ represents the particle density; t represents time; u i Indicates along Velocity component in the direction; u j Indicates along Velocity component in the direction; x j Indicates along The displacement component in the x direction; i Indicates along The displacement component in the direction; τ ij represents viscous stress; E represents total energy; p represents pressure; q j represents heat flow; V k,j represents the diffusion rate; represents the net generation rate of component mass; Y k represents the mass fraction of the kth component.

[0025] Furthermore, the method for solving the compressible equations in step 2.2.1) is: using the finite volume method to integrate and discretize the continuity equation, momentum equation and total energy equation on the grid respectively, and then solve them; using the fractional step method to decompose the component equations into ordinary differential equations and partial differential equations with passive terms, and then solve them.

[0026] Furthermore, in step 2.3), the calculation formula of the aerodynamic thrust F is:

[0027]

[0028] Among them: P3 represents the detonation combustion pressure; P1 represents the initial pressure of the combustion chamber; U represents the detonation wave velocity; V represents the volume of the combustion chamber; f represents the repetition frequency; K represents an empirical constant, which is generally taken as 5.

[0029] Furthermore, the specific process of step 3) is:

[0030] 3.1) Using the density parameters, velocity parameters, pressure parameters, temperature parameters, and component distribution parameters output in step 2.2.2) as initial input conditions, solve Maxwell's equations according to the model parameter settings to obtain the electromagnetic field distribution in the simulation area;

[0031] 3.2) Use Newton's equation of motion to solve the position and velocity of the macroparticle under the above electromagnetic field distribution:

[0032] 3.3) Use the Monte Carlo method to process the inter-particle collisions and obtain the particle dynamics distribution parameters after a calculation time step. Then enter the iterative loop until the calculation reaches stability, and use the particle dynamics distribution parameters calculated last time as the output;

[0033] 3.4) Based on the output particle dynamics distribution parameters, the number density distribution, electric field distribution parameters, and electromagnetic distribution parameters are calculated respectively, and the electromagnetic thrust T is obtained by solving.

[0034] Furthermore, in step 3.1), Maxwell's equations are:

[0035]

[0036] in: represents the vector partial derivative operator; H represents the magnetic field intensity vector; J represents the current density vector; D represents the electric displacement vector; E1 represents the electric field intensity vector; B represents the magnetic induction intensity vector.

[0037] Furthermore, in step 3.2), the Newtonian equation of motion is:

[0038]

[0039] Where: v represents the velocity of the particle; m represents the mass of the particle; e represents the charge of the electron; and x represents the displacement vector.

[0040] Furthermore, in step 3.4), the calculation formula of the electromagnetic thrust T is:

[0041]

[0042] Among them: B θ represents the magnetic induction intensity component; j r represents the radial current density component; j z represents the axial current density component.

[0043] Beneficial effects of the present invention:

[0044] 1. The present invention adopts a weak coupling method of unsteady simulation of detonation combustion and full-particle simulation of plasma. First, the finite volume method is used to discretely solve the compressible equations to realize the unsteady simulation of hydrogen-oxygen detonation combustion. Then, the solved parameter distribution results such as combustion chamber pressure, temperature, particle composition, etc. are used as the initial conditions of the full-particle simulation of plasma. The PIC / MCC method is applied to simulate the dynamics of hydrogen-oxygen mixed gas under the action of electromagnetic field, which can realize the simulation study of the dynamics of hydrogen-oxygen mixed gas under the thermal electromagnetic composite field.

[0045] 2. The dynamic weak coupling simulation method of hydrogen-oxygen mixture under the thermal electromagnetic composite field provided by the present invention comprehensively considers the influence of the thermal electromagnetic composite field on particle dynamics, simplifies the complex within a reasonable range, and is easy to implement simulation, providing a reference for the dynamic simulation research of new engines with the combined action of multiple physical fields. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] Figure 1 A schematic diagram of the simulation method provided by the present invention;

[0047] Figure 2 Schematic diagram of the unsteady simulation process of detonation combustion in the present invention;

[0048] Figure 3 Schematic diagram of the plasma full particle simulation process in the present invention;

[0049] Figure 4 A schematic diagram of a computer simulation model established for an embodiment of the present invention;

[0050] Figure 5 is the pressure distribution parameter result obtained by the present invention;

[0051] Figure 6 The gas density distribution parameter results obtained by the present invention;

[0052] Figure 7 The electron spatial distribution results are obtained for the present invention. DETAILED DESCRIPTION

[0053] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0054] Example

[0055] See also Figure 1 The dynamic simulation method for hydrogen-oxygen mixtures under a thermo-electromagnetic composite field provided in this embodiment adopts a weakly coupled simulation scheme that combines detonation combustion simulation with plasma simulation. Primarily, the compressible equations are discretely solved using the finite volume method to implement unsteady numerical detonation simulation, obtaining the distribution parameters of the particle state and the aerodynamic thrust. The solved combustion component distribution, density distribution, and velocity distribution are then used as initial conditions for the plasma evolution in the electromagnetic force solution. The particle grid element (PIC) and Monte Carlo collision (MCC) method are applied to calculate the plasma flow evolution law generated by the detonation combustion inside the thruster, obtaining thermodynamic parameters and electromagnetic thrust. The aerodynamic thrust and electromagnetic thrust are summed to obtain the combined thrust of the thruster.

[0056] The method for simulating the dynamics of a hydrogen-oxygen mixture under a thermal-electromagnetic composite field provided in this embodiment includes the following steps:

[0057] 1) Read grid data, boundary data, initial field data, thermodynamic reaction data, pressure data, temperature data, particle density data, velocity data, and component distribution data; and mesh the simulation area;

[0058] 2) using all the data read in step 1) as input, performing an unsteady simulation of the hydrogen-oxygen detonation combustion reaction in the engine to obtain particle state distribution parameters and aerodynamic thrust;

[0059] 3) Using the particle state distribution parameters from step 2) as initial input conditions, using particle grid units and the Monte Carlo collision method, simulate the plasma flow pattern inside the engine to obtain thermodynamic distribution parameters and electromagnetic thrust;

[0060] 4) The aerodynamic thrust of step 2) and the electromagnetic thrust of step 3) are summed to obtain the thrust of the engine.

[0061] In this embodiment, the boundary data includes relevant data such as wall type and outlet type, and the thermodynamic reaction data includes thermodynamic data, transport data, reaction data, density, velocity, pressure, temperature, component distribution, etc.; for example, thermodynamic reaction data such as specific heat, enthalpy, viscosity coefficient, thermal conductivity, and chemical reaction rate.

[0062] See also Figure 2 The unsteady simulation of detonation combustion provided in this embodiment considers the hydrogen-oxygen detonation combustion reaction in the thruster and performs an unsteady numerical detonation simulation on the hydrogen-oxygen detonation combustion reaction. The specific process is as follows.

[0063] 2.1) Initialize all the read data, assign initial values to each grid in the entire field, and then divide the grid.

[0064] In this embodiment, the specific division of the grid needs to take into account both effective control of the computational complexity and accurate capture of the propagation process of the detonation wave.

[0065] 2.2) Detonation combustion has a strong compressibility effect, so it is necessary to solve the compressibility equations when simulating it.

[0066] Continuity equation:

[0067] Momentum equation:

[0068] Energy equation:

[0069] Component equation:

[0070] Where: ρ represents the particle density; t represents time; u i Indicates along Velocity component in the direction; u j Indicates along Velocity component in the direction; x j Indicates along The displacement component in the x direction; i Indicates along The displacement component in the direction; τ ij represents viscous stress; E represents total energy; p represents pressure; q j represents heat flow; V k,j represents the diffusion rate; represents the net generation rate of component mass; Y k represents the mass fraction of the kth component.

[0071] When solving, since the continuity equation (Equation 1), momentum equation (Equation 2), and total energy equation (Equation 3) do not contain source terms, these equations can be integrated on the grid (semi-discrete). Specifically, the finite volume method is used to discretize the three control equations of the continuity equation, momentum equation, and total energy equation to obtain the format shown in Equation 5, and then the solution is obtained.

[0072]

[0073] Where ΔV is the grid volume, and U is the conserved quantity, i.e., ρ, ρu i And ρE, the symbol “-” means taking the volume average value within the grid, is the numerical flux of U on the grid boundary.

[0074] However, when solving the equation (Equation 4), since the component equation (Equation 4) contains chemical reaction source terms, it will lead to rigidity problems. Therefore, when solving the equation (Equation 4), it is necessary to integrate the component equation (Equation 4) on the grid to obtain:

[0075]

[0076] Where, and They are respectively the conserved quantities ρY k as well as The volume average within the grid, Represents ρY k Numerical flux at the mesh boundaries.

[0077] Assumptions:

[0078]

[0079] The fractional step method can be used to decompose Equation 6 into an ordinary differential equation (ODE) of the active term and a partial differential equation (PDE) of the passive term, as shown in Equation 8 and Equation 9, respectively, and then solve them.

[0080]

[0081]

[0082] Specifically, time advancement is performed during the calculation process (as shown in the dashed box). First, the time value is set, and the operator splitting method is used to couple and solve the compressible equations within one time step.

[0083] Specifically, the PDE equation (i.e., partial derivative equation or partial differential equation) is first coupled and solved to obtain distribution parameters such as density, velocity component, pressure, and total energy; then the chemical reaction ODE equation (ordinary differential equation) is solved.

[0084] Then update the read data and initialize it, enter the next time step, and solve the compressible equations in a coupled manner according to the above method; until the set calculation time is over, output the final density distribution parameters, particle velocity distribution parameters, pressure distribution parameters, total energy distribution parameters, component distribution parameters and temperature distribution parameters.

[0085] 2.3) Based on the calculated output density distribution parameters, particle velocity distribution parameters, pressure distribution parameters, total energy distribution parameters, component distribution parameters and temperature distribution parameters, the aerodynamic thrust F is calculated using the following formula (10): thereby completing the time-dependent detonation numerical simulation process.

[0086] The calculation formula of aerodynamic thrust F is shown in formula (10):

[0087]

[0088] Among them: P3 represents the detonation combustion pressure; P1 represents the initial pressure of the combustion chamber; U represents the detonation wave velocity; V represents the volume of the combustion chamber; f represents the repetition frequency; K represents an empirical constant, which is generally taken as 5.

[0089] See also Figure 3 This embodiment simulates the plasma flow generated by detonation combustion, adopts particle grid unit PIC and Monte Carlo collision MCC method, and uses macro particles to replace real charged particles for calculation. The detailed implementation process is described as follows.

[0090] 3.1) The density parameters, velocity parameters, pressure parameters, temperature parameters, and component distribution parameters of the hydrogen-oxygen detonation combustion process obtained from the detonation combustion simulation are used as initial input conditions. Then, according to the engine operating conditions, the Maxwell equations (Equation 11) are solved to obtain the distribution of the electromagnetic field in the computational domain.

[0091]

[0092] Among them: Among them: represents the vector partial derivative operator; H represents the magnetic field intensity vector; J represents the current density vector; D represents the electric displacement vector; E1 represents the electric field intensity vector; B represents the magnetic induction intensity vector.

[0093] 3.2) Use Newton’s equation of motion (Eq. 12) to solve the position and velocity of the macroparticle.

[0094]

[0095] Where: v represents the velocity of the particle; m represents the mass of the particle; e represents the charge of the electron; and x represents the displacement vector.

[0096] 3.3) The Monte Carlo method is used to process the inter-particle collisions and obtain the particle dynamics distribution parameters after a calculation time step. Then an iterative loop is entered until the calculation reaches stability, and the particle dynamics distribution parameters of the last calculation are used as output.

[0097] 3.4) Based on the output particle dynamics distribution parameters, the number density distribution, electric field distribution parameters, and electromagnetic distribution parameters are calculated respectively, and the electromagnetic thrust T is obtained by solving.

[0098] The electric field distribution parameters and electromagnetic distribution parameters are mainly: radial current density component j r ; Axial current density component j z ; Magnetic induction intensity component B θ ), V represents the volume of the combustion chamber; according to the integral solution of (Equation 13), the electromagnetic thrust T is obtained:

[0099]

[0100] The thrust of the thermo-electromagnetic composite engine is obtained by adding the obtained electromagnetic thrust T to the aerodynamic thrust F obtained by the detonation combustion simulation.

[0101] Taking a certain engine as an example, the weak coupling method provided by the present invention is used for simulation.

[0102] The engine is cylindrical in shape, with a closed front end and the cathode at the center, coaxially mounted with the anode cylinder. The simulation model established is as follows Figure 4 shown.

[0103] See also Figure 4, the red area represents the hydrogen-oxygen mixed gas injection area, the orange area represents the cathode area of the ceramic sleeve, the lower blue area is the cathode, and the upper blue area is the anode. The numerical simulation uses a two-dimensional axisymmetric model of 2D-3V. The length of the anode and cathode is 450mm, and the radius of the anode and cathode is 18mm and 3mm respectively. The initial voltage between the cathode and cathode is 50kV, and the current is 8-20kA. In one calculation cycle, the amount of H2 and O2 used is 0.011g and 0.089g respectively. The initial temperature of the combustion chamber is set to 300K. In order to ensure that the boundary of the constructed physical model is closer to the actual working state and to facilitate the observation of the particle physics process outside the electrode, the length of the particle simulation area is extended by 50mm in the axial direction.

[0104] First, read the data and divide it into grids.

[0105] Secondly, the read data is initialized and the initial value is assigned to each grid in the simulation area; then the detonation combustion simulation is performed, and the compressible equations are solved to obtain the density distribution parameters, particle velocity distribution parameters, pressure distribution parameters, total energy distribution parameters, component distribution parameters and temperature distribution parameters. The pressure distribution parameters are shown in Figure 5 , gas density distribution parameters refer to Figure 6 .

[0106] According to the detonation combustion simulation results, the detonation combustion pressure is 0.433 MPa, the initial pressure of the thruster is 0.062 MPa, the detonation wave speed is 2680 m / s, and the thruster volume is 3.05×10 -4 m 3 , the detonation frequency is 50 Hz, and the aerodynamic thrust is calculated to be approximately 11 N.

[0107] Finally, the parameter results of the combustion simulation are used as the initial conditions for the plasma particle calculation, and the plasma full particle simulation (all particles include electrons and various ions) is performed to obtain the number density distribution of electrons and various ions, and the electric and magnetic field distribution parameters. Figure 7 shown.

[0108] According to the current and magnetic field distribution results obtained by simulation, the electromagnetic force calculation formula is used to estimate that the electromagnetic thrust obtained under currents of 8 to 20 kA ranges from 11 to 68 N.

[0109] Combining the detonation combustion output and electromagnetic particle simulation output results, it can be concluded that under the simulation conditions set in the scheme, the engine with this structure can achieve a thrust in the range of 22 to 79N.

[0110] In summary, the weak coupling simulation method provided by the present invention is used to realize the dynamic simulation of hydrogen-oxygen mixed gas under the thermal electromagnetic composite field, providing a reference for the numerical simulation of particle dynamics in complex field environments.

Claims

1. A method for simulating the dynamics of hydrogen-oxygen mixtures under a thermal-electromagnetic composite field, characterized in that: The following steps are involved: 1) Read grid data, boundary data, initial field data, thermodynamic reaction data, pressure data, temperature data, particle density data, velocity data, and component distribution data; and mesh the simulation area; 2) using all the data read in step 1) as input, performing an unsteady simulation of the hydrogen-oxygen detonation combustion reaction in the engine to obtain particle state distribution parameters and aerodynamic thrust; 3) Using the particle state distribution parameters from step 2) as initial input conditions, using particle grid units and the Monte Carlo collision method, simulate the plasma flow pattern inside the engine to obtain thermodynamic distribution parameters and electromagnetic thrust; 4) The aerodynamic thrust of step 2) and the electromagnetic thrust of step 3) are summed to obtain the thrust of the engine.

2. The method for dynamic simulation of hydrogen-oxygen mixture under the thermal electromagnetic composite field according to claim 1, characterized in that: The specific process of step 2) is: 2.1) Initialize all the data read in step 1) and assign initial values to each grid in the simulation area; 2.2) Solve the compressible equations for the hydrogen-oxygen chemical reaction kinetics during hydrogen-oxygen detonation combustion to obtain density distribution parameters, particle velocity distribution parameters, pressure distribution parameters, total energy distribution parameters, component distribution parameters, and temperature distribution parameters; 2.3) The aerodynamic thrust F is obtained based on the density distribution parameters, particle velocity distribution parameters, pressure distribution parameters, total energy distribution parameters, component distribution parameters, and temperature distribution parameters obtained above.

3. The method for dynamic simulation of hydrogen-oxygen mixture under the thermal electromagnetic composite field according to claim 2, characterized in that: The step 2.2) comprises the following steps: 2.2.1) Set the computation time and use the operator splitting method to solve the coupled compressible equations within one time step; 2.2.2) Update all data read in step 1) and process them according to step 2.1), then proceed to the next time step and continue solving according to step 2.2.1) until the set calculation time is completed, and output the final density parameters, velocity parameters, pressure parameters, temperature parameters, and component distribution parameters.

4. The method for dynamic simulation of hydrogen-oxygen mixture under the thermal electromagnetic composite field according to claim 3, characterized in that: In step 2.2.1), the compressible equations include a continuity equation, a momentum equation, a total energy equation, and a component equation; The continuity equation is The momentum equation is The total energy equation is The component equation is Where: ρ represents the particle density; t represents time; u i Indicates along Velocity component in the direction; u j Indicates along Velocity component in the direction; x j Indicates along The displacement component in the x direction; i Indicates along The displacement component in the direction; τ ij represents viscous stress; E represents total energy; p represents pressure; q j represents heat flow; V k,j represents the diffusion rate; Y represents the net generation rate of component mass; k represents the mass fraction of the kth component.

5. The method for dynamic simulation of hydrogen-oxygen mixture under the thermal electromagnetic composite field according to claim 4, characterized in that: The method for solving the compressible equations in step 2.2.1) is: using the finite volume method to integrate and discretize the continuity equation, momentum equation and total energy equation on the grid respectively, and then solve them; using the fractional step method to decompose the component equations into ordinary differential equations and partial differential equations with passive terms, and then solve them.

6. The method for dynamic simulation of hydrogen-oxygen mixture under the thermal electromagnetic composite field according to claim 5, characterized in that: In step 2.3), the calculation formula of the aerodynamic thrust F is: Among them: P3 represents the detonation combustion pressure; P1 represents the initial pressure of the combustion chamber; U represents the detonation wave velocity; V represents the volume of the combustion chamber; f represents the repetition frequency; K represents an empirical constant, which is generally taken as 5.

7. The method for dynamic simulation of hydrogen-oxygen mixture under a thermo-electromagnetic composite field according to any one of claims 3 to 6, characterized in that: The specific process of step 3) is: 3.1) Using the density parameters, velocity parameters, pressure parameters, temperature parameters, and component distribution parameters output in step 2.2.2) as initial input conditions, solve Maxwell's equations according to the model parameter settings to obtain the electromagnetic field distribution in the simulation area; 3.2) Use Newton's equation of motion to solve the position and velocity of the macroparticle: 3.3) Use the Monte Carlo method to process the inter-particle collisions and obtain the particle dynamics distribution parameters after a calculation time step. Then enter the iterative loop until the calculation reaches stability, and use the particle dynamics distribution parameters calculated last time as the output; 3.4) Based on the output particle dynamics distribution parameters, the number density distribution, electric field distribution parameters, and electromagnetic distribution parameters are calculated respectively, and the electromagnetic thrust T is obtained by solving.

8. The method for dynamic simulation of hydrogen-oxygen mixture under the thermal electromagnetic composite field according to claim 7, characterized in that: In step 3.1), Maxwell's equations are: in: represents the vector partial derivative operator; H represents the magnetic field intensity vector; J represents the current density vector; D represents the electric displacement vector; E1 represents the electric field intensity vector; B represents the magnetic induction intensity vector.

9. The method for dynamic simulation of hydrogen-oxygen mixture under the thermal-electromagnetic composite field according to claim 8, characterized in that: In step 3.2), the Newtonian equation of motion is: Where: v represents the velocity of the particle; m represents the mass of the particle; e represents the charge of the electron; and x represents the displacement vector.

10. The method for dynamic simulation of hydrogen-oxygen mixture under the thermal-electromagnetic composite field according to claim 9, characterized in that: In step 3.4), the calculation formula of the electromagnetic thrust T is: Among them: B θ represents the magnetic induction intensity component; j r represents the radial current density component; j z represents the axial current density component.

Images