Multi-physical field simulation method based on solid engine high-viscosity lining throwing and coating process
The high-viscosity liner coating process of solid rocket engines was optimized through multi-physics field simulation methods, which solved the spraying quality problem caused by inaccurate parameters, achieved a highly precise and controllable coating effect, and improved the structural stability of the engine.
Patent Information
- Application Number
- CN202510897179.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-07-01
- Publication Date
- 2025-10-17
AI Technical Summary
The existing technology lacks the means to accurately simulate and optimize the key parameters in the high-viscosity liner coating process of solid rocket engines, resulting in problems such as uneven spraying quality and residual bubbles, which affect the performance of the liner.
The multi-physics field simulation method is used to analyze the influence of parameters such as the coating port diameter, compressed air pressure, and coating head speed on the coating effect through simulation. Combined with the turbulence model and the Euler-Euler multiphase flow model, the process of slurry particles colliding with the shell is refined to optimize the coating process.
The accuracy and controllability of liner spraying are improved, the quality and efficiency of spraying are ensured, particle breakage and uneven liquid film thickness are prevented, and the stability of the engine structure is improved.
Smart Images
Figure CN120805622A_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The present application relates to the technical field of digital simulation, in particular to a multi-physical field simulation method based on a high-viscosity liner spraying process of a solid rocket engine. BACKGROUND
[0002] The liner of a solid rocket engine is a thin layer that plays a transitional role, which is coated between the heat insulation layer in the combustion chamber and the grain, and due to the high viscosity of the liner, the two can be closely adhered together, which can effectively prevent cracks or direct debonding between the grain and the heat insulation layer. The bonding performance of the liner is directly related to whether the engine can maintain an integrated structure, and also determines the stability of the grain combustion. The liner / grain interface with adhesion failure may cause the grain combustion not to proceed according to the designed combustion standard. It will also cause the shell to bear excessive heat, thereby causing the shell material to lose strength and eventually may lead to engine failure or even disintegration.
[0003] With the rapid development of rocket technology, rockets of different shapes need to be developed to meet actual needs, and the size of the engine shape also needs to be changed. In the process of spraying the liner of a thin-walled component, in order to improve the coating effect of the coating, the spraying direction and the atomization effect of the coating need to be adjusted. At present, the forming process of the liquid film in the coating process is complex, and the factors affecting the final coating quality include the incident port diameter, the atomized particle size and the spraying speed. In the process of spraying the liner, the diameter of the slurry particles, the spraying speed and the spacing between the spraying ports directly affect the final quality of the liner. The traditional spraying process often relies on experience to set parameters, which is easy to cause problems such as uneven particle breakage, uneven liquid film thickness and bubble residue of the slurry during the spraying process, thereby affecting the performance of the liner. The existing technology still lacks optimization means for precise simulation of these parameters, which makes it difficult to achieve the ideal effect of the sprayed liner.
[0004] Therefore, the multi-physical field simulation method for the high-viscosity liner spraying process of a solid rocket engine is proposed to improve the accuracy and controllability of the liner spraying process. It promotes the research and improvement of existing spraying technology. SUMMARY
[0005] (I) Technical problems to be solved
[0006] In view of the deficiencies of the prior art, the present application provides a multi-physical field simulation method based on a high-viscosity liner spraying process of a solid rocket engine, which simulates and analyzes the process of the collision of the slurry particles with the shell after the liner slurry is sprayed out and the formation of the liquid film after the collision of the slurry particles with the shell, thereby improving the accuracy and controllability of the liner spraying process.
[0007] (II) Technical solutions
[0008] To achieve the above object, the application provides the following technical scheme: a multi-physical field simulation method based on a high-viscosity lining throwing process of a solid engine, comprising the following steps: S1, establishing a parameterized solid rocket engine combustion chamber lining geometric model; S2, defining lining shell and lining slurry material parameters; S3, mesh division; S4, turbulent flow model setting; S5, simulation analysis of the influence of the throwing port diameter on the throwing effect; S6, simulation analysis of the influence of the compressed air pressure at the throwing outlet on the throwing effect; S7, simulation analysis of the influence of the throwing head rotation speed on the throwing effect; S8, simulation analysis of the influence of the throwing port diameter on the formed liquid film; S9, simulation analysis of the influence of the lining slurry atomization degree on the formed liquid film; S10, simulation analysis of the influence of the throwing speed on the formed liquid film; S11, simulation analysis of the particle collision shell condition under different throwing port diameters; S12, simulation of the particle collision shell condition under different throwing speeds; and S13, simulation analysis of the particle collision shell condition under different throwing port spacings.
[0009] Preferably, in S1, in order to meet the propulsion requirements of different purpose aircrafts, the parameter model is established to facilitate subsequent modification of the model size according to different requirements, a certain size of solid rocket engine combustion chamber is taken as the research object, the complex internal structure and minor detail features that have little influence on the simulation results are ignored, the linear segment area and the head segment area of the engine are respectively created, the linear segment area is a cylindrical cylinder structure, the head segment area is a complex curved surface inner cavity structure with an arc, and a formed lining shell structure numerical model is established.
[0010] Preferably, in S2, the material properties of the lining slurry are set as density 1800 kg / m 3 , viscosity 15 Pa·s, and the material parameter basis is provided for the simulation analysis.
[0011] Preferably, in S3, the patch conforming method is selected in the mesh division module to divide the mesh of the lining shell structure numerical model established in S1.
[0012] Preferably, in S4, when the lining slurry is thrown into the air and interacts with the airflow, it generally moves irregularly and unsteadily and is in a turbulent flow state, so the turbulent flow model is activated when the numerical simulation is performed, the standard k-ε model is selected for the turbulent flow model, the influence of molecular viscosity is ignored, and it is assumed that the flow is completely turbulent.
[0013] Preferably, in S5, S6 and S7, the lining slurry throwing direction needs to be changed for the lining throwing of the head segment, here, the method of meeting the high-speed compressed air after the coating is thrown to change the slurry movement track is adopted. Two-phase flow is simulated, the primary phase is air, and the secondary phase is the lining slurry. The control variable method is used for simulation analysis, other variables are kept unchanged, and the throwing port diameter, the compressed air pressure and the throwing head rotation speed are changed one by one.
[0014] Preferably, in S8, S9, S10, the movement of the liner material particles in the gas phase after the atomization is completed and the collision forming process of the particles after the particles meet the shell are simulated, the influence of different incident port diameters, atomized particle sizes and spraying speeds on the final liquid film forming is analyzed by the control variable method. The gas phase is regarded as a continuum, the gas phase is described in the Euler coordinate system, and the transport equation of the gas phase is solved. The atomized liner slurry particle group is regarded as a discrete body, the differential equation is obtained by integrating the force between the slurry particles, and then the discrete equation set is solved. The trajectory calculation of the slurry particles is carried out in the Lagrangian coordinate system, and the heat transfer and mass loss caused by the collision between the particles can be calculated. The calculation domain is constructed according to the shell size and the spraying area, and the calculation domain range can accommodate the whole process of particle movement.
[0015] Preferably, in S11, S12, S13, after the spraying liquid film forming is simulated macroscopically, further simulation analysis should be carried out on the problem of slurry particle collision to the shell. The simulation analysis of the slurry particle collision to the shell under different spraying port diameters, spraying speeds and spraying port interval distances is analyzed. The Euler-Euler multiphase flow model is selected to calculate the mixing behavior of the two fluids and the transient (Transient) setting is adopted. The control variable method is used for simulation analysis of the slurry particle collision to the shell process of Region diameter, spraying speed and the distance between Regions.
[0016] (Three) beneficial effects
[0017] The application provides a multi-physical field simulation method based on a high-viscosity liner spraying process of a solid rocket engine, and has the following beneficial effects:
[0018] 1. By simulating and analyzing the spraying port, the influence of the spraying port diameter, the compressed air port pressure and the spraying speed on the spraying quality is found, so that appropriate parameters are set to improve the spraying quality.
[0019] 2. By numerically simulating and analyzing the collision of the liner slurry with the shell after the liner slurry is sprayed out to form a liquid film, the influence of the diameter of the incident port, the diameter of the liner slurry particles and the incident speed on the spraying quality is found, so that appropriate parameters are set to improve the spraying stability.
[0020] 3. By simulating and analyzing the problem of slurry particle collision to the shell, the rule of the slurry particle collision to the shell under the spraying port diameter, the spraying speed and the spraying port interval distance is found, so that appropriate parameters are set to improve the spraying efficiency. BRIEF DESCRIPTION OF DRAWINGS
[0021] Figure 1 Workflow diagram of the application
[0022] Figure 2 Schematic diagram for partitioning straight section and head section of solid rocket engine shell
[0023] Figure 3 Pressure nephogram of particle collision shell under different throw coating port spacing DETAILED DESCRIPTION
[0024] In order to make the objects, characteristics and advantages of the present application more obvious and easy to understand, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor are within the protection scope of the present application.
[0025] The present application provides a technical solution: a multi-physical field simulation method based on a high-viscosity lining throw coating process of a solid engine, comprising the following steps: S1, establishing a parameterized solid rocket engine combustion chamber lining geometric model; S2, defining lining shell and lining slurry material parameters; S3, mesh division; S4, turbulent flow model setting; S5, simulation analysis of the influence of throw coating port diameter on throw coating effect; S6, simulation analysis of the influence of compressed air pressure at the throw coating outlet on throw coating effect; S7, simulation analysis of the influence of throw head rotation speed on throw coating effect; S8, simulation analysis of the influence of throw coating port diameter on formed liquid film; S9, simulation analysis of the influence of lining slurry atomization degree on formed liquid film; S10, simulation analysis of the influence of throw coating speed on formed liquid film; S11, simulation analysis of particle collision shell under different throw coating port diameters; S12, simulation of particle collision shell under different throw coating speeds; S13, simulation analysis of particle collision shell under different throw coating port spacings.
[0026] Further, in S1, in order to meet the propulsion requirements of different purpose aircrafts, the parameterized model is established to facilitate subsequent modification of model size according to different requirements, a certain size of solid rocket engine combustion chamber is taken as the research object, the complex internal structure and minor detail features which have little influence on the simulation results are ignored for modeling, the straight section area and the head section area of the engine are created respectively, the straight section area is a cylindrical body structure, the head section area is a complex curved surface inner cavity structure with an arc, and a formed lining shell structure numerical model is established.
[0027] Further, in S2, the material properties of the lining slurry are set as density 1800 kg / m 3 , viscosity 15 Pa·s, to provide material parameter basis for simulation analysis.
[0028] Further, in S3, the patch conforming method is selected in the mesh division module to divide the mesh of the lining shell structure numerical model established in S1.
[0029] Further, in S4, the liner slurry is thrown into the air and interacts with the airflow, generally making non-constant and irregular motion, and being in a turbulent flow state, so in the following numerical simulation, a turbulent flow model is activated, a standard k-ε model is selected, the influence of molecular viscosity is ignored, and it is assumed that the flow is fully turbulent.
[0030] Further, in S5, S6 and S7, the throwing direction of the liner slurry needs to be changed for the liner throwing of the head section, and here, the method that the slurry trajectory is changed after meeting high-speed compressed air is adopted. Two-phase flow is simulated, the main phase is air, and the secondary phase is the liner slurry. The simulation analysis is carried out by the control variable method, other variables are kept unchanged, and the throwing port diameter, compressed air pressure and throwing head rotating speed are changed one by one.
[0031] Further, in S8, S9 and S10, the movement of the liner material particles thrown after atomization in the gas phase and the collision and forming process of the particles after meeting the shell are simulated, the influence of different incident port diameters, atomized particle sizes and throwing speeds on the final liquid film forming is analyzed by the control variable method. The gas phase is regarded as a continuum, is described in the Euler coordinate system, and the transport equation of the gas phase is solved. The atomized liner slurry particle group is regarded as a discrete body, the integral of the force between the slurry particles is obtained to obtain the differential equation, and then the discrete equation set is solved. The trajectory calculation of the slurry particles is carried out in the Lagrangian coordinate system, and the heat transfer and mass loss caused by the collision between the particles can be calculated. The calculation domain is constructed according to the shell size and the spraying area, and it is ensured that the calculation domain range can accommodate the whole process of particle movement.
[0032] Further, in S11, S12 and S13, after the throwing liquid film forming is simulated macroscopically, further simulation analysis should be carried out on the problem of slurry particle collision to the shell. The simulation analysis of the slurry particle collision to the shell under different throwing port diameters, throwing speeds and throwing port interval distances is analyzed. The Euler-Euler multiphase flow model is selected, is used for calculating the mixing behavior of two fluids, and is set as transient (Transient). The simulation analysis of the slurry particle collision to the shell is carried out by the control variable method, the Region diameter, the throwing speed and the interval distance between Regions.
[0033] The work flow of the application is as follows: firstly, a parameterized solid rocket engine combustion chamber liner geometric model is established, the material properties of the liner slurry are set as density 1800kg / m 3The viscosity is 15 Pa s, the patch conforming method is selected in the mesh division module to divide the mesh of the established lining shell structure numerical model, and the turbulent flow model is set. Secondly, the simulation analysis of the influence of the diameter of the throwing coating port on the throwing coating effect, the simulation analysis of the influence of the air pressure at the throwing coating outlet on the throwing coating effect, and the simulation analysis of the influence of the throwing head speed on the throwing coating effect are carried out. Thirdly, the simulation analysis of the influence of the diameter of the throwing coating port on the formed liquid film, the simulation analysis of the influence of the lining slurry atomization degree on the formed liquid film, and the simulation analysis of the influence of the throwing coating speed on the formed liquid film are carried out. Finally, the simulation analysis of the particle collision shell under different throwing coating port diameters, the simulation of the particle collision shell under different throwing coating speeds, and the simulation analysis of the particle collision shell under different throwing coating port spacings are carried out.
[0034] It should be noted that the relational terms herein such as first and second and the like are used solely to distinguish one entity or action from another, without necessarily requiring or implying any such actual relationship or order between such entities or actions. Moreover, the terms "comprises", "comprising", or any other variations thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can include other elements not expressly listed or inherent to such process, method, article, or apparatus.
[0035] Although embodiments of the present application have been shown and described, it is to be understood that various modifications, substitutions, replacements and variations can be made to these embodiments without departing from the principles and spirit of the present application, and the scope of the present application is defined by the appended claims and their equivalents.
Claims
1. A multi-physics simulation method based on the high viscosity liner coating process of solid rocket motor, characterized in that The method includes the following steps: S1 establishing a parameterized solid rocket engine combustion chamber lining geometric model S2 defining the lining shell and lining slurry material parameters S3 meshing S4 turbulence model setting S5 simulation analysis of the influence of the coating port diameter on the coating effect. S6 simulation analysis of the influence of the compressed air pressure at the coating outlet on the coating effect. S7 simulation analysis of the influence of the coating head rotation speed on the coating effect. S8 simulation analysis of the influence of the coating port diameter on the formed liquid film. S9 simulation analysis of the influence of the atomization degree of the lining slurry on the formed liquid film. S10 simulation analysis of the influence of the coating speed on the formed liquid film. S11 simulation analysis of the particle collision with the shell under different coating port diameters. S12 simulation of the particle collision with the shell under different coating speeds. S13 simulation analysis of the particle collision with the shell under different coating port spacings.
2. The multi-physics field simulation method based on the high-viscosity liner coating process of a solid rocket motor according to claim 1, characterized in that: In S1, in order to meet the propulsion requirements of aircraft for different purposes, a parametric model is established to facilitate the subsequent modification of the model size according to different needs. The combustion chamber of a solid rocket engine of a certain model and size is taken as the research object, and its complex internal structure and minor detail features that have little effect on the simulation results are ignored for modeling. The straight section area and head section area of the engine are created separately. The straight section area is a cylindrical barrel structure, and the head section area is a special-shaped complex curved surface inner cavity structure with an arc, and a digital model of the formed liner shell structure is established.
3. The multi-physics field simulation method based on the high-viscosity liner coating process of a solid rocket motor according to claim 1, characterized in that: In S2, the material properties of the lining slurry Set to a density of 1800 kg / m 3 , viscosity 15Pa·s, providing material parameter basis for simulation analysis.
4. The multi-physics field simulation method based on the high-viscosity liner coating process of a solid rocket motor according to claim 1, characterized in that: In S3, the Patch Conformal Method was selected in the Meshing Module to mesh the liner shell structure model established in S1. Then, the Fluent settings were used to convert the mesh to a polyhedron and set boundary layer refinement to obtain a suitable mesh.
5. The multi-physics field simulation method based on the high-viscosity liner coating process of a solid rocket motor according to claim 1, characterized in that: In S4, when the lining slurry is thrown into the air and interacts with the airflow, it generally performs unsteady and irregular motion and is in a turbulent state. The turbulence model must be activated when performing numerical simulations in the following studies. The standard k-ε model is selected as the turbulence model, the influence of molecular viscosity is ignored, and the flow is assumed to be completely turbulent.
6. The multi-physics field simulation method based on the high-viscosity liner coating process of a solid rocket motor according to claim 1, characterized in that: In S5, S6, and S7, the lining coating of the head section requires changing the coating direction. This approach uses high-speed compressed air to alter the slurry's trajectory after the coating is ejected. A two-phase flow is simulated, with air as the primary phase and the lining slurry as the secondary phase. The simulation analysis uses the control variable method, keeping other variables constant while varying the coating orifice diameter, compressed air pressure, and coating head speed.
7. The multi-physics field simulation method based on the high-viscosity liner coating process of a solid rocket motor according to claim 1, characterized in that: In S8, S9, and S10, the movement of the lining material particles in the gas phase after atomization is completed and the collision formation process after the particles encounter the shell are simulated. The influence of different inlet diameters, atomized particle sizes, and coating speeds on the final liquid film formation is analyzed by the control variable method. The gas phase is described as a continuum in the Euler coordinate system, and the gas phase transport equation is solved. The atomized lining slurry particle group is regarded as a discrete body. By integrating the forces between the slurry particles, the differential equation is obtained, and these discrete equations are then solved. The trajectory calculation of these slurry particles is performed in the Laplace coordinate system, and the heat transfer and mass loss caused by the collision between the particles can be calculated. The calculation domain is constructed according to the shell size and the injection area to ensure that the calculation domain range can accommodate the entire process of particle movement.
8. The multi-physics field simulation method based on the high-viscosity liner coating process of a solid rocket motor according to claim 1, characterized in that: In S11, S12, and S13, after simulating the formation of the coating liquid film at a macro level, further simulation analysis should be conducted on the issue of slurry particles colliding with the shell. The simulation analysis of the lining slurry particles colliding with the shell under different coating port diameters, coating speeds, and coating port spacings is analyzed. The Euler-Euler multiphase flow model is selected to calculate the mixing behavior of the two fluids and a transient setting is adopted. The control variable method is used to simulate and analyze the influence of region diameter, coating speed, and spacing between regions on the process of slurry particles colliding with the shell.