Development Of Simulation System For Solid Rocket Motor Grain Burning Surface Transition

The grain design and combustion surface transition are one of the core contents of solid rocket motor design.Based on the idea of grid method and parallel layer combustion law,the parametric modeling and surface dispersion of complex three-dimensional charges,and one-dimensional interior ballistics.Coupling and combustible charge method of burning surface shifting are studied,and the charge design and the development of the burning surface shifting simulation system were completed.First of all,on the basis of previous research,this article improves the charge design program based on the UG NX secondary development interface,increase the parameterized modeling of the tube-shaped charge,and do the discrete stage of the charge.Optimized design and improved calculation efficiency.At the same time,developing a method for dispersing the fitting surface of the tube-shaped charge and a custom discrete program for the combined charge,making the design of the charge more diversified.Secondly,writing the calculation program for the combustion surface transition.By analyzing the changes in the geometry of the tube and trough-shaped charge during the process,the problem of the intersection of the combustion surface and the flow surface of the tube and the trough-shaped charge and the density processing of discrete points are solved and improved.The combustion surface moving process coupled with the non-tubular tank charge and the one-dimensional interior ballistic is optimized,the management method of discrete point data is optimized,and the calculation efficiency is improved.Finally,the data transmission between the combustion surface transition and the charge design expert system and the visualization of the combustion process is realized,and the data collection of the expert system knowledge base is provided,making the charge design system more complete.At the same time,the combustion surface transition process of the combined charge shape is analyzed,and the mathematical formula of the combustion surface,aeration area and free volume change with the thickness of the burned flesh is deduced,and the impact of the erosion effect is considered,and the combined charge shape is compiled.The analytical solution calculation program of the combustion surface transition solves the problem of the transition section of the combined charge transition in the improved grid method in this paper.The research results of this paper are applicable to both tubular and non-tubular single-channel charges,and a preliminary study on the combustion surface transition of the combined charge is carried out.The combustion surface transition simulation system can accurately predict the combustion process of the solid rocket motor charge,which possesses engineering application value.