| Based on related development work of a certain remote rocket, In order to solve the problems of solid rocket engine design, performance analysis, numerical simulation of working process and optimization propellant, the further research on energy characteristic, combustion characteristic and thermal physical parameters determine in the working process of solid rocket engine and software platform development were carried out in this dissertation, its'main contents were as follows:1. The Gibbs free energy minimization method for energy characteristic calculation of solid rocket engine was concretely educed. The various possible losses of solid rocket engine s were analyzed, the problem of obvious deviation between measured value and theoretical value for solid rocket engine was solved by introducing actual factor analysis and the induction of comprehensive factor, the prediction precision of performance of solid rocket engine was greatly improved.2. Some phenomenon of agglomeration would occurred for fine-grained AP has a poor dispersion, so a burning rate prediction model for CMDB propellant with fine-grained AP was established by introducing process particle size; In addition, catalytic mechanism hypothesis was proposed, which the catalyst would further effected the cracking behavior of free radical clusters in the gas phase near the combustion surface, the catalystic impact factors with physical meaning were constructed, a catalystic burning rate prediction model of AP-Al-HTPB propellant which could reflect type and content of the catalyst was also established. Finally, the prediction precision of the burning rate was significantly improved, the prediction scope of the burning rate was also broadened.3. Summarized the methods for calculating thermal physical parameters of multi-com-ponent gas with high pressure and high temperature in the solid rocket engine. By introducing the methods of Lennard-Jones potential energy and Svehla polynomia, the thermal physical parameters of one-component or multi-component gas in numerical simulation of working process of solid rocket engine were well determined, some conditions were created for improving numerical simulation precision in the working process of solid rocket engine.4. With the platform of Microsoft Access database, the information database covered with numerous and jumbled data such as formula, component, thermal transport of the product composition was established and improved, which was firstly and fully used the database structure. Choosing Visual C++ as development tools, using MFC ODBC data access interface technology, the software SRPS based on database for synthetical performance prediction of solid propellant rocket engine was developed, which has a friendly interface, convenience in practice and high specialization. The application platform for related development work of solid propellant rocket engine was provided. The generality and convenience of theoretical prediction methods were improved.5. With the platform of SRPS software, the general scheme demonstration and performance prediction of remote rocket weapon were successfully completed, the correcting errors of specific impulse was increased to 2.0%, a theoretical criterion of rationally controlling structure parameters tolerance for effectively reducing range dispersion was given, at the same time, thermal physical parameters for numerical simulation of working process of remote rocket Y-300 engine were given accurately, finally, the cycle and cost of development was greatly reduced.Some good calculation models and approaches for energy characteristic, combustion characteristic and thermal physical parameters determine in the working process of solid rocket engine were obtained through this research, the check results were satisfactorily too, combined with the development platform of SRPS software, some theoretical guidance and technical support were provided, which were used fundamental research and engineering application.
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