The Solid Rocket Motor Combustion Products Of The Physical Parameters Of The Theory Predicts That

Along with the increasing requirement of modern warfare for weapon system in remote and mobility aspects, the rocket and missile weapons of using solid rocket motor as power play a very important role. For estimation of the theoretical performance and the numerical simulation of working process in solid rocket motor, a professional theoretical estimation software was exploited with friendly interface and convenient usage. The software can predict physical performance parameters of combustion products in solid rocket motor (including the thermodynamic parameters and heat transport coefficient, such as enthalpy, specific heat, entropy, viscosity coefficient, thermal conductivity coefficient, diffusion coefficient, Prandtl Number, etc).Three contents are mainly completed. first, in many computational methods of heat transport parameter of mixed gas, Lennard-Jones potential correction method and Svehla polynomial fitting method are studied and summarized because the methods suit physical performance parameters calculation of single-component and multi-component in solid rocket motor; Secondly, the parameter databases of physical performance and the thermodynamic database based on JANAF thermodynamic data are established or improved where relation data model is adopted. Users can easily query, add, delete or print thermodynamic data information of combustion product and heat transport data, also can compute thermodynamic parameters of a single combustion product or mixture with random temperature; Finally, with development tool of Visual C++6.0, using MFC ODBC data access interface, the theory estimation software of physical performance parameters, suitable for Windows XP/Vista and Windows 7, was developed.Combined reference data, the fittingness and the accuracy of Lennard-Jones potential correction method and Svehla polynomial fitting method were checked. The results show that the two methods can meet the engineering need. Finally, a solid rocket motor of M-21 was selected as example, combined balance components of combustion product in the combustion chamber and the nozzle, while the change regularity of physical performance parameters of combustion product were calculated and analyzed which provided more accurate reference data for performance analysis and numerical simulation of solid rocket motor.