Design And Research Of Pouring Experimental Device For Propellant Pouring For Solid Rocket Motor

In this paper,based on the National Natural Science Foundation Project "Study on Gas-Hole Defect and Control Mechanism of Solid Rocket Motor Propellant During Core-Inserting process ".Solid Rocket Motor due to its complex structure,high manufacturing cost,complex and difficult experimental conditions,and extremely expensive experimental cost,it is difficult to achieve a large number of repetitive experiments and obtain a large number of research data.To produce high quality and high reliability of Solid Rocket Motor,we need the influence of temperature,vacuum degree,time and inserting speed on the quality of porosity of the grain forming is clarified through experiments.It is of great significance to establish a more reasonable numerical simulation model based on numerical simulation method,to explore the forming mechanism of slurry in the process of core-inserting,and to design reasonable Solid Rocket Motor charging equipment.It is of great significance to improve the pouring quality of Solid Rocket Motor.The specific research contents include:(1)According to the practical core-inserting pouring production process of Solid Rocket Motor grain,the function of pouring and core-inserting and overall scheme of control systemthe including pressure and temperature are determined.(2)The design of experimental device.Including the overall design of the vacuum cylinder,the design of the pouring assembly and the design of the core-inserting mechanism.The design of pouring assembly includes pouring hopper design,hopper frame design and type selection of pinch valve;the design of core-inserting mechanism includes lifting platform assembly design,leveling platform design and core-inserting supporting design.(3)Heating scheme and structure design of vacuum cylinder.Based on the preliminary design of the vacuum cylinder,the finite volume element method is used to analyze and compare four different heating schemes of the vacuum cylinder.By comparing the temperature field values,the optimal heating scheme is determined,and the heating structure of the vacuum cylinder is determined.(4)The core mechanism and core module are optimized based on numerical simulation analysis including finite element method and finite volume element methods.To meet the linear requirements of the core mode and the engine core axis,complete the lightweight design of the core mechanism.(5)Thermal analysis of core-inserting mechanism.Based on the optimized core-inserting mechanism,the thermal analysis method is used to simulate and calculate the coaxiality of the mandrel and the engine caused by the thermal stress and strain of the core-inserting mechanism under the working environment of 20 ℃ ～ 57 ℃,and to verify the rationality of the mechanism design.The experimental research work to be completed will lay the foundation for the experimental verification of the accuracy of the numerical simulation calculation of the pouring core-inserting process.Through the combination of experiment and numerical simulation theory,reasonable pouring device avoiding pore defects can be designed,so as to improve the charging quality,reduce the charging cost,shorten the charging cycle,reduce the charging pollution.In order to achieve the purpose of high reliability and safety of propellant charging technology.