Numerical Simulation Of Unsteady Burning Of Solid Rocket Motors Erosion

The erosive burning has a greatly effect on the performances of the solid rocket motors. H.Muraour first made the effects of erosive burning of a solid propellant since the1927, researched and controled the erosive burning have been charged an important issue in the field of the solid rocket motors. According to this important subject, the main conclusions are as follows:(1) Diaphragm rupture process is a strong unsteady process in solid rocket motor and has great influence on solid rocket motor, but has been neglected, especially erosive burning in the ignition stage. Through the secondary development of the Fluent software using UDF interface programme, the rupture process was numerically simulated for free filling grain in a solid rocket motor model. Good agreement is obtained between experimental firing data and predictions from the model for head-end pressure-time profiles. Then detailed analysis the flow characteristics of the inner flow field which caused by the rupture process and which provides reference for understanding ignition and designing igniter.(2) In order to further study the erosive burning solid rocket motor. Through the Fluent software and dynamic mesh technique, an axisymmetric numerical simulation method which coupled the propellant combustion model of transient Zeldovich-Novozhilov energy equation, a moving boundary was carried out the unsteady erosion burning process of a solid rocket motor with side burn. More accurate to obtain the specifics of inner flow field and the pictures about moving burning surface. Dynamic analysis changes rule of the erosion ratio and the gas passage diameter. The research as a reference for design motors and to test has reference significance for this type solid rocket motor.