Working Process Simulation And Performance Analysis For Solid Fuel Ramjet Projectile

For the excellent characters of simple configuration, high specific impulse and low cost, Solid Fuel Ramjet (SFRJ) has become the preferred power system for the next long-range and ultralong-range projectiles. Aiming at a 155mm SFRJ extended range projectile, this dissertation explores computation and analysis research for it's overall and power system performance in the method of theoretical analysis combined with numerical simulation.Based on two-dimensional Steady-Compressible N-S equations, standard two-equation ( k～ε) turbulence model and Eddy-Dissipation combustion model, the work process simulation model for SFRJ is established. Then, the characters of flow and combustion are analyzed, on which the correlations among average regression rate, air mass flux, air temperature and pass-diameter are obtained. After comparing the calculated results with foreign experimental data, the model is proved reliable. Then the work process of the 155mm SFRJ is simulated and the regression rate calculated formula is induced through identification. Based on that, the engine performance parameters of thrust and specific impulse are analyzed, and then the curves which present the relationships between performance parameters and their influential elements are gained.Based on two-dimensional Steady-Compressible N-S equations and standard two-equation (k～ε) turbulence model, a simulation model is established which is applied to the internal and external flow of SFRJ projectiles. Then flow characters of both the internal and external flow field under different Mach number are analyzed, as well as the influence of inlet worked on the flow field. Based on simulated results of the flow field, a projectile-engine integrated computing model for exterior ballistic trajectory, including the dynamic model and drag computing model, is established. The exterior ballistic trajectory for the SFRJ projectile designed is simulated, according to which the relationships between range and engine structural parameters are obtained. So, the study can serve as the basic of the overall optimization for SFRJ projectiles.A finite-element computing model is established, based on which the force condition and stress-strain distribution of the projectile bearing large load in the process of launching are analyzed. Then the projectile structure is improved and computing results proved that the stress concentration is obviously weakened.Research results in this dissertation have some reference value and instructional significance in the development of SFRJ Projectiles.