Numerical Simulation And Parameter Design On Missile Gas-ejection Interior Ballistic

Gas ejector system is an important device for missile catapult process,its role is to help the missile take off quickly,increase the missile range,improve combat capability.Gas Ejection depend on its simple launch device,highly mobile,the high speed of the cartridge is widely used in missile weapon system’s launch.The research of Gas-ejection Interior Ballistic has a crucial role in enhancing combat capability,improving ejector performance and ensuring launch safety.At present,most of the research on gas ejection system adopts the method of experimental demonstration after the first theoretical analysis.This paper put the missile gas catapult as the research object,establish the mathematical model for numerical simulation,analyzed the physical process of Gas-ejection,at the same time,has the optimal design of the parameters of the Gas-ejection Interior Ballistic.The main parts are concluded as follows:a)Based on the classical intra-trajectory theory equations,established the z ero-dimensional interior ballistic mathematical model of the gas catapult system.The fourth-order Runge-Kutta method and the iterative algorithm.was used to numerical simulation calculation.And analyzed the influence of different factors on gas ejection processb)Based on the established zero dimensional interior ballistic mathematical model,the genetic algorithm is used to optimize the five interior ballistic parameters.The optimization goal is the theoretical calculation value and the target value.The experimental results showed that the optimized parameters can effectively improved the accuracy and predictability of the interior ballistic mathematical model,thus verifiedthe feasibility and validity of applying the genetic algorithm to the optimization of the inner trajectory parameters.c)The two dimensional numerical simulation of the fuel catapult process is carried out.Using Fluent software to establish the grid,call the solver to solve the calculation.Finally generated the pressure field,velocity field,temperature field and other flow field distribution cloud and vector diagram of pressure,temperature andvelocity varying with time.d)Building the integrated software of numerical simulation for the internal ballistic trajectory.The software implementate numerical simulation of the zero dimensional interior ballistic mathematical and two-dimensional trajectory mathematical model by programming,generated data report based on simulation results.A set of internal trajectory parameters are obtained by numerical simulation and parameter design of the internal combustion trajectory model.The simulation results are moderate,the pressure change is stable and the speed also meets the requirements of takeoff。The mean pressure of the high pressure chamber,the average pressure of the launching cylinder,the average temperature of the launching cylinder,the velocity of the missile,the displacement and the acceleration of the time and the flow field are drawn to provide the theoretical basis for the design of the catapult.