Simulation Of Solid Rocket Motor Working Process Based On One Step Chemical Reaction

In the design of solid rocket motor, the accurate calculation of internal flow fieldproperties is very important to the performance prediction of internal ballistic parameter,efficient design and the manufacture of solid rocket motor. In the present, researches onsimulation of solid rocket motor working process are2-D simplified geometry models on thecondition of fixed total temperature, without the consideration of the influence of the changeof heat release in propellant combustion. But in the working process of real motor, the flowfield is3-D, and heat release in propellant combustion with the temperature, pressure,propellant burning rate in flow field are intercoupling and interacted. So the research ofpropellant burning and gas flow in the solid rocket motor is a very important part of numericalsimulation of solid rocket motor working process, and of important significance to researchon performance parameters and the design of solid rocket motor.Based on simple chemical reaction, the interaction of propellant burning and gas flow isstudied in this paper by numerical simulation on internal ballistic flow field in solid rocketmotor with the help of Fluent. In the numerical simulation of working process in solid rocketmotor, complex chemical reaction mechanism is simplified into the general step of chemicalreaction, and with the help of data about general step of chemical reaction on solid rocketmotor which has been confirmed in foreign countries, precise simulation on chemical reactionis studied in this paper.Based on One-step chemical reaction of K. K. Kou, establish2-D simulation model offlow field in solid rocket motor. By Laminar Finite-Rate model, Eddy Dissipation model andFinite-Rate/Eddy-Dissipation mixed model,the numerical simulation of internal ballisticflow field is performed. By comparing the influence on burning field between differentmodels, Eddy Dissipation model agrees with the simulation on the process of turbulentcombustion with high pressure and temperature very well.According to turbulent boundary layer model theory on chemical reaction, the numericalsimulation on turbulent boundary layer of burning surface on propellant is studied, and thevariation of flow field in turbulent boundary layer which has chemical reaction on the surfaceof propellant is studied.By the use of Eddy Dissipation model and k turbulence model, the process in solid rocket motor of2-D, quasi steady state is simulated. Internal ballistic properties basedon One-step chemical reaction in the working process of solid rocket motor at four differenttimes is studied, so is the change rule of internal ballistic properties and parameters inworking process.Based on the analysis above,3-D numerical simulation on internal ballistic flow field insolid rocket motor is performed. The interaction relationship of distribution of solid rocketmotor’s performance parameter and propellant burning, gas flow is analyzed. And comparethe results of simulation on3-D flow field in solid rocket motor between the model based onOne-step chemical reaction and model without chemical reaction.