Numerical Research On Working Process And Combustion Organization For Hybrid Rocket Motor

With the advantages of high safety,high reliability,low cost,adjustable thrust,restartablity,non-pollution,hybrid rocket notor is highly competitive and prospective.in the field of aerospace propulsion system.In this paper,hybrid rocket notor is the research object,the theoretical analysis and numerical simulation are combined to study the working process and combustion organization of hybrid rocket notor.It provides a theoretical basis for the design and application of hybrid rocket motor.The complex physical and chemical processes like atomization and evaporation of liquid oxidizer,solid fuel pyrolysis,regression of burning surface,and gas phase component mixing and combustion inside the hybrid rocket motor have been analysed.Based on two-dimensional axisymmetric Reynolds averaged Navier–Stokes equations,coupled with coupled gas/solid phase formulations and fuel pyrolysis additive model,combined with the dynamic mesh method,the unsteady numerical simulation model of internal combustion and flow in the motor has been established.Compared with the classical test data,the accuracy of the model is verified,which provides an important basis for the simulation research of hybrid rocket motor.Coupled with ignition gas generation model and oxidizer droplet Lagrange trajectory model,The unsteady numerical simulation of the whole woking process from the ignition to the normal operation to the flameout of a N₂O/HTPB hybrid rocket motor carried out.The internal ballistic curve of the motor is obtained.The physical and chemical processes in the process of motor operation and the influence mechanism and law on motor performance parameters are analyzed.The effect of oxidizer flux on engine performance was further analyzed.It provides technical support for the simulation of combustion organization of hybrid rocket motor.Based on different engine configurations,unsteady state simulations of combustion organization in hybrid rocket motor have been carried out.The working processes and performances of the motor were calculated under the conditions of different grain lengths,lengths of post combustion chamber and the positions of diaphragm.The influences of different factors on the working processes and performances of the motor were analyzed.The better combustion organization mode was explored.It provides data reference for the configuration design of hybrid rocket motor.Based on the combination of GOX/HTPB propellant,the three-dimensional steady numerical simulations of the star swirl fuel grain hybrid rocket motor have been carried out.The interior temperature distribution,engine oxidizer mass fraction,gaseous fuel mass fraction distribution and regression rate distribution are discussed.Analysis of different oxidant flow and grain configuration on regression rate and the effect of oxygen fuel ratio,the combustion efficiency of the engine performance parameters have been carried out.It provides technical support and data support for the simulation research of complex grain hybrid rocket motor.The results of this study will promote the development of the hybrid rocket notor technology,promoting the hybrid rocket notor numerical simulation technology.It has important theoretical significance and engineering application value for the development and application of hybrid rocket notor.