Investigation On Solid Rocket Ramjet Flowpath Design And Its Component Performance Fast Prediction Method

The Ramjet is composed of inlet,combustor,nozzle,etc.It involves a wide range of aerodynamic problems,each component in different operating conditions of the flow field is very complex.Using computational fluid dynamics software to calculate the flow field takes a long time.For this reason,a digital system for the design of ramjet flow passage is built,and the fast prediction method for the flowpath is studied.The main work of this paper is as followsFirst of all,a set of flow passage design program for solid rocket ramjet is developed.The inlet design includes two-dimensional plane inlet and axisymmetric inlet,and the viscosity is modified.The afterburning chamber is designed as an axisymmetric structure.The nozzle design module consists of a conical nozzle and two special nozzles.Secondly,for the fast prediction of complex flow field,this paper introduces a method which combines the proper orthogonal decomposition and the radial basis function proxy model to build the prediction model.Finally,this method is used to predict different parts of the solid rocket ramjet.In the fast prediction of inlet flow field,Mach number(single factor)and angle of attack(two factors)are used as variables.In the fast prediction of afterburner flow field,the air flow rate is taken as the variable.The back pressure is taken as a variable to predict the flow field of the nozzle.The results show that the prediction method is fast and accurate.The prediction results of the whole flow field are in good agreement with the CFD results.It can truly reflect the internal flow field structure and accurately predict the performance.The fast prediction method has a good application prospect in the design of the flow field and the prediction of the flow field of the solid rocket ramjet.