Research On The Analysis Method Of Transition State Of Solid Rocket Ramjet

Based on the engineering application of a large diameter solid rocket ramjet engine,the ground direct connection test and numerical simulation of the engine are carried out,and then the transient process of the integrated flow field of missile body,inlet and afterburner is numerically analyzed,and the characteristics of the two-phase combustion flow field in the afterburner are discussed.It provides theoretical guidance for the engineering application of this type of solid rocket ramjet in missiles.(1)In this paper,according to the flight conditions of a solid rocket ramjet,the ground direct connection test is carried out.The total pressure and temperature of the inlet and the pressure and temperature near the wall of the afterburner are measured.The condensed phase combustion products in the internal and outdoor collectors of the engine are collected,and the composition and distribution of the combustion products are studied.(2)In this paper,a numerical model of the internal flow field structure of the engine direct connected test device is established.The accuracy of the calculation method used in the numerical analysis of the engine is checked by using the test results.The relative error of the measuring points at the same position is less than 10%.The calculation method used in the simulation is reliable.(3)In this paper,the steady-state and unsteady-state numerical analysis of the missile body inlet afterburner integrated model is carried out.The steady-state analysis of the integrated model can predict the internal and external flow field of the whole missile model in advance,which is helpful to the convergence of the unsteady calculation process.In addition,the influence of the increase of the gas flow rate on the internal thrust characteristics of the gasfired engine is studied by numerical simulation.