Investigation On Operating Characteristics Of Solid-fuel Rocket Scramjet Engine

Scramjet technology has been studied extensively all over the world now. With theresearch of liquid-fuel scramjet engine, the study of solid-fuel scramjet engine has beenrising quietly. At present, the configuration of solid-fuel scramjet engine is still thesame as the configuration of inner-hole combustion for the subsonic solid-fuel ramjetengine. However, there are certain deficiencies for this boundary diffusion combustionmethod, such as unsteady flame, unpredictable and uncontrolled burning rate andinefficient fuel burning. This paper presents and designs configuration of solid-fuelrocket scramjet engine and investigates the flow and combustion process in the secondcombustor of solid-fuel rocket scramjet engine by numerical simulation andexperimental research.Two configurations for solid-fuel rocket scramjet engine are proposed, namely,side fuel-inlet model and nose fuel-inlet model solid-fuel rocket scramjet engine.The side fuel-inlet solid fuel scramjet engine connected-pipe test is introduced andthe test data are analyzed. Based on the characteristics of solid-fuel rocket scramjetengine in connected-pipe test, the numerical simulation model for solid-fuel rocketscramjet engine is established. The flow field of second combustor for side fuel-inletsolid-fuel rocket scramjet engine is simulated. The numerical results agree well with theexperimental data, reflecting the validity of the simulation method. According to thenumerical simulation, the flow field of engine is analyzed.The nose fuel-inlet solid-fuel rocket scramjet engine is designed and processed andthe second combustor flow field for Mach4and Mach6, as well as different conditionsof the gas-generator at Mach6are numerically simulated and analyzed, providingreference to the further experiments and data analysis.The connected-pipe tests of nose fuel-inlet solid-fuel scramjet engine have beenperformed. Combining the numerical analysis and experiment data, it shows that therich-gas produced by gas generator can burn in the supersonic flow. And the thrustproduced by burning of rich gas is estimated.