Coupling Analysis Between Inlet Passage And Secondary Combustion Chamber In The Solid Rocket Ramjet

In this paper,performance and the flow field characteristics of the inlet passage in the large-diameter solid rocket-ramjet were investigated via experiments and numerical approaches.And numerical investigation of the secondary combustion chamber coupled with the inlet passage was conducted to provide guidance for designing and optimizing of the solid rocket-ramjet.(1)The connected pipe facility was employed to conduct the experimental researches of the air intake,the operating condition of the experiments was determined by the flight conditions.In addition,the pressure of the inlet passage wall was measured to verify the numerical cases.This is to make sure the performance of the inlet passage could be analyzed accurately.(2)The inlet passage performance was investigated based on the three aspects of the secondary combustion chamber,such as Mach number,angle of attack,and back pressure.The results indicated that decreasing the Mach number can increase the total pressure recovery coefficient and reduce the flow coefficient;The wave system structure of the air intake could be sensitive to the angle of attack.And based on the above obtained results,the large back pressure and wide working range could be withstood by the present inlet passage which is satisfied with the requirement of the solid rocket-ramjet.(3)A series of simulation was conducted to explore the effect of non-uniform flow filed of the secondary combustion chamber.Moreover,the influence of intake angle on the Blended Combustion performance was studied without changing the layout of the engine.