Study of Combustion Mode Identification Method on Dual-Mode Solid Rocket Scramjet

A Direct connection experiment study of combustion mode transition was completed under the air conditions with Mach 2.2, total pressure 1.1 MPa and total temperature 1660 K, and a real-time identification method of combustion mode on dual-mode solid rocket scramjet was proposed. Based on the adiabatic assumption, the Mach number at the isolator exit could be calculated and used as the criterion for identifying the combustion mode. The pressure of the upper engine wall was measured during the test. It was found that the pressure of the isolator changes significantly during the combustion mode transition by analyzing the pressure changes in the isolator. The ratio of pressure between the exit and inlet P 𝑖/P 0 is below 2 when the combustion works in scram-mode, while the value of P 𝑖/P 0 is over 2 when it is in ram-mode.