LAUSR

Abstract In this paper, a new scramjet configuration using solid fuel as propellant is proposed, namely, the solid rocket fuel gas scramjet. The ignition and combustion characteristics and performance of the engine were evaluated by the experimental and numerical methods. The experiment simulated a flight environment of Mach 5.3 at a 21 km altitude. Solid oxygen-poor propellant containing boron was used in this study. The experiment results show that primary rich fuel gas can be reliably ignited in the supersonic combustor and can maintain stable combustion, which demonstrates the feasibility of the solid rocket fuel gas scramjet configuration. The numerical simulation results show that the combustion efficiency of the combustor is 0.56 and the total pressure recovery coefficient is 0.44, which further demonstrates the feasibility of the solid rocket fuel gas scramjet configuration proposed in this paper.