Analysis on thermodynamic cycle performance for turbocharged solid propellant ramjet

The concept of turbocharged solid propellant ramjet(TSPR), a combined engine of SPR and ATR is proposed. This engine needs to meet the requirements for future propellant system including a higher specific impulse, a broader Mach number operational range and flight altitude variation. The thermodynamic analysis of TSPR was discussed, and corresponding thermodynamic cycle model was developed. The thermodynamic performance of TSPR, ATR and SPR was compared in a flight trace. The results show that TSPR, has the highest specific net work output during a cycle, and the thermal efficiency is slightly lower than ATR. It possesses superior integrated performance when flying in a broader Mach number operational range.