Performance analysis of a hybrid pulse detonation engine using liquid hydrogen as fuel

Abstract

Aimed at enhancing the comprehensive performance of the air turbo rocket engine (ATR), two schemes of hybrid pulse detonation engine (PDE) configurations based on the ATR were proposed. The engines are fueled by liquid hydrogen, and the oxidant is the incoming air or self-carried liquid oxygen. The ideal thermodynamic cycle processes of the engines were analyzed, and the relevant mathematical models were established. The fuel pump pressure ratio of the ATREX and the oxidant-fuel ratio of the ATR-GG are respectively used as iterative variables. The performances of the two engine schemes at the design point were obtained and compared with that of the traditional ATR. The results show that, under ideal conditions, the specific thrust and specific impulse of the hybrid PDE based on the ATREX are about 20% higher than those of the traditional ATREX. Moreover, the mass of the oxidant required by the hybrid PDE based on the ATR-GG is about 49.5% lower than that of the traditional ATR-GG, while the specific thrust and specific impulse are not reduced as compared with those of the traditional ATR-GG.