Abstract: The problem of continuous thrust orbit transfer has become one of the research hotspots in the aerospace field in recent years.This problem has also promoted the development of high specific impulse and small thrust engines. The pulse detonation engine based on detonation combustion has the characteristics of high thermal efficiency, high specific impulse and simple structure. The related performance research is carried out. First, the mathematical model of the detonation technology is given, and the analysis method of the equal volume cycle model is introduced. Then the numerical results of the CEA model and the simulation results are compared to verify the reliability of the designed detonation model. And different external gas working fluids, nozzle configurations, and respective simulation analysis of engine internal flow field and performance analysis are carried out under 0.1atm, 0.01atm, 0.001atm ambient pressure. The result analysis shows that the pulse detonation engine can meet the requirements of high specific impulse and small thrust, and the convergent expansion nozzle has the greatest gain in engine performance. As the ambient pressure decreases, the engine thrust increases.

Key words: pulse detonation rocket engine, specific impulse, thrust, detonation wave, numerical simulation