Abstract
A theoretical performance analytical model of air breathing pulse detonation engine is established in flight regime. It is based on single-cycle pulse detonation engine analytical model. The influence of the flight regime change on performance of pulse detonation engine was studied. The results show that the average thrust is decreased with the increase of flight altitude at given Mach number, and the influence of Mach number on thrust depends on the propulsive characteristics of inlet and detonation chamber. The effects of detonation frequency and combustor diameter are also considered in the model which is useful to the design and analysis of pulse detonation engine.
| Original language | English |
|---|---|
| Pages (from-to) | 656-659 |
| Number of pages | 4 |
| Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| Volume | 19 |
| Issue number | 5 |
| State | Published - Oct 2004 |
Keywords
- Aerospace propulsion system
- Air breathing
- Performance
- Pulse detonation engine