Analysis Of Thrust Development In A Pulse Detonaton Engine

Abstract

Pulse detonation engines (PDE) employ detonation waves to compress and burn the fuel and oxidizer mixture which results in the release of high pressure and temperature. The objective of the present study is to analytically model the PDE cycle and to study the pressure, temperature, velocity and density distributions during the Taylor rarefaction wave, reflected rarefaction wave and the blow down process. A two-dimensional supersonic nozzle is designed analytically by using the method of characteristics. The average values of nozzle thrust for one PDE cycle are calculated analytically using the impulse function and thrust coefficient. The variation of PDE thrust with the change in altitude is studied by designing the nozzle for two design points.