Abstract
For an application of PDE to hypersonic air-breathing engines, thrust performances of air-breathing PDEs are estimated analytically in this study. Thrust/weight ratio of the engine decreases with increasing flight speed because of a low density of atmospheric air. In order to improve this disadvantage, new concept air-breathing PDE is proposed. By closing the exit of the PDE combustion chamber during a filling phase, ram pressure of the intake can be utilized effectively. Furthermore, by cooling the intake exit air by the cryogenic fuel, flight range can be extended for M 0.5. After system analysis of the air-breathing PDE, PDRJE (Pulse Detonation Ram Jet Engine) with air precooler is proposed. Size of PDRJE is 0.3 m in cowl inlet diameter. Engine thrust and weight are estimated to be 4.6x103 N and 74 kg respectively. To evaluate the basic performances of the PDE, firing test of the scaled model was performed using GH2 and GOX. Heat flux of the combustion chamber was approximately 5 kW/m2/Hz.
