Progress on Pulsed Detonation Rocket Propulsion at AFRL: Constant-Volume Limit Studies and LOX Spray Detonations.

摘要

Progress and plans for research at AFRL on pulsed-detonation rocket engines are described. Analytical studies of the constant-volume limit of pulsed-propulsion have been completed and have shown that the specific impulse penalty of using a fixed area ratio nozzle is less than 3%. Numerical studies of pulsed combustors have elucidated the importance of characteristic times for heat release, chamber blowdown and injector pulsing period. Experimental studies are under way to demonstrate the feasibility of the concept and provide anchoring data for the model. Plans for LOX spray detonation studies are described.