R&T Effort on Pulsed and Continuous Detonation Wave Engines

Due to its thermodynamic cycle, the pulsed detonation engine (PDE) has theoretically a higher performance than classical iso-pressure combustion propulsion concepts. Nevertheless, PDE design must avoid this advantage being not fully compensated by the difficulties encountered for practical use of the PDE concept or by the complex technology, which could be needed to implement it in an operational flying system, particularly due to severe generated vibration environment. The Continuous Detonation Wave Engine (CDWE) can also be considered to reduce the environmental conditions generated by PDE while reducing the importance of initiation issue and simplifying some integration aspects. Specific experimental program has been performed by MBDA and Lavrentiev Institute to understand unsteady, three dimensional flow behind the detonation wave and to address some key points for the feasibility of an operational rotating wave engine for space launcher. On the basis of these results, a preliminary design of an operational engine has been performed by taking into account all engine/airframe integration issues in order to optimize the ben efit of detonation wave engine. Beyond these first steps, MBDA designed a large scale ground demonstrator allowing to address all issues for a continuous detonation rocket engine using LH2/LOx mixture. As a first step toward the development of this large scale engine, a small scale demo is to be tested in Fall 2009.