the continuous detonation wave rocket engine : dream or reality ?

Paper number

IAC-08.C4.6.7

Author

Mr. Francois FALEMPIN, MBDA France, France

Year

2008

Abstract

Detonation wave engines, thanks to their more efficient thermodynamic properties, are expected to exhibit a higher level of performance than more conventional propulsion system that rely on constant-pressure combustion processes. 
Nevertheless, it still has to be proved that this advantage is not superseded by the difficulties which could be encountered to practically define a real engine and to implement it in an operational flying system. In that respect, continuous detonation wave principle appears less challenging than the pulsed detonation process and should lead to the development of more efficient propulsion systems, even if such radical adaptation of the overall engine concept and of the vehicle architecture would be necessary. Moreover, compared to a Pulsed Detonation Engine, this design allows an easier operation in reduced-pressure environment and an increase in engine mass flow rate and thrust-to-weight ratio.
During past years, MBDA performed some theoretical and experimental works, mainly in cooperation with the Lavrentyev Institute of Hydrodynamics in Novosibirsk. These studies aimed at obtaining a preliminary demonstration of the feasibility of a Continuous Detonation Wave Engine for air-breathing and rocket application. These studies were focused on global performance and understanding of the unsteady, three dimensional flow behind the detonation wave. 
Then, 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 :
two-phase mixture detonation,
operating limits (injection pressure for example),
noise generated by a CDWE operating at several kilohertz,
heat fluxes (intensity, areas) and cooling strategies,
composite materials (Carbon / Silicon Carbide) compatibility,
engine thrust vectoring capability.
Beyond these first steps, MBDA designed a large scale ground demonstrator allowing to address all already mentioned issues for a continuous detonation rocket engine using LH2/LOx mixture. This demonstrator will be described in the paper and status of its development will be provided. 
On the basis of these results, a preliminary design of an operational Continuous Detonation Wave Rocket Engine (CDWRE) usable for the upper stage of a space launcher has been performed taking into account all engine/airframe integration issues in order to optimize the benefit of detonation wave engine.
The proposed paper will provide a synthesis of acquired experimental results and the main outputs of the CDWRE preliminary design works in order to conclude on the actual potential of such a technology for space launcher application.

Abstract document

IAC-08.C4.6.7.pdf

Manuscript document

IAC-08.C4.6.7.pdf (🔒 authorized access only).

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