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Etude de la détonation continue rotative - Application à la propulsion

Abstract : The concept of the continuous detonation engine, applied here to the space propulsion, is based on the detonation maintained in an annular chamber by a continuous supplying of reactive mixture in front of it. An experimental device was designed to characterize its propulsive performance at or under atmospheric pressure. Restrictions or nozzles can be adapted to the ejection section of the engine to increase its performance. The observation of the physical phenomena related to the rotary detonation requires fast metrology and cameras. The performances are evaluated on the basis of thrust measurements. Wall temperature and vibrations are also measured.

The experimental observations show the existence of a regime of continuous reactive fronts. Parametric studies on the operation and the geometry of the engine highlight the constancy of this mode of fronts. Their number, constant in stationary phase, is generally contained between 1 and 8 according to the conditions of test, their celerity very little between 1000 and 1300 m/s and the pressure ratio through the fronts is close to 2 or 3. The characteristics of this mode (pressure, celerity) are definitely lower than the properties of the Chapman – Jouguet detonations mainly because the mixing of the fresh mixture with the burned gases decreases its reactive properties. The feasibility of the continuous detonation engine was proven but its performances will have to be the subject of other studies to specify its interest in propulsion.
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Contributor : Gabriel Canteins <>
Submitted on : Tuesday, January 16, 2007 - 11:19:16 AM
Last modification on : Thursday, March 7, 2019 - 3:08:05 PM
Long-term archiving on: : Tuesday, April 6, 2010 - 8:08:48 PM


  • HAL Id : tel-00124803, version 1



Gabriel Canteins. Etude de la détonation continue rotative - Application à la propulsion. Energie électrique. Université de Poitiers, 2006. Français. ⟨tel-00124803⟩



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