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Experimental demonstration of the operation process of a pulse-detonation liquid rocket engine

Combustion, Explosion, and Shock Waves

Abstract

A low-frequency demonstrator of the operation process of a pulse-detonation liquid-fuel rocket engine, intended for shaping the future design of a new type of rocket engines for spacecraft control, is for the first time developed and tested. As a result, the conditions are determined under which the demonstrator provides reliable deflagration-to-detonation transition (DDT) in a single-pulse or repetition mode. Because DDT occurs within a very short distance (less than 10 bores of the detonation tube), the operating frequency of the demonstrator can be substantially increased.

Keywords

pulse detonation liquid-fuel rocket engine deflagration-to-detonation transition repetition mode experimental studies 

References

  1. 1.
    Pulse Detonation Engines, Ed. by S. M. Frolov (Torus Press, Moscow, 2006) [in Russian].Google Scholar
  2. 2.
    Ya. B. Zel’dovich, Zh. Tekh. Fiz. 10(17), 1453 (1940).Google Scholar

Copyright information

© Pleiades Publishing, Ltd. 2011

Authors and Affiliations

  1. 1.Semenov Institute of Chemical PhysicsRussian Academy of SciencesMoscowRussia

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