A number of promising alternative rocket propulsion concepts have been developed over the past two decades that take advantage of unsteady combustion waves in order to produce thrust. These concepts include the Pulse Detonation Rocket Engine (PDRE), in which repetitive ignition, propagation, and reflection of detonations and shocks can create a high pressure chamber from which gases may be exhausted in a controlled manner. The Pulse Detonation Rocket Induced Magnetohydrodynamic Ejector (PDRIME) is a modification of the basic PDRE concept, developed by Cambier (1998), which has the potential for performance improvements based on magnetohydrodynamic (MHD) thrust augmentation. The PDRIME has the advantage of both low combustion chamber seeding pressure, per the PDRE concept,and efficient energy distribution in the system, per the rocket-induced MHD ejector (RIME) concept of Cole, et al. (1995).


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    Title :

    Combustion and Magnetohydrodynamic Processes in Advanced Pulse Detonation Rocket Engines


    Contributors:
    L. K. Cole (author)

    Publication date :

    2012


    Size :

    251 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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    Preliminary Modeling of Pulse Detonation Rocket Engines

    Cambier, J.-L. / American Institute of Aeronautics and Astronautics| Society of Automotive Engineers| American Society of Mechanical Engineers| American Society for Engineering Education | British Library Conference Proceedings | 1999


    Axisymmetric Modeling of Pulse Detonation Rocket Engines

    Morris, C. I. / American Institute of Aeronautics and Astronautics / Society of Automotive Engineers et al. | British Library Conference Proceedings | 2005