Pulse detonation rocket engines (PDREs) offer potential performance improvements over conventional designs, but represent a challenging modellng task. A simplified model for an idealized, straight-tube, single-shot PDRE blowdown process and thrust determination is described and implemented. In order to form an assessment of the accuracy of the model, the flowfield time history is compared to experimental data from Stanford University. Parametric Studies of the effect of mixture stoichiometry, initial fill temperature, and blowdown pressure ratio on the performance of a PDRE are performed using the model. PDRE performance is also compared with a conventional steady-state rocket engine over a range of pressure ratios using similar gasdynamic assumptions.


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    Title :

    Simplified Analysis of Pulse Detonation Rocket Engine Blowdown Gasdynamics and Performance


    Contributors:

    Publication date :

    2002


    Size :

    23 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English






    Simplified Analysis of Pulse Detonation Rocket Engine Blowdown Gasdynamics and Performance

    Morris, C. I. / American Institute of Aeronautics and Astronautics / Society of Automotive Engineers et al. | British Library Conference Proceedings | 2002