A new approach to thrust measurement for pulse detonation engines was developed to account for the effects of system dynamics. The approach was applied to a pulse detonation engine operating at 10 and 20 Hz. System parameters such as steady-state response, effective mass of the combined pulse detonation engine and thrust measurement rig structure, and mass flow rates of the fuel/oxidizer were first determined. The system dynamics of the pulse detonation engine, deconvolved in the frequency domain, was studied. The system’s transfer function between the thrust and a corresponding pressure obtained by a single propagating detonation pressure history during pulse detonation engine operation was established and used to reconstruct the thrust response for pulsed operation. A proper reconstruction of the deconvolved thrust values was accomplished through this technique. The acceleration experienced by the pulse detonation engine thrust measurement rig was also measured. This measured acceleration when multiplied by an empirical effective mass gave an estimate of the inertial force. The estimated inertial force when subtracted from the deconvolved force gave actual thrust. The measured and compensated thrust were expressed in the form of impulse.


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    Title :

    Unsteady Thrust Measurement for Pulse Detonation Engines


    Contributors:

    Published in:

    Publication date :

    2016-01-01




    Type of media :

    Conference paper , Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




    Unsteady Thrust Measurement for Pulse Detonation Engines

    Joshi, Dibesh D | Online Contents | 2016


    On the Unsteady Thrust Measurement for Pulse Detonation Engines

    Joshi, D. / Lu, F. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2012