Chamber pressure, as it develops during rocket combustion, strongly correlates with many of the internal motor ballistic properties, including combustion stability, fuel regression rate, and mass flow. Chamber pressure is also an essential measurement for calculating achieved thrust coefficient and characteristic velocity. Because of the combustion environment hostility, sensing chamber pressure with high fidelity presents a difficult measurement problem, especially for solid and hybrid rocket systems, where combustion by-products contain high amounts of carbon and other sooty materials. These contaminants tend to deposit within the pneumatic tubing used to transmit pressure oscillations from the thrust chamber to the sensing transducer. Partially clogged transmission tubes exhibit significant response latency and damp high-frequency pressure oscillations that may be of interest to the testers. A maximum-likelihood method for fitting a second-order model to chamber-pressure response is presented. The resulting model is subsequently used to reconstruct a high-fidelity motor response via optimal deconvolution. The method is applied to small hybrid-thruster results from three separate testing campaigns. Key performance parameters, such as thrust coefficient, characteristic velocity, and specific impulse, are recalculated using the reconstructed data. Results are compared to the unreconstructed data and are shown to exhibit consistently better agreement with theoretical predictions.


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    Titel :

    Attenuated Chamber-Pressure Signal Reconstruction Using Maximum-Likelihood Estimation and Optimal Deconvolution


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    2021-01-28


    Format / Umfang :

    15 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch