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Non-Contact Acoustic Method for Determining the Pressure in the Combustion Chamber of a Model Solid Rocket Motor

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Combustion, Explosion, and Shock Waves Aims and scope

Abstract

This paper presents a non-contact diagnostic technique for solid rocket motors (SRM) based on the analysis of acoustic vibrations generated by the supersonic jet of combustion products from the nozzle. The pressure in the combustion chamber of a E-5-0 model sold rocket motor was determined experimentally by a noninvasive control method using a dynamic microphone placed at a prescribed distance from the test object and recording the acoustic fields generated by the operating engine. Experiments confirmed the possibility of non-contact determination of combustion chamber pressure from the frequency of acoustic vibrations and the sound pressure generated by the jet of combustion products of the model SRM. Calculated pressures are in satisfactory agreement with the values recorded by an intra-chamber pressure transducer.

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Authors and Affiliations

  1. Bauman Moscow State Technical University, 105005, Moscow, Russia

    K. E. Kovalev, D. A. Yagodnikov & A. N. Bobrov

Authors
  1. K. E. Kovalev
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  2. D. A. Yagodnikov
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  3. A. N. Bobrov
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Correspondence to K. E. Kovalev.

Additional information

Translated from Fizika Goreniya i Vzryva, 2023, Vol. 59, No. 4, pp. 78-84. https://doi.org/10.15372/FGV20230409.

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Kovalev, K.E., Yagodnikov, D.A. & Bobrov, A.N. Non-Contact Acoustic Method for Determining the Pressure in the Combustion Chamber of a Model Solid Rocket Motor. Combust Explos Shock Waves 59, 464–470 (2023). https://doi.org/10.1134/S0010508223040093

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  • DOI: https://doi.org/10.1134/S0010508223040093

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