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Scale Effects on Solid Rocket Combustion Instability Behaviour

Author

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  • David R. Greatrix

    (Department of Aerospace Engineering, Ryerson University, 350 Victoria Street, Toronto, Ontario, M5B 2K3, Canada)

Abstract

The ability to understand and predict the expected internal behaviour of a given solid-propellant rocket motor under transient conditions is important. Research towards predicting and quantifying undesirable transient axial combustion instability symptoms necessitates a comprehensive numerical model for internal ballistic simulation under dynamic flow and combustion conditions. A numerical model incorporating pertinent elements, such as a representative transient, frequency-dependent combustion response to pressure wave activity above the burning propellant surface, is applied to the investigation of scale effects (motor size, i.e. , grain length and internal port diameter) on influencing instability-related behaviour in a cylindrical-grain motor. The results of this investigation reveal that the motor’s size has a significant influence on transient pressure wave magnitude and structure, and on the appearance and magnitude of an associated base pressure rise.

Suggested Citation

  • David R. Greatrix, 2011. "Scale Effects on Solid Rocket Combustion Instability Behaviour," Energies, MDPI, vol. 4(1), pages 1-18, January.
    • Handle: RePEc:gam:jeners:v:4:y:2011:i:1:p:90-107:d:10889
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    Citations

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    Cited by:

    1. Lin Sun & Futing Bao & Ning Zhang & Weihua Hui & Shaozeng Wang & Nan Zhang & Heng Deng, 2016. "Thermo-Structural Response Caused by Structure Gap and Gap Design for Solid Rocket Motor Nozzles," Energies, MDPI, vol. 9(6), pages 1-21, June.
    2. David Greatrix, 2015. "Numerical Evaluation of the Use of Aluminum Particles for Enhancing Solid Rocket Motor Combustion Stability," Energies, MDPI, vol. 8(2), pages 1-21, February.

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