International Journal of Aerospace System Engineering

The Society for Aerospace System Engineering (항공우주시스템공학회)
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Nonlinear Combustion Instability Analysis of Solid Rocket Motor Based on Experimental Data

  • Wei, Shaojuan (Science and Technology on Combustion, Internal Flow and Thermal-structure Laboratory, Northwestern Polytechnical University) ;
  • Liu, Peijin (Science and Technology on Combustion, Internal Flow and Thermal-structure Laboratory, Northwestern Polytechnical University) ;
  • Jin, Bingning (Science and Technology on Combustion, Internal Flow and Thermal-structure Laboratory, Northwestern Polytechnical University)
  • Received : 2015.09.04
  • Accepted : 2015.10.11
  • Published : 2015.12.30
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Abstract

Combustion instability in solid rocket motors is a long-term open problem since the first rockets were used. Based on the numerous previous studies, it is known that the limit cycle amplitude is one of the key characteristics of the nonlinear combustion instability in solid rocket motors. Flandro's extended energy balance corollary, aims to predict the limit cycle amplitude of complex, nonlinear pressure oscillations for rockets or air-breathing engines, and leads to a precise assessment of nonlinear combustion instability in solid rocket motors. However, based on the comparison with experimental data, it is revealed that the Flandro's method cannot accurately describe such a complex oscillatory pressure. Thus in this work we make modifications of the nonlinear term in the nonlinear wave equations which represents the interaction of different modes. Through this modified method, a numerical simulation of the cylindrical solid rocket has been carried out, and the simulated result consists well with the experimental data. It means that the added coefficient makes the nonlinear wave growth equations describe the experimental data better.

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References

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