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<p>The present research proposes a simplified discrete and continuum model for calculating erosive burn rates that considers elements such as mass flux, mass burning rate, and propellant temperature sensitivity in relation to <i>L</i>/<i>D</i> (length-to-diameter ratio), combustion pressure, and motor scale. This model is specifically designed to evaluate the performance of highly aluminized composite propellant internal ballistic solid rocket motors. By utilizing a minimum distance and time step approach, the internal chamber pressure over time can be predicted by measuring the propellant's local regression. These methods can handle intricate geometric designs in a manner that is comparable to existing techniques based on the progression of analytical geometry. The accuracy of the method was confirmed with published static experimental test outcomes. The parameters for the correlative equation were deduced from the test results of cylindrical motor experiments. The calculation's output includes the pressure–time (<i>p</i>–<i>t</i>) curve and the propellant burnout time, both of which have an accuracy of over 98% and 96.5%, respectively.</p>

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A development of simplified discrete and continuum erosive grain burn back model for composite solid propellant

  • 期刊论文

  • 发表日期：

    2025年11月22日

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  • Zulfam Adnan,
  • Nurul Musfirah Mazlan

摘要

The present research proposes a simplified discrete and continuum model for calculating erosive burn rates that considers elements such as mass flux, mass burning rate, and propellant temperature sensitivity in relation to L/D (length-to-diameter ratio), combustion pressure, and motor scale. This model is specifically designed to evaluate the performance of highly aluminized composite propellant internal ballistic solid rocket motors. By utilizing a minimum distance and time step approach, the internal chamber pressure over time can be predicted by measuring the propellant's local regression. These methods can handle intricate geometric designs in a manner that is comparable to existing techniques based on the progression of analytical geometry. The accuracy of the method was confirmed with published static experimental test outcomes. The parameters for the correlative equation were deduced from the test results of cylindrical motor experiments. The calculation's output includes the pressure–time (p–t) curve and the propellant burnout time, both of which have an accuracy of over 98% and 96.5%, respectively.