Hot fragments generated during the impact of shaped charge jets may penetrate the cartridge casing and induce propellant ignition. To simulate hot fragment conductive ignition, a comprehensive model has been formulated and validated by conducting detailed experiments. The model has been based on an assumed decomposition behavior of the various binder ingredients contained in the nitramine-composite propellant. The objective of this work is to describe the effects of incorporating an improved knowledge about the thermal decomposition behavior of these binder ingredients into the existing model. Rapid thermolysis experiments have revealed that essentially no decomposition occurs of the major ingredients CAB and ATEC over the range of temperatures from 450 to 600 K. The use of these findings has enabled an improved predictive capability of the propellant's rate of gasification, as well as the of the location of the Go/No-Go ignition boundary for both partially and fully confined enclosures. It should also be noted that the use of different reactions among CH2O and NO2 for describing the ignition event has shown only a limited impact on the location of Go/No-Go ignition boundary.
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