Effect of Spherical Fragments with Different Ballistic Behavior on Propellant charge Reaction Characteristics Glysidylazidepolymer/RDX/Triethyleneglycoldinitrate
X. Wang, Y.-Q. Wu
State Key Laboratory of Explosion Science and Safety Protection, Beijing Institute of Technology, Beijing, China
Keywords: high-energy propellant, fragmentation impact, delayed reaction, ballistic behavior, ballistic limits
Abstract
The question of how solid rocket propellants react to fragment impacts remains relevant. Identifying potential mechanisms for propellant propellant reaction to fragment damage is crucial for assessing the safety of solid rocket motors and developing high-energy, low-sensitivity propellants. In this study, a fragment impact experiment on a propellant propellant consisting of glycidyl azide polymer, hexogen, and triethylene glycol dinitrate (GRT) was conducted using a 14.5-mm ballistic gun and a high-speed camera to obtain images of the propellant reaction time history under various ballistic behaviors. Based on the obtained images and measured ballistic data, the relationship between propellant reaction characteristics, the primary reaction mechanisms, and two ballistic limits was analyzed. The results of a 10.0 mm diameter tungsten ball impact on a GRT charge contained in a 3 mm thick cylindrical steel shell show that the threshold reaction velocity corresponds to the ballistic limit of fragment penetration into the shell. Below this ballistic limit, no propellant reaction occurs. In the case of a significant reaction delay caused by the ignition of RDX crystal hot spots rather than ammonium perchlorate particles, the propellant reaction upon complete penetration is combustion. Only when a large number of ammonium perchlorate particles and RDX crystals simultaneously ignite hot spots, and the fragment's initial velocity exceeds the charge's ballistic limit by 2.2 times, can the charge undergo reactions more intense than combustion.
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