Abstract

Nanometer (nano) ammonium perchlorate (AP) and ammonium nitrate (AN) were prepared with 2D network structures by the ultra-low temperature spray method. Scanning electron microscopy (SEM), X-ray diffractometry (XRD), differential scanning calorimetry (DSC) and thermogravimetric analysis/infrared spectrometry (TG-IR) were employed to probe the micron structure, crystal phase, and thermal decomposition of nano AP and nano AN. SEM images revealed that the sizes of nano AP and AN were in the nanometer scale (<100 nm) in one dimension. XRD patterns showed that the crystal phases of nano AP and AN were in accordance with those of raw AP and raw AN, respectively. DSC traces indicated that the thermal decomposition process of AP depended on its particle size, while the thermolysis of AN was independent of the particle size of AN. TG-IR analyses illustrated that the decomposition products of nano AP were NO2, N2O, HCl and H2O, with a small amount of NOCl, and the main decomposition products of nano AN were N2O and H2O, with a small amount of NH3. The results of mechanical sensitivity tests indicated that nano AP was more sensitive than raw AP and both nano AN and raw AN were very insensitive to impact and friction stimuli.

Highlights

  • Ammonium perchlorate (AP) and ammonium nitrate (AN) are the most commonly used oxidizers applied in solid propellants [1,2,3]

  • Researchers have found that the performance of ammonium perchlorate (AP) and AN is a function of their particle sizes

  • Ammonium perchlorate (AP) and ammonium nitrate (AN) were purchased from Tianjin Guangfu Chemical Co., Ltd. (Tianjin, China) and liquid nitrogen was purchased from Taiyuan Taineng Gas Co., Ltd. (Taiyuan, China)

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Summary

Introduction

Ammonium perchlorate (AP) and ammonium nitrate (AN) are the most commonly used oxidizers applied in solid propellants [1,2,3] In addition to their use in propellants, AP and AN are employed as oxygen-enriched ingredients in explosives and pyrotechnics [4,5,6]. A decrease in particle size of AN is beneficial as it decreases the combustion pressure exponent of AN-based propellants [9]. The mechanism concerning this is still obscure, and is not the theme of this work

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