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Thermal Decomposition of BAMO/HMX Propellants

✍ Scribed by Yoshio Oyumi; Kiyotaka Inokami; Kazuhiro Yamazaki; Koki Matsumoto

Publisher
John Wiley and Sons
Year
1993
Tongue
English
Weight
552 KB
Volume
18
Category
Article
ISSN
0721-3115

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✦ Synopsis

Abstract

Thermal decomposition of BAMO [bis(azidomethyl)oxetane/tetrahydrofuran copolymer]/HMX composite propellants was studied by isothermal TGA (thermogravimetric analysis) and DSC (differential scanning calorimetry) in helium atmosphere, which was showing overall two steps first‐order kinetics. The effects of cross‐link ratio on the accelerated aging of the BAMO/HMX propellants were also measured with infrared spectroscopy and gas chromatography. The accelerated aging was conducted at 347 K for several weeks. BAMO/HMX propellants for a very low cross‐link ratio made the cavity between HMX and BAMO binder by N~2~, CO~2~, and H~2~O evolutions during accelerated aging. An exotherm, generated by the decomposition of azide binder, initiated and accelerated the thermal decomposition of HMX. The burning rate of BAMO/HMX propellant was larger than those of BAMO binder and HMX, respectively. However, the propellant could not maintain the combustion at low pressure, at which its burning rate was equal to that of BAMO binder.

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