The decomposition preceding autoignition of an ammonium-perchlorate-based composite propellant was experimentally investigated. Autoignition temperature is measured for a selected heating rate. At that same heating rate, differential scanning calorimetry, thermogravimetric analysis, Fourier transform infrared spectroscopy, and hot-stage microscopy are employed to study the propellant behavior leading to reaction. These experiments are conducted on both cured composite propellant and individual ingredients, including neat ammonium perchlorate and a cured binder. For a heating rate of , it is determined using thermogravimetric analysis/Fourier transform infrared that ammonium perchlorate and the binder begin to react together near 150°C, whereas differential scanning calorimetry shows initial exothermic behavior after the orthorhombic-to-cubic phase transition near 240°C. This disparity is discussed and further investigated using larger-scale cubes of propellant heated in ovens at the same heating rate of . It is found that the larger-scale testing is consistent with the findings of the thermogravimetric analysis/Fourier transform infrared. Changes in the gas phase composition are observed when ammonium perchlorate, the binder, and propellant are slowly heated. Implications of these experimental observations are discussed.
Experimental Investigation of the Decomposition Preceding Cookoff in a Composite Propellant
Journal of Propulsion and Power ; 30 , 6 ; 1667-1674
2014-11-01
Article (Journal)
Electronic Resource
English
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