Abstract
Abstract : By application of reaction rate methods to available data for 4 propellant formulations obtained over a range of temperatures, it was found that a reasonable prediction of the mechanical properties could be made, at least for the static case. This method of analysis was applied to data for the propellant formulations OGK, ARP, T-16, and X-8. Since isothermal data had been obtained at only one temperature, the analysis could not be extended to relate mechanical performance to molecular structure. Reaction rate analysis does not seem completely applicable to high rate data since for the propellants studied the process appears to be too rapid for the individual elements to respond to the loading process leading to failure. However, the time to failure is a function of the reciprocal of the absolute temperature and from this relationship a prediction of failure stress may be made. (Author)
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