Propellant stretching in combustion leads to an essential increase (up to 50% and more) in burn rate. The analysis of existing representations about the influence of stretch deformations on propellant burn rate is carried out. It is shown, that for composite solid propellants the basic mechanism of increase in the burn rate under stretch conditions is detachment of the binder from particles of oxidizers, formation of additional burning surface, and change of structure of a burnt zone.
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