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Some Aspects of Time‐Temperature Superposition Principle Applied for Predicting Mechanical Properties of Solid Rocket Propellants
Author(s) -
Jeremic Radun
Publication year - 1999
Publication title -
propellants, explosives, pyrotechnics
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.56
H-Index - 65
eISSN - 1521-4087
pISSN - 0721-3115
DOI - 10.1002/(sici)1521-4087(199908)24:4<221::aid-prep221>3.0.co;2-u
Subject(s) - materials science , propellant , solid fuel rocket , composite material , physics , thermodynamics , chemistry , organic chemistry
Optimal test conditions for determining the mechanical properties of rocket propellants (temperatures and strain rates ranges) for delivering master curves were investigated. From master curves it is possible to predict the modulus, maximum stress and maximum strain in vide intervals of temperatures and strain rates, and especially the existing conditions during the ignition of rocket motor. Using the control experiments, at high strain rates, the good agreement between the results obtained from master curves was shown. The obtained results for composite rocket propellants (with carboxy‐terminated polybutadiene, CTPB, as a binder), point out the drastic decreasing of maximum strain at high strain rates and low temperatures.