الفهرس 
Propellant ChemistryOnly 14 pages are availabe for public view
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Abstract
The influence of different burning rate modifiers (catalysts) on the double base rocket
propellants was studied. HPLC, GC and AAS were used to investigate and check the
components of the propellant samples. Able heat test, Bergman & Junk test, methyl violet test,
Lenze & Pleuss test, explosion temperature and calorimetric value were used to study the effect
of these modifiers on thermal stability of these propellants. Mechanical properties (maximum
stress, strain at maximum stress, young’s modulus…etc) which very important for good
functioning of the propellants during their uses and storage were measured by compression test
at two different temperatures (50 and 25°C). The effect of the burning rate modifiers on the
thermal decomposition of these propellants was studied by TGA, DSC and DTA. The kinetic
parameters for this decomposition were calculated by Ozawa and Kissinger methods.
Catalysed propellants decomposed at lower temperatures than the control. Rate constants were
higher and energy of activation was lower for catalysed propellants. Results obtained from
TGA, DSC and DTA suggest that the investigated modifiers led to some improvement in
ballistic performance characteristics of these propellants. The ballistic performance
characteristics of the double base propellants were measured at two different temperatures (+50
and -20°C) by Teledyne Taber bonded strain gage pressure transducer (stand test). Results
obtained from this test showed that the used burning rate modifiers impart some enhancement
in these characteristics through stable combustion and formation of plateau region at low
pressure