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Modern energetic materials include explosives, blasting powders,
pyrotechnic m- tures and rocket propellants [1, 2]. The study of
high-temperature decomposition of condensed phases of propellants
and their components (liquid, solid and hybrid) is currently of
special importance for the development of space-system engineering
[3, 4]. To better understand the burning mechanisms (stationary,
nonstationary, - steady) of composite solid propellants and their
components, information about the macrokinetics of their
high-temperature decomposition is required [5]. To be able to
evaluate the ignition parameters and conditions of safe handling of
heat-affected explosives, one needs to know the kinetic constants
of their high-temperature - composition. The development of new
composite solid propellants characterized by high performance
characteristics (high burning rates, high thermal stability,
stability to intrachamber perturbations, and other aspects) is not
possible without quanti- tive data on the high-temperature
decomposition of composite solid propellants and their components
[6]. The same reasons have resulted in signi?cant theoretical and
practical interest in the high-temperature decomposition of
components of hybrid propellants. It is known that hybrid
propellants have not been used very widely due to the low bu- ing
(pyrolysis) rates of the polymer blocks in the combustion chambers
of hybrid rocket engines. To increase the burning rates it is
necessary to obtain information about their relationships to the
corresponding kinetic and thermophysical prop- ties of the fuels.
Modern energetic materials include explosives, blasting powders,
pyrotechnic m- tures and rocket propellants [1, 2]. The study of
high-temperature decomposition of condensed phases of propellants
and their components (liquid, solid and hybrid) is currently of
special importance for the development of space-system engineering
[3, 4]. To better understand the burning mechanisms (stationary,
nonstationary, - steady) of composite solid propellants and their
components, information about the macrokinetics of their
high-temperature decomposition is required [5]. To be able to
evaluate the ignition parameters and conditions of safe handling of
heat-affected explosives, one needs to know the kinetic constants
of their high-temperature - composition. The development of new
composite solid propellants characterized by high performance
characteristics (high burning rates, high thermal stability,
stability to intrachamber perturbations, and other aspects) is not
possible without quanti- tive data on the high-temperature
decomposition of composite solid propellants and their components
[6]. The same reasons have resulted in signi?cant theoretical and
practical interest in the high-temperature decomposition of
components of hybrid propellants. It is known that hybrid
propellants have not been used very widely due to the low bu- ing
(pyrolysis) rates of the polymer blocks in the combustion chambers
of hybrid rocket engines. To increase the burning rates it is
necessary to obtain information about their relationships to the
corresponding kinetic and thermophysical prop- ties of the fuels.
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