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Портал Begell Электронная Бибилиотека e-Книги Журналы Справочники и Сборники статей Коллекции
International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.149 SNIP: 0.16 CiteScore™: 0.29

ISSN Печать: 2150-766X
ISSN Онлайн: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.v6.i4.70
pages 511-527

CHARACTERIZATION OF RUBBERY COMPOSITE PROPELLANT AND ITS COMPATIBILITY WITH THE COMPONENTS OF THE 70-mm. ROCKET ENGINES

Enrique F. Quinones
Departamento de Quimica, Academia Politécnica Militar, Valenzuela Llanos, 623, La Reina, Santiago
Rodrigo F. A. Guerra
Departamento de Investigaciones, Instituto de Investigaciones y Control del Ejército de Chile, Pedro Montt 2050, Santiago

Краткое описание

The objectives of this work are to characterize the composite solid propellants developed by FAMAE and to study the chemical compatibility between the components of a specific rocket engine. The Arrhenius kinetic constants for the thermally unstable materials were taken from ASTM E-698. STANAG 4147 was used in the determination of compatibilities of explosives to each other and to other materials, and in the qualitative analysis of the energy curves. This method was proposed by METTLER Toledo company. Differential Scanning Calorimetry (DSC) was utilized for thermal analysis. Experiments were conducted to characterize the rubbery composite propellants by determining their activation energies, frequency factors, the pre-exponential constants of reaction, their average lifetimes, and their percentages of conversion at given temperatures. Also, their caloric capacities were determined as a function of temperature. Compatibility tests were also performed, for different components used in the rocket engine. Aging of the rubbery composite propellant material was studied by artificial heating to 65°C for periods of 30, 60, and 90 days. The results are given in the paper.


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