Determination of glass transition activation energy for homogeneous solid rocket propellants

The paper presents results of thermal decomposition analysis of selected solid rocket propellants. Homogeneous propellant PAC and heterogeneous propellant H2 were subjected to simultaneous thermal analysis with the use of NETZSCH STA 2500 Regulus device with five heating rates of 2.5, 5, 7.5, 10 and 15 K/min. The method combines TG, DTG and DTA analytical techniques in a single measurement. The aim of the conducted experiments was to study thermal decomposition of these energetic materials as well as to determine activation energy of the decomposition process and the preconditioning factor from the TG curves. The tested materials properties and chemical composition along with a brief description of the experimental procedure are described. The inverse procedure of calculating the activation energy, based on the Ozawa-Flynn-Wall model is described. Finally, the results of thermal decomposition of two tested solid rocket propellants are presented along with maximum decomposition rates and percentage of mass loss.

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An analysis of the mechanical properties of HTPB-propellants using DMA

Materiały Wysokoenergetyczne / High Energy Materials ◽

10.22211/matwys/0192 ◽

2020 ◽

pp. 81-91

Author(s):

Katarzyna Gańczyk-Specjalska ◽

Paulina Magnuszewska

Keyword(s):

Mechanical Properties ◽

Glass Transition ◽

Transition Temperature ◽

Mechanical Analysis ◽

Thermomechanical Properties ◽

Dynamic Force ◽

Rocket Propellants ◽

Hard Segments ◽

Solid Rocket ◽

Solid Rocket Propellants

The paper presents the thermomechanical properties of solid rocket propellants containing hydroxyl-terminated polybutadiene. Dynamic mechanical analysis (DMA) was used in analysing the mechanical properties of propellant for two different sample geometries (cuboid and cylindrical). Nonisothermal and isothermal analyses were carried out in two holders: dual-cantilever and compression. The glass transition temperature of soft and hard segments in the propellants, the effect of dynamic force on sample strain, the creep-relaxation process (based on which parameters in the Burgers model were calculated) were determined based on the results of the analysis.

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HIGH BURNING RATE SOLID ROCKET PROPELLANTS

International Journal of Energetic Materials and Chemical Propulsion ◽

10.1615/intjenergeticmaterialschemprop.v4.i1-6.610 ◽

1997 ◽

Vol 4 (1-6) ◽

pp. 646-660 ◽

Cited By ~ 1

Author(s):

G. Doriath

Keyword(s):

Burning Rate ◽

Rocket Propellants ◽

Solid Rocket ◽

Solid Rocket Propellants

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Synthesis of HTPB using a semi-batch method

Materiały Wysokoenergetyczne / High Energy Materials ◽

10.22211/matwys/0115e ◽

2020 ◽

pp. 192-202

Author(s):

Michał Chmielarek ◽

Wincenty Skupiński ◽

Zdzisław Wieczorek

Keyword(s):

Mechanical Properties ◽

Hydrogen Peroxide ◽

Synthesis Method ◽

Batch Method ◽

Synthesis Conditions ◽

Rocket Propellants ◽

Wide Range ◽

Military Applications ◽

Solid Rocket ◽

Solid Rocket Propellants

Hydroxyl-terminated polybutadiene is widely used in industry for both civil and military applications. In munitions, HTPB is mostly used as a binder for heterogenic rocket propellants and as a component of plastic bonded explosives, as well as a phlegmatizer in explosives sensitive to friction and impact. The wide range of HTPB applications results from the good mechanical properties of HTPB-based polyurethanes, in particular at temperatures down to –40 °C. A synthesis method for HTPB, different from the commonly used semi-batch and continuous methods, is presented. The effect of parameters including reaction temperature, 1,3-butadiene pressure and hydrogen peroxide concentration on the properties of the obtained polymer is determined. The synthesis conditions enabling new HTPB species to be obtained, which meet the requirements for binders used in solid rocket propellants, are specified.

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