Study on heterogeneous solid rocket propellants based on hydroxy-terminated polybutadiene rubber Badanie heterogenicznych stałych paliw rakietowych na bazie syntetycznego kauczuku butadienowego z grupami hydroksylowymi

2016 ◽  
Vol 1 (12) ◽  
pp. 66-69
Author(s):  
Rafał Bogusz
Keyword(s):  
Rocket Propellants ◽  
Polybutadiene Rubber ◽  
Solid Rocket ◽  
Solid Rocket Propellants ◽  
Heterogeneous Solid

STUDIES OF THE INFLUENCE OF ENERGETIC ADDITIVES ON SELECTED PROPERTIES OF HETEROGENEOUS SOLID ROCKET PROPELLANT WITH LOW CONTENT OF HCL IN COMBUSTION PRODUCTS

2018 ◽  
Vol 144 (4) ◽  
pp. 15-30
Author(s):  
Paulina MAGNUSZEWSKA ◽  
Rafał Bogusz ◽  
Bogdan Florczak
Keyword(s):  
Sodium Nitrate ◽  
Specific Impulse ◽  
Combustion Products ◽  
Heat Of Combustion ◽  
Mechanical Stimuli ◽  
Rocket Propellants ◽  
Ballistic Properties ◽  
Solid Rocket ◽  
Solid Rocket Propellants ◽  
Heterogeneous Solid

The paper presents influence of additives like aluminium, magnesium, AMD (aluminium-magnesium dust) and boron on selected properties of heterogeneous solid rocket propellants (HSRP) based on HTPB in which ammonium chlorate was partly replaced by sodium nitrate. The presence of sodium nitrate reduces the content of hydrogen chloride (HCl) in combustion products. Theoretical values of thermochemical and thermodynamical properties like isochoric heat of combustion (Q), specific impulse (Isp) and combustion products in motor chamber and nozzle were identified by ICT-Code program. A laboratory rocket motor (LRM) was used to examine ballistic properties for prepared samples of propellants. Their temperature of decomposition, heat of combustion and hardness were tested both with sensitivity to mechanical stimuli (impact, friction) and rheological properties at curing.

Thermo-Mechanical Analysis of Homo- and Heterogeneous Solid Rocket Propellants

2015 ◽  
Vol 1126 ◽  
pp. 194-200 ◽  
Author(s):  
Marcin Cegła ◽  
Janusz Zmywaczyk ◽  
Piotr Koniorczyk ◽  
Jacek Borkowski ◽  
Kamil Prusak
Keyword(s):  
Physical Properties ◽  
Loss Modulus ◽  
Mechanical Analysis ◽  
Operating Conditions ◽  
Temperature Range ◽  
Rocket Propellants ◽  
Solid Rocket ◽  
Solid Rocket Propellants ◽  
Thermo Physical Properties ◽  
Heterogeneous Solid

The paper analyses results of experimental research of homogeneous and heterogeneous solid rocket propellants. The homogeneous sample PAC with density 1.58 g/cm3 and heterogeneous sample H2 with density 1.77 g/cm3 were both subjected to complex thermo-mechanical analysis. The thermo-physical properties of both samples were determined using KD2 Pro apparatus made by Decagon Devices, Inc. (USA). The temperature characteristics of thermal conductivity k (T), thermal diffusivity D(T), and volumetric heat capacity C(T) were measured within the temperature range from-200 C to +800 C. Mechanical properties such as storage modulus (E’), loss modulus (E’’) and tan (delta) were measured using Netzsch DMA 242C analyser within temperature range from-1200 C to +800 C at heating rate of 2K/min. The rectangular test samples were subjected to the dual cantilever mode with frequency f = 1Hz recommended by the NATO 4540 standard. Special attention was devoted to determining the glass transition temperature and softening temperature of the propellants. The temperature values obtained during DMA experiments supported by thermo-physical properties are essential for safe usage of solid rocket propellants under operating conditions and they may be applied in numerical modeling of temperature and thermal stress distributions of such materials.

scholarly journals Synthesis of HTPB using a semi-batch method

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.

Experimental and theoretical burning of solid rocket propellants near the pressure deflagration limit

1985 ◽  
Vol 12 (5) ◽  
pp. 351-360 ◽  
Author(s):  
Claudio Bruno ◽  
Giulio Riva ◽  
Claudio Zanotti ◽  
Roberto Dondè ◽  
Carlo Grimaldi ◽  
...  
Keyword(s):  
Rocket Propellants ◽  
Solid Rocket ◽  
Solid Rocket Propellants
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