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.

STUDIES OF HIGH EXPLOSIVES IMPACT ON REDUCTION OF HCL IN HETEROGENEOUS SOLID ROCKET PROPELLANTS

2017 ◽  
pp. 29-45
Author(s):  
Rafał Bogusz ◽  
Paulina Magnuszewska ◽  
Bogdan Florczak
Keyword(s):  
Specific Impulse ◽  
Calorific Value ◽  
Combustion Products ◽  
Decomposition Temperature ◽  
Mechanical Stimuli ◽  
High Explosives ◽  
Combustion Heat ◽  
Rocket Propellants ◽  
Solid Rocket ◽  
Heterogeneous Solid

The paper describes an influence of high explosives: hexogene (RDX), octogene (HMX), and dinitro-diaminoethene (FOX-7) on the properties of heterogeneous solid rocket propellant (HSRP) prepared on the base of Hydroxy Terminated Polybutadiene (HTPB) in which ammonium perchlorate (AP) was partially replaced by sodium nitrate (SN). It reduced the content of HCl in combustion products. Theoretical values of thermochemical and thermodynamic properties such as isochoric combustion heat (Q), specific impulse (Isp) and contents of combustion products in motor combustion chamber and nozzle have been identified by using the ICT-Code program. The rheological properties (virtual viscosity) of the propellant slurry during curing process, the sensitivity to mechanical stimuli (impact, friction), decomposition temperature, calorific value and hardness of propellants containing explosive materials were tested by instruments and ballistic properties were investigated by laboratory rocket motor (LRM).

scholarly journals Effects of Nano-Sized Al on the Combustion Performance of Fuel Rich Solid Rocket Propellants

2016 ◽  
Vol 18 (3) ◽  
pp. 197 ◽  
Author(s):  
W.Q. Pang ◽  
F.Q. Zhao ◽  
L.T. DeLuca ◽  
C. Kappenstein ◽  
H.X. Xu ◽  
...  
Keyword(s):  
Burning Rate ◽  
Mass Fraction ◽  
Impact Sensitivity ◽  
Heat Of Combustion ◽  
Nominal Composition ◽  
Rocket Propellants ◽  
Burning Rates ◽  
Solid Rocket ◽  
Friction Sensitivity ◽  
Solid Rocket Propellants

Several industrial- and research – type fuel rich solid rocket propellants containing nano-metric aluminum metal particles, featuring the same nominal composition, were prepared and experimentally analyzed. The effects of nano-sized aluminum (nAl) on the rheological properties of metal/HTPB slurries and fuel rich solid propellant slurries were investigated. The energetic properties (heat of combustion and density) and the hazardous properties (impact sensitivity and friction sensitivity) of propellants prepared were analyzed and the properties mentioned above compared to those of a conventional aluminized (micro-Al, mAl) propellant. The strand burning rate and the associated combustion fl ame structure of propellants were also determined. The results show that nAl powder is nearly “round” or “ellipse” shaped, which is different from the tested micrometric Al used as a reference metal fuel. Two kinds of Al (nAl and mAl) powder can be dispersed in HTPB binder suffi ciently. The density of propellant decreases with increasing mass fraction of nAl powder; the measured heat of combustion, friction sensitivity, and impact sensitivity of propellants increase with increasing mass fraction of nAl powder in the formulation. The burning rates of fuel rich propellant increase with increasing pressure, and the burning rate of the propellant loaded with 20% mass fraction of nAl powder increases 77.2% at 1 MPa, the pressure exponent of propellant increase a little with increasing mass fraction of nAl powder in the explored pressure ranges.

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.

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