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).

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.

ESTIMATION OF THERMODYNAMIC AND THERMOCHEMICAL PROPERTIES OF SOLID HETEROGENEOUS ROCKET PROPELLANTS CONTAINING SCAVENGERS

2019 ◽  
Vol 150 (2) ◽  
pp. 59-70
Author(s):  
Katarzyna Gańczyk-Specjalska ◽  
Rafał Bogusz ◽  
Rafał Lewczuk ◽  
Paulina Magnuszewska
Keyword(s):  
Hydrogen Chloride ◽  
Alkaline Earth ◽  
Specific Impulse ◽  
Earth Metal ◽  
Combustion Products ◽  
Metal Salts ◽  
Alkaline Earth Metal ◽  
Oxygen Balance ◽  
Thermochemical Properties ◽  
Rocket Propellants

A new trend in development of solid heterogeneous rocket propellants (SHRP) is a reduction of emission of gases, generated during combustion of propellants, leaving a trace of white smoke behind the nozzle as a result of condensation of combustion products including above all the hydrogen chloride. This smoke is called as secondary smoke in accordance with the AGARD classification. The SHRP based on ammonium perchlorate (commonly used oxidizer) generates significant amounts of hydrogen chloride in combustion products. There are various methods to reduce the emission of secondary smokes – one of them is the ad-dition of scavengers to SHRP. Alkaline earth metal salts are used as scavengers. The estimation of thermodynamic and thermochemical properties of SHRP containing selected scavengers was carried out by using the ICT-Code software (The ICT-Thermodynamic Code). The influence of different scavengers and their amount on selected properties, e.g. oxygen balance, density, caloricity, specific impulse, and amount of hydrogen chloride in combustion products, was determined.

Facile Template Free Shape Controlled Synthesis of α-Fe2O3 Truncated Octahedral Microstructures for the Thermal Decomposition of Ammonium Perchlorate

2020 ◽  
Vol 12 ◽  
Author(s):  
Vijayasree Haridas ◽  
Sankaran Sugunan ◽  
Binitha N. Narayanan
Keyword(s):  
Electron Microscopy ◽  
Thermal Decomposition ◽  
Ammonium Perchlorate ◽  
Low Cost ◽  
Decomposition Temperature ◽  
Scanning Calorimetry ◽  
Rocket Propellants ◽  
High Resolution Tem ◽  
Template Free ◽  
Solid Rocket

Background: The combustion behaviour of the solid rocket propellants is highly dependent on the thermal decomposition characteristics of ammonium perchlorate (AP) and thus lowcost, facile and scalable preparation of the additive metal oxide based catalysts are highly desired for the AP decomposition. Objective: A template free one-step low-cost preparation of α-Fe2O3 for its use as a catalyst in the decomposition of AP. Methods: The catalyst is prepared by the simple heating of ferric chloride at 380 °C without any chemical treatment. The material is characterized by X-ray diffraction (XRD), scanning electron microscopy (SEM), transmission electron microscopy (TEM) and high-resolution TEM (HRTEM). The catalytic thermal decomposition of AP over α-Fe2O3 was measured by differential scanning calorimetry (DSC). Results: The material exhibited pure α-Fe2O3 crystalline phase. Morphological investigations revealed the uniform formation of truncated octahedral microstructures of αFe2O3. DSC analysis confirmed the two step exothermic thermal decomposition of AP with decreased decomposition temperatures with the catalytic assistance of α-Fe2O3. Conclusions: With the catalytic assistance of present low-cost and easily prepared α-Fe2O3, the decomposition temperature is decreased by 30 ºC when compared to the pure ammonium perchlorate and a high decomposition heat release of 807 Jg-1 is observed.

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 Modelling of the formulated solid rocket propellant characteristics

2021 ◽  
Vol 6 (2) ◽  
pp. 061-073
Author(s):  
Oyedeko K.F.K ◽  
Egwenu S. O.
Keyword(s):  
Mathematical Model ◽  
Combustion Temperature ◽  
Specific Impulse ◽  
Combustion Process ◽  
General Rule ◽  
Combustion Products ◽  
Potassium Nitrate ◽  
Chamber Pressure ◽  
Performance Parameters ◽  
Solid Rocket

This study is a mathematical model to obtain the characteristics performance of magnesium metal (powder) and carbon on a potassium nitrate-sucrose (KNSU) solid propellant formulation. Characterization of propellant is, as a general rule, important to determine its performance before it can be suitable for use for a rocket flight or any mission. Method of ballistic load cell evaluation was used to validate results and a mathematical model using the combustion exhaust products was solved to obtain the characteristics performance parameters of the propellant. The carbon constituent which acts as an opacifier and coolant was kept constant at 2% in order to arrest some of the heat during the combustion process and helped to lower the combustion temperature, because high combustion temperature could lead to combustion chamber rupture or failure. The effect of addition of magnesium which was optimized for 3% in the formulation contributed significantly in improving the overall performance of the propellant. The utilization of magnesium in KNSU propellant provided higher values parameters and better performance compared to when not included. This was confirmed with the model equations. The propellant combustion products equation was used to model and obtain the characteristics performance parameters. This gave propellant specific impulse (122.9s), combustion temperature (1821K), heat ratio (1.1592), molecular weight (36.89g/mole), propellant density (1912.5kg/m3) and characteristics velocity (1000m/s) result while maintaining the same chamber pressure.

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