Micro-fibre based Porous Composite Propellants with High Regression Rates

2017 ◽  
Vol 67 (3) ◽  
pp. 240
Author(s):  
R.A. Chandru ◽  
S. Chappa ◽  
R.S. Bharath ◽  
C. Oommen ◽  
B.N. Raghunandan
Keyword(s):  
High Energy ◽  
Space Propulsion ◽  
Micro Scale ◽  
Rocket Propellants ◽  
Burning Rates ◽  
Solid Explosives ◽  
Launch Systems ◽  
Solid Rocket ◽  
Solid Rocket Propellants ◽  
Practical Implications

Harnessing energy at micro-scale from high energy sources has gained significance in recent times for space propulsion and other applications. Conventional solid rocket propellants have advantages in terms of being efficient, compact and safe to handle, though with much lower regression rates as compared to solid explosives. An approach to high regression rates in composite propellants is demonstrated in the present work by the enhancement of fuel-oxidiser interaction, and by the incorporation of micro-scale porosity into the propellant grain. The porous polystyrene-ammonium perchlorate grain designed in this work, based on electrospun micro-fibres and aqueous impregnation, exhibits burning rates more than 25 times as compared to the non-porous grain. Such high regression rates using insensitive propellant compositions have practical implications in the development of micro-thrusters, and in gas generating devices such as MAV launch systems and turbine starters. Detailed preparatory procedure, characterisation techniques, and flame regression studies are included in this paper.

INVESTIGATING EXPLOSIVE SENSITIVITY TO ELECTROSTATIC DISCHARGE ACCORDING TO NATO STANDARDIZATION DOCUMENTS

2016 ◽  
pp. 39-60
Author(s):  
Maciej MISZCZAK, ◽  
Cezary Kwiecień ◽  
Sławomir Gryka
Keyword(s):  
Large Scale ◽  
Small Scale ◽  
Rocket Propellants ◽  
Smokeless Powders ◽  
Solid Explosives ◽  
Solid Rocket ◽  
Susceptibility Tests ◽  
Explosive Sensitivity ◽  
Solid Rocket Propellants ◽  
Large Scale Tests

Some small scale methods for testing the sensitivity against ESD (Electro Static Discharge) of solid explosives like primary explosives, booster explosives, high explosives, gun and rocket propellants (smokeless powders and solid rocket propellants) and pyrotechnic compositions are overviewed in the paper from the point of NATO standardisation documentation that includes Standard Agreement (STANAG) 4490 [1], Allied Ordnance Publication AOP-7 [2] and STANAG 4170 [3]. The overview is supplemented with analyses and assessments of methods and received results. ESD sensitivity tests of explosives in small scale have not been unified yet in NATO standardization documentation in contradiction to NATO large scale tests. Such unification would be beneficial as it could lead to a greater reliability of results of explosive ESD susceptibility tests performed e.g. in the frame of interlaboratory tests.

Tailoring burning rates using reactive wires in composite solid rocket propellants

2017 ◽  
Vol 36 (2) ◽  
pp. 2283-2290 ◽  
Author(s):  
Sarah Isert ◽  
Colin D. Lane ◽  
I. Emre Gunduz ◽  
Steven F. Son
Keyword(s):  
Rocket Propellants ◽  
Burning Rates ◽  
Solid Rocket ◽  
Solid Rocket Propellants ◽  
Composite Solid

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.

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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