scholarly journals Effect of Metal Nanopowders on the Performance of Solid Rocket Propellants: A Review

Nanomaterials ◽  
2021 ◽  
Vol 11 (10) ◽  
pp. 2749
Author(s):  
Weiqiang Pang ◽  
Yang Li ◽  
Luigi T. DeLuca ◽  
Daolun Liang ◽  
Zhao Qin ◽  
...  
Keyword(s):  
Burning Rate ◽  
Solid Rocket Motors ◽  
Rocket Motors ◽  
Rocket Propellants ◽  
Different Types ◽  
Composite Fuel ◽  
Solid Rocket ◽  
Double Base ◽  
Friction Sensitivity ◽  
Solid Rocket Propellants

The effects of different types of nano-sized metal particles, such as aluminum (nAl), zirconium (nZr), titanium (nTi), and nickel (nNi), on the properties of a variety of solid rocket propellants (composite, fuel-rich, and composite modified double base (CMDB)) were analyzed and compared with those of propellants loaded with micro-sized Al (mAl) powder. Emphasis was placed on the investigation of burning rate, pressure exponent (n), and hazardous properties, which control whether a propellant can be adopted in solid rocket motors. It was found that nano-sized additives can affect the combustion behavior and increase the burning rate of propellants. Compared with the corresponding micro-sized ones, the nano-sized particles promote higher impact sensitivity and friction sensitivity. In this paper, 101 references are enclosed.

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 PERHITUNGAN DAN PERANCANGAN IGNITER BERBASIS KALKULASI PROPULSI ROKET (Studi Kasus Roket RX-320)

2012 ◽  
Vol 9 (2) ◽  
Author(s):  
Ganda Samosir
Keyword(s):  
Extreme Environment ◽  
Tube Length ◽  
Internal Factor ◽  
Internal Factors ◽  
Solid Rocket Motors ◽  
Rocket Motors ◽  
Main Charge ◽  
Composite Fuel ◽  
Solid Rocket ◽  
Outside Diameter

The solid rocket motors, like all the LAPAN’s rocket, has been using the composite fuel of Hydroxyl Terminated Poly Butadiene (HTPB) type which is not easy to self-igniting. The quite extreme environment conditions are needed in order to ignite this non-hypergolic solid fuel, such as the ambiance pressure and temperature must be about 40 bar and 280°C respectively. The aforementioned conditions must be well given by the prime igniter designed or commonly known as igniter. The performance of an igniter could be very influenced by 2 (two) massive variables; first one is the internal factor, such as: squib ingredient, filament material, primer composition, igniter main charge, and the second one is external factor, such as: propellant’s type, dimension and the configuration of the rocket’s combustion chamber. In other word, chosen the proper rocket’s igniter are depending on the type and its mission.The propulsion calculation applied in this paper to design the igniter of the rocket RX-320, gives some major variables, i.e.: the biggest tube length; = 357 mm, its outside diameter; = 51 mm, total orifices and its diameter are 165 and 4 mm respectively. iL lcφ Keywords: Extreme conditions, Internal factors, External factors.

Short-Action Solid Rocket Motors with Double-Base Propellants

1996 ◽  
Vol 21 (3) ◽  
pp. 118-126 ◽  
Author(s):  
H. Kentgens ◽  
H. P. Mackowiak ◽  
R. Schöffl
Keyword(s):  
Solid Rocket Motors ◽  
Rocket Motors ◽  
Solid Rocket ◽  
Double Base
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