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 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.

Burning Rate and Ignition Delay Times of AP/HTPB-Based Solid Rocket Propellants Containing Graphene

2016 ◽  
Author(s):  
Catherine A. Dillier ◽  
Andrew R. Demko ◽  
Thomas Sammet ◽  
Kevin Grossman ◽  
Sudipta Seal ◽  
...  
Keyword(s):  
Burning Rate ◽  
Ignition Delay ◽  
Rocket Propellants ◽  
Ignition Delay Times ◽  
Delay Times ◽  
Solid Rocket ◽  
Solid Rocket Propellants

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.

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

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.

Inorganic Nanoparticles for Gun Propellants

2005 ◽  
Vol 896 ◽  
Author(s):  
Barbara Baschung
Keyword(s):  
Burning Rate ◽  
Theoretical Models ◽  
Inorganic Nanoparticles ◽  
Solid Propellants ◽  
Rocket Propellants ◽  
Burning Behavior ◽  
High Pressure Range ◽  
Solid Rocket ◽  
Gun Propellants ◽  
Solid Rocket Propellants

AbstractThe possibility of increasing the burning rate of solid rocket propellants by adding nanoparticles of aluminum into the propellant formulation has already been well-known for many years. This paper deals with micron- and nanoparticles embedded in gun propellants. The objective is to increase the gun performance. The burning behavior of solid propellants based on ultra-fine aluminum powder was investigated in a high pressure range which is reached in a gun tube. The burning rate of such a propellant is much higher (nearly two orders of magnitude) than for the similar propellant with the micron-sized aluminum. This paper presents a review of burning experiments with propellants based on the nano- and micron-sized particles of aluminum. The burning behavior of NENA solid propellants based on nano-scale aluminum was studied as a function of the portion of aluminum in the mixture. The burning of these propellants follows Vieille's burning law. The burning rate increases by augmenting the aluminum portion in the propellant. Theoretical models are reviewed in order to understand these experimental burning results. An advanced propellant coated with appropriate nanoparticles is presented in the conclusion. With this propellant and a special ignition by microwaves it should be possible to ignite solid propellants by using high loading densities (> 1.2 g/cm3).

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