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

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.

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).

Ignition Characteristics of a Fischer-Tropsch Synthetic Jet Fuel

2008 ◽  
Author(s):  
P. Gokulakrishnan ◽  
M. S. Klassen ◽  
R. J. Roby
Keyword(s):  
Kinetic Model ◽  
Ignition Delay ◽  
Flow Reactor ◽  
Kinetic Mechanism ◽  
Jet Fuel ◽  
Synthetic Jet ◽  
Jet Fuels ◽  
Ignition Delay Times ◽  
Delay Times ◽  
Ignition Characteristics

Ignition delay times of a “real” synthetic jet fuel (S8) were measured using an atmospheric pressure flow reactor facility. Experiments were performed between 900 K and 1200 K at equivalence ratios from 0.5 to 1.5. Ignition delay time measurements were also performed with JP8 fuel for comparison. Liquid fuel was prevaporized to gaseous form in a preheated nitrogen environment before mixing with air in the premixing section, located at the entrance to the test section of the flow reactor. The experimental data show shorter ignition delay times for S8 fuel than for JP8 due to the absence of aromatic components in S8 fuel. However, the ignition delay time measurements indicate higher overall activation energy for S8 fuel than for JP8. A detailed surrogate kinetic model for S8 was developed by validating against the ignition delay times obtained in the present work. The chemical composition of S8 used in the experiments consisted of 99.7 vol% paraffins of which approximately 80 vol% was iso-paraffins and 20% n-paraffins. The detailed kinetic mechanism developed in the current work included n-decane and iso-octane as the surrogate components to model ignition characteristics of synthetic jet fuels. The detailed surrogate kinetic model has approximately 700 species and 2000 reactions. This kinetic mechanism represents a five-component surrogate mixture to model generic kerosene-type jets fuels, namely, n-decane (for n-paraffins), iso-octane (for iso-paraffins), n-propylcyclohexane (for naphthenes), n-propylbenzene (for aromatics) and decene (for olefins). The sensitivity of iso-paraffins on jet fuel ignition delay times was investigated using the detailed kinetic model. The amount of iso-paraffins present in the jet fuel has little effect on the ignition delay times in the high temperature oxidation regime. However, the presence of iso-paraffins in synthetic jet fuels can increase the ignition delay times by two orders of magnitude in the negative temperature (NTC) region between 700 K and 900 K, typical gas turbine conditions. This feature can have a favorable impact on preventing flashback caused by the premature autoignition of liquid fuels in lean premixed prevaporized (LPP) combustion systems.

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