IGNITION AND COMBUSTION OF SOLID PROPELLANTS

1962 ◽  
Author(s):  
Rex C. Mitchell ◽  
John A. Keller ◽  
Alva D. Baer ◽  
Norman W. Ryan
Keyword(s):  
Solid Propellants ◽  
Ignition And Combustion

Modeling of Ignition and Combustion of Boron-Containing Solid Propellants

2021 ◽  
Vol 57 (3) ◽  
pp. 308-313
Author(s):  
V. A. Arkhipov ◽  
S. A. Basalaev ◽  
V. T. Kuznetsov ◽  
V. A. Poryazov ◽  
A. V. Fedorychev
Keyword(s):  
Solid Propellants ◽  
Ignition And Combustion

Potential Usage of Energetic Nano-sized Powders for Combustion and Rocket Propulsion

2003 ◽  
Vol 800 ◽  
Author(s):  
Kenneth K. Kuo ◽  
Grant A. Risha ◽  
Brian J. Evans ◽  
Eric Boyer
Keyword(s):  
Burning Rate ◽  
Energy Release ◽  
Solid Propellant ◽  
Nano Particles ◽  
Solid Fuels ◽  
Solid Propellants ◽  
Regression Rate ◽  
Combustion Behavior ◽  
Boron Particles ◽  
Ignition And Combustion

ABSTRACTNano-sized energetic metals and boron particles (with dimensions less than 100 nanometers) possess desirable combustion characteristics such as high heats of combustion and fast energy release rates. Because of their capability to enhance performance, various metals have been introduced in solid propellant formulations, gel propellants, and solid fuels. There are many advantages of incorporating nano-sized materials into fuels and propellants, such as: 1) shortened ignition delay; 2) shortened burn times, resulting in more complete combustion in volume-limited propulsion systems; 3) enhanced heat-transfer rates from higher specific surface area; 4) greater flexibility in designing new energetic fuel/propellants with desirable physical properties; 5) nano-particles can act as a gelling agent to replace inert or low-energy gellants; 6) nano-sized particles can also be dispersed into high-temperature zone for direct oxidation reaction and rapid energy release, and 7) enhanced propulsive performance with increased density impulse. In view of these advantages, numerous techniques have been developed for synthesizing nano-particles of different sizes and shapes. To reduce any possible hazards associated with the handling of nano-sized particles as well as unwanted particle oxidation, various passivation procedures have been developed. Some of these coating materials could enhance the ignition and combustion behavior, others could increase the compatibility of the particles with the surrounding material. Many researchers have been actively engaged in the characterization of the ignition and combustion behavior of nano-sized particles as well as the assessment of performance enhancement of propellants and fuels containing energetic nano-particles. For example, solid fuels could contain a significant percentage of nano-sized particles to increase the mass-burning rate in hybrid rocket motors, the regression rate of solid propellants can be increased by several times when nano-sized particles are incorporated into the formulation. Specifically, hybrid motor data showed that the addition of 13% energetic aluminum powders can increase the linear regression rate of solid HTPB-based fuel by 123% in comparison to the non-aluminized HTPB fuel at a moderate gaseous oxidizer mass flow rate. Strand burner studies of two identical solid propellant formulations (one with 18% regular aluminum powder and the other with 9% aluminum replaced by Alex® powder) showed that nano-sized particles can increase the linear burning rate of solid propellants by 100%. In addition to solid fuels and propellants, spray combustion of bipropellants has been conducted using gel propellants impregnated with nano-sized boron particles as the fuel in a rocket engine. High combustion efficiencies were obtained from burning nano-sized boron particles contained in a non-toxic liquid-fuel spray. Materials characterization such as chemical analyses to determine the active aluminum content, density measurements, and imaging using an electron microscope have been performed on both neat nano-sized particles and mixtures containing the energetic materials. In general, using energetic nano-sized particles as a new design parameter, propulsion performance of future propellants and fuels can be greatly enhanced.

Heterogeneous reactions in ignition and combustion of solid propellants

AIAA Journal ◽  
1964 ◽  
Vol 2 (1) ◽  
pp. 179-180 ◽  
Author(s):  
RALPH ANDERSON ◽  
ROBERT S. BROWN ◽  
LARRY J. SHANNON
Keyword(s):  
Heterogeneous Reactions ◽  
Solid Propellants ◽  
Ignition And Combustion

scholarly journals Ignition and combustion of high-energy materials containing aluminum, boron and aluminum diboride

2018 ◽  
Vol 194 ◽  
pp. 01055
Author(s):  
Alexander Korotkikh ◽  
Ivan Sorokin ◽  
Ekaterina Selikhova
Keyword(s):  
Burning Rate ◽  
Ignition Delay ◽  
Delay Time ◽  
Solid Propellant ◽  
Ignition Delay Time ◽  
High Energy ◽  
Solid Propellants ◽  
Amorphous Boron ◽  
Aluminum Diboride ◽  
Ignition And Combustion

Boron and its compounds are among the most promising metal fuel components to be used in solid propellants for solid fuel rocket engine and ramjet engine. Papers studying boron oxidation mostly focus on two areas: oxidation of single particles and powders of boron, as well as boron-containing composite solid propellants. This paper presents the results of an experimental study of the ignition and combustion of the high-energy material samples based on ammonium perchlorate, ammonium nitrate, and an energetic combustible binder. Powders of aluminum, amorphous boron and aluminum diboride, obtained by the SHS method, were used as the metallic fuels. It was found that the use of aluminum diboride in the solid propellant composition makes it possible to reduce the ignition delay time by 1.7–2.2 times and significantly increase the burning rate of the sample (by 4.8 times) as compared to the solid propellant containing aluminum powder. The use of amorphous boron in the solid propellant composition leads to a decrease in the ignition delay time of the sample by a factor of 2.2–2.8 due to high chemical activity and a difference in the oxidation mechanism of boron particles. The burning rate of this sample does not increase significantly.

Simulation of Ignition and Combustion of Boron-Containing Solid Propellants

2021 ◽  
Vol 57 (3) ◽  
pp. 58-64
Author(s):  
V.A. Arkhipov ◽  
S.A. Basalaev ◽  
V.T. Kuznetsov ◽  
V.A. Poryazov ◽  
A.V. Fedorychev
Keyword(s):  
Solid Propellants ◽  
Ignition And Combustion

Ignition and combustion behavior of mechanically activated Al–Mg particles in composite solid propellants

2018 ◽  
Vol 194 ◽  
pp. 410-418 ◽  
Author(s):  
Hatem Belal ◽  
Chang W. Han ◽  
Ibrahim E. Gunduz ◽  
Volkan Ortalan ◽  
Steven F. Son
Keyword(s):  
Solid Propellants ◽  
Combustion Behavior ◽  
Composite Solid Propellants ◽  
Ignition And Combustion ◽  
Composite Solid
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