Abstract
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.
| Original language | English |
|---|---|
| Article number | 01055 |
| Journal | MATEC Web of Conferences |
| Volume | 194 |
| DOIs | |
| Publication status | Published - 21 Aug 2018 |
| Event | 2018 Heat and Mass Transfer in the Thermal Control System of Technical and Technological Energy Equipment, HMTTSC 2018 - Tomsk, Russian Federation Duration: 24 Apr 2018 → 26 Apr 2018 |
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ASJC Scopus subject areas
- Chemistry(all)
- Materials Science(all)
- Engineering(all)
Cite this
Ignition and combustion of high-energy materials containing aluminum, boron and aluminum diboride. / Korotkikh, Alexander; Sorokin, Ivan; Selikhova, Ekaterina.
In: MATEC Web of Conferences, Vol. 194, 01055, 21.08.2018.Research output: Contribution to journal › Conference article
}
TY - JOUR
T1 - Ignition and combustion of high-energy materials containing aluminum, boron and aluminum diboride
AU - Korotkikh, Alexander
AU - Sorokin, Ivan
AU - Selikhova, Ekaterina
PY - 2018/8/21
Y1 - 2018/8/21
N2 - 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.
AB - 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.
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U2 - 10.1051/matecconf/201819401055
DO - 10.1051/matecconf/201819401055
M3 - Conference article
AN - SCOPUS:85058400294
VL - 194
JO - MATEC Web of Conferences
JF - MATEC Web of Conferences
SN - 2261-236X
M1 - 01055
ER -