Abstract
The ignition of polymethylmethacrylate (typical model propellant of the hybrid rocket motor) by a hot particle in a shape of parallelepiped, polyhedron, disk is investigated numerically. The initial temperature of a heat source varied within the range 950–1150 K, size of particle – within the range 2–6 mm. It is established that varying these parameters influenced significantly the main characteristic of the process – ignition delay time under ignition conditions close to critical. For considered shape of particles, ignition delay time is in ascending sequence: parallelepiped, polyhedron, disk. Three polymer ignition regimes, which characterized by the initial temperature of a heat source, ignition delay time and a location of an ignition zone in a vicinity of a hot particle, are emphasized. It is illustrated that taking into account the dependence of thermal and physical characteristics of polymethylmethacrylate on temperature, the ignition delay time increased due to augmentation of energy accumulated by a subsurface layer.
| Original language | English |
|---|---|
| Pages (from-to) | 387-396 |
| Number of pages | 10 |
| Journal | Acta Astronautica |
| Volume | 133 |
| DOIs | |
| Publication status | Published - 1 Apr 2017 |
Fingerprint
Keywords
- Hot particle
- Hybrid rocket motor
- Ignition
- Mathematical simulation
- Polymer propellant
ASJC Scopus subject areas
- Aerospace Engineering
Cite this
Ignition of a polymer propellant of hybrid rocket motor by a hot particle. / Glushkov, D. O.; Kuznetsov, G. V.; Strizhak, P. A.
In: Acta Astronautica, Vol. 133, 01.04.2017, p. 387-396.Research output: Contribution to journal › Article
}
TY - JOUR
T1 - Ignition of a polymer propellant of hybrid rocket motor by a hot particle
AU - Glushkov, D. O.
AU - Kuznetsov, G. V.
AU - Strizhak, P. A.
PY - 2017/4/1
Y1 - 2017/4/1
N2 - The ignition of polymethylmethacrylate (typical model propellant of the hybrid rocket motor) by a hot particle in a shape of parallelepiped, polyhedron, disk is investigated numerically. The initial temperature of a heat source varied within the range 950–1150 K, size of particle – within the range 2–6 mm. It is established that varying these parameters influenced significantly the main characteristic of the process – ignition delay time under ignition conditions close to critical. For considered shape of particles, ignition delay time is in ascending sequence: parallelepiped, polyhedron, disk. Three polymer ignition regimes, which characterized by the initial temperature of a heat source, ignition delay time and a location of an ignition zone in a vicinity of a hot particle, are emphasized. It is illustrated that taking into account the dependence of thermal and physical characteristics of polymethylmethacrylate on temperature, the ignition delay time increased due to augmentation of energy accumulated by a subsurface layer.
AB - The ignition of polymethylmethacrylate (typical model propellant of the hybrid rocket motor) by a hot particle in a shape of parallelepiped, polyhedron, disk is investigated numerically. The initial temperature of a heat source varied within the range 950–1150 K, size of particle – within the range 2–6 mm. It is established that varying these parameters influenced significantly the main characteristic of the process – ignition delay time under ignition conditions close to critical. For considered shape of particles, ignition delay time is in ascending sequence: parallelepiped, polyhedron, disk. Three polymer ignition regimes, which characterized by the initial temperature of a heat source, ignition delay time and a location of an ignition zone in a vicinity of a hot particle, are emphasized. It is illustrated that taking into account the dependence of thermal and physical characteristics of polymethylmethacrylate on temperature, the ignition delay time increased due to augmentation of energy accumulated by a subsurface layer.
KW - Hot particle
KW - Hybrid rocket motor
KW - Ignition
KW - Mathematical simulation
KW - Polymer propellant
UR - http://www.scopus.com/inward/record.url?scp=85005992242&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85005992242&partnerID=8YFLogxK
U2 - 10.1016/j.actaastro.2016.10.030
DO - 10.1016/j.actaastro.2016.10.030
M3 - Article
VL - 133
SP - 387
EP - 396
JO - Acta Astronautica
JF - Acta Astronautica
SN - 0094-5765
ER -