Abstract
Two-dimensional axisymmetric interior ballistics simulations in the projectile launch system utilizing long slotted tubular solid propellant are carried out using solid/gas two-phase fluid dynamics code of Eulerian-Lagrangian approaches. The movement of slotted tubular solid propellant is simulated one-dimensionally by Lagrangian approach. The simulation results are compared with experimental data for validation. The histories of the breech pressure and projectile velocity under various conditions are in good agreement with the experimental data. We examine the effects of the projectile and propellant mass conditions on the energy release rate of solid propellant and the projectile kinetic energy at the muzzle. A series of the simulations by changing the mass of projectile and propellant clarifies that the launch system requires the heavier projectile for ensuring the sufficient time of the projectile staying in the launch tube to convert efficiently the propellant chemical energy to the projectile kinetic energy.
| Original language | English |
|---|---|
| Title of host publication | 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit |
| Publication status | Published - 2008 |
| Event | 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit - Hartford, CT, United States Duration: 2008 Jul 21 → 2008 Jul 23 |
Other
| Other | 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit |
|---|---|
| Country | United States |
| City | Hartford, CT |
| Period | 08/7/21 → 08/7/23 |
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ASJC Scopus subject areas
- Aerospace Engineering
- Control and Systems Engineering
- Space and Planetary Science
- Energy(all)
- Electrical and Electronic Engineering
- Mechanical Engineering
Cite this
Interior ballistics simulation of projectile launch system utilizing tubular solid propellant. / Miura, H.; Matsuo, Akiko; Nakamura, Y.
44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. 2008.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Interior ballistics simulation of projectile launch system utilizing tubular solid propellant
AU - Miura, H.
AU - Matsuo, Akiko
AU - Nakamura, Y.
PY - 2008
Y1 - 2008
N2 - Two-dimensional axisymmetric interior ballistics simulations in the projectile launch system utilizing long slotted tubular solid propellant are carried out using solid/gas two-phase fluid dynamics code of Eulerian-Lagrangian approaches. The movement of slotted tubular solid propellant is simulated one-dimensionally by Lagrangian approach. The simulation results are compared with experimental data for validation. The histories of the breech pressure and projectile velocity under various conditions are in good agreement with the experimental data. We examine the effects of the projectile and propellant mass conditions on the energy release rate of solid propellant and the projectile kinetic energy at the muzzle. A series of the simulations by changing the mass of projectile and propellant clarifies that the launch system requires the heavier projectile for ensuring the sufficient time of the projectile staying in the launch tube to convert efficiently the propellant chemical energy to the projectile kinetic energy.
AB - Two-dimensional axisymmetric interior ballistics simulations in the projectile launch system utilizing long slotted tubular solid propellant are carried out using solid/gas two-phase fluid dynamics code of Eulerian-Lagrangian approaches. The movement of slotted tubular solid propellant is simulated one-dimensionally by Lagrangian approach. The simulation results are compared with experimental data for validation. The histories of the breech pressure and projectile velocity under various conditions are in good agreement with the experimental data. We examine the effects of the projectile and propellant mass conditions on the energy release rate of solid propellant and the projectile kinetic energy at the muzzle. A series of the simulations by changing the mass of projectile and propellant clarifies that the launch system requires the heavier projectile for ensuring the sufficient time of the projectile staying in the launch tube to convert efficiently the propellant chemical energy to the projectile kinetic energy.
UR - http://www.scopus.com/inward/record.url?scp=77957837590&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=77957837590&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:77957837590
SN - 9781563479434
BT - 44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit
ER -