Abstract
Nonlinear, pressurization-rate dependent combustion during initial pressurization in solid propellant rockets is simulated computationally. The "ignition" spike commonly observed in motors with small L* and usually attributed to erosive burning or igniter mass flux is simulated for a tactical motor with AP composite propellant, similar to what has been previously demonstrated for homogeneous propellant. A mechanism for bulk-mode, nonlinear limit cycle behavior (amplitude-limited oscillations) is also presented.
| Original language | English (US) |
|---|---|
| State | Published - 2001 |
| Event | 37th Joint Propulsion Conference and Exhibit 2001 - Salt Lake City, UT, United States Duration: Jul 8 2001 → Jul 11 2001 |
Other
| Other | 37th Joint Propulsion Conference and Exhibit 2001 |
|---|---|
| Country/Territory | United States |
| City | Salt Lake City, UT |
| Period | 7/8/01 → 7/11/01 |
ASJC Scopus subject areas
- Energy Engineering and Power Technology
- Aerospace Engineering
- Control and Systems Engineering
- Electrical and Electronic Engineering
- Mechanical Engineering