Abstract
Unsteady thrust response of HMX was measured during laser and pressure-driven combustion. A CO2 laser was used as a heating source to ignite and sustain propellant combustion during pressure-driven tests by providing a constant heat flux. The laser acted as a source of ignition and oscillatory heat flux during laser-driven combustion. The laser-driven tests were performed at frequencies ranging from 3.9 to 250 Hz. Mean incident laser heat fluxes of 35, 60 and 90 W/cm2 were used. Pressure-driven thrust measurements were made in a different chamber with a 10% peak-to-peak pressure variation about the mean. The driving frequencies ranged from 4 to 100 Hz. Tests were conducted with air as the ambient gas at atmospheric pressure. The thrust response amplitude and phase as a function of frequency and heat flux were collected under both test conditions. A, B, n and ns parameters were obtained from the experiments and compared to theoretical values.
| Original language | English (US) |
|---|---|
| State | Published - 1999 |
| Event | 35th Joint Propulsion Conference and Exhibit, 1999 - Los Angeles, United States Duration: Jun 20 1999 → Jun 24 1999 |
Other
| Other | 35th Joint Propulsion Conference and Exhibit, 1999 |
|---|---|
| Country/Territory | United States |
| City | Los Angeles |
| Period | 6/20/99 → 6/24/99 |
All Science Journal Classification (ASJC) codes
- Energy Engineering and Power Technology
- Electrical and Electronic Engineering
- Mechanical Engineering
- Control and Systems Engineering
- Aerospace Engineering