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Erosive burning study utilizing ultrasonic measurement techniques
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Furfaro, James A. |
| Copyright Year | 2003 |
| Description | A 6-segment subscale motor was developed to generate a range of internal environments from which multiple propellants could be characterized for erosive burning. The motor test bed was designed to provide a high Mach number, high mass flux environment. Propellant regression rates were monitored for each segment utilizing ultrasonic measurement techniques. These data were obtained for three propellants RSRM, ETM- 03, and Castor@ IVA, which span two propellant types, PBAN (polybutadiene acrylonitrile) and HTPB (hydroxyl terminated polybutadiene). The characterization of these propellants indicates a remarkably similar erosive burning response to the induced flow environment. Propellant burnrates for each type had a conventional response with respect to pressure up to a bulk flow velocity threshold. Each propellant, however, had a unique threshold at which it would experience an increase in observed propellant burn rate. Above the observed threshold each propellant again demonstrated a similar enhanced burn rate response corresponding to the local flow environment. |
| File Size | 783815 |
| Page Count | 12 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20030066165 |
| Archival Resource Key | ark:/13960/t0tr0vn91 |
| Language | English |
| Publisher Date | 2003-07-23 |
| Access Restriction | Open |
| Subject Keyword | Propellants And Fuels Combustion Physics Propellants Htpb Propellants Acrylonitriles Flow Velocity Polybutadiene Combustion Chambers Burning Rate Erosive Burning Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
