Holographic Investigation of Solid Propellant Combustion
Abstract
An investigation into the behavior of aluminized solid propellant combustion in a two-dimensional windowed rocket motor was conducted using holographic techniques. Holograms were recorded in the motor port, aft of the propellant grain and at the entrance to the exhaust nozzle for two different propellant compositions at varying operating pressures. Quantitative particle size data for particles larger than 20 microns were obtained from the holograms. From these data, the mean diameters (D32) of the larger particles were calculated and utilized to compare what effects pressure, location in the motor and aluminum content had on the behavior of the aluminum/aluminum oxide particles. D32 was found to decrease with increasing pressure, but was unaffected by variations in low values of propellant aluminum loading. D32 at the grain exit was found to be significantly less than within the grain port. Keywords: Solid propellant rocket engines, Solid rocket propellants, Theses.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1988
- Accession Number
- ADA203928
Entities
People
- Albert G. Butler
Organizations
- Naval Postgraduate School