Determination of the Combustion Mechanisms of Aluminized Propellants
Abstract
This research project is concerned with determining the mechanisms governing the formation and combustion of metal/agglomerate/metal oxide particles throughout the solid rocket motor, that is, surface/near surface, cavity, and nozzle regions. Also of concern is the influence these particles have on propellant combustion characteristics and motor performance. The efforts of this past year were directed toward developing the experimental equipment needed for determining particle size distributions at and near the propellant surface. A solid propellant strand window bomb with a servo controlled positioning device was constructed and operated. Also, the interface of this equipment with data recording and reduction equipment was accomplished. The laser imaging device to be used to measure particle size distributions is undergoing calibration tests. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 26, 1981
- Accession Number
- ADA109058
Entities
People
- H. M. Pressley
- J .r. Osborn
- J. P. Renie
- J. S. Lilley
Organizations
- Purdue University