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, propellant surface/near surface, motor cavity, and nozzle regions. Also of concern is the influence these particles have on propellant combustion characteristics and overall motor performance. This part year's efforts have been directed toward developing the experimental equipment and/or techniques required for determining particle size distributions at or near the propellant surface. The approach taken involves making use of a laboratory scale, servo-controlled strand window bomb in conjunction with both an imaging-type particle size analyzer and a high speed, pulse-it photographic technique. In this report, the servo-controlled strand window bomb is described following a brief review of past research efforts have employed similar propellant feed mechanisms. Next, the theory and operation of the particle size analyzer is detailed. Finally, the feasibility of employing high speed, pulse-lit photography in the study of metal particle/agglomerate combustion is discussed.
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 27, 1982
- Accession Number
- ADA121692
Entities
People
- J .r. Osborn
- J. P. Renie
Organizations
- Purdue University