Particle sizing in solid rocket motors
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Authors
Hovland, Douglas Lyle
Subjects
particle sizing
solid propellant rocket motors
light scattering
solid propellant rocket motors
light scattering
Advisors
Netzer, David W.
Date of Issue
1989-03
Date
March 1989
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
Particle size distribution measurements were made with a Malvern 2600c forward laser light diffraction system across the exhaust nozzle entrance and exhaust plume of a small two-dimensional rocket motor. The solid propellants tested were GAP propellants containing 2.0% and 4.69% aluminum. Surface agglomeration of the aluminum, indicated by the in-motor results, was found to decrease as the motor chamber pressures were increased. At low pressures, increasing the aluminum loading with fixed total solids decreased the mean particle size at the nozzle entrance. Exhaust plume particle size was practically independent of nozzle inlet particle diameters, supporting the critical Weber number particle breakup theory. Initial validation of the Malvern 2600c measurements was accomplished by favorable comparison to exhaust plume particle distribution results obtained using a particle collection probe.
Type
Thesis
Description
Series/Report No
Department
Aeronautics and Astronautics
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Air Force Astronautics Laboratory F04611-88-X0021
Funder
Air Force Astronautics Laboratory F04611-88-X0021
Format
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.