Particle sizing in solid rocket motors
By: Douglas Lyle Hovland
Contributors: Naval Postgraduate School (U.S.)
Publisher: Naval Postgraduate School
Published: 1989
Place of publication: Monterey, California
Language: eng
Number of pages: 103
Description: 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. Particle sizing; Solid propellant rocket engines; Light scattering; Theses.
Notes: Thesis advisor: Netzer, David Willis.

"March 1989."

Thesis (Degree of Aeronautical Engineer) : Naval Postgraduate School, March 1989.

Includes bibliographic references: (p. 101-102).

Approved for public release, distribution unlimited.

US Navy (USN) author.