Combustion Dynamics in Rockets.
Annual rept. 1 Oct 81-30 Sep 82,
GEORGIA INST OF TECH ATLANTA SCHOOL OF AEROSPACE ENGINEERING
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Progress is reported on four distinct projects which are administered as a group. The projects are identified as tasks. A summary for each task follows Task I. In the first phase of this program the previously developed impedance tube setup utilized to determine the dependence of solid propellants pressure coupled response functions and associated gas phase losses upon the aluminum content of the propellant. Tests over the 400-100 Hz frequency range showed that increasing the aluminum content of the propellant increases both the propellant driving and associated gas phase losses. Furthermore, it shifts the frequency at which maximum driving occurs. In the second phase of this task, the modified impedance tube setup has been utilized in the investigation of the characteristics of the velocity coupled response factor. The status of this investigation is summarized in this report.
- Combustion and Ignition
- Solid Rocket Propellants