Rocket Research at Georgia Tech.
Interim technical rept.,
GEORGIA INST OF TECH ATLANTA SCHOOL OF AEROSPACE ENGINEERING
Pagination or Media Count:
Task I. During the reporting period, the impedance tube setup was utilized in the determination of the admittances ot two aluminized solid propellants. Both the pressure coupled response and the gas phase losses have been determined over the frequency range of 400-1200 Hertz. In a separate study, the feasibility of utilizing either quartz or piezoceramic crystals in the direct measurement of the mass loss of burning solid propellants has been investigated. Finally studies aimed at the adaptation of the impedance tube setup for the measurement of the simulating heating values for practical propellants, have been started. Task II. Studies were continued on burning in and around the near wake of an axisymmetric model at Mach 3. Burning tests with radiant and axial injection of pure hydrogen have been completed. Burning tests with axial injection of diluted hydrogen, velocity coupled response of burning solid propellant has been initiated. Task III. Further studies were made of aluminum accumulation and agglomeration on the propellant burning surface and droplet combustion in the gas flow from the surface. Modification of the aluminum powder to control agglomeretion were evaluated by propellant combustion studies and found to be highly effective. Task IV. Experimental and analytical studies were continued on the subject of turbulence-induced pressure flucuations in a rocket-like cavity. An advanced theory has provided closure between theory and experiment on one experimental facility. A fuel rocket motor simulator was built and preliminary results were attained to show the separation between propagational sound and local hydrodynamic noise.
- Combustion and Ignition
- Solid Propellant Rocket Engines
- Solid Rocket Propellants