Rocket Research at Georgia Tech.
Interim rept. 1 Oct 78-30 Sep 79,
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 individual projects are identified as tasks and reported on separately. A summary for each task follows Task I. Work concerned improvement and application of the impedance tube method for measurement of the presure-coupled combustion response of solid propellants and measurement of the bulk damping in the product flow. Improvements included increaed sites and amplitude range of pressure measurements increased capacity of the data acquisition system and a modified, more rapid data reduction program. Admittances and bulk loss coefficients of nonaluminized and aluminized propellants were measured over a range of frequencies. Task II. Studies were continued on external burning using an axisymmetric model at Mach 3. Tests with actual combustion of radially and axially injected hydrogen are then reported. Outstanding performance values with significant base drag reduction is shown for injection and burning directly in the near-wake base burning. Task III. Investigations continued of the accumulation processes of aluminum on the propellant burning surface that lead to formation of agglomerate droplets, the size of which dominates aluminum combustion. Task IV. Experimental and analytical studies were continued on the subject of turbulence-induced pressure fluctuations in a rocket-like cavity. A new theory was constructed for the generation of pressure disturbances by the turbulence. Undeniable separation has been achieved between propagational and local pressure fluctuations, and the agreement between theory and experiment are adequate.
- Combustion and Ignition
- Solid Propellant Rocket Engines
- Solid Rocket Propellants