PARAMETRIC STUDY OF ROCKET INSTABILITY.
PURDUE UNIV LAFAYETTE IND SCHOOL OF MECHANICAL ENGINEERING
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Research was conducted to determine those dimensionless parameters that may be employed as criteria for predicting the stability of combustion in a thrust chamber. UNMIXED GASEOUS PROPELLANTS Unmixed propellants with impinging jet injectors yield combustion pressure oscillation similar to that obtained for premixed propellants with respect to fuel reactivity. BIPHASE PROPELLANTS LIQUID FUEL-GASEOUS OXIDIZER Investigations were conducted to determine the effects of 1 both the air and propellant injection velocities, chamber pressure, and fuel-air ratio on the steady-state operating characteristics of a rocket motor, and 2 selected parameters on propellant vaporization rate. CORRELATION OF RESULTS WITH SIMILARITY VARIABLES Dimensionless parameters were derived that are sensitive to the occurrence of small amplitude pressure oscillations in the burning gaseous medium in a cylindrical combustion chamber. THEORETICAL ANALYSIS An analysis was completed of the longitudinal combustion pressure oscillations for one model of the combustion zone.