Influence of storable propellant liquid rocket design parameters on combustion instability.

Abstract : An experimental and analytical investigation has been conducted to establish correlation between thrust chamber design parameters and resultant combustion phenomena. The tests were made with self-impinging doublet injectors in a 15-in. -diameter pulse motor using Nitrogen tetroxide and monomethyl hydrazine. Pulse guns were used to disturb the combustion process and rate combustion stability. The analytical, vaporization-controlled, combustion models were used to compute the stability characteristics of the experimental thrust chamber at each operating condition. The stability model was then evaluated by comparing the hot-firing test results with the predicted stability characteristics. (Author)