Hydrazine-chlorine pentafluoride reaction in a laboratory rocket combustor.

Abstract

The combustion of hydrazine and chlorine pentafluoride was studied in a small, approximately 10-lb thrust, combustion chamber through use of a differentially pumped sampling system and time-of-flight mass spectrometric analysis. A qualitative identification of combustion product species including HF, HC1, H2, GIF, N2, and NHs, taken from the nozzle end of the combustor, was made for stoichiometric to fuel-rich mixture ratios. A condensate that was deposited under some operating conditions on the combustor walls was collected and analyzed as hydrazine hydrofluoride. Based upon limited, available, chemical kinetic information, a reaction mechanism is postulated which is consistent with the experimental observations. A nonequilibrium combustion model for hydrazine-rich combustion is proposed, and the effect of greater-than-equilibrium concentrations of ammonia upon the theoretical performance of this propellant combination is predicted.