Monopropellant hydrazine resisto jet

Abstract

Mathematical models for the electrothermal hydrazine thruster are provided which can be utilized to aid in preliminary design definition, interpretation of test data, and the evaluation of design and operational changes. Three computer programs were formulated to provide the necessary steady state and transient performance design tools. These included: preliminary evaluation of the energy balance characteristics of the thruster; a means of evaluating steady state performance relative to the primary design, configuration, and operational parameters; and a model to provide a means of evaluating transient (pulse mode) operation of the thruster relative to primary design and operational parameters.