No abstract

This paper describes the results of a study to define the ignition characteristics and thruster pulse mode capabilities o f the GOX/ ethanol propellant combination. Ignition limits were defined in terms of mixture ratio and cold flow pressure using a spark initiated torch igniter. Igniter tests were run over a wide range of cold flow pressure, propellant temperature and mixture ratio. The product o f cold flow pressure and igniter chamber diameter was used t o correlate mixture ratio rpaimes of ianition and nan-~~ ignition. ~ Eigine-dignitioi reliability aid pulse mode capability were demonstrated using a 620 IbF thruster with an integrated torch ign~iter. The nominal chamber pressure and mixture ratio were 150 psia and 1.8, respectively, thruster tests were run over a wide range of chamber pressures and mixture ratios. The feasibility of thruster pulse mode operation with the non-hypergolic GOX/ ethanol propellant combination was demonstrated.

No abstract

No abstract

No abstract