The technology development of the 30-cm J-serie-mercury ion thruster for prime propulsion applic4tion in Solar Electric Propulsion Systems (SEPS) has been conducted at NASA-Lewis Research Center, This development included the Fabrication and Testing of the 30-cm thruster. The present J-series thruster design is the result of an intensive effort to eliminate real and potential uesign deficiencies that were uncovered during initial endurance, structural, and performance tests. A standardized set of test and data recording proCeoure was formulated to allow for the chzrdcterization of the J-series thruster, This Pape-will briefly review the design of the J-series thruster and will present a compilation of recent test results that define the J-series thruster characteristics. introduction

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The cesium microthruster system i s described.The ion engine subsystem consists of a singlebutton porous tungsten ionizer, electrodes. neutralizer filaments, and a cesium storage and feed system. trol logic and power conditioning. logic provides the necessary electronics for sequencing the microthruster startup and shutdown cycles, standby operating powers. telemetry signal conditioning, command interface circuits, and digital-to-analog controls. The rated thrust level of the thruster i s 20 plb at a specific impulse of 6700 sec. The beam deflection, which provides two-axis deflection for thrust vectoring, i s discussed. and such characteristics as critical temperature and perveance of the thruster a r e presented.Power input to the control logic/power conditioner at the 20 g b thrust level i s approximately 34 W.

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