THE INVESTIGATION SEEKS TO FURTHER DEVELOP A MULTI-FUNCTIONAL SMALLSAT TECHNOLOGY FOR LOW-POWER ATTITUDE AND THERMAL CONTROL FOR INFUSION INTO DEEP SPACE MISSIONS. THE FILM-EVAPORATION MEMS TUNABLE ARRAY (FEMTA) SMALLSAT TECHNOLOGY INITIALLY DEVELOPED BY PURDUE UNIVERSITY AND NASA GODDARD SPACE FLIGHT CENTER UNDER SSTP NNX13AR02A UTILIZES MICROSCALE EFFECTS IN FLUID SURFACE TENSION AND ADVANCED MEMS MICROFABRICATION TO ACHIEVE A HIGHLY TUNABLE THRUST AT A THRUST-TO-POWER RATIO OF ABOUT 200 MICRON/ W. UNDER NNX15AW40A GRANT FOUR FEMTA THRUSTERS HAS BEEN INTEGRATED INTO A 1U CUBESAT PROTOTYPE AND DEMONSTRATED>360 DEG ROTATION OF 1U CUBESAT IN LESS THAN 1 MINUTE AT A 0.23 DEG/S2 ANGULAR ACCELERATION AND UP TO 8 DEG/S SLEW RATE WITH<0.25W INPUT POWER DURING VACUUM TESTING. THE MAIN GOAL OF THE PROPOSED TECHNOLOGY ADVANCEMENT IS TO ACHIEVE FLIGHT DEMONSTRATION READINESS OF A STAND-ALONE<0.25U FEMTA PROPULSION MODULE. THE SPECIFIC OBJECTIVES INCLUDE (I) DEVELOPMENT OF GRAVITY-FREE PROPELLANT DISTRIBUTION; (II) EVALUATION OF LONG-TERM PERFORMANCE OF ELECTROTHERMAL MICROSHUTTERS INTEGRATED WITH FEMTA THRUSTERS BY THERMAL VACUUM AND VIBRATION TESTING; (III) EVALUATION OF MICROFABRICATION UNCERTAINTY EFFECTS ON THERMAL PERFORMANCE AND THRUSTER PLUME/ SPACECRAFT INTERACTION AND CONTAMINATION MITIGATION STUDIES. ADDITIONALLY WE WILL FURTHER ADVANCE THE FEMTA MICROCONTROLLER DESIGN AND EVALUATE OPTIONS FOR STAND-ALONE SOLAR POWER GENERATION STORAGE AND WIRELESS ACTUATION. THE RESULTING FEMTA PROPULSION TECHNOLOGY ENABLES PRECISE LOW-POWER ATTITUDE CONTROL OF PICOSATELLITES BEYOND LOW EARTH ORBIT. THE INVESTIGATION WILL BE CONDUCTED BY PURDUE UNIVERSITY IN PARTNERSHIP WITH NASA GODDARD SPACE FLIGHT CENTER FOR FEMTA TECHNOLOGY AND IN COLLABORATION WITH NASA MARSHALL SPACE FLIGHT CENTER FOR EVALUATION OF FEMTA APPLICATION TO SMALLSAT-BASED DEEP SPACE MISSIONS THAT REQUIRE PRECISE MANEUVERING OF DEPLOYABLE STRUCTURES.