Purdue university seeks to develop spaceflight testing of a multi-functional smallsat technology for low-power attitude and thermal control using the film-evaporation mems tunable array (femta)…

Purdue University was awarded a $264,872.68 research grant by a civilian federal agency to advance the Film-Evaporation MEMS Tunable Array (FEMTA) micropropulsion technology through spaceflight testing. FEMTA is a multi-functional smallsat technology designed for low-power attitude and thermal control that leverages microscale fluid dynamics and advanced MEMS microfabrication to achieve a thrust-to-power ratio of 200 Newtons per Watt using pure water as propellant. The award was issued on January 15, 2019, with an ultimate completion date of January 14, 2025, under the SpaceTech-REDDI-2018 program, which focuses on advancing space technology capabilities through demonstration and innovation.

The project involves conducting zero-gravity flight testing aboard the New Shepard suborbital launch vehicle to validate the spaceflight-rated micropropulsion module's operability and structural integrity under actual spaceflight conditions. Key technical objectives include developing a flight-qualified module, demonstrating propellant management system functionality in zero-gravity, and verifying thruster performance under spaceflight loading. The test methodology includes capturing comprehensive data on propellant vapor pressure, temperature, flow rates, ambient pressure, module acceleration, and video throughout the experiment, with pre- and post-flight inspections of the FEMTA thrusters. The project is notable for its significant educational component, with undergraduate students at Purdue's West Lafayette campus actively participating in the design, fabrication, and implementation of the flight demonstration under the guidance of principal investigators and graduate student mentors.

Purdue university seeks to develop spaceflight testing of a multi-functional smallsat technology for low-power attitude and thermal control using the film-evaporation mems tunable array (femta) technology developed to TRL5 under NASA smallsat technology partnership program. Femta utilizes microscale effects in fluid surface tension and advanced mems microfabrication to achieve a highly tunable micropropulsion at a thrust-to-power ratio of 200 n/w using pure water as propellant. Under the spacetech- reddi-2018 we seek to advance femta technology utilizing suborbital vehicles demonstrating zero-g, in-space operation of the femta thruster with the vapor-pressure driven propellant management system. Technical objectives of flight testing include (i) develop a spaceflight rated micropropulsion module; (II) prove the operability of the propulsion module in spaceflight operating conditions (III) verify the integrity of the femta thruster under spaceflight loading conditions. The flight testing will be carried out on new shepard launch vehicle in an external payload locker exposed to vacuum. During ascent and while the ambient pressure is less than 10 KPA, the zero-g tank will vent to equalize with the environment. Once in zero-g, a valve will open to allow propellant to flow from the propellant tanks to a collection chamber. The femtas will also be powered during this time to simulated operation. Alcohol vapor pressure and temperature, propellant flow rates, ambient pressure, propulsion module acceleration, and video will be recorded at all times throughout the experiment. Femta thrusters will be inspected and tested before and after the flight. A team of undergraduate students at purdue will be involved in the design and building of the flight module and the implementation of the suborbital flight demonstration. PI, CO-PI and key personnel including graduate students will coordinate and advise the undergraduate team. The undergraduate student activities will be carried out through a AAE 490 spacecraft design course.