Fundamental research into the feasibility of microrockets for primary propulsion and attitude control for far-term micro/integrated spacecraft is being performed. These rockets would be fabricated using microelectrical and mechanical systems (MEMS) technology. The enabling technology is being developed at the Massachusetts Institute of Technology (MIT). The NASA/MIT program leverages a very large Army Research Office and Defense Advanced Research Projects Agency (DARPA) program for the development of microturbine technology. The microrocket motor is complete with regenerative cooling, turbopumps, and control valves etched onto the same chip. They would be fabricated in large numbers in parallel using semiconductor manufacturing techniques. The technology may lead to the development of microsatellites as fully integrated MEMS devices that could be mass produced at a fraction of the cost of current satellites.
Silicon half-rocket chamber, complete with cooling channels. For scaling, this component is shown sitting atop a nickel.
This microrocket would have a specific impulse of 300 sec at a chamber pressure of 125 atm in a 15-N-thrust class engine and would use propellants such as liquid oxygen and ethanol. The motor, fabricated from silicon or silicon carbide, would have a thrust-to-weight ratio of 1500:1 compared to 15:1 for a conventional engine in this thrust range. The regeneratively cooled silicon structure is predicted to have an operating temperature less than 1400 K.
Because of the fundamental nature of the work, near-term efforts will focus on the basic feasibility issues. These include (1) MEMS fabrication technology, (2) component/propellant compatibility, (3) bonding and leakage, (4) heat transfer capabilities, (5) component life, and (6) performance.
Lewis contact: Dr. Steven J. Schneider, (216) 977-7484,
Steven.J.Schneider@grc.nasa.gov
Author: Dr. Steven J. Schneider
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Programs/Projects: New Millenium Program, MTPE
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