Journal of Micromechanics and Microengineering · 2005 · 51 citations · 9 references
EngineeringAerospace EngineeringMechanical EngineeringMicroelectromechanical SystemsPropulsionSpacecraft DesignManeuvering PropulsionMems DesignPropulsion System PerformancePropulsion SystemsSmall Satellite DesignSpacecraft TestAttitude Control SystemsElectrothermal PropulsionExperimental Performance TestingMiniaturized Propulsion SystemsPropulsion System DesignResistojetsSmall Satellite Mission DesignSpacecraft Propulsion
Interest in micro‑ and nanosatellites is growing, and constellations of small satellites may replace larger spacecraft as a cheaper, more flexible alternative, requiring efficient, low‑cost propulsion systems. This work develops and evaluates a MEMS‑based electrothermal propulsion system, the Free Molecule Micro‑Resistojet, for on‑orbit maneuvers of nanosatellites weighing less than 10 kg. The FMMR was tested on a torsion force balance using helium, argon, nitrogen, and carbon dioxide propellants to measure thrust performance and validate the design. Measured thrust and specific impulse agree with gas‑kinetic theory predictions and are adequate for attitude‑control maneuvers on the University nanosatellite mission.
There is a growing interest in the use of micro and nanosatellites within the aerospace community. Constellations of small satellites may eventually replace much larger, single function spacecraft as a cheaper, more flexible alternative. Micro-technologies will be required to enable small satellite missions including efficient, low-cost propulsion systems for maneuvering. A MEMS fabricated propulsion system has been developed for maneuvers on an upcoming University nanosatellite mission. The Free Molecule Micro-Resistojet (FMMR) is an electrothermal propulsion system designed for on-orbit maneuvers of nanosatellites, which are defined as spacecraft with an initial mass less than 10 kg. The FMMR has been tested using a torsion force balance to assess its performance using a variety of propellants including helium, argon, nitrogen and carbon dioxide. The experimental performance results compare favorably with results obtained from gas kinetic theory, which were used in the design phase to estimate the thruster's performance. The measured performance of the FMMR in this study has proven to be adequate to perform attitude control maneuvers for the University nanosatellite mission.
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Physics of Electric Propulsion
R. G. Jahn, F. A. Lyman · Journal of Applied Mechanics · 1969 · 837 citations · Full text