Ionic Liquid Dual-Mode Spacecraft Propulsion Assessment
Analytical and numerical investigations of the performance of a series of potential dual-mode propulsion systems using ionic liquids are presented. A comparison of the predicted specific impulse of ionic liquids with hydrazine and unsymmetrical dimethylhydrazine shows that ionic liquid fuels have a 3-12% lower specific impulse when paired with a nitrogen tetroxide oxidizer. However, when paired with hydroxylammonium nitrate oxidizer, the specific impulse of the ionic liquids is 1-4% lower than that of hydrazine and unsymmetrical dimethylhydrazine paired with nitrogen tetroxide. Analytical investigation of an electrospray electric propulsion system shows that ion extraction in the pure ion regime provides a very high specific impulse, outside the optimum range for potential missions. Results suggest a deceleration grid, a lower ion fraction, or emission of higher solvated states is required. Analysis of a dual-mode ionic-liquid-propelled spacecraft shows that the electric propulsion component determines the overall feasibility compared with current technology. Results indicate that the specific power for anionic liquid electrospray system must be at least 15W/ kg in order for a dual-mode ionic liquid system to compete with traditional hydrazine and Hall thruster technology.
B. R. Donius and J. L. Rovey, "Ionic Liquid Dual-Mode Spacecraft Propulsion Assessment," Journal of Spacecraft and Rockets, American Institute of Aeronautics and Astronautics (AIAA), Jan 2011.
The definitive version is available at https://doi.org/10.2514/1.49959
Mechanical and Aerospace Engineering
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© 2011 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.