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Electrolysis propulsion breadboard installed inside a high-altitude simulation chamber. Parameters recorded during testing were the electrolysis unit supply current and voltage, and temperatures and pressures inside the electrolysis unit, near the storage tanks, and in the 1.1-N thruster. Quantities derived from these data were the propellant generation rate as a function of supplied power and electrolysis unit gas pressure, thruster mass flow rates, and propellant mixture ratios. The test bed was cycled with input powers varying from 1 to 18 W. Results showed a high degree of repeatability. Combustion chamber oxygen-to-fuel mass flow rates varied from 7 to 9 during blowdown tests. Combustion chamber outer wall temperatures did not exceed 1600 °F for the duration of the thruster firings, which lasted between 2.5 and 4.5 seconds. In a flight system, the gravity-fed electrolyzer utilized for these experiments is replaced with a vapor-feed electrolyzer. Neither mechanical pumps nor pressurant gas is required to feed a water electrolysis rocket system because electrolyzers are able to electrochemically "pump" water decomposition products from ambient pressure up to pressures of at least 20 MPa. The absence of a pressurization system simplifies the propellant feed significantly and eliminates components that must have long-term compatibility with propellants. For deep space missions, water is significantly easier to contain than hypergolic Earth storables (those that can ignite without an outside source of ignition), offering stability over a relatively wide temperature range. Bibliography Mitlitsky, F., et al.: Integrated Modular Propulsion and Regenerative Electro-Energy Storage System (IMPRESS) for Small Satellites. 10th Annual AIAA/USU Conference on Small Satellites, 1996. de Groot, W.A., et al.: Electrolysis Propulsion for Spacecraft Applications. AIAA Paper 97-2948, 1997. Lewis contact: Dr. Wim A. de Groot, (216) 977-7485,PDF Image | Electrolysis Spacecraft Propulsion
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