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- W3119808403 abstract "A warm gas thruster using a catalyzed Tridyne propellant (10% $H_2$, 5% $O_2$, and 85% $N_2$) is being developed at the University of Washington in collaboration with Aerojet Rocketdyne for the purposes of advancing micro-propulsion technologies. A trade analysis was conducted to identify the advantages of Tridyne over conventional state-of-the-art microthrusters. A bench-top thruster was designed and constructed to test the performance capabilities of Tridyne. Pressure, temperature, and mass flow rate were measured with bench-top thruster testing for conditions corresponding to an estimated thrust of 1N. The bench-top thruster was tested for two different Tridyne reaction configurations: ignition via flow over a heated pebble bed, and ignition via flow over a catalyst bed composed of an iridium-alumina catalyst. The adiabatic flame temperature was observed in both configurations, with the heated pebble bed only reaching that temperature at steady state for propellant flow rates under 0.8 g/s. The adiabatic flame temperature was reached with use of catalyst. The characteristic velocity of the catalyzed-thruster was in the range of 0.78 - 0.94 of the theoretical value. Chemical reaction startup rise times in the range of 5-10 seconds suggest that the Tridyne thruster technology is best suited for missions requiring a minimal number of startup cycles." @default.
- W3119808403 created "2021-01-18" @default.
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- W3119808403 date "2021-01-04" @default.
- W3119808403 modified "2023-10-16" @default.
- W3119808403 title "Development of a Tridyne Propulsion System for CubeSat Applications" @default.
- W3119808403 cites W2008996841 @default.
- W3119808403 cites W2586753726 @default.
- W3119808403 doi "https://doi.org/10.2514/6.2021-2028" @default.
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