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- W2001692216 abstract "The contamination that results from the exhaust plume of small thrusters used for attitude control maneuvers can pose severe problems for long-life satellite systems. In order to assess this type of contamination problem, analytical and experimental techniques must be developed. Mass deposition rate measurements of a representative 0.44-N thrust hydrazine thruster were made in a space simulation chamber using five appropriately placed variable-temperature quartz crystal microbalances. The mass deposition rates within the thruster plume were measured while operating the thruster over a wide range of operating parameters, including duty cycles, catalyst bed start temperatures, propellant water variation, as well as thruster aging effects. The contamination measurements were made over a temperature range of 144 to 256 K for all duty cycles. In addition, the nominal duty cycle of 100 msec on and 10 sec off was run at a temperature of 106 K. These data will make possible better prediction of deposition rates of contaminants from thrusters used in satellite systems." @default.
- W2001692216 created "2016-06-24" @default.
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- W2001692216 date "1977-07-01" @default.
- W2001692216 modified "2023-10-04" @default.
- W2001692216 title "Small monopropellant thruster contamination measurement in a high-vacuum low-temperature facility" @default.
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- W2001692216 doi "https://doi.org/10.2514/3.27977" @default.
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