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□ Nuclear Elect ric/lv.o-way ■ Nuclest Elect ric/'ore-mey

Figure 5.10. Ratio of total propellant weight to satellite weight for two electric propulsion systems..

Figure 5.10. Ratio of total propellant weight to satellite weight for two electric propulsion systems..

figure is 190.5 kg of propellant per kilogram of LEO propellant delivered), the future holds a dramatic reduction in that quantity by a factor about 20 just by using hydrogen/oxygen propulsion in space, and using a combination of hydrogen/ oxygen rocket and airbreathing propulsion for the launcher. With space electric propulsion and hydrogen/oxygen rocket plus airbreathing propulsion for the launcher that ratio can be reduced to 1 or 3 kg of burnt propellant per kilogram delivered to orbit. The orbital tanker is now competitive with a KC-135 or modified B-767 for refueling missions.

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