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- W756541210 abstract "Installing less than the optimum amount of power on an eLectricaLly propelled spacecraft can drastically reduce its payload capability. A technique for improving the payload at low power is proposed which involves reducing the total mass of the spacecraft, It is shown that an optimum total mass of the electric propulsion spacecraft can be less than the maximum injected mass capability of the chemical-rocket launch vehicle at any given Lnjection velocity, An exqmpbe of the method is given for a Mercury orbiter mission using a solar-electric-propulsion spacecraft launched by a Titan IIID/Centaur. AN IMPROVED METHOD FOR MAXIMIZING THE PAYLOAD OF ELECTRIC PROPUTSION SPACECMFT AT LOW POWER LEVEL" @default.
- W756541210 created "2016-06-24" @default.
- W756541210 creator A5038332913 @default.
- W756541210 date "1971-02-01" @default.
- W756541210 modified "2023-09-27" @default.
- W756541210 title "An improved method for maximizing the payload of electric propulsion spacecraft at low power level" @default.
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