Effect of voltage level on power system design for solar electric propulsion missions
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Effect of voltage level on power system design for solar electric propulsion missions

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Published by National Aeronautics and Space Administration, Glenn Research Center, Available from NASA Center for Aerospace Information, National Technical Information Center [distributor in [Cleveland, Ohio], Hanover, MD, Springfield, VA .
Written in English


Book details:

Edition Notes

StatementThomas W. Kerslake.
SeriesNASA/TM -- 2003-212304., NASA technical memorandum -- 212304.
ContributionsNASA Glenn Research Center.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL17635034M
OCLC/WorldCa56799261

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  This paper presents study results quantifying the benefits of higher voltage, electric power system designs for a typical solar electric propulsion spacecraft Earth orbiting mission. A conceptual power system architecture was defined and design points were generated for several system voltages using state-of-the-art or advanced by: 2.   This paper presents study results quantifying the benefits of higher voltage, electric power system designs for a typical solar electric propulsion spacecraft Earth orbiting mission. A conceptual power system architecture was defined and design points were generated for system voltages of V, V, V and V using state-of-the-art or Cited by: 9. the power source for solar-electric propulsion (SEP) missions []. The current plan for the In this propulsion system, high-power photovoltaic arrays provide energy's to a xenon-fueled electrical engine. One of the proposed applications of the high-power SEP technology is File Size: 5MB. Solar electric propulsion (SEP) refers to the combination of solar cells and electric thrusters to propel a spacecraft through outer space. This technology has been exploited in a variety of spacecraft by the European Space Agency, the Japanese Space Agency, Indian Space Research Organisation and NASA. SEP has a significantly higher specific impulse than normal chemical rockets, thus requiring.

Get this from a library! Effect of voltage level on power system design for solar electric propulsion missions. [Thomas W Kerslake; NASA Glenn Research Center.]. missions, the onboard propulsion systems and their required propellant may make up more than half of the overall spacecraft mass. By utilizing solar electric propulsion (SEP), the mass of the propulsion system and propellant can be reduced by up to 90 percent by . Frequently Asked Questions. History of NASA's involvement. Hear DS1's radio signals! SOLAR ELECTRIC (ION) PROPULSION. Click here to see a time lapse video ( MB Quicktime movie) of the DS1 Ion Thruster Compatibility Test taped on Febru (Or you can get a smaller version: MB).This testing was carried out on the DS1 spacecraft in the Solar Thermal Vacuum Chamber at JPL. Solar Electric Propulsion (SEP) trajectories are shown for Mars missions between late and 1. Mission performance is presented as burn-out mass along contours of constant flight time.

The Solar Electric Propulsion project is developing large solar arrays and high-power electric thrusters for an integrated in-space test-flight. Compared with current conventional chemical propulsion systems, at launch it will weigh two times less and use four times less storage for the electricity produced, and will operate at radiation levels. Electric Propulsion Options and Trades • Benefits: • Much higher specific impulse • Arcjets – s • Hall Thrusters – – s • Ion thrusters – – 10,s • Other concepts (VASIMIR, MPD, PIT) in same range • Higher Isp results in much lower propellant mass • Trades: • Need external source of power and electronics to match to the thruster. spacecraft propulsion. With literally hundreds of electric thrusters now operating in orbit on communications satellites, and ion and Hall thrusters both having been successfully used for primary propulsion in deep-space scientific missions, the future for electric propulsion has arrived. An electrically-powered spacecraft propulsion system uses electrical, and possibly also magnetic fields, to change the velocity of a of these kinds of spacecraft propulsion systems work by electrically expelling propellant (reaction mass) at high speed.. Electric thrusters typically use much less propellant than chemical rockets because they have a higher exhaust speed (operate.