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Mass comparisons of electric propulsion systems for NSSK of geosynchronous spacecraftA model was developed and exercised to allow wet mass comparisons of three-axis stabilized communications satellites delivered to geosynchronous transfer orbit. The mass benefits of using advanced chemical propulsion for apogee injection and north-south stationkeeping (NSSK) functions or electric propulsion (hydrazine arcjets and xenon ion thrusters) for NSSK functions are documented. A large derated ion thruster is proposed which minimizes thruster lifetime concerns and qualification test times when compared to those of smaller ion thrusters planned for NSSK applications. The mass benefits, which depend on the spacecraft mass and mission duration, increase dramatically with arcjet specific impulse in the 500-600 s range, but are nearly constant for the derated ion thruster operated in the 2300-3000 s range. For a given mission, the mass benefits with an ion system are typically double those of the arcjet system; however, the total thrusting time with arcjets is less than one-third that with ion thrusters for the same thruster power.
Document ID
19910061185
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Rawlin, V. K.
(NASA Lewis Research Center Cleveland, OH, United States)
Majcher, G. A.
(Cleveland State University OH, United States)
Date Acquired
August 14, 2013
Publication Date
June 1, 1991
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 91-2347
Accession Number
91A45808
Distribution Limits
Public
Copyright
Other

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