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Solar electric propulsion for the orbital transfer of large spacecraft to geosynchronous orbitLow thrust trajectories utilizing electric propulsion and photovoltaic power sources are derived for the transfer of a large spacecraft from assembly in low earth orbit to operation at geosynchronous orbit. Conventional silicon photovoltaic devices are assumed. A 1 MeV equivalent electron flux model is used. The solar panel mass and size are taken from Advanced Photovoltaic Solar Array design concepts with 3-mil shielding. Shadowing of the vehicle and low earth orbit atmospheric drag are also modeled. The power system is sized so that end of life output is 30 percent of initial output. Steering of the thrust vector is defined by a three term series in which the coefficients are varied as controls to minimize the total power loss with cumulative exposure in the Van Allen region.
Document ID
19920069471
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Garrison, James L.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Astrodynamics
Report/Patent Number
AIAA PAPER 92-4579
Meeting Information
Meeting: 1992 AIAA/AAS Astrodynamics Conference
Location: Hilton Head Island, SC
Country: United States
Start Date: August 10, 1992
End Date: August 12, 1992
Accession Number
92A52095
Distribution Limits
Public
Copyright
Other

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