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Integrated propulsion for near-Earth space missions. Volume 2: TechnicalThe calculation approach is described for parametric analysis of candidate electric propulsion systems employed in LEO to GEO missions. Occultation relations, atmospheric density effects, and natural radiation effects are presented. A solar cell cover glass tradeoff is performed to determine optimum glass thickness. Solar array and spacecraft pointing strategies are described for low altitude flight and for optimum array illumination during ascent. Mass ratio tradeoffs versus transfer time provide direction for thruster technology improvements. Integrated electric propulsion analysis is performed for orbit boosting, inclination change, attitude control, stationkeeping, repositioning, and disposal functions as well as power sharing with payload on orbit. Comparison with chemical auxiliary propulsion is made to quantify the advantages of integrated propulsion in terms of weight savings and concomittant launch cost savings.
Document ID
19820025549
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Dailey, C. L.
(TRW Defense and Space Systems Group Redondo Beach, CA, United States)
Meissinger, H. F.
(TRW Defense and Space Systems Group Redondo Beach, CA, United States)
Lovberg, R. H.
(TRW Defense and Space Systems Group Redondo Beach, CA, United States)
Zafran, S.
(TRW Defense and Space Systems Group Redondo Beach, CA, United States)
Date Acquired
September 4, 2013
Publication Date
October 1, 1981
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
TRW-37255-6002-UT-VOL-2
NASA-CR-167889-VOL-2
NAS 1.26:167889-VOL-2
Accession Number
82N33425
Funding Number(s)
CONTRACT_GRANT: NAS3-22661
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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