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ISEE orbital decay due to lunar third-body perturbationsThe orbital decay of the International Sun-Earth Explorer (ISEE-1) and ISEE-2 spacecraft was studied. The perturbative forces due to the nonspherical components of the earth's gravitational field, atmospheric drag, solar radiation pressure, and third-body perturbations are examined. The dynamics of the earth-spacecraft-moon system is analyzed as well. Various scenarios using the perturbative forces in conjunction with propulsive energy are evaluated to determine the requirements for extending the lifetime of this type of mission.
Document ID
19890025331
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Amenabar, J. P. (Computer Sciences Corp. Silver Spring, MD, United States)
Bobrowsky, M. (Computer Sciences Corp. Silver Spring, MD, United States)
Phenneger, M. C. (Computer Sciences Corp. System Sciences Div., Lanham, MD, United States)
Hoge, S. L. (Computer Sciences Corp. Silver Spring, MD, United States)
Cuevas, O. O. (NASA Goddard Space Flight Center Greenbelt, MD, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1988
Subject Category
Astrodynamics
Report/Patent Number
AAS PAPER 87-535
Report Number: AAS PAPER 87-535
Meeting Information
Meeting: AAS/AIAA Astrodynamics Conference
Location: Kalispell, MT
Country: United States
Start Date: December 6, 1987
End Date: December 9, 1987
Sponsors: AAS, AIAA
Accession Number
89A12702
Funding Number(s)
CONTRACT_GRANT: NAS5-27600
Distribution Limits
Public
Copyright
Other

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