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A new trajectory concept for exploring the earth's geomagnetic tailAn innovative trajectory technique for a magnetotail mapping mission is described which can control the apsidal rotation of an elliptical earth orbit and keep its apogee segment inside the tail region. The required apsidal rotation rate of approximately 1 deg/day is achieved by using the moon to carry out a prescribed sequence of gravity-assist maneuvers. Apogee distances are alternately raised and lowered by the lunar-swingby maneuvers; several categories of the 'sun-synchronous' swingby trajectories are identified. The strength and flexibility of the new trajectory concept is demonstrated by using real-world simulations showing that a large variety of trajectory shapes can be used to explore the earth's geomagnetic tail between 60 and 250 R sub E.
Document ID
19810038570
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Farquhar, R. W.
(NASA Goddard Space Flight Center Greenbelt, Md., United States)
Dunham, D. W.
(Computer Sciences Corp. Silver Spring, Mo., United States)
Date Acquired
August 11, 2013
Publication Date
April 1, 1981
Subject Category
Astrodynamics
Report/Patent Number
AIAA PAPER 80-0112
Accession Number
81A22974
Distribution Limits
Public
Copyright
Other

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