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Two locations, two times, and the element setA robust analytical formulation is developed to apply classical initial orbital determination to artificial satellites whose locations are uncertain to about 1 cu km and separated in time by no more than 30 min. An analytical simplification reduces Gauss's method, iteration on the semilatus rectum, iteration on the true anomaly, and the Lambert-Euler technique, to the solution of a single equation in one unknown, instead of the usual coupled triplet of three equations in three unknowns. The method is demonstrated for all common artificial satellite orbits over a variety of time intervals between the two location vectors, and for a varied set of position and distance errors.
Document ID
19860054848
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
External Source(s)
Authors
Taff, L. G.
(Massachusetts Inst. of Tech. Lexington, MA, United States)
Randall, P. M. S.
(MIT Lexington, MA, United States)
Date Acquired
August 12, 2013
Publication Date
October 1, 1985
Publication Information
Publication: Celestial Mechanics
Volume: 37
ISSN: 0008-8714
Subject Category
Astrodynamics
Report/Patent Number
AD-A170553
ESD-TR-86-076
Accession Number
86A39586
Funding Number(s)
CONTRACT_GRANT: NAGW-232
CONTRACT_GRANT: F19628-85-C-0002
Distribution Limits
Public
Copyright
Other

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