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Improving the numerical integration solution of satellite orbits in the presence of solar radiation pressure using modified back differencesThe method of modified back differences, a technique that significantly reduces the numerical integration errors associated with crossing shadow boundaries using a fixed-mesh multistep integrator without a significant increase in computer run time, is presented. While Hubbard's integral approach can produce significant improvements to the trajectory solution, the interpolation method provides the best overall results. It is demonstrated that iterating on the point mass term correction is also important for achieving the best overall results. It is also shown that the method of modified back differences can be implemented with only a small increase in execution time.
Document ID
19930033970
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lundberg, J. B.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Feulner, M. R.
(NASA Goddard Space Flight Center Greenbelt, MD, United States)
Abusali, P. A. M.
(Texas Univ. Austin, United States)
Ho, C. S.
(National Cheng Kung Univ. Tainan, Taiwan)
Date Acquired
August 15, 2013
Publication Date
January 1, 1991
Publication Information
Publication: In: Spaceflight mechanics 1991; Proceedings of the 1st AAS(AIAA Annual Spaceflight Mechanics Meeting, Houston, TX, Feb. 11-13, 1991. Pt. 2 (A93-17901 05-13)
Publisher: Univelt, Inc.
Subject Category
Astrodynamics
Report/Patent Number
AAS PAPER 91-187
Accession Number
93A17967
Funding Number(s)
CONTRACT_GRANT: NAG5-940
Distribution Limits
Public
Copyright
Other

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