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Pines method for circular and elliptical orbitsThe Pines method for trajectory integration is derived from the equations of two-body motion. The concept of the perturbation derivative is explained and a formal definition is presented. An algorithm for applying the Pines method to numerical integration of trajectories is included.
Document ID
19760014147
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Semar, C. (Lockheed Electronics Co. Houston, TX, United States)
Date Acquired
September 3, 2013
Publication Date
February 1, 1976
Subject Category
Astrodynamics
Report/Patent Number
NASA-CR-147538
LEC-7951
JSC-10924
Report Number: NASA-CR-147538
Report Number: LEC-7951
Report Number: JSC-10924
Accession Number
76N21235
Funding Number(s)
CONTRACT_GRANT: NAS9-12200
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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