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Theoretical basis for the Double Precision Orbit Determination Program /DPODP/. III - Probe trajectoryDifferential motion equations of probe numerically integrated in rectangular coordinate system for probe ephemeris
Document ID
19670005096
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Moyer, T. D. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Date Acquired
August 3, 2013
Publication Date
September 30, 1966
Subject Category
Communications
Accession Number
67N14425
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
EPHEMERIS
SPACECRAFT TRAJECTORY
NUMERICAL INTEGRATION
MOTION EQUATION
DIFFERENTIAL EQUATION
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