Spacecraft.ModifiedEquinoctialH Property |
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DescriptionThe h component of the Modified Equinoctial element set, defined by: h = tan(i/2)*cos(RAAN) where i is the orbit inclination and RAAN is the Keplerian Right Ascension of the Ascending Node. These orbit properties are with respect to the Mean of J2000 Earth-Equator coordinate frame.
Timing Precision Mode This page describes functionality in millisecond timing precision mode. Click here to see the documentation for this object in nanosecond timing precision mode.
Attributes
Syntax
See also Coverage and Contact Analysis Guide
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