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True Anomaly, `nu`[E]

Last modified by
on
Sep 15, 2020, 12:34:53 AM
Created by
on
May 27, 2014, 7:32:04 PM
`nu = arccos( (cos(E) - e) / ( 1-e*cos(E)) )`
`(e)"Eccentricity"`
`(E)"Eccentric Anomaly"`
Tags
Astronomy Orbital Mechanics Astronomical Satellites true anomaly
UUID
94fa3b89-e5d5-11e3-b7aa-bc764e2038f2

The True Anomaly calculator computes the True Anomaly (ν) of an orbit from the inputs:

True Anomaly (ν): The True Anomaly is the angle between the direction of periapsis and the current position of the body.

/attachments/94fa3b89-e5d5-11e3-b7aa-bc764e2038f2/TrueAnomalynuE-illustration.png
This equation, True Anomaly, `nu`[E], references 1 page
This equation, True Anomaly, `nu`[E], is used in 1 page
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