Nu2M:

Path: Orbit/OrbitMechanics

% Converts true anomaly to mean anomaly.

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   Form:
   [meanAnom,eccAnom] = Nu2M( e, nu )
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   ------
   Inputs
   ------
   e             (1,1)  Eccentricity
   nu            (1,:)  True anomaly

   -------
   Outputs
   -------
   meanAnom       (1,:)  Mean anomaly
   eccAnom        (1,:)  Eccentric anomaly

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Children:

Orbit: OrbitMechanics/E2M
Orbit: OrbitMechanics/Nu2E
Common: Graphics/Plot2D

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