|
SUPPORT SITE |
|
|
|
SUPPORT SITE |
|
Path: SC/BasicOrbit
% Approximate root to Kepler's Equation for elliptical and hyperbolic orbits.
Since version 1.
--------------------------------------------------------------------------
Form:
eccAnom = M2EApp( e, meanAnom )
--------------------------------------------------------------------------
------
Inputs
------
e (: or 1) Eccentricity
meanAnom (:) Mean anomaly
-------
Outputs
-------
eccAnom (:) Eccentric anomaly
--------------------------------------------------------------------------
References: Battin, R.H. (1987). An Introduction to the
Mathematics and Methods of Astrodynamics, AIAA Press, p. 194.
--------------------------------------------------------------------------
Common: Graphics/Plot2D Math: Linear/DupVect
Back to the SC Module page