Path: Orbit/OrbitMechanics
% Computes a polar lunar orbit
--------------------------------------------------------------------------
Form:
x = LunarPolarOrbit( a, e, jD )
--------------------------------------------------------------------------
-------
Inputs
-------
a (1,1) Semi-major axis
e (1,1) Eccentricity
jD (1,1) Julian date
-------
Outputs
-------
x (6,1) [r;v] (km,km/s) ECI
--------------------------------------------------------------------------
SC: BasicOrbit/El2RV SC: Ephem/MoonRot Common: Database/Constant Common: Quaternion/QForm Common: Quaternion/U2Q Math: Linear/Unit
Back to the Orbit Module page