Path: SC/Ephem
% Generate the moon vector in an earth or spacecraft centered frame.
The earth-centered inertial frame is default or, if a spacecraft vector is
input, the vector is in the spacecraft centered frame.
This is the moderate precision model.
See also MoonV1.
Since version 1.
--------------------------------------------------------------------------
Form:
[u, r] = MoonV2( jD, rSc )
--------------------------------------------------------------------------
Inputs
------
jd (:) Julian date
rsc (:) Spacecraft vector in the ECI frame (km)
-------
Outputs
-------
u (3,:) Unit moon vector
r (:) Distance from origin to moon (km)
--------------------------------------------------------------------------
References: Montenbruck, O., T.Pfleger, Astronomy on the Personal
Computer, Springer-Verlag, Berlin, 1991, pp. 103-111.
--------------------------------------------------------------------------
Common: Time/DTSToDTA Common: Time/Date2JD Math: Linear/Mag Math: Linear/Unit
Back to the SC Module page