elliptic_to_rectangular.h   elliptic_to_rectangular.h 
/************************************************************************ /************************************************************************
The code in this file is heavily inspired by the TASS17 and GUST86 theories The code in this file is heavily inspired by the TASS17 and GUST86 theories
found on found on
ftp://ftp.imcce.fr/pub/ephem/satel ftp://ftp.imcce.fr/pub/ephem/satel
I (Johannes Gajdosik) have just taken the Fortran code and data I (Johannes Gajdosik) have just taken the Fortran code and data
obtained from above and rearranged it into this piece of software. obtained from above and rearranged it into this piece of software.
I can neigther allow nor forbid the above theories. I can neither allow nor forbid the above theories.
The copyright notice below covers just my work, The copyright notice below covers just my work,
that is the compilation of the data obtained from above that is the compilation of the data obtained from above
into the software supplied in this file. into the software supplied in this file.
Copyright (c) 2005 Johannes Gajdosik Copyright (c) 2005 Johannes Gajdosik
Permission is hereby granted, free of charge, to any person obtaining a Permission is hereby granted, free of charge, to any person obtaining a
copy of this software and associated documentation files (the "Software"), copy of this software and associated documentation files (the "Software"),
to deal in the Software without restriction, including without limitation to deal in the Software without restriction, including without limitation
the rights to use, copy, modify, merge, publish, distribute, sublicense, the rights to use, copy, modify, merge, publish, distribute, sublicense,
skipping to change at line 52 skipping to change at line 52
#endif #endif
/* /*
Given the orbital elements at some time t0 calculate the Given the orbital elements at some time t0 calculate the
rectangular coordinates at time (t0+dt). rectangular coordinates at time (t0+dt).
mu = G*(m1+m2) .. gravitational constant of the two body problem mu = G*(m1+m2) .. gravitational constant of the two body problem
a .. semi major axis a .. semi major axis
n = mean motion = 2*M_PI/(orbit period) n = mean motion = 2*M_PI/(orbit period)
elem[0] .. unused (eigther a or n) elem[0] .. either a (EllipticToRectangularA()) or n (EllipticToRectangul arN())
elem[1] .. L elem[1] .. L
elem[2] .. K=e*cos(Omega+omega) elem[2] .. K=e*cos(Omega+omega)
elem[3] .. H=e*sin(Omega+omega) elem[3] .. H=e*sin(Omega+omega)
elem[4] .. Q=sin(i/2)*cos(Omega) elem[4] .. Q=sin(i/2)*cos(Omega)
elem[5] .. P=sin(i/2)*sin(Omega) elem[5] .. P=sin(i/2)*sin(Omega)
Omega = longitude of ascending node Omega = longitude of ascending node
omega = argument of pericenter omega = argument of pericenter
L = mean longitude = Omega + omega + M L = mean longitude = Omega + omega + M
M = mean anomaly M = mean anomaly
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