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core/planetsephems/elliptic_to_rectangular.h

00001 /************************************************************************
00002 
00003 The code in this file is heavily inspired by the TASS17 and GUST86 theories
00004 found on
00005 ftp://ftp.imcce.fr/pub/ephem/satel
00006 
00007 I (Johannes Gajdosik) have just taken the Fortran code and data
00008 obtained from above and rearranged it into this piece of software.
00009 
00010 I can neigther allow nor forbid the above theories.
00011 The copyright notice below covers just my work,
00012 that is the compilation of the data obtained from above
00013 into the software supplied in this file.
00014 
00015 
00016 Copyright (c) 2005 Johannes Gajdosik
00017 
00018 Permission is hereby granted, free of charge, to any person obtaining a
00019 copy of this software and associated documentation files (the "Software"),
00020 to deal in the Software without restriction, including without limitation
00021 the rights to use, copy, modify, merge, publish, distribute, sublicense,
00022 and/or sell copies of the Software, and to permit persons to whom the
00023 Software is furnished to do so, subject to the following conditions:
00024 
00025 The above copyright notice and this permission notice shall be included
00026 in all copies or substantial portions of the Software.
00027 
00028 THE SOFTWARE IS PROVIDED "AS IS", WITHOUT WARRANTY OF ANY KIND, EXPRESS OR
00029 IMPLIED, INCLUDING BUT NOT LIMITED TO THE WARRANTIES OF MERCHANTABILITY,
00030 FITNESS FOR A PARTICULAR PURPOSE AND NONINFRINGEMENT. IN NO EVENT SHALL THE
00031 AUTHORS OR COPYRIGHT HOLDERS BE LIABLE FOR ANY CLAIM, DAMAGES OR OTHER
00032 LIABILITY, WHETHER IN AN ACTION OF CONTRACT, TORT OR OTHERWISE, ARISING FROM,
00033 OUT OF OR IN CONNECTION WITH THE SOFTWARE OR THE USE OR OTHER DEALINGS IN THE
00034 SOFTWARE.
00035 
00036 ****************************************************************/
00037 
00038 #ifndef _ELLIPTIC_TO_RECTANGULAR_
00039 #define _ELLIPTIC_TO_RECTANGULAR_
00040 
00041 #ifdef __cplusplus
00042 extern "C" {
00043 #endif
00044 
00045 /*
00046    Given the orbital elements at some time t0 calculate the
00047    rectangular coordinates at time (t0+dt).
00048    
00049    mu = G*(m1+m2) .. gravitational constant of the two body problem
00050    a .. semi major axis
00051    n = mean motion = 2*M_PI/(orbit period)
00052    
00053    elem[0] .. unused (eigther a or n)
00054    elem[1] .. L
00055    elem[2] .. K=e*cos(Omega+omega)
00056    elem[3] .. H=e*sin(Omega+omega)
00057    elem[4] .. Q=sin(i/2)*cos(Omega)
00058    elem[5] .. P=sin(i/2)*sin(Omega)
00059    
00060    Omega = longitude of ascending node
00061    omega = argument of pericenter
00062    L = mean longitude = Omega + omega + M
00063    M = mean anomaly
00064    i = inclination
00065    e = excentricity
00066    
00067    Units are suspected to be: Julian days, AU, rad
00068 */
00069 
00070 void EllipticToRectangularN(double mu,const double elem[6],double dt,
00071                             double xyz[]);
00072 void EllipticToRectangularA(double mu,const double elem[6],double dt,
00073                             double xyz[]);
00074 
00075 #ifdef __cplusplus
00076 }
00077 #endif
00078 
00079 #endif