/usr/include/simgear/ephemeris/celestialBody.hxx is in libsimgear-dev 3.0.0-1.
This file is owned by root:root, with mode 0o644.
The actual contents of the file can be viewed below.
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* celestialBody.hxx
* Written by Durk Talsma. Originally started October 1997, for distribution
* with the FlightGear project. Version 2 was written in August and
* September 1998. This code is based upon algorithms and data kindly
* provided by Mr. Paul Schlyter. (pausch@saaf.se).
*
* This library is free software; you can redistribute it and/or
* modify it under the terms of the GNU Library General Public
* License as published by the Free Software Foundation; either
* version 2 of the License, or (at your option) any later version.
*
* This library is distributed in the hope that it will be useful,
* but WITHOUT ANY WARRANTY; without even the implied warranty of
* MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU
* Library General Public License for more details.
*
* You should have received a copy of the GNU General Public License
* along with this program; if not, write to the Free Software
* Foundation, Inc., 51 Franklin Street, Fifth Floor, Boston, MA 02110-1301, USA.
*
* $Id$
**************************************************************************/
#ifndef _CELESTIALBODY_H_
#define _CELESTIALBODY_H_
#ifndef __cplusplus
# error This library requires C++
#endif
#include <simgear/constants.h>
class Star;
class CelestialBody
{
protected: // make the data protected, in order to give the
// inherited classes direct access to the data
double NFirst; /* longitude of the ascending node first part */
double NSec; /* longitude of the ascending node second part */
double iFirst; /* inclination to the ecliptic first part */
double iSec; /* inclination to the ecliptic second part */
double wFirst; /* first part of argument of perihelion */
double wSec; /* second part of argument of perihelion */
double aFirst; /* semimayor axis first part*/
double aSec; /* semimayor axis second part */
double eFirst; /* eccentricity first part */
double eSec; /* eccentricity second part */
double MFirst; /* Mean anomaly first part */
double MSec; /* Mean anomaly second part */
double N, i, w, a, e, M; /* the resulting orbital elements, obtained from the former */
double rightAscension, declination;
double r, R, s, FV;
double magnitude;
double lonEcl, latEcl;
double sgCalcEccAnom(double M, double e);
double sgCalcActTime(double mjd);
void updateOrbElements(double mjd);
public:
CelestialBody(double Nf, double Ns,
double If, double Is,
double wf, double ws,
double af, double as,
double ef, double es,
double Mf, double Ms, double mjd);
CelestialBody(double Nf, double Ns,
double If, double Is,
double wf, double ws,
double af, double as,
double ef, double es,
double Mf, double Ms);
void getPos(double *ra, double *dec);
void getPos(double *ra, double *dec, double *magnitude);
double getRightAscension();
double getDeclination();
double getMagnitude();
double getLon() const;
double getLat() const;
void updatePosition(double mjd, Star *ourSun);
};
inline double CelestialBody::getRightAscension() { return rightAscension; }
inline double CelestialBody::getDeclination() { return declination; }
inline double CelestialBody::getMagnitude() { return magnitude; }
inline double CelestialBody::getLon() const
{
return lonEcl;
}
inline double CelestialBody::getLat() const
{
return latEcl;
}
#endif // _CELESTIALBODY_H_
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