158 lines
5.0 KiB
C++
158 lines
5.0 KiB
C++
/**************************************************************************
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* celestialBody.cxx
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* Written by Durk Talsma. Originally started October 1997, for distribution
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* with the FlightGear project. Version 2 was written in August and
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* September 1998. This code is based upon algorithms and data kindly
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* provided by Mr. Paul Schlyter. (pausch@saaf.se).
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*
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* This program is free software; you can redistribute it and/or
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* modify it under the terms of the GNU General Public License as
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* published by the Free Software Foundation; either version 2 of the
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* License, or (at your option) any later version.
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*
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* This program is distributed in the hope that it will be useful, but
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* WITHOUT ANY WARRANTY; without even the implied warranty of
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* MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU
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* General Public License for more details.
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*
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* You should have received a copy of the GNU General Public License
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* along with this program; if not, write to the Free Software
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* Foundation, Inc., 675 Mass Ave, Cambridge, MA 02139, USA.
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*
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* $Id$
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* (Log is kept at end of this file)
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**************************************************************************/
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#include "celestialBody.hxx"
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#include "star.hxx"
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#include <Debug/logstream.hxx>
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#ifdef __BORLANDC__
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# define exception c_exception
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#endif
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#include <math.h>
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/**************************************************************************
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* void CelestialBody::updatePosition(fgTIME *t, Star *ourSun)
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*
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* Basically, this member function provides a general interface for
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* calculating the right ascension and declinaion. This function is
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* used for calculating the planetary positions. For the planets, an
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* overloaded member function is provided to additionally calculate the
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* planet's magnitude.
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* The sun and moon have their own overloaded updatePosition member, as their
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* position is calculated an a slightly different manner.
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*
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* arguments:
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* fgTIME t: provides the current time.
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* Star *ourSun: the sun's position is needed to convert heliocentric
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* coordinates into geocentric coordinates.
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*
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* return value: none
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*
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*************************************************************************/
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void CelestialBody::updatePosition(fgTIME *t, Star *ourSun)
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{
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double eccAnom, v, ecl, actTime,
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xv, yv, xh, yh, zh, xg, yg, zg, xe, ye, ze;
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updateOrbElements(t);
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actTime = fgCalcActTime(t);
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// calcualate the angle bewteen ecliptic and equatorial coordinate system
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ecl = DEG_TO_RAD * (23.4393 - 3.563E-7 *actTime);
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eccAnom = fgCalcEccAnom(M, e); //calculate the eccentric anomaly
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xv = a * (cos(eccAnom) - e);
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yv = a * (sqrt (1.0 - e*e) * sin(eccAnom));
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v = atan2(yv, xv); // the planet's true anomaly
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r = sqrt (xv*xv + yv*yv); // the planet's distance
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// calculate the planet's position in 3D space
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xh = r * (cos(N) * cos(v+w) - sin(N) * sin(v+w) * cos(i));
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yh = r * (sin(N) * cos(v+w) + cos(N) * sin(v+w) * cos(i));
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zh = r * (sin(v+w) * sin(i));
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// calculate the ecliptic longitude and latitude
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xg = xh + ourSun->getxs();
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yg = yh + ourSun->getys();
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zg = zh;
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xe = xg;
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ye = yg * cos(ecl) - zg * sin(ecl);
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ze = yg * sin(ecl) + zg * cos(ecl);
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rightAscension = atan2(ye, xe);
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declination = atan2(ze, sqrt(xe*xe + ye*ye));
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FG_LOG(FG_GENERAL, FG_INFO, "Planet found at : "
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<< rightAscension << " (ra), " << declination << " (dec)" );
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//calculate some variables specific to calculating the magnitude
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//of the planet
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R = sqrt (xg*xg + yg*yg + zg*zg);
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s = ourSun->getDistance();
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FV = RAD_TO_DEG * acos( (r*r + R*R - s*s) / (2*r*R));
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};
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/****************************************************************************
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* double CelestialBody::fgCalcEccAnom(double M, double e)
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* this private member calculates the eccentric anomaly of a celestial body,
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* given its mean anomaly and eccentricity.
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*
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* -Mean anomaly: the approximate angle between the perihelion and the current
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* position. this angle increases uniformly with time.
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*
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* True anomaly: the actual angle between perihelion and current position.
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*
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* Eccentric anomaly: this is an auxilary angle, used in calculating the true
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* anomaly from the mean anomaly.
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*
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* -eccentricity. Indicates the amount in which the orbit deviates from a
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* circle (0 = circle, 0-1, is ellipse, 1 = parabola, > 1 = hyperbola).
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*
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* This function is also known as solveKeplersEquation()
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*
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* arguments:
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* M: the mean anomaly
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* e: the eccentricity
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*
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* return value:
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* the eccentric anomaly
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*
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****************************************************************************/
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double CelestialBody::fgCalcEccAnom(double M, double e)
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{
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double
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eccAnom, E0, E1, diff;
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eccAnom = M + e * sin(M) * (1.0 + e * cos (M));
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// iterate to achieve a greater precision for larger eccentricities
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if (e > 0.05)
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{
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E0 = eccAnom;
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do
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{
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E1 = E0 - (E0 - e * sin(E0) - M) / (1 - e *cos(E0));
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diff = fabs(E0 - E1);
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E0 = E1;
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}
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while (diff > (DEG_TO_RAD * 0.001));
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return E0;
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}
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return eccAnom;
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}
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