Sg-ifying names.

simgear/ephemeris/celestialBody.cxx

@@ -59,12 +59,12 @@ void CelestialBody::updatePosition(double mjd, Star *ourSun)
     xv, yv, xh, yh, zh, xg, yg, zg, xe, ye, ze;
 
   updateOrbElements(mjd);
-  actTime = fgCalcActTime(mjd);
+  actTime = sgCalcActTime(mjd);
 
   // calcualate the angle bewteen ecliptic and equatorial coordinate system
   ecl = DEG_TO_RAD * (23.4393 - 3.563E-7 *actTime);
   
-  eccAnom = fgCalcEccAnom(M, e);  //calculate the eccentric anomaly
+  eccAnom = sgCalcEccAnom(M, e);  //calculate the eccentric anomaly
   xv = a * (cos(eccAnom) - e);
   yv = a * (sqrt (1.0 - e*e) * sin(eccAnom));
   v = atan2(yv, xv);           // the planet's true anomaly
@@ -111,7 +111,7 @@ void CelestialBody::updatePosition(double mjd, Star *ourSun)
 };
 
 /****************************************************************************
- * double CelestialBody::fgCalcEccAnom(double M, double e)
+ * double CelestialBody::sgCalcEccAnom(double M, double e)
  * this private member calculates the eccentric anomaly of a celestial body, 
  * given its mean anomaly and eccentricity.
  * 
@@ -136,7 +136,7 @@ void CelestialBody::updatePosition(double mjd, Star *ourSun)
  * the eccentric anomaly
  *
  ****************************************************************************/
-double CelestialBody::fgCalcEccAnom(double M, double e)
+double CelestialBody::sgCalcEccAnom(double M, double e)
 {
   double 
     eccAnom, E0, E1, diff;

simgear/ephemeris/celestialBody.hxx

@@ -60,8 +60,8 @@ protected:              // make the data protected, in order to give the
   double magnitude;
   double lonEcl, latEcl;
 
-  double fgCalcEccAnom(double M, double e);
+  double sgCalcEccAnom(double M, double e);
-  double fgCalcActTime(double mjd);
+  double sgCalcActTime(double mjd);
   void updateOrbElements(double mjd);
 
 public:
@@ -149,7 +149,7 @@ inline CelestialBody::CelestialBody(double Nf, double Ns,
  ***************************************************************************/
 inline void CelestialBody::updateOrbElements(double mjd)
 {
-  double actTime = fgCalcActTime(mjd);
+  double actTime = sgCalcActTime(mjd);
    M = DEG_TO_RAD * (MFirst + (MSec * actTime));
    w = DEG_TO_RAD * (wFirst + (wSec * actTime));
    N = DEG_TO_RAD * (NFirst + (NSec * actTime));
@@ -158,7 +158,7 @@ inline void CelestialBody::updateOrbElements(double mjd)
    a = aFirst + (aSec * actTime);
 }
 /*****************************************************************************
- * inline double CelestialBody::fgCalcActTime(double mjd)
+ * inline double CelestialBody::sgCalcActTime(double mjd)
  * this private member function returns the offset in days from the epoch for
  * wich the orbital elements are calculated (Jan, 1st, 2000).
  * 
@@ -166,7 +166,7 @@ inline void CelestialBody::updateOrbElements(double mjd)
  *
  * return value: the (fractional) number of days until Jan 1, 2000.
  ****************************************************************************/
-inline double CelestialBody::fgCalcActTime(double mjd)
+inline double CelestialBody::sgCalcActTime(double mjd)
 {
   return (mjd - 36523.5);
 }

simgear/ephemeris/moon.cxx

@@ -88,12 +88,12 @@ void Moon::updatePosition(double mjd, double lst, double lat, Star *ourSun)
     geoRa, geoDec;
   
   updateOrbElements(mjd);
-  actTime = fgCalcActTime(mjd);
+  actTime = sgCalcActTime(mjd);
 
   // calculate the angle between ecliptic and equatorial coordinate system
   // in Radians
   ecl = ((DEG_TO_RAD * 23.4393) - (DEG_TO_RAD * 3.563E-7) * actTime);  
-  eccAnom = fgCalcEccAnom(M, e);  // Calculate the eccentric anomaly
+  eccAnom = sgCalcEccAnom(M, e);  // Calculate the eccentric anomaly
   xv = a * (cos(eccAnom) - e);
   yv = a * (sqrt(1.0 - e*e) * sin(eccAnom));
   v = atan2(yv, xv);               // the moon's true anomaly

simgear/ephemeris/saturn.cxx

@@ -67,7 +67,7 @@ void Saturn::updatePosition(double mjd, Star *ourSun)
 {
   CelestialBody::updatePosition(mjd, ourSun);
   
-  double actTime = fgCalcActTime(mjd);
+  double actTime = sgCalcActTime(mjd);
   double ir = 0.4897394;
   double Nr = 2.9585076 + 6.6672E-7*actTime;
   double B = asin (sin(declination) * cos(ir) - 

simgear/ephemeris/star.cxx

@@ -84,9 +84,9 @@ void Star::updatePosition(double mjd)
 
   updateOrbElements(mjd);
   
-  actTime = fgCalcActTime(mjd);
+  actTime = sgCalcActTime(mjd);
   ecl = DEG_TO_RAD * (23.4393 - 3.563E-7 * actTime); // Angle in Radians
-  eccAnom = fgCalcEccAnom(M, e);  // Calculate the eccentric Anomaly (also known as solving Kepler's equation)
+  eccAnom = sgCalcEccAnom(M, e);  // Calculate the eccentric Anomaly (also known as solving Kepler's equation)
   
   xv = cos(eccAnom) - e;
   yv = sqrt (1.0 - e*e) * sin(eccAnom);