/// <summary>
/// Creates a instance of the class from geodetic coordinates.
/// </summary>
/// <param name="geo">The geocentric coordinates.</param>
/// <param name="date">The Julian date.</param>
/// <remarks>
/// Assumes the Earth is an oblate spheroid.
/// Reference: The 1992 Astronomical Almanac, page K11
/// Reference: www.celestrak.com (Dr. T.S. Kelso)
/// </remarks>
public Eci(Geo geo, Julian date)
{
double lat = geo.LatitudeRad;
double lon = geo.LongitudeRad;
double alt = geo.Altitude;
// Calculate Local Mean Sidereal Time (theta)
double theta = date.ToLmst(lon);
double c = 1.0 / Math.Sqrt(1.0 + Globals.F * (Globals.F - 2.0) *
Globals.Sqr(Math.Sin(lat)));
double s = Globals.Sqr(1.0 - Globals.F) * c;
double achcp = (Globals.Xkmper * c + alt) * Math.Cos(lat);
Position = new Vector();
Position.X = achcp * Math.Cos(theta); // km
Position.Y = achcp * Math.Sin(theta); // km
Position.Z = (Globals.Xkmper * s + alt) * Math.Sin(lat); // km
Position.W = Math.Sqrt(Globals.Sqr(Position.X) +
Globals.Sqr(Position.Y) +
Globals.Sqr(Position.Z)); // range, km
Velocity = new Vector();
double mfactor = Globals.TwoPi * (Globals.OmegaE / Globals.SecPerDay);
Velocity.X = -mfactor * Position.Y; // km / sec
Velocity.Y = mfactor * Position.X; // km / sec
Velocity.Z = 0.0; // km / sec
Velocity.W = Math.Sqrt(Globals.Sqr(Velocity.X) + // range rate km/sec^2
Globals.Sqr(Velocity.Y));
}
/// <summary>
/// Creates a instance of the class from geodetic coordinates.
/// </summary>
/// <param name="geo">The geocentric coordinates.</param>
/// <param name="date">The Julian date.</param>
/// <remarks>
/// Assumes the Earth is an oblate spheroid.
/// Reference: The 1992 Astronomical Almanac, page K11
/// Reference: www.celestrak.com (Dr. T.S. Kelso)
/// </remarks>
public Eci(Geo geo, Julian date)
{
double lat = geo.LatitudeRad;
double lon = geo.LongitudeRad;
double alt = geo.Altitude;
// Calculate Local Mean Sidereal Time (theta)
double theta = date.ToLmst(lon);
double c = 1.0 / Math.Sqrt(1.0 + Globals.F * (Globals.F - 2.0) *
Globals.Sqr(Math.Sin(lat)));
double s = Globals.Sqr(1.0 - Globals.F) * c;
double achcp = (Globals.Xkmper * c + alt) * Math.Cos(lat);
Position = new Vector();
Position.X = achcp * Math.Cos(theta); // km
Position.Y = achcp * Math.Sin(theta); // km
Position.Z = (Globals.Xkmper * s + alt) * Math.Sin(lat); // km
Position.W = Math.Sqrt(Globals.Sqr(Position.X) +
Globals.Sqr(Position.Y) +
Globals.Sqr(Position.Z)); // range, km
Velocity = new Vector();
double mfactor = Globals.TwoPi * (Globals.OmegaE / Globals.SecPerDay);
Velocity.X = -mfactor * Position.Y; // km / sec
Velocity.Y = mfactor * Position.X; // km / sec
Velocity.Z = 0.0; // km / sec
Velocity.W = Math.Sqrt(Globals.Sqr(Velocity.X) + // range rate km/sec^2
Globals.Sqr(Velocity.Y));
}
/// <summary>
/// Returns the topo-centric (azimuth, elevation, etc.) coordinates for
/// a target object described by the given ECI coordinates.
/// </summary>
/// <param name="eci">The ECI coordinates of the target object.</param>
/// <returns>The look angle to the target object.</returns>
public TopoTime GetLookAngle(EciTime eci)
{
// Calculate the ECI coordinates for this Site object at the time
// of interest.
Julian date = eci.Date;
EciTime eciSite = PositionEci(date);
Vector vecRgRate = new Vector(eci.Velocity.X - eciSite.Velocity.X,
eci.Velocity.Y - eciSite.Velocity.Y,
eci.Velocity.Z - eciSite.Velocity.Z);
double x = eci.Position.X - eciSite.Position.X;
double y = eci.Position.Y - eciSite.Position.Y;
double z = eci.Position.Z - eciSite.Position.Z;
double w = Math.Sqrt(Globals.Sqr(x) + Globals.Sqr(y) + Globals.Sqr(z));
Vector vecRange = new Vector(x, y, z, w);
// The site's Local Mean Sidereal Time at the time of interest.
double theta = date.ToLmst(LongitudeRad);
double sin_lat = Math.Sin(LatitudeRad);
double cos_lat = Math.Cos(LatitudeRad);
double sin_theta = Math.Sin(theta);
double cos_theta = Math.Cos(theta);
double top_s = sin_lat * cos_theta * vecRange.X +
sin_lat * sin_theta * vecRange.Y -
cos_lat * vecRange.Z;
double top_e = -sin_theta * vecRange.X +
cos_theta * vecRange.Y;
double top_z = cos_lat * cos_theta * vecRange.X +
cos_lat * sin_theta * vecRange.Y +
sin_lat * vecRange.Z;
double az = Math.Atan(-top_e / top_s);
if (top_s > 0.0)
{
az += Globals.Pi;
}
if (az < 0.0)
{
az += 2.0 * Globals.Pi;
}
double el = Math.Asin(top_z / vecRange.W);
double rate = (vecRange.X * vecRgRate.X +
vecRange.Y * vecRgRate.Y +
vecRange.Z * vecRgRate.Z) / vecRange.W;
TopoTime topo = new TopoTime(az, // azimuth, radians
el, // elevation, radians
vecRange.W, // range, km
rate, // rate, km / sec
eci.Date);
#if WANT_ATMOSPHERIC_CORRECTION
// Elevation correction for atmospheric refraction.
// Reference: Astronomical Algorithms by Jean Meeus, pp. 101-104
// Note: Correction is meaningless when apparent elevation is below horizon
topo.ElevationRad += Globals.ToRadians((1.02 /
Math.Tan(Globals.ToRadians(Globals.ToDegrees(el) + 10.3 /
(Globals.ToDegrees(el) + 5.11)))) / 60.0);
if (topo.ElevationRad < 0.0)
{
topo.ElevationRad = el; // Reset to true elevation
}
if (topo.ElevationRad > (Math.PI / 2.0))
{
topo.ElevationRad = (Math.PI / 2.0);
}
#endif
return(topo);
}
