public static AstroRaDec GetPlanet(double jDate, EO planetIn, double locLat, double locLong, double locHeight)
{
int planet = (int)planetIn;
//C++ TO C# CONVERTER NOTE: This static local variable declaration (not allowed in C#) has been moved just prior to the method:
// static CAAGalileanMoonsDetails galDetails;
//C++ TO C# CONVERTER NOTE: This static local variable declaration (not allowed in C#) has been moved just prior to the method:
// static CAAEllipticalPlanetaryDetails jupDetails;
//C++ TO C# CONVERTER NOTE: This static local variable declaration (not allowed in C#) has been moved just prior to the method:
// static CAAPhysicalJupiterDetails jupPhisical;
//C++ TO C# CONVERTER NOTE: This static local variable declaration (not allowed in C#) has been moved just prior to the method:
// static double jDateLast = 0;
locLong = -locLong;
if (planet < 9)
{
EPD Details = ELL.Calculate(jDate, planetIn);
COR corrected = CAAParallax.Equatorial2Topocentric(Details.ApparentGeocentricRA, Details.ApparentGeocentricDeclination, Details.ApparentGeocentricDistance, locLong, locLat, locHeight, jDate);
return(new AstroRaDec(corrected.X, corrected.Y, Details.ApparentGeocentricDistance, false, false));
}
else if (planet == 9)
{
double lat = CAAMoon.EclipticLatitude(jDate);
double lng = CAAMoon.EclipticLongitude(jDate);
double dis = CAAMoon.RadiusVector(jDate) / 149598000;
double epsilon = CAANutation.TrueObliquityOfEcliptic(jDate);
COR d = CT.Ec2Eq(lng, lat, epsilon);
COR corrected = CAAParallax.Equatorial2Topocentric(d.X, d.Y, dis, locLong, locLat, locHeight, jDate);
return(new AstroRaDec(corrected.X, corrected.Y, dis, false, false));
}
else
{
if (jDate != jDateLast)
{
jupDetails = ELL.Calculate(jDate, (EO)4);
jupPhisical = CAAPhysicalJupiter.Calculate(jDate);
COR corrected = CAAParallax.Equatorial2Topocentric(jupDetails.ApparentGeocentricRA, jupDetails.ApparentGeocentricDeclination, jupDetails.ApparentGeocentricDistance, locLong, locLat, locHeight, jDate);
jupDetails.ApparentGeocentricRA = corrected.X;
jupDetails.ApparentGeocentricDeclination = corrected.Y;
galDetails = GM.Calculate(jDate);
jDateLast = jDate;
}
double jupiterDiameter = 0.000954501;
double scale = (Math.Atan(.5 * (jupiterDiameter / jupDetails.ApparentGeocentricDistance))) / 3.1415927 * 180;
double raScale = (scale / Math.Cos(jupDetails.ApparentGeocentricDeclination / 180.0 * 3.1415927)) / 15;
double xMoon = 0;
double yMoon = 0;
double zMoon = 0;
bool shadow = false;
bool eclipsed = false;
switch (planet)
{
case 10: // IO
xMoon = galDetails.Satellite1.ApparentRectangularCoordinates.X;
yMoon = galDetails.Satellite1.ApparentRectangularCoordinates.Y;
zMoon = galDetails.Satellite1.ApparentRectangularCoordinates.Z;
eclipsed = galDetails.Satellite1.bInEclipse;
shadow = galDetails.Satellite1.bInShadowTransit;
break;
case 11: //Europa
xMoon = galDetails.Satellite2.ApparentRectangularCoordinates.X;
yMoon = galDetails.Satellite2.ApparentRectangularCoordinates.Y;
zMoon = galDetails.Satellite2.ApparentRectangularCoordinates.Z;
eclipsed = galDetails.Satellite2.bInEclipse;
shadow = galDetails.Satellite2.bInShadowTransit;
break;
case 12: //Ganymede
xMoon = galDetails.Satellite3.ApparentRectangularCoordinates.X;
yMoon = galDetails.Satellite3.ApparentRectangularCoordinates.Y;
zMoon = galDetails.Satellite3.ApparentRectangularCoordinates.Z;
eclipsed = galDetails.Satellite3.bInEclipse;
shadow = galDetails.Satellite3.bInShadowTransit;
break;
case 13: //Callisto
xMoon = galDetails.Satellite4.ApparentRectangularCoordinates.X;
yMoon = galDetails.Satellite4.ApparentRectangularCoordinates.Y;
zMoon = galDetails.Satellite4.ApparentRectangularCoordinates.Z;
eclipsed = galDetails.Satellite4.bInEclipse;
shadow = galDetails.Satellite4.bInShadowTransit;
break;
case 14: // IO Shadow
xMoon = galDetails.Satellite1.ApparentShadowRectangularCoordinates.X;
yMoon = galDetails.Satellite1.ApparentShadowRectangularCoordinates.Y;
zMoon = galDetails.Satellite1.ApparentShadowRectangularCoordinates.Z * .9;
shadow = galDetails.Satellite1.bInShadowTransit;
break;
case 15: //Europa Shadow
xMoon = galDetails.Satellite2.ApparentShadowRectangularCoordinates.X;
yMoon = galDetails.Satellite2.ApparentShadowRectangularCoordinates.Y;
zMoon = galDetails.Satellite2.ApparentShadowRectangularCoordinates.Z * .9;
shadow = galDetails.Satellite2.bInShadowTransit;
break;
case 16: //Ganymede Shadow
xMoon = galDetails.Satellite3.ApparentShadowRectangularCoordinates.X;
yMoon = galDetails.Satellite3.ApparentShadowRectangularCoordinates.Y;
zMoon = galDetails.Satellite3.ApparentShadowRectangularCoordinates.Z * .9;
shadow = galDetails.Satellite3.bInShadowTransit;
break;
case 17: //Callisto Shadow
xMoon = galDetails.Satellite4.ApparentShadowRectangularCoordinates.X;
yMoon = galDetails.Satellite4.ApparentShadowRectangularCoordinates.Y;
zMoon = galDetails.Satellite4.ApparentShadowRectangularCoordinates.Z * .9;
shadow = galDetails.Satellite4.bInShadowTransit;
break;
}
double xTemp;
double yTemp;
double radians = jupPhisical.P / 180.0 * 3.1415927;
xTemp = xMoon * Math.Cos(radians) - yMoon * Math.Sin(radians);
yTemp = xMoon * Math.Sin(radians) + yMoon * Math.Cos(radians);
xMoon = xTemp;
yMoon = yTemp;
return(new AstroRaDec(jupDetails.ApparentGeocentricRA - (xMoon * raScale), jupDetails.ApparentGeocentricDeclination + yMoon * scale, jupDetails.ApparentGeocentricDistance + (zMoon * jupiterDiameter / 2), shadow, eclipsed));
}
}
public static CAAParabolicObjectDetails Calculate(double JD, CAAParabolicObjectElements elements)
{
double Epsilon = CAANutation.MeanObliquityOfEcliptic(elements.JDEquinox);
double JD0 = JD;
//What will be the return value
CAAParabolicObjectDetails details = new CAAParabolicObjectDetails();
Epsilon = CT.D2R(Epsilon);
double omega = CT.D2R(elements.omega);
double w = CT.D2R(elements.w);
double i = CT.D2R(elements.i);
double sinEpsilon = Math.Sin(Epsilon);
double cosEpsilon = Math.Cos(Epsilon);
double sinOmega = Math.Sin(omega);
double cosOmega = Math.Cos(omega);
double cosi = Math.Cos(i);
double sini = Math.Sin(i);
double F = cosOmega;
double G = sinOmega * cosEpsilon;
double H = sinOmega * sinEpsilon;
double P = -sinOmega * cosi;
double Q = cosOmega * cosi * cosEpsilon - sini * sinEpsilon;
double R = cosOmega * cosi * sinEpsilon + sini * cosEpsilon;
double a = Math.Sqrt(F * F + P * P);
double b = Math.Sqrt(G * G + Q * Q);
double c = Math.Sqrt(H * H + R * R);
double A = Math.Atan2(F, P);
double B = Math.Atan2(G, Q);
double C = Math.Atan2(H, R);
C3D SunCoord = CAASun.EquatorialRectangularCoordinatesAnyEquinox(JD, elements.JDEquinox);
for (int j = 0; j < 2; j++)
{
double W = 0.03649116245 / (elements.q * Math.Sqrt(elements.q)) * (JD0 - elements.T);
double s = CalculateBarkers(W);
double v = 2 * Math.Atan(s);
double r = elements.q * (1 + s * s);
double x = r * a * Math.Sin(A + w + v);
double y = r * b * Math.Sin(B + w + v);
double z = r * c * Math.Sin(C + w + v);
if (j == 0)
{
details.HeliocentricRectangularEquatorial.X = x;
details.HeliocentricRectangularEquatorial.Y = y;
details.HeliocentricRectangularEquatorial.Z = z;
//Calculate the heliocentric ecliptic coordinates also
double u = omega + v;
double cosu = Math.Cos(u);
double sinu = Math.Sin(u);
details.HeliocentricRectangularEcliptical.X = r * (cosOmega * cosu - sinOmega * sinu * cosi);
details.HeliocentricRectangularEcliptical.Y = r * (sinOmega * cosu + cosOmega * sinu * cosi);
details.HeliocentricRectangularEcliptical.Z = r * sini * sinu;
details.HeliocentricEclipticLongitude = Math.Atan2(y, x);
details.HeliocentricEclipticLongitude = CT.M24(CT.R2D(details.HeliocentricEclipticLongitude) / 15);
details.HeliocentricEclipticLatitude = Math.Asin(z / r);
details.HeliocentricEclipticLatitude = CT.R2D(details.HeliocentricEclipticLatitude);
}
double psi = SunCoord.X + x;
double nu = SunCoord.Y + y;
double sigma = SunCoord.Z + z;
double Alpha = Math.Atan2(nu, psi);
Alpha = CT.R2D(Alpha);
double Delta = Math.Atan2(sigma, Math.Sqrt(psi * psi + nu * nu));
Delta = CT.R2D(Delta);
double Distance = Math.Sqrt(psi * psi + nu * nu + sigma * sigma);
if (j == 0)
{
details.TrueGeocentricRA = CT.M24(Alpha / 15);
details.TrueGeocentricDeclination = Delta;
details.TrueGeocentricDistance = Distance;
details.TrueGeocentricLightTime = ELL.DistanceToLightTime(Distance);
}
else
{
details.AstrometricGeocenticRA = CT.M24(Alpha / 15);
details.AstrometricGeocentricDeclination = Delta;
details.AstrometricGeocentricDistance = Distance;
details.AstrometricGeocentricLightTime = ELL.DistanceToLightTime(Distance);
double RES = Math.Sqrt(SunCoord.X * SunCoord.X + SunCoord.Y * SunCoord.Y + SunCoord.Z * SunCoord.Z);
details.Elongation = CT.R2D(Math.Acos((RES * RES + Distance * Distance - r * r) / (2 * RES * Distance)));
details.PhaseAngle = CT.R2D(Math.Acos((r * r + Distance * Distance - RES * RES) / (2 * r * Distance)));
}
if (j == 0) //Prepare for the next loop around
{
JD0 = JD - details.TrueGeocentricLightTime;
}
}
return(details);
}
//Static methods
//////////////////////////////// Implementation ///////////////////////////////
public static CAASaturnRingDetails Calculate(double JD)
{
//What will be the return value
CAASaturnRingDetails details = new CAASaturnRingDetails();
double T = (JD - 2451545) / 36525;
double T2 = T * T;
//Step 1. Calculate the inclination of the plane of the ring and the longitude of the ascending node referred to the ecliptic and mean equinox of the date
double i = 28.075216 - 0.012998 * T + 0.000004 * T2;
double irad = CT.D2R(i);
double omega = 169.508470 + 1.394681 * T + 0.000412 * T2;
double omegarad = CT.D2R(omega);
//Step 2. Calculate the heliocentric longitude, latitude and radius vector of the Earth in the FK5 system
double l0 = CAAEarth.EclipticLongitude(JD);
double b0 = CAAEarth.EclipticLatitude(JD);
l0 += CAAFK5.CorrectionInLongitude(l0, b0, JD);
double l0rad = CT.D2R(l0);
b0 += CAAFK5.CorrectionInLatitude(l0, JD);
double b0rad = CT.D2R(b0);
double R = CAAEarth.RadiusVector(JD);
//Step 3. Calculate the corresponding coordinates l,b,r for Saturn but for the instance t-lightraveltime
double DELTA = 9;
double PreviousEarthLightTravelTime = 0;
double EarthLightTravelTime = ELL.DistanceToLightTime(DELTA);
double JD1 = JD - EarthLightTravelTime;
bool bIterate = true;
double x = 0;
double y = 0;
double z = 0;
double l = 0;
double b = 0;
double r = 0;
while (bIterate)
{
//Calculate the position of Saturn
l = CAASaturn.EclipticLongitude(JD1);
b = CAASaturn.EclipticLatitude(JD1);
l += CAAFK5.CorrectionInLongitude(l, b, JD1);
b += CAAFK5.CorrectionInLatitude(l, JD1);
double lrad = CT.D2R(l);
double brad = CT.D2R(b);
r = CAASaturn.RadiusVector(JD1);
//Step 4
x = r * Math.Cos(brad) * Math.Cos(lrad) - R * Math.Cos(l0rad);
y = r * Math.Cos(brad) * Math.Sin(lrad) - R * Math.Sin(l0rad);
z = r * Math.Sin(brad) - R * Math.Sin(b0rad);
DELTA = Math.Sqrt(x * x + y * y + z * z);
EarthLightTravelTime = ELL.DistanceToLightTime(DELTA);
//Prepare for the next loop around
bIterate = (Math.Abs(EarthLightTravelTime - PreviousEarthLightTravelTime) > 2E-6); //2E-6 corresponds to 0.17 of a second
if (bIterate)
{
JD1 = JD - EarthLightTravelTime;
PreviousEarthLightTravelTime = EarthLightTravelTime;
}
}
//Step 5. Calculate Saturn's geocentric Longitude and Latitude
double lambda = Math.Atan2(y, x);
double beta = Math.Atan2(z, Math.Sqrt(x * x + y * y));
//Step 6. Calculate B, a and b
details.B = Math.Asin(Math.Sin(irad) * Math.Cos(beta) * Math.Sin(lambda - omegarad) - Math.Cos(irad) * Math.Sin(beta));
details.a = 375.35 / DELTA;
details.b = details.a * Math.Sin(Math.Abs(details.B));
details.B = CT.R2D(details.B);
//Step 7. Calculate the longitude of the ascending node of Saturn's orbit
double N = 113.6655 + 0.8771 * T;
double Nrad = CT.D2R(N);
double ldash = l - 0.01759 / r;
double ldashrad = CT.D2R(ldash);
double bdash = b - 0.000764 * Math.Cos(ldashrad - Nrad) / r;
double bdashrad = CT.D2R(bdash);
//Step 8. Calculate Bdash
details.Bdash = CT.R2D(Math.Asin(Math.Sin(irad) * Math.Cos(bdashrad) * Math.Sin(ldashrad - omegarad) - Math.Cos(irad) * Math.Sin(bdashrad)));
//Step 9. Calculate DeltaU
double U1 = Math.Atan2(Math.Sin(irad) * Math.Sin(bdashrad) + Math.Cos(irad) * Math.Cos(bdashrad) * Math.Sin(ldashrad - omegarad), Math.Cos(bdashrad) * Math.Cos(ldashrad - omegarad));
double U2 = Math.Atan2(Math.Sin(irad) * Math.Sin(beta) + Math.Cos(irad) * Math.Cos(beta) * Math.Sin(lambda - omegarad), Math.Cos(beta) * Math.Cos(lambda - omegarad));
details.DeltaU = CT.R2D(Math.Abs(U1 - U2));
//Step 10. Calculate the Nutations
double Obliquity = CAANutation.TrueObliquityOfEcliptic(JD);
double NutationInLongitude = CAANutation.NutationInLongitude(JD);
//Step 11. Calculate the Ecliptical longitude and latitude of the northern pole of the ring plane
double lambda0 = omega - 90;
double beta0 = 90 - i;
//Step 12. Correct lambda and beta for the aberration of Saturn
lambda += CT.D2R(0.005693 * Math.Cos(l0rad - lambda) / Math.Cos(beta));
beta += CT.D2R(0.005693 * Math.Sin(l0rad - lambda) * Math.Sin(beta));
//Step 13. Add nutation in longitude to lambda0 and lambda
//double NLrad = CAACoordinateTransformation::DegreesToRadians(NutationInLongitude/3600);
lambda = CT.R2D(lambda);
lambda += NutationInLongitude / 3600;
lambda = CT.M360(lambda);
lambda0 += NutationInLongitude / 3600;
lambda0 = CT.M360(lambda0);
//Step 14. Convert to equatorial coordinates
beta = CT.R2D(beta);
COR GeocentricEclipticSaturn = CT.Ec2Eq(lambda, beta, Obliquity);
double alpha = CT.H2R(GeocentricEclipticSaturn.X);
double delta = CT.D2R(GeocentricEclipticSaturn.Y);
COR GeocentricEclipticNorthPole = CT.Ec2Eq(lambda0, beta0, Obliquity);
double alpha0 = CT.H2R(GeocentricEclipticNorthPole.X);
double delta0 = CT.D2R(GeocentricEclipticNorthPole.Y);
//Step 15. Calculate the Position angle
details.P = CT.R2D(Math.Atan2(Math.Cos(delta0) * Math.Sin(alpha0 - alpha), Math.Sin(delta0) * Math.Cos(delta) - Math.Cos(delta0) * Math.Sin(delta) * Math.Cos(alpha0 - alpha)));
return(details);
}
//private Vector3d GetTragectoryPoint(double jNow, out Vector3d vector)
//{
//int min = 0;
//int max = Trajectory.Count - 1;
//Vector3d point = new Vector3d();
//vector = new Vector3d();
//int current = max / 2;
//bool found = false;
//while (!found)
//{
// if (current < 1)
// {
// vector = Trajectory[0].Position - Trajectory[1].Position;
// return Trajectory[0].Position;
// }
// if (current == Trajectory.Count - 1)
// {
// vector = Trajectory[current - 1].Position - Trajectory[current].Position;
// return Trajectory[current].Position;
// }
// if ((Trajectory[current-1].Time <= jNow) && (Trajectory[current].Time > jNow))
// {
// double denominator = Trajectory[current].Time -Trajectory[current-1].Time;
// double numerator = jNow - Trajectory[current - 1].Time;
// double tween = numerator / denominator;
// vector = Trajectory[current - 1].Position - Trajectory[current].Position;
// point = Vector3d.Lerp(Trajectory[current - 1].Position, Trajectory[current].Position, tween);
// return point;
// }
// if (Trajectory[current].Time < jNow)
// {
// int next = current + ( max - current + 1) / 2;
// min = current;
// current = next;
// }
// else
// if (Trajectory[current - 1].Time > jNow)
// {
// int next = current - ( current - min + 1) / 2;
// max = current;
// current = next;
// }
//}
//return point;
//}
private void ComputeOrbital(RenderContext renderContext)
{
EOE ee = Elements;
Vector3d point = ELL.CalculateRectangularJD(SpaceTimeController.JNow, ee);
Vector3d pointInstantLater = ELL.CalculateRectangular(ee, MeanAnomoly + .001);
Vector3d direction = Vector3d.SubtractVectors(point, pointInstantLater);
direction.Normalize();
Vector3d up = point;
up.Normalize();
direction.Normalize();
double dist = point.Length();
double scaleFactor = 1.0;
switch (SemiMajorAxisUnits)
{
case AltUnits.Meters:
scaleFactor = 1.0;
break;
case AltUnits.Feet:
scaleFactor = 1.0 / 3.2808399;
break;
case AltUnits.Inches:
scaleFactor = (1.0 / 3.2808399) / 12;
break;
case AltUnits.Miles:
scaleFactor = 1609.344;
break;
case AltUnits.Kilometers:
scaleFactor = 1000;
break;
case AltUnits.AstronomicalUnits:
scaleFactor = UiTools.KilometersPerAu * 1000;
break;
case AltUnits.LightYears:
scaleFactor = UiTools.AuPerLightYear * UiTools.KilometersPerAu * 1000;
break;
case AltUnits.Parsecs:
scaleFactor = UiTools.AuPerParsec * UiTools.KilometersPerAu * 1000;
break;
case AltUnits.MegaParsecs:
scaleFactor = UiTools.AuPerParsec * UiTools.KilometersPerAu * 1000 * 1000000;
break;
case AltUnits.Custom:
scaleFactor = 1;
break;
default:
break;
}
scaleFactor *= 1 / renderContext.NominalRadius;
WorldMatrix = Matrix3d.Identity;
Matrix3d look = Matrix3d.LookAtLH(Vector3d.Create(0, 0, 0), direction, up);
look.Invert();
WorldMatrix = Matrix3d.Identity;
double localScale = (1 / renderContext.NominalRadius) * Scale * MeanRadius;
WorldMatrix.Scale(Vector3d.Create(localScale, localScale, localScale));
Matrix3d mat = Matrix3d.MultiplyMatrix(Matrix3d.MultiplyMatrix(Matrix3d.RotationY(Heading), Matrix3d.RotationX(Pitch)), Matrix3d.RotationZ(Roll));
if (RotationalPeriod != 0)
{
double rotationCurrent = (((SpaceTimeController.JNow - this.ZeroRotationDate) / RotationalPeriod) * 360) % (360);
WorldMatrix.Multiply(Matrix3d.RotationX(-rotationCurrent));
}
point = Vector3d.Scale(point, scaleFactor);
WorldMatrix.Translate(point);
if (StationKeeping)
{
WorldMatrix = Matrix3d.MultiplyMatrix(look, WorldMatrix);
}
}
public static EPD Calculate(double JD, EO @object)
{
//What will the the return value
EPD details = new EPD();
double JD0 = JD;
double L0 = 0;
double B0 = 0;
double R0 = 0;
double cosB0 = 0;
if (@object != EO.SUN)
{
L0 = CAAEarth.EclipticLongitude(JD0);
B0 = CAAEarth.EclipticLatitude(JD0);
R0 = CAAEarth.RadiusVector(JD0);
L0 = CT.D2R(L0);
B0 = CT.D2R(B0);
cosB0 = Math.Cos(B0);
}
//Calculate the initial values
double L = 0;
double B = 0;
double R = 0;
double Lrad;
double Brad;
double cosB;
double cosL;
double x;
double y;
double z;
bool bRecalc = true;
bool bFirstRecalc = true;
double LPrevious = 0;
double BPrevious = 0;
double RPrevious = 0;
while (bRecalc)
{
switch (@object)
{
case EO.SUN:
{
L = CAASun.GeometricEclipticLongitude(JD0);
B = CAASun.GeometricEclipticLatitude(JD0);
R = CAAEarth.RadiusVector(JD0);
break;
}
case EO.MERCURY:
{
L = CAAMercury.EclipticLongitude(JD0);
B = CAAMercury.EclipticLatitude(JD0);
R = CAAMercury.RadiusVector(JD0);
break;
}
case EO.VENUS:
{
L = CAAVenus.EclipticLongitude(JD0);
B = CAAVenus.EclipticLatitude(JD0);
R = CAAVenus.RadiusVector(JD0);
break;
}
case EO.MARS:
{
L = CAAMars.EclipticLongitude(JD0);
B = CAAMars.EclipticLatitude(JD0);
R = CAAMars.RadiusVector(JD0);
break;
}
case EO.JUPITER:
{
L = CAAJupiter.EclipticLongitude(JD0);
B = CAAJupiter.EclipticLatitude(JD0);
R = CAAJupiter.RadiusVector(JD0);
break;
}
case EO.SATURN:
{
L = CAASaturn.EclipticLongitude(JD0);
B = CAASaturn.EclipticLatitude(JD0);
R = CAASaturn.RadiusVector(JD0);
break;
}
case EO.URANUS:
{
L = CAAUranus.EclipticLongitude(JD0);
B = CAAUranus.EclipticLatitude(JD0);
R = CAAUranus.RadiusVector(JD0);
break;
}
case EO.NEPTUNE:
{
L = CAANeptune.EclipticLongitude(JD0);
B = CAANeptune.EclipticLatitude(JD0);
R = CAANeptune.RadiusVector(JD0);
break;
}
case EO.PLUTO:
{
L = CAAPluto.EclipticLongitude(JD0);
B = CAAPluto.EclipticLatitude(JD0);
R = CAAPluto.RadiusVector(JD0);
break;
}
default:
{
Debug.Assert(false);
break;
}
}
if (!bFirstRecalc)
{
bRecalc = ((Math.Abs(L - LPrevious) > 0.00001) || (Math.Abs(B - BPrevious) > 0.00001) || (Math.Abs(R - RPrevious) > 0.000001));
LPrevious = L;
BPrevious = B;
RPrevious = R;
}
else
{
bFirstRecalc = false;
}
//Calculate the new value
if (bRecalc)
{
double distance = 0;
if (@object != EO.SUN)
{
Lrad = CT.D2R(L);
Brad = CT.D2R(B);
cosB = Math.Cos(Brad);
cosL = Math.Cos(Lrad);
x = R * cosB * cosL - R0 * cosB0 * Math.Cos(L0);
y = R * cosB * Math.Sin(Lrad) - R0 * cosB0 * Math.Sin(L0);
z = R * Math.Sin(Brad) - R0 * Math.Sin(B0);
distance = Math.Sqrt(x * x + y * y + z * z);
}
else
{
distance = R; //Distance to the sun from the earth is in fact the radius vector
}
//Prepare for the next loop around
JD0 = JD - ELL.DistanceToLightTime(distance);
}
}
Lrad = CT.D2R(L);
Brad = CT.D2R(B);
cosB = Math.Cos(Brad);
cosL = Math.Cos(Lrad);
x = R * cosB * cosL - R0 * cosB0 * Math.Cos(L0);
y = R * cosB * Math.Sin(Lrad) - R0 * cosB0 * Math.Sin(L0);
z = R * Math.Sin(Brad) - R0 * Math.Sin(B0);
double x2 = x * x;
double y2 = y * y;
details.ApparentGeocentricLatitude = CT.R2D(Math.Atan2(z, Math.Sqrt(x2 + y2)));
details.ApparentGeocentricDistance = Math.Sqrt(x2 + y2 + z * z);
details.ApparentGeocentricLongitude = CT.M360(CT.R2D(Math.Atan2(y, x)));
details.ApparentLightTime = ELL.DistanceToLightTime(details.ApparentGeocentricDistance);
//Adjust for Aberration
COR Aberration = ABR.EclipticAberration(details.ApparentGeocentricLongitude, details.ApparentGeocentricLatitude, JD);
details.ApparentGeocentricLongitude += Aberration.X;
details.ApparentGeocentricLatitude += Aberration.Y;
//convert to the FK5 system
double DeltaLong = CAAFK5.CorrectionInLongitude(details.ApparentGeocentricLongitude, details.ApparentGeocentricLatitude, JD);
details.ApparentGeocentricLatitude += CAAFK5.CorrectionInLatitude(details.ApparentGeocentricLongitude, JD);
details.ApparentGeocentricLongitude += DeltaLong;
//Correct for nutation
double NutationInLongitude = CAANutation.NutationInLongitude(JD);
double Epsilon = CAANutation.TrueObliquityOfEcliptic(JD);
details.ApparentGeocentricLongitude += CT.DMS2D(0, 0, NutationInLongitude);
//Convert to RA and Dec
COR ApparentEqu = CT.Ec2Eq(details.ApparentGeocentricLongitude, details.ApparentGeocentricLatitude, Epsilon);
details.ApparentGeocentricRA = ApparentEqu.X;
details.ApparentGeocentricDeclination = ApparentEqu.Y;
return(details);
}
//Static methods
public static GMDS Calculate(double JD)
{
//Calculate the position of the Sun
double sunlong = CAASun.GeometricEclipticLongitude(JD);
double sunlongrad = CT.D2R(sunlong);
double beta = CAASun.GeometricEclipticLatitude(JD);
double betarad = CT.D2R(beta);
double R = CAAEarth.RadiusVector(JD);
//Calculate the the light travel time from Jupiter to the Earth
double DELTA = 5;
double PreviousEarthLightTravelTime = 0;
double EarthLightTravelTime = ELL.DistanceToLightTime(DELTA);
double JD1 = JD - EarthLightTravelTime;
bool bIterate = true;
double x = 0;
double y = 0;
double z = 0;
double l = 0;
double lrad = 0;
double b = 0;
double brad = 0;
double r = 0;
while (bIterate)
{
//Calculate the position of Jupiter
l = CAAJupiter.EclipticLongitude(JD1);
lrad = CT.D2R(l);
b = CAAJupiter.EclipticLatitude(JD1);
brad = CT.D2R(b);
r = CAAJupiter.RadiusVector(JD1);
x = r * Math.Cos(brad) * Math.Cos(lrad) + R * Math.Cos(sunlongrad);
y = r * Math.Cos(brad) * Math.Sin(lrad) + R * Math.Sin(sunlongrad);
z = r * Math.Sin(brad) + R * Math.Sin(betarad);
DELTA = Math.Sqrt(x * x + y * y + z * z);
EarthLightTravelTime = ELL.DistanceToLightTime(DELTA);
//Prepare for the next loop around
bIterate = (Math.Abs(EarthLightTravelTime - PreviousEarthLightTravelTime) > 2E-6); //2E-6 corresponds to 0.17 of a second
if (bIterate)
{
JD1 = JD - EarthLightTravelTime;
PreviousEarthLightTravelTime = EarthLightTravelTime;
}
}
//Calculate the details as seen from the earth
GMDS details1 = CalculateHelper(JD, sunlongrad, betarad, R);
FillInPhenomenaDetails(details1.Satellite1);
FillInPhenomenaDetails(details1.Satellite2);
FillInPhenomenaDetails(details1.Satellite3);
FillInPhenomenaDetails(details1.Satellite4);
//Calculate the the light travel time from Jupiter to the Sun
JD1 = JD - EarthLightTravelTime;
l = CAAJupiter.EclipticLongitude(JD1);
lrad = CT.D2R(l);
b = CAAJupiter.EclipticLatitude(JD1);
brad = CT.D2R(b);
r = CAAJupiter.RadiusVector(JD1);
x = r * Math.Cos(brad) * Math.Cos(lrad);
y = r * Math.Cos(brad) * Math.Sin(lrad);
z = r * Math.Sin(brad);
DELTA = Math.Sqrt(x * x + y * y + z * z);
double SunLightTravelTime = ELL.DistanceToLightTime(DELTA);
//Calculate the details as seen from the Sun
GMDS details2 = CalculateHelper(JD + SunLightTravelTime - EarthLightTravelTime, sunlongrad, betarad, 0);
FillInPhenomenaDetails(details2.Satellite1);
FillInPhenomenaDetails(details2.Satellite2);
FillInPhenomenaDetails(details2.Satellite3);
FillInPhenomenaDetails(details2.Satellite4);
//Finally transfer the required values from details2 to details1
details1.Satellite1.bInEclipse = details2.Satellite1.bInOccultation;
details1.Satellite2.bInEclipse = details2.Satellite2.bInOccultation;
details1.Satellite3.bInEclipse = details2.Satellite3.bInOccultation;
details1.Satellite4.bInEclipse = details2.Satellite4.bInOccultation;
details1.Satellite1.bInShadowTransit = details2.Satellite1.bInTransit;
details1.Satellite2.bInShadowTransit = details2.Satellite2.bInTransit;
details1.Satellite3.bInShadowTransit = details2.Satellite3.bInTransit;
details1.Satellite4.bInShadowTransit = details2.Satellite4.bInTransit;
//C++ TO C# CONVERTER WARNING: The following line was determined to be a copy assignment (rather than a reference assignment) - this should be verified and a 'CopyFrom' method should be created if it does not yet exist:
//ORIGINAL LINE: details1.Satellite1.ApparentShadowRectangularCoordinates = details2.Satellite1.ApparentRectangularCoordinates;
details1.Satellite1.ApparentShadowRectangularCoordinates = details2.Satellite1.ApparentRectangularCoordinates;
//C++ TO C# CONVERTER WARNING: The following line was determined to be a copy assignment (rather than a reference assignment) - this should be verified and a 'CopyFrom' method should be created if it does not yet exist:
//ORIGINAL LINE: details1.Satellite2.ApparentShadowRectangularCoordinates = details2.Satellite2.ApparentRectangularCoordinates;
details1.Satellite2.ApparentShadowRectangularCoordinates = details2.Satellite2.ApparentRectangularCoordinates;
//C++ TO C# CONVERTER WARNING: The following line was determined to be a copy assignment (rather than a reference assignment) - this should be verified and a 'CopyFrom' method should be created if it does not yet exist:
//ORIGINAL LINE: details1.Satellite3.ApparentShadowRectangularCoordinates = details2.Satellite3.ApparentRectangularCoordinates;
details1.Satellite3.ApparentShadowRectangularCoordinates = details2.Satellite3.ApparentRectangularCoordinates;
//C++ TO C# CONVERTER WARNING: The following line was determined to be a copy assignment (rather than a reference assignment) - this should be verified and a 'CopyFrom' method should be created if it does not yet exist:
//ORIGINAL LINE: details1.Satellite4.ApparentShadowRectangularCoordinates = details2.Satellite4.ApparentRectangularCoordinates;
details1.Satellite4.ApparentShadowRectangularCoordinates = details2.Satellite4.ApparentRectangularCoordinates;
return(details1);
}
//////////////////////////////// Implementation ///////////////////////////////
protected static GMDS CalculateHelper(double JD, double sunlongrad, double betarad, double R)
{
//What will be the return value
GMDS details = new GMDS();
//Calculate the position of Jupiter decreased by the light travel time from Jupiter to the specified position
double DELTA = 5;
double PreviousLightTravelTime = 0;
double LightTravelTime = ELL.DistanceToLightTime(DELTA);
double x = 0;
double y = 0;
double z = 0;
double l = 0;
double lrad = 0;
double b = 0;
double brad = 0;
double r = 0;
double JD1 = JD - LightTravelTime;
bool bIterate = true;
while (bIterate)
{
//Calculate the position of Jupiter
l = CAAJupiter.EclipticLongitude(JD1);
lrad = CT.D2R(l);
b = CAAJupiter.EclipticLatitude(JD1);
brad = CT.D2R(b);
r = CAAJupiter.RadiusVector(JD1);
x = r * Math.Cos(brad) * Math.Cos(lrad) + R * Math.Cos(sunlongrad);
y = r * Math.Cos(brad) * Math.Sin(lrad) + R * Math.Sin(sunlongrad);
z = r * Math.Sin(brad) + R * Math.Sin(betarad);
DELTA = Math.Sqrt(x * x + y * y + z * z);
LightTravelTime = ELL.DistanceToLightTime(DELTA);
//Prepare for the next loop around
bIterate = (Math.Abs(LightTravelTime - PreviousLightTravelTime) > 2E-6); //2E-6 corresponds to 0.17 of a second
if (bIterate)
{
JD1 = JD - LightTravelTime;
PreviousLightTravelTime = LightTravelTime;
}
}
//Calculate Jupiter's Longitude and Latitude
double lambda0 = Math.Atan2(y, x);
double beta0 = Math.Atan(z / Math.Sqrt(x * x + y * y));
double t = JD - 2443000.5 - LightTravelTime;
//Calculate the mean longitudes
double l1 = 106.07719 + 203.488955790 * t;
double l1rad = CT.D2R(l1);
double l2 = 175.73161 + 101.374724735 * t;
double l2rad = CT.D2R(l2);
double l3 = 120.55883 + 50.317609207 * t;
double l3rad = CT.D2R(l3);
double l4 = 84.44459 + 21.571071177 * t;
double l4rad = CT.D2R(l4);
//Calculate the perijoves
double pi1 = CT.D2R(CT.M360(97.0881 + 0.16138586 * t));
double pi2 = CT.D2R(CT.M360(154.8663 + 0.04726307 * t));
double pi3 = CT.D2R(CT.M360(188.1840 + 0.00712734 * t));
double pi4 = CT.D2R(CT.M360(335.2868 + 0.00184000 * t));
//Calculate the nodes on the equatorial plane of jupiter
double w1 = 312.3346 - 0.13279386 * t;
double w1rad = CT.D2R(w1);
double w2 = 100.4411 - 0.03263064 * t;
double w2rad = CT.D2R(w2);
double w3 = 119.1942 - 0.00717703 * t;
double w3rad = CT.D2R(w3);
double w4 = 322.6186 - 0.00175934 * t;
double w4rad = CT.D2R(w4);
//Calculate the Principal inequality in the longitude of Jupiter
double GAMMA = 0.33033 * Math.Sin(CT.D2R(163.679 + 0.0010512 * t)) + 0.03439 * Math.Sin(CT.D2R(34.486 - 0.0161731 * t));
//Calculate the "phase of free libration"
double philambda = CT.D2R(199.6766 + 0.17379190 * t);
//Calculate the longitude of the node of the equator of Jupiter on the ecliptic
double psi = CT.D2R(316.5182 - 0.00000208 * t);
//Calculate the mean anomalies of Jupiter and Saturn
double G = CT.D2R(30.23756 + 0.0830925701 * t + GAMMA);
double Gdash = CT.D2R(31.97853 + 0.0334597339 * t);
//Calculate the longitude of the perihelion of Jupiter
double PI = CT.D2R(13.469942);
//Calculate the periodic terms in the longitudes of the satellites
double Sigma1 = 0.47259 * Math.Sin(2 * (l1rad - l2rad)) + -0.03478 * Math.Sin(pi3 - pi4) + 0.01081 * Math.Sin(l2rad - 2 * l3rad + pi3) + 0.00738 * Math.Sin(philambda) + 0.00713 * Math.Sin(l2rad - 2 * l3rad + pi2) + -0.00674 * Math.Sin(pi1 + pi3 - 2 * PI - 2 * G) + 0.00666 * Math.Sin(l2rad - 2 * l3rad + pi4) + 0.00445 * Math.Sin(l1rad - pi3) + -0.00354 * Math.Sin(l1rad - l2rad) + -0.00317 * Math.Sin(2 * psi - 2 * PI) + 0.00265 * Math.Sin(l1rad - pi4) + -0.00186 * Math.Sin(G) + 0.00162 * Math.Sin(pi2 - pi3) + 0.00158 * Math.Sin(4 * (l1rad - l2rad)) + -0.00155 * Math.Sin(l1rad - l3rad) + -0.00138 * Math.Sin(psi + w3rad - 2 * PI - 2 * G) + -0.00115 * Math.Sin(2 * (l1rad - 2 * l2rad + w2rad)) + 0.00089 * Math.Sin(pi2 - pi4) + 0.00085 * Math.Sin(l1rad + pi3 - 2 * PI - 2 * G) + 0.00083 * Math.Sin(w2rad - w3rad) + 0.00053 * Math.Sin(psi - w2rad);
double Sigma2 = 1.06476 * Math.Sin(2 * (l2rad - l3rad)) + 0.04256 * Math.Sin(l1rad - 2 * l2rad + pi3) + 0.03581 * Math.Sin(l2rad - pi3) + 0.02395 * Math.Sin(l1rad - 2 * l2rad + pi4) + 0.01984 * Math.Sin(l2rad - pi4) + -0.01778 * Math.Sin(philambda) + 0.01654 * Math.Sin(l2rad - pi2) + 0.01334 * Math.Sin(l2rad - 2 * l3rad + pi2) + 0.01294 * Math.Sin(pi3 - pi4) + -0.01142 * Math.Sin(l2rad - l3rad) + -0.01057 * Math.Sin(G) + -0.00775 * Math.Sin(2 * (psi - PI)) + 0.00524 * Math.Sin(2 * (l1rad - l2rad)) + -0.00460 * Math.Sin(l1rad - l3rad) + 0.00316 * Math.Sin(psi - 2 * G + w3rad - 2 * PI) + -0.00203 * Math.Sin(pi1 + pi3 - 2 * PI - 2 * G) + 0.00146 * Math.Sin(psi - w3rad) + -0.00145 * Math.Sin(2 * G) + 0.00125 * Math.Sin(psi - w4rad) + -0.00115 * Math.Sin(l1rad - 2 * l3rad + pi3) + -0.00094 * Math.Sin(2 * (l2rad - w2rad)) + 0.00086 * Math.Sin(2 * (l1rad - 2 * l2rad + w2rad)) + -0.00086 * Math.Sin(5 * Gdash - 2 * G + CT.D2R(52.225)) + -0.00078 * Math.Sin(l2rad - l4rad) + -0.00064 * Math.Sin(3 * l3rad - 7 * l4rad + 4 * pi4) + 0.00064 * Math.Sin(pi1 - pi4) + -0.00063 * Math.Sin(l1rad - 2 * l3rad + pi4) + 0.00058 * Math.Sin(w3rad - w4rad) + 0.00056 * Math.Sin(2 * (psi - PI - G)) + 0.00056 * Math.Sin(2 * (l2rad - l4rad)) + 0.00055 * Math.Sin(2 * (l1rad - l3rad)) + 0.00052 * Math.Sin(3 * l3rad - 7 * l4rad + pi3 + 3 * pi4) + -0.00043 * Math.Sin(l1rad - pi3) + 0.00041 * Math.Sin(5 * (l2rad - l3rad)) + 0.00041 * Math.Sin(pi4 - PI) + 0.00032 * Math.Sin(w2rad - w3rad) + 0.00032 * Math.Sin(2 * (l3rad - G - PI));
double Sigma3 = 0.16490 * Math.Sin(l3rad - pi3) + 0.09081 * Math.Sin(l3rad - pi4) + -0.06907 * Math.Sin(l2rad - l3rad) + 0.03784 * Math.Sin(pi3 - pi4) + 0.01846 * Math.Sin(2 * (l3rad - l4rad)) + -0.01340 * Math.Sin(G) + -0.01014 * Math.Sin(2 * (psi - PI)) + 0.00704 * Math.Sin(l2rad - 2 * l3rad + pi3) + -0.00620 * Math.Sin(l2rad - 2 * l3rad + pi2) + -0.00541 * Math.Sin(l3rad - l4rad) + 0.00381 * Math.Sin(l2rad - 2 * l3rad + pi4) + 0.00235 * Math.Sin(psi - w3rad) + 0.00198 * Math.Sin(psi - w4rad) + 0.00176 * Math.Sin(philambda) + 0.00130 * Math.Sin(3 * (l3rad - l4rad)) + 0.00125 * Math.Sin(l1rad - l3rad) + -0.00119 * Math.Sin(5 * Gdash - 2 * G + CT.D2R(52.225)) + 0.00109 * Math.Sin(l1rad - l2rad) + -0.00100 * Math.Sin(3 * l3rad - 7 * l4rad + 4 * pi4) + 0.00091 * Math.Sin(w3rad - w4rad) + 0.00080 * Math.Sin(3 * l3rad - 7 * l4rad + pi3 + 3 * pi4) + -0.00075 * Math.Sin(2 * l2rad - 3 * l3rad + pi3) + 0.00072 * Math.Sin(pi1 + pi3 - 2 * PI - 2 * G) + 0.00069 * Math.Sin(pi4 - PI) + -0.00058 * Math.Sin(2 * l3rad - 3 * l4rad + pi4) + -0.00057 * Math.Sin(l3rad - 2 * l4rad + pi4) + 0.00056 * Math.Sin(l3rad + pi3 - 2 * PI - 2 * G) + -0.00052 * Math.Sin(l2rad - 2 * l3rad + pi1) + -0.00050 * Math.Sin(pi2 - pi3) + 0.00048 * Math.Sin(l3rad - 2 * l4rad + pi3) + -0.00045 * Math.Sin(2 * l2rad - 3 * l3rad + pi4) + -0.00041 * Math.Sin(pi2 - pi4) + -0.00038 * Math.Sin(2 * G) + -0.00037 * Math.Sin(pi3 - pi4 + w3rad - w4rad) + -0.00032 * Math.Sin(3 * l3rad - 7 * l4rad + 2 * pi3 + 2 * pi4) + 0.00030 * Math.Sin(4 * (l3rad - l4rad)) + 0.00029 * Math.Sin(l3rad + pi4 - 2 * PI - 2 * G) + -0.00028 * Math.Sin(w3rad + psi - 2 * PI - 2 * G) + 0.00026 * Math.Sin(l3rad - PI - G) + 0.00024 * Math.Sin(l2rad - 3 * l3rad + 2 * l4rad) + 0.00021 * Math.Sin(l3rad - PI - G) + -0.00021 * Math.Sin(l3rad - pi2) + 0.00017 * Math.Sin(2 * (l3rad - pi3));
double Sigma4 = 0.84287 * Math.Sin(l4rad - pi4) + 0.03431 * Math.Sin(pi4 - pi3) + -0.03305 * Math.Sin(2 * (psi - PI)) + -0.03211 * Math.Sin(G) + -0.01862 * Math.Sin(l4rad - pi3) + 0.01186 * Math.Sin(psi - w4rad) + 0.00623 * Math.Sin(l4rad + pi4 - 2 * G - 2 * PI) + 0.00387 * Math.Sin(2 * (l4rad - pi4)) + -0.00284 * Math.Sin(5 * Gdash - 2 * G + CT.D2R(52.225)) + -0.00234 * Math.Sin(2 * (psi - pi4)) + -0.00223 * Math.Sin(l3rad - l4rad) + -0.00208 * Math.Sin(l4rad - PI) + 0.00178 * Math.Sin(psi + w4rad - 2 * pi4) + 0.00134 * Math.Sin(pi4 - PI) + 0.00125 * Math.Sin(2 * (l4rad - G - PI)) + -0.00117 * Math.Sin(2 * G) + -0.00112 * Math.Sin(2 * (l3rad - l4rad)) + 0.00107 * Math.Sin(3 * l3rad - 7 * l4rad + 4 * pi4) + 0.00102 * Math.Sin(l4rad - G - PI) + 0.00096 * Math.Sin(2 * l4rad - psi - w4rad) + 0.00087 * Math.Sin(2 * (psi - w4rad)) + -0.00085 * Math.Sin(3 * l3rad - 7 * l4rad + pi3 + 3 * pi4) + 0.00085 * Math.Sin(l3rad - 2 * l4rad + pi4) + -0.00081 * Math.Sin(2 * (l4rad - psi)) + 0.00071 * Math.Sin(l4rad + pi4 - 2 * PI - 3 * G) + 0.00061 * Math.Sin(l1rad - l4rad) + -0.00056 * Math.Sin(psi - w3rad) + -0.00054 * Math.Sin(l3rad - 2 * l4rad + pi3) + 0.00051 * Math.Sin(l2rad - l4rad) + 0.00042 * Math.Sin(2 * (psi - G - PI)) + 0.00039 * Math.Sin(2 * (pi4 - w4rad)) + 0.00036 * Math.Sin(psi + PI - pi4 - w4rad) + 0.00035 * Math.Sin(2 * Gdash - G + CT.D2R(188.37)) + -0.00035 * Math.Sin(l4rad - pi4 + 2 * PI - 2 * psi) + -0.00032 * Math.Sin(l4rad + pi4 - 2 * PI - G) + 0.00030 * Math.Sin(2 * Gdash - 2 * G + CT.D2R(149.15)) + 0.00029 * Math.Sin(3 * l3rad - 7 * l4rad + 2 * pi3 + 2 * pi4) + 0.00028 * Math.Sin(l4rad - pi4 + 2 * psi - 2 * PI) + -0.00028 * Math.Sin(2 * (l4rad - w4rad)) + -0.00027 * Math.Sin(pi3 - pi4 + w3rad - w4rad) + -0.00026 * Math.Sin(5 * Gdash - 3 * G + CT.D2R(188.37)) + 0.00025 * Math.Sin(w4rad - w3rad) + -0.00025 * Math.Sin(l2rad - 3 * l3rad + 2 * l4rad) + -0.00023 * Math.Sin(3 * (l3rad - l4rad)) + 0.00021 * Math.Sin(2 * l4rad - 2 * PI - 3 * G) + -0.00021 * Math.Sin(2 * l3rad - 3 * l4rad + pi4) + 0.00019 * Math.Sin(l4rad - pi4 - G) + -0.00019 * Math.Sin(2 * l4rad - pi3 - pi4) + -0.00018 * Math.Sin(l4rad - pi4 + G) + -0.00016 * Math.Sin(l4rad + pi3 - 2 * PI - 2 * G);
details.Satellite1.MeanLongitude = CT.M360(l1);
details.Satellite1.TrueLongitude = CT.M360(l1 + Sigma1);
double L1 = CT.D2R(details.Satellite1.TrueLongitude);
details.Satellite2.MeanLongitude = CT.M360(l2);
details.Satellite2.TrueLongitude = CT.M360(l2 + Sigma2);
double L2 = CT.D2R(details.Satellite2.TrueLongitude);
details.Satellite3.MeanLongitude = CT.M360(l3);
details.Satellite3.TrueLongitude = CT.M360(l3 + Sigma3);
double L3 = CT.D2R(details.Satellite3.TrueLongitude);
details.Satellite4.MeanLongitude = CT.M360(l4);
details.Satellite4.TrueLongitude = CT.M360(l4 + Sigma4);
double L4 = CT.D2R(details.Satellite4.TrueLongitude);
//Calculate the periodic terms in the latitudes of the satellites
double B1 = Math.Atan(0.0006393 * Math.Sin(L1 - w1rad) + 0.0001825 * Math.Sin(L1 - w2rad) + 0.0000329 * Math.Sin(L1 - w3rad) + -0.0000311 * Math.Sin(L1 - psi) + 0.0000093 * Math.Sin(L1 - w4rad) + 0.0000075 * Math.Sin(3 * L1 - 4 * l2rad - 1.9927 * Sigma1 + w2rad) + 0.0000046 * Math.Sin(L1 + psi - 2 * PI - 2 * G));
details.Satellite1.EquatorialLatitude = CT.R2D(B1);
double B2 = Math.Atan(0.0081004 * Math.Sin(L2 - w2rad) + 0.0004512 * Math.Sin(L2 - w3rad) + -0.0003284 * Math.Sin(L2 - psi) + 0.0001160 * Math.Sin(L2 - w4rad) + 0.0000272 * Math.Sin(l1rad - 2 * l3rad + 1.0146 * Sigma2 + w2rad) + -0.0000144 * Math.Sin(L2 - w1rad) + 0.0000143 * Math.Sin(L2 + psi - 2 * PI - 2 * G) + 0.0000035 * Math.Sin(L2 - psi + G) + -0.0000028 * Math.Sin(l1rad - 2 * l3rad + 1.0146 * Sigma2 + w3rad));
details.Satellite2.EquatorialLatitude = CT.R2D(B2);
double B3 = Math.Atan(0.0032402 * Math.Sin(L3 - w3rad) + -0.0016911 * Math.Sin(L3 - psi) + 0.0006847 * Math.Sin(L3 - w4rad) + -0.0002797 * Math.Sin(L3 - w2rad) + 0.0000321 * Math.Sin(L3 + psi - 2 * PI - 2 * G) + 0.0000051 * Math.Sin(L3 - psi + G) + -0.0000045 * Math.Sin(L3 - psi - G) + -0.0000045 * Math.Sin(L3 + psi - 2 * PI) + 0.0000037 * Math.Sin(L3 + psi - 2 * PI - 3 * G) + 0.0000030 * Math.Sin(2 * l2rad - 3 * L3 + 4.03 * Sigma3 + w2rad) + -0.0000021 * Math.Sin(2 * l2rad - 3 * L3 + 4.03 * Sigma3 + w3rad));
details.Satellite3.EquatorialLatitude = CT.R2D(B3);
double B4 = Math.Atan(-0.0076579 * Math.Sin(L4 - psi) + 0.0044134 * Math.Sin(L4 - w4rad) + -0.0005112 * Math.Sin(L4 - w3rad) + 0.0000773 * Math.Sin(L4 + psi - 2 * PI - 2 * G) + 0.0000104 * Math.Sin(L4 - psi + G) + -0.0000102 * Math.Sin(L4 - psi - G) + 0.0000088 * Math.Sin(L4 + psi - 2 * PI - 3 * G) + -0.0000038 * Math.Sin(L4 + psi - 2 * PI - G));
details.Satellite4.EquatorialLatitude = CT.R2D(B4);
//Calculate the periodic terms for the radius vector
details.Satellite1.r = 5.90569 * (1 + (-0.0041339 * Math.Cos(2 * (l1rad - l2rad)) + -0.0000387 * Math.Cos(l1rad - pi3) + -0.0000214 * Math.Cos(l1rad - pi4) + 0.0000170 * Math.Cos(l1rad - l2rad) + -0.0000131 * Math.Cos(4 * (l1rad - l2rad)) + 0.0000106 * Math.Cos(l1rad - l3rad) + -0.0000066 * Math.Cos(l1rad + pi3 - 2 * PI - 2 * G)));
details.Satellite2.r = 9.39657 * (1 + (0.0093848 * Math.Cos(l1rad - l2rad) + -0.0003116 * Math.Cos(l2rad - pi3) + -0.0001744 * Math.Cos(l2rad - pi4) + -0.0001442 * Math.Cos(l2rad - pi2) + 0.0000553 * Math.Cos(l2rad - l3rad) + 0.0000523 * Math.Cos(l1rad - l3rad) + -0.0000290 * Math.Cos(2 * (l1rad - l2rad)) + 0.0000164 * Math.Cos(2 * (l2rad - w2rad)) + 0.0000107 * Math.Cos(l1rad - 2 * l3rad + pi3) + -0.0000102 * Math.Cos(l2rad - pi1) + -0.0000091 * Math.Cos(2 * (l1rad - l3rad))));
details.Satellite3.r = 14.98832 * (1 + (-0.0014388 * Math.Cos(l3rad - pi3) + -0.0007919 * Math.Cos(l3rad - pi4) + 0.0006342 * Math.Cos(l2rad - l3rad) + -0.0001761 * Math.Cos(2 * (l3rad - l4rad)) + 0.0000294 * Math.Cos(l3rad - l4rad) + -0.0000156 * Math.Cos(3 * (l3rad - l4rad)) + 0.0000156 * Math.Cos(l1rad - l3rad) + -0.0000153 * Math.Cos(l1rad - l2rad) + 0.0000070 * Math.Cos(2 * l2rad - 3 * l3rad + pi3) + -0.0000051 * Math.Cos(l3rad + pi3 - 2 * PI - 2 * G)));
details.Satellite4.r = 26.36273 * (1 + (-0.0073546 * Math.Cos(l4rad - pi4) + 0.0001621 * Math.Cos(l4rad - pi3) + 0.0000974 * Math.Cos(l3rad - l4rad) + -0.0000543 * Math.Cos(l4rad + pi4 - 2 * PI - 2 * G) + -0.0000271 * Math.Cos(2 * (l4rad - pi4)) + 0.0000182 * Math.Cos(l4rad - PI) + 0.0000177 * Math.Cos(2 * (l3rad - l4rad)) + -0.0000167 * Math.Cos(2 * l4rad - psi - w4rad) + 0.0000167 * Math.Cos(psi - w4rad) + -0.0000155 * Math.Cos(2 * (l4rad - PI - G)) + 0.0000142 * Math.Cos(2 * (l4rad - psi)) + 0.0000105 * Math.Cos(l1rad - l4rad) + 0.0000092 * Math.Cos(l2rad - l4rad) + -0.0000089 * Math.Cos(l4rad - PI - G) + -0.0000062 * Math.Cos(l4rad + pi4 - 2 * PI - 3 * G) + 0.0000048 * Math.Cos(2 * (l4rad - w4rad))));
//Calculate T0
double T0 = (JD - 2433282.423) / 36525;
//Calculate the precession in longitude from Epoch B1950 to the date
double P = CT.D2R(1.3966626 * T0 + 0.0003088 * T0 * T0);
//Add it to L1 - L4 and psi
L1 += P;
details.Satellite1.TropicalLongitude = CT.M360(CT.R2D(L1));
L2 += P;
details.Satellite2.TropicalLongitude = CT.M360(CT.R2D(L2));
L3 += P;
details.Satellite3.TropicalLongitude = CT.M360(CT.R2D(L3));
L4 += P;
details.Satellite4.TropicalLongitude = CT.M360(CT.R2D(L4));
psi += P;
//Calculate the inclination of Jupiter's axis of rotation on the orbital plane
double T = (JD - 2415020.5) / 36525;
double I = 3.120262 + 0.0006 * T;
double Irad = CT.D2R(I);
double X1 = details.Satellite1.r * Math.Cos(L1 - psi) * Math.Cos(B1);
double X2 = details.Satellite2.r * Math.Cos(L2 - psi) * Math.Cos(B2);
double X3 = details.Satellite3.r * Math.Cos(L3 - psi) * Math.Cos(B3);
double X4 = details.Satellite4.r * Math.Cos(L4 - psi) * Math.Cos(B4);
double X5 = 0;
double Y1 = details.Satellite1.r * Math.Sin(L1 - psi) * Math.Cos(B1);
double Y2 = details.Satellite2.r * Math.Sin(L2 - psi) * Math.Cos(B2);
double Y3 = details.Satellite3.r * Math.Sin(L3 - psi) * Math.Cos(B3);
double Y4 = details.Satellite4.r * Math.Sin(L4 - psi) * Math.Cos(B4);
double Y5 = 0;
double Z1 = details.Satellite1.r * Math.Sin(B1);
double Z2 = details.Satellite2.r * Math.Sin(B2);
double Z3 = details.Satellite3.r * Math.Sin(B3);
double Z4 = details.Satellite4.r * Math.Sin(B4);
double Z5 = 1;
//Now do the rotations, first for the ficticious 5th satellite, so that we can calculate D
double omega = CT.D2R(EPO.JupiterLongitudeAscendingNode(JD));
double i = CT.D2R(EPO.JupiterInclination(JD));
double A6 = 0;
double B6 = 0;
double C6 = 0;
C3D north = new C3D();
double[] abc = Rotations(X5, Y5, Z5, Irad, psi, i, omega, lambda0, beta0, north);
A6 = abc[0];
B6 = abc[1];
C6 = abc[2];
double D = Math.Atan2(A6, C6);
//Now calculate the values for satellite 1
abc = Rotations(X1, Y1, Z1, Irad, psi, i, omega, lambda0, beta0, details.Satellite1.EclipticRectangularCoordinates);
A6 = abc[0];
B6 = abc[1];
C6 = abc[2];
details.Satellite1.TrueRectangularCoordinates.X = A6 * Math.Cos(D) - C6 * Math.Sin(D);
details.Satellite1.TrueRectangularCoordinates.Y = A6 * Math.Sin(D) + C6 * Math.Cos(D);
details.Satellite1.TrueRectangularCoordinates.Z = B6;
//Now calculate the values for satellite 2
abc = Rotations(X2, Y2, Z2, Irad, psi, i, omega, lambda0, beta0, details.Satellite2.EclipticRectangularCoordinates);
A6 = abc[0];
B6 = abc[1];
C6 = abc[2];
details.Satellite2.TrueRectangularCoordinates.X = A6 * Math.Cos(D) - C6 * Math.Sin(D);
details.Satellite2.TrueRectangularCoordinates.Y = A6 * Math.Sin(D) + C6 * Math.Cos(D);
details.Satellite2.TrueRectangularCoordinates.Z = B6;
//Now calculate the values for satellite 3
abc = Rotations(X3, Y3, Z3, Irad, psi, i, omega, lambda0, beta0, details.Satellite3.EclipticRectangularCoordinates);
A6 = abc[0];
B6 = abc[1];
C6 = abc[2];
details.Satellite3.TrueRectangularCoordinates.X = A6 * Math.Cos(D) - C6 * Math.Sin(D);
details.Satellite3.TrueRectangularCoordinates.Y = A6 * Math.Sin(D) + C6 * Math.Cos(D);
details.Satellite3.TrueRectangularCoordinates.Z = B6;
//And finally for satellite 4
abc = Rotations(X4, Y4, Z4, Irad, psi, i, omega, lambda0, beta0, details.Satellite4.EclipticRectangularCoordinates);
A6 = abc[0];
B6 = abc[1];
C6 = abc[2];
details.Satellite4.TrueRectangularCoordinates.X = A6 * Math.Cos(D) - C6 * Math.Sin(D);
details.Satellite4.TrueRectangularCoordinates.Y = A6 * Math.Sin(D) + C6 * Math.Cos(D);
details.Satellite4.TrueRectangularCoordinates.Z = B6;
//apply the differential light-time correction
details.Satellite1.ApparentRectangularCoordinates.X = details.Satellite1.TrueRectangularCoordinates.X + Math.Abs(details.Satellite1.TrueRectangularCoordinates.Z) / 17295 * Math.Sqrt(1 - (details.Satellite1.TrueRectangularCoordinates.X / details.Satellite1.r) * (details.Satellite1.TrueRectangularCoordinates.X / details.Satellite1.r));
details.Satellite1.ApparentRectangularCoordinates.Y = details.Satellite1.TrueRectangularCoordinates.Y;
details.Satellite1.ApparentRectangularCoordinates.Z = details.Satellite1.TrueRectangularCoordinates.Z;
details.Satellite2.ApparentRectangularCoordinates.X = details.Satellite2.TrueRectangularCoordinates.X + Math.Abs(details.Satellite2.TrueRectangularCoordinates.Z) / 21819 * Math.Sqrt(1 - (details.Satellite2.TrueRectangularCoordinates.X / details.Satellite2.r) * (details.Satellite2.TrueRectangularCoordinates.X / details.Satellite2.r));
details.Satellite2.ApparentRectangularCoordinates.Y = details.Satellite2.TrueRectangularCoordinates.Y;
details.Satellite2.ApparentRectangularCoordinates.Z = details.Satellite2.TrueRectangularCoordinates.Z;
details.Satellite3.ApparentRectangularCoordinates.X = details.Satellite3.TrueRectangularCoordinates.X + Math.Abs(details.Satellite3.TrueRectangularCoordinates.Z) / 27558 * Math.Sqrt(1 - (details.Satellite3.TrueRectangularCoordinates.X / details.Satellite3.r) * (details.Satellite3.TrueRectangularCoordinates.X / details.Satellite3.r));
details.Satellite3.ApparentRectangularCoordinates.Y = details.Satellite3.TrueRectangularCoordinates.Y;
details.Satellite3.ApparentRectangularCoordinates.Z = details.Satellite3.TrueRectangularCoordinates.Z;
details.Satellite4.ApparentRectangularCoordinates.X = details.Satellite4.TrueRectangularCoordinates.X + Math.Abs(details.Satellite4.TrueRectangularCoordinates.Z) / 36548 * Math.Sqrt(1 - (details.Satellite4.TrueRectangularCoordinates.X / details.Satellite4.r) * (details.Satellite4.TrueRectangularCoordinates.X / details.Satellite4.r));
details.Satellite4.ApparentRectangularCoordinates.Y = details.Satellite4.TrueRectangularCoordinates.Y;
details.Satellite4.ApparentRectangularCoordinates.Z = details.Satellite4.TrueRectangularCoordinates.Z;
//apply the perspective effect correction
double W = DELTA / (DELTA + details.Satellite1.TrueRectangularCoordinates.Z / 2095);
details.Satellite1.ApparentRectangularCoordinates.X *= W;
details.Satellite1.ApparentRectangularCoordinates.Y *= W;
W = DELTA / (DELTA + details.Satellite2.TrueRectangularCoordinates.Z / 2095);
details.Satellite2.ApparentRectangularCoordinates.X *= W;
details.Satellite2.ApparentRectangularCoordinates.Y *= W;
W = DELTA / (DELTA + details.Satellite3.TrueRectangularCoordinates.Z / 2095);
details.Satellite3.ApparentRectangularCoordinates.X *= W;
details.Satellite3.ApparentRectangularCoordinates.Y *= W;
W = DELTA / (DELTA + details.Satellite4.TrueRectangularCoordinates.Z / 2095);
details.Satellite4.ApparentRectangularCoordinates.X *= W;
details.Satellite4.ApparentRectangularCoordinates.Y *= W;
return(details);
}
//Static methods
//////////////////////////////// Implementation ///////////////////////////////
public static CAAPhysicalMarsDetails Calculate(double JD)
{
//What will be the return value
CAAPhysicalMarsDetails details = new CAAPhysicalMarsDetails();
//Step 1
double T = (JD - 2451545) / 36525;
double Lambda0 = 352.9065 + 1.17330 * T;
double Lambda0rad = CT.D2R(Lambda0);
double Beta0 = 63.2818 - 0.00394 * T;
double Beta0rad = CT.D2R(Beta0);
//Step 2
double l0 = CAAEarth.EclipticLongitude(JD);
double l0rad = CT.D2R(l0);
double b0 = CAAEarth.EclipticLatitude(JD);
double b0rad = CT.D2R(b0);
double R = CAAEarth.RadiusVector(JD);
double PreviousLightTravelTime = 0;
double LightTravelTime = 0;
double x = 0;
double y = 0;
double z = 0;
bool bIterate = true;
double DELTA = 0;
double l = 0;
double lrad = 0;
double b = 0;
double brad = 0;
double r = 0;
while (bIterate)
{
double JD2 = JD - LightTravelTime;
//Step 3
l = CAAMars.EclipticLongitude(JD2);
lrad = CT.D2R(l);
b = CAAMars.EclipticLatitude(JD2);
brad = CT.D2R(b);
r = CAAMars.RadiusVector(JD2);
//Step 4
x = r * Math.Cos(brad) * Math.Cos(lrad) - R * Math.Cos(l0rad);
y = r * Math.Cos(brad) * Math.Sin(lrad) - R * Math.Sin(l0rad);
z = r * Math.Sin(brad) - R * Math.Sin(b0rad);
DELTA = Math.Sqrt(x * x + y * y + z * z);
LightTravelTime = ELL.DistanceToLightTime(DELTA);
//Prepare for the next loop around
bIterate = (Math.Abs(LightTravelTime - PreviousLightTravelTime) > 2E-6); //2E-6 correponds to 0.17 of a second
if (bIterate)
{
PreviousLightTravelTime = LightTravelTime;
}
}
//Step 5
double lambdarad = Math.Atan2(y, x);
double lambda = CT.R2D(lambdarad);
double betarad = Math.Atan2(z, Math.Sqrt(x * x + y * y));
double beta = CT.R2D(betarad);
//Step 6
details.DE = CT.R2D(Math.Asin(-Math.Sin(Beta0rad) * Math.Sin(betarad) - Math.Cos(Beta0rad) * Math.Cos(betarad) * Math.Cos(Lambda0rad - lambdarad)));
//Step 7
double N = 49.5581 + 0.7721 * T;
double Nrad = CT.D2R(N);
double ldash = l - 0.00697 / r;
double ldashrad = CT.D2R(ldash);
double bdash = b - 0.000225 * (Math.Cos(lrad - Nrad) / r);
double bdashrad = CT.D2R(bdash);
//Step 8
details.DS = CT.R2D(Math.Asin(-Math.Sin(Beta0rad) * Math.Sin(bdashrad) - Math.Cos(Beta0rad) * Math.Cos(bdashrad) * Math.Cos(Lambda0rad - ldashrad)));
//Step 9
double W = CT.M360(11.504 + 350.89200025 * (JD - LightTravelTime - 2433282.5));
//Step 10
double e0 = CAANutation.MeanObliquityOfEcliptic(JD);
double e0rad = CT.D2R(e0);
COR PoleEquatorial = CT.Ec2Eq(Lambda0, Beta0, e0);
double alpha0rad = CT.H2R(PoleEquatorial.X);
double delta0rad = CT.D2R(PoleEquatorial.Y);
//Step 11
double u = y * Math.Cos(e0rad) - z * Math.Sin(e0rad);
double v = y * Math.Sin(e0rad) + z * Math.Cos(e0rad);
double alpharad = Math.Atan2(u, x);
double alpha = CT.R2H(alpharad);
double deltarad = Math.Atan2(v, Math.Sqrt(x * x + u * u));
double delta = CT.R2D(deltarad);
double xi = Math.Atan2(Math.Sin(delta0rad) * Math.Cos(deltarad) * Math.Cos(alpha0rad - alpharad) - Math.Sin(deltarad) * Math.Cos(delta0rad), Math.Cos(deltarad) * Math.Sin(alpha0rad - alpharad));
//Step 12
details.w = CT.M360(W - CT.R2D(xi));
//Step 13
double NutationInLongitude = CAANutation.NutationInLongitude(JD);
double NutationInObliquity = CAANutation.NutationInObliquity(JD);
//Step 14
lambda += 0.005693 * Math.Cos(l0rad - lambdarad) / Math.Cos(betarad);
beta += 0.005693 * Math.Sin(l0rad - lambdarad) * Math.Sin(betarad);
//Step 15
Lambda0 += NutationInLongitude / 3600;
Lambda0rad = CT.D2R(Lambda0);
lambda += NutationInLongitude / 3600;
lambdarad = CT.D2R(lambda);
e0 += NutationInObliquity / 3600;
e0rad = CT.D2R(e0rad);
//Step 16
COR ApparentPoleEquatorial = CT.Ec2Eq(Lambda0, Beta0, e0);
double alpha0dash = CT.H2R(ApparentPoleEquatorial.X);
double delta0dash = CT.D2R(ApparentPoleEquatorial.Y);
COR ApparentMars = CT.Ec2Eq(lambda, beta, e0);
double alphadash = CT.H2R(ApparentMars.X);
double deltadash = CT.D2R(ApparentMars.Y);
//Step 17
details.P = CT.M360(CT.R2D(Math.Atan2(Math.Cos(delta0dash) * Math.Sin(alpha0dash - alphadash), Math.Sin(delta0dash) * Math.Cos(deltadash) - Math.Cos(delta0dash) * Math.Sin(deltadash) * Math.Cos(alpha0dash - alphadash))));
//Step 18
double SunLambda = CAASun.GeometricEclipticLongitude(JD);
double SunBeta = CAASun.GeometricEclipticLatitude(JD);
COR SunEquatorial = CT.Ec2Eq(SunLambda, SunBeta, e0);
details.X = MIFR.PositionAngle(SunEquatorial.X, SunEquatorial.Y, alpha, delta);
//Step 19
details.d = 9.36 / DELTA;
details.k = IFR.IlluminatedFraction2(r, R, DELTA);
details.q = (1 - details.k) * details.d;
return(details);
}
