예제 #1
0
    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);
    }
예제 #2
0
//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);
    }