public GpstkOrbitUtil(EphemerisParam eph)
{
this.af0 = eph.ClockBias;
this.af1 = eph.ClockDrift;
this.af2 = eph.DriftRate;
this.ctToc = eph.Toe;//
this.Cic = eph.Cic;
this.Crc = eph.Crc;
this.Crs = eph.Crs;
this.OMEGAdot = eph.OmegaDot;
this.e0 = eph.Eccentricity;//
this.Cuc = eph.Cuc;
this.Cis = eph.Cis;
this.Cus = eph.Cus;
this.ctToe = eph.Toe;
this.Adot = 0;//??
this.A = eph.SqrtA * eph.SqrtA;
this.dn = eph.DeltaN;
this.M0 = eph.MeanAnomaly;
this.ecc = eph.Eccentricity;
this.REL_CONST = eph.Eccentricity;
this.PI = CoordConsts.PI;
this.eye0 = eph.Inclination;
this.Omega = eph.ArgumentOfPerigee;
this.OMEGA0 = eph.LongOfAscension;
this.dndot = 0;//??
this.idot = eph.EyeDot;
this.prn = eph.Prn;
}
public eph_t(EphemerisParam eph)
{
this.A = eph.SqrtA * eph.SqrtA;
this.toe = eph.Toe;
// this.sat = eph.sat;
this.M0 = eph.MeanAnomaly;
this.deln = eph.DeltaN;
this.e = eph.Eccentricity;
this.omg = eph.ArgumentOfPerigee;
this.cuc = eph.Cuc;
this.crs = eph.Crs;
this.cis = eph.Cis;
this.cus = eph.Cus;
this.cic = eph.Cis;
this.crc = eph.Crc;
this.OMG0 = eph.LongOfAscension;
this.OMGd = eph.OmegaDot;
this.toes = eph.Toe;
this.toc = eph.Toe;//??;
this.f0 = eph.ClockBias;
this.f1 = eph.ClockDrift;
this.f2 = eph.DriftRate;
this.sva = eph.SVAccuracy;
this.i0 = eph.Inclination;
this.idot = eph.EyeDot;
}
public static double STD_BRDCCLK = 30.0; /* error of broadcast clock (m) */
public static XYZ GetPos(double secOfWeek, EphemerisParam param)
{
double [] rs = new double [3];
double dts = 0, var = 0;
eph2pos(secOfWeek, new eph_t(param), rs, ref dts, ref var, param.Prn);
return(XYZ.Parse(rs));
}
public static RmsedXYZ GetPosXYZ(EphemerisParam eph, double secOfWeek)
{
GpstkOrbitUtil o = new GpstkOrbitUtil(eph);
Xvt xvt = o.svXvt(secOfWeek);
XYZ xyzGpstk = XYZ.Parse(xvt.x);
XYZ velercity = XYZ.Parse(xvt.v);
return(new RmsedXYZ(xyzGpstk, velercity));
}
public override bool Equals(object obj)
{
EphemerisParam p = obj as EphemerisParam;
if (p == null)
{
return(false);
}
return(this.Prn.Equals(p.Prn) && this.Time.Equals(p.Time));
}
private static double KeplerEqForEccAnomaly1(EphemerisParam eph, double M)
{
int n;
double Ek, E1;
for (n = 0, E1 = M, Ek = 0.0; Math.Abs(E1 - Ek) > 1e-14; n++)
{
Ek = E1;
E1 -= (E1 - eph.Eccentricity * Math.Sin(E1) - M) / (1.0 - eph.Eccentricity * Math.Cos(E1));
}
return(E1);
}
/// <summary>
/// 获取卫星钟差
/// </summary>
/// <param name="record">星历参数</param>
/// <param name="gpsTime">时间</param>
/// <returns></returns>
public static double GetClockOffset(EphemerisParam record, Time gpsTime)
{
double toc = record.Time.SecondsOfWeek;
double t = gpsTime.SecondsOfWeek;
double differTime = t - record.Toe;
//GPS卫星以钟为周秒，考虑到一个星期的开始或结束
if (differTime > 302400)
{
differTime -= 604800;
}
else if (differTime < -302400)
{
differTime += 604800;
}
return(record.GetOffset(differTime));
}
/// <summary>
/// 根据轨道根数计算卫星位置。
/// 核心计算程序。
/// </summary>
/// <param name="secOfWeek">GPS周秒</param>
/// <param name="isGeosynchronous">是否是地球同步轨道卫星</param>
/// <returns></returns>
public static Geo.Coordinates.XYZ GetSatXyz(EphemerisParam eph, double gpsSecOfWeek, SatelliteType satelliteType = SatelliteType.G, bool isGeosynchronous = false)
{
double e = eph.Eccentricity;
double A, en0, tk, en, M, E, sinE, cosE, f, u, cos2u, sin2u, duk, drk, dik;
double uk, rk, eyek, cosEyek, xpk, ypk, omgk, cosOmgk, sinOmgk, xk, yk, zk;
double secOfWeek = gpsSecOfWeek;
if (satelliteType == SatelliteType.C)//如果是北斗，需要转换为北斗时间来计算。
{
secOfWeek = gpsSecOfWeek - 14;
}
//*** time since orbit reference epoch
tk = Time.GetDifferSecondOfWeek(secOfWeek, eph.Toe);
Geo.Referencing.IEllipsoid ellipsoid = GnssSystem.GetGnssSystem(satelliteType).Ellipsoid;
double GM = ellipsoid.GM; // MU_GPS;
double omge = ellipsoid.AngleVelocity; // OMGE;
//平均角速度
A = eph.SqrtA * eph.SqrtA;
en0 = Math.Sqrt(GM) / (A * eph.SqrtA);
//改正平均角度
en = en0 + eph.DeltaN;
//*** mean anomaly, M
M = eph.MeanAnomaly + en * tk;
//*** solve kepler's equation for eccentric anomaly, E
E = KeplerEqForEccAnomaly(M, e);
//var E0 = KeplerEqForEccAnomalyOld(M, e);
//var E1 = KeplerEqForEccAnomaly1(M, e);
// double E1 = KeplerEqForEccAnomaly1(eph, M);
sinE = Math.Sin(E);
cosE = Math.Cos(E);
//*** true anomaly, L
f = Math.Atan2(Math.Sqrt(1.0 - e * e) * sinE, cosE - e);
//*** argument of latitude, rightHandSide
u = f + eph.ArgumentOfPerigee;
cos2u = Math.Cos(u + u);
sin2u = Math.Sin(u + u);
//*** corrections to the arg. of lat., radius, and inclination
duk = eph.Cuc * cos2u + eph.Cus * sin2u;
drk = eph.Crc * cos2u + eph.Crs * sin2u;
dik = eph.Cic * cos2u + eph.Cis * sin2u;
//*** correct the arg. of lat., radius, and inclination
uk = u + duk;
rk = A * (1.0 - e * cosE) + drk;
eyek = eph.Inclination + eph.EyeDot * tk + dik;
//*** position in the orbital plane
xpk = rk * Math.Cos(uk);
ypk = rk * Math.Sin(uk);
cosEyek = Math.Cos(eyek);
//*** correct the longitude of the ascending node
XYZ xyz = new XYZ();
//同步轨道卫星，如北斗
if (isGeosynchronous)
{
omgk = eph.LongOfAscension + eph.OmegaDot * tk - omge * eph.Toe;
cosOmgk = Math.Cos(omgk);
sinOmgk = Math.Sin(omgk);
//*** compute ecbf coordinates
double xg = xpk * cosOmgk - ypk * sinOmgk * cosEyek;
double yg = xpk * sinOmgk + ypk * cosOmgk * cosEyek;
double zg = ypk * Math.Sin(eyek);
double sino = Math.Sin(omge * tk);
double coso = Math.Cos(omge * tk);
double x = xg * coso + yg * sino * COS_5 + zg * sino * SIN_5;
double y = -xg * sino + yg * coso * COS_5 + zg * coso * SIN_5;
double z = -yg * SIN_5 + zg * COS_5;
xyz = new XYZ(x, y, z);
}
else
{
omgk = eph.LongOfAscension + (eph.OmegaDot - omge) * tk - omge * eph.Toe;
cosOmgk = Math.Cos(omgk);
sinOmgk = Math.Sin(omgk);
//*** compute ecbf coordinates
xk = xpk * cosOmgk - ypk * sinOmgk * cosEyek;
yk = xpk * sinOmgk + ypk * cosOmgk * cosEyek;
zk = ypk * Math.Sin(eyek);
xyz = new XYZ(xk, yk, zk);
}
return(xyz);
//以下为测试比较
XYZ xyz2 = RtkLibOrbitUtil.GetPos(secOfWeek, eph);
//XYZ xyzGpstk = GetPosXYZ(eph, secOfWeek);
// return xyzGpstk;
}
/// <summary>
/// 计算位置。
/// </summary>
/// <param name="record"></param>
/// <param name="gpstime">周秒</param>
/// <param name="X"></param>
/// <param name="Y"></param>
/// <param name="Z"></param>
public static void GetSatPos(EphemerisParam record, double gpstime, out double X, out double Y, out double Z)
{
double mu = 3.986005e14;
double n0, n;
n0 = Math.Sqrt(mu) / (record.SqrtA * record.SqrtA * record.SqrtA);
n = n0 + record.DeltaN;
//double t = GetGPSTime(clk.Year + 2000,
// clk.Month, clk.Day, clk.Hour, clk.Minute, clk.Second);
double t = gpstime;// -0.075;
double tk = t - record.Toe;
if (tk > 302400)
{
tk -= 604800;
}
else if (tk < -302400)
{
tk += 604800;
}
double Mk = record.MeanAnomaly + n * tk;
double Ek0, Ek;
Ek0 = Mk;
while (true)
{
Ek = Mk + record.Eccentricity * Math.Sin(Ek0);
if (Math.Abs(Ek - Ek0) < 1e-8)
{
break;
}
Ek0 = Ek;
}
//double fk = Math.Atan(Math.Sqrt(1 - clk.east * clk.east) * Math.Sin(Ek) / (Math.Cos(Ek) - clk.east));
double fk = 2 * Math.Atan(Math.Sqrt(1 + record.Eccentricity) / Math.Sqrt(1 - record.Eccentricity) * Math.Tan(Ek / 2));
double fik = fk + record.ArgumentOfPerigee;
double deltau = record.Cuc * Math.Cos(2 * fik) + record.Cus * Math.Sin(2 * fik);
double deltar = record.Crc * Math.Cos(2 * fik) + record.Crs * Math.Sin(2 * fik);
double deltai = record.Cic * Math.Cos(2 * fik) + record.Cis * Math.Sin(2 * fik);
double uk = fik + deltau;
double rk = record.SqrtA * record.SqrtA * (1 - record.Eccentricity * Math.Cos(Ek)) + deltar;
double ik = record.Inclination + deltai + record.EyeDot * tk;
double xk = rk * Math.Cos(uk);
double yk = rk * Math.Sin(uk);
double omegae = 7.2921151467e-5;
double omegak = record.LongOfAscension + (record.OmegaDot - omegae) * tk - omegae * record.Toe;
//卫星在地心地固坐标系中的位置。
X = xk * Math.Cos(omegak) - yk * Math.Cos(ik) * Math.Sin(omegak);
Y = xk * Math.Sin(omegak) + yk * Math.Cos(ik) * Math.Cos(omegak);
Z = yk * Math.Sin(ik);
}
static double RTOL_KEPLER = 1E-14; /* relative tolerance for Kepler equation */
public static Geo.Coordinates.XYZ GetSatXyz(EphemerisParam eph, double secOfWeek)
{
bool isGeosynchronous = eph.Prn.PRN <= 5 && eph.Prn.SatelliteType == SatelliteType.C;
return(GetSatXyz(eph, secOfWeek, eph.Prn.SatelliteType, isGeosynchronous));
}