/// <summary>
/// 卫星天线相位中心改正，参照RTKLIB
/// </summary>
/// <param name="satelliteType"></param>
/// <param name="satPos"></param>
/// <param name="ReceiverPosition"></param>
/// <param name="sunPosition"></param>
/// <param name="svPCcorr"></param>
/// <param name="antenna"></param>
/// <returns></returns>
private static double GetPhaseCorrection1(SatelliteNumber prn, XYZ satPos, XYZ ReceiverPosition, XYZ sunPosition, double svPCcorr, IAntenna antenna)
{
XYZ ru = ReceiverPosition - satPos;
XYZ rz = -satPos;
double[] eu = new double[3]; eu[0] = ru.X / ru.Length; eu[1] = ru.Y / ru.Length; eu[2] = ru.Z / ru.Length;
double[] ez = new double[3]; ez[0] = rz.X / rz.Length; ez[1] = rz.Y / rz.Length; ez[2] = rz.Z / rz.Length;
double cosa = eu[0] * ez[0] + eu[1] * ez[1] + eu[2] * ez[2];
cosa = cosa < -1.0 ? -1.0 : (cosa > 1.0 ? 1.0 : cosa);
double nadir = Math.Acos(cosa) * CoordConsts.RadToDegMultiplier;
//// The nadir angle should always smaller than 14.0 deg,
// // but some times it's a bit bigger than 14.0 deg, we
// // force it to 14.0 deg to stop throwing an exception.
// // The Reference is available at:
// // http://igscb.jpl.nasa.gov/igscb/resource/pubs/02_ott/session_8.pdf
// nadir = (nadir > 14) ? 14.0 : nadir;
double elev = 90.0 - nadir;
// Get antenna eccentricity for frequency "G01" (L1), in
// satellite reference system.
// NOTE: It is NOT in ECEF, it is in UEN!!!
RinexSatFrequency freq = new RinexSatFrequency(prn, 1);
// NEU satAnt = antenna.GetAntennaEccentricity(AntennaFrequency.G01);
NEU satAnt = antenna.GetPcoValue(freq);
if (satAnt.Equals(NEU.Zero))
{
return(0);
}
//Now, get the phase center variation.
var var = antenna.GetPcvValue(freq, elev); //只有U方向有值
// Projection of "svAntenna" vector to line of sight vector rrho
// svPCcorr = var.U;
return(var);
}
/// <summary>
/// 计算改正数
/// </summary>
/// <param name="input"></param>
public override void Correct(EpochInformation input)
{
if (input.EnabledSatCount == 0)
{
return;
}
var correction = new Dictionary <RinexSatFrequency, NEU>();
IAntenna antenna = input.SiteInfo.Antenna;
if (antenna == null)
{
if (!WarnedSites.Contains(input.SiteInfo.SiteName))
{
WarnedSites.Add(input.SiteInfo.SiteName);
log.Warn(input.Name + "接收机天线为: " + input.SiteInfo.AntennaType + ", " + input.SiteInfo.AntennaNumber + " 没有在天线文件夹中找到该类型的天线，无法进行 PCV 改正，精度影响可达10厘米（特别是高程）！请到 https://www.ngs.noaa.gov/ANTCAL/ 下载对应天线改正信息，并追加到.atx文件中");
}
this.Correction = correction;
return;
}
foreach (var item in antenna.Data)
{
var satFreq = item.Key;
var pco = antenna.GetPcoValue(satFreq); //这个值不变，实际上一次赋值就可以了！！//2018.08.02， czs，in hmx
correction.Add(satFreq, pco);
}
//多频的权宜之计
if (input.SatelliteTypes.Count > 0)
{
correction[RinexSatFrequency.BdsA] = correction[RinexSatFrequency.GpsA];
correction[RinexSatFrequency.BdsB] = correction[RinexSatFrequency.GpsB];
correction[RinexSatFrequency.GalileoA] = correction[RinexSatFrequency.GpsA];
correction[RinexSatFrequency.GalileoB] = correction[RinexSatFrequency.GpsB];
}
this.Correction = correction;
}
/// <summary>
/// 根据太阳计算卫星偏差
/// </summary>
/// <param name="prn"></param>
/// <param name="eph"></param>
/// <param name="emissionTime"></param>
/// <returns></returns>
private XYZ GetSatAntOff(SatelliteNumber prn, IEphemeris eph, Time emissionTime)
{
ErpItem erpv = null;
if (DataSouceProvider.ErpDataService != null)
{
erpv = DataSouceProvider.ErpDataService.Get(emissionTime);
}
if (erpv == null)
{
erpv = ErpItem.Zero;
}
XYZ rsun = new XYZ();
//sun position in ecef
// rsun = EpochSat.EpochInfo.DataSouceProvider.UniverseObjectProvider.GetSunPosition(emissionTime);
this.DataSouceProvider.UniverseObjectProvider.GetSunPosition(emissionTime, erpv, ref rsun);
//unit vetcors of satellite fixed coordinates
XYZ ez = -1 * eph.XYZ.UnitVector();
XYZ es = (rsun - eph.XYZ).UnitVector();
//outer product of 3D vectors
XYZ r = new XYZ();
r.X = ez.Y * es.Z - ez.Z * es.Y;
r.Y = ez.Z * es.X - ez.X * es.Z;
r.Z = ez.X * es.Y - ez.Y * es.X;
XYZ r0 = new XYZ();
r0.X = r.Y * ez.Z - r.Z * ez.Y;
r0.Y = r.Z * ez.X - r.X * ez.Z;
r0.Z = r.X * ez.Y - r.Y * ez.X;
XYZ ex = r0.UnitVector();
XYZ ey = r.UnitVector();
//XYZ ex = new XYZ();
//ex.X = ey.Y * ez.Z - ey.Z * ez.Y;
//ex.Y = ey.Z * ez.X - ey.X * ez.Z;
//ex.Z = ey.X * ez.Y - ey.Y * ez.X;
//use L1 value
if (DataSouceProvider.AntennaDataSource == null)
{
return(new XYZ());
}
IAntenna antenna = DataSouceProvider.AntennaDataSource.Get(prn.ToString(), emissionTime);
//如果为空，则返回 0 坐标
if (antenna == null)
{
return(new XYZ());
}
// Get antenna eccentricity for frequency "G01" (L1), in
// satellite reference system.
// NOTE: It is NOT in ECEF, it is in UEN!!!
RinexSatFrequency freq = new RinexSatFrequency(prn, 1);
// NEU satAnt = antenna.GetAntennaEccentricity(AntennaFrequency.G01);
NEU satAnt = antenna.GetPcoValue(freq);
XYZ dant = new XYZ();
dant.X = satAnt.E * ex.X + satAnt.N * ey.X + satAnt.U * ez.X;
dant.Y = satAnt.E * ex.Y + satAnt.N * ey.Y + satAnt.U * ez.Y;
dant.Z = satAnt.E * ex.Z + satAnt.N * ey.Z + satAnt.U * ez.Z;
// Unitary vector from satellite to Earth mass center (ECEF)
XYZ satToEarthUnit = (-1.0) * eph.XYZ.UnitVector();
// Unitary vector from Earth mass center to Sun (ECEF)
XYZ earthToSunUnit = rsun.UnitVector();
// rj = rk x ri: Rotation axis of solar panels (ECEF)
XYZ rj = satToEarthUnit.Cross(earthToSunUnit);
// Redefine ri: ri = rj x rk (ECEF)
earthToSunUnit = rj.Cross(satToEarthUnit);
// Let's funcKeyToDouble ri to an unitary vector. (ECEF)
earthToSunUnit = earthToSunUnit.UnitVector();
XYZ dant1 = new XYZ();
dant1.X = satAnt.E * rj.X + satAnt.N * earthToSunUnit.X + satAnt.U * satToEarthUnit.X;
dant1.Y = satAnt.E * rj.Y + satAnt.N * earthToSunUnit.Y + satAnt.U * satToEarthUnit.Y;
dant1.Z = satAnt.E * rj.Z + satAnt.N * earthToSunUnit.Z + satAnt.U * satToEarthUnit.Z;
return(dant1);
}
/// <summary>
/// 卫星天线相位中心改正，参照GPSTK模块
/// </summary>
/// <param name="satelliteType"></param>
/// <param name="satPos"></param>
/// <param name="ReceiverPosition"></param>
/// <param name="sunPosition"></param>
/// <param name="svPCcorr"></param>
/// <param name="antenna"></param>
/// <returns></returns>
private static double GetPhaseCorrection(SatelliteNumber prn, XYZ satPos, XYZ ReceiverPosition, XYZ sunPosition, double svPCcorr, IAntenna antenna)
{
// Unitary vector from satellite to Earth mass center (ECEF)
XYZ satToEarthUnit = (-1.0) * satPos.UnitVector();
// Unitary vector from Earth mass center to Sun (ECEF)
XYZ earthToSunUnit = sunPosition.UnitVector();
// rj = rk x ri: Rotation axis of solar panels (ECEF)
XYZ rj = satToEarthUnit.Cross(earthToSunUnit);
// Redefine ri: ri = rj x rk (ECEF)
earthToSunUnit = rj.Cross(satToEarthUnit);
// Let's funcKeyToDouble ri to an unitary vector. (ECEF)
earthToSunUnit = earthToSunUnit.UnitVector();
// Get vector from Earth mass center to receiver
XYZ receiverPos = ReceiverPosition;
// Compute unitary vector vector from satellite to RECEIVER
XYZ satToReceverUnit = (receiverPos - satPos).UnitVector();
// When not using Antex information, if satellite belongs to block
// "IIR" its correction is 0.0, else it will depend on satellite model.
// We will need the elevation, in degrees. It is found using
// dot product and the corresponding unitary angles
double cosa = satToReceverUnit.Dot(satToEarthUnit);
cosa = cosa < -1.0 ? -1.0 : (cosa > 1.0 ? 1.0 : cosa);
double nadir = Math.Acos(cosa) * CoordConsts.RadToDegMultiplier;
if (!DoubleUtil.IsValid(nadir))
{
return(0);
}
// The nadir angle should always smaller than 14.0 deg,
// but some times it's a bit bigger than 14.0 deg, we
// force it to 14.0 deg to stop throwing an exception.
// The Reference is available at:
// http://igscb.jpl.nasa.gov/igscb/resource/pubs/02_ott/session_8.pdf
nadir = (nadir > 14) ? 14.0 : nadir;
double elev = 90.0 - nadir;
// Get antenna eccentricity for frequency "G01" (L1), in
// satellite reference system.
// NOTE: It is NOT in ECEF, it is in UEN!!!
RinexSatFrequency freq = new RinexSatFrequency(prn, 1);
// NEU satAnt = antenna.GetAntennaEccentricity(AntennaFrequency.G01);
NEU satAnt = antenna.GetPcoValue(freq);
if (satAnt.Equals(NEU.Zero))
{
return(0);
}
//Now, get the phase center variation.
NEU var = new NEU(0, 0, antenna.GetPcvValue(freq, elev));
// We must substract them
satAnt = satAnt - var;
// Change to ECEF
// 原 satAnt t is in UEN!!!,本satAnt为NEU，分量相对应
// satAnt[0] = U
// Triple svAntenna( satAnt[2]*ri + satAnt[1]*rj + satAnt[0]*rk );
// XYZ svAntenna = satAnt.N * earthToSunUnit + satAnt.E * rj + satAnt.U * satToEarthUnit;
XYZ svAntenna = -(var.N * earthToSunUnit + var.E * rj + var.U * satToEarthUnit);
// Projection of "svAntenna" vector to line of sight vector rrho
svPCcorr = (satToReceverUnit.Dot(svAntenna));
return(svPCcorr);
}