public override void Correct(EpochSatellite epochSatellite)
{
Time gpsTime = epochSatellite.RecevingTime;
IEphemeris sat = epochSatellite.Ephemeris;
SatelliteNumber prn = epochSatellite.Prn;
//计算太阳位置方法
//XYZ sunPosition = epochSatellite.EpochInfo.DataSouceProvider.UniverseObjectProvider.GetSunPosition(gpsTime);
//新的计算太阳位置方法
Time tutc = gpsTime.GpstToUtc();
//查找地球自转信息
Gnsser.Data.ErpItem erpv = null;
if (DataSouceProvider.ErpDataService != null)
{
erpv = DataSouceProvider.ErpDataService.Get(tutc);
}
if (erpv == null)
{
erpv = ErpItem.Zero;
}
XYZ sunPosition = new XYZ();
DataSouceProvider.UniverseObjectProvider.GetSunPosition(gpsTime, erpv, ref sunPosition);
//use L1 value
IAntenna antenna = DataSouceProvider.AntennaDataSource.Get(prn.ToString(), gpsTime);
if (antenna == null)
{
return;
}
string AntennaType = antenna.AntennaType;
XYZ svPos = sat.XYZ;
XYZ receiverPosition = epochSatellite.SiteInfo.EstimatedXyz;
if (receiverPosition.Equals(XYZ.Zero))
{
return;
}
bool cycleSlip = epochSatellite.IsUnstable;
if (cycleSlip || !PhaseManager.Contains(prn)) //a cycle slip happend
{
PhaseManager[prn] = new SatVectorPhase();
}
double windUpCorrection = GetSatPhaseWindUpCorectValue(prn, gpsTime, svPos, receiverPosition, sunPosition, AntennaType);
//double windUpCorrection2 = GetSatPhaseWindUpCorectValue(satelliteType, gpsTime, svPos, receiverPosition, epochSatellite, sunPosition);
this.Correction = (windUpCorrection);
}
public override void Correct(EpochSatellite epochSatellite)
{
IEphemeris sat = epochSatellite.Ephemeris;
double correction = GetRelativeCorrection(sat) * GnssConst.LIGHT_SPEED;
this.Correction = (correction);
}
/// <summary>
/// 相对论效应改正。
/// 由于卫星速度快，产生相对论效应，使卫星钟变慢。
/// </summary>
/// <param name="sat"></param>
/// <returns></returns>
public static double GetRelativeCorrection(IEphemeris sat)
{
XYZ pos = sat.XYZ;
XYZ speed = sat.XyzDot;
return(EphemerisUtil.GetRelativeCorrection(pos, speed));
}
public override bool Revise(ref IEphemeris eph)
{
//eph.XYZ = EphemerisUtil.CorrectEarthSagnac(eph.XYZ, ReceiverPos);
//eph.XyzDot = EphemerisUtil.CorrectEarthSagnac(eph.XyzDot, ReceiverPos);
// 卫星坐标的地球自转改正
double len = (eph.XYZ - ReceiverPos).Length;
double elapsedTime = len / GnssConst.LIGHT_SPEED;
double sag = GnssConst.EARTH_ROTATE_SPEED * elapsedTime;
double sx = Math.Cos(sag) * eph.XYZ.X + Math.Sin(sag) * eph.XYZ.Y;
double sy = -Math.Sin(sag) * eph.XYZ.X + Math.Cos(sag) * eph.XYZ.Y;
eph.XYZ.X = sx;
eph.XYZ.Y = sy;
sx = Math.Cos(sag) * eph.XyzDot.X + Math.Sin(sag) * eph.XyzDot.Y;
sy = -Math.Sin(sag) * eph.XyzDot.X + Math.Cos(sag) * eph.XyzDot.Y;
eph.XyzDot.X = sx;
eph.XyzDot.Y = sy;
return(true);
}
public override bool Revise(ref IEphemeris eph)
{
XYZ dant1 = GetSatAntOff(eph.Prn, eph, eph.Time);
eph.XYZ = eph.XYZ + dant1;
return(true);
}
/// <summary>
/// 相对论改正钟差
/// </summary>
/// <param name="eph"></param>
/// <returns></returns>
public override bool Revise(ref IEphemeris eph)
{
//采用精密钟差服务改正
if (ClockDataSource != null)
{
if (Failes.Contains(eph.Prn))
{
return(true);
}
var clock = ClockDataSource.Get(eph.Prn, eph.Time);
if (clock != null)
{
if (clock.ClockBias != 0)
{
eph.ClockBias = clock.ClockBias;
}
//if (clock.ClockDrift != 0) { eph.ClockDrift = clock.ClockDrift; } //如果钟漂不为 0 ，则赋值。
}
else//获取失败
{
int i = 0;
//下次避免再次计算
Failes.Add(eph.Prn);
}
}
else
{
log.Debug("没有钟差服务！钟差不会单独改正" + eph);
}
return(true);
}
//// ===============
//// LOCAL FUNCTIONS
//// ===============
////
//// This is the function used to get the position and velocity vectors
//// for the major solar system bodies and the moon. It is patterned after
//// the solarsystem() function in the original NOVAS-C package. You can
//// pass an IDispatch pointer for an ephemeris component, and it will be
//// used. If that is NULL the internal solsys3() function is used.
////
//// This function must set error info... it is designed to work with
//// reflected exceptions from the attached ephemeris
////
internal static short solarsystem_nov(ref IEphemeris ephDisp, double tjd, double tdb, Body planet, Origin origin, ref double[] pos, ref double[] vel)
{
//Dim pl As NOVAS2.Body, org As NOVAS2.Origin
//Dim TL As New TraceLogger("", "solarsystem_nov")
short rc = 0;
//TL.Enabled = True
//TL.LogMessage("solarsystem_nov", "Start")
////
//// solsys3 takes tdb, ephemeris takes tjd
////
//Select Case origin
// Case OriginType.nvBarycentric
//org = NOVAS2.Origin.SolarSystemBarycentre
// Case OriginType.nvHeliocentric
//org = NOVAS2.Origin.CentreOfMassOfSun
//End Select
//Select Case planet
// Case PlanetNumber.nvEarth
//pl = NOVAS2.Body.Earth
// Case PlanetNumber.nvJupiter
//pl = NOVAS2.Body.Jupiter
// Case PlanetNumber.nvMars
//pl = NOVAS2.Body.Mars
// Case PlanetNumber.nvMercury
//pl = NOVAS2.Body.Mercury
// Case PlanetNumber.nvMoon
//pl = NOVAS2.Body.Moon
// Case PlanetNumber.nvNeptune
//pl = NOVAS2.Body.Neptune
// Case PlanetNumber.nvPluto
//pl = NOVAS2.Body.Pluto
// Case PlanetNumber.nvSaturn
//pl = NOVAS2.Body.Saturn
// Case PlanetNumber.nvSun
//pl = NOVAS2.Body.Sun
// Case PlanetNumber.nvUranus
//pl = NOVAS2.Body.Uranus
// Case PlanetNumber.nvVenus
//pl = NOVAS2.Body.Venus
//End Select
//TL.LogMessage("solarsystem_nov", "After planet")
if (ephDisp == null) //No ephemeris attached
{
//rc = solsys3_nov(tdb, planet, origin, pos, vel)
throw (new Exceptions.ValueNotSetException("EphemerisCode:SolarSystem_Nov No emphemeris object supplied"));
}
else
{
//CHECK TDB BELOW IS CORRECT!
//TL.LogMessage("solarsystem_nov", "Before ephemeris_nov")
ephemeris_nov(ephDisp, tdb, BodyType.MajorPlanet, planet, "", origin, ref pos, ref vel);
//TL.LogMessage("solarsystem_nov", "After ephemeris_nov")
}
//TL.Enabled = False
//TL.Dispose()
//TL = Nothing
return(rc);
}
public IEphemeris Revise(IEphemeris eph)
{
foreach (var item in EphemerisProcessors)
{
item.Revise(ref eph);
}
return(eph);
}
public override void Correct(EpochSatellite epochSatellite)
{
IEphemeris sat = epochSatellite.Ephemeris;
XYZ reXyz = epochSatellite.SiteInfo.EstimatedXyz;
double correction = GetRelativeCorrection(sat, reXyz);
this.Correction = (correction);
}
/// <summary>
/// 地球自转效应改正。
///
/// </summary>
/// <param name="sat"></param>
/// <returns></returns>
public static double GetRelativeCorrection(IEphemeris sat, XYZ rr)
{
XYZ rs = sat.XYZ;
//double OMGE = 7.2921151467E-5; /* earth angular velocity (IS-GPS) (rad/s) */
double sagnacCorrect = GnssConst.EARTH_ROTATE_SPEED * (rs.X * rr.Y - rs.Y * rr.X) / GnssConst.LIGHT_SPEED;
return(sagnacCorrect);
}
public Earth()
{
this.m_BaryPos = new PositionVector();
this.m_HeliPos = new PositionVector();
this.m_BaryVel = new VelocityVector();
this.m_HeliVel = new VelocityVector();
this.m_EarthEph = (IEphemeris) new Ephemeris();
this.m_EarthEph.BodyType = BodyType.Moon;
this.m_EarthEph.Number = Body.Earth;
this.m_EarthEph.Name = "Earth";
this.m_Valid = false;
}
/// <summary>
/// 相对论改正钟差
/// </summary>
/// <param name="eph"></param>
/// <returns></returns>
public override bool Revise(ref IEphemeris eph)
{
//地球自转改正之后，计算相对论改正
XYZ SatXyz = eph.XYZ;
XYZ SatSpeed = eph.XyzDot;
double relativeTime = GetRelativeCorrection(SatXyz, SatSpeed);
eph.ClockBias += relativeTime;
eph.RelativeCorrection = relativeTime;
return(true);
}
public Planet()
{
this.m_ephdisps = new int[5];
this.m_earthephdisps = new int[5];
this.m_name = (string)null;
this.m_bDTValid = false;
this.m_ephobj = (IEphemeris) new ASCOM.Astrometry.Kepler.Ephemeris();
this.m_earthephobj = (IEphemeris) new ASCOM.Astrometry.Kepler.Ephemeris();
this.m_earthephobj.BodyType = BodyType.Moon;
this.m_earthephobj.Name = "Earth";
this.m_earthephobj.Number = Body.Earth;
this.Nov31 = new NOVAS31();
}
public override void Correct(EpochSatellite epochSatellite)
{
IEphemeris sat = epochSatellite.Ephemeris;
if (sat == null)
{
return;
}
XYZ svPos = sat.XYZ;
XYZ nominalPos = epochSatellite.SiteInfo.EstimatedXyz;
double correction = GetSatGravDelayCorrection(svPos, nominalPos);
this.Correction = (correction);
}
internal static void get_earth_nov(ref IEphemeris pEphDisp, double tjd, ref double tdb, ref double[] peb, ref double[] veb, ref double[] pes, ref double[] ves)
{
short i, rc;
double dummy = 0, secdiff = 0;
double ltdb;
double[] lpeb = new double[3];
double[] lveb = new double[3];
double[] lpes = new double[3];
double[] lves = new double[3];
Tdb2Tdt(tjd, ref dummy, ref secdiff);
ltdb = tjd + secdiff / 86400;
try
{
rc = solarsystem_nov(ref pEphDisp, tjd, ltdb, Body.Earth, Origin.Barycentric, ref lpeb, ref lveb);
if (rc != 0)
{
throw new Exceptions.NOVASFunctionException("EphemerisCode:get_earth_nov Earth eph exception", "solarsystem_nov", rc);
}
}
catch (Exception ex)
{
get_earth_tjd_last = 0;
throw;
}
try
{
rc = solarsystem_nov(ref pEphDisp, tjd, ltdb, Body.Earth, Origin.Heliocentric, ref lpes, ref lves);
if (rc != 0)
{
throw new Exceptions.NOVASFunctionException("EphemerisCode:get_earth_nov Earth eph exception", "solarsystem_nov", rc);
}
}
catch (Exception ex)
{
get_earth_tjd_last = 0;
throw;
}
get_earth_tjd_last = tjd;
tdb = ltdb;
for (i = 0; i <= 2; i++)
{
peb[i] = lpeb[i];
veb[i] = lveb[i];
pes[i] = lpes[i];
ves[i] = lves[i];
}
}
internal static short solarsystem_nov(ref IEphemeris ephDisp, double tjd, double tdb, Body planet, Origin origin, ref double[] pos, ref double[] vel)
{
short rc = 0;
if ((ephDisp == null))
{
throw new Exceptions.ValueNotSetException("EphemerisCode:SolarSystem_Nov No emphemeris object supplied");
}
else
{
ephemeris_nov(ref ephDisp, tdb, BodyType.MajorPlanet, (int)planet, "", origin, ref pos, ref vel);
}
return(rc);
}
public override void Correct(EpochSatellite epochSatellite)
{
if (AntennaDataSource == null || SatInfoService == null)
{
return;
}
Time gpsTime = epochSatellite.RecevingTime;
// XYZ sunPosition = epochSatellite.EpochInfo.DataSouceProvider.UniverseObjectProvider.GetSunPosition(gpsTime);// 这个可以每个历元算一次，有待优化。？？？czs 2014.10.05
//下面是新的计算太阳位置
Time tutc = gpsTime.GpstToUtc();
//查找地球自转信息
Gnsser.Data.ErpItem erpv = null;
if (ErpDataService != null)
{
erpv = ErpDataService.Get(tutc);
}
if (erpv == null)
{
erpv = ErpItem.Zero;
}
XYZ sunPosition = new XYZ();
UniverseObjectProvider.GetSunPosition(gpsTime, erpv, ref sunPosition);
IEphemeris sat = epochSatellite.Ephemeris;
XYZ svPos = sat.XYZ;
XYZ receiverPosition = epochSatellite.SiteInfo.EstimatedXyz;
SatelliteNumber prn = epochSatellite.Prn;
SatInfoFile periodSatInfoCollection = SatInfoService.SatInfoFile;
IAntenna antenna = AntennaDataSource.Get(prn.ToString(), gpsTime);
double correction = GetSatPhaseCenterCorectValue(prn, gpsTime, svPos, receiverPosition, sunPosition, periodSatInfoCollection, antenna);
this.Correction = (correction);//
}
/// <summary>
/// 改正
/// </summary>
/// <param name="epochSatellite"></param>
public override void Correct(EpochSatellite epochSatellite)
{
Dictionary <RinexSatFrequency, double> correction = new Dictionary <RinexSatFrequency, double>();
IEphemeris sat = epochSatellite.Ephemeris;
XYZ satPos = sat.XYZ;
XYZ receiverPosition = epochSatellite.SiteInfo.EstimatedXyz;
XYZ ray = satPos - receiverPosition;
GeoCoord rcvGeoCoord = epochSatellite.SiteInfo.ApproxGeoCoord;
int i = 0;
List <RinexSatFrequency> frequences = epochSatellite.RinexSatFrequences;
foreach (var item in frequences)
{
XYZ dant1 = GetSatAntOff(epochSatellite.Prn, item, epochSatellite.Ephemeris, epochSatellite.Ephemeris.Time);
//Compute vector station-satellite, in ECEF
//Rotate vector ray to UEN reference frame
//此处修改为 NEU 坐标系。
//NEU rayNeu = CoordTransformer.XyzToNeu(ray, rcvGeoCoord, AngleUnit.Degree);
//double rangeCorretion = CoordUtil.GetDirectionLength(dant1, epochSatellite.Polar);
//ray = XYZ.RotateZ(ray, lon);
//ray = XYZ.RotateY(ray, -lat);
//Convert ray to an unitary vector
// XYZ xyzNeu = new XYZ(rayNeu.N, rayNeu.E, rayNeu.U);
//NEU unit = rayNeu.UnitNeuVector();
//计算沿着射线方向的改正数。Compute corrections = displacement vectors components along ray direction.
XYZ unit2 = ray.UnitVector();
double range2 = dant1.Dot(unit2);
//double correctForL = dant1.Dot(unit);
//double rang = dant1.Dot(unit);
if (range2 != 0)
{
correction.Add(item, range2);
}
i++;
}
this.Correction = (correction);
}
////
//// Ephemeris() - Wrapper for external ephemeris generator
////
//// The ephemeris generator must support a single method:
////
//// result(6) = GetPositionAndVelocity(tjd, Type, Number, Name)
////
//// tjd Terrestrial Julian Date
//// Type Type of body: 0 = major planet, Sun, or Moon
//// 1 = minor planet
//// Number: For Type = 0: Mercury = 1, ..., Pluto = 9
//// For Type = 1: minor planet number or 0 for unnumbered MP
//// Name: For Type = 0: n/a
//// For Type = 1: n/a for numbered MPs. For unnumbered MPs, this
//// is the MPC PACKED designation.
//// result A SAFEARRAY of VARIANT, each element VT_R8 (double). Elements
//// 0-2 are the position vector of the body, elements 3.5 are the
//// velocity vector of the body.
////
internal static void ephemeris_nov(IEphemeris ephDisp, double tjd, BodyType btype, int num, string name, Origin origin, ref double[] pos, ref double[] vel)
{
int i = 0;
double[] posvel = new double[7];
double[] p = new double[3];
double[] v = new double[3];
//Dim bdy As bodystruct
//Dim org As NOVAS2Net.Origin
//Dim rc As Short
//Dim TL As New TraceLogger("", "EphNov")
//TL.Enabled = True
// TL.LogMessage("EphNov", "Start")
////
//// Check inputs
////
if (ephDisp == null)
{
throw (new Exceptions.ValueNotSetException("Ephemeris_nov Ephemeris object not set"));
}
else
{
if ((origin != origin.Barycentric) && (origin != origin.Heliocentric))
{
throw (new Utilities.Exceptions.InvalidValueException("Ephemeris_nov Origin is neither barycentric or heliocentric"));
}
////
//// Call the ephemeris for the heliocentric J2000.0 equatorial coordinates
BodyType kbtype = default(BodyType);
//TL.LogMessage("EphNov", "Before Case Btype")
if (btype == BodyType.Comet)
{
kbtype = BodyType.Comet;
}
else if (btype == BodyType.MajorPlanet)
{
kbtype = BodyType.MajorPlanet;
}
else if (btype == BodyType.MinorPlanet)
{
kbtype = BodyType.MinorPlanet;
}
Body knum = default(Body);
switch (num)
{
case 1:
knum = Body.Mercury;
break;
case 2:
knum = Body.Venus;
break;
case 3:
knum = Body.Earth;
break;
case 4:
knum = Body.Mars;
break;
case 5:
knum = Body.Jupiter;
break;
case 6:
knum = Body.Saturn;
break;
case 7:
knum = Body.Uranus;
break;
case 8:
knum = Body.Neptune;
break;
case 9:
knum = Body.Pluto;
break;
}
ephDisp.BodyType = kbtype;
ephDisp.Number = knum;
if (name != "")
{
ephDisp.Name = name;
}
//TL.LogMessage("EphNov", "Before ephDisp GetPosAndVel")
posvel = ephDisp.GetPositionAndVelocity(tjd);
//TL.LogMessage("EphNov", "After ephDisp GetPosAndVel")
}
if (origin == origin.Barycentric)
{
double[] sun_pos = new double[4];
double[] sun_vel = new double[4];
//// CHICKEN AND EGG ALERT!!! WE CANNOT CALL OURSELVES FOR
//// BARYCENTER CALCULATION -- AS AN APPROXIMATION, WE USE
//// OUR INTERNAL SOLSYS3() FUNCTION TO GET THE BARYCENTRIC
//// SUN. THIS SHOULD BE "GOOD ENOUGH". IF WE EVER GET
//// AN EPHEMERIS GEN THAT HANDLES BARYCENTRIC, WE CAN
//// CAN THIS...
//TL.LogMessage("EphNov", "Before solsys3")
solsys3_nov(tjd, Body.Sun, origin.Barycentric, ref sun_pos, ref sun_vel);
//TL.LogMessage("EphNov", "After solsys3")
for (i = 0; i <= 2; i++)
{
posvel[i] += sun_pos[i];
posvel[i + 3] += (int)(sun_vel[i]);
}
}
for (i = 0; i <= 2; i++)
{
pos[i] = posvel[i];
vel[i] = posvel[i + 3];
}
//TL.Enabled = False
//TL.Dispose()
}
/// <summary>
/// 星历矫正
/// </summary>
/// <param name="info"></param>
/// <returns></returns>
public override bool Revise(ref EpochInformation info)
{
BuildEphemerisReviser(info);
foreach (var sat in info)
{
EmissionEphemerisRolver solver = null;
//if (info.Time.Correction == 0
// || info.SiteInfo.EstimatedXyzRms.Length > 100
// || Math.Abs(info.Time.Correction) > 86400) //没有平差，或坐标初值不准确的情况下,直接采用伪距估算卫星发射时刻
{
solver = new EmissionEphemerisRolverWithRange(EphemerisService, Context, sat);
}
//else //坐标初值已经算出，采用精确坐标计算卫星发射时刻
//{
// solver = new EmissionEphemerisRolverWithCoord(service, DataSouceProvider, sat);
//}
IEphemeris eph = solver.Get(); //第一次获取
if (eph == null)
{ //采用第二星历服务
if (SecondEphemerisService != null)
{
solver = new EmissionEphemerisRolverWithRange(SecondEphemerisService, Context, sat);
eph = solver.Get();//第2次获取
}
if (eph == null)
{
continue;
}
}
//查看差多少，如果少于1cm，则极速取消，2018.10.06， hmx， czs
eph = Revise(eph); //测试校正，差了100多米啊！！！
sat.Ephemeris = eph; //第一次赋值
//update and once more //第二次计算
eph = solver.Get();
if (eph == null)
{
continue;
}
eph = Revise(eph);
if (false)//测试校正，差了0.1m ！！！
{
var diff = eph.XYZ - sat.Ephemeris.XYZ;
int i = 0;
}
sat.Ephemeris = eph;
//eph = solver.Get();//第3次计算
//if (eph == null) continue;
//eph = Revise(eph);
//if (true)//测试校正，差了0.0m ！！！
//{
// var diff = eph.XYZ - sat.Ephemeris.XYZ;
// int i = 0;
//}
}
return(true);
}
/// <summary>
/// 用于比较排序。
/// </summary>
/// <param name="other"></param>
/// <returns></returns>
public int CompareTo(IEphemeris other)
{
return((int)this.Time.CompareTo(other.Time));
}
/// <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);
}
internal static void ephemeris_nov(ref IEphemeris ephDisp, double tjd, BodyType btype, int num, string name, Origin origin, ref double[] pos, ref double[] vel)
{
int i;
double[] posvel, p, v;
if ((ephDisp == null))
{
throw new Exceptions.ValueNotSetException("Ephemeris_nov Ephemeris object not set");
}
else
{
if (((origin != Origin.Barycentric) & (origin != Origin.Heliocentric)))
{
throw new Utilities.Exceptions.InvalidValueException("Ephemeris_nov Origin is neither barycentric or heliocentric");
}
BodyType kbtype;
switch (btype)
{
case BodyType.Comet:
kbtype = BodyType.Comet;
break;
case BodyType.MajorPlanet:
kbtype = BodyType.MajorPlanet;
break;
case BodyType.MinorPlanet:
kbtype = BodyType.MinorPlanet;
break;
default:
throw new NotSupportedException();
}
Body knum;
switch (num)
{
case 1:
knum = Body.Mercury;
break;
case 2:
knum = Body.Venus;
break;
case 3:
knum = Body.Earth;
break;
case 4:
knum = Body.Mars;
break;
case 5:
knum = Body.Jupiter;
break;
case 6:
knum = Body.Saturn;
break;
case 7:
knum = Body.Uranus;
break;
case 8:
knum = Body.Neptune;
break;
case 9:
knum = Body.Pluto;
break;
default:
throw new ArgumentException();
}
ephDisp.BodyType = kbtype;
ephDisp.Number = knum;
if ((name != ""))
{
ephDisp.Name = name;
}
posvel = ephDisp.GetPositionAndVelocity(tjd);
if ((origin == Origin.Barycentric))
{
double[] sun_pos = new double[3], sun_vel = new double[3];
solsys3_nov(tjd, Body.Sun, Origin.Barycentric, ref sun_pos, ref sun_vel);
for (i = 0; i <= 2; i++)
{
posvel[i] += sun_pos[i];
posvel[i + 3] += sun_vel[i];
}
}
for (i = 0; i <= 2; i++)
{
pos[i] = posvel[i];
vel[i] = posvel[i + 3];
}
}
}
public abstract bool Revise(ref IEphemeris eph);
internal static void get_earth_nov(ref IEphemeris pEphDisp, double tjd, ref double tdb, ref double[] peb, ref double[] veb, ref double[] pes, ref double[] ves)
{
short i = 0;
short rc = 0;
double dummy = 0;
double secdiff = 0;
// static double tjd_last = 0.0; VBConversions Note: Static variable moved to class level and renamed get_earth_nov_tjd_last. Local static variables are not supported in C#.
double ltdb = 0;
double[] lpeb = new double[4];
double[] lveb = new double[4];
double[] lpes = new double[4];
double[] lves = new double[4];
//Dim TL As New TraceLogger("", "get_earth_nov")
//TL.Enabled = True
//TL.LogMessage("get_earth_nov", "Start")
////
//// Compute the TDB Julian date corresponding to 'tjd'.
////
//If (Abs(tjd - tjd_last) > 0.000001) Then 'Optimize repeated calls
Tdb2Tdt(tjd, dummy, secdiff);
//TL.LogMessage("get_earth_nov", "after tbd2tdt")
ltdb = tjd + secdiff / 86400.0;
////
//// Get position and velocity of the Earth wrt barycenter of
//// solar system and wrt center of the sun. These calls reflect
//// exceptions thrown by the attached ephemeris generator, so
//// we just return the hr ... the ErrorInfo is already set!
////
try {
//TL.LogMessage("get_earth_nov", "before solsysnov barycentric")
rc = solarsystem_nov(ref pEphDisp, tjd, ltdb, Body.Earth, Origin.Barycentric, ref lpeb, ref lveb);
//TL.LogMessage("get_earth_nov", "after solsysnov barycentric")
if (rc != 0)
{
throw (new Exceptions.NOVASFunctionException("EphemerisCode:get_earth_nov Earth eph exception", "solarsystem_nov", rc));
}
}
catch (Exception) {
get_earth_nov_tjd_last = 0.0;
throw;
}
try {
//TL.LogMessage("get_earth_nov", "before solsysnov heliocentric")
rc = solarsystem_nov(ref pEphDisp, tjd, ltdb, Body.Earth, Origin.Heliocentric, ref lpes, ref lves);
//TL.LogMessage("get_earth_nov", "after solsysnov heliocentric")
if (rc != 0)
{
throw (new Exceptions.NOVASFunctionException("EphemerisCode:get_earth_nov Earth eph exception", "solarsystem_nov", rc));
}
}
catch (Exception) {
get_earth_nov_tjd_last = 0.0;
throw;
}
get_earth_nov_tjd_last = tjd;
//End If
tdb = ltdb;
for (i = 0; i <= 2; i++)
{
peb[i] = lpeb[i];
veb[i] = lveb[i];
pes[i] = lpes[i];
ves[i] = lves[i];
}
//TL.Enabled = False
//TL.Dispose()
//TL = Nothing
}
/// <summary>
/// 改正
/// </summary>
/// <param name="epochSatellite"></param>
public override void Correct(EpochSatellite epochSatellite)
{
if (AntennaDataSource == null || SatInfoService == null)
{
return;
}
//Time gpsTime = epochSatellite.RecevingTime;
Time emmissiontime = epochSatellite.EmissionTime;
// XYZ sunPosition = epochSatellite.EpochInfo.DataSouceProvider.UniverseObjectProvider.GetSunPosition(gpsTime);// 这个可以每个历元算一次，有待优化。？？？czs 2014.10.05
//下面是新的计算太阳位置
//Time tutc = gpsTime.GpstToUtc();
//查找地球自转信息
Gnsser.Data.ErpItem erpv = null;
if (ErpDataService != null)
{
//erpv = ErpDataService.Get(tutc);
erpv = ErpDataService.Get(emmissiontime);
}
if (erpv == null)
{
erpv = ErpItem.Zero;
}
XYZ sunPosition = new XYZ();
UniverseObjectProvider.GetSunPosition(emmissiontime, erpv, ref sunPosition);
//UniverseObjectProvider.GetSunPosition(gpsTime, erpv, ref sunPosition);
IEphemeris sat = epochSatellite.Ephemeris;
XYZ svPos = sat.XYZ;
XYZ receiverPosition = epochSatellite.SiteInfo.EstimatedXyz;
var prn = epochSatellite.Prn;
var satType = prn.SatelliteType;
SatInfoFile periodSatInfoCollection = SatInfoService.SatInfoFile;
IAntenna antenna = AntennaDataSource.Get(prn.ToString(), emmissiontime);
if (antenna == null)
{
if (!noAntSats.Contains(prn))
{
log.Warn(prn + " 没有获取到天线信息！");
noAntSats.Add(prn);
}
return;
}
List <RinexSatFrequency> frequences = epochSatellite.RinexSatFrequences;
Dictionary <RinexSatFrequency, double> correction = new Dictionary <RinexSatFrequency, double>();
GeoCoord rcvGeoCoord = epochSatellite.SiteInfo.ApproxGeoCoord;
int i = 0;
foreach (var item in frequences)
{
double rang = GetSatPhaseCenterCorectValue(prn, item, emmissiontime, svPos, receiverPosition, rcvGeoCoord, sunPosition, periodSatInfoCollection, antenna);
if (rang != 0 && frequences.Count > i)
{
correction.Add(frequences[i], rang);
}
i++;
}
this.Correction = (correction);//
}
