private void ProcessTLE_Click(object sender, RoutedEventArgs e)
{
var lines = TLEedit.Text.Split(new char[] { '\n', '\r' }, 3);
if (lines.Count() < 3) return;
var nm = lines[0].TrimEnd(new char[] { ' ' });
tle = new Tle(nm, lines[1], lines[2]);
}
/// <summary>
/// Standard constructor.
/// </summary>
/// <param name="tle">TLE data.</param>
/// <param name="name">Optional satellite name.</param>
public Satellite(Tle tle, string name = "")
{
Orbit = new Orbit(tle);
if (name == "")
{
Name = Orbit.SatName;
}
else
{
Name = name;
}
}
/// <summary>
/// Standard constructor.
/// </summary>
/// <param name="tle">TLE data.</param>
/// <param name="name">Optional satellite name.</param>
public Satellite(Tle tle, string name = "")
{
Orbit = new Orbit(tle);
if (name == "")
{
Name = Orbit.SatName;
}
else
{
Name = name;
}
}
/// <summary>
/// Standard constructor.
/// </summary>
/// <param name="tle">Two-line element orbital parameters.</param>
public Orbit(Tle tle)
{
Tle = tle;
Epoch = Tle.EpochJulian;
m_Inclination = GetRad(Tle.Field.Inclination);
m_Eccentricity = Tle.GetField(Tle.Field.Eccentricity);
m_RAAN = GetRad(Tle.Field.Raan);
m_ArgPerigee = GetRad(Tle.Field.ArgPerigee);
m_BStar = Tle.GetField(Tle.Field.BStarDrag);
m_Drag = Tle.GetField(Tle.Field.MeanMotionDt);
m_MeanAnomaly = GetRad(Tle.Field.MeanAnomaly);
m_TleMeanMotion = Tle.GetField(Tle.Field.MeanMotion);
// Recover the original mean motion and semimajor axis from the
// input elements.
double mm = TleMeanMotion;
double rpmin = mm * Globals.TwoPi / Globals.MinPerDay; // rads per minute
double a1 = Math.Pow(Globals.Xke / rpmin, 2.0 / 3.0);
double e = Eccentricity;
double i = Inclination;
double temp = (1.5 * Globals.Ck2 * (3.0 * Globals.Sqr(Math.Cos(i)) - 1.0) /
Math.Pow(1.0 - e * e, 1.5));
double delta1 = temp / (a1 * a1);
double a0 = a1 *
(1.0 - delta1 *
((1.0 / 3.0) + delta1 *
(1.0 + 134.0 / 81.0 * delta1)));
double delta0 = temp / (a0 * a0);
m_rmMeanMotionRec = rpmin / (1.0 + delta0);
m_aeAxisSemiMajorRec = a0 / (1.0 - delta0);
m_aeAxisSemiMinorRec = m_aeAxisSemiMajorRec * Math.Sqrt(1.0 - (e * e));
m_kmPerigeeRec = Globals.Xkmper * (m_aeAxisSemiMajorRec * (1.0 - e) - Globals.Ae);
m_kmApogeeRec = Globals.Xkmper * (m_aeAxisSemiMajorRec * (1.0 + e) - Globals.Ae);
if (Period.TotalMinutes >= 225.0)
{
// SDP4 - period >= 225 minutes.
NoradModel = new NoradSDP4(this);
}
else
{
// SGP4 - period < 225 minutes
NoradModel = new NoradSGP4(this);
}
}
/// <summary>
/// Standard constructor.
/// </summary>
/// <param name="tle">Two-line element orbital parameters.</param>
public Orbit(Tle tle)
{
Tle = tle;
Epoch = Tle.EpochJulian;
m_Inclination = GetRad(Tle.Field.Inclination);
m_Eccentricity = Tle.GetField(Tle.Field.Eccentricity);
m_RAAN = GetRad(Tle.Field.Raan);
m_ArgPerigee = GetRad(Tle.Field.ArgPerigee);
m_BStar = Tle.GetField(Tle.Field.BStarDrag);
m_Drag = Tle.GetField(Tle.Field.MeanMotionDt);
m_MeanAnomaly = GetRad(Tle.Field.MeanAnomaly);
m_TleMeanMotion = Tle.GetField(Tle.Field.MeanMotion);
// Recover the original mean motion and semimajor axis from the
// input elements.
double mm = TleMeanMotion;
double rpmin = mm * Globals.TwoPi / Globals.MinPerDay; // rads per minute
double a1 = Math.Pow(Globals.Xke / rpmin, 2.0 / 3.0);
double e = Eccentricity;
double i = Inclination;
double temp = (1.5 * Globals.Ck2 * (3.0 * Globals.Sqr(Math.Cos(i)) - 1.0) /
Math.Pow(1.0 - e * e, 1.5));
double delta1 = temp / (a1 * a1);
double a0 = a1 *
(1.0 - delta1 *
((1.0 / 3.0) + delta1 *
(1.0 + 134.0 / 81.0 * delta1)));
double delta0 = temp / (a0 * a0);
m_rmMeanMotionRec = rpmin / (1.0 + delta0);
m_aeAxisSemiMajorRec = a0 / (1.0 - delta0);
m_aeAxisSemiMinorRec = m_aeAxisSemiMajorRec * Math.Sqrt(1.0 - (e * e));
m_kmPerigeeRec = Globals.Xkmper * (m_aeAxisSemiMajorRec * (1.0 - e) - Globals.Ae);
m_kmApogeeRec = Globals.Xkmper * (m_aeAxisSemiMajorRec * (1.0 + e) - Globals.Ae);
if (Period.TotalMinutes >= 225.0)
{
// SDP4 - period >= 225 minutes.
NoradModel = new NoradSDP4(this);
}
else
{
// SGP4 - period < 225 minutes
NoradModel = new NoradSGP4(this);
}
}
public static void Main()
{
string str1 = "ISS (ZARYA) ";
string str2 = "1 25544U 98067A 13222.08683053 .00004563 00000-0 87202-4 0 3628";
string str3 = "2 25544 51.6485 201.2720 0004128 298.2475 180.8024 15.50224716843064";
Tle tle1 = new Tle(str1, str2, str3);
Site siteEquator = new Site(52.1259155, -0.219355, 0);
Orbit orbit = new Orbit(tle1);
DateTime now = DateTime.Now;
Track t = new Track();
t.GetPasses(siteEquator, orbit, DateTime.Now);
while (true)
{
EciTime eciSDP4 = orbit.GetPosition(DateTime.Now);
Topo topoLook = siteEquator.GetLookAngle(eciSDP4);
CoordGeo g = eciSDP4.ToGeo();
Debug.Print(g.Latitude.ToString() + " " + g.Longitude.ToString() + " " + g.Altitude.ToString());
Thread.Sleep(1000);
}
}
// ///////////////////////////////////////////////////////////////////
public Orbit(Tle tle)
{
m_tle = tle;
m_jdEpoch = m_tle.EpochJulian;
// Recover the original mean motion and semimajor axis from the
// input elements.
double mm = mnMotion;
double rpmin = mm * Globals.TWOPI / Globals.MIN_PER_DAY; // rads per minute
double a1 = Math.Pow(Globals.XKE / rpmin, Globals.TWOTHRD);
double e = Eccentricity;
double i = Inclination;
double temp = (1.5 * Globals.CK2 * (3.0 * Globals.Sqr(Math.Cos(i)) - 1.0) /
Math.Pow(1.0 - e * e, 1.5));
double delta1 = temp / (a1 * a1);
double a0 = a1 *
(1.0 - delta1 *
((1.0 / 3.0) + delta1 *
(1.0 + 134.0 / 81.0 * delta1)));
double delta0 = temp / (a0 * a0);
m_rmMeanMotionRec = rpmin / (1.0 + delta0);
m_aeAxisSemiMajorRec = a0 / (1.0 - delta0);
m_aeAxisSemiMinorRec = m_aeAxisSemiMajorRec * Math.Sqrt(1.0 - (e * e));
m_kmPerigeeRec = Globals.XKMPER * (m_aeAxisSemiMajorRec * (1.0 - e) - Globals.AE);
m_kmApogeeRec = Globals.XKMPER * (m_aeAxisSemiMajorRec * (1.0 + e) - Globals.AE);
if (Period.TotalMinutes >= 225.0)
{
// SDP4 - period >= 225 minutes.
m_NoradModel = new NoradSDP4(this);
}
else
{
// SGP4 - period < 225 minutes
m_NoradModel = new NoradSGP4(this);
}
}
void TimerTick(Timer timer)
{
string str1 = "ISS (ZARYA) ";
string str2 = "1 25544U 98067A 15352.54319571 .00014358 00000-0 21741-3 0 9990";
string str3 = "2 25544 51.6437 244.0274 0008333 295.0996 127.4199 15.54892795976727";
Tle tle1 = new Tle(str1, str2, str3);
Site siteEquator = new Site(52.454935, 0.201279, 0);
Orbit orbit = new Orbit(tle1);
DateTime now = DateTime.Now;
EciTime eciSDP4 = orbit.GetPosition(now);
Topo topoLook = siteEquator.GetLookAngle(eciSDP4);
CoordGeo coords = eciSDP4.ToGeo();
UpdateTextBlock(RealTimeClock.GetDateTime().ToString(@"dd\/MM\/yyyy HH:mm"), "date");
UpdateTextBlock(coords.Altitude.ToString("F2"), "satAlt");
UpdateTextBlock(coords.Latitude.ToString("F2"), "satLat");
UpdateTextBlock((360 - coords.Longitude).ToString("F2"), "satLon");
UpdateTextBlock(topoLook.AzimuthDeg.ToString("F2"), "satAz");
UpdateTextBlock(topoLook.ElevationDeg.ToString("F2"), "satEl");
}
// ///////////////////////////////////////////////////////////////////
protected double GetDeg(Tle.Field fld)
{
return(Tle.GetField(fld, Tle.Unit.Degrees));
}
public static Tle[] TlesFromTxt(string filename)
{
ArrayList list1 = new ArrayList();
StreamReader sr = new StreamReader(filename);
int i = 1;
string line1 = "", line2 = "", line3 = "";
while (sr.Peek() >= 0)
{
switch (i)
{
case 1:
line1 = sr.ReadLine();
i++;
break;
case 2:
line2 = sr.ReadLine();
i++;
break;
case 3:
line3 = sr.ReadLine();
Tle tle0 = new Tle(line1, line2, line3);
list1.Add(tle0);
i = 1;
break;
}
}
Tle[] tles = (Tle[])(list1).ToArray(typeof(Tle));
return tles;
}
// ///////////////////////////////////////////////////////////////////
protected double GetRad(Tle.Field fld)
{
return(Tle.GetField(fld, Tle.Unit.Radians));
}
// ///////////////////////////////////////////////////////////////////
protected double GetDeg(Tle.Field fld)
{
return Tle.GetField(fld, Tle.Unit.Degrees);
}
// //////////////////////////////////////////////////////////////////////////
public Tle(Tle tle) :
this(tle.Name, tle.Line1, tle.Line2)
{
}
// ///////////////////////////////////////////////////////////////////
protected double GetRad(Tle.Field fld)
{
return Tle.GetField(fld, Tle.Unit.Radians);
}
/// <summary>
/// 计算DOP值，返回可见卫星数
/// </summary>
/// <param name="tle"></param>
/// <param name="time">要计算的时间</param>
/// <param name="B">测站的，单位：度</param>
/// <param name="L"></param>
/// <param name="H">单位：米</param>
/// <param name="cor_limit">截止高度角，度</param>
/// <param name="GDOP"></param>
/// <param name="PDOP"></param>
/// <param name="HDOP"></param>
/// <param name="VDOP"></param>
/// <param name="TDOP"></param>
/// <returns></returns>
public static int CalcDops(Tle[] tles, DateTime time, double B, double L, double H, double cor_limit, ref double GDOP, ref double PDOP, ref double HDOP, ref double VDOP, ref double TDOP)
{
double x2 = 0; double y2 = 0; double z2 = 0; //测站坐标
BLToXYZ(B / 180 * Math.PI, L / 180 * Math.PI, H, ref x2, ref y2, ref z2);
ArrayList temp = new ArrayList();
Site siteEquator2 = new Site(B, L, H);
Tle tle;
Orbit orbit;
Eci eci;
CoordGeo cg;
int sum = 0;
for (int i = 0; i < tles.Length; i++)
{
tle = tles[i];
orbit = new Orbit(tle);
eci = orbit.GetPosition(time);
double x = eci.Position.X * 1000;
double y = eci.Position.Y * 1000;
double z = eci.Position.Z * 1000; //化成米
cg = eci.ToGeo();
CoordTopo topoLook = siteEquator2.GetLookAngle(eci);
topoLook.Elevation = Globals.Rad2Deg(topoLook.Elevation);
topoLook.Azimuth = Globals.Rad2Deg(topoLook.Azimuth); //化成度
if (topoLook.Elevation > cor_limit)
{
sum++;
double d_x = x - x2;
double d_y = y - y2;
double d_z = z - z2;
double r2 = Math.Sqrt(d_x * d_x + d_y * d_y + d_z * d_z);
temp.Add(d_x / r2);
temp.Add(d_y / r2);
temp.Add(d_z / r2);
}
}
NNMatrix Q = new NNMatrix(sum, 4);
NNMatrix Q_x = new NNMatrix(4, 4);
for (int j = 0; j < temp.Count; j++)
{
if ((j + 1) % 3 == 1)
{
Q.Matrix[j / 3, 0] = (double)temp[j];
}
else if ((j + 1) % 3 == 2)
{
Q.Matrix[j / 3, 1] = (double)temp[j];
}
else if ((j + 1) % 3 == 0)
{
Q.Matrix[j / 3, 2] = (double)temp[j];
}
Q.Matrix[j / 3, 3] = 1;
}
Q_x = NNMatrix.Invers(NNMatrix.Transpos(Q) * Q);
GDOP = Math.Sqrt(Q_x.Matrix[0, 0] + Q_x.Matrix[1, 1] + Q_x.Matrix[2, 2] + Q_x.Matrix[3, 3]);
PDOP = Math.Sqrt(Q_x.Matrix[0, 0] + Q_x.Matrix[1, 1] + Q_x.Matrix[2, 2]);
HDOP = Math.Sqrt(Q_x.Matrix[0, 0] + Q_x.Matrix[1, 1]);
VDOP = Math.Sqrt(Q_x.Matrix[2, 2]);
TDOP = Math.Sqrt(Q_x.Matrix[3, 3]);
return sum;
}
// //////////////////////////////////////////////////////////////////////////
public Tle(Tle tle) :
this(tle.Name, tle.Line1, tle.Line2)
{
}
// /////////////////////////////////////////////////////////////////// protected double GetRad(Tle.Field fld) => Tle.GetField(fld, Tle.Unit.Radians);
// /////////////////////////////////////////////////////////////////// protected double GetDeg(Tle.Field fld) => Tle.GetField(fld, Tle.Unit.Degrees);
