示例#1
0
        // /////////////////////////////////////////////////////////////////////
        static void Main(string[] args)
        {
            // Sample obsCodeode to test the SGP4 and SDP4 implementation. The test
            // TLEs come from the NORAD document "Space Track Report No. 3".

            // Test SGP4
            string str1 = "SGP4 Test";
            string str2 = "1 88888U          80275.98708465  .00073094  13844-3  66816-4 0     8";
            string str3 = "2 88888  72.8435 115.9689 0086731  52.6988 110.5714 16.05824518   105";

            TwoLineElement tle1 = new TwoLineElement(str1, str2, str3);

            PrintPosVel(tle1);

            Console.WriteLine();

            // Test SDP4
            str1 = "SDP4 Test";
            str2 = "1 11801U          80230.29629788  .01431103  00000-0  14311-1       8";
            str3 = "2 11801  46.7916 230.4354 7318036  47.4722  10.4117  2.28537848     6";

            TwoLineElement tle2 = new TwoLineElement(str1, str2, str3);

            PrintPosVel(tle2);

            Console.WriteLine("\nExample output:");

            // Example: Define a location on the earth, then determine the look-angle
            // to the SDP4 satellite defined above.

            // Create an orbit object using the SDP4 TLE object.
            // Satellite satSDP4 = new Satellite(tle2);
            Orbit orbit = new Orbit(tle2);
            // Get the location of the satellite from the Orbit object. The
            // earth-centered inertial information is placed into eciSDP4.
            // Here we ask for the location of the satellite 90 minutes after
            // the TLE epoch.
            TimedMotionState eciSDP4 = orbit.PositionEci(90.0);

            // Now create a site object. Site objects represent a location on the
            // surface of the earth. Here we arbitrarily select a point on the
            // equator.
            GeoCoord siteEquator = new GeoCoord(0.0, -100.0, 0); // 0.00 N, 100.00 W, 0 km altitude

            // Now get the "look angle" from the site to the satellite.
            // Note that the ECI object "eciSDP4" has a time associated
            // with the coordinates it contains; this is the time at which
            // the look angle is valid.
            TopoCoord topoLook = OrbitUtils.GetSatTopoCoord(eciSDP4, siteEquator);

            // Print out the results. Note that the Azimuth and Elevation are
            // stored in the CoordTopo object as radians. Here we funcKeyToDouble
            // to degrees using Rad2Deg()
            Console.Write("AZ: {0:f3}  EL: {1:f3}\n",
                          topoLook.Azimuth,
                          topoLook.Elevation);
        }
示例#2
0
        private void button_radarCaculate_Click(object sender, EventArgs e)
        {
            bool isGeoCoord = this.radioButton_geoCoord.Checked;

            GeoCoord siteCoord = null;

            if (isGeoCoord)
            {
                siteCoord      = GeoCoord.Parse(this.textBox_coord.Text);
                siteCoord.Unit = AngleUnit.Degree;
            }
            else
            {
                XYZ xyz = XYZ.Parse(this.textBox_coord.Text);
                siteCoord = CoordTransformer.XyzToGeoCoord(xyz);
            }

            TwoLineElement tle = GetTwoLineElement();

            Gnsser.Orbits.Orbit orbit = new Gnsser.Orbits.Orbit(tle);

            double intervalMin = Double.Parse(this.textBox_intervalMin.Text);
            double count       = Int32.Parse(this.textBox_count.Text);

            lonlats = new List <AnyInfo.Geometries.Point>();
            lonlats.Add(new AnyInfo.Geometries.Point(siteCoord, "SitePoint"));
            for (int i = 0; i < count; i++)
            {
                double           time     = i * intervalMin;
                TimedMotionState eciSDP4  = orbit.PositionEci(time);
                TopoCoord        topoLook = OrbitUtils.GetSatTopoCoord(eciSDP4, siteCoord);

                if (topoLook.Elevation > 0)
                {
                    GeoCoord geoCoord = CoordTransformer.XyzToGeoCoord(eciSDP4.Position * 1000, AngleUnit.Degree);
                    lonlats.Add(new AnyInfo.Geometries.Point(geoCoord, i + ""));
                }
            }
        }
示例#3
0
        /// <summary>
        /// 根据卫星位置和测站位置计算其在站星坐标系中的位置。
        /// Returns the topo-centric (azimuth, elevation, etc.) coordinates for
        /// a target object described by the given ECI coordinates.
        /// </summary>
        /// <param name="satPos">The ECI coordinates of the target object.</param>
        /// <param name="siteCoord">The ECI coordinates of the 观测站</param>
        /// <returns>The look angle to the target object.</returns>
        public static TopoCoord GetSatTopoCoord(TimedMotionState satPos, GeoCoord siteCoord)
        {
            // Calculate the ECI coordinates for this Site object at the time of interest.
            Julian      date    = satPos.Date;
            MotionState sitePos = OrbitUtils.GetMovingState(siteCoord, date);
            XYZ         vecV    = satPos.Velocity - sitePos.Velocity;
            XYZ         vecP    = satPos.Position - sitePos.Position;

            // The site's Local Mean Sidereal Time at the time of interest.
            double thetaRad = date.GetLocalMeanSiderealTime(siteCoord.Lon, false);

            double sinLat   = Math.Sin(siteCoord.Lat);
            double cosLat   = Math.Cos(siteCoord.Lat);
            double sinTheta = Math.Sin(thetaRad);
            double cosTheta = Math.Cos(thetaRad);

            double top_s = sinLat * cosTheta * vecP.X +
                           sinLat * sinTheta * vecP.Y -
                           cosLat * vecP.Z;
            double top_e = -sinTheta * vecP.X +
                           cosTheta * vecP.Y;
            double top_z = cosLat * cosTheta * vecP.X +
                           cosLat * sinTheta * vecP.Y +
                           sinLat * vecP.Z;
            double az = Math.Atan(-top_e / top_s);

            if (top_s > 0.0)
            {
                az += OrbitConsts.PI;
            }

            if (az < 0.0)
            {
                az += 2.0 * OrbitConsts.PI;
            }

            double el   = Math.Asin(top_z / vecP.Radius());
            double rate = vecP.Dot(vecV) / vecP.Radius();

            TopoCoord topo = new TopoCoord(
                az,                                // azimuth, radians
                el,                                // elevation, radians
                vecP.Radius(),                     // range
                rate                               // rate, per sec
                );

            #if WANT_ATMOSPHERIC_CORRECTION
            // Elevation correction for atmospheric refraction.
            // Reference:  Astronomical Algorithms by Jean Meeus, pp. 101-104
            // Note:  Correction is meaningless when apparent elevation is below horizon
            topo.Elevation += AngularConvert.DegToRad((1.02 /
                                                       Math.Tan(AngularConvert.DegToRad(AngularConvert.RadToDeg(el) + 10.3 /
                                                                                        (AngularConvert.RadToDeg(el) + 5.11)))) / 60.0);
            if (topo.Elevation < 0.0)
            {
                topo.Elevation = el;    // Reset to true elevation
            }

            if (topo.Elevation > (Consts.PI / 2.0))
            {
                topo.Elevation = (Consts.PI / 2.0);
            }
            #endif
            return(topo);
        }