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505 lines
19 KiB
C++
505 lines
19 KiB
C++
///////////////////////////////////////////////////////////////////////////////////
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// Copyright (C) 2021 Jon Beniston, M7RCE //
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// Copyright (C) 2013 Daniel Warner <contact@danrw.com> //
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// //
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// This program is free software; you can redistribute it and/or modify //
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// it under the terms of the GNU General Public License as published by //
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// the Free Software Foundation as version 3 of the License, or //
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// (at your option) any later version. //
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// //
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// This program is distributed in the hope that it will be useful, //
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// but WITHOUT ANY WARRANTY; without even the implied warranty of //
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// MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the //
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// GNU General Public License V3 for more details. //
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// //
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// You should have received a copy of the GNU General Public License //
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// along with this program. If not, see <http://www.gnu.org/licenses/>. //
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///////////////////////////////////////////////////////////////////////////////////
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#include <cmath>
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#include <CoordTopocentric.h>
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#include <CoordGeodetic.h>
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#include <Observer.h>
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#include <SGP4.h>
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#include "util/units.h"
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#include "satellitetrackersgp4.h"
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// Convert QGP4 DateTime to Qt QDataTime
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static QDateTime dateTimeToQDateTime(DateTime dt)
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{
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QDateTime qdt(QDate(dt.Year(), dt.Month(), dt.Day()), QTime(dt.Hour(), dt.Minute(), dt.Second(), (int)(dt.Microsecond()/1000.0)), Qt::UTC);
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return qdt;
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}
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// Convert Qt QDataTime to QGP4 DateTime
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static DateTime qDateTimeToDateTime(QDateTime qdt)
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{
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QDateTime utc = qdt.toUTC();
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QDate date = utc.date();
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QTime time = utc.time();
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DateTime dt(date.year(), date.month(), date.day(), time.hour(), time.minute(), time.second());
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return dt;
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}
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// Get ground track
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// Throws SatelliteException, DecayedException and TleException
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void getGroundTrack(QDateTime dateTime,
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const QString& tle0, const QString& tle1, const QString& tle2,
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int steps, bool forward,
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QList<QGeoCoordinate *>& coordinates)
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{
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Tle tle = Tle(tle0.toStdString(), tle1.toStdString(), tle2.toStdString());
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SGP4 sgp4(tle);
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OrbitalElements ele(tle);
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double periodMins;
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double timeStep;
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// Note map doesn't support paths wrapping around Earth
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DateTime currentTime = qDateTimeToDateTime(dateTime);
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DateTime endTime;
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if (forward)
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{
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periodMins = ele.Period() * 0.9;
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endTime = currentTime.AddMinutes(periodMins);
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timeStep = periodMins / (steps * 0.9);
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}
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else
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{
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periodMins = ele.Period() * 0.4;
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endTime = currentTime.AddMinutes(-periodMins);
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timeStep = -periodMins / (steps * 0.4);
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}
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coordinates.clear();
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while ((forward && (currentTime < endTime)) || (!forward && (currentTime > endTime)))
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{
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// Calculate satellite position
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Eci eci = sgp4.FindPosition(currentTime);
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// Convert satellite position to geodetic coordinates (lat and long)
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CoordGeodetic geo = eci.ToGeodetic();
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QGeoCoordinate *coord = new QGeoCoordinate(Units::radiansToDegrees(geo.latitude),
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Units::radiansToDegrees(geo.longitude),
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geo.altitude * 1000.0);
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coordinates.append(coord);
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// Map is stretched at poles, so use finer steps
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if (std::abs(Units::radiansToDegrees(geo.latitude)) >= 70)
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currentTime = currentTime.AddMinutes(timeStep/4);
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else
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currentTime = currentTime.AddMinutes(timeStep);
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}
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}
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// Find azimuth and elevation points during a pass
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void getPassAzEl(QLineSeries* azimuth, QLineSeries* elevation, QLineSeries* polar,
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const QString& tle0, const QString& tle1, const QString& tle2,
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double latitude, double longitude, double altitude,
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QDateTime& aos, QDateTime& los)
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{
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try
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{
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Tle tle = Tle(tle0.toStdString(), tle1.toStdString(), tle2.toStdString());
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SGP4 sgp4(tle);
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Observer obs(latitude, longitude, altitude);
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DateTime aosTime = qDateTimeToDateTime(aos);
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DateTime losTime = qDateTimeToDateTime(los);
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DateTime currentTime(aosTime);
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int steps = 20;
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double timeStep = (losTime - aosTime).TotalSeconds() / steps;
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if (timeStep <= 0.0)
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{
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qDebug() << "getPassAzEl: AOS is the same as or after LOS";
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return;
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}
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while (currentTime <= losTime)
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{
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// Calculate satellite position
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Eci eci = sgp4.FindPosition(currentTime);
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// Calculate angle to satellite from antenna
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CoordTopocentric topo = obs.GetLookAngle(eci);
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// Save azimuth and elevation in series
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QDateTime qdt = dateTimeToQDateTime(currentTime);
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if (azimuth != nullptr)
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azimuth->append(qdt.toMSecsSinceEpoch(), Units::radiansToDegrees(topo.azimuth));
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if (elevation != nullptr)
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elevation->append(qdt.toMSecsSinceEpoch(), Units::radiansToDegrees(topo.elevation));
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if (polar != nullptr)
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polar->append(Units::radiansToDegrees(topo.azimuth), 90.0-Units::radiansToDegrees(topo.elevation));
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currentTime = currentTime.AddSeconds(timeStep);
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}
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}
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catch (SatelliteException& se)
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{
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qDebug() << se.what();
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}
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catch (DecayedException& de)
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{
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qDebug() << de.what();
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}
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catch (TleException& tlee)
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{
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qDebug() << tlee.what();
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}
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}
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// Get whether a pass passes through 0 degreees
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bool getPassesThrough0Deg(const QString& tle0, const QString& tle1, const QString& tle2,
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double latitude, double longitude, double altitude,
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QDateTime& aos, QDateTime& los)
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{
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try
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{
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Tle tle = Tle(tle0.toStdString(), tle1.toStdString(), tle2.toStdString());
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SGP4 sgp4(tle);
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Observer obs(latitude, longitude, altitude);
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DateTime aosTime = qDateTimeToDateTime(aos);
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DateTime losTime = qDateTimeToDateTime(los);
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DateTime currentTime(aosTime);
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int steps = 20;
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double timeStep = (losTime - aosTime).TotalSeconds() / steps;
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double prevAz;
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for (int i = 0; i < steps; i++)
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{
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// Calculate satellite position
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Eci eci = sgp4.FindPosition(currentTime);
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// Calculate angle to satellite from antenna
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CoordTopocentric topo = obs.GetLookAngle(eci);
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double az = Units::radiansToDegrees(topo.azimuth);
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if (i == 0)
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prevAz = az;
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// Does it cross 0 degrees?
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if (((prevAz > 270.0) && (az < 90.0)) || ((prevAz < 90.0) && (az >= 270.0)))
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return true;
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prevAz = az;
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currentTime = currentTime.AddSeconds(timeStep);
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}
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}
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catch (SatelliteException& se)
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{
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qDebug() << se.what();
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}
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catch (DecayedException& de)
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{
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qDebug() << de.what();
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}
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catch (TleException& tlee)
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{
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qDebug() << tlee.what();
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}
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return false;
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}
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// Find maximum elevation in a pass
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static double findMaxElevation(Observer& obs1, SGP4& sgp4, const DateTime& aos, const DateTime& los)
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{
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Observer obs(obs1.GetLocation());
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bool running;
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double timeStep = (los - aos).TotalSeconds() / 9.0;
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DateTime currentTime(aos);
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DateTime time1(aos);
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DateTime time2(los);
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double maxElevation;
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do
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{
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running = true;
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maxElevation = -INFINITY;
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while (running && (currentTime < time2))
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{
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Eci eci = sgp4.FindPosition(currentTime);
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CoordTopocentric topo = obs.GetLookAngle(eci);
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if (topo.elevation > maxElevation)
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{
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maxElevation = topo.elevation;
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currentTime = currentTime.AddSeconds(timeStep);
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if (currentTime > time2)
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currentTime = time2;
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}
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else
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running = false;
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}
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time1 = currentTime.AddSeconds(-2.0 * timeStep);
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time2 = currentTime;
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currentTime = time1;
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timeStep = (time2 - time1).TotalSeconds() / 9.0;
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}
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while (timeStep > 1.0);
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return Units::radiansToDegrees(maxElevation);
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}
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// Find the time at which the satellite crossed the minimum elevation required for AOS or LOS
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static DateTime findCrossingPoint(Observer& obs, SGP4& sgp4, const DateTime& initialTime1, const DateTime& initialTime2, double minElevation, bool findingAOS)
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{
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bool running;
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int cnt;
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DateTime time1(initialTime1);
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DateTime time2(initialTime2);
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DateTime middleTime;
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running = true;
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cnt = 0;
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while (running && (cnt++ < 16))
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{
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middleTime = time1.AddSeconds((time2 - time1).TotalSeconds() / 2.0);
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Eci eci = sgp4.FindPosition(middleTime);
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CoordTopocentric topo = obs.GetLookAngle(eci);
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if (topo.elevation > minElevation)
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{
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if (findingAOS)
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time2 = middleTime;
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else
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time1 = middleTime;
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}
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else
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{
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if (findingAOS)
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time1 = middleTime;
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else
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time2 = middleTime;
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}
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if ((time2 - time1).TotalSeconds() < 1.0)
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{
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running = false;
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int us = middleTime.Microsecond();
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middleTime = middleTime.AddMicroseconds(-us);
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middleTime = middleTime.AddSeconds(findingAOS ? 1 : -1);
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}
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}
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running = true;
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cnt = 0;
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while (running && (cnt++ < 6))
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{
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Eci eci = sgp4.FindPosition(middleTime);
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CoordTopocentric topo = obs.GetLookAngle(eci);
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if (topo.elevation > minElevation)
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middleTime = middleTime.AddSeconds(findingAOS ? -1 : 1);
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else
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running = false;
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}
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return middleTime;
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}
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// Find when AOS occured, by stepping backwards
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static DateTime findAOSBackwards(Observer& obs, SGP4& sgp4, DateTime& startTime,
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int predictionPeriod, double minElevation, bool& aosUnknown)
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{
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DateTime previousTime(startTime);
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DateTime currentTime(startTime);
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DateTime endTime(startTime.AddDays(-predictionPeriod));
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while (currentTime >= endTime)
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{
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Eci eci = sgp4.FindPosition(currentTime);
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CoordTopocentric topo = obs.GetLookAngle(eci);
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if (topo.elevation < minElevation)
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{
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aosUnknown = false;
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return findCrossingPoint(obs, sgp4, currentTime, previousTime, minElevation, true);
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}
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previousTime = currentTime;
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currentTime = currentTime - TimeSpan(0, 0, 180);
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}
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aosUnknown = true;
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return currentTime;
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}
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bool inPassWindow(DateTime dateTime, QTime passStartTime, QTime passEndTime, bool utc)
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{
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// Don't compare seconds as not currently settable in GUI
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QDateTime qdt = dateTimeToQDateTime(dateTime);
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if (!utc)
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qdt = qdt.toLocalTime();
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QTime qt(qdt.time().hour(), qdt.time().minute());
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passStartTime = QTime(passStartTime.hour(), passStartTime.minute());
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passEndTime = QTime(passEndTime.hour(), passEndTime.minute());
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// If passEndTime is before passStartTime, then we allow overnight passes
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if (passEndTime > passStartTime)
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{
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return (qt >= passStartTime) && (qt <= passEndTime);
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}
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else
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{
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return (qt <= passEndTime) || (qt >= passStartTime);
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}
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}
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// Create a list of satellite passes, between the given start and end times, that exceed the specified minimum elevation
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// We return an uninitalised QDateTime if AOS or LOS is outside of predictionPeriod
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static QList<SatellitePass *> createPassList(Observer& obs, SGP4& sgp4, DateTime& startTime,
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int predictionPeriod, double minAOSElevation, double minPassElevationDeg,
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QTime passStartTime, QTime passEndTime, bool utc,
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int noOfPasses)
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{
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QList<SatellitePass *> passes;
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bool aos = false;
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bool aosUnknown = true;
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double aosAz;
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double losAz;
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DateTime previousTime(startTime);
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DateTime currentTime(startTime);
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DateTime endTime(startTime.AddDays(predictionPeriod));
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DateTime aosTime;
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DateTime losTime;
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while (currentTime < endTime)
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{
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bool endOfPass = false;
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Eci eci = sgp4.FindPosition(currentTime);
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CoordTopocentric topo = obs.GetLookAngle(eci);
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if (!aos && (topo.elevation > minAOSElevation))
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{
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if (startTime == currentTime)
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{
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// AOS is before startTime
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aosTime = findAOSBackwards(obs, sgp4, startTime, predictionPeriod, minAOSElevation, aosUnknown);
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}
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else
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{
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aosTime = findCrossingPoint(obs, sgp4, previousTime, currentTime, minAOSElevation, true);
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aosUnknown = false;
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}
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aos = true;
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eci = sgp4.FindPosition(aosTime);
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topo = obs.GetLookAngle(eci);
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aosAz = Units::radiansToDegrees(topo.azimuth);
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}
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else if (aos && (topo.elevation < minAOSElevation))
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{
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aos = false;
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endOfPass = true;
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losTime = findCrossingPoint(obs, sgp4, previousTime, currentTime, minAOSElevation, false);
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eci = sgp4.FindPosition(losTime);
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topo = obs.GetLookAngle(eci);
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losAz = Units::radiansToDegrees(topo.azimuth);
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double maxElevationDeg = findMaxElevation(obs, sgp4, aosTime, losTime);
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if ((maxElevationDeg >= minPassElevationDeg)
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&& inPassWindow(aosTime, passStartTime, passEndTime, utc)
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&& inPassWindow(losTime, passStartTime, passEndTime, utc))
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{
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SatellitePass *pass = new SatellitePass;
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pass->m_aos = aosUnknown ? QDateTime() : dateTimeToQDateTime(aosTime);
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pass->m_los = dateTimeToQDateTime(losTime);
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pass->m_maxElevation = maxElevationDeg;
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pass->m_aosAzimuth = aosAz;
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pass->m_losAzimuth = losAz;
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pass->m_northToSouth = std::min(360.0-aosAz, aosAz-0.0) < std::min(360.0-losAz, losAz-0.0);
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passes.append(pass);
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noOfPasses--;
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if (noOfPasses <= 0)
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return passes;
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}
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}
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previousTime = currentTime;
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if (endOfPass)
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currentTime = currentTime + TimeSpan(0, 30, 0); // 30 minutes - no orbit likely to be that fast
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else
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currentTime = currentTime + TimeSpan(0, 0, 180);
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if (currentTime > endTime)
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currentTime = endTime;
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}
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if (aos)
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{
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// Pass still in progress at end time
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Eci eci = sgp4.FindPosition(currentTime);
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CoordTopocentric topo = obs.GetLookAngle(eci);
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losAz = Units::radiansToDegrees(topo.azimuth);
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double maxElevationDeg = findMaxElevation(obs, sgp4, aosTime, losTime);
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if ((maxElevationDeg >= minPassElevationDeg)
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&& inPassWindow(aosTime, passStartTime, passEndTime, utc)
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&& inPassWindow(losTime, passStartTime, passEndTime, utc))
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{
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SatellitePass *pass = new SatellitePass;
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pass->m_aos = aosUnknown ? QDateTime() : dateTimeToQDateTime(aosTime);
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pass->m_los = QDateTime();
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pass->m_aosAzimuth = aosAz;
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pass->m_losAzimuth = losAz;
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pass->m_maxElevation = maxElevationDeg;
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pass->m_northToSouth = std::min(360.0-aosAz, aosAz-0.0) < std::min(360.0-losAz, losAz-0.0);
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passes.append(pass);
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}
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}
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return passes;
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}
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void getSatelliteState(QDateTime dateTime,
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const QString& tle0, const QString& tle1, const QString& tle2,
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double latitude, double longitude, double altitude,
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int predictionPeriod, int minAOSElevationDeg, int minPassElevationDeg,
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QTime passStartTime, QTime passFinishTime, bool utc,
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int noOfPasses, int groundTrackSteps, SatelliteState *satState)
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{
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try {
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Tle tle = Tle(tle0.toStdString(), tle1.toStdString(), tle2.toStdString());
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SGP4 sgp4(tle);
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Observer obs(latitude, longitude, altitude);
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DateTime dt = qDateTimeToDateTime(dateTime);
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// Calculate satellite position
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Eci eci = sgp4.FindPosition(dt);
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// Calculate angle to satellite from antenna
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CoordTopocentric topo = obs.GetLookAngle(eci);
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// Convert satellite position to geodetic coordinates (lat and long)
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CoordGeodetic geo = eci.ToGeodetic();
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satState->m_latitude = Units::radiansToDegrees(geo.latitude);
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satState->m_longitude = Units::radiansToDegrees(geo.longitude);
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satState->m_altitude = geo.altitude;
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satState->m_azimuth = Units::radiansToDegrees(topo.azimuth);
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satState->m_elevation = Units::radiansToDegrees(topo.elevation);
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satState->m_range = topo.range;
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satState->m_rangeRate = topo.range_rate;
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OrbitalElements ele(tle);
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satState->m_speed = eci.Velocity().Magnitude();
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satState->m_period = ele.Period();
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if (noOfPasses > 0)
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{
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qDeleteAll(satState->m_passes);
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satState->m_passes = createPassList(obs, sgp4, dt, predictionPeriod,
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Units::degreesToRadians((double)minAOSElevationDeg),
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minPassElevationDeg,
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passStartTime, passFinishTime, utc,
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noOfPasses);
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}
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qDeleteAll(satState->m_groundTrack);
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qDeleteAll(satState->m_predictedGroundTrack);
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getGroundTrack(dateTime, tle0, tle1, tle2, groundTrackSteps, false, satState->m_groundTrack);
|
|
getGroundTrack(dateTime, tle0, tle1, tle2, groundTrackSteps, true, satState->m_predictedGroundTrack);
|
|
}
|
|
catch (SatelliteException& se)
|
|
{
|
|
qDebug() << "getSatelliteState: " << satState->m_name << ": " << se.what();
|
|
}
|
|
catch (DecayedException& de)
|
|
{
|
|
qDebug() << "getSatelliteState: " << satState->m_name << ": " << de.what();
|
|
}
|
|
catch (TleException& tlee)
|
|
{
|
|
qDebug() << "getSatelliteState: " << satState->m_name << ": " << tlee.what();
|
|
}
|
|
}
|