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/***********************************************/
/**
* @file simulateOrbit.cpp
*
* @brief Pure dynamical orbit integration.
*
* @author Matthias Ellmer
* @date 2004-09-12
*/
/***********************************************/
// Latex documentation
#define DOCSTRING docstring
static const char *docstring = R"(
This program integrates an \file{orbit}{instrument} from a given force function (dynamic orbit).
The force functions are given by \configClass{forces}{forcesType}.
For computation of non-conservative forces a \file{satelliteModel}{satelliteModel} is needed.
The integration method must be selected with \configClass{propagator}{orbitPropagatorType}.
Because the orbit data are calculated in the celestial reference frame (CRF) you need
\configClass{earthRotation}{earthRotationType} to transform the force function
from the terrestrial reference frame (TRF).
The integration start and end time, as well as the sampling, are derived from
the \config{timeSeries} option. It is possible to integrate the arc in \config{reverse},
where the initial conditions are assumed to be met at the end time of the \config{timeSeries}.
)";
/***********************************************/
#include "programs/program.h"
#include "base/kepler.h"
#include "files/fileInstrument.h"
#include "files/fileSatelliteModel.h"
#include "classes/timeSeries/timeSeries.h"
#include "classes/earthRotation/earthRotation.h"
#include "classes/ephemerides/ephemerides.h"
#include "classes/forces/forces.h"
#include "classes/orbitPropagator/orbitPropagator.h"
/***** CLASS ***********************************/
/** @brief Pure dynamical orbit integration.
* @ingroup programsGroup */
class SimulateOrbit
{
public:
void run(Config &config, Parallel::CommunicatorPtr comm);
};
GROOPS_REGISTER_PROGRAM(SimulateOrbit, SINGLEPROCESS, "pure dynamical orbit integration", Simulation, Orbit, Instrument)
/***********************************************/
void SimulateOrbit::run(Config &config, Parallel::CommunicatorPtr /*comm*/)
{
try
{
FileName fileNameOrbit;
FileName fileNameSatellite;
FileName fileNameStart;
TimeSeriesPtr timeSeries;
OrbitPropagatorPtr orbitPropagator;
OrbitEpoch startEpoch;
EarthRotationPtr earthRotation;
EphemeridesPtr ephemerides;
ForcesPtr forces;
Bool reverse;
Double margin;
renameDeprecatedConfig(config, "satelliteModel", "inputfileSatelliteModel", date2time(2020, 8, 19));
readConfig(config, "outputfileOrbit", fileNameOrbit, Config::MUSTSET, "", "orbit file to be written.");
readConfig(config, "inputfileSatelliteModel", fileNameSatellite, Config::OPTIONAL, "{groopsDataDir}/satelliteModel/", "satellite macro model");
readConfig(config, "timeSeries", timeSeries, Config::MUSTSET, "", "time points for simulated orbit epochs.");
std::string choice;
readConfigChoice(config, "integrationConstants", choice, Config::MUSTSET, "", "");
if(readConfigChoiceElement(config, "kepler", choice, ""))
{
Double GM, a, e;
Angle i, Omega, omega, M;
readConfig(config, "majorAxis", a, Config::MUSTSET, "", "[m]");
readConfig(config, "eccentricity", e, Config::MUSTSET, "", "[-]");
readConfig(config, "inclination", i, Config::MUSTSET, "", "[degree]");
readConfig(config, "ascendingNode", Omega, Config::MUSTSET, "", "[degree]");
readConfig(config, "argumentOfPerigee", omega, Config::MUSTSET, "", "[degree]");
readConfig(config, "meanAnomaly", M, Config::MUSTSET, "", "[degree]");
readConfig(config, "GM", GM, Config::DEFAULT, STRING_DEFAULT_GM, "Geocentric gravitational constant");
if(!isCreateSchema(config))
{
Kepler kepler(Time(), Omega, i, omega, a, e, M, GM);
kepler.orbit(Time(), startEpoch.position, startEpoch.velocity);
}
}
if(readConfigChoiceElement(config, "positionAndVelocity", choice, ""))
{
readConfig(config, "position0x", startEpoch.position.x(), Config::MUSTSET, "", "[m] in CRF");
readConfig(config, "position0y", startEpoch.position.y(), Config::MUSTSET, "", "[m] in CRF");
readConfig(config, "position0z", startEpoch.position.z(), Config::MUSTSET, "", "[m] in CRF");
readConfig(config, "velocity0x", startEpoch.velocity.x(), Config::MUSTSET, "", "[m/s]");
readConfig(config, "velocity0y", startEpoch.velocity.y(), Config::MUSTSET, "", "[m/s]");
readConfig(config, "velocity0z", startEpoch.velocity.z(), Config::MUSTSET, "", "[m/s]");
}
if(readConfigChoiceElement(config, "file", choice, ""))
{
readConfig(config, "inputfileOrbit", fileNameStart, Config::MUSTSET, "", "only epoch at timeStart is used");
readConfig(config, "margin", margin, Config::DEFAULT, "1e-5", "[seconds] used when finding initial epoch in orbitFile");
}
endChoice(config);
readConfig(config, "propagator", orbitPropagator, Config::MUSTSET, "polynomial", "orbit propagation method.");
readConfig(config, "earthRotation", earthRotation, Config::MUSTSET, "", "");
readConfig(config, "ephemerides", ephemerides, Config::OPTIONAL, "jpl", "");
readConfig(config, "forces", forces, Config::MUSTSET, "", "considered in orbit propagation.");
readConfig(config, "reverse", reverse, Config::DEFAULT, "0", "start integration at last epoch in timeSeries, going backward in time.");
if(isCreateSchema(config)) return;
// Setup
// -----
SatelliteModelPtr satellite;
if(!fileNameSatellite.empty())
readFileSatelliteModel(fileNameSatellite, satellite);
std::vector<Time> times = timeSeries->times();
Time timeStart = times.front();
Time sampling = 1./(times.size()-1) * (times.back()-times.front());
if(!isRegular(times))
throw(Exception("Time intervals must be regularly spaced."));
// Need to flip?
if(reverse)
{
timeStart = times.back();
sampling = -sampling;
}
// read startEpoch from file
// -------------------------
if(!fileNameStart.empty())
{
OrbitArc orbit = InstrumentFile::read(fileNameStart);
for(UInt i=0; i<orbit.size(); i++)
if(std::fabs((orbit.at(i).time-timeStart).seconds())<margin)
startEpoch = orbit.at(i);
if(std::fabs((startEpoch.time-timeStart).seconds())>margin)
throw (Exception("Requested start time "+timeStart.dateTimeStr()+" not present in file <"+fileNameStart.str()+">"));
}
// Integrate
// ---------
logStatus<<"integrating orbit"<<Log::endl;
startEpoch.time = timeStart;
OrbitArc orbit = orbitPropagator->integrateArc(startEpoch, sampling, times.size(), forces, satellite, earthRotation, ephemerides);
if(reverse)
orbit = OrbitPropagator::flip(orbit);
// Save
// ----
logStatus<<"write orbit data to file <"<<fileNameOrbit<<">"<<Log::endl;
InstrumentFile::write(fileNameOrbit, orbit);
}
catch(std::exception &e)
{
GROOPS_RETHROW(e)
}
}
/***********************************************/
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