50 lines
1.4 KiB
C++
50 lines
1.4 KiB
C++
#include "SatelliteOrbit.h"
|
|
|
|
SatelliteOrbit::SatelliteOrbit(void) {
|
|
}
|
|
|
|
SatelliteOrbit::~SatelliteOrbit(void) {
|
|
}
|
|
|
|
void SatelliteOrbit::SetTle(const Tle& tle) {
|
|
|
|
sgp4_.SetTle(tle);
|
|
}
|
|
|
|
bool SatelliteOrbit::IsGeostationary() {
|
|
|
|
if (sgp4_.MeanMotion() == 0.0)
|
|
return true;
|
|
|
|
/*
|
|
radius of apogee
|
|
the distance from the centre of the planet to the point in the orbit furthest away from the planet
|
|
*/
|
|
const double apogee_altitude = sgp4_.RecoveredSemiMajorAxis() * (1.0 + sgp4_.Eccentricity()) - Globals::XKMPER();
|
|
|
|
/*
|
|
* check if almost same speed as earth
|
|
* or altitude is over 35000 km
|
|
*/
|
|
if (fabs(sgp4_.MeanMotion() - Globals::OMEGA_E()) < 0.0005 || apogee_altitude > 35000)
|
|
return true;
|
|
else
|
|
return false;
|
|
}
|
|
|
|
unsigned int SatelliteOrbit::GetOrbitNumber(const Julian& jul) const {
|
|
|
|
double diff = jul.SpanMin(sgp4_.Epoch());
|
|
|
|
return static_cast<unsigned int> (floor((sgp4_.MeanMotion() * 1440.0 / Globals::TWOPI() +
|
|
diff * sgp4_.BStar() * Globals::AE()) * diff +
|
|
sgp4_.MeanAnomoly() / Globals::TWOPI())) + sgp4_.OrbitNumber() - 1;
|
|
}
|
|
|
|
double SatelliteOrbit::Footprint(const double& altitude) {
|
|
|
|
if (altitude > 0)
|
|
return 2.0 * Globals::XKMPER() * acos(Globals::XKMPER() / (Globals::XKMPER() + altitude));
|
|
else
|
|
return 0.0;
|
|
} |