55 lines
1.6 KiB
C++
55 lines
1.6 KiB
C++
|
#include "SatelliteOrbit.h"
|
||
|
|
|
||
|
|
SatelliteOrbit::SatelliteOrbit(void) {
|
||
|
|
}
|
||
|
|
|
||
|
|
SatelliteOrbit::~SatelliteOrbit(void) {
|
||
|
|
}
|
||
|
|
|
||
|
|
void SatelliteOrbit::SetTle(const Tle& tle) {
|
||
|
|
|
||
|
|
sgdp4_.SetTle(tle);
|
||
|
|
}
|
||
|
|
|
||
|
|
bool SatelliteOrbit::IsGeostationary() {
|
||
|
|
#if 0
|
||
|
|
if (sgdp4_.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 = sgdp4_.RecoveredSemiMajorAxis() * (1.0 + sgdp4_.Eccentricity()) - Globals::XKMPER();
|
||
|
|
|
||
|
|
/*
|
||
|
|
* check if almost same speed as earth
|
||
|
|
* or altitude is over 35000 km
|
||
|
|
*/
|
||
|
|
if (fabs(sgdp4_.MeanMotion() - Globals::OMEGA_E()) < 0.0005 || apogee_altitude > 35000)
|
||
|
|
return true;
|
||
|
|
else
|
||
|
|
#endif
|
||
|
|
return false;
|
||
|
|
}
|
||
|
|
|
||
|
|
unsigned int SatelliteOrbit::GetOrbitNumber(const Julian& jul) const{
|
||
|
|
#if 0
|
||
|
|
double diff = jul.SpanMin(sgdp4_.Epoch());
|
||
|
|
|
||
|
|
return (unsigned int)floor((sgdp4_.MeanMotion() * 1440.0 / Globals::TWOPI() +
|
||
|
|
diff * sgdp4_.BStar() * Globals::AE()) * diff +
|
||
|
|
sgdp4_.MeanAnomoly() / Globals::TWOPI()) + sgdp4_.OrbitNumber() - 1.0;
|
||
|
|
#endif
|
||
|
|
return 0;
|
||
|
|
}
|
||
|
|
|
||
|
|
#if 0
|
||
|
|
/* same formulas, but the one from predict is nicer */
|
||
|
|
//sat->footprint = 2.0 * xkmper * acos (xkmper/sat->pos.w);
|
||
|
|
sat->footprint = 12756.33 * acos(xkmper / (xkmper + sat->alt));
|
||
|
|
age = sat->jul_utc - sat->jul_epoch;
|
||
|
|
sat->orbit = (long) floor((sat->tle.xno * xmnpda / twopi +
|
||
|
|
age * sat->tle.bstar * ae) * age +
|
||
|
|
sat->tle.xmo / twopi) + sat->tle.revnum - 1;
|
||
|
|
#endif
|