//! EpochTime constructor.
/*!
* \param EpochTime
* Contructs EpochTime from EpochTime Object
*/
public EpochTime(EpochTime _EpochTime)
{
hour = _EpochTime.getHour();
minutes = _EpochTime.getMin();
seconds = _EpochTime.getSec();
year = _EpochTime.getYear();
month = _EpochTime.getMonth();
day = _EpochTime.getDay();
epoch = _EpochTime.getEpoch();
}
//! EpochTime constructor.
/*!
\param EpochTime
Contructs EpochTime from EpochTime Object
*/
public EpochTime(EpochTime _EpochTime)
{
hour = _EpochTime.getHour();
minutes = _EpochTime.getMin();
seconds = _EpochTime.getSec();
year = _EpochTime.getYear();
month = _EpochTime.getMonth();
day = _EpochTime.getDay();
epoch = _EpochTime.getEpoch();
}
//! Run the sgp4 calculations
/*!
\param EpochTime starttime
\param EpochTime stoptime
\param double step in minutes
calculates the orbit of the satellite starting from start to stoptime
*/
public void runSgp4Cal(EpochTime starttime, EpochTime stoptime, double step)
{
EpochTime time = starttime;
int startY = starttime.getYear();
int stopY = stoptime.getYear();
if (startY < 1900)
{
if (startY < 50)
startY = startY + 2000;
else
startY = startY + 1900;
}
if (stopY < 1900)
{
if (stopY < 50)
stopY = stopY + 2000;
else
stopY = stopY + 1900;
}
double starD = starttime.getEpoch();
double stopD = stoptime.getEpoch();
satCalcData.rec_srtime = (startY - 1950) * 365 + (startY - 1949) / 4 + starD;
satCalcData.rec_sptime = (stopY - 1950) * 365 + (stopY - 1949) / 4 + stopD;
satCalcData.rec_deltamin = step;
double temp_t = (satCalcData.rec_srtime - satCalcData.rec_eptime) * 1440.0;
satCalcData.neo.neo_t = temp_t;
double stopTime = (satCalcData.rec_sptime - satCalcData.rec_eptime) * 1440.0 +
satCalcData.rec_deltamin;
while (temp_t < stopTime)
{
resultOrbitData.Add(calcSgp4());
temp_t = temp_t + satCalcData.rec_deltamin;
satCalcData.neo.neo_t = temp_t;
}
}
