PredicThirteen::geodetic_t PredicThirteen::calc(PredicThirteen::tle_t t){
printTle(&t);
DEBUG_PRINTLN("----------------------------------------");
PredicThirteen::vector_t zero_vector={0,0,0,0};
PredicThirteen::vector_t pos = zero_vector;
PredicThirteen::vector_t vel = zero_vector;
PredicThirteen::geodetic_t geo = {0,0,0,0};
jul_utc = daynum +723244000000LL;
jul_epoch=Julian_Date_of_Epoch(t.epoch_year, t.epoch_day);
printUint64("TestNum", (uint64_t) 11118562939LL);
printUint64("daynum", daynum);
printUint64("jul_utc",jul_utc);
printUint64("jul_epoch",jul_epoch);
tsince = ((jul_utc - jul_epoch)/1000000.0) * minday;
select_ephemeris(&t);
SGP4(tsince, &t, &pos, &vel);
Convert_Sat_State(&pos, &vel);
Magnitude(&vel);
printVar("jul_utc", jul_utc);
Calculate_LatLonAlt(jul_utc, &pos, &geo);
printVector(&pos);
printVector(&vel);
printGeo(&geo);
LAT = geo.lat;
LON = geo.lon;
Serial.print("LAT: ");
Serial.println(LAT);
Serial.print("LON: ");
Serial.println(LON);
return geo;
}
void TLE_Handler_Update(TM * time)
{
double epoch;
int year = time->tm_year;
while (year > 100) { year -= 100; }
epoch = (double)year * 100.0;
epoch += time->tm_yday;
epoch += (double)time->tm_hour / (double)HOURS_PER_DAY;
epoch += (double)time->tm_min / (double)MINS_PER_DAY;
epoch += (double)time->tm_sec / (double)S_PER_DAY;
sgp4call(Julian_Date_of_Epoch(epoch), &pos, NULL, &s_data);
Convert_Sat_State(&pos, NULL);
}
void SatGL::RenderTrail(Satellite *sat, QMatrix4x4 projection, float distance, QQuaternion quat, bool trackon) // QMatrix4x4 modelview, bool trackon)
{
QVector<GLfloat> postrail;
double
tsince, // Time since epoch (in minutes)
jul_epoch, // Julian date of epoch
jul_utc; // Julian UTC date
QSgp4Date nowutc = QSgp4Date::NowUTC();
jul_utc = nowutc.Julian();
jul_epoch = Julian_Date_of_Epoch(sat->GetEpoch());
QMatrix4x4 model;
model.translate(0.0, 0.0, distance);
model.rotate(quat);
QMatrix4x4 modelview;
modelview = model;
QMatrix4x4 modelocta;
QColor col(0,255,255);
QEci qeci;
QVector3D pos;
double id;
int nbrVertices = 0;
tsince = (jul_utc - jul_epoch) * MIN_PER_DAY; // in minutes
for( id = tsince - 5; id < tsince; id++ )
{
(*sat).qsgp4->getPosition(id, qeci);
QGeodetic qgeo = qeci.ToGeo();
LonLat2PointRad(qgeo.latitude, qgeo.longitude, &pos, 1.001f);
if(id < tsince && id >= tsince - 5 )
{
modelocta = model;
modelocta.translate(pos.x(), pos.y(), pos.z());
modelocta.scale(0.004f);
octa->render(projection, modelocta, col);
}
}
if(trackon)
{
for( id = tsince - opts.realminutesshown + 1; id <= tsince + opts.realminutesshown; id++ ) // nbr of id's = 2 * opts.realminutesshown
{
(*sat).qsgp4->getPosition(id, qeci);
QGeodetic qgeo = qeci.ToGeo();
LonLat2PointRad(qgeo.latitude, qgeo.longitude, &pos, 1.001f);
postrail.append(pos.x());
postrail.append(pos.y());
postrail.append(pos.z());
}
positionsTrail.bind();
if(tdiff != opts.realminutesshown)
{
tdiff = opts.realminutesshown;
positionsTrail.allocate(postrail.data(), postrail.size() * sizeof(GLfloat));
}
else
{
positionsTrail.write(0, postrail.data(), postrail.size() * sizeof(GLfloat));
}
nbrVertices = positionsTrail.size() / (3 * sizeof(GLfloat));
positionsTrail.release();
QOpenGLVertexArrayObject::Binder vaoBinder(&vaotrail);
program->bind();
program->setUniformValue("MVP", projection * modelview);
QMatrix3x3 norm = modelview.normalMatrix();
program->setUniformValue("NormalMatrix", norm);
QColor rendercolor(opts.sattrackcolor);
program->setUniformValue("outcolor", QVector4D(rendercolor.redF(), rendercolor.greenF(), rendercolor.blueF(), 1.0f));
glDrawArrays(GL_LINE_STRIP, 0, nbrVertices);
}
}
/** \brief Initialise satellite data.
* \param sat The satellite to initialise.
* \param qth Optional QTH info, use (0,0) if NULL.
*
* This function calculates the satellite data at t = 0, ie. epoch time
* The function is called automatically by gtk_sat_data_read_sat.
*/
void
gtk_sat_data_init_sat (sat_t *sat, qth_t *qth)
{
geodetic_t obs_geodetic;
obs_set_t obs_set;
geodetic_t sat_geodetic;
double jul_utc, age;
g_return_if_fail (sat != NULL);
jul_utc = Julian_Date_of_Epoch (sat->tle.epoch); // => tsince = 0.0
sat->jul_epoch = jul_utc;
/* initialise observer location */
if (qth != NULL) {
obs_geodetic.lon = qth->lon * de2ra;
obs_geodetic.lat = qth->lat * de2ra;
obs_geodetic.alt = qth->alt / 1000.0;
obs_geodetic.theta = 0;
}
else {
obs_geodetic.lon = 0.0;
obs_geodetic.lat = 0.0;
obs_geodetic.alt = 0.0;
obs_geodetic.theta = 0;
}
/* execute computations */
if (sat->flags & DEEP_SPACE_EPHEM_FLAG)
SDP4 (sat, 0.0);
else
SGP4 (sat, 0.0);
/* scale position and velocity to km and km/sec */
Convert_Sat_State (&sat->pos, &sat->vel);
/* get the velocity of the satellite */
Magnitude (&sat->vel);
sat->velo = sat->vel.w;
Calculate_Obs (jul_utc, &sat->pos, &sat->vel, &obs_geodetic, &obs_set);
Calculate_LatLonAlt (jul_utc, &sat->pos, &sat_geodetic);
while (sat_geodetic.lon < -pi)
sat_geodetic.lon += twopi;
while (sat_geodetic.lon > (pi))
sat_geodetic.lon -= twopi;
sat->az = Degrees (obs_set.az);
sat->el = Degrees (obs_set.el);
sat->range = obs_set.range;
sat->range_rate = obs_set.range_rate;
sat->ssplat = Degrees (sat_geodetic.lat);
sat->ssplon = Degrees (sat_geodetic.lon);
sat->alt = sat_geodetic.alt;
sat->ma = Degrees (sat->phase);
sat->ma *= 256.0/360.0;
sat->footprint = 2.0 * xkmper * acos (xkmper/sat->pos.w);
age = 0.0;
sat->orbit = (long) floor((sat->tle.xno * xmnpda/twopi +
age * sat->tle.bstar * ae) * age +
sat->tle.xmo/twopi) + sat->tle.revnum - 1;
/* orbit type */
sat->otype = get_orbit_type (sat);
}
/* Main program */
int
main(void)
{
/* TLE source file */
char tle_file[] = "./rax.txt";
/* Observer's geodetic co-ordinates. */
/* Lat North, Lon East in rads, Alt in km */
geodetic_t obs_geodetic = {0.7368, -1.4615, 0.251, 0.0};
/* Two-line Orbital Elements for the satellite */
tle_t tle ;
/* Zero vector for initializations */
vector_t zero_vector = {0,0,0,0};
/* Satellite position and velocity vectors */
vector_t vel = zero_vector;
vector_t pos = zero_vector;
/* Satellite Az, El, Range, Range rate */
vector_t obs_set;
/* Solar ECI position vector */
vector_t solar_vector = zero_vector;
/* Solar observed azi and ele vector */
vector_t solar_set;
/* Calendar date and time (UTC) */
struct tm utc;
/* Satellite's predicted geodetic position */
geodetic_t sat_geodetic;
double
tsince, /* Time since epoch (in minutes) */
jul_epoch, /* Julian date of epoch */
jul_utc, /* Julian UTC date */
eclipse_depth = 0, /* Depth of satellite eclipse */
/* Satellite's observed position, range, range rate */
sat_azi, sat_ele, sat_range, sat_range_rate,
/* Satellites geodetic position and velocity */
sat_lat, sat_lon, sat_alt, sat_vel,
/* Solar azimuth and elevation */
sun_azi, sun_ele;
/* Used for storing function return codes */
int flg;
char
ephem[5], /* Ephemeris in use string */
sat_status[12]; /* Satellite eclipse status */
/* Input one (first!) TLE set from file */
flg = Input_Tle_Set(tle_file, &tle);
/* Abort if file open fails */
if( flg == -1 )
{
printf(" File open failed - Exiting!\n");
exit(-1);
}
/* Print satellite name and TLE read status */
printf(" %s: ", tle.sat_name);
if( flg == -2 )
{
printf("TLE set bad - Exiting!\n");
exit(-2);
}
else
printf("TLE set good - Happy Tracking!\n");
/* Printout of tle set data for tests if needed */
/* printf("\n %s %s %i %i %i\n"
" %14f %10f %8f %8f\n"
" %8f %8f %9f %8f %8f %12f\n",
tle.sat_name, tle.idesg, tle.catnr, tle.elset, tle.revnum,
tle.epoch, tle.xndt2o, tle.xndd6o, tle.bstar,
tle.xincl, tle.xnodeo, tle.eo, tle.omegao, tle.xmo, tle.xno);
*/
/** !Clear all flags! **/
/* Before calling a different ephemeris */
/* or changing the TLE set, flow control */
/* flags must be cleared in main(). */
ClearFlag(ALL_FLAGS);
/** Select ephemeris type **/
/* Will set or clear the DEEP_SPACE_EPHEM_FLAG */
/* depending on the TLE parameters of the satellite. */
/* It will also pre-process tle members for the */
/* ephemeris functions SGP4 or SDP4 so this function */
/* must be called each time a new tle set is used */
select_ephemeris(&tle);
do /* Loop */
{
/* Get UTC calendar and convert to Julian */
UTC_Calendar_Now(&utc);
jul_utc = Julian_Date(&utc);
/* Convert satellite's epoch time to Julian */
/* and calculate time since epoch in minutes */
jul_epoch = Julian_Date_of_Epoch(tle.epoch);
tsince = (jul_utc - jul_epoch) * xmnpda;
/* Copy the ephemeris type in use to ephem string */
if( isFlagSet(DEEP_SPACE_EPHEM_FLAG) )
strcpy(ephem,"SDP4");
else
strcpy(ephem,"SGP4");
/* Call NORAD routines according to deep-space flag */
if( isFlagSet(DEEP_SPACE_EPHEM_FLAG) )
SDP4(tsince, &tle, &pos, &vel);
else
SGP4(tsince, &tle, &pos, &vel);
/* Scale position and velocity vectors to km and km/sec */
Convert_Sat_State( &pos, &vel );
/* Calculate velocity of satellite */
Magnitude( &vel );
sat_vel = vel.w;
/** All angles in rads. Distance in km. Velocity in km/s **/
/* Calculate satellite Azi, Ele, Range and Range-rate */
Calculate_Obs(jul_utc, &pos, &vel, &obs_geodetic, &obs_set);
/* Calculate satellite Lat North, Lon East and Alt. */
Calculate_LatLonAlt(jul_utc, &pos, &sat_geodetic);
/* Calculate solar position and satellite eclipse depth */
/* Also set or clear the satellite eclipsed flag accordingly */
Calculate_Solar_Position(jul_utc, &solar_vector);
Calculate_Obs(jul_utc,&solar_vector,&zero_vector,&obs_geodetic,&solar_set);
if( Sat_Eclipsed(&pos, &solar_vector, &eclipse_depth) )
SetFlag( SAT_ECLIPSED_FLAG );
else
ClearFlag( SAT_ECLIPSED_FLAG );
/* Copy a satellite eclipse status string in sat_status */
if( isFlagSet( SAT_ECLIPSED_FLAG ) )
strcpy( sat_status, "Eclipsed" );
else
strcpy( sat_status, "In Sunlight" );
/* Convert and print satellite and solar data */
sat_azi = Degrees(obs_set.x);
sat_ele = Degrees(obs_set.y);
sat_range = obs_set.z;
sat_range_rate = obs_set.w;
sat_lat = Degrees(sat_geodetic.lat);
sat_lon = Degrees(sat_geodetic.lon);
sat_alt = sat_geodetic.alt;
sun_azi = Degrees(solar_set.x);
sun_ele = Degrees(solar_set.y);
printf("\n Date: %02d/%02d/%04d UTC: %02d:%02d:%02d Ephemeris: %s"
"\n Azi=%6.1f Ele=%6.1f Range=%8.1f Range Rate=%6.2f"
"\n Lat=%6.1f Lon=%6.1f Alt=%8.1f Vel=%8.3f"
"\n Stellite Status: %s - Depth: %2.3f"
"\n Sun Azi=%6.1f Sun Ele=%6.1f\n",
utc.tm_mday, utc.tm_mon, utc.tm_year,
utc.tm_hour, utc.tm_min, utc.tm_sec, ephem,
sat_azi, sat_ele, sat_range, sat_range_rate,
sat_lat, sat_lon, sat_alt, sat_vel,
sat_status, eclipse_depth,
sun_azi, sun_ele);
sleep(1);
} /* End of do */
while( 1 ); /* This stops Compaq ccc 'unreachcode' warning! */
return(0);
} /* End of main() */
/* This is the old Calc() function. */
int predict_orbit(const predict_orbital_elements_t *orbital_elements, struct predict_orbit *m, double utc)
{
/* Set time to now if now time is provided: */
if (utc == 0) utc = predict_to_julian(time(NULL));
/* Satellite position and velocity vectors */
vec3_set(m->position, 0, 0, 0);
vec3_set(m->velocity, 0, 0, 0);
m->time = utc;
double julTime = utc + 2444238.5;
/* Convert satellite's epoch time to Julian */
/* and calculate time since epoch in minutes */
double epoch = 1000.0*orbital_elements->epoch_year + orbital_elements->epoch_day;
double jul_epoch = Julian_Date_of_Epoch(epoch);
double tsince = (julTime - jul_epoch)*xmnpda;
/* Call NORAD routines according to deep-space flag. */
struct model_output output;
switch (orbital_elements->ephemeris) {
case EPHEMERIS_SDP4:
sdp4_predict((struct _sdp4*)orbital_elements->ephemeris_data, tsince, &output);
break;
case EPHEMERIS_SGP4:
sgp4_predict((struct _sgp4*)orbital_elements->ephemeris_data, tsince, &output);
break;
default:
//Panic!
return -1;
}
m->position[0] = output.pos[0];
m->position[1] = output.pos[1];
m->position[2] = output.pos[2];
m->velocity[0] = output.vel[0];
m->velocity[1] = output.vel[1];
m->velocity[2] = output.vel[2];
m->phase = output.phase;
m->argument_of_perigee = output.omgadf;
m->inclination = output.xinck;
m->right_ascension = output.xnodek;
/* TODO: Remove? Scale position and velocity vectors to km and km/sec */
Convert_Sat_State(m->position, m->velocity);
/* Calculate satellite Lat North, Lon East and Alt. */
geodetic_t sat_geodetic;
Calculate_LatLonAlt(utc, m->position, &sat_geodetic);
m->latitude = sat_geodetic.lat;
m->longitude = sat_geodetic.lon;
m->altitude = sat_geodetic.alt;
// Calculate solar position
double solar_vector[3];
sun_predict(m->time, solar_vector);
// Find eclipse depth and if sat is eclipsed
m->eclipsed = is_eclipsed(m->position, solar_vector, &m->eclipse_depth);
// Calculate footprint
m->footprint = 2.0*xkmper*acos(xkmper/(xkmper + m->altitude));
// Calculate current number of revolutions around Earth
double temp = twopi/xmnpda/xmnpda;
double age = julTime - jul_epoch;
double xno = orbital_elements->mean_motion*temp*xmnpda;
double xmo = orbital_elements->mean_anomaly * M_PI / 180.0;
m->revolutions = (long)floor((xno*xmnpda/(M_PI*2.0) + age*orbital_elements->bstar_drag_term)*age + xmo/(2.0*M_PI)) + orbital_elements->revolutions_at_epoch;
//calculate whether orbit is decayed
m->decayed = predict_decayed(orbital_elements, utc);
return 0;
}