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;
}
/** \brief Copy satellite data.
* \param source Pointer to the source satellite to copy data from.
* \param dest Pointer to the destination satellite to copy data into.
* \param qth Pointer to the observer data (needed to initialize sat)
*
* This function copies the satellite data from a source sat_t structure into
* the destination. The function copies the tle_t data and calls gtk_sat_data_inti_sat()
* function for initializing the other fields.
*
*/
void gtk_sat_data_copy_sat (const sat_t *source, sat_t *dest, qth_t *qth)
{
guint i;
g_return_if_fail ((source != NULL) && (dest != NULL));
dest->tle.epoch = source->tle.epoch;
dest->tle.epoch_year = source->tle.epoch_year;
dest->tle.epoch_day = source->tle.epoch_day;
dest->tle.epoch_fod = source->tle.epoch_fod;
dest->tle.xndt2o = source->tle.xndt2o;
dest->tle.xndd6o = source->tle.xndd6o;
dest->tle.bstar = source->tle.bstar;
dest->tle.xincl = source->tle.xincl;
dest->tle.xnodeo = source->tle.xnodeo;
dest->tle.eo = source->tle.eo;
dest->tle.omegao = source->tle.omegao;
dest->tle.xmo = source->tle.xmo;
dest->tle.xno = source->tle.xno;
dest->tle.catnr = source->tle.catnr;
dest->tle.elset = source->tle.elset;
dest->tle.revnum = source->tle.revnum;
dest->name = g_strdup (source->name);
dest->nickname = g_strdup (source->nickname);
for (i = 0; i < 9; i++)
dest->tle.idesg[i] = source->tle.idesg[i];
dest->tle.status = source->tle.status;
dest->tle.xincl1 = source->tle.xincl1;
dest->tle.omegao1 = source->tle.omegao1;
dest->otype = source->otype;
/* very important */
dest->flags = 0;
select_ephemeris (dest);
/* initialise variable fields */
dest->jul_utc = 0.0;
dest->tsince = 0.0;
dest->az = 0.0;
dest->el = 0.0;
dest->range = 0.0;
dest->range_rate = 0.0;
dest->ra = 0.0;
dest->dec = 0.0;
dest->ssplat = 0.0;
dest->ssplon = 0.0;
dest->alt = 0.0;
dest->velo = 0.0;
dest->ma = 0.0;
dest->footprint = 0.0;
dest->phase = 0.0;
dest->aos = 0.0;
dest->los = 0.0;
gtk_sat_data_init_sat (dest, qth);
}
/* Main program */
int main( const int argc, const char **argv)
{
const char *tle_filename = ((argc == 1) ? "test.tle" : argv[1]);
FILE *ifile = fopen( tle_filename, "rb");
tle_t tle; /* Pointer to two-line elements set for satellite */
char line1[100], line2[100];
int ephem = 1; /* default to SGP4 */
int i; /* Index for loops etc */
int n_failures = 0, n_simple = 0, n_simplex = 0;
bool failures_only = false;
for( i = 2; i < argc; i++)
if( argv[i][0] == '-')
switch( argv[i][1])
{
case 'f':
failures_only = true;
break;
case 'v':
verbose = 1;
break;
case 'd':
dist_offset = atof( argv[i] + 2);
break;
case 's':
vel_offset = atof( argv[i] + 2);
break;
default:
printf( "Option '%s' unrecognized\n", argv[i]);
break;
}
if( !ifile)
{
printf( "Couldn't open input TLE file %s\n", tle_filename);
exit( -1);
}
*line1 = '\0';
while( fgets( line2, sizeof( line2), ifile))
{
int got_data = 0;
double state_vect[6];
set_tle_defaults( &tle);
if( strlen( line2) > 110 && line2[7] == '.' && line2[18] == '.'
&& line2[0] == '2' && line2[1] == '4')
{
got_data = 3; /* Find_Orb state vector ephemeris */
tle.epoch = atof( line2);
sscanf( line2 + 13, "%lf %lf %lf %lf %lf %lf",
state_vect + 0, state_vect + 1, state_vect + 2,
state_vect + 3, state_vect + 4, state_vect + 5);
}
else if( strlen( line1) > 55 && !memcmp( line1 + 50, " (TDB)", 6))
{ /* JPL Horizons vector */
const double obliq_2000 = 23.4392911 * PI / 180.;
tle.epoch = atof( line1); /* get JD epoch from header... */
strcpy( line1, line2);
if( fgets( line2, sizeof( line2), ifile))
got_data = 1;
sscanf( line1, "%lf %lf %lf",
state_vect + 0, state_vect + 1, state_vect + 2);
sscanf( line2, "%lf %lf %lf",
state_vect + 3, state_vect + 4, state_vect + 5);
/* Cvt ecliptic to equatorial 2000: */
rotate_vector( state_vect , obliq_2000, 0);
rotate_vector( state_vect + 3, obliq_2000, 0);
}
else if( parse_elements( line1, line2, &tle) >= 0)
got_data = 2;
if( got_data == 1 || got_data == 3)
tle.epoch -= 68.00 / 86400.; /* rough convert TDT to UTC */
if( got_data) /* hey! we got a TLE! */
{
double sat_params[N_SAT_PARAMS], trial_state[6];
int simple_rval;
bool failed = false;
tle_t new_tle;
if( got_data == 1 || got_data == 3)
{
ephem = 3; /* Use SDP4 for JPL Horizons vectors */
for( i = 0; i < 6 && fabs( state_vect[i]) < 1.; i++)
;
if( i == 6) /* all small quantities, must be in AU & AU/day : */
{
for( i = 0; i < 6; i++)
state_vect[i] *= AU_IN_KM;
for( i = 3; i < 6; i++)
state_vect[i] /= seconds_per_day;
}
for( i = 3; i < 6; i++) /* cvt km/sec to km/min */
state_vect[i] *= seconds_per_minute;
if( !failures_only)
show_results( "Before:", NULL, state_vect);
}
else
{
int is_deep = select_ephemeris( &tle);
if( is_deep && (ephem == 1 || ephem == 2))
ephem += 2; /* switch to an SDx */
if( !is_deep && (ephem == 3 || ephem == 4))
ephem -= 2; /* switch to an SGx */
/* Calling of NORAD routines */
/* Each NORAD routine (SGP, SGP4, SGP8, SDP4, SDP8) */
/* will be called in turn with the appropriate TLE set */
switch( ephem)
{
case 0:
SGP_init( sat_params, &tle);
SGP( 0., &tle, sat_params, state_vect, state_vect + 3);
break;
case 1:
SGP4_init( sat_params, &tle);
SGP4( 0., &tle, sat_params, state_vect, state_vect + 3);
break;
case 2:
SGP8_init( sat_params, &tle);
SGP8( 0., &tle, sat_params, state_vect, state_vect + 3);
break;
case 3:
SDP4_init( sat_params, &tle);
SDP4( 0., &tle, sat_params, state_vect, state_vect + 3);
break;
case 4:
SDP8_init( sat_params, &tle);
SDP8( 0., &tle, sat_params, state_vect, state_vect + 3);
break;
}
if( !failures_only)
show_results( "Before:", &tle, state_vect);
}
new_tle = tle;
simple_rval = compute_tle_from_state_vector( &new_tle, state_vect, ephem, trial_state);
if( simple_rval)
{
n_simplex++;
find_tle_via_simplex_method( &new_tle, state_vect, trial_state, ephem);
}
else
n_simple++;
compute_new_state_vect( &new_tle, trial_state, ephem);
for( i = 0; i < 6; i++)
{
trial_state[i] -= state_vect[i];
if( fabs( trial_state[i]) > 1e-6)
failed = true;
}
if( failed && failures_only)
show_results( "Before:", &tle, state_vect);
if( failed || !failures_only)
show_results( (simple_rval ? "Simplex result:" : "Simplest method:"),
&new_tle, trial_state);
if( failed)
n_failures++;
}
strcpy( line1, line2);
}
fclose( ifile);
printf( "%d solved with simple method; %d with simplex\n", n_simple, n_simplex);
if( n_failures)
printf( "%d failures\n", n_failures);
return(0);
} /* End of main() */
/** \brief Read TLE data for a given satellite into memory.
* \param catnum The catalog number of the satellite.
* \param sat Pointer to a valid sat_t structure.
* \return 0 if successfull, 1 if an I/O error occurred,
* 2 if the TLE data appears to be bad.
*
*/
gint
gtk_sat_data_read_sat (gint catnum, sat_t *sat)
{
guint errorcode = 0;
GError *error = NULL;
GKeyFile *data;
gchar *filename = NULL, *path = NULL;
gchar *tlestr1,*tlestr2,*rawtle;
/* ensure that sat != NULL */
g_return_val_if_fail (sat != NULL, 1);
/* .sat file names */
filename = g_strdup_printf ("%d.sat", catnum);
path = sat_file_name_from_catnum (catnum);
/* open .sat file */
data = g_key_file_new ();
if (!g_key_file_load_from_file (data, path, G_KEY_FILE_KEEP_COMMENTS, &error)) {
/* an error occurred */
sat_log_log (SAT_LOG_LEVEL_ERROR,
_("%s: Failed to load data from %s (%s)"),
__func__, path, error->message);
g_clear_error (&error);
errorcode = 1;
}
else {
/* read name, nickname, and website */
sat->name = g_key_file_get_string (data, "Satellite", "NAME", &error);
if (error != NULL) {
sat_log_log (SAT_LOG_LEVEL_ERROR,
_("%s: Error reading NAME from %s (%s)"),
__func__, path, error->message);
g_clear_error (&error);
sat->name = g_strdup ("Error");
}
sat->nickname = g_key_file_get_string (data, "Satellite", "NICKNAME", &error);
if (error != NULL) {
sat_log_log (SAT_LOG_LEVEL_INFO,
_("%s: Satellite %d has no NICKNAME"),
__func__, catnum);
g_clear_error (&error);
sat->nickname = g_strdup (sat->name);
}
sat->website = g_key_file_get_string (data, "Satellite", "WEBSITE", NULL); /* website may be NULL */
/* get TLE data */
tlestr1 = g_key_file_get_string (data, "Satellite", "TLE1", NULL);
if (error != NULL) {
sat_log_log (SAT_LOG_LEVEL_ERROR,
_("%s: Error reading TLE line 1 from %s (%s)"),
__func__, path, error->message);
g_clear_error (&error);
}
tlestr2 = g_key_file_get_string (data, "Satellite", "TLE2", NULL);
if (error != NULL) {
sat_log_log (SAT_LOG_LEVEL_ERROR,
_("%s: Error reading TLE line 2 from %s (%s)"),
__func__, path, error->message);
g_clear_error (&error);
}
rawtle = g_strconcat (tlestr1, tlestr2, NULL);
if (!Good_Elements (rawtle)) {
sat_log_log (SAT_LOG_LEVEL_ERROR,
_("%s: TLE data for %d appears to be bad"),
__func__, catnum);
errorcode = 2;
} else {
Convert_Satellite_Data (rawtle, &sat->tle);
}
if (g_key_file_has_key(data, "Satellite", "STATUS",NULL))
sat->tle.status = g_key_file_get_integer (data, "Satellite", "STATUS", NULL);
g_free (tlestr1);
g_free (tlestr2);
g_free (rawtle);
/* VERY, VERY important! If not done, some sats
will not get initialised, the first time SGP4/SDP4
is called. Consequently, the resulting data will
be NAN, INF or similar nonsense.
For some reason, not even using g_new0 seems to
be enough.
*/
sat->flags = 0;
select_ephemeris (sat);
/* initialise variable fields */
sat->jul_utc = 0.0;
sat->tsince = 0.0;
sat->az = 0.0;
sat->el = 0.0;
sat->range = 0.0;
sat->range_rate = 0.0;
sat->ra = 0.0;
sat->dec = 0.0;
sat->ssplat = 0.0;
sat->ssplon = 0.0;
sat->alt = 0.0;
sat->velo = 0.0;
sat->ma = 0.0;
sat->footprint = 0.0;
sat->phase = 0.0;
sat->aos = 0.0;
sat->los = 0.0;
/* calculate satellite data at epoch */
gtk_sat_data_init_sat (sat, NULL);
}
g_free (filename);
g_free (path);
g_key_file_free (data);
return errorcode;
}
/* 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() */
int main( const int argc, const char **argv)
{
const char *tle_file_name = "ALL_TLE.TXT";
FILE *ifile = fopen( argv[1], "rb"), *tle_file;
FILE *stations;
char line1[100], line2[100], buff[90];
double search_radius = .2; /* default to .2-degree search */
double lon = 0., rho_sin_phi = 0., rho_cos_phi = 0.;
char curr_mpc_code[4];
int i, debug_level = 0, show_non_mpc_report_lines = 0;
char prev_obj[20];
double prev_jd = 0., prev_ra = 0., prev_dec = 0.;
if( argc == 1)
error_exit( -2);
if( !ifile)
{
printf( "Couldn't open input file %s\n", argv[1]);
exit( -1);
}
stations = fopen( "ObsCodes.html", "rb");
if( !stations) /* perhaps stored with truncated extension? */
stations = fopen( "ObsCodes.htm", "rb");
if( !stations) /* Or as a text file? */
stations = fopen( "stations.txt", "rb");
if( !stations)
{
printf( "Failed to find MPC station list 'ObsCodes.html'\n");
printf( "This can be downloaded at:\n\n");
printf( "http://www.minorplanetcenter.org/iau/lists/ObsCodes.html\n");
exit( -1);
}
curr_mpc_code[0] = curr_mpc_code[3] = '\0';
for( i = 1; i < argc; i++)
if( argv[i][0] == '-')
switch( argv[i][1])
{
case 'r':
search_radius = atof( argv[i] + 2);
break;
case 't':
tle_file_name = argv[i] + 2;
break;
break;
case 'd':
debug_level = atoi( argv[i] + 2);
break;
case 'a':
show_non_mpc_report_lines = 1;
break;
default:
printf( "Unrecognized command-line option '%s'\n", argv[i]);
exit( -2);
break;
}
tle_file = fopen( tle_file_name, "rb");
if( !tle_file)
{
printf( "Couldn't open TLE file %s\n", tle_file_name);
exit( -1);
}
*prev_obj = '\0';
while( fgets( buff, sizeof( buff), ifile))
{
double target_ra, target_dec, jd;
if( !get_mpc_data( buff, &jd, &target_ra, &target_dec))
{
char preceding_line[80], line0[100];
double observer_loc[3], observer_loc2[3];
printf( "\n%s", buff);
if( !memcmp( prev_obj, buff, 12) && fabs( jd - prev_jd) < .3)
{
double motion, posn_ang;
if( !compute_motion( jd - prev_jd,
(target_ra - prev_ra) * cos( (prev_dec + target_dec) / 2.),
(target_dec - prev_dec), &motion, &posn_ang))
printf( " Object motion is %.3lf'/sec at PA %.1lf\n",
motion, posn_ang);
}
memcpy( prev_obj, buff, 12);
prev_ra = target_ra;
prev_dec = target_dec;
prev_jd = jd;
if( memcmp( curr_mpc_code, buff + 77, 3))
{
char tbuff[100];
int got_it = 0;
memcpy( curr_mpc_code, buff + 77, 3);
fseek( stations, 0L, SEEK_SET);
while( !got_it && fgets( tbuff, sizeof( tbuff), stations))
got_it = !memcmp( tbuff, curr_mpc_code, 3);
if( got_it)
sscanf( tbuff + 3, "%lf %lf %lf",
&lon, &rho_cos_phi, &rho_sin_phi);
if( !got_it)
printf( "FAILED to find MPC code %s\n", curr_mpc_code);
}
if( debug_level)
printf( "lon = %.5lf rho cos phi = %.5lf rho sin phi = %.5lf\n",
lon, rho_cos_phi, rho_sin_phi);
observer_cartesian_coords( jd,
lon * PI / 180., rho_cos_phi, rho_sin_phi, observer_loc);
observer_cartesian_coords( jd + TIME_EPSILON,
lon * PI / 180., rho_cos_phi, rho_sin_phi, observer_loc2);
fseek( tle_file, 0L, SEEK_SET);
*line0 = '\0';
if( fgets( line1, sizeof( line1), tle_file))
while( fgets( line2, sizeof( line2), tle_file))
{
tle_t tle; /* Structure for two-line elements set for satellite */
if( parse_elements( line1, line2, &tle) >= 0)
{ /* hey! we got a TLE! */
int is_deep = select_ephemeris( &tle);
double sat_params[N_SAT_PARAMS], radius, d_ra, d_dec;
double ra, dec, dist_to_satellite, t_since;
double pos[3]; /* Satellite position vector */
double unused_delta2;
if( debug_level > 1)
printf( "%s", line1);
t_since = (jd - tle.epoch) * 1440.;
if( is_deep)
{
SDP4_init( sat_params, &tle);
SDP4( t_since, &tle, sat_params, pos, NULL);
}
else
{
SGP4_init( sat_params, &tle);
SGP4( t_since, &tle, sat_params, pos, NULL);
}
if( debug_level > 1)
printf( "%s", line2);
if( debug_level > 2)
printf( " %.5lf %.5lf %.5lf\n", pos[0], pos[1], pos[2]);
get_satellite_ra_dec_delta( observer_loc, pos,
&ra, &dec, &dist_to_satellite);
if( debug_level > 3)
printf( "RA: %.5lf dec: %.5lf\n", ra * 180. / PI,
dec * 180. / PI);
epoch_of_date_to_j2000( jd, &ra, &dec);
d_ra = (ra - target_ra + PI * 4.);
while( d_ra > PI)
d_ra -= PI + PI;
d_dec = dec - target_dec;
radius = sqrt( d_ra * d_ra + d_dec * d_dec) * 180. / PI;
if( radius < search_radius) /* good enough for us! */
{
double arcmin_per_sec, posn_ang;
/* Compute position one second later, so we */
/* can show speed/PA of motion: */
t_since += TIME_EPSILON * 1440.;
if( is_deep)
SDP4( t_since, &tle, sat_params, pos, NULL);
else
SGP4( t_since, &tle, sat_params, pos, NULL);
get_satellite_ra_dec_delta( observer_loc2, pos,
&d_ra, &d_dec, &unused_delta2);
epoch_of_date_to_j2000( jd, &d_ra, &d_dec);
d_ra -= ra;
d_dec -= dec;
while( d_ra > PI)
d_ra -= PI + PI;
while( d_ra < -PI)
d_ra += PI + PI;
/* Put RA into 0 to 2pi range: */
if( !compute_motion( TIME_EPSILON, d_ra * cos( dec), d_dec,
&arcmin_per_sec, &posn_ang))
{
line1[8] = line1[16] = '\0';
memcpy( line1 + 30, line1 + 11, 6);
line1[11] = '\0';
printf( " %s = %s%s-%s",
line1 + 2, (line1[9] >= '6' ? "19" : "20"),
line1 + 9, line1 + 30);
printf( " e=%.2lf; P=%.1lf min; i=%.1lf",
tle.eo,
2. * PI / tle.xno,
tle.xincl * 180. / PI);
if( strlen( line0) < 30) /* object name given... */
printf( ": %s\n", line0); /* not all TLEs do this */
else
printf( "\n");
printf( " delta=%8.1lf km; offset=%5.2lf degrees; motion %6.3lf'/sec at PA=%.1lf\n",
dist_to_satellite, radius, arcmin_per_sec,
posn_ang);
/* "Speed" is displayed in arcminutes/second,
or in degrees/minute */
}
}
}
strcpy( preceding_line, line1);
strcpy( line0, line1);
strcpy( line1, line2);
for( i = 0; line0[i] >= ' '; i++)
;
line0[i] = '\0'; /* remove trailing CR/LF */
}
}
else if( show_non_mpc_report_lines)
printf( "%s", buff);
}
fclose( tle_file);
fclose( stations);
fclose( ifile);
return( 0);
} /* End of main() */
int main( const int argc, const char **argv)
{
FILE *ifile = fopen( argv[1], "rb");
char line1[100], line2[100];
const char *intl_id = NULL;
double step_size = .1;
int i, n_steps = 100;
if( !ifile)
{
printf( "Couldn't open input file\n");
exit( -1);
}
for( i = 1; i < argc; i++)
if( argv[i][0] == '-')
switch( argv[i][1])
{
case 'i':
intl_id = argv[i] + 2;
break;
case 'n':
n_steps = atoi( argv[i] + 2);
break;
default:
printf( "Unrecognized option '%s'\n", argv[i]);
break;
}
*line1 = '\0';
sxpx_set_implementation_param( SXPX_DUNDEE_COMPLIANCE, 1);
while( fgets( line2, sizeof( line2), ifile))
{
tle_t tle; /* Pointer to two-line elements set for satellite */
int err_val;
if( (!intl_id || !memcmp( intl_id, line1 + 9, 6))
&& (err_val = parse_elements( line1, line2, &tle)) >= 0)
{ /* hey! we got a TLE! */
int is_deep = select_ephemeris( &tle);
double sat_params[N_SAT_PARAMS], observer_loc[3];
if( err_val)
printf( "WARNING: TLE parsing error %d\n", err_val);
for( i = 0; i < 3; i++)
observer_loc[i] = '\0';
if( is_deep)
SDP4_init( sat_params, &tle);
else
SGP4_init( sat_params, &tle);
for( i = 0; i < n_steps; i++)
{
double ra, dec, dist_to_satellite;
double pos[3]; /* Satellite position vector */
double t_since = (double)( i - n_steps / 2) * step_size;
double jd = tle.epoch + t_since;
t_since *= 1440.;
if( is_deep)
err_val = SDP4( t_since, &tle, sat_params, pos, NULL);
else
err_val = SGP4( t_since, &tle, sat_params, pos, NULL);
if( err_val)
printf( "Ephemeris error %d\n", err_val);
get_satellite_ra_dec_delta( observer_loc, pos,
&ra, &dec, &dist_to_satellite);
epoch_of_date_to_j2000( jd, &ra, &dec);
printf( "%-14sC%13.5f %08.4f %+08.4f",
intl_id, jd, ra * 180. / PI, dec * 180. / PI);
printf( " TLEs 500\n");
}
}
strcpy( line1, line2);
}
fclose( ifile);
return( 0);
} /* End of main() */
