kopia lustrzana https://github.com/dl9rdz/rdz_ttgo_sonde
149 wiersze
6.8 KiB
C
149 wiersze
6.8 KiB
C
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typedef struct {
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uint16_t prn;
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uint16_t week;
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uint32_t toa;
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char epoch[20];
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double toe;
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double toc;
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double e;
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double delta_n;
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double delta_i;
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double i0;
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double OmegaDot;
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double sqrta;
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double Omega0;
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double w;
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double M0;
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double tgd;
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double idot;
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double cuc;
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double cus;
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double crc;
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double crs;
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double cic;
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double cis;
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double af0;
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double af1;
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double af2;
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int gpsweek;
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uint16_t svn;
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uint8_t ura;
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uint8_t health;
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uint8_t conf;
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} EPHEM_t;
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typedef struct {
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uint32_t t;
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double pseudorange;
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double pseudorate;
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double clock_corr;
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double clock_drift;
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double X;
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double Y;
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double Z;
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double vX;
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double vY;
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double vZ;
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int ephhr;
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double PR;
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double ephtime;
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int prn;
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} SAT_t;
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typedef struct {double X; double Y; double Z;} LOC_t;
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typedef struct {double X; double Y; double Z;
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double vX; double vY; double vZ;} VEL_t;
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double dist(double X1, double Y1, double Z1, double X2, double Y2, double Z2);
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void GPS_SatelliteClockCorrection(
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const unsigned short transmission_gpsweek, // GPS week when signal was transmit (0-1024+) [weeks]
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const double transmission_gpstow, // GPS time of week when signal was transmit [s]
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const unsigned short ephem_week, // ephemeris: GPS week (0-1024+) [weeks]
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const double toe, // ephemeris: time of week [s]
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const double toc, // ephemeris: clock reference time of week [s]
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const double af0, // ephemeris: polynomial clock correction coefficient [s],
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const double af1, // ephemeris: polynomial clock correction coefficient [s/s],
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const double af2, // ephemeris: polynomial clock correction coefficient [s/s^2]
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const double ecc, // ephemeris: eccentricity of satellite orbit []
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const double sqrta, // ephemeris: square root of the semi-major axis of orbit [m^(1/2)]
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const double delta_n, // ephemeris: mean motion difference from computed value [rad]
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const double m0, // ephemeris: mean anomaly at reference time [rad]
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const double tgd, // ephemeris: group delay differential between L1 and L2 [s]
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double* clock_correction );
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void GPS_SatellitePosition_Ephem(
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const unsigned short gpsweek, // gps week of signal transmission (0-1024+) [week]
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const double gpstow, // time of week of signal transmission (gpstow-psr/c) [s]
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EPHEM_t ephem,
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double* clock_correction, // clock correction for this satellite for this epoch [m]
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double* satX, // satellite X position WGS84 ECEF [m]
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double* satY, // satellite Y position WGS84 ECEF [m]
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double* satZ // satellite Z position WGS84 ECEF [m]
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);
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void GPS_SatelliteClockDriftCorrection(
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const unsigned short transmission_gpsweek, // GPS week when signal was transmit (0-1024+) [weeks]
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const double transmission_gpstow, // GPS time of week when signal was transmit [s]
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const unsigned short ephem_week, // ephemeris: GPS week (0-1024+) [weeks]
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const double toe, // ephemeris: time of week [s]
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const double toc, // ephemeris: clock reference time of week [s]
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const double af0, // ephemeris: polynomial clock correction coefficient [s],
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const double af1, // ephemeris: polynomial clock correction coefficient [s/s],
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const double af2, // ephemeris: polynomial clock correction coefficient [s/s^2]
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const double ecc, // ephemeris: eccentricity of satellite orbit []
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const double sqrta, // ephemeris: square root of the semi-major axis of orbit [m^(1/2)]
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const double delta_n, // ephemeris: mean motion difference from computed value [rad]
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const double m0, // ephemeris: mean anomaly at reference time [rad]
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const double tgd, // ephemeris: group delay differential between L1 and L2 [s]
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double* clock_correction, // ephemeris: satellite clock correction [m]
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double* clock_drift ) ;
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void GPS_SatellitePositionVelocity_Ephem(
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const unsigned short gpsweek, // gps week of signal transmission (0-1024+) [week]
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const double gpstow, // time of week of signal transmission (gpstow-psr/c) [s]
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EPHEM_t ephem,
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double* clock_correction, // clock correction for this satellite for this epoch [m]
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double* clock_drift, // clock correction for this satellite for this epoch [m]
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double* satX, // satellite X position WGS84 ECEF [m]
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double* satY, // satellite Y position WGS84 ECEF [m]
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double* satZ, // satellite Z position WGS84 ECEF [m]
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double* satvX, // satellite X velocity WGS84 ECEF [m]
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double* satvY, // satellite Y velocity WGS84 ECEF [m]
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double* satvZ // satellite Z velocity WGS84 ECEF [m]
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);
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int NAV_ClosedFormSolution_FromPseudorange(
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SAT_t sats[4], // input: satellite position and pseudorange
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double* latitude, // output: ellipsoid latitude [rad]
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double* longitude, // ellipsoid longitude [rad]
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double* height, // ellipsoid height [m]
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double* rx_clock_bias, // receiver clock bias [m]
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double pos_ecef[3] );
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int calc_DOPn(int n, SAT_t satss[], double pos_ecef[3], double DOP[4]);
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int NAV_LinP(int N, SAT_t satv[], double pos_ecef[3], double dt,
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double dpos_ecef[3], double *cc);
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void ecef2elli(double X, double Y, double Z, double *lat, double *lon, double *alt);
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int NAV_LinP(int N, SAT_t satv[], double pos_ecef[3], double dt,
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double dpos_ecef[3], double *cc);
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int NAV_LinV(int N, SAT_t satv[], double pos_ecef[3],
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double vel_ecef[3], double dt,
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double dvel_ecef[3], double *cc);
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int NAV_bancroft1(int N, SAT_t sats[], double pos_ecef[3], double *cc);
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EPHEM_t *read_RNXpephs(const char *file);
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