mirror of
https://github.com/gnss-sdr/gnss-sdr
synced 2025-10-31 15:23:04 +00:00
Added GPS L2 Ephemeris and Clock parameters CNAV frame bit structure
definitions
This commit is contained in:
Javier
@@ -300,14 +300,14 @@ void gps_l2_m_dll_pll_tracking_cc::update_local_carrier()
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{
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float phase_rad, phase_step_rad;
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phase_step_rad = static_cast<float>(GPS_TWO_PI) * d_carrier_doppler_hz / static_cast<float>(d_fs_in);
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phase_step_rad = static_cast<float>(GPS_L2_TWO_PI) * d_carrier_doppler_hz / static_cast<float>(d_fs_in);
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phase_rad = d_rem_carr_phase_rad;
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for(int i = 0; i < d_current_prn_length_samples; i++)
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{
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d_carr_sign[i] = gr_complex(cos(phase_rad), -sin(phase_rad));
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phase_rad += phase_step_rad;
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}
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//d_rem_carr_phase_rad = fmod(phase_rad, GPS_TWO_PI);
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//d_rem_carr_phase_rad = fmod(phase_rad, GPS_L2_TWO_PI);
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//d_acc_carrier_phase_rad = d_acc_carrier_phase_rad + d_rem_carr_phase_rad;
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}
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@@ -413,7 +413,7 @@ int gps_l2_m_dll_pll_tracking_cc::general_work (int noutput_items, gr_vector_int
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// ################## PLL ##########################################################
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// PLL discriminator
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carr_error_hz = pll_cloop_two_quadrant_atan(*d_Prompt) / static_cast<float>(GPS_TWO_PI);
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carr_error_hz = pll_cloop_two_quadrant_atan(*d_Prompt) / static_cast<float>(GPS_L2_TWO_PI);
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// Carrier discriminator filter
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carr_error_filt_hz = d_carrier_loop_filter.get_carrier_nco(carr_error_hz);
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// New carrier Doppler frequency estimation
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@@ -421,10 +421,10 @@ int gps_l2_m_dll_pll_tracking_cc::general_work (int noutput_items, gr_vector_int
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// New code Doppler frequency estimation
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d_code_freq_chips = GPS_L2_M_CODE_RATE_HZ + ((d_carrier_doppler_hz * GPS_L2_M_CODE_RATE_HZ) / GPS_L2_FREQ_HZ);
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//carrier phase accumulator for (K) doppler estimation
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d_acc_carrier_phase_rad = d_acc_carrier_phase_rad + GPS_TWO_PI * d_carrier_doppler_hz * GPS_L2_M_PERIOD;
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d_acc_carrier_phase_rad = d_acc_carrier_phase_rad + GPS_L2_TWO_PI * d_carrier_doppler_hz * GPS_L2_M_PERIOD;
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//remanent carrier phase to prevent overflow in the code NCO
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d_rem_carr_phase_rad = d_rem_carr_phase_rad + GPS_TWO_PI * d_carrier_doppler_hz * GPS_L2_M_PERIOD;
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d_rem_carr_phase_rad = fmod(d_rem_carr_phase_rad, GPS_TWO_PI);
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d_rem_carr_phase_rad = d_rem_carr_phase_rad + GPS_L2_TWO_PI * d_carrier_doppler_hz * GPS_L2_M_PERIOD;
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d_rem_carr_phase_rad = fmod(d_rem_carr_phase_rad, GPS_L2_TWO_PI);
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// ################## DLL ##########################################################
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// DLL discriminator
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@@ -45,7 +45,6 @@
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#include <gnuradio/block.h>
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#include <gnuradio/msg_queue.h>
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#include "concurrent_queue.h"
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#include "gps_sdr_signal_processing.h"
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#include "gnss_synchro.h"
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#include "tracking_2nd_DLL_filter.h"
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#include "tracking_2nd_PLL_filter.h"
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@@ -37,6 +37,7 @@ set(SYSTEM_PARAMETERS_SOURCES
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sbas_satellite_correction.cc
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sbas_telemetry_data.cc
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galileo_fnav_message.cc
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gps_cnav_ephemeris.cc
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)
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@@ -33,6 +33,20 @@
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#define GNSS_SDR_GPS_L2C_H_
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#include <stdint.h>
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#include <complex>
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#include <vector>
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#include <utility> // std::pair
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#include <gnss_satellite.h>
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#include "MATH_CONSTANTS.h"
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// Physical constants
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const double GPS_L2_C_m_s = 299792458.0; //!< The speed of light, [m/s]
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const double GPS_L2_C_m_ms = 299792.4580; //!< The speed of light, [m/ms]
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const double GPS_L2_PI = 3.1415926535898; //!< Pi as defined in IS-GPS-200E
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const double GPS_L2_TWO_PI = 6.283185307179586;//!< 2Pi as defined in IS-GPS-200E
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const double GPS_L2_OMEGA_EARTH_DOT = 7.2921151467e-5; //!< Earth rotation rate, [rad/s]
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const double GPS_L2_GM = 3.986005e14; //!< Universal gravitational constant times the mass of the Earth, [m^3/s^2]
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const double GPS_L2_F = -4.442807633e-10; //!< Constant, [s/(m)^(1/2)]
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// carrier and code frequencies
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@@ -78,4 +92,120 @@ const int32_t GPS_L2C_M_INIT_REG[115] =
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0706202440, 0705056276, 0020373522, 0746013617,
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0132720621, 0434015513, 0566721727, 0140633660};
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// CNAV GPS NAVIGATION MESSAGE STRUCTURE
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// NAVIGATION MESSAGE FIELDS POSITIONS (from IS-GPS-200E Appendix III)
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#define GPS_CNAV_PREAMBLE {1, 0, 0, 0, 1, 0, 1, 1}
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// common to all messages
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const std::vector<std::pair<int,int> > CNAV_PRN( { {9,6} } );
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const std::vector<std::pair<int,int> > CNAV_MSG_TYPE( { {15,6} } );
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const std::vector<std::pair<int,int> > CNAV_TOW( { {21,17} } );
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const std::vector<std::pair<int,int> > CNAV_ALERT_FLAG( { {38,1} } );
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// MESSAGE TYPE 10 (Ephemeris 1)
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const std::vector<std::pair<int,int> > CNAV_WN({{39,13}});
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const std::vector<std::pair<int,int> > CNAV_HEALTH({{52,3}});
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const std::vector<std::pair<int,int> > CNAV_TOP1({{55,11}});
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const double CNAV_TOP1_LSB = 300;
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const std::vector<std::pair<int,int> > CNAV_URA({{66,5}});
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const std::vector<std::pair<int,int> > CNAV_TOE1({{71,11}});
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const double CNAV_TOE1_LSB = 300;
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const std::vector<std::pair<int,int> > CNAV_DELTA_A({{82,26}}); //Relative to AREF = 26,559,710 meters
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const double CNAV_DELTA_A_LSB = TWO_N9;
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const std::vector<std::pair<int,int> > CNAV_A_DOT({{108,25}});
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const double CNAV_A_DOT_LSB = TWO_N21;
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const std::vector<std::pair<int,int> > CNAV_DELTA_N0({{133,17}});
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const double CNAV_DELTA_N0_LSB = TWO_N44;
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const std::vector<std::pair<int,int> > CNAV_DELTA_N0_DOT({{150,23}});
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const double CNAV_DELTA_N0_DOT_LSB = TWO_N57;
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const std::vector<std::pair<int,int> > CNAV_M0({{173,33}});
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const double CNAV_M0_LSB = TWO_N32;
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const std::vector<std::pair<int,int> > CNAV_E_ECCENTRICITY({{206,33}});
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const double CNAV_E_ECCENTRICITY_LSB = TWO_N34;
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const std::vector<std::pair<int,int> > CNAV_OMEGA({{239,33}});
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const double CNAV_OMEGA_LSB = TWO_N32;
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const std::vector<std::pair<int,int> > CNAV_INTEGRITY_FLAG({{272,1}});
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const std::vector<std::pair<int,int> > CNAV_L2_PHASING_FLAG({{273,1}});
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// MESSAGE TYPE 11 (Ephemeris 2)
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const std::vector<std::pair<int,int> > CNAV_TOE2({{39,11}});
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const double CNAV_TOE2_LSB = 300;
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const std::vector<std::pair<int,int> > CNAV_OMEGA0({{50,33}});
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const double CNAV_OMEGA0_LSB = TWO_N32;
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const std::vector<std::pair<int,int> > CNAV_I0({{83,33}});
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const double CNAV_I0_LSB = TWO_N32;
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const std::vector<std::pair<int,int> > CNAV_DELTA_OMEGA_DOT({{116,17}}); //Relative to REF = -2.6 x 10-9 semi-circles/second.
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const double CNAV_DELTA_OMEGA_DOT_LSB = TWO_N44;
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const std::vector<std::pair<int,int> > CNAV_I0_DOT({{133,15}});
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const double CNAV_I0_DOT_LSB = TWO_N44;
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const std::vector<std::pair<int,int> > CNAV_CIS({{148,16}});
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const double CNAV_CIS_LSB = TWO_N30;
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const std::vector<std::pair<int,int> > CNAV_CIC({{164,16}});
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const double CNAV_CIC_LSB = TWO_N30;
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const std::vector<std::pair<int,int> > CNAV_CRS({{180,24}});
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const double CNAV_CRS_LSB = TWO_N8;
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const std::vector<std::pair<int,int> > CNAV_CRC({{204,24}});
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const double CNAV_CRC_LSB = TWO_N8;
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const std::vector<std::pair<int,int> > CNAV_CUS({{228,21}});
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const double CNAV_CUS_LSB = TWO_N30;
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const std::vector<std::pair<int,int> > CNAV_CUC({{249,21}});
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const double CNAV_CUC_LSB = TWO_N30;
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// MESSAGE TYPE 30 (CLOCK, IONO, GRUP DELAY)
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const std::vector<std::pair<int,int> > CNAV_TOP2({{39,11}});
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const double CNAV_TOP2_LSB = 300;
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const std::vector<std::pair<int,int> > CNAV_URA_NED0({{50,5}});
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const std::vector<std::pair<int,int> > CNAV_URA_NED1({{55,3}});
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const std::vector<std::pair<int,int> > CNAV_URA_NED2({{58,3}});
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const std::vector<std::pair<int,int> > CNAV_TOC({{61,11}});
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const double CNAV_TOC_LSB = 300;
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const std::vector<std::pair<int,int> > CNAV_AF0({{72,26}});
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const double CNAV_AF0_LSB = TWO_N60;
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const std::vector<std::pair<int,int> > CNAV_AF1({{98,20}});
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const double CNAV_AF1_LSB = TWO_N48;
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const std::vector<std::pair<int,int> > CNAV_AF2({{118,10}});
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const double CNAV_AF2_LSB = TWO_N35;
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const std::vector<std::pair<int,int> > CNAV_TGD({{128,13}});
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const double CNAV_TGD_LSB = TWO_N35;
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const std::vector<std::pair<int,int> > CNAV_ISCL1({{141,13}});
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const double CNAV_ISCL1_LSB = TWO_N35;
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const std::vector<std::pair<int,int> > CNAV_ISCL2({{154,13}});
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const double CNAV_ISCL2_LSB = TWO_N35;
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const std::vector<std::pair<int,int> > CNAV_ISCL5I({{167,13}});
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const double CNAV_ISCL5I_LSB = TWO_N35;
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const std::vector<std::pair<int,int> > CNAV_ISCL5Q({{180,13}});
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const double CNAV_ISCL5Q_LSB = TWO_N35;
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const std::vector<std::pair<int,int> > CNAV_ALPHA0({{193,8}});
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const double CNAV_ALPHA0_LSB = TWO_N30;
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const std::vector<std::pair<int,int> > CNAV_ALPHA1({{201,8}});
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const double CNAV_ALPHA1_LSB = TWO_N27;
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const std::vector<std::pair<int,int> > CNAV_ALPHA2({{209,8}});
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const double CNAV_ALPHA2_LSB = TWO_N24;
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const std::vector<std::pair<int,int> > CNAV_ALPHA3({{217,8}});
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const double CNAV_ALPHA3_LSB = TWO_N24;
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const std::vector<std::pair<int,int> > CNAV_BETA0({{225,8}});
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const double CNAV_BETA0_LSB = TWO_P11;
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const std::vector<std::pair<int,int> > CNAV_BETA1({{233,8}});
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const double CNAV_BETA1_LSB = TWO_P14;
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const std::vector<std::pair<int,int> > CNAV_BETA2({{241,8}});
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const double CNAV_BETA2_LSB = TWO_P16;
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const std::vector<std::pair<int,int> > CNAV_BETA3({{249,8}});
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const double CNAV_BETA3_LSB = TWO_P16;
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const std::vector<std::pair<int,int> > CNAV_WNOP({{257,8}});
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// TODO: Add more frames (Almanac, etc...)
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#endif /* GNSS_SDR_GPS_L2C_H_ */
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@@ -76,12 +76,17 @@ const double TWO_N35 = (2.91038304567337e-011); //!< 2^-35
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const double TWO_N38 = (3.637978807091713e-012); //!< 2^-38
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const double TWO_N43 = (1.136868377216160e-013); //!< 2^-43
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const double TWO_N44 = (5.684341886080802e-14); //!< 2^-44
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const double TWO_N46 = (1.4210854715202e-014); //!< 2^-46
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const double TWO_N48 = (3.552713678800501e-15); //!< 2^-46
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const double TWO_N50 = (8.881784197001252e-016); //!< 2^-50
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const double TWO_N51 = (4.44089209850063e-016); //!< 2^-51
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const double TWO_N55 = (2.775557561562891e-017); //!< 2^-55
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const double TWO_N57 = (6.938893903907228e-18); //!< 2^-57
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const double TWO_N59 = (1.73472347597681e-018); //!< 2^-59
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const double TWO_N60 = (8.673617379884036e-19); //!< 2^-60
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const double PI_TWO_N19 = (5.992112452678286e-006); //!< Pi*2^-19
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const double PI_TWO_N43 = (3.571577341960839e-013); //!< Pi*2^-43
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115
src/core/system_parameters/gps_cnav_ephemeris.cc
Normal file
115
src/core/system_parameters/gps_cnav_ephemeris.cc
Normal file
@@ -0,0 +1,115 @@
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/*!
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* \file Gps_CNAV_Ephemeris.cc
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* \brief Interface of a GPS CNAV EPHEMERIS storage and orbital model functions
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*
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* See http://www.gps.gov/technical/icwg/IS-GPS-200E.pdf Appendix II
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* \author Javier Arribas, 2015. jarribas(at)cttc.es
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*
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* -------------------------------------------------------------------------
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*
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* Copyright (C) 2010-2015 (see AUTHORS file for a list of contributors)
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*
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* GNSS-SDR is a software defined Global Navigation
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* Satellite Systems receiver
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*
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* This file is part of GNSS-SDR.
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*
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* GNSS-SDR is free software: you can redistribute it and/or modify
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* it under the terms of the GNU General Public License as published by
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* the Free Software Foundation, either version 3 of the License, or
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* (at your option) any later version.
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*
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* GNSS-SDR is distributed in the hope that it will be useful,
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* but WITHOUT ANY WARRANTY; without even the implied warranty of
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* MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
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* GNU General Public License for more details.
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*
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* You should have received a copy of the GNU General Public License
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* along with GNSS-SDR. If not, see <http://www.gnu.org/licenses/>.
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*
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* -------------------------------------------------------------------------
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*/
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#include "gps_cnav_ephemeris.h"
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Gps_CNAV_Ephemeris::Gps_CNAV_Ephemeris()
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{
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i_satellite_PRN = 0;
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d_TOW = 0;
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d_Crs = 0;
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d_M_0 = 0;
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d_Cuc = 0;
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d_e_eccentricity = 0;
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d_Cus = 0;
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d_Toe = 0;
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d_Toc = 0;
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d_Cic = 0;
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d_OMEGA0 = 0;
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d_Cis = 0;
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d_i_0 = 0;
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d_Crc = 0;
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d_OMEGA = 0;
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d_IDOT = 0;
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i_GPS_week = 0;
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d_TGD = 0; // Estimated Group Delay Differential: L1-L2 correction term only for the benefit of "L1 P(Y)" or "L2 P(Y)" s users [s]
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d_A_f0 = 0; // Coefficient 0 of code phase offset model [s]
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d_A_f1 = 0; // Coefficient 1 of code phase offset model [s/s]
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d_A_f2 = 0; // Coefficient 2 of code phase offset model [s/s^2]
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b_integrity_status_flag = false;
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b_alert_flag = false; // If true, indicates that the SV URA may be worse than indicated in d_SV_accuracy, use that SV at our own risk.
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b_antispoofing_flag = false; // If true, the AntiSpoofing mode is ON in that SV
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//Plane A (info from http://www.navcen.uscg.gov/?Do=constellationStatus)
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satelliteBlock[9] = "IIA";
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satelliteBlock[31] = "IIR-M";
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satelliteBlock[8] = "IIA";
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satelliteBlock[7] = "IIR-M";
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satelliteBlock[27] = "IIA";
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//Plane B
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satelliteBlock[16] = "IIR";
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satelliteBlock[25] = "IIF";
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satelliteBlock[28] = "IIR";
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satelliteBlock[12] = "IIR-M";
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satelliteBlock[30] = "IIA";
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//Plane C
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satelliteBlock[29] = "IIR-M";
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satelliteBlock[3] = "IIA";
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satelliteBlock[19] = "IIR";
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satelliteBlock[17] = "IIR-M";
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satelliteBlock[6] = "IIA";
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//Plane D
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satelliteBlock[2] = "IIR";
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satelliteBlock[1] = "IIF";
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satelliteBlock[21] = "IIR";
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satelliteBlock[4] = "IIA";
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satelliteBlock[11] = "IIR";
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satelliteBlock[24] = "IIA"; // Decommissioned from active service on 04 Nov 2011
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//Plane E
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satelliteBlock[20] = "IIR";
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satelliteBlock[22] = "IIR";
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satelliteBlock[5] = "IIR-M";
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satelliteBlock[18] = "IIR";
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satelliteBlock[32] = "IIA";
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satelliteBlock[10] = "IIA";
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//Plane F
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satelliteBlock[14] = "IIR";
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satelliteBlock[15] = "IIR-M";
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satelliteBlock[13] = "IIR";
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satelliteBlock[23] = "IIR";
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satelliteBlock[26] = "IIA";
|
||||
|
||||
d_satClkDrift = 0.0;
|
||||
d_dtr = 0.0;
|
||||
d_satpos_X = 0.0;
|
||||
d_satpos_Y = 0.0;
|
||||
d_satpos_Z = 0.0;
|
||||
d_satvel_X = 0.0;
|
||||
d_satvel_Y = 0.0;
|
||||
d_satvel_Z = 0.0;
|
||||
}
|
||||
179
src/core/system_parameters/gps_cnav_ephemeris.h
Normal file
179
src/core/system_parameters/gps_cnav_ephemeris.h
Normal file
@@ -0,0 +1,179 @@
|
||||
/*!
|
||||
* \file Gps_CNAV_Ephemeris.h
|
||||
* \brief Interface of a GPS EPHEMERIS storage
|
||||
* \author Javier Arribas, 2013. jarribas(at)cttc.es
|
||||
*
|
||||
* -------------------------------------------------------------------------
|
||||
*
|
||||
* Copyright (C) 2010-2015 (see AUTHORS file for a list of contributors)
|
||||
*
|
||||
* GNSS-SDR is a software defined Global Navigation
|
||||
* Satellite Systems receiver
|
||||
*
|
||||
* This file is part of GNSS-SDR.
|
||||
*
|
||||
* GNSS-SDR is free software: you can redistribute it and/or modify
|
||||
* it under the terms of the GNU General Public License as published by
|
||||
* the Free Software Foundation, either version 3 of the License, or
|
||||
* (at your option) any later version.
|
||||
*
|
||||
* GNSS-SDR is distributed in the hope that it will be useful,
|
||||
* but WITHOUT ANY WARRANTY; without even the implied warranty of
|
||||
* MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the
|
||||
* GNU General Public License for more details.
|
||||
*
|
||||
* You should have received a copy of the GNU General Public License
|
||||
* along with GNSS-SDR. If not, see <http://www.gnu.org/licenses/>.
|
||||
*
|
||||
* -------------------------------------------------------------------------
|
||||
*/
|
||||
|
||||
|
||||
#ifndef GNSS_SDR_Gps_CNAV_Ephemeris_H_
|
||||
#define GNSS_SDR_Gps_CNAV_Ephemeris_H_
|
||||
|
||||
#include <iostream>
|
||||
#include <map>
|
||||
#include <string>
|
||||
#include "boost/assign.hpp"
|
||||
#include <boost/serialization/nvp.hpp>
|
||||
#include "GPS_L2C.h"
|
||||
|
||||
|
||||
/*!
|
||||
* \brief This class is a storage and orbital model functions for the GPS SV ephemeris data as described in IS-GPS-200E
|
||||
*
|
||||
* See http://www.gps.gov/technical/icwg/IS-GPS-200E.pdf Appendix II
|
||||
*/
|
||||
class Gps_CNAV_Ephemeris
|
||||
{
|
||||
private:
|
||||
|
||||
public:
|
||||
unsigned int i_satellite_PRN; // SV PRN NUMBER
|
||||
|
||||
//Message Types 10 and 11 Parameters (1 of 2)
|
||||
int i_GPS_week; //!< GPS week number, aka WN [week]
|
||||
int i_URA; //!< ED Accuracy Index
|
||||
int i_signal_health; //!< Signal health (L1/L2/L5)
|
||||
double d_Top; //!< Data predict time of week
|
||||
double d_DELTA_A; //!< Semi-major axis difference at reference time
|
||||
double d_A_DOT; //!< Change rate in semi-major axis
|
||||
double d_Delta_n; //!< Mean Motion Difference From Computed Value [semi-circles/s]
|
||||
double d_DELTA_DOT_N; // Rate of mean motion difference from computed value
|
||||
double d_M_0; //!< Mean Anomaly at Reference Time [semi-circles]
|
||||
double d_e_eccentricity; //< Eccentricity
|
||||
double d_OMEGA; //!< Argument of Perigee [semi-cicles]
|
||||
double d_OMEGA0; //!< Longitude of Ascending Node of Orbit Plane at Weekly Epoch [semi-cicles]
|
||||
double d_Toe; //!< Ephemeris data reference time of week (Ref. 20.3.3.4.3 IS-GPS-200E) [s]
|
||||
double d_DELTA_OMEGA_DOT; //!< Rate of Right Ascension difference [semi-circles/s]
|
||||
double d_i_0; //!< Inclination Angle at Reference Time [semi-circles]
|
||||
double d_IDOT; //!< Rate of Inclination Angle [semi-circles/s]
|
||||
double d_Cis; //!< Amplitude of the Sine Harmonic Correction Term to the Angle of Inclination [rad]
|
||||
double d_Cic; //!< Amplitude of the Cosine Harmonic Correction Term to the Angle of Inclination [rad]
|
||||
double d_Crs; //!< Amplitude of the Sine Harmonic Correction Term to the Orbit Radius [m]
|
||||
double d_Crc; //!< Amplitude of the Cosine Harmonic Correction Term to the Orbit Radius [m]
|
||||
double d_Cus; //!< Amplitude of the Sine Harmonic Correction Term to the Argument of Latitude [rad]
|
||||
double d_Cuc; //!< Amplitude of the Cosine Harmonic Correction Term to the Argument of Latitude [rad]
|
||||
|
||||
//Clock Correction and Accuracy Parameters
|
||||
double d_Toc; //!< clock data reference time (Ref. 20.3.3.3.3.1 IS-GPS-200E) [s]
|
||||
double d_A_f0; //!< Coefficient 0 of code phase offset model [s]
|
||||
double d_A_f1; //!< Coefficient 1 of code phase offset model [s/s]
|
||||
double d_A_f2; //!< Coefficient 2 of code phase offset model [s/s^2]
|
||||
|
||||
double d_URA0; //!<NED Accuracy Index
|
||||
double d_URA1; //!<NED Accuracy Change Index
|
||||
double d_URA2; //!< NED Accuracy Change Rate Index
|
||||
|
||||
|
||||
//Group Delay Differential Parameters
|
||||
double d_TGD; //!< Estimated Group Delay Differential: L1-L2 correction term only for the benefit of "L1 P(Y)" or "L2 P(Y)" s users [s]
|
||||
double d_ISCL1;
|
||||
double d_ISCL2;
|
||||
double d_ISCL5I;
|
||||
double d_ISCL5Q;
|
||||
|
||||
double d_TOW; //!< Time of GPS Week of the ephemeris set (taken from subframes TOW) [s]
|
||||
|
||||
|
||||
|
||||
|
||||
// Flags
|
||||
|
||||
/*! \brief If true, enhanced level of integrity assurance.
|
||||
*
|
||||
* If false, indicates that the conveying signal is provided with the legacy level of integrity assurance.
|
||||
* That is, the probability that the instantaneous URE of the conveying signal exceeds 4.42 times the upper bound
|
||||
* value of the current broadcast URA index, for more than 5.2 seconds, without an accompanying alert, is less
|
||||
* than 1E-5 per hour. If true, indicates that the conveying signal is provided with an enhanced level of
|
||||
* integrity assurance. That is, the probability that the instantaneous URE of the conveying signal exceeds 5.73
|
||||
* times the upper bound value of the current broadcast URA index, for more than 5.2 seconds, without an
|
||||
* accompanying alert, is less than 1E-8 per hour.
|
||||
*/
|
||||
bool b_integrity_status_flag;
|
||||
bool b_alert_flag; //!< If true, indicates that the SV URA may be worse than indicated in d_SV_accuracy, use that SV at our own risk.
|
||||
bool b_antispoofing_flag; //!< If true, the AntiSpoofing mode is ON in that SV
|
||||
|
||||
// clock terms derived from ephemeris data
|
||||
double d_satClkDrift; //!< GPS clock error
|
||||
double d_dtr; //!< relativistic clock correction term
|
||||
|
||||
// satellite positions
|
||||
double d_satpos_X; //!< Earth-fixed coordinate x of the satellite [m]. Intersection of the IERS Reference Meridian (IRM) and the plane passing through the origin and normal to the Z-axis.
|
||||
double d_satpos_Y; //!< Earth-fixed coordinate y of the satellite [m]. Completes a right-handed, Earth-Centered, Earth-Fixed orthogonal coordinate system.
|
||||
double d_satpos_Z; //!< Earth-fixed coordinate z of the satellite [m]. The direction of the IERS (International Earth Rotation and Reference Systems Service) Reference Pole (IRP).
|
||||
|
||||
// Satellite velocity
|
||||
double d_satvel_X; //!< Earth-fixed velocity coordinate x of the satellite [m]
|
||||
double d_satvel_Y; //!< Earth-fixed velocity coordinate y of the satellite [m]
|
||||
double d_satvel_Z; //!< Earth-fixed velocity coordinate z of the satellite [m]
|
||||
|
||||
std::map<int,std::string> satelliteBlock; //!< Map that stores to which block the PRN belongs http://www.navcen.uscg.gov/?Do=constellationStatus
|
||||
|
||||
template<class Archive>
|
||||
|
||||
/*!
|
||||
* \brief Serialize is a boost standard method to be called by the boost XML serialization. Here is used to save the ephemeris data on disk file.
|
||||
*/
|
||||
void serialize(Archive& archive, const unsigned int version)
|
||||
{
|
||||
using boost::serialization::make_nvp;
|
||||
if(version){};
|
||||
|
||||
archive & make_nvp("i_satellite_PRN", i_satellite_PRN); // SV PRN NUMBER
|
||||
archive & make_nvp("d_TOW", d_TOW); //!< Time of GPS Week of the ephemeris set (taken from subframes TOW) [s]
|
||||
archive & make_nvp("d_Crs", d_Crs); //!< Amplitude of the Sine Harmonic Correction Term to the Orbit Radius [m]
|
||||
archive & make_nvp("d_M_0", d_M_0); //!< Mean Anomaly at Reference Time [semi-circles]
|
||||
archive & make_nvp("d_Cuc", d_Cuc); //!< Amplitude of the Cosine Harmonic Correction Term to the Argument of Latitude [rad]
|
||||
archive & make_nvp("d_e_eccentricity", d_e_eccentricity); //!< Eccentricity [dimensionless]
|
||||
archive & make_nvp("d_Cus", d_Cus); //!< Amplitude of the Sine Harmonic Correction Term to the Argument of Latitude [rad]
|
||||
archive & make_nvp("d_Toe", d_Toe); //!< Ephemeris data reference time of week (Ref. 20.3.3.4.3 IS-GPS-200E) [s]
|
||||
archive & make_nvp("d_Toc", d_Toe); //!< clock data reference time (Ref. 20.3.3.3.3.1 IS-GPS-200E) [s]
|
||||
archive & make_nvp("d_Cic", d_Cic); //!< Amplitude of the Cosine Harmonic Correction Term to the Angle of Inclination [rad]
|
||||
archive & make_nvp("d_OMEGA0", d_OMEGA0); //!< Longitude of Ascending Node of Orbit Plane at Weekly Epoch [semi-circles]
|
||||
archive & make_nvp("d_Cis", d_Cis); //!< Amplitude of the Sine Harmonic Correction Term to the Angle of Inclination [rad]
|
||||
archive & make_nvp("d_i_0", d_i_0); //!< Inclination Angle at Reference Time [semi-circles]
|
||||
archive & make_nvp("d_Crc", d_Crc); //!< Amplitude of the Cosine Harmonic Correction Term to the Orbit Radius [m]
|
||||
archive & make_nvp("d_OMEGA", d_OMEGA); //!< Argument of Perigee [semi-cicles]
|
||||
archive & make_nvp("d_IDOT", d_IDOT); //!< Rate of Inclination Angle [semi-circles/s]
|
||||
archive & make_nvp("i_GPS_week", i_GPS_week); //!< GPS week number, aka WN [week]
|
||||
archive & make_nvp("d_TGD", d_TGD); //!< Estimated Group Delay Differential: L1-L2 correction term only for the benefit of "L1 P(Y)" or "L2 P(Y)" s users [s]
|
||||
|
||||
|
||||
archive & make_nvp("d_A_f0", d_A_f0); //!< Coefficient 0 of code phase offset model [s]
|
||||
archive & make_nvp("d_A_f1", d_A_f1); //!< Coefficient 1 of code phase offset model [s/s]
|
||||
archive & make_nvp("d_A_f2", d_A_f2); //!< Coefficient 2 of code phase offset model [s/s^2]
|
||||
|
||||
archive & make_nvp("b_integrity_status_flag", b_integrity_status_flag);
|
||||
archive & make_nvp("b_alert_flag", b_alert_flag); //!< If true, indicates that the SV URA may be worse than indicated in d_SV_accuracy, use that SV at our own risk.
|
||||
archive & make_nvp("b_antispoofing_flag", b_antispoofing_flag); //!< If true, the AntiSpoofing mode is ON in that SV
|
||||
}
|
||||
|
||||
/*!
|
||||
* Default constructor
|
||||
*/
|
||||
Gps_CNAV_Ephemeris();
|
||||
};
|
||||
|
||||
#endif
|
||||
Reference in New Issue
Block a user