mirror of https://github.com/gnss-sdr/gnss-sdr
206 lines
12 KiB
C++
206 lines
12 KiB
C++
/*!
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* \file gps_ephemeris.h
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* \brief Interface of a GPS EPHEMERIS storage
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* \author Javier Arribas, 2013. jarribas(at)cttc.es
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*
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* -------------------------------------------------------------------------
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*
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* Copyright (C) 2010-2013 (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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#ifndef GNSS_SDR_GPS_EPHEMERIS_H_
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#define GNSS_SDR_GPS_EPHEMERIS_H_
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#include <iostream>
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#include <map>
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#include "boost/assign.hpp"
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#include <boost/serialization/nvp.hpp>
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#include "GPS_L1_CA.h"
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/*!
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* \brief This class is a storage and orbital model functions for the GPS SV ephemeris data as described in IS-GPS-200E
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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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*/
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class Gps_Ephemeris
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{
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private:
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/*
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* Accounts for the beginning or end of week crossover
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*
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* See paragraph 20.3.3.3.3.1 (IS-GPS-200E)
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* \param[in] - time in seconds
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* \param[out] - corrected time, in seconds
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*/
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double check_t(double time);
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public:
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unsigned int i_satellite_PRN; // SV PRN NUMBER
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double d_TOW; //!< Time of GPS Week of the ephemeris set (taken from subframes TOW) [s]
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double d_Crs; //!< Amplitude of the Sine Harmonic Correction Term to the Orbit Radius [m]
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double d_Delta_n; //!< Mean Motion Difference From Computed Value [semi-circles/s]
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double d_M_0; //!< Mean Anomaly at Reference Time [semi-circles]
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double d_Cuc; //!< Amplitude of the Cosine Harmonic Correction Term to the Argument of Latitude [rad]
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double d_e_eccentricity; //!< Eccentricity [dimensionless]
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double d_Cus; //!< Amplitude of the Sine Harmonic Correction Term to the Argument of Latitude [rad]
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double d_sqrt_A; //!< Square Root of the Semi-Major Axis [sqrt(m)]
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double d_Toe; //!< Ephemeris data reference time of week (Ref. 20.3.3.4.3 IS-GPS-200E) [s]
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double d_Toc; //!< clock data reference time (Ref. 20.3.3.3.3.1 IS-GPS-200E) [s]
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double d_Cic; //!< Amplitude of the Cosine Harmonic Correction Term to the Angle of Inclination [rad]
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double d_OMEGA0; //!< Longitude of Ascending Node of Orbit Plane at Weekly Epoch [semi-circles]
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double d_Cis; //!< Amplitude of the Sine Harmonic Correction Term to the Angle of Inclination [rad]
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double d_i_0; //!< Inclination Angle at Reference Time [semi-circles]
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double d_Crc; //!< Amplitude of the Cosine Harmonic Correction Term to the Orbit Radius [m]
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double d_OMEGA; //!< Argument of Perigee [semi-cicles]
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double d_OMEGA_DOT; //!< Rate of Right Ascension [semi-circles/s]
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double d_IDOT; //!< Rate of Inclination Angle [semi-circles/s]
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int i_code_on_L2; //!< If 1, P code ON in L2; if 2, C/A code ON in L2;
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int i_GPS_week; //!< GPS week number, aka WN [week]
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bool b_L2_P_data_flag; //!< When true, indicates that the NAV data stream was commanded OFF on the P-code of the L2 channel
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int i_SV_accuracy; //!< User Range Accuracy (URA) index of the SV (reference paragraph 6.2.1) for the standard positioning service user (Ref 20.3.3.3.1.3 IS-GPS-200E)
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int i_SV_health;
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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]
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double d_IODC; //!< Issue of Data, Clock
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int i_AODO; //!< Age of Data Offset (AODO) term for the navigation message correction table (NMCT) contained in subframe 4 (reference paragraph 20.3.3.5.1.9) [s]
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bool b_fit_interval_flag;//!< indicates the curve-fit interval used by the CS (Block II/IIA/IIR/IIR-M/IIF) and SS (Block IIIA) in determining the ephemeris parameters, as follows: 0 = 4 hours, 1 = greater than 4 hours.
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double d_spare1;
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double d_spare2;
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double d_A_f0; //!< Coefficient 0 of code phase offset model [s]
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double d_A_f1; //!< Coefficient 1 of code phase offset model [s/s]
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double d_A_f2; //!< Coefficient 2 of code phase offset model [s/s^2]
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// Flags
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/*! \brief If true, enhanced level of integrity assurance.
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*
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* If false, indicates that the conveying signal is provided with the legacy level of integrity assurance.
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* That is, the probability that the instantaneous URE of the conveying signal exceeds 4.42 times the upper bound
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* value of the current broadcast URA index, for more than 5.2 seconds, without an accompanying alert, is less
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* than 1E-5 per hour. If true, indicates that the conveying signal is provided with an enhanced level of
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* integrity assurance. That is, the probability that the instantaneous URE of the conveying signal exceeds 5.73
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* times the upper bound value of the current broadcast URA index, for more than 5.2 seconds, without an
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* accompanying alert, is less than 1E-8 per hour.
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*/
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bool b_integrity_status_flag;
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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.
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bool b_antispoofing_flag; //!< If true, the AntiSpoofing mode is ON in that SV
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// clock terms derived from ephemeris data
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double d_satClkDrift; // GPS clock error
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double d_dtr; // relativistic clock correction term
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// satellite positions
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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.
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double d_satpos_Y; //!< Earth-fixed coordinate y of the satellite [m]. Completes a right-handed, Earth-Centered, Earth-Fixed orthogonal coordinate system.
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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).
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// Satellite velocity
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double d_satvel_X; //!< Earth-fixed velocity coordinate x of the satellite [m]
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double d_satvel_Y; //!< Earth-fixed velocity coordinate y of the satellite [m]
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double d_satvel_Z; //!< Earth-fixed velocity coordinate z of the satellite [m]
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std::map<int,std::string> satelliteBlock; //!< Map that stores to which block the PRN belongs http://www.navcen.uscg.gov/?Do=constellationStatus
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template<class Archive>
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/*
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* \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.
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*/
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void serialize(Archive& archive, const unsigned int version)
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{
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using boost::serialization::make_nvp;
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archive & make_nvp("i_satellite_PRN", i_satellite_PRN); // SV PRN NUMBER
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archive & make_nvp("d_TOW", d_TOW); //!< Time of GPS Week of the ephemeris set (taken from subframes TOW) [s]
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archive & make_nvp("d_Crs", d_Crs); //!< Amplitude of the Sine Harmonic Correction Term to the Orbit Radius [m]
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archive & make_nvp("d_Delta_n", d_Delta_n); //!< Mean Motion Difference From Computed Value [semi-circles/s]
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archive & make_nvp("d_M_0", d_M_0); //!< Mean Anomaly at Reference Time [semi-circles]
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archive & make_nvp("d_Cuc", d_Cuc); //!< Amplitude of the Cosine Harmonic Correction Term to the Argument of Latitude [rad]
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archive & make_nvp("d_e_eccentricity", d_e_eccentricity); //!< Eccentricity [dimensionless]
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archive & make_nvp("d_Cus", d_Cus); //!< Amplitude of the Sine Harmonic Correction Term to the Argument of Latitude [rad]
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archive & make_nvp("d_sqrt_A", d_sqrt_A); //!< Square Root of the Semi-Major Axis [sqrt(m)]
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archive & make_nvp("d_Toe", d_Toe); //!< Ephemeris data reference time of week (Ref. 20.3.3.4.3 IS-GPS-200E) [s]
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archive & make_nvp("d_Toc", d_Toe); //!< clock data reference time (Ref. 20.3.3.3.3.1 IS-GPS-200E) [s]
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archive & make_nvp("d_Cic", d_Cic); //!< Amplitude of the Cosine Harmonic Correction Term to the Angle of Inclination [rad]
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archive & make_nvp("d_OMEGA0", d_OMEGA0); //!< Longitude of Ascending Node of Orbit Plane at Weekly Epoch [semi-circles]
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archive & make_nvp("d_Cis", d_Cis); //!< Amplitude of the Sine Harmonic Correction Term to the Angle of Inclination [rad]
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archive & make_nvp("d_i_0", d_i_0); //!< Inclination Angle at Reference Time [semi-circles]
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archive & make_nvp("d_Crc", d_Crc); //!< Amplitude of the Cosine Harmonic Correction Term to the Orbit Radius [m]
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archive & make_nvp("d_OMEGA", d_OMEGA); //!< Argument of Perigee [semi-cicles]
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archive & make_nvp("d_OMEGA_DOT", d_OMEGA_DOT); //!< Rate of Right Ascension [semi-circles/s]
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archive & make_nvp("d_IDOT", d_IDOT); //!< Rate of Inclination Angle [semi-circles/s]
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archive & make_nvp("i_code_on_L2", i_code_on_L2); //!< If 1, P code ON in L2; if 2, C/A code ON in L2;
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archive & make_nvp("i_GPS_week", i_GPS_week); //!< GPS week number, aka WN [week]
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archive & make_nvp("b_L2_P_data_flag", b_L2_P_data_flag); //!< When true, indicates that the NAV data stream was commanded OFF on the P-code of the L2 channel
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archive & make_nvp("i_SV_accuracy", i_SV_accuracy); //!< User Range Accuracy (URA) index of the SV (reference paragraph 6.2.1) for the standard positioning service user (Ref 20.3.3.3.1.3 IS-GPS-200E)
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archive & make_nvp("i_SV_health", i_SV_health);
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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]
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archive & make_nvp("d_IODC", d_IODC); //!< Issue of Data, Clock
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archive & make_nvp("i_AODO", i_AODO); //!< Age of Data Offset (AODO) term for the navigation message correction table (NMCT) contained in subframe 4 (reference paragraph 20.3.3.5.1.9) [s]
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archive & make_nvp("b_fit_interval_flag", b_fit_interval_flag);//!< indicates the curve-fit interval used by the CS (Block II/IIA/IIR/IIR-M/IIF) and SS (Block IIIA) in determining the ephemeris parameters, as follows: 0 = 4 hours, 1 = greater than 4 hours.
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archive & make_nvp("d_spare1", d_spare1);
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archive & make_nvp("d_spare2", d_spare2);
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archive & make_nvp("d_A_f0", d_A_f0); //!< Coefficient 0 of code phase offset model [s]
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archive & make_nvp("d_A_f1", d_A_f1); //!< Coefficient 1 of code phase offset model [s/s]
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archive & make_nvp("d_A_f2", d_A_f2); //!< Coefficient 2 of code phase offset model [s/s^2]
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archive & make_nvp("b_integrity_status_flag", b_integrity_status_flag);
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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.
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archive & make_nvp("b_antispoofing_flag", b_antispoofing_flag); //!< If true, the AntiSpoofing mode is ON in that SV
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}
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/*!
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* \brief Compute the ECEF SV coordinates and ECEF velocity
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* Implementation of Table 20-IV (IS-GPS-200E)
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*/
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void satellitePosition(double transmitTime);
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/*!
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* \brief Sets (\a d_satClkDrift)and returns the clock drift in seconds according to the User Algorithm for SV Clock Correction
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* (IS-GPS-200E, 20.3.3.3.3.1)
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*/
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double sv_clock_drift(double transmitTime);
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/*!
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* \brief Sets (\a d_dtr) and returns the clock relativistic correction term in seconds according to the User Algorithm for SV Clock Correction
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* (IS-GPS-200E, 20.3.3.3.3.1)
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*/
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double sv_clock_relativistic_term(double transmitTime);
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/*!
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* Default constructor
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*/
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Gps_Ephemeris();
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};
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#endif
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