mirror of https://github.com/gnss-sdr/gnss-sdr
254 lines
7.8 KiB
C++
254 lines
7.8 KiB
C++
/*!
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* \file gnss_ephemeris.cc
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* \brief Base class for GNSS Ephemeris
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* \author Carles Fernandez, 2021. cfernandez(at)cttc.es
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*
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*
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* -----------------------------------------------------------------------------
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*
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* GNSS-SDR is a Global Navigation Satellite System software-defined receiver.
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* This file is part of GNSS-SDR.
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*
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* Copyright (C) 2010-2021 (see AUTHORS file for a list of contributors)
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* SPDX-License-Identifier: GPL-3.0-or-later
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*
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* -----------------------------------------------------------------------------
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*/
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#include "gnss_ephemeris.h"
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#include "MATH_CONSTANTS.h"
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#include <cmath>
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void Gnss_Ephemeris::satellitePosition(double transmitTime)
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{
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// Restore semi-major axis
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const double a = this->sqrtA * this->sqrtA;
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// Computed mean motion
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double n0;
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if (this->System == 'E')
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{
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n0 = sqrt(GALILEO_GM / (a * a * a));
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}
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else if (this->System == 'B')
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{
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n0 = sqrt(BEIDOU_GM / (a * a * a));
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}
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else
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{
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n0 = sqrt(GPS_GM / (a * a * a));
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}
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// Time from ephemeris reference epoch
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double tk = check_t(transmitTime - static_cast<double>(this->toe));
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// Corrected mean motion
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const double n = n0 + this->delta_n;
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// Mean anomaly
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double M = this->M_0 + n * tk;
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// Reduce mean anomaly to between 0 and 2pi
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M = fmod((M + 2.0 * GNSS_PI), (2.0 * GNSS_PI));
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// Initial guess of eccentric anomaly
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double E = M;
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double E_old;
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double dE;
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// --- Iteratively compute eccentric anomaly -------------------------------
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for (int32_t ii = 1; ii < 20; ii++)
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{
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E_old = E;
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E = M + this->ecc * sin(E);
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dE = fmod(E - E_old, 2.0 * GNSS_PI);
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if (fabs(dE) < 1e-12)
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{
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// Necessary precision is reached, exit from the loop
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break;
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}
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}
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const double sek = sin(E);
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const double cek = cos(E);
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const double OneMinusecosE = 1.0 - this->ecc * cek;
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const double sq1e2 = sqrt(1.0 - this->ecc * this->ecc);
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const double ekdot = n / OneMinusecosE;
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// Compute the true anomaly
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const double tmp_Y = sq1e2 * sek;
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const double tmp_X = cek - this->ecc;
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const double nu = atan2(tmp_Y, tmp_X);
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// Compute angle phi (argument of Latitude)
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double phi = nu + this->omega;
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// Reduce phi to between 0 and 2*pi rad
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phi = fmod((phi), (2.0 * GNSS_PI));
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const double s2pk = sin(2.0 * phi);
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const double c2pk = cos(2.0 * phi);
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const double pkdot = sq1e2 * ekdot / OneMinusecosE;
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// Correct argument of latitude
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const double u = phi + this->Cuc * c2pk + this->Cus * s2pk;
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const double suk = sin(u);
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const double cuk = cos(u);
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const double ukdot = pkdot * (1.0 + 2.0 * (this->Cus * c2pk - this->Cuc * s2pk));
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// Correct radius
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const double r = a * OneMinusecosE + this->Crc * c2pk + this->Crs * s2pk;
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const double rkdot = a * this->ecc * sek * ekdot + 2.0 * pkdot * (this->Crs * c2pk - this->Crc * s2pk);
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// Correct inclination
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const double i = this->i_0 + this->idot * tk + this->Cic * c2pk + this->Cis * s2pk;
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const double sik = sin(i);
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const double cik = cos(i);
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const double ikdot = this->idot + 2.0 * pkdot * (this->Cis * c2pk - this->Cic * s2pk);
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// Compute the angle between the ascending node and the Greenwich meridian
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double Omega;
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double Omega_dot;
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if (this->System == 'B')
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{
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Omega_dot = this->OMEGAdot - BEIDOU_OMEGA_EARTH_DOT;
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Omega = this->OMEGA_0 + Omega_dot * tk - BEIDOU_OMEGA_EARTH_DOT * static_cast<double>(this->toe);
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}
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else
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{
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Omega_dot = this->OMEGAdot - GNSS_OMEGA_EARTH_DOT;
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Omega = this->OMEGA_0 + Omega_dot * tk - GNSS_OMEGA_EARTH_DOT * static_cast<double>(this->toe);
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}
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// Reduce to between 0 and 2*pi rad
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Omega = fmod((Omega + 2.0 * GNSS_PI), (2.0 * GNSS_PI));
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const double sok = sin(Omega);
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const double cok = cos(Omega);
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// --- Compute satellite coordinates in Earth-fixed coordinates
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const double xprime = r * cuk;
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const double yprime = r * suk;
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this->satpos_X = xprime * cok - yprime * cik * sok;
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this->satpos_Y = xprime * sok + yprime * cik * cok; // ********NOTE: in GALILEO ICD this expression is not correct because it has minus (- sin(u) * r * cos(i) * cos(Omega)) instead of plus
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this->satpos_Z = yprime * sik;
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// Satellite's velocity. Can be useful for Vector Tracking loops
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const double xpkdot = rkdot * cuk - yprime * ukdot;
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const double ypkdot = rkdot * suk + xprime * ukdot;
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const double tmp = ypkdot * cik - this->satpos_Z * ikdot;
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this->satvel_X = -Omega_dot * this->satpos_Y + xpkdot * cok - tmp * sok;
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this->satvel_Y = Omega_dot * this->satpos_X + xpkdot * sok + tmp * cok;
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this->satvel_Z = yprime * cik * ikdot + ypkdot * sik;
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// Time from ephemeris reference clock
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tk = check_t(transmitTime - this->toc);
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this->dtr = this->af0 + this->af1 * tk + this->af2 * tk * tk;
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if (this->System == 'E')
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{
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this->dtr -= 2.0 * sqrt(GALILEO_GM * a) * this->ecc * sek / (SPEED_OF_LIGHT_M_S * SPEED_OF_LIGHT_M_S);
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}
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else if (this->System == 'B')
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{
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this->dtr -= 2.0 * sqrt(BEIDOU_GM * a) * this->ecc * sek / (SPEED_OF_LIGHT_M_S * SPEED_OF_LIGHT_M_S);
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}
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else
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{
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this->dtr -= 2.0 * sqrt(GPS_GM * a) * this->ecc * sek / (SPEED_OF_LIGHT_M_S * SPEED_OF_LIGHT_M_S);
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}
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}
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double Gnss_Ephemeris::sv_clock_drift(double transmitTime)
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{
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const double dt = check_t(transmitTime - this->toc);
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this->dtr = sv_clock_relativistic_term(transmitTime);
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this->satClkDrift = this->af0 + this->af1 * dt + this->af2 * (dt * dt) + this->dtr;
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return this->satClkDrift;
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}
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double Gnss_Ephemeris::sv_clock_relativistic_term(double transmitTime) const
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{
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// Restore semi-major axis
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const double a = this->sqrtA * this->sqrtA;
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// Time from ephemeris reference epoch
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const double tk = check_t(transmitTime - this->toe);
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// Computed mean motion
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double n0;
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if (this->System == 'E')
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{
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n0 = sqrt(GALILEO_GM / (a * a * a));
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}
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if (this->System == 'E')
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{
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n0 = sqrt(BEIDOU_GM / (a * a * a));
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}
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else
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{
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n0 = sqrt(GPS_GM / (a * a * a));
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}
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// Corrected mean motion
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const double n = n0 + this->delta_n;
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// Mean anomaly
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const double M = this->M_0 + n * tk;
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// Reduce mean anomaly to between 0 and 2pi
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// M = fmod((M + 2.0 * GNSS_PI), (2.0 * GNSS_PI));
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// Initial guess of eccentric anomaly
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double E = M;
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double E_old;
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double dE;
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// --- Iteratively compute eccentric anomaly ----------------------------
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for (int32_t ii = 1; ii < 20; ii++)
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{
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E_old = E;
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E = M + this->ecc * sin(E);
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dE = fmod(E - E_old, 2.0 * GNSS_PI);
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if (fabs(dE) < 1e-12)
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{
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// Necessary precision is reached, exit from the loop
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break;
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}
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}
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const double sek = sin(E);
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// Compute relativistic correction term
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double dtr_;
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if (this->System == 'E')
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{
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dtr_ = GALILEO_F * this->ecc * this->sqrtA * sek;
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}
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if (this->System == 'B')
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{
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dtr_ = BEIDOU_F * this->ecc * this->sqrtA * sek;
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}
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else
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{
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dtr_ = GPS_F * this->ecc * this->sqrtA * sek;
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}
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return dtr_;
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}
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double Gnss_Ephemeris::check_t(double time) const
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{
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const double half_week = 302400.0; // seconds
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double corrTime = time;
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if (time > half_week)
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{
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corrTime = time - 2.0 * half_week;
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}
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else if (time < -half_week)
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{
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corrTime = time + 2.0 * half_week;
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}
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return corrTime;
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}
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