INSTINCT Code Coverage Report

Directory:	src/
File:	Navigation/GNSS/Satellite/Ephemeris/IRNSSEphemeris.hpp
Date:	2025-02-07 16:54:41

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Lines:	1	1	100.0%
Functions:	1	1	100.0%
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      // This file is part of INSTINCT, the INS Toolkit for Integrated
    
      // Navigation Concepts and Training by the Institute of Navigation of
    
      // the University of Stuttgart, Germany.
    
      //
    
      // This Source Code Form is subject to the terms of the Mozilla Public
    
      // License, v. 2.0. If a copy of the MPL was not distributed with this
    
      // file, You can obtain one at https://mozilla.org/MPL/2.0/.
    
      /// @file IRNSSEphemeris.hpp
    
      /// @brief IRNSS Ephemeris information
    
      /// @author P. Peitschat (Hiwi)
    
      /// @author T. Topp (topp@ins.uni-stuttgart.de)
    
      /// @date 2023-10-24
    
      #pragma once
    
      #include <bitset>
    
      #include "Navigation/GNSS/Satellite/internal/SatNavData.hpp"
    
      #include "Navigation/Time/InsTime.hpp"
    
      namespace NAV
    
      {
    
      /// @brief Broadcasted ephemeris message data
    
      /// @note See \cite IRNSS-SIS-ICD-1.1 IRNSS ICD, Table 11, p.19 and Table 12, p.20
    
      class IRNSSEphemeris final : public SatNavData
    
      {
    
        public:
    
          // #######################################################################################################
    
          //                                                Members
    
          // #######################################################################################################
    
          // ------------------------------------------ Time Parameters --------------------------------------------
    
          /// @brief Time of Clock
    
          const InsTime toc;
    
          /// @brief Time of Ephemeris
    
          const InsTime toe;
    
          /// @brief Issue of Data for Ephemeris and Clock
    
          ///
    
          /// 8-bit number which indicates the issue number of the data set.
    
          /// Provides the user with a convenient means of detecting any change in the ephemeris and clock parameters.
    
          ///
    
          /// The IODEC values can be found according to the following table:
    
          /// -----------------------------------------------------------------------------------------------------------------------------
    
          /// IODEC range      | Update   | Description
    
          /// -----------------------------------------------------------------------------------------------------------------------------
    
          /// 0 to 11(12 sets) | 2 hours  | Nominal set for current day, uplinked in advance with broadcast ephemeris and clock parameters
    
          /// 12 to 23         | 2 hours  | For update to nominal sets
    
          /// 24 to 29         | 4 hours  | For the ephemeris and clock parameters with update rate greater than 2 hours
    
          /// 30 to 75         | ----- reserved for future -----
    
          /// 76 to 159        | 2 hours  | During AutoNav mode of operation, IODEC values are in the range .
    
          /// 160 to 255       | < 30 min | For the ephemeris and clock parameters with update rate lesser than 30 minutes
    
          /// -----------------------------------------------------------------------------------------------------------------------------
    
          ///
    
          /// @note See \cite IRNSS-SIS-ICD-1.1 IRNSS ICD, ch. 6.2.1.3, p.29 f.
    
          const size_t IODEC;
    
          /// Polynomial coefficients for clock correction
    
          /// - a(0) bias [s]
    
          /// - a(1) drift [s/s]
    
          /// - a(2) drift rate (aging) [s/s^2]
    
          ///
    
          /// @note See \cite IRNSS-SIS-ICD-1.1 IRNSS ICD, ch. 6.2.1.2, p.29
    
          const std::array<double, 3> a;
    
          // --------------------------------------- Keplerian Parameters ------------------------------------------
    
          const double sqrt_A;  ///< Square root of the semi-major axis [m^1/2]
    
          const double e;       ///< Eccentricity [-]
    
          const double i_0;     ///< Inclination angle at reference time [rad]
    
          const double Omega_0; ///< Longitude of Ascending Node of Orbit Plane at Weekly Epoch [rad]
    
          const double omega;   ///< Argument of perigee [rad]
    
          const double M_0;     ///< Mean anomaly at reference time [rad]
    
          // -------------------------------------- Pertubation Parameters -----------------------------------------
    
          const double delta_n;   ///< Mean motion difference from computed value [rad/s]
    
          const double Omega_dot; ///< Rate of right ascension [rad/s]
    
          const double i_dot;     ///< Rate of inclination angle [rad/s]
    
          const double Cus;       ///< Amplitude of the sine harmonic correction term to the argument of latitude [rad]
    
          const double Cuc;       ///< Amplitude of the cosine harmonic correction term to the argument of latitude [rad]
    
          const double Cis;       ///< Amplitude of the sine harmonic correction term to the angle of inclination [rad]
    
          const double Cic;       ///< Amplitude of the cosine harmonic correction term to the angle of inclination [rad]
    
          const double Crs;       ///< Amplitude of the sine harmonic correction term to the orbit radius [m]
    
          const double Crc;       ///< Amplitude of the cosine harmonic correction term to the orbit radius [m]
    
          // ----------------------------------------------- Other -------------------------------------------------
    
          /// @brief SV accuracy [m]
    
          ///
    
          /// Derived from an URA index of the SV for the standard positioning service user.
    
          ///
    
          /// @note See \cite IRNSS-SIS-ICD-1.1 IRNSS ICD, ch. 6.2.1.4, p.30
    
          /// @note See \cite IS-GPS-200M GPS ICD, ch. 20.3.3.3.1.3, p.92ff
    
          const double svAccuracy;
    
          /// @brief SV health
    
          ///
    
          /// There are two one-bit health flags. Each one-bit health flag indicates the health
    
          /// of NAV data on L5 and S signals as follows:
    
          /// -----------------------------------------------------------------------
    
          /// Flag    | Value | Description
    
          /// -----------------------------------------------------------------------
    
          /// L5 flag |   0   | All navigation data on L5 SPS signal are OK
    
          ///         |   1   | Some or all navigation data on L5 SPS signal are bad
    
          /// -----------------------------------------------------------------------
    
          /// S flag  |   0   | All navigation data on S SPS signal are OK
    
          ///         |   1   | Some or all navigation data on S SPS signal are bad
    
          /// -----------------------------------------------------------------------
    
          ///
    
          /// @note See \cite IRNSS-SIS-ICD-1.1 IRNSS ICD, ch. 6.2.1.6, p.31
    
          const std::bitset<2> svHealth;
    
          /// @brief Total Group Delay
    
          /// @note See \cite IRNSS-SIS-ICD-1.1 IRNSS ICD, ch. 6.2.1.5, p.31
    
          const double T_GD;
    
          // #######################################################################################################
    
          //                                               Functions
    
          // #######################################################################################################
    
          /// @brief Constructor
    
          /// @param[in] toc Time the Clock information is calculated (Time of Clock)
    
          /// @param[in] toe Time the Orbit information is calculated (Time of Ephemeris)
    
          /// @param[in] IODEC Issue of Data for Ephemeris and Clock
    
          /// @param[in] a Polynomial coefficients for clock correction (a0 bias [s], a1 drift [s/s], a2 drift rate (aging) [s/s^2])
    
          /// @param[in] sqrt_A Square root of the semi-major axis [m^1/2]
    
          /// @param[in] e Eccentricity [-]
    
          /// @param[in] i_0 Inclination angle at reference time [rad]
    
          /// @param[in] Omega_0 Longitude of Ascending Node of Orbit Plane at Weekly Epoch [rad]
    
          /// @param[in] omega Argument of perigee [rad]
    
          /// @param[in] M_0 Mean anomaly at reference time [rad]
    
          /// @param[in] delta_n Mean motion difference from computed value [rad/s]
    
          /// @param[in] Omega_dot Rate of right ascension [rad/s]
    
          /// @param[in] i_dot Rate of inclination angle [rad/s]
    
          /// @param[in] Cus Amplitude of the sine harmonic correction term to the argument of latitude [rad]
    
          /// @param[in] Cuc Amplitude of the cosine harmonic correction term to the argument of latitude [rad]
    
          /// @param[in] Cis Amplitude of the sine harmonic correction term to the angle of inclination [rad]
    
          /// @param[in] Cic Amplitude of the cosine harmonic correction term to the angle of inclination [rad]
    
          /// @param[in] Crs Amplitude of the sine harmonic correction term to the orbit radius [m]
    
          /// @param[in] Crc Amplitude of the cosine harmonic correction term to the orbit radius [m]
    
          /// @param[in] svAccuracy SV accuracy [m]
    
          /// @param[in] svHealth Signal Health
    
          /// @param[in] T_GD Total Group Delay [s]
    
          IRNSSEphemeris(const InsTime& toc, const InsTime& toe,
    
                         const size_t& IODEC,
    
                         const std::array<double, 3>& a,
    
                         const double& sqrt_A, const double& e, const double& i_0, const double& Omega_0, const double& omega, const double& M_0,
    
                         const double& delta_n, const double& Omega_dot, const double& i_dot, const double& Cus, const double& Cuc,
    
                         const double& Cis, const double& Cic, const double& Crs, const double& Crc,
    
                         const double& svAccuracy, uint8_t svHealth,
    
                         const double& T_GD);
    
      #ifdef TESTING
    
          /// @brief Constructor for pasting raw data from Nav files
    
          /// @param[in] year Time of Clock year
    
          /// @param[in] month Time of Clock month
    
          /// @param[in] day Time of Clock day
    
          /// @param[in] hour Time of Clock hour
    
          /// @param[in] minute Time of Clock minute
    
          /// @param[in] second Time of Clock second
    
          /// @param[in] svClockBias Clock correction a(0) bias [s]
    
          /// @param[in] svClockDrift Clock correction a(1) drift [s/s]
    
          /// @param[in] svClockDriftRate Clock correction a(2) drift rate (aging) [s/s^2]
    
          /// @param[in] IODEC Issue of Data for Ephemeris and Clock
    
          /// @param[in] Crs Amplitude of the sine harmonic correction term to the orbit radius [m]
    
          /// @param[in] delta_n Mean motion difference from computed value [rad/s]
    
          /// @param[in] M_0 Mean anomaly at reference time [rad]
    
          /// @param[in] Cuc Amplitude of the cosine harmonic correction term to the argument of latitude [rad]
    
          /// @param[in] e Eccentricity [-]
    
          /// @param[in] Cus Amplitude of the sine harmonic correction term to the argument of latitude [rad]
    
          /// @param[in] sqrt_A Square root of the semi-major axis [m^1/2]
    
          /// @param[in] Toe Time of Ephemeris
    
          /// @param[in] Cic Amplitude of the cosine harmonic correction term to the angle of inclination [rad]
    
          /// @param[in] Omega_0 Longitude of Ascending Node of Orbit Plane at Weekly Epoch [rad]
    
          /// @param[in] Cis Amplitude of the sine harmonic correction term to the angle of inclination [rad]
    
          /// @param[in] i_0 Inclination angle at reference time [rad]
    
          /// @param[in] Crc Amplitude of the cosine harmonic correction term to the orbit radius [m]
    
          /// @param[in] omega Argument of perigee [rad]
    
          /// @param[in] Omega_dot Rate of right ascension [rad/s]
    
          /// @param[in] i_dot Rate of inclination angle [rad/s]
    
          /// @param[in] spare1 Spare data
    
          /// @param[in] IRNWeek IRN Week to go with Toe
    
          /// @param[in] spare2 Spare data
    
          /// @param[in] svAccuracy SV accuracy [m]
    
          /// @param[in] svHealth SV health
    
          /// @param[in] T_GD Total Group Delay [s]
    
          /// @param[in] spare3 Spare data
    
          /// @param[in] TransmissionTimeOfMessage Transmission time of message [s of IRNSS week]
    
          /// @param[in] spare4 Spare data
    
          /// @param[in] spare5 Spare data
    
          /// @param[in] spare6 Spare data
    
          IRNSSEphemeris(int32_t year, int32_t month, int32_t day, int32_t hour, int32_t minute, double second, double svClockBias, double svClockDrift, double svClockDriftRate,
    
                         double IODEC, double Crs, double delta_n, double M_0,
    
                         double Cuc, double e, double Cus, double sqrt_A,
    
                         double Toe, double Cic, double Omega_0, double Cis,
    
                         double i_0, double Crc, double omega, double Omega_dot,
    
                         double i_dot, double spare1, double IRNWeek, double spare2,
    
                         double svAccuracy, double svHealth, double T_GD, double spare3,
    
                         double TransmissionTimeOfMessage, double spare4 = 0.0, double spare5 = 0.0, double spare6 = 0.0);
    
      #endif
    
          /// @brief Destructor
    
      4
          ~IRNSSEphemeris() final = default;
    
          /// @brief Copy constructor
    
          IRNSSEphemeris(const IRNSSEphemeris&) = default;
    
          /// @brief Move constructor
    
          IRNSSEphemeris(IRNSSEphemeris&&) = default;
    
          /// @brief Copy assignment operator
    
          IRNSSEphemeris& operator=(const IRNSSEphemeris&) = delete;
    
          /// @brief Move assignment operator
    
          IRNSSEphemeris& operator=(IRNSSEphemeris&&) = delete;
    
          /// @brief Calculates the Variance of the satellite position in [m^2]
    
          [[nodiscard]] double calcSatellitePositionVariance() const final;
    
          /// @brief Calculates clock bias and drift of the satellite
    
          /// @param[in] recvTime Receive time of the signal
    
          /// @param[in] dist Distance between receiver and satellite (normally the pseudorange) [m]
    
          /// @param[in] freq Signal Frequency
    
          /// @note See \cite IRNSS-SIS-ICD-1.1 IRNSS ICD, Appendix A, p.43
    
          [[nodiscard]] Corrections calcClockCorrections(const InsTime& recvTime, double dist, const Frequency& freq) const final;
    
          /// @brief Checks whether the signal is healthy
    
          [[nodiscard]] bool isHealthy() const final;
    
        private:
    
          /// @brief Calculates position, velocity and acceleration of the satellite at transmission time
    
          /// @param[in] transTime Transmit time of the signal
    
          /// @param[in] calc Flags which determine what should be calculated and returned
    
          /// @note See \cite IRNSS-SIS-ICD-1.1 IRNSS ICD, Appendix B, p.45 ff.
    
          /// @note See \cite IS-GPS-200M IS-GPS-200, ch. 20.3.3.4.3.1 Table 20-IV p.106-109
    
          [[nodiscard]] PosVelAccel calcSatelliteData(const InsTime& transTime, Orbit::Calc calc) const final;
    
      };
    
      } // namespace NAV

Line	Exec	Source
1		// This file is part of INSTINCT, the INS Toolkit for Integrated
2		// Navigation Concepts and Training by the Institute of Navigation of
3		// the University of Stuttgart, Germany.
4		//
5		// This Source Code Form is subject to the terms of the Mozilla Public
6		// License, v. 2.0. If a copy of the MPL was not distributed with this
7		// file, You can obtain one at https://mozilla.org/MPL/2.0/.
8
9		/// @file IRNSSEphemeris.hpp
10		/// @brief IRNSS Ephemeris information
11		/// @author P. Peitschat (Hiwi)
12		/// @author T. Topp (topp@ins.uni-stuttgart.de)
13		/// @date 2023-10-24
14
15		#pragma once
16
17		#include <bitset>
18
19		#include "Navigation/GNSS/Satellite/internal/SatNavData.hpp"
20
21		#include "Navigation/Time/InsTime.hpp"
22
23		namespace NAV
24		{
25
26		/// @brief Broadcasted ephemeris message data
27		/// @note See \cite IRNSS-SIS-ICD-1.1 IRNSS ICD, Table 11, p.19 and Table 12, p.20
28		class IRNSSEphemeris final : public SatNavData
29		{
30		public:
31		// #######################################################################################################
32		// Members
33		// #######################################################################################################
34
35		// ------------------------------------------ Time Parameters --------------------------------------------
36
37		/// @brief Time of Clock
38		const InsTime toc;
39
40		/// @brief Time of Ephemeris
41		const InsTime toe;
42
43		/// @brief Issue of Data for Ephemeris and Clock
44		///
45		/// 8-bit number which indicates the issue number of the data set.
46		/// Provides the user with a convenient means of detecting any change in the ephemeris and clock parameters.
47		///
48		/// The IODEC values can be found according to the following table:
49		/// -----------------------------------------------------------------------------------------------------------------------------
50		/// IODEC range \| Update \| Description
51		/// -----------------------------------------------------------------------------------------------------------------------------
52		/// 0 to 11(12 sets) \| 2 hours \| Nominal set for current day, uplinked in advance with broadcast ephemeris and clock parameters
53		/// 12 to 23 \| 2 hours \| For update to nominal sets
54		/// 24 to 29 \| 4 hours \| For the ephemeris and clock parameters with update rate greater than 2 hours
55		/// 30 to 75 \| ----- reserved for future -----
56		/// 76 to 159 \| 2 hours \| During AutoNav mode of operation, IODEC values are in the range .
57		/// 160 to 255 \| < 30 min \| For the ephemeris and clock parameters with update rate lesser than 30 minutes
58		/// -----------------------------------------------------------------------------------------------------------------------------
59
60		///
61		/// @note See \cite IRNSS-SIS-ICD-1.1 IRNSS ICD, ch. 6.2.1.3, p.29 f.
62		const size_t IODEC;
63
64		/// Polynomial coefficients for clock correction
65		/// - a(0) bias [s]
66		/// - a(1) drift [s/s]
67		/// - a(2) drift rate (aging) [s/s^2]
68		///
69		/// @note See \cite IRNSS-SIS-ICD-1.1 IRNSS ICD, ch. 6.2.1.2, p.29
70		const std::array<double, 3> a;
71
72		// --------------------------------------- Keplerian Parameters ------------------------------------------
73
74		const double sqrt_A; ///< Square root of the semi-major axis [m^1/2]
75		const double e; ///< Eccentricity [-]
76		const double i_0; ///< Inclination angle at reference time [rad]
77		const double Omega_0; ///< Longitude of Ascending Node of Orbit Plane at Weekly Epoch [rad]
78		const double omega; ///< Argument of perigee [rad]
79		const double M_0; ///< Mean anomaly at reference time [rad]
80
81		// -------------------------------------- Pertubation Parameters -----------------------------------------
82
83		const double delta_n; ///< Mean motion difference from computed value [rad/s]
84		const double Omega_dot; ///< Rate of right ascension [rad/s]
85		const double i_dot; ///< Rate of inclination angle [rad/s]
86		const double Cus; ///< Amplitude of the sine harmonic correction term to the argument of latitude [rad]
87		const double Cuc; ///< Amplitude of the cosine harmonic correction term to the argument of latitude [rad]
88		const double Cis; ///< Amplitude of the sine harmonic correction term to the angle of inclination [rad]
89		const double Cic; ///< Amplitude of the cosine harmonic correction term to the angle of inclination [rad]
90		const double Crs; ///< Amplitude of the sine harmonic correction term to the orbit radius [m]
91		const double Crc; ///< Amplitude of the cosine harmonic correction term to the orbit radius [m]
92
93		// ----------------------------------------------- Other -------------------------------------------------
94
95		/// @brief SV accuracy [m]
96		///
97		/// Derived from an URA index of the SV for the standard positioning service user.
98		///
99		/// @note See \cite IRNSS-SIS-ICD-1.1 IRNSS ICD, ch. 6.2.1.4, p.30
100		/// @note See \cite IS-GPS-200M GPS ICD, ch. 20.3.3.3.1.3, p.92ff
101		const double svAccuracy;
102
103		/// @brief SV health
104		///
105		/// There are two one-bit health flags. Each one-bit health flag indicates the health
106		/// of NAV data on L5 and S signals as follows:
107		/// -----------------------------------------------------------------------
108		/// Flag \| Value \| Description
109		/// -----------------------------------------------------------------------
110		/// L5 flag \| 0 \| All navigation data on L5 SPS signal are OK
111		/// \| 1 \| Some or all navigation data on L5 SPS signal are bad
112		/// -----------------------------------------------------------------------
113		/// S flag \| 0 \| All navigation data on S SPS signal are OK
114		/// \| 1 \| Some or all navigation data on S SPS signal are bad
115		/// -----------------------------------------------------------------------
116		///
117		/// @note See \cite IRNSS-SIS-ICD-1.1 IRNSS ICD, ch. 6.2.1.6, p.31
118		const std::bitset<2> svHealth;
119
120		/// @brief Total Group Delay
121		/// @note See \cite IRNSS-SIS-ICD-1.1 IRNSS ICD, ch. 6.2.1.5, p.31
122		const double T_GD;
123
124		// #######################################################################################################
125		// Functions
126		// #######################################################################################################
127
128		/// @brief Constructor
129		/// @param[in] toc Time the Clock information is calculated (Time of Clock)
130		/// @param[in] toe Time the Orbit information is calculated (Time of Ephemeris)
131		/// @param[in] IODEC Issue of Data for Ephemeris and Clock
132		/// @param[in] a Polynomial coefficients for clock correction (a0 bias [s], a1 drift [s/s], a2 drift rate (aging) [s/s^2])
133		/// @param[in] sqrt_A Square root of the semi-major axis [m^1/2]
134		/// @param[in] e Eccentricity [-]
135		/// @param[in] i_0 Inclination angle at reference time [rad]
136		/// @param[in] Omega_0 Longitude of Ascending Node of Orbit Plane at Weekly Epoch [rad]
137		/// @param[in] omega Argument of perigee [rad]
138		/// @param[in] M_0 Mean anomaly at reference time [rad]
139		/// @param[in] delta_n Mean motion difference from computed value [rad/s]
140		/// @param[in] Omega_dot Rate of right ascension [rad/s]
141		/// @param[in] i_dot Rate of inclination angle [rad/s]
142		/// @param[in] Cus Amplitude of the sine harmonic correction term to the argument of latitude [rad]
143		/// @param[in] Cuc Amplitude of the cosine harmonic correction term to the argument of latitude [rad]
144		/// @param[in] Cis Amplitude of the sine harmonic correction term to the angle of inclination [rad]
145		/// @param[in] Cic Amplitude of the cosine harmonic correction term to the angle of inclination [rad]
146		/// @param[in] Crs Amplitude of the sine harmonic correction term to the orbit radius [m]
147		/// @param[in] Crc Amplitude of the cosine harmonic correction term to the orbit radius [m]
148		/// @param[in] svAccuracy SV accuracy [m]
149		/// @param[in] svHealth Signal Health
150		/// @param[in] T_GD Total Group Delay [s]
151		IRNSSEphemeris(const InsTime& toc, const InsTime& toe,
152		const size_t& IODEC,
153		const std::array<double, 3>& a,
154		const double& sqrt_A, const double& e, const double& i_0, const double& Omega_0, const double& omega, const double& M_0,
155		const double& delta_n, const double& Omega_dot, const double& i_dot, const double& Cus, const double& Cuc,
156		const double& Cis, const double& Cic, const double& Crs, const double& Crc,
157		const double& svAccuracy, uint8_t svHealth,
158		const double& T_GD);
159
160		#ifdef TESTING
161		/// @brief Constructor for pasting raw data from Nav files
162		/// @param[in] year Time of Clock year
163		/// @param[in] month Time of Clock month
164		/// @param[in] day Time of Clock day
165		/// @param[in] hour Time of Clock hour
166		/// @param[in] minute Time of Clock minute
167		/// @param[in] second Time of Clock second
168		/// @param[in] svClockBias Clock correction a(0) bias [s]
169		/// @param[in] svClockDrift Clock correction a(1) drift [s/s]
170		/// @param[in] svClockDriftRate Clock correction a(2) drift rate (aging) [s/s^2]
171		/// @param[in] IODEC Issue of Data for Ephemeris and Clock
172		/// @param[in] Crs Amplitude of the sine harmonic correction term to the orbit radius [m]
173		/// @param[in] delta_n Mean motion difference from computed value [rad/s]
174		/// @param[in] M_0 Mean anomaly at reference time [rad]
175		/// @param[in] Cuc Amplitude of the cosine harmonic correction term to the argument of latitude [rad]
176		/// @param[in] e Eccentricity [-]
177		/// @param[in] Cus Amplitude of the sine harmonic correction term to the argument of latitude [rad]
178		/// @param[in] sqrt_A Square root of the semi-major axis [m^1/2]
179		/// @param[in] Toe Time of Ephemeris
180		/// @param[in] Cic Amplitude of the cosine harmonic correction term to the angle of inclination [rad]
181		/// @param[in] Omega_0 Longitude of Ascending Node of Orbit Plane at Weekly Epoch [rad]
182		/// @param[in] Cis Amplitude of the sine harmonic correction term to the angle of inclination [rad]
183		/// @param[in] i_0 Inclination angle at reference time [rad]
184		/// @param[in] Crc Amplitude of the cosine harmonic correction term to the orbit radius [m]
185		/// @param[in] omega Argument of perigee [rad]
186		/// @param[in] Omega_dot Rate of right ascension [rad/s]
187		/// @param[in] i_dot Rate of inclination angle [rad/s]
188		/// @param[in] spare1 Spare data
189		/// @param[in] IRNWeek IRN Week to go with Toe
190		/// @param[in] spare2 Spare data
191		/// @param[in] svAccuracy SV accuracy [m]
192		/// @param[in] svHealth SV health
193		/// @param[in] T_GD Total Group Delay [s]
194		/// @param[in] spare3 Spare data
195		/// @param[in] TransmissionTimeOfMessage Transmission time of message [s of IRNSS week]
196		/// @param[in] spare4 Spare data
197		/// @param[in] spare5 Spare data
198		/// @param[in] spare6 Spare data
199		IRNSSEphemeris(int32_t year, int32_t month, int32_t day, int32_t hour, int32_t minute, double second, double svClockBias, double svClockDrift, double svClockDriftRate,
200		double IODEC, double Crs, double delta_n, double M_0,
201		double Cuc, double e, double Cus, double sqrt_A,
202		double Toe, double Cic, double Omega_0, double Cis,
203		double i_0, double Crc, double omega, double Omega_dot,
204		double i_dot, double spare1, double IRNWeek, double spare2,
205		double svAccuracy, double svHealth, double T_GD, double spare3,
206		double TransmissionTimeOfMessage, double spare4 = 0.0, double spare5 = 0.0, double spare6 = 0.0);
207		#endif
208
209		/// @brief Destructor
210	4	~IRNSSEphemeris() final = default;
211		/// @brief Copy constructor
212		IRNSSEphemeris(const IRNSSEphemeris&) = default;
213		/// @brief Move constructor
214		IRNSSEphemeris(IRNSSEphemeris&&) = default;
215		/// @brief Copy assignment operator
216		IRNSSEphemeris& operator=(const IRNSSEphemeris&) = delete;
217		/// @brief Move assignment operator
218		IRNSSEphemeris& operator=(IRNSSEphemeris&&) = delete;
219
220		/// @brief Calculates the Variance of the satellite position in [m^2]
221		[[nodiscard]] double calcSatellitePositionVariance() const final;
222
223		/// @brief Calculates clock bias and drift of the satellite
224		/// @param[in] recvTime Receive time of the signal
225		/// @param[in] dist Distance between receiver and satellite (normally the pseudorange) [m]
226		/// @param[in] freq Signal Frequency
227		/// @note See \cite IRNSS-SIS-ICD-1.1 IRNSS ICD, Appendix A, p.43
228		[[nodiscard]] Corrections calcClockCorrections(const InsTime& recvTime, double dist, const Frequency& freq) const final;
229
230		/// @brief Checks whether the signal is healthy
231		[[nodiscard]] bool isHealthy() const final;
232
233		private:
234		/// @brief Calculates position, velocity and acceleration of the satellite at transmission time
235		/// @param[in] transTime Transmit time of the signal
236		/// @param[in] calc Flags which determine what should be calculated and returned
237		/// @note See \cite IRNSS-SIS-ICD-1.1 IRNSS ICD, Appendix B, p.45 ff.
238		/// @note See \cite IS-GPS-200M IS-GPS-200, ch. 20.3.3.4.3.1 Table 20-IV p.106-109
239		[[nodiscard]] PosVelAccel calcSatelliteData(const InsTime& transTime, Orbit::Calc calc) const final;
240		};
241
242		} // namespace NAV
243