Add gnss namespace

src/dynamics/orbit/encke_orbit_propagation.cpp

@@ -90,8 +90,8 @@ void EnckeOrbitPropagation::Initialize(double current_time_jd, math::Vector<3> r
   // reference orbit
   reference_position_i_m_ = reference_position_i_m;
   reference_velocity_i_m_s_ = reference_velocity_i_m_s;
-  OrbitalElements oe_ref(gravity_constant_m3_s2_, current_time_jd, reference_position_i_m, reference_velocity_i_m_s);
-  reference_kepler_orbit = KeplerOrbit(gravity_constant_m3_s2_, oe_ref);
+  orbit::OrbitalElements oe_ref(gravity_constant_m3_s2_, current_time_jd, reference_position_i_m, reference_velocity_i_m_s);
+  reference_kepler_orbit = orbit::KeplerOrbit(gravity_constant_m3_s2_, oe_ref);
 
   // difference orbit
   difference_position_i_m_.FillUp(0.0);

src/dynamics/orbit/encke_orbit_propagation.hpp

@@ -65,7 +65,7 @@ class EnckeOrbitPropagation : public Orbit, public math::OrdinaryDifferentialEqu
   // reference orbit
   math::Vector<3> reference_position_i_m_;    //!< Reference orbit position in the inertial frame [m]
   math::Vector<3> reference_velocity_i_m_s_;  //!< Reference orbit velocity in the inertial frame [m/s]
-  KeplerOrbit reference_kepler_orbit;         //!< Reference Kepler orbital element
+  orbit::KeplerOrbit reference_kepler_orbit;  //!< Reference Kepler orbital element
 
   // difference orbit
   math::Vector<3> difference_position_i_m_;    //!< Difference orbit position in the inertial frame [m]

src/dynamics/orbit/initialize_orbit.cpp

@@ -46,8 +46,8 @@ Orbit* InitOrbit(const CelestialInformation* celestial_information, std::string
     // initialize orbit for relative dynamics of formation flying
     RelativeOrbit::RelativeOrbitUpdateMethod update_method =
         (RelativeOrbit::RelativeOrbitUpdateMethod)(conf.ReadInt(section_, "relative_orbit_update_method"));
-    RelativeOrbitModel relative_dynamics_model_type = (RelativeOrbitModel)(conf.ReadInt(section_, "relative_dynamics_model_type"));
-    StmModel stm_model_type = (StmModel)(conf.ReadInt(section_, "stm_model_type"));
+    orbit::RelativeOrbitModel relative_dynamics_model_type = (orbit::RelativeOrbitModel)(conf.ReadInt(section_, "relative_dynamics_model_type"));
+    orbit::StmModel stm_model_type = (orbit::StmModel)(conf.ReadInt(section_, "stm_model_type"));
 
     math::Vector<3> init_relative_position_lvlh;
     conf.ReadVector<3>(section_, "initial_relative_position_lvlh_m", init_relative_position_lvlh);
@@ -62,15 +62,15 @@ Orbit* InitOrbit(const CelestialInformation* celestial_information, std::string
                               init_relative_velocity_lvlh, update_method, relative_dynamics_model_type, stm_model_type, relative_information);
   } else if (propagate_mode == "KEPLER") {
     // initialize orbit for Kepler propagation
-    OrbitalElements oe;
+    orbit::OrbitalElements oe;
     // TODO: init_mode_kepler should be removed in the next major update
     if (initialize_mode == OrbitInitializeMode::kInertialPositionAndVelocity) {
       // initialize with position and velocity
       math::Vector<3> init_pos_m;
       conf.ReadVector<3>(section_, "initial_position_i_m", init_pos_m);
       math::Vector<3> init_vel_m_s;
       conf.ReadVector<3>(section_, "initial_velocity_i_m_s", init_vel_m_s);
-      oe = OrbitalElements(gravity_constant_m3_s2, current_time_jd, init_pos_m, init_vel_m_s);
+      oe = orbit::OrbitalElements(gravity_constant_m3_s2, current_time_jd, init_pos_m, init_vel_m_s);
     } else {
       // initialize with orbital elements
       double semi_major_axis_m = conf.ReadDouble(section_, "semi_major_axis_m");
@@ -79,9 +79,9 @@ Orbit* InitOrbit(const CelestialInformation* celestial_information, std::string
       double raan_rad = conf.ReadDouble(section_, "raan_rad");
       double arg_perigee_rad = conf.ReadDouble(section_, "argument_of_perigee_rad");
       double epoch_jday = conf.ReadDouble(section_, "epoch_jday");
-      oe = OrbitalElements(epoch_jday, semi_major_axis_m, eccentricity, inclination_rad, raan_rad, arg_perigee_rad);
+      oe = orbit::OrbitalElements(epoch_jday, semi_major_axis_m, eccentricity, inclination_rad, raan_rad, arg_perigee_rad);
     }
-    KeplerOrbit kepler_orbit(gravity_constant_m3_s2, oe);
+    orbit::KeplerOrbit kepler_orbit(gravity_constant_m3_s2, oe);
     orbit = new KeplerOrbitPropagation(celestial_information, current_time_jd, kepler_orbit);
   } else if (propagate_mode == "ENCKE") {
     // initialize orbit for Encke's method
@@ -130,8 +130,8 @@ math::Vector<6> InitializePosVel(std::string initialize_file, double current_tim
     double raan_rad = conf.ReadDouble(section_, "raan_rad");
     double arg_perigee_rad = conf.ReadDouble(section_, "argument_of_perigee_rad");
     double epoch_jday = conf.ReadDouble(section_, "epoch_jday");
-    OrbitalElements oe(epoch_jday, semi_major_axis_m, eccentricity, inclination_rad, raan_rad, arg_perigee_rad);
-    KeplerOrbit kepler_orbit(gravity_constant_m3_s2, oe);
+    orbit::OrbitalElements oe(epoch_jday, semi_major_axis_m, eccentricity, inclination_rad, raan_rad, arg_perigee_rad);
+    orbit::KeplerOrbit kepler_orbit(gravity_constant_m3_s2, oe);
 
     kepler_orbit.CalcOrbit(current_time_jd);
     position_i_m = kepler_orbit.GetPosition_i_m();

src/dynamics/orbit/kepler_orbit_propagation.hpp

@@ -13,7 +13,7 @@
  * @class KeplerOrbitPropagation
  * @brief Class to propagate spacecraft orbit with Kepler equation
  */
-class KeplerOrbitPropagation : public Orbit, public KeplerOrbit {
+class KeplerOrbitPropagation : public Orbit, public orbit::KeplerOrbit {
  public:
   // Initialize with orbital elements
   /**
@@ -23,7 +23,7 @@ class KeplerOrbitPropagation : public Orbit, public KeplerOrbit {
    * @param [in] current_time_jd: Current Julian day [day]
    * @param [in] kepler_orbit: Kepler orbit
    */
-  KeplerOrbitPropagation(const CelestialInformation* celestial_information, const double current_time_jd, KeplerOrbit kepler_orbit);
+  KeplerOrbitPropagation(const CelestialInformation* celestial_information, const double current_time_jd, orbit::KeplerOrbit kepler_orbit);
   /**
    * @fn ~KeplerOrbitPropagation
    * @brief Destructor

src/dynamics/orbit/relative_orbit.cpp

@@ -10,8 +10,8 @@
 
 RelativeOrbit::RelativeOrbit(const CelestialInformation* celestial_information, double gravity_constant_m3_s2, double time_step_s,
                              int reference_spacecraft_id, math::Vector<3> relative_position_lvlh_m, math::Vector<3> relative_velocity_lvlh_m_s,
-                             RelativeOrbitUpdateMethod update_method, RelativeOrbitModel relative_dynamics_model_type, StmModel stm_model_type,
-                             RelativeInformation* relative_information)
+                             RelativeOrbitUpdateMethod update_method, orbit::RelativeOrbitModel relative_dynamics_model_type,
+                             orbit::StmModel stm_model_type, RelativeInformation* relative_information)
     : Orbit(celestial_information),
       math::OrdinaryDifferentialEquation<6>(time_step_s),
       gravity_constant_m3_s2_(gravity_constant_m3_s2),
@@ -66,12 +66,12 @@ void RelativeOrbit::InitializeState(math::Vector<3> relative_position_lvlh_m, ma
   TransformEcefToGeodetic();
 }
 
-void RelativeOrbit::CalculateSystemMatrix(RelativeOrbitModel relative_dynamics_model_type, const Orbit* reference_sat_orbit,
+void RelativeOrbit::CalculateSystemMatrix(orbit::RelativeOrbitModel relative_dynamics_model_type, const Orbit* reference_sat_orbit,
                                           double gravity_constant_m3_s2) {
   switch (relative_dynamics_model_type) {
-    case RelativeOrbitModel::kHill: {
+    case orbit::RelativeOrbitModel::kHill: {
       double reference_sat_orbit_radius = reference_sat_orbit->GetPosition_i_m().CalcNorm();
-      system_matrix_ = CalcHillSystemMatrix(reference_sat_orbit_radius, gravity_constant_m3_s2);
+      system_matrix_ = orbit::CalcHillSystemMatrix(reference_sat_orbit_radius, gravity_constant_m3_s2);
     }
     default: {
       // NOT REACHED
@@ -80,11 +80,12 @@ void RelativeOrbit::CalculateSystemMatrix(RelativeOrbitModel relative_dynamics_m
   }
 }
 
-void RelativeOrbit::CalculateStm(StmModel stm_model_type, const Orbit* reference_sat_orbit, double gravity_constant_m3_s2, double elapsed_sec) {
+void RelativeOrbit::CalculateStm(orbit::StmModel stm_model_type, const Orbit* reference_sat_orbit, double gravity_constant_m3_s2,
+                                 double elapsed_sec) {
   switch (stm_model_type) {
-    case StmModel::kHcw: {
+    case orbit::StmModel::kHcw: {
       double reference_sat_orbit_radius = reference_sat_orbit->GetPosition_i_m().CalcNorm();
-      stm_ = CalcHcwStm(reference_sat_orbit_radius, gravity_constant_m3_s2, elapsed_sec);
+      stm_ = orbit::CalcHcwStm(reference_sat_orbit_radius, gravity_constant_m3_s2, elapsed_sec);
     }
     default: {
       // NOT REACHED

src/dynamics/orbit/relative_orbit.hpp

@@ -41,7 +41,7 @@ class RelativeOrbit : public Orbit, public math::OrdinaryDifferentialEquation<6>
    */
   RelativeOrbit(const CelestialInformation* celestial_information, double gravity_constant_m3_s2, double time_step_s, int reference_spacecraft_id,
                 math::Vector<3> relative_position_lvlh_m, math::Vector<3> relative_velocity_lvlh_m_s, RelativeOrbitUpdateMethod update_method,
-                RelativeOrbitModel relative_dynamics_model_type, StmModel stm_model_type, RelativeInformation* relative_information);
+                orbit::RelativeOrbitModel relative_dynamics_model_type, orbit::StmModel stm_model_type, RelativeInformation* relative_information);
   /**
    * @fn ~RelativeOrbit
    * @brief Destructor
@@ -80,10 +80,10 @@ class RelativeOrbit : public Orbit, public math::OrdinaryDifferentialEquation<6>
   math::Vector<3> relative_position_lvlh_m_;    //!< Relative position in the LVLH frame
   math::Vector<3> relative_velocity_lvlh_m_s_;  //!< Relative velocity in the LVLH frame
 
-  RelativeOrbitUpdateMethod update_method_;          //!< Update method
-  RelativeOrbitModel relative_dynamics_model_type_;  //!< Relative dynamics model type
-  StmModel stm_model_type_;                          //!< State Transition Matrix model type
-  RelativeInformation* relative_information_;        //!< Relative information
+  RelativeOrbitUpdateMethod update_method_;                 //!< Update method
+  orbit::RelativeOrbitModel relative_dynamics_model_type_;  //!< Relative dynamics model type
+  orbit::StmModel stm_model_type_;                          //!< State Transition Matrix model type
+  RelativeInformation* relative_information_;               //!< Relative information
 
   /**
    * @fn InitializeState
@@ -102,7 +102,7 @@ class RelativeOrbit : public Orbit, public math::OrdinaryDifferentialEquation<6>
    * @param [in] reference_sat_orbit: Orbit information of reference satellite
    * @param [in] gravity_constant_m3_s2: Gravity constant of the center body [m3/s2]
    */
-  void CalculateSystemMatrix(RelativeOrbitModel relative_dynamics_model_type, const Orbit* reference_sat_orbit, double gravity_constant_m3_s2);
+  void CalculateSystemMatrix(orbit::RelativeOrbitModel relative_dynamics_model_type, const Orbit* reference_sat_orbit, double gravity_constant_m3_s2);
   /**
    * @fn CalculateStm
    * @brief Calculate State Transition Matrix
@@ -111,7 +111,7 @@ class RelativeOrbit : public Orbit, public math::OrdinaryDifferentialEquation<6>
    * @param [in] gravity_constant_m3_s2: Gravity constant of the center body [m3/s2]
    * @param [in] elapsed_sec: Elapsed time [sec]
    */
-  void CalculateStm(StmModel stm_model_type, const Orbit* reference_sat_orbit, double gravity_constant_m3_s2, double elapsed_sec);
+  void CalculateStm(orbit::StmModel stm_model_type, const Orbit* reference_sat_orbit, double gravity_constant_m3_s2, double elapsed_sec);
   /**
    * @fn PropagateRk4
    * @brief Propagate relative orbit with RK4

src/environment/global/gnss_satellites.cpp

@@ -15,6 +15,8 @@
 #include "setting_file_reader/initialize_file_access.hpp"
 #include "utilities/macros.hpp"
 
+using namespace gnss;
+
 const size_t kNumberOfInterpolation = 9;
 
 void GnssSatellites::Initialize(const std::vector<Sp3FileReader>& sp3_files, const EpochTime start_time) {
@@ -38,7 +40,7 @@ void GnssSatellites::Initialize(const std::vector<Sp3FileReader>& sp3_files, con
   reference_time_ = EpochTime(initial_sp3_file.GetEpochData(reference_interpolation_id_));
 
   // Initialize orbit
-  orbit_.assign(number_of_calculated_gnss_satellites_, InterpolationOrbit(kNumberOfInterpolation));
+  orbit_.assign(number_of_calculated_gnss_satellites_, orbit::InterpolationOrbit(kNumberOfInterpolation));
 
   // Initialize clock
   std::vector<double> temp;

src/environment/global/gnss_satellites.hpp

@@ -54,7 +54,7 @@ class GnssSatellites : public ILoggable {
    * @param [in] sp3_files: List of SP3 files
    * @param [in] start_time: The simulation start time
    */
-  void Initialize(const std::vector<Sp3FileReader>& sp3_files, const EpochTime start_time);
+  void Initialize(const std::vector<gnss::Sp3FileReader>& sp3_files, const EpochTime start_time);
 
   /**
    * @fn IsCalcEnabled
@@ -113,15 +113,15 @@ class GnssSatellites : public ILoggable {
  private:
   bool is_calc_enabled_ = false;  //!< Flag to manage the GNSS satellite position calculation
 
-  std::vector<Sp3FileReader> sp3_files_;         //!< List of SP3 files
+  std::vector<gnss::Sp3FileReader> sp3_files_;   //!< List of SP3 files
   size_t number_of_calculated_gnss_satellites_;  //!< Number of calculated GNSS satellites
   size_t sp3_file_id_;                           //!< Current SP3 file ID
   EpochTime reference_time_;                     //!< Reference start time of the SP3 handling
   size_t reference_interpolation_id_ = 0;        //!< Reference epoch ID of the interpolation
   EpochTime current_epoch_time_;                 //!< The last updated time
 
-  std::vector<InterpolationOrbit> orbit_;   //!< GNSS satellite orbit with interpolation
-  std::vector<math::Interpolation> clock_;  //!< GNSS satellite clock offset with interpolation
+  std::vector<orbit::InterpolationOrbit> orbit_;  //!< GNSS satellite orbit with interpolation
+  std::vector<math::Interpolation> clock_;        //!< GNSS satellite clock offset with interpolation
 
   // References
   const EarthRotation& earth_rotation_;  //!< Earth rotation
@@ -133,7 +133,7 @@ class GnssSatellites : public ILoggable {
    * @param [in] current_time: Target time
    * @return true means no error, false means the time argument is out of range
    */
-  bool GetCurrentSp3File(Sp3FileReader& current_sp3_file, const EpochTime current_time);
+  bool GetCurrentSp3File(gnss::Sp3FileReader& current_sp3_file, const EpochTime current_time);
 
   /**
    * @fn UpdateInterpolationInformation

src/math_physics/gnss/antex_file_reader.cpp

@@ -10,6 +10,8 @@
 #include <iostream>
 #include <math_physics/gnss/gnss_satellite_number.hpp>
 
+namespace gnss {
+
 #define ANTEX_LINE_TYPE_POSITION (60)
 
 AntexGridDefinition::AntexGridDefinition(const double zenith_start_angle_deg, const double zenith_end_angle_deg, const double zenith_step_angle_deg,
@@ -196,3 +198,5 @@ DateTime AntexFileReader::ReadDateTime(std::string line) {
   sscanf(line.c_str(), "%zu %2zu %2zu %2zu %2zu %10lf", &year, &month, &day, &hour, &minute, &second);
   return DateTime(year, month, day, hour, minute, second);
 }
+
+}  // namespace gnss

src/math_physics/gnss/antex_file_reader.hpp

@@ -16,6 +16,8 @@
 #include <string>
 #include <vector>
 
+namespace gnss {
+
 /**
  * @class AntexGridDefinition
  * @brief grid data definition in ANTEX file
@@ -343,4 +345,6 @@ class AntexFileReader {
   DateTime ReadDateTime(std::string line);
 };
 
+}  // namespace gnss
+
 #endif  // S2E_LIBRARY_ANTEX_FILE_READER_HPP_

src/math_physics/gnss/bias_sinex_file_reader.cpp

@@ -9,6 +9,8 @@
 #include <fstream>
 #include <iostream>
 
+namespace gnss {
+
 bool BiasSinexFileReader::ReadFile(const std::string file_name) {
   // File open
   std::ifstream bias_sinex_file(file_name);
@@ -242,3 +244,5 @@ void BiasSolutionData::SetTargetSignal(const std::string signal1, const std::str
     target_signal_ = BiasTargetSignal::kError;
   }
 }
+
+}  // namespace gnss

src/math_physics/gnss/bias_sinex_file_reader.hpp

@@ -10,6 +10,8 @@
 #include <string>
 #include <vector>
 
+namespace gnss {
+
 /**
  * @enum BiasIdentifier
  * @brief Bias Identifier
@@ -184,4 +186,6 @@ class BiasSinexFileReader {
   void ReadBiasSolution(std::ifstream& bias_sinex_file);
 };
 
+}  // namespace gnss
+
 #endif  // S2E_LIBRARY_BIAS_SINEX_FILE_READER_HPP_

src/math_physics/gnss/gnss_satellite_number.cpp

@@ -5,6 +5,8 @@
 
 #include "gnss_satellite_number.hpp"
 
+namespace gnss {
+
 size_t ConvertGnssSatelliteNumberToIndex(const std::string satellite_number) {
   switch (satellite_number.front()) {
     case 'G':
@@ -58,3 +60,5 @@ std::string ConvertIndexToGnssSatelliteNumber(const size_t index) {
 
   return output;
 }
+
+}  // namespace gnss

src/math_physics/gnss/gnss_satellite_number.hpp

@@ -10,6 +10,8 @@
 
 #include <string>
 
+namespace gnss {
+
 // GNSS satellite number definition
 // TODO: Move to initialized file?
 const size_t kNumberOfGpsSatellite = 32;      //!< Number of GPS satellites
@@ -44,4 +46,6 @@ size_t ConvertGnssSatelliteNumberToIndex(const std::string satellite_number);
  */
 std::string ConvertIndexToGnssSatelliteNumber(const size_t index);
 
+}  // namespace gnss
+
 #endif  // S2E_LIBRARY_GNSS_GNSS_SATELLITE_NUMBER_HPP_

src/math_physics/gnss/igs_product_name_handling.hpp

@@ -10,6 +10,8 @@
 
 #include <string>
 
+namespace gnss {
+
 /**
  * @fn GetOrbitClockFileName
  * @brief Return IGS orbit and clock final product file name
@@ -83,4 +85,6 @@ size_t IncrementYearDoy(const size_t year_doy) {
   return output;
 }
 
+}  // namespace gnss
+
 #endif  // S2E_LIBRARY_GNSS_IGS_PRODUCT_NAME_HANDLING_HPP_

src/math_physics/gnss/sp3_file_reader.cpp

@@ -11,6 +11,8 @@
 #include <fstream>
 #include <iostream>
 
+namespace gnss {
+
 Sp3FileReader::Sp3FileReader(const std::string file_name) { ReadFile(file_name); }
 
 DateTime Sp3FileReader::GetEpochData(const size_t epoch_id) const {
@@ -419,3 +421,5 @@ Sp3VelocityClockRateCorrelation Sp3FileReader::DecodeVelocityClockRateCorrelatio
 
   return correlation;
 }
+
+}  // namespace gnss

src/math_physics/gnss/sp3_file_reader.hpp

@@ -17,6 +17,8 @@
 #include <string>
 #include <vector>
 
+namespace gnss {
+
 #define SP3_BAD_CLOCK_VALUE (999999.999999)
 #define SP3_BAD_POSITION_VALUE (0.000000)
 
@@ -234,4 +236,6 @@ class Sp3FileReader {
   Sp3VelocityClockRateCorrelation DecodeVelocityClockRateCorrelation(std::string line);
 };
 
+}  // namespace gnss
+
 #endif  // S2E_LIBRARY_GNSS_SP3_FILE_READER_HPP_

src/math_physics/gnss/test_antex_file_reader.cpp

@@ -7,6 +7,8 @@
 
 #include "antex_file_reader.hpp"
 
+using namespace gnss;
+
 /**
  * @brief Test Constructor
  */

src/math_physics/gnss/test_bias_sinex_file_reader.cpp

@@ -2,6 +2,8 @@
 
 #include "bias_sinex_file_reader.hpp"
 
+using namespace gnss;
+
 TEST(BiasSinex, Constructor) {
   // File read error check
   BiasSinexFileReader bias_sinex_file_fault("false_file_path.BSX");

src/math_physics/gnss/test_gnss_satellite_number.cpp

@@ -6,6 +6,8 @@
 
 #include "gnss_satellite_number.hpp"
 
+using namespace gnss;
+
 /**
  * @brief Test satellite number to index
  */