Fix format

ut-issl · Jul 20, 2024 · 80cfe1f · 80cfe1f
1 parent c9f20d4
commit 80cfe1f
Show file tree

Hide file tree

Showing 4 changed files with 9 additions and 8 deletions.
diff --git a/src/dynamics/orbit/encke_orbit_propagation.hpp b/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]
-  orbit::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]

diff --git a/src/dynamics/orbit/relative_orbit.cpp b/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, orbit::RelativeOrbitModel relative_dynamics_model_type, orbit::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),
@@ -80,7 +80,8 @@ void RelativeOrbit::CalculateSystemMatrix(orbit::RelativeOrbitModel relative_dyn
   }
 }
 
-void RelativeOrbit::CalculateStm(orbit::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 orbit::StmModel::kHcw: {
       double reference_sat_orbit_radius = reference_sat_orbit->GetPosition_i_m().CalcNorm();

diff --git a/src/dynamics/orbit/relative_orbit.hpp b/src/dynamics/orbit/relative_orbit.hpp
@@ -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
+  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
+  RelativeInformation* relative_information_;               //!< Relative information
 
   /**
    * @fn InitializeState

diff --git a/src/environment/global/gnss_satellites.hpp b/src/environment/global/gnss_satellites.hpp
@@ -120,8 +120,8 @@ class GnssSatellites : public ILoggable {
   size_t reference_interpolation_id_ = 0;        //!< Reference epoch ID of the interpolation
   EpochTime current_epoch_time_;                 //!< The last updated time
 
-  std::vector<orbit::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