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Merge pull request #692 from ut-issl/feature/add-orbit-interpolation
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Add orbit interpolation method as an Orbit calculation feature
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@fukudakazuya
fukudakazuya authored Sep 30, 2024
2 parents a95ff06 + 7d36c93 commit 6d7e6d4
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Showing 9 changed files with 386 additions and 3 deletions.
101 changes: 101 additions & 0 deletions settings/sample_satellite/orbit_files/time_series_orbit.csv
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ephemeris_time[s],position_i_x[m],position_i_y[m],position_i_z[m],velocity_i_x[m/s],velocity_i_y[m/s],velocity_i_z[m/s]
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11 changes: 11 additions & 0 deletions settings/sample_satellite/satellite.ini
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Expand Up @@ -60,6 +60,7 @@ logging = ENABLE
// RELATIVE : Relative dynamics (for formation flying simulation)
// KEPLER : Kepler orbit propagation without disturbances and thruster maneuver
// ENCKE : Encke orbit propagation with disturbances and thruster maneuver
// TIME_SERIES_FILE : Orbit propagation with time series file
propagate_mode = RK4

// Orbit initialize mode for RK4, KEPLER, and ENCKE
Expand Down Expand Up @@ -123,6 +124,16 @@ reference_satellite_id = 1
error_tolerance = 0.0001
///////////////////////////////////////////////////////////////////////////////

// Settings for orbit propagation with time series file ///////////
time_series_file_path = SETTINGS_DIR_FROM_EXE/sample_satellite/orbit_files/time_series_orbit.csv
number_of_interpolation = 5
// Interpolation method
0: POLYNOMIAL
1: TRIGONOMETRIC
interpolation_method = 0
orbital_period_correction_s = 86659.2 // Only used for trigonometric method. This sample value is used for the gnss satellits (24 * 60 * 60 * 1.003).
///////////////////////////////////////////////////////////////////////////////


[THERMAL]
calculation = DISABLE
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1 change: 1 addition & 0 deletions src/dynamics/CMakeLists.txt
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Original file line number Diff line number Diff line change
Expand Up @@ -8,6 +8,7 @@ add_library(${PROJECT_NAME} STATIC
orbit/relative_orbit.cpp
orbit/kepler_orbit_propagation.cpp
orbit/encke_orbit_propagation.cpp
orbit/time_series_file_orbit_propagation.cpp
orbit/initialize_orbit.cpp

thermal/node.cpp
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11 changes: 11 additions & 0 deletions src/dynamics/orbit/initialize_orbit.cpp
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Original file line number Diff line number Diff line change
Expand Up @@ -11,6 +11,7 @@
#include "relative_orbit.hpp"
#include "rk4_orbit_propagation.hpp"
#include "sgp4_orbit_propagation.hpp"
#include "time_series_file_orbit_propagation.hpp"

Orbit* InitOrbit(const CelestialInformation* celestial_information, std::string initialize_file, double step_width_s, double current_time_jd,
double gravity_constant_m3_s2, std::string section, RelativeInformation* relative_information) {
Expand Down Expand Up @@ -96,6 +97,16 @@ Orbit* InitOrbit(const CelestialInformation* celestial_information, std::string
double error_tolerance = conf.ReadDouble(section_, "error_tolerance");
orbit = new EnckeOrbitPropagation(celestial_information, gravity_constant_m3_s2, step_width_s, current_time_jd, position_i_m, velocity_i_m_s,
error_tolerance);
} else if (propagate_mode == "TIME_SERIES_FILE") {
// initialize orbit for propagation with time series file
const std::string time_series_file_path = conf.ReadString(section_, "time_series_file_path");
const int number_of_interpolation = conf.ReadInt(section_, "number_of_interpolation");
const int interpolation_method = conf.ReadInt(section_, "interpolation_method");
const double orbital_period_correction_s = conf.ReadDouble(section_, "orbital_period_correction_s");

orbit = new TimeSeriesFileOrbitPropagation(celestial_information, time_series_file_path, number_of_interpolation, interpolation_method,
orbital_period_correction_s, current_time_jd);

} else {
std::cerr << "ERROR: orbit propagation mode: " << propagate_mode << " is not defined!" << std::endl;
std::cerr << "The orbit mode is automatically set as RK4" << std::endl;
Expand Down
3 changes: 2 additions & 1 deletion src/dynamics/orbit/orbit.hpp
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Original file line number Diff line number Diff line change
Expand Up @@ -25,7 +25,8 @@ enum class OrbitPropagateMode {
kSgp4, //!< SGP4 propagation using TLE without thruster maneuver
kRelativeOrbit, //!< Relative dynamics (for formation flying simulation)
kKepler, //!< Kepler orbit propagation without disturbances and thruster maneuver
kEncke //!< Encke orbit propagation with disturbances and thruster maneuver
kEncke, //!< Encke orbit propagation with disturbances and thruster maneuver
kTimeSeriesFile //!< Orbit propagation using time series file
};

/**
Expand Down
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