diff --git a/Specifications/Dynamics/Spec_Orbit.md b/Specifications/Dynamics/Spec_Orbit.md
index a8203225..c914294a 100644
--- a/Specifications/Dynamics/Spec_Orbit.md
+++ b/Specifications/Dynamics/Spec_Orbit.md
@@ -27,7 +27,7 @@
- This setting works only for `RK4`, `KEPLER`, and `ENCKE` mode.
- Set the orbit information in the ini file
- You can see the details in the documents for each orbit propagation mode.
- - The definition of the coordinate system is decided in `PlanetSelect.ini`
+ - The definition of the coordinate system is decided at `[CELESTIAL_INFORMATION]` section in `sample_simulation_base.ini`.
## 2. Explanation of Algorithm
In the Orbit base class provides the following common functions for every propagator.
diff --git a/Specifications/Dynamics/Spec_RelativeOrbit.md b/Specifications/Dynamics/Spec_RelativeOrbit.md
index f1c925dd..3c994f91 100644
--- a/Specifications/Dynamics/Spec_RelativeOrbit.md
+++ b/Specifications/Dynamics/Spec_RelativeOrbit.md
@@ -58,7 +58,7 @@
+ Add the name of the dynamics model to `StmModel` enum in `relative_orbit_models.hpp`.
+ Add the function to calculate the system matrix as `CalcHcwStm`in `relative_orbit_models.hpp`.
- + Edit the `CalculateSTM` function in `relative_orbit.hpp`.
+ + Edit the `CalculateStm` function in `relative_orbit.hpp`.
## 2. Explanation of Algorithm
@@ -69,20 +69,11 @@
2. inputs and outputs
+ input
- * `initial_relative_position_lvlh_m`, `initial_relative_velocity_lvlh_m_s`
+ * `relative_position_lvlh_m`, `relative_velocity_lvlh_m_s`
- The initial state of the satellite
* `gravity_constant_m3_s2`
- The gravity constant of the reference celestial body $\mu$
- * `reference_sat_initial_orbit`
- - The initial orbit of the reference satellite
- - NOTE: This is used only for the initialization.
- * `current_jd`
- - The initial Julian day
- * `timestep`
- - RK4 propagation timestep
- * `wgs`
- - Type of the World Geometric System
- * `init_time`
+ * `initial_time_s`
- Initial simulation time (default value is 0)
+ output
* none
@@ -102,7 +93,7 @@
- The type of relative dynamics model
* `reference_sat_orbit`
- The orbit of the reference satellite
- * `mu`
+ * `gravity_constant_m3_s2`
- The gravity constant $\mu$
+ output
* none
@@ -111,10 +102,10 @@
4. note
-1. `CalculateSTM`
+1. `CalculateStm`
1. overview
- + The `CalculateSTM` function is used only inside the `RelativeOrbit` class. This function calls the system matrix calculation function according to `stm_model_type`.
+ + The `CalculateStm` function is used only inside the `RelativeOrbit` class. This function calls the system matrix calculation function according to `stm_model_type`.
2. inputs and outputs
+ input
@@ -122,7 +113,7 @@
- The type of relative dynamics model
* `reference_sat_orbit`
- The orbit of the reference satellite
- * `mu`
+ * `gravity_constant_m3_s2`
- The gravity constant $\mu$
* `elapsed_sec`
- Elapsed simulation time
@@ -137,13 +128,13 @@
1. overview
+ The `CalculateHillSystemMatrix` function calculates the system matrix of the Hill equation.
- + This function is declared in `RelativeOrbitModels.h` and is used by the
+ + This function is declared in `relative_orbit_models.hpp` and is used by the
2. inputs and outputs
+ input
* `orbit_radius`
- Radius of the reference satellite orbit $R$
- * `mu`
+ * `gravity_constant_m3_s2`
- The gravity constant $\mu$
+ output
* `system_matrix`
@@ -172,17 +163,17 @@
4. note
-1. `CalculateHCWSTM`
+1. `CalculateHcwStm`
1. overview
- + The `CalculateHCWSTM` function calculates the Hill-Clohessy-Wiltshire STM.
- + This function is declared in `RelativeOrbitModels.h` and is used by the
+ + The `CalculateHcwStm` function calculates the Hill-Clohessy-Wiltshire STM.
+ + This function is declared in `relative_orbit_models.hpp` and is used by the
2. inputs and outputs
+ input
* `orbit_radius`
- Radius of the reference satellite orbit $R$
- * `mu`
+ * `gravity_constant_m3_s2`
- The gravity constant $\mu$
* `elapsed_sec`
- Elapsed simulation time
@@ -223,62 +214,60 @@
2. conditions for the verification
1. input files
- Initialization files for the two satellites were prepared.
- - `Sat0.ini`
- - `Sat1.ini`
+ - `satellite0.ini`
+ - `satellite1.ini`
2. initial values
- - The orbit of the reference satellite (Sat0) is GEO. The initial position of the satellite (Sat1) is $(0\mathrm{m}, 100\mathrm{m}, 0\mathrm{m})^\mathrm{T}$ in LVLH frame. The orbit was propagated for 86400 sec (the period of GEO).
- - `Sat0.ini`
+ - The orbit of the reference satellite (satellite0) is GEO. The initial position of the satellite (satellite1) is $(0\mathrm{m}, 100\mathrm{m}, 0\mathrm{m})^\mathrm{T}$ in LVLH frame. The orbit was propagated for 86400 sec (the period of GEO).
+ - `satellite0.ini`
```
- propagate_mode = 0
+ propagate_mode = RK4
//Information used for orbital propagation by the Runge-Kutta method///////////
//initial satellite position[m]
//＊The coordinate system is defined in PlanetSelect.ini
- init_position(0) = 4.2164140100E+07 //radius of GEO
- init_position(1) = 0
- init_position(2) = 0
+ initial_position_i_m(0) = 4.2164140100E+07 //radius of GEO
+ initial_position_i_m(1) = 0
+ initial_position_i_m(2) = 0
//initial satellite velocity[m/s]
//＊The coordinate system is defined in PlanetSelect.ini
- init_velocity(0) = 0
- init_velocity(1) = 3.074661E+03 //Speed of a spacecraft in GEO
- init_velocity(2) = 0
+ initial_velocity_i_m_s(0) = 0
+ initial_velocity_i_m_s(1) = 3.074661E+03 //Speed of a spacecraft in GEO
+ initial_velocity_i_m_s(2) = 0
///////////////////////////////////////////////////////////////////////////////
```
- - `Sat1.ini`
+ - `satellite1.ini`
```
- propagate_mode = 2
+ propagate_mode = RELATIVE
//Information used for relative orbit propagation//////////////////////////////
//Relative Orbit Update Method (0 means RK4, 1 means STM)
- update_method = 0
- //RK4 Relative Dynamics model type (only valid for RK4 update)
- //0: Hill
+ relative_orbit_update_method = 0
+ // RK4 Relative Dynamics model type (only valid for RK4 update)
+ // 0: Hill
relative_dynamics_model_type = 0
- //STM Relative Dynamics model type (only valid for STM update)
- //0: HCW
+ // STM Relative Dynamics model type (only valid for STM update)
+ // 0: HCW
stm_model_type = 0
- //initial satellite position relative to the reference satellite in LVLH frame[m]
- //＊The coordinate system is defined in PlanetSelect.ini
- init_relative_position_lvlh(0) = 0.0
- init_relative_position_lvlh(1) = 100.0
- init_relative_position_lvlh(2) = 0.0
- //initial satellite velocity relative to the reference satellite in LVLH frame[m/s]
- //＊The coordinate system is defined in PlanetSelect.ini
- init_relative_velocity_lvlh(0) = 0.0
- init_relative_velocity_lvlh(1) = 0.0
- init_relative_velocity_lvlh(2) = 0.0
- //information of reference satellite
- reference_sat_id = 0
- reference_sat_ini_file = ../../data/ini/Sat0.ini
+ // Initial satellite position relative to the reference satellite in LVLH frame[m]
+ // * The coordinate system is defined at [PLANET_SELECTION] in SampleSimBase.ini
+ initial_relative_position_lvlh_m(0) = 0.0
+ initial_relative_position_lvlh_m(1) = 100.0
+ initial_relative_position_lvlh_m(2) = 0.0
+ // initial satellite velocity relative to the reference satellite in LVLH frame[m/s]
+ initial_relative_velocity_lvlh_m_s(0) = 0.0
+ initial_relative_velocity_lvlh_m_s(1) = 0.0
+ initial_relative_velocity_lvlh_m_s(2) = 0.0
+ // information of reference satellite
+ reference_satellite_id = 0
///////////////////////////////////////////////////////////////////////////////
```
3. results
- - The position of Sat1 seen from Sat0 in the inertia frame was calculated.
+ - The position of satellite1 seen from satellite0 in the inertia frame was calculated.
@@ -294,4 +283,4 @@
## 4. References
-1. Kapila, V., Sparks, A. G., Buffington, J. M., & Yan, Q. (2000). Spacecraft formation flying: Dynamics and control. Journal of Guidance, Control, and Dynamics, 23(3), 561-564.
\ No newline at end of file
+1. Kapila, V., Sparks, A. G., Buffington, J. M., & Yan, Q. (2000). Spacecraft formation flying: Dynamics and control. Journal of Guidance, Control, and Dynamics, 23(3), 561-564.
diff --git a/Specifications/Environment/Spec_Atmosphere.md b/Specifications/Environment/Spec_Atmosphere.md
index b5adcfb9..d7831263 100644
--- a/Specifications/Environment/Spec_Atmosphere.md
+++ b/Specifications/Environment/Spec_Atmosphere.md
@@ -9,8 +9,6 @@
+ `Atmosphere` class is defined.
+ `src/environment/local/local_environment.cpp, .hpp`
+ `Atmosphere` class is used here as a member variable of `LocalEnvironment` class.
- + `src/environment/local/initialize_local_environment.cpp, .hpp`
- + `Atmosphere` class is instanced here based on the `.ini` file for the environment.
+ `src/library/external/nrlmsise00/wrapper_nrlmsise00.cpp, .hpp`
+ An air density is calculated using an external library, NRLMSISE00 atmosphere model.
@@ -19,6 +17,8 @@
+ Model
+ `STANDARD`
+ The air density is calculated using scale height.
+ + `HARRIS_PRIESTER`
+ + The air density is calculated using the Harris-Priester model.
+ `NRLMSISE00`
+ The air density is calculated using the NRLMSISE00 model.
+ If users use this model, the following additional parameters must be set in the `.ini` file.
@@ -53,7 +53,7 @@
+ NRLMSISE00
1. Read Space weather table
- + F10.7 and Kp/Ap index, which indicates the solar activity cycle, are necessary as inputs for NRLMSISE00.
+ + `F10.7` and `Kp/Ap` index, which indicates the solar activity cycle, are necessary as inputs for NRLMSISE00.
These parameters, which are only during the simulation period, are read from SpaceWeather.txt.
+ Note
+ If SpaceWeather.txt cannot be read, the atmosphere model is automatically set to STANDARD.
@@ -84,21 +84,21 @@
2. initial values
+ Case1 : Default initialize files
```
- StartYMDHMS=2020/01/01 11:00:00.0
- EndTimeSec=200
- StepTimeSec=0.1
- OrbitPropagateStepTimeSec=0.1
- LogPeriod = 5
- SimulationSpeed = 0
+ simulation_start_time_utc = 2020/01/01 11:00:00.0
+ simulation_duration_s = 200
+ simulation_step_s = 0.1
+ orbit_update_period_s = 0.1
+ log_output_period_s = 0.1
+ simulation_speed_setting = 0
```
+ Case2 : Start year only was changed to 2015.
```
- StartYMDHMS=2015/01/01 11:00:00.0
- EndTimeSec=200
- StepTimeSec=0.1
- OrbitPropagateStepTimeSec=0.1
- LogPeriod = 5
- SimulationSpeed = 0
+ simulation_start_time_utc = 2015/01/01 11:00:00.0
+ simulation_duration_s = 200
+ simulation_step_s = 0.1
+ orbit_update_period_s = 0.1
+ log_output_period_s = 0.1
+ simulation_speed_setting = 0
```
+ Especially, we chose following TLE for orbit calculation
```
diff --git a/Specifications/Environment/Spec_CelestialInformation.md b/Specifications/Environment/Spec_CelestialInformation.md
index 5610ad7a..8bdef0ea 100644
--- a/Specifications/Environment/Spec_CelestialInformation.md
+++ b/Specifications/Environment/Spec_CelestialInformation.md
@@ -4,15 +4,13 @@
1. Functions
- `CelestialInformation` manages the celestial bodies position and velocity on the inertial frame.
- This class also manages the celestial body information like the gravity constant, the radius, and the rotation.
- - The actual calculations are executed by CSPICE or `CelestialRotation`, and this class just calls their functions.
+ - The actual calculations are executed by CSPICE or `EarthRotation`, and this class just calls their functions.
2. Related files
- `src/environment/global/celestial_information.cpp, .hpp`
- `CelestialInformation` class is defined.
- `src/environment/global/global_environment.cpp, .hpp`
- `CelestialInformation` class is used here as a member variable of `GlobalEnvironment` class.
- - `src/environment/global/initialize_global_environment.cpp, .hpp`
- - `CelestialInformation` class is instanced here based on the `.ini` file for the environment.
3. How to use
- Call ` UpdateAllObjectsInformation` function to calculates the celestial bodies position and velocity.
diff --git a/Specifications/Environment/Spec_CelestialRotation.md b/Specifications/Environment/Spec_CelestialRotation.md
index 1971743c..7c23418a 100644
--- a/Specifications/Environment/Spec_CelestialRotation.md
+++ b/Specifications/Environment/Spec_CelestialRotation.md
@@ -1,23 +1,23 @@
-# Specification of Celestial Rotation
+# Specification of Earth Rotation
## 1. Overview
1. Functions
- - The `CelestialRotation` class calculates the rotational motion of central objects. Currently, only the Earth is supported as the central object.
+ - The `EarthRotation` class calculates the rotational motion of the Earth.
2. Related files
- - `src/environment/global/celestial_rotation.cpp, .hpp`
- - `CelestialRotation` class is defined here.
+ - `src/environment/global/earth_rotation.cpp, .hpp`
+ - `EarthRotation` class is defined here.
- `src/environment/global/celestial_information.cpp, .hpp`
- - `CelestialRotation` class is used here.
+ - `EarthRotation` class is used here.
3. How to use
- - Make an instance of the `CelestialRotation` class in `CelestialInformation` class.
+ - Make an instance of the `EarthRotation` class in `CelestialInformation` class.
- Select rotation mode in `sample_simulation_base.ini`
- - `Idle` : no motion ( $\mathrm{DCM_{ECItoECEF}}$ is set as the unit matrix)
- - If the rotation mode input is neither `Full` nor `Simple`, the `Idle` mode is set.
- - `Simple` : axial rotation only ( $\mathrm{DCM_{ECItoECEF}} = \bf{R}$ )
- - `Full` : Precession and Nutation are taken into account ( $\mathrm{DCM_{ECItoECEF}} = \bf{R}\bf{N}\bf{P}$ )
+ - `IDLE` : no motion ( $\mathrm{DCM_{ECItoECEF}}$ is set as the unit matrix)
+ - If the rotation mode input is neither `FULL` nor `SIMPLE`, the `IDLE` mode is set.
+ - `SIMPLE` : axial rotation only ( $\mathrm{DCM_{ECItoECEF}} = \bf{R}$ )
+ - `FULL` : Precession and Nutation are taken into account ( $\mathrm{DCM_{ECItoECEF}} = \bf{R}\bf{N}\bf{P}$ )
- $\bf{R}$, $\bf{N}$, $\bf{P}$ stand for the DCM of axial rotation, nutation, precession, respectively.
## 2. Explanation of Algorithm
diff --git a/Specifications/Environment/Spec_GeomagneticField.md b/Specifications/Environment/Spec_GeomagneticField.md
index 74a6d789..438c5052 100644
--- a/Specifications/Environment/Spec_GeomagneticField.md
+++ b/Specifications/Environment/Spec_GeomagneticField.md
@@ -10,17 +10,15 @@
+ `GeomagneticField` class is defined.
+ `src/environment/local/local_environment.cpp, .hpp`
+ `GeomagneticField` class is used here as a member variable of `LocalEnvironment` class.
- + `src/environment/local/initialize_local_environment.cpp, .hpp`
- + `GeomagneticField` class is instanced here based on the `.ini` file for environment.
+ `src/library/external/igrf/igrf.cpp, h`
+ A magnetic field in the ECI frame is calculated by the IGRF model.
3. How to use
+ Set a coefficient file path for the IGRF and random walk / white noise in .ini file
- - coefficient_file: File path to the IGRF coefficients table.
- - magnetic_field_random_walk_standard_deviation_nT: Standard deviation of the random walk noise
- - magnetic_field_random_walk_limit_nT: Limit of the random walk noise
- - magnetic_field_white_noise_standard_deviation_nT: Standard deviation of the normal random noise
+ - `coefficient_file`: File path to the IGRF coefficients table.
+ - `magnetic_field_random_walk_standard_deviation_nT`: Standard deviation of the random walk noise
+ - `magnetic_field_random_walk_limit_nT`: Limit of the random walk noise
+ - `magnetic_field_white_noise_standard_deviation_nT`: Standard deviation of the normal random noise
+ Public functions
+ `CalcMagneticField` : Update the magnetic field
+ `GetGeomagneticField_i_nT` : Return the magnetic field (nT) in the ECI
@@ -43,12 +41,12 @@
2. initial values
- To check the result in an example orbit, the EndTime was changed to 9000 s.
```
- StartYMDHMS=2020/01/01 11:00:00.0
- EndTimeSec=9000
- StepTimeSec=5
- OrbitPropagateStepTimeSec=0.1
- LogPeriod = 5
- SimulationSpeed = 0
+ simulation_start_time_utc = 2020/01/01 11:00:00.0
+ simulation_duration_s = 9000
+ simulation_step_s = 5
+ orbit_update_period_s = 0.1
+ log_output_period_s = 5
+ simulation_speed_setting = 0
```
- Especially, we chose the following TLE for orbit calculation (ISS orbit).
```
diff --git a/Specifications/Environment/Spec_GnssSatellites_en.md b/Specifications/Environment/Spec_GnssSatellites_en.md
index e4f1d0fa..c3b56c42 100644
--- a/Specifications/Environment/Spec_GnssSatellites_en.md
+++ b/Specifications/Environment/Spec_GnssSatellites_en.md
@@ -3,7 +3,7 @@
## 1. Overview
1. function
- A class to read data about orbit and clock bias of GNSS satellites such as .sp3 and .clk_30s and use them in other classes.
- - Determine the file name of GNSS satellites' data and time from `[GNSS_SATELLIES]` in `sample_gnss.ini`.
+ - Determine the file name of GNSS satellites' data and time from `[GNSS_SATELLITES]` in `sample_gnss.ini`.
2. Related files
- `src/environment/global/globalEnvironment.cpp, .hpp`
diff --git a/Specifications/Environment/Spec_HipparcosCatalogue_en.md b/Specifications/Environment/Spec_HipparcosCatalogue_en.md
index 7deaf9ee..9323151a 100644
--- a/Specifications/Environment/Spec_HipparcosCatalogue_en.md
+++ b/Specifications/Environment/Spec_HipparcosCatalogue_en.md
@@ -12,8 +12,6 @@
2. files
+ `HipparcosCatalogue.cpp` ，`HipparcosCatalogue.hpp`
* Definitions and declarations of the class
- + `initialize_global_environment.cpp`
- * The initialize function is defined here.
+ `sample_simulation_base.ini`
* Parameters for initialization
+ `hip_main.csv`
diff --git a/Specifications/Environment/Spec_HipparcosCatalogue_ja.md b/Specifications/Environment/Spec_HipparcosCatalogue_ja.md
index c47b3008..11903bb5 100644
--- a/Specifications/Environment/Spec_HipparcosCatalogue_ja.md
+++ b/Specifications/Environment/Spec_HipparcosCatalogue_ja.md
@@ -16,7 +16,7 @@
+ `sample_simulation_base.ini`
* 初期化ファイル
+ `hip_main.csv`
- * ヒッパルコス星表の元データ． `s2e-core` 外の `ExtLibralies` に保存される．使用しやすいように，HIP ID順ではなく，視等級の小さい順にソートされている．
+ * ヒッパルコス星表の元データ． `s2e-core` 外の `ExtLibraries` に保存される．使用しやすいように，HIP ID順ではなく，視等級の小さい順にソートされている．
3. 外部ライブラリのダウンロードに関して
+ まずは`hip_main.csv` のダウンロードを済ませる必要がある．このためのスクリプトとして `s2e-core/scripts/download_HIPcatalogue.sh`を用意した．Git Bashなどを利用して，このスクリプトがあるディレクトリで以下を実行することで，必要なcsvファイルをダウンロードすることができる．
* Macユーザーは，Mac標準のターミナルからではなく，Docker内のUbuntuのターミナルから実行する必要がある．（ `sed` の仕様がMacとLinuxで違うので，正しいcsvファイルを生成することができないため．参考：
）
diff --git a/Specifications/Environment/Spec_LocalCelestialInformation.md b/Specifications/Environment/Spec_LocalCelestialInformation.md
index 33fa850a..fed1d756 100644
--- a/Specifications/Environment/Spec_LocalCelestialInformation.md
+++ b/Specifications/Environment/Spec_LocalCelestialInformation.md
@@ -9,8 +9,7 @@
- `LocalCelestialInformation` class is defined.
- `src/environment/local/local_environment.cpp, .hpp`
- `LocalCelestialInformation` class is used here as a member variable of `LocalEnvironment` class.
- - `src/environment/local/initialize_local_environment.cpp, .hpp`
- - `LocalCelestialInformation` class is instanced here based on the `.ini` file for the environment.
+
3. How to use
- Call ` UpdateAllObjectsInformation` function to calculates the celestial bodies position and velocity.
- Users can get calculated values by using the following functions:
diff --git a/Specifications/Environment/Spec_SRPEnvironment.md b/Specifications/Environment/Spec_SRPEnvironment.md
index 23ad9765..c0e82c10 100644
--- a/Specifications/Environment/Spec_SRPEnvironment.md
+++ b/Specifications/Environment/Spec_SRPEnvironment.md
@@ -10,8 +10,6 @@
- `SolarRadiationPressureEnvironment` class is defined.
- `src/environment/local/local_environment.cpp, .hpp`
- `SolarRadiationPressureEnvironment` class is used here as a member variable of `LocalEnvironment` class.
- - `src/environment/local/initialize_local_environment.cpp, .hpp`
- - `SolarRadiationPressureEnvironment` class is instanced here based on the `.ini` file for the environment.
3. How to use
- Call `UpdateAllStates` function to calculates solar power flux and updates the eclipse flag.
@@ -151,4 +149,4 @@
## 4. References
-1. Montenbruck, O., Gill, E., & Lutze, F. (2002). Satellite orbits: models, methods, and applications. Appl. Mech. Rev., 55(2), B27-B28.
\ No newline at end of file
+1. Montenbruck, O., Gill, E., & Lutze, F. (2002). Satellite orbits: models, methods, and applications. Appl. Mech. Rev., 55(2), B27-B28.
diff --git a/Specifications/Interface/Spec_PowerPort.md b/Specifications/Interface/Spec_PowerPort.md
index 5e814ae2..3b64f5d7 100644
--- a/Specifications/Interface/Spec_PowerPort.md
+++ b/Specifications/Interface/Spec_PowerPort.md
@@ -5,29 +5,29 @@
- `PowerPort` class provides features of an electrical power connection.
- Users can use the class to control the electrical power switching of components and calculate the component's consumed electrical current.
2. Related files
- - Main files: `PowerPort.cpp, .h`
- - Referenced files: `ComponentBase.cpp, .h` and `PCU.cpp, .h`
+ - Main files: `power_port.cpp, .hpp`
+ - Referenced files: `component.cpp, .hpp` and `power_control_unit.cpp, .hpp`
3. How to use
- - **Example**: The `SampleComponents` in the `s2e-core/Simulation/Spacecraft/SampleSpacecraft` is helpful to know how to use the feature.
- - Make a component class that inherits the `ComponentBase` class.
- - The `ComponentBase` class has the `PowerPort` class as a member and controls the component's action according to the electrical power switches.
- - Make an instance of `PCU` and connect the power port.
- - The `PCU` base class has a member of the `map` of the `PowerPort` class and manages the port id and connection of the `PowerPort`.
- - Users can make their PCU by inheriting the `PCU` base class and can control the power switching in the `MainRoutine` function.
+ - **Example**: The `sample_components.hpp` in the `s2e-core/simulation_sample/spacecraft/` is helpful to know how to use the feature.
+ - Make a component class that inherits the `Component` class.
+ - The `Component` class has the `PowerPort` class as a member and controls the component's action according to the electrical power switches.
+ - Make an instance of `PowerControlUnit` and connect the power port.
+ - The `PowerControlUnit` base class has a member of the `map` of the `PowerPort` class and manages the port id and connection of the `PowerPort`.
+ - Users can make their PCU by inheriting the `PowerControlUnit` base class and can control the power switching in the `MainRoutine` function.
```cpp
- pcu_ = new PCU(clock_gen);
+ pcu_ = new PowerControlUnit(clock_gen);
pcu_->ConnectPort(0, 0.5, 3.3, 0.3);
```
- Make an instance of the components with the connected `PowerPort`.
```cpp
- obc_ = new OBC(1, clock_gen, pcu_->GetPowerPort(0));
+ obc_ = new OnBoardComputer(1, clock_gen, pcu_->GetPowerPort(0));
```
- - Control the power switches by using the `PCU`.
+ - Control the power switches by using the `PowerControlUnit`.
- The default setting of the power switch is `off`, so users need to power on the port to execute the `MainRoutine` of the components.
```cpp
pcu_->GetPowerPort(0)->SetVoltage(3.3);
```
- - **Note**: The virtual power port is created when users make an instance of the `ComponentBase` class and its subclasses without the `PowerPort` information. The virtual port has a minus value port ID, and the switch state is originally `ON`, but the consumed power is zero.
+ - **Note**: The virtual power port is created when users make an instance of the `Component` class and its subclasses without the `PowerPort` information. The virtual port has a minus value port ID, and the switch state is originally `ON`, but the consumed power is zero.
## 2. Explanation of Algorithm
1. SetVoltage
@@ -67,4 +67,4 @@
N/A
## 4. References
-N/A
\ No newline at end of file
+N/A
diff --git a/Specifications/OverallStructure/OverallStructure.md b/Specifications/OverallStructure/OverallStructure.md
index 289a765e..aad8c402 100644
--- a/Specifications/OverallStructure/OverallStructure.md
+++ b/Specifications/OverallStructure/OverallStructure.md
@@ -9,12 +9,12 @@
### 2.1. Simulation Case
-- The highest layer of the structure of S2E is the `Simulation Case`, which is defined in the `src/Simulation/Case/SimulationCase.cpp`.
-- The `SimulationCase` always has `SimulationConfig` and `Global Environment`.
- - `SimulationConfig` has basic information on the interface of the simulation, such as `log output` and `initialize input` information.
- - `GlobalEnvironment` is defined as the common environment for the whole simulation case. It includes time, celestial information, star catalog, and GNSS satellite position.
-- Users can make their `SimulationCase` by inheriting the `SimulationCase` base class and adding simulation target objects (e.g., spacecraft and ground station) for their demand.
-- The defined simulation objects can use the information of `SimulationConfig` and `GlobalEnvironment`.
+- The highest layer of the structure of S2E is the `Simulation Case`, which is defined in the `src/simulation/case/simulation_case.cpp`.
+- The `Simulation Case` always has `Simulation Configuration` and `Global Environment`.
+ - `Simulation Configuration` has basic information on the interface of the simulation, such as `log output` and `initialize input` information.
+ - `Global Environment` is defined as the common environment for the whole simulation case. It includes time, celestial information, star catalog, and GNSS satellite position.
+- Users can make their `Simulation Case` by inheriting the `Simulation Case` base class and adding simulation target objects (e.g., spacecraft and ground station) for their demand.
+- The defined simulation objects can use the information of `Simulation Configuration` and `Global Environment`.
### 2.2. Spacecraft
- An essential simulation object is the `Spacecraft` class.
@@ -41,8 +41,8 @@
### 2.4. Structure of initializing files
- The structure of the initializing files follows the above figure.
-- `SimBase.ini` sets the parameters for `SimulationCase`, and file paths to each simulation object.
-- `Sat.ini` sets the parameters for `Spacecraft` and file paths to each component.
+- `simulation_base.ini` sets the parameters for `SimulationCase`, and file paths to each simulation object.
+- `satellite.ini` sets the parameters for `Spacecraft` and file paths to each component.
## 3. Structure of spacecraft components
**Note:** the structure of components is implemented now. So the following figure is just an idea, and it may be modified.
diff --git a/Specifications/Simulation/Spec_MonteCarloSimulation.md b/Specifications/Simulation/Spec_MonteCarloSimulation.md
index 6edbf93e..1d0662b3 100644
--- a/Specifications/Simulation/Spec_MonteCarloSimulation.md
+++ b/Specifications/Simulation/Spec_MonteCarloSimulation.md
@@ -6,11 +6,12 @@
- The `Monte Carlo Simulation` feature of S2E provides a framework for Monte Carlo simulation
2. Related files(TBW)
- - `src/Simulation/MCSim`
- - `InitParameter`: A class to initialize randomized parameters
- - `MCSimExecutor`: The main class for Monte Carlo simulation
- - `SimulationObject`:
- - `data/SampleSat/ini/MCSim.ini`
+ - `src/simulation/monte_carlo_simulation`
+ - `initialize_monte_carlo_parameters`: A class to initialize randomized parameters
+ - `initialize_monte_carlo_simulation`
+ - `monte_carlo_simulation_executor`: The main class for Monte Carlo simulation
+ - `simulation_object`:
+ - `data/sample/initialize_files/sample_simulation_base.ini`
3. How to use
- Read [How to use Monte Carlo simulation](../../Tutorials/HowToUseMonteCarloSimulation.md)
diff --git a/Tutorials/HowToAddComponents.md b/Tutorials/HowToAddComponents.md
index 493308d3..864b9906 100644
--- a/Tutorials/HowToAddComponents.md
+++ b/Tutorials/HowToAddComponents.md
@@ -5,13 +5,15 @@
- In the [How To Make New Simulation Scenario](./HowToMakeNewSimulationScenario.md) tutorial, we have made an `s2e-user` directory for our simulation scenario.
- This tutorial explains how to add components to your scenario.
- A similar procedure is available for other components in the `s2e-core`.
+ - Please see the components listed in the [components directory](https://github.com/ut-issl/s2e-core/tree/develop/src/components).
- The supported version of this document
- Please confirm that the version of the documents and s2e-core is compatible.
## 2. Add a Gyro sensor
-- This chapter explains how to add a gyro sensor component to your `s2e-user` simulation case.
+- This chapter explains how to add a gyro sensor component to your `s2e-user` simulation case step by step.
+- Users can find the sample code of this section in [s2e-user-example/sample/how-to-add-components](https://github.com/ut-issl/s2e-user-example/tree/sample/how-to-add-components).
1. Open & edit `user_components.hpp`
- Add the following descriptions at the one line below of `#include `
diff --git a/Tutorials/HowToAddControlAlgorithms.md b/Tutorials/HowToAddControlAlgorithms.md
index 6fa4b232..132bf018 100644
--- a/Tutorials/HowToAddControlAlgorithms.md
+++ b/Tutorials/HowToAddControlAlgorithms.md
@@ -1,26 +1,27 @@
# How To Add Control Algorithms
## 1. Overview
-- In the [How To Make New Components](./HowToMakeNewComponents.md) tutorial, we have newly made components emulating codes in [s2e-core](https://github.com/ut-issl/s2e-core) and adding the new components into our simulation scenario.
+- In the [How To Make New Components](./HowToMakeNewComponents.md) tutorial, we have newly made components emulating codes and adding the new components into our simulation scenario.
- Now we can simulate the behavior of spacecraft **free motion** and emulate the behavior of sensors and actuators.
-- This tutorial explains how to add a **Control Algorithm** into the simulation scenario.
-- For a practical satellite project, we should implement the control algorithm as actual flight software like [C2A](https://github.com/ut-issl/c2a-core) into the S2E. However, using actual flight software is usually overdoing for use cases as research, the initial phase of satellite projects.
+- This tutorial explains how to add a **Control Algorithm** to the simulation scenario.
+- For a practical satellite project, we should implement the control algorithm as actual flight software like [C2A](https://github.com/ut-issl/c2a-core) into the S2E. However, using actual flight software is usually overdoing for use cases such as research and the initial phase of satellite projects.
- So, we introduce the following three methods, and users can choose a suitable method.
- - Direct method: Directly control physical quantity without sensors, actuators, and their noises
- - For theoretical researches and preliminary analysis for satellite projects
- - Component method: Control using sensors and actuators without flight S/W framework
- - For engineering researches and preliminary analysis for satellite projects
- - From v6.0.0, we have `ideal` and `real` directories in the `s2e-core/src/components`. Users can use `ideal` components for early stage of the analysis and can use `real` components for more detailed analysis. Mixing these components is also possible.
- - Flight S/W method: Control using sensors and actuators with flight S/W framework
+ - `Direct method`: Directly control physical quantity without sensors, actuators, and their noises
+ - For theoretical research and preliminary analysis for satellite projects
+ - `Component method`: Control using sensors and actuators without flight S/W framework
+ - We can include sensing and actuation noise.
+ - For engineering research and preliminary analysis for satellite projects
+ - From v6.0.0, we have `ideal` and `real` directories in the `s2e-core/src/components`. Users can use `ideal` components for the early stage of the analysis and can use `real` components for more detailed analysis. Mixing these components is also possible.
+ - `Flight S/W method`: Control using sensors and actuators with flight S/W framework
- For actual satellite projects
- The supported version of this document
- - Please confirm that the version of the documents and s2e-core is compatible.
+ - Please confirm that the version of the documents and s2e-core are compatible.
## 2. Direct method
- This chapter introduces how to add a control algorithm without sensors and actuators.
- This method directly measures the satellite's physical quantity and generates torque and force acting on the satellite.
- To do that, users need to edit the `Update` function in the `UserSat.cpp`.
- - A sample code is in `./Tutorials/SampleCodes/control_algorithm/direct_method/user_satellite.cpp`
+ - A sample code is in [s2e-user-example/sample/how-to-add-control-algorithm-direct-method](https://github.com/ut-issl/s2e-user-example/tree/sample/how-to-add-control-algorithm-direct-method)
- The `UserSatellite` class already has satellite attitude, orbit, and local environment information since it inherits the `Spacecraft` base class. So users can easily access these values.
- To measure physical quantities, users can use getter functions defined in the `Attitude`, `Orbit`, and `LocalEnvironment` classes as `dynamics_->GetAttitude().GetAngularVelocity_b_rad_s()`.
- To generate torque and force, users can use `dynamics_->AddTorque_b_Nm` and `dynamics_->AddForce_b_N`.
@@ -36,11 +37,13 @@
## 3. Component method: Using ideal components
- TBW
+- Users can refer the [s2e-ff](https://github.com/ut-issl/s2e-ff/tree/feature/example-three-along-track-ff-with-control) as an example of the ideal component method.
+
## 4. Component method: Using real components
- This chapter introduces a method to add a control algorithm using realistic sensors and actuators. - This method measures a satellite's physical quantity via sensors, generates torque and force via actuators, and executes control algorithms on OBC.
- This tutorial assumes the spacecraft has a three-axis gyro sensor, a reaction wheel, and an OBC.
-- The sample codes are in `SampleCodes/control_algorithm/component_method/`
+- The sample codes are in [s2e-user-example/sample/how-to-add-control-algorithm-using-real-component](https://github.com/ut-issl/s2e-user-example/tree/sample/how-to-add-control-algorithm-using-real-component).
- Firstly, users need to make the `UserOnBoardComputer` class to emulate the OBC.
- Copy the `user_on_board_computer` files to the `s2e-user/src/components` from the `component_method/src/components`, and add the `user_on_board_computer.cpp` to the `set(SOURCE_FILES)` in the `CMakeLists.txt` to compile it.
- The `UserOnBoardComputer` class has the `UserComponents` class as a member, and users can access all components to get sensing information or set the output of actuators.
@@ -63,3 +66,4 @@
## 5. FlightSW method: Control algorithm within C2A
- TBW
+- Users can refer the [s2e-aobc](https://github.com/ut-issl/s2e-aobc) as an example of the flight software method.
diff --git a/Tutorials/HowToIntegrateC2A.md b/Tutorials/HowToIntegrateC2A.md
index 3d14af9b..4c2821ff 100644
--- a/Tutorials/HowToIntegrateC2A.md
+++ b/Tutorials/HowToIntegrateC2A.md
@@ -2,34 +2,34 @@
## 1. Overview
- [C2A](https://github.com/ut-issl/c2a-core) (Command Centric Architecture) is an architecture for spacecraft flight software developed by [ISSL](https://www.space.t.u-tokyo.ac.jp/nlab/index.html).
-- S2E can execute [C2A](https://github.com/ut-issl/c2a-core) as a flight software for onboard algorithm development and debugging.
+- S2E can execute [C2A](https://github.com/ut-issl/c2a-core) as flight software for onboard algorithm development and debugging.
- This document describes how to integrate the C2A within S2E.
- Notes
- C2A is written in C language, but S2E builds C2A as C++.
- The supported version of this document
- - Please confirm that the version of the documents and s2e-core is compatible.
+ - Please confirm that the version of the documents and s2e-core are compatible.
## 2. Overview of C2A execution in S2E
-- Directory construction
+- Directory Construction
- Make `FlightSW` directory at same directory with `s2e-core` and `s2e-user`.
- Make a `c2a-user` directory in `FlightSW` and set the C2A source code you want to use.
```
- ├─ExtLibraries
- ├─FlightSW
- │ └─c2a-user
- │ └─src_user
- │ └─src_core
- ├─s2e-core
- └─s2e-user
+ ├─ FlightSW
+ │ └─ c2a-user
+ │ └─ src_user
+ │ └─ src_core
+ └─ s2e-user-example
+ ├─ s2e-core
+ └─ ExtLibraries
```
- Edit `s2e-user/CMakeLists.txt` as follows.
- `set(C2A_NAME "c2a_oss")`
- Edit the directory name `c2a_oss` according to your situation.
- - In the case of above directory structure, you need to edit as `c2a-user`
+ - In the case of the above directory structure, you need to edit as `c2a-user`
- `option(USE_C2A "Use C2A" OFF)`
- Turn on the `USE_C2A` flag as `option(USE_C2A "Use C2A" ON)`
- Notes
- - In the default setting of S2E, C2A is built but isn't executed. To execute the C2A, users need to add a on board computer, which can execute the C2A.
+ - In the default setting of S2E, C2A is built but isn't executed. To execute the C2A, users need to add an onboard computer, which can execute the C2A.
- The `s2e-core` has the [ObcWithC2a](https://github.com/ut-issl/s2e-core/blob/develop/src/components/real/cdh/on_board_computer_with_c2a.hpp) class as a component, and users can use it to execute the C2A.
- Users can use the `ObcWithC2a` class in the `UserComponents` class, the same as other components.
- Build the `s2e_user`
@@ -38,12 +38,11 @@
## 3. How to build C2A in S2E with the sample codes
- Sample codes
- - A sample of s2e-user: [s2e-user-for-c2a-core](https://github.com/ut-issl/s2e-user-for-c2a-core)
+ - A sample of s2e-user: [s2e-user-example/sample/how-to-integrate-c2a](https://github.com/ut-issl/s2e-user-example/tree/sample/how-to-integrate-c2a)
- A sample of c2a-user: [C2A minimum user](https://github.com/ut-issl/c2a-core/tree/develop/Examples/minimum_user) in `c2a-core`.
+
- Preparing development environment
- - Clone the `s2e-core v6.0.1`.
- - Please set the environment for that the s2e-core can work without C2A.
- - Clone `s2e-user-for-c2a-core v2.0.0` at same directory with `s2e-core`.
+ - Clone the `s2e-user-example` and switch the branch to `sample/how-to-integrate-c2a`.
- Make `FlightSW` directory at same directory with `s2e-core`.
- Clone `c2a-core v3.8.0` in the `FlightSW` directory.
- Execute setup script
@@ -53,7 +52,17 @@
- **For users who don't use Windows**
- open `c2a-core/Examples/minimum_user/CMakeLists.txt` and edit `option(USE_SCI_COM_WINGS "Use SCI_COM_WINGS" ON)` to `option(USE_SCI_COM_WINGS "Use SCI_COM_WINGS" OFF)`
- This setting turns off the feature to communicate with [WINGS](https://github.com/ut-issl/wings) ground station. Currently, this feature is available only for Windows users.
- - Build and execute the `s2e-user-for-c2a-core`.
+ - Please check the following directory construction
+ ```
+ ├─ FlightSW
+ │ └─ c2a-core
+ │ └─ Examples
+ │ └─ minimum_user
+ └─ s2e-user-example
+ ├─ s2e-core
+ └─ ExtLibraries
+ ```
+ - Build and execute the `s2e-user-example`.
- Users can see the following output in a terminal. The `CYCLE: TOTAL` value is incremented.
@@ -83,20 +92,21 @@
# 5. Example of S2E-C2A communication
-- This section shows an example of communication between a component in S2E and an application in C2A. The sample codes are in `Tutorials/SampleCodes/c2a_integration`.
+- This section shows an example of communication between a component in S2E and an application in C2A.
+- The sample codes
+ - S2E: [s2e-user-example/sample/how-to-integrate-c2a](https://github.com/ut-issl/s2e-user-example/tree/sample/how-to-integrate-c2a)
+ - C2A: [Tutorials/SampleCodes/c2a_integration/](./SampleCodes/c2a_integration/c2a_src_user/)
- Preparation
- See `Ch. 3 How to build C2A in S2E with the sample codes`.
- Modification of the S2E side
- Users can use the [ExampleSerialCommunicationWithObc](https://github.com/ut-issl/s2e-core/blob/v6.0.0/src/components/examples/example_serial_communication_with_obc.hpp) class in `s2e-core` as a test component to communicate with C2A.
- - Please refer the sample codes in `Tutorials/SampleCodes/c2a_integration/s2e_src`.
- - The directory structure of `s2e_src` is same with that of `s2e-user-for-c2a-core`.
- - Add `ExampleSerialCommunicationWithObc` as a component in `c2a_core_sample_components.cpp and .hpp`.
- - Or simply just copy the source codes in `c2a_integration/s2e_src` to `s2e-user-for-c2a-core`.
+ - Please refer the sample codes in [s2e-user-example/sample/how-to-integrate-c2a](https://github.com/ut-issl/s2e-user-example/tree/sample/how-to-integrate-c2a).
+ - Add `ExampleSerialCommunicationWithObc` as a component in `user_components.cpp and .hpp`.
- In this example, the `ObcWithC2a` is executed as 1kHz, and the `ExampleSerialCommunicationWithObc` is executed as 1Hz.
- Modification of the C2A side
- Please refer the sample codes in `Tutorials/SampleCodes/c2a_integration/c2a_src_user`.
- - The directory structure of `c2a_src_user` is same with that of `c2a-core/Examples/minimum_user/src/src_user`.
- - We need to add a new driver instance application to communicate with the `EXP` component.
+ - The directory structure of `c2a_src_user` is the same with that of `c2a-core/Examples/minimum_user/src/src_user`.
+ - We need to add a new driver instance application to communicate with the `ExampleSerialCommunicationWithObc` component.
- Copy `Application/DriverInstances/di_s2e_uart_test.c and .h`
- Edit `CMakeLists.txt` in the Application directory to add `di_s2e_uart_test.c` as a compile target.
- Edit `app_registry.c, h` and `app_headers.h` in the `Application` directory to register the applications of `di_s2e_uart_test`.
diff --git a/Tutorials/HowToMakeNewComponents.md b/Tutorials/HowToMakeNewComponents.md
index 251309aa..c0079743 100644
--- a/Tutorials/HowToMakeNewComponents.md
+++ b/Tutorials/HowToMakeNewComponents.md
@@ -19,7 +19,7 @@
- The main features of the components such as observation, generate force, noise addition, communication, etc... should be written in this function.
- `PowerOffRoutine` is also important especially for actuators. This function is called when the component power line is turned off. Users can stop force and torque generation and initialize the component states.
- Power related functions
- - `SetPowerState`, `GetCurrent` are power related functions. If you want to emulate power consumption and switch control, you need to use the functions.
+ - `SetPowerState` and `GetCurrent` are power related functions. If you want to emulate power consumption and switch control, you need to use the functions.
- `ILoggable` class
- This base class has two important virtual functions `GetLogHeader` and `GetLogValue`, for CSV log output.
- These functions are registered into the log output list when the components are added in `UserComponents::LogSetUp`
@@ -28,29 +28,23 @@
- These base classes also support a feature to execute HILS function.
-## 3. Make a simple clock sensor
+## 3. Make a simple clock sensor without initialize file
- This chapter explains how to make a simple clock sensor, which observes the simulation elapsed time with a bias noise.
+- Users can find the sample codes in [s2e-user-example/sample/how-to-make-new-components](https://github.com/ut-issl/s2e-user-example/tree/sample/how-to-make-new-components).
+ - The sample codes already including the initialize file for the `ClockSensor`. Please edit the code a bit to learn the procedure step by step.
-1. Copy the following files in the directory `./Tutorials/SampleCode/clock_sensor` to the directory `s2e-user/src/components`.
- - `clock_sensor.cpp`
- - `clock_sensor.hpp`
+1. The `clock_sensor.cpp, .hpp` are created in the `components` directory.
+ - The `ClockSensor` class counts clock with a constant bias noise.
+ - The class inherits the `Component` and the `ILoggable` base classes as explained above.
-1. Edit `./s2e-user/CMakeList.txt` to add target source files for the compiler. Please add the following description in `set(SOURCE_FILES)`
+1. The `user_components.hpp` and `user_components.cpp` are edit similar procedure with the [How To Add Components](./HowToAddComponents.md)
- ```
- src/components/clock_sensor.cpp
- ```
-
-1. Build `s2e-user` and check there is no error.
-
-1. Edit `user_components.hpp` and `user_components.cpp` as referring [How To Add Components](./HowToAddComponents.md)
-
- - The constructor of the `ClockSensor` requires arguments as `prescaler`, `clock_generator`, `simulation_time`, and `bias_sec`.
- - `prescaler` and `bias_sec` are user setting parameters for the sensor, and you can freely set these values.
+ - The constructor of the `ClockSensor` requires arguments as `prescaler`, `clock_generator`, `simulation_time`, and `bias_s`.
+ - `prescaler` and `bias_s` are user setting parameters for the sensor, and you can freely set these values.
- `clock_generator` is an argument for the `Component` base class.
- - `simulation_time` is a specific argument for the `ClockSensor` to get time information. `SimulationTime` class is managed in the `GlobalEnvironment`, and the `GlobalEnvironment` is instantiated in the `SimulationCase` class.
- - You need to edit the `user_components.cpp` as follows.
+ - `simulation_time` is a specific argument for the `ClockSensor` to get true time information. The `SimulationTime` class is managed in the `GlobalEnvironment`, and the `GlobalEnvironment` is instantiated in the `SimulationCase` class.
+ - We need to add the following codes to `user_components.cpp`.
- Instantiate the `ClockSensor` in the constructor.
```c++
clock_sensor_ = new ClockSensor(10, clock_generator, global_environment->GetSimulationTime(), 0.001);
@@ -66,29 +60,19 @@
1. Build `s2e-user` and execute it
-1. Check the log file to confirm the output of the `clock_sensor`
- - The output of the clock sensor has an offset error, and the update frequency is decided by the `prescaler` and the `component_update_period_s` in the base ini file.
+1. Check the log file to confirm the output of the `clock_sensor_observed_time[sec]`
+ - The output of the clock sensor has an offset error defined by the `bias_s` value, and the update frequency is decided by the `prescaler` and the `component_update_period_s` in the base ini file.
## 4. Make an initialize file for the clock sensor
- Usually, we want to change the parameters of components such as noise properties, mounting coordinates, and others without rebuilding. So this section explains how to make an initialize file for the `ClockSensor`.
-1. Copy the following files in the directory `./Tutorials/SampleCode/clock_sensor` to the directory `s2e-user/src/components`.
- - `initialize_clock_sensor.cpp`
- - `initialize_clock_sensor.hpp`
-
-1. Edit `./s2e-user/CMakeList.txt` to add target source files for the compiler. Please add the following description in `set(SOURCE_FILES)`
-
- ```
- src/components/initialize_clock_sensor.cpp
- ```
-
+1. The initialize function `InitClockSensor` is defined in the `clock_sensor.hpp`.
+ - The initialize function requires arguments as `clock_generator`, `simulation_time`, and `file_name`.
+ - `clock_generator` and `simulation_time` are same argument with the constructor of the `ClockGenerator`.
+ - `file_name` is the file path to the initialize file for the `ClockSensor`.
+
1. Edit the `user_components.hpp` and `user_components.cpp` as follows
- - `user_components.hpp`
- - Replace include files from `clock_sensor.hpp` to as follows
- ```c++
- #include "../../components/initialize_clock_sensor.hpp"
- ```
- `user_components.cpp`
- Edit making instance of the `clock_sensor` at the constructor
```c++
@@ -97,14 +81,18 @@
configuration_->main_logger_->CopyFileToLogDirectory(file_name);
clock_sensor_ = new ClockSensor(InitClockSensor(clock_generator, global_environment->GetSimulationTime(), file_name));
```
+ - The first line get the file path of the initialize file of the clock sensor.
+ - The second line copy the initialize file to the log output directory to save the simulation setting.
+ - The third line make the instance of the `ClockSensor`.
-1. Copy `clock_sensor.ini` into `s2e-user/data/initialize_files/components` from `./Tutorial/SampleCodes/clock_sensor`
+1. Make `clock_sensor.ini` into `s2e-user/data/initialize_files/components` from `./Tutorial/SampleCodes/clock_sensor`
1. Edit `user_satellite.ini` to add the following line at the [COMPONENT_FILES] section of the file
```c++
- clock_sensor_file = ../../data/initialize_files/components/clock_sensor.ini
+ clock_sensor_file = INI_FILE_DIR_FROM_EXE/components/clock_sensor.ini
```
+ - The keyword `INI_FILE_DIR_FROM_EXE` is defined in the `CMakeList.txt` to handle the relative path to the initialize files.
1. Build `s2e-user` and execute it
diff --git a/Tutorials/HowToMakeNewSimulationScenario.md b/Tutorials/HowToMakeNewSimulationScenario.md
index 5ebde17d..cc0cb0ee 100644
--- a/Tutorials/HowToMakeNewSimulationScenario.md
+++ b/Tutorials/HowToMakeNewSimulationScenario.md
@@ -8,76 +8,99 @@
- Source codes for the `main`
- Source codes for `simulation scenario`
- Source codes for `components` if the target spacecraft has components, which strongly depends on your project.
- - Initialize files
- - Compile setting files as [CMake files](https://cmake.org/), [Visual Studio Solution files](https://visualstudio.microsoft.com/downloads/), or others.
+ - `Initialize files`
+ - `Compile setting` files as [CMake files](https://cmake.org/), [Visual Studio Solution files](https://visualstudio.microsoft.com/downloads/), or others.
- This tutorial explains an example of how to make `s2e-user` repository and execute it.
- The supported version of this document
- Please confirm that the version of the documents and `s2e-core` is compatible.
-## 2. Setup S2E_CORE
+## 2. Structure of S2E-USER directory
+ - We provides a sample of a s2e-user repository as [s2e-user-example](https://github.com/ut-issl/s2e-user-example).
+ - The repository is constructed as follows.
+ - The repository includes `s2e-core` by using `git submodule` feature.
+ - The `ExtLibraries` for the user side repository should be generated by using the `CMake` files in the `s2e-core`.
-1. Clone [s2e-core](https://github.com/ut-issl/s2e-core) repository in a working directory.
-
-2. Download mandatory `ExtLibraries` (CSPICE and NRLMSISE-00).
- - Please see a `How To Compile` document suit wity your platform.
```
- └─s2e-core
- └─ExtLibraries
- └─ cspice
- └─ GeoPotential
- └─ nrlmsise00
+ └─ s2e-user-example
+ └─ src
+ └─ data
+ └─ s2e-core (git submodule)
+ └─ ExtLibraries (generated by the following procedure)
+ └─ other files
```
-## 3. Setup & Compile s2e-user
+## 3. Setup s2e-user-example
-1. Make a new directory `s2e-user`. It will be a root directory of s2e-user.
- ```
- └─s2e-user
- └─s2e-core
- └─ExtLibraries
- ```
-**NOTE** This directory structure is an example. Users can use `s2e-core` as `git submodule` as shown in [S2E-FF](https://github.com/ut-issl/s2e-ff).
+1. Clone [s2e-user-example](https://github.com/ut-issl/s2e-user-example) repository in a working directory.
+ - Because the repository includes [s2e-core](https://github.com/ut-issl/s2e-core) with the `git submodule`, please use the following commands to construct the directory.
+ ```
+ $ git clone git@github.com:ut-issl/s2e-user-example.git
+ $ cd s2e-user-example/
+ $ git submodule init
+ $ git submodule update
+ ```
+ Or use the following command to clone the repository.
+ ```
+ $ git clone --recursive git@github.com:ut-issl/s2e-user-example.git
+ ```
-2. Copy directories and files in the `./Tutorials/SampleCodes/s2e-user`.
+2. Download mandatory `ExtLibraries` (CSPICE and NRLMSISE-00).
+ - Users need to use the `CMakeList.txt` in the `s2e-user-example/s2e-core/ExtLibraries` to download the mandatory external libraries.
+ - The construction procedure is same with the s2e-core. Please see a `How To Build` document suit with your platform.
+ ```
+ └─ s2e-user-example
+ └─ src
+ └─ data
+ └─ s2e-core (git submodule)
+ └─ ExtLibraries
+ └─ CMakeLists.txt (Use this file in this step)
+ └─ ExtLibraries (This directory is generated by this step)
+ └─ cspice
+ └─ GeoPotential
+ └─ nrlmsise00
+ ```
-3. According to the `How to compile` document, open the `s2e-user/CMakeList.txt` and build the s2e-user.
+3. According to the `How To Build` document, use the `s2e-user-example/CMakeList.txt` and build the s2e-user.
4. Execute and check the `s2e-user/data/logs`.
-5. Similar to [Getting Started](./GettingStarted.md), you can edit initialize files and check the log file .
+5. Similar to [Getting Started](./GettingStarted.md), you can edit initialize files in `s2e-user-example/data/initialize_files` and check the log file.
**Note:** Users can use other characters instead of `user` for a practical case. For example, you can name it `s2e_equuleus` to indicate the EQUULEUS spacecraft project.
-## 4. Overview of S2E_USER
+## 4. Overview of S2E-USER-EXAMPLE
-- This chapter explains the overview of `s2e-user` in the `SampleCodes` directory.
+- This chapter explains the overview of the `main` branch of the `s2e-user-example`.
- The files in the directory are as follows. From here, the detail of each file is described.
```
- └─s2e-user
- └─CMakeLists.txt
- └─CMakeSetting.json
- └─data
- └─initialize_files
- └─logs
- └─src
- └─simulation
- └─case
- └─user_case.cpp
- └─user_case.hpp
- └─Spacecraft
- └─user_components.cpp
- └─user_components.hpp
- └─user_satellite.cpp
- └─user_satellite.hpp
- └─s2e_user.cpp
+ └─ s2e-user-example
+ └─ CMakeLists.txt
+ └─ CMakeSetting.json
+ └─ data
+ └─ initialize_files
+ └─ logs
+ └─ src
+ └─ simulation
+ └─ case
+ └─ user_case.cpp
+ └─ user_case.hpp
+ └─ Spacecraft
+ └─ user_components.cpp
+ └─ user_components.hpp
+ └─ user_satellite.cpp
+ └─ user_satellite.hpp
+ └─ s2e_user.cpp
+ └─ s2e-core (git submodule)
```
+
1. `CMakeLists.txt` and `CMakeSetting.json`
- `CMakeLists.txt` is a [CMake file](https://cmake.org/) for a compile setting.
- Details of description rules for CMake files can be searched on the internet, so please refer to them.
- - Of course, when you add new source files, you have to edit the CMake file to compile them.
+ - When you add new source files, the new files is automatically included as the build target. If you do not include them, please add them to excluding list in the `CMakeList.txt`.
- `CMakeSetting.json ` is a compile setting file for Visual Studio.
+
2. `data/initialize_files` and `data/logs`
- In the `initialize_files` directory, there are several initialize files.
- The most important initialize file is `user_simulation_base.ini`.
@@ -87,13 +110,17 @@
- Basic files are described in [Getting Started](./GettingStarted.md).
- `logs`
- CSV log files will be outputted here. The output directory is also defined in `user_simulation_base.ini`, so that you can change it.
+
3. `src/s2e_user.cpp`
- This is the main file of this program.
- In this code, `user_simulation_base.ini` is defined as the base file for the simulation, and an instance of the `SimulationCase` class named `UserCase` is created and initialized. And finally, the main routine of the class is executed.
+
4. `src/simulation/case/user_case.cpp, .hpp`
- `UserCase` class is defined here. `UserCase` class inherits the `SimulationCase` base class in the `s2e-core`. The `SimulationCase` class has a `SimulationConfiguration` and `GlobalEnvironment` class. The `UserCase` class has an instance of the `spacecraft` class named as `UserSatellite`.
+
5. `src/simulation/spacecraft/user_satellite.cpp, .hpp`
- `UserSatellite` class is defined here. `UserSatellite` class inherits the `Spacecraft` class in the `s2e-core`. The `Spacecraft` base class has instances of `Dynamics`, `LocalEnvironment`, `Disturbance`, and `Structure`. And the `UserSatellite` class has an instance of `UserComponents`.
+
6. `src/simulation/spacecraft/user_components.cpp, .hpp`
- The `UserComponents` class is defined here. Most users edit this code to custom the S2E for their satellite projects.
- Users select components they want to use from the `s2e-core/src/components`.
diff --git a/Tutorials/HowToSimulateMultipleSatellites.md b/Tutorials/HowToSimulateMultipleSatellites.md
index 06c206dd..f162bc55 100644
--- a/Tutorials/HowToSimulateMultipleSatellites.md
+++ b/Tutorials/HowToSimulateMultipleSatellites.md
@@ -3,22 +3,22 @@
## 1. Overview
- S2E can simulate multiple satellites.
- This document describes how to simulate multiple satellites.
-- For the sample codes, please see `./Tutorials/SampleCodes/multiple_satellites`
+- For the sample codes, please see [s2e-user-example/sample/how-to-simulate-multiple-satellites](https://github.com/ut-issl/s2e-user-example/tree/sample/how-to-simulate-multiple-satellites).
- The supported version of this document
- - Please confirm that the version of the documents and s2e-core is compatible.
+ - Please confirm that the version of the documents and s2e-core are compatible.
## 2. How to add a new satellite
1. Edit `ini` files
1. Add `ini` files for the new satellite.
- `satellite.ini`, `disturbance.ini`, `local_environment.ini`, `structure.ini` are needed.
- 2. Register the ini file for the new satellite in `simulation_base.ini`
+ 2. Register the `ini` file for the new satellite in `simulation_base.ini`
- The arguments of `satellite_file` are used as satellite ID in simulation.
```
[SIMULATION_SETTINGS]
number_of_simulated_spacecraft = 2
- spacecraft_file(0) = ../../data/initialize_files/user_satellite1.ini
- spacecraft_file(1) = ../../data/initialize_files/user_satellite2.ini
+ spacecraft_file(0) = INI_FILE_DIR_FROM_EXE/user_satellite.ini
+ spacecraft_file(1) = INI_FILE_DIR_FROM_EXE/user_satellite2.ini
```
2. Edit source code
@@ -29,16 +29,16 @@
```
2. Edit `user_case.cpp` to copy the spacecraft related codes as the sample code.
- - Please see sample code for more details.
+ - Please see the sample code for more details.
3. Build and execute the `s2e-user`
-4. You can see the log `spacecraft_angular_velocity_b_x[rad/s]` twice. The first one is angular velocity of `satellite0_`, and the second one is angular velocity of `satellite1_` in the log file.
+4. You can see the log `spacecraft_angular_velocity_b_x[rad/s]` twice. The first one is the angular velocity of `satellite 0`, and the second one is the angular velocity of `satellite 1` in the log file.
## 3. Advanced usage
-- In the sample, the `satellite0_` and the `satellite1_` are completely same, but users can change the setting of these satellites with editing the `ini` files.
+- In the sample, the `satellite0_` and the `satellite1_` are completely the same, but users can change the settings of these satellites with editing the `ini` files.
- Users can change the orbit, initial attitude, satellite structure and so on.
-- Users also can set the different component for the `satellite` 0 and 1, when users define different `UserSatellite` and `UserComponents` class.
+- Users also can set the different components for the `satellite` 0 and 1, when users define different `UserSatellite` and `UserComponents` classes.
- The document to use `relative information` will be written.
- Users can also refer the [S2E-FF](https://github.com/ut-issl/s2e-ff) repository.
diff --git a/Tutorials/HowToUseMonteCarloSimulation.md b/Tutorials/HowToUseMonteCarloSimulation.md
index adb85ca3..65e3d77d 100644
--- a/Tutorials/HowToUseMonteCarloSimulation.md
+++ b/Tutorials/HowToUseMonteCarloSimulation.md
@@ -6,19 +6,19 @@
- The feature provides a framework to randomize arbitrary parameters in each class.
- Users can set the mean value and standard deviation for the randomized parameters with `simulation_base.ini` file of each user.
- Please see the specification document for [Monte Carlo Simulation](../Specifications/Simulation/Spec_MonteCarloSimulation.md) for a detailed description.
-- This tutorial explains how to randomly change the initial value of the angular velocity.
- - There are sample codes in `SampleCodes\monte_carlo_simulation`.
+- This tutorial explains how to randomly change the initial value of the spacecraft angular velocity.
+ - There are sample codes in [s2e-user-example/sample/how-to-use-monte-carlo-simulation](https://github.com/ut-issl/s2e-user-example/tree/sample/how-to-use-monte-carlo-simulation).
- The supported version of this document
- Please confirm that the version of the documents and s2e-core is compatible.
## 2. Edit Simulation Case
-- To use the MCSim, users have to edit their `user_case.hpp` and `user_case.cpp`
+- To use the Monte Carlo simulation, users have to edit their `user_case.hpp` and `user_case.cpp`
- `user_case.hpp`
- Add header including
```c++
#include <./simulation/monte_carlo_simulation/monte_carlo_simulation_executor.hpp>
```
- - Add private member variables for MCSimExecutor and string.
+ - Add private member variables for `MonteCarloSimulationExecutor`.
```c++
MonteCarloSimulationExecutor &monte_carlo_simulator_;
```
@@ -38,7 +38,7 @@
```
- Edit `InitializeTargetObjects` function
- Edit log file name definition and
- - Add MCSim initialization
+ - Add `MonteCarloSimulationExecutor` initialization
```c++
// Monte Carlo Simulation
monte_carlo_simulator_.SetSeed();
@@ -76,7 +76,7 @@
}
```
-## 3. Edit `S2E_USER` code
+## 3. Edit `s2e_user.cpp` code
- To use the Monte Carlo Simulator, users have to edit their `s2e_user.cpp`
- Add header file
```c++
@@ -115,7 +115,7 @@
delete mc_simulator;
```
-## 4. Initialize file for MCSim
+## 4. Initialize file for Monte Carlo simulator
- Edit `user_simulation_base.ini` to add the following description
```c++
diff --git a/Tutorials/SampleCodes/c2a_integration/s2e_src/simulation/spacecraft/c2a_core_sample_components.cpp b/Tutorials/SampleCodes/c2a_integration/s2e_src/simulation/spacecraft/c2a_core_sample_components.cpp
deleted file mode 100644
index ff3ed0b7..00000000
--- a/Tutorials/SampleCodes/c2a_integration/s2e_src/simulation/spacecraft/c2a_core_sample_components.cpp
+++ /dev/null
@@ -1,48 +0,0 @@
-/**
- * @file c2a_core_sample_components.cpp
- * @brief User side components management installed on a spacecraft for C2A-CORE
- */
-
-#include "c2a_core_sample_components.hpp"
-
-#include
-
-#ifdef USE_C2A
-#include "src_user/Settings/port_config.h"
-#endif
-
-C2aCoreSampleComponents::C2aCoreSampleComponents(const Dynamics* dynamics, Structure* structure, const LocalEnvironment* local_environment,
- const GlobalEnvironment* global_environment, const SimulationConfiguration* configuration,
- ClockGenerator* clock_generator)
- : dynamics_(dynamics),
- structure_(structure),
- local_environment_(local_environment),
- global_environment_(global_environment),
- configuration_(configuration) {
-#ifdef USE_C2A
- obc_ = new ObcWithC2a(clock_generator, 100);
- exp_serial_communication_ = new ExampleSerialCommunicationWithObc(clock_generator, 1, 1, obc_);
-
- obc_->ConnectComPort(PORT_CH_RS422_MOBC_EXT, 1024, 1024); // UART通信用にとりあえず繋いでおく
-#endif
-}
-
-C2aCoreSampleComponents::~C2aCoreSampleComponents() {
- delete exp_serial_communication_;
- // OBC must be deleted the last since it has com ports
- delete obc_;
-}
-
-Vector<3> C2aCoreSampleComponents::GenerateForce_b_N() {
- // There is no orbit control component, so it remains 0
- Vector<3> force_b_N(0.0);
- return force_b_N;
-}
-
-Vector<3> C2aCoreSampleComponents::GenerateTorque_b_Nm() {
- // No attitude control component
- Vector<3> torque_b_Nm(0.0);
- return torque_b_Nm;
-}
-
-void C2aCoreSampleComponents::LogSetup(Logger& logger) { UNUSED(logger); }
diff --git a/Tutorials/SampleCodes/c2a_integration/s2e_src/simulation/spacecraft/c2a_core_sample_components.hpp b/Tutorials/SampleCodes/c2a_integration/s2e_src/simulation/spacecraft/c2a_core_sample_components.hpp
deleted file mode 100644
index b4e6713d..00000000
--- a/Tutorials/SampleCodes/c2a_integration/s2e_src/simulation/spacecraft/c2a_core_sample_components.hpp
+++ /dev/null
@@ -1,68 +0,0 @@
-/**
- * @file c2a_core_sample_components.hpp
- * @brief User side components management installed on a spacecraft for C2A-CORE
- */
-
-#ifndef S2E_SIMULATION_SPACECRAFT_C2A_CORE_SAMPLE_COMPONENTS_HPP_
-#define S2E_SIMULATION_SPACECRAFT_C2A_CORE_SAMPLE_COMPONENTS_HPP_
-
-#include
-#include
-#include
-#include
-#include
-
-// include for components
-#include
-#include
-
-/**
- * @class C2aCoreSampleComponents
- * @brief User side components management installed on a spacecraft for C2A-CORE
- */
-class C2aCoreSampleComponents : public InstalledComponents {
- public:
- /**
- * @fn C2aCoreSampleComponents
- * @brief Constructor
- */
- C2aCoreSampleComponents(const Dynamics* dynamics, Structure* structure, const LocalEnvironment* local_environment,
- const GlobalEnvironment* global_environment, const SimulationConfiguration* configuration, ClockGenerator* clock_generator);
-
- /**
- * @fn ~C2aCoreSampleComponents
- * @brief Destructor
- */
- ~C2aCoreSampleComponents();
-
- // Override functions for InstalledComponents
- /**
- * @fn GenerateForce_b_N
- * @brief Return force generated by components in unit Newton in body fixed frame
- */
- libra::Vector<3> GenerateForce_b_N();
- /**
- * @fn GenerateTorque_b_Nm
- * @brief Return torque generated by components in unit Newton-meter in body fixed frame
- */
- libra::Vector<3> GenerateTorque_b_Nm();
- /**
- * @fn LogSetup
- * @brief Setup the logger for components
- */
- void LogSetup(Logger& logger);
-
- private:
- // Components
- ObcWithC2a* obc_; //!< Onboard Computer with C2A
- ExampleSerialCommunicationWithObc* exp_serial_communication_;
-
- // References
- const Dynamics* dynamics_; //!< Dynamics information of the spacecraft
- const Structure* structure_; //!< Structure information of the spacecraft
- const LocalEnvironment* local_environment_; //!< Local environment information around the spacecraft
- const GlobalEnvironment* global_environment_; //!< Global environment information around the spacecraft
- const SimulationConfiguration* configuration_; //!< Simulation settings
-};
-
-#endif // S2E_SIMULATION_SPACECRAFT_C2A_CORE_SAMPLE_COMPONENTS_HPP_
diff --git a/Tutorials/SampleCodes/clock_sensor/clock_sensor.cpp b/Tutorials/SampleCodes/clock_sensor/clock_sensor.cpp
deleted file mode 100644
index 6f309224..00000000
--- a/Tutorials/SampleCodes/clock_sensor/clock_sensor.cpp
+++ /dev/null
@@ -1,30 +0,0 @@
-/**
- * @file clock_sensor.cpp
- * @brief An example to emulate a sensor to measure simulation elapsed time
- */
-
-#include "clock_sensor.hpp"
-
-ClockSensor::ClockSensor(const int prescaler, ClockGenerator* clock_generator, const SimulationTime& simulation_time, const double bias_sec)
- : Component(prescaler, clock_generator), simulation_time_(simulation_time), bias_sec_(bias_sec), time_output_sec_(0.0) {}
-
-void ClockSensor::MainRoutine(const int time_count) {
- UNUSED(time_count);
- time_output_sec_ = simulation_time_.GetElapsedTime_s() + bias_sec_;
-}
-
-std::string ClockSensor::GetLogHeader() const {
- std::string str_tmp = "";
- std::string section = "clock_sensor_";
- str_tmp += WriteScalar(section + "observed_time", "sec");
-
- return str_tmp;
-}
-
-std::string ClockSensor::GetLogValue() const {
- std::string str_tmp = "";
-
- str_tmp += WriteScalar(time_output_sec_);
-
- return str_tmp;
-}
diff --git a/Tutorials/SampleCodes/clock_sensor/clock_sensor.hpp b/Tutorials/SampleCodes/clock_sensor/clock_sensor.hpp
deleted file mode 100644
index ed451a31..00000000
--- a/Tutorials/SampleCodes/clock_sensor/clock_sensor.hpp
+++ /dev/null
@@ -1,54 +0,0 @@
-/**
- * @file clock_sensor.hpp
- * @brief An example to emulate a sensor to measure simulation elapsed time
- */
-
-#ifndef S2E_COMPONENTS_CLOCK_SENSOR_HPP_
-#define S2E_COMPONENTS_CLOCK_SENSOR_HPP_
-
-#include
-#include
-#include
-
-/**
- * @class ClockSensor
- * @brief An example to emulate a sensor to measure simulation elapsed time
- */
-class ClockSensor : public Component, public ILoggable {
- public:
- /**
- * @fn ClockSensor
- * @brief Constructor
- * @param [in] prescaler: Frequency scale factor for update
- * @param [in] clock_generator: Clock generator
- * @param [in] simulation_time: Simulation time information
- * @param [in] bias_sec: Bias value for clock observation [sec]
- */
- ClockSensor(const int prescaler, ClockGenerator* clock_generator, const SimulationTime& simulation_time, const double bias_sec);
-
- private:
- // Override functions for Component
- /**
- * @fn MainRoutine
- * @brief Main routine for sensor observation
- */
- void MainRoutine(const int time_count) override;
-
- // Override ILoggable
- /**
- * @fn GetLogHeader
- * @brief Override GetLogHeader function of ILoggable
- */
- virtual std::string GetLogHeader() const;
- /**
- * @fn GetLogValue
- * @brief Override GetLogValue function of ILoggable
- */
- virtual std::string GetLogValue() const;
-
- const SimulationTime& simulation_time_; //!< Simulation time information
- double bias_sec_; //!< Bias value for clock observation [sec]
- double time_output_sec_; //!< Output of measured time information
-};
-
-#endif // S2E_COMPONENTS_CLOCK_SENSOR_HPP_
diff --git a/Tutorials/SampleCodes/clock_sensor/clock_sensor.ini b/Tutorials/SampleCodes/clock_sensor/clock_sensor.ini
deleted file mode 100644
index 6bed9e7e..00000000
--- a/Tutorials/SampleCodes/clock_sensor/clock_sensor.ini
+++ /dev/null
@@ -1,3 +0,0 @@
-[ClockSensor]
-prescaler = 10 // period = prescaler * CompoUpdateIntervalSec [sec]
-bias_sec = 0.005 // [sec]
diff --git a/Tutorials/SampleCodes/clock_sensor/edited_codes/user_components.cpp b/Tutorials/SampleCodes/clock_sensor/edited_codes/user_components.cpp
deleted file mode 100644
index 4708cb2a..00000000
--- a/Tutorials/SampleCodes/clock_sensor/edited_codes/user_components.cpp
+++ /dev/null
@@ -1,49 +0,0 @@
-/**
- * @file user_components.cpp
- * @brief An example of user side components management installed on a spacecraft
- */
-
-#include "user_components.hpp"
-
-#include
-
-UserComponents::UserComponents(const Dynamics *dynamics, Structure *structure, const LocalEnvironment *local_environment,
- const GlobalEnvironment *global_environment, const SimulationConfiguration *configuration,
- ClockGenerator *clock_generator, const unsigned int spacecraft_id)
- : configuration_(configuration),
- dynamics_(dynamics),
- structure_(structure),
- local_environment_(local_environment),
- global_environment_(global_environment) {
- IniAccess iniAccess = IniAccess(configuration_->spacecraft_file_list_[spacecraft_id]);
-
- obc_ = new OnBoardComputer(clock_generator);
-
- // Clock Sensor
- std::string file_name = iniAccess.ReadString("COMPONENT_FILES", "clock_sensor_file");
- configuration_->main_logger_->CopyFileToLogDirectory(file_name);
- clock_sensor_ = new ClockSensor(InitClockSensor(clock_generator, global_environment->GetSimulationTime(), file_name));
-}
-
-UserComponents::~UserComponents() {
- delete clock_sensor_;
- // OBC must be deleted the last since it has com ports
- delete obc_;
-}
-
-Vector<3> UserComponents::GenerateForce_b_N() {
- // There is no orbit control component, so it remains 0
- Vector<3> force_b_N(0.0);
- return force_b_N;
-}
-
-Vector<3> UserComponents::GenerateTorque_b_Nm() {
- // No attitude control component
- Vector<3> torque_b_Nm(0.0);
- return torque_b_Nm;
-}
-
-void UserComponents::LogSetup(Logger &logger) {
- // Users can set log output when they need component log
- logger.AddLogList(clock_sensor_);
-}
diff --git a/Tutorials/SampleCodes/clock_sensor/edited_codes/user_components.hpp b/Tutorials/SampleCodes/clock_sensor/edited_codes/user_components.hpp
deleted file mode 100644
index 75209381..00000000
--- a/Tutorials/SampleCodes/clock_sensor/edited_codes/user_components.hpp
+++ /dev/null
@@ -1,43 +0,0 @@
-/**
- * @file sample_components.hpp
- * @brief An example of user side components management installed on a spacecraft
- */
-
-#ifndef S2E_SIMULATION_SPACECRAFT_USER_COMPONENTS_HPP_
-#define S2E_SIMULATION_SPACECRAFT_USER_COMPONENTS_HPP_
-
-#include
-#include
-#include
-#include
-#include
-
-// include for components
-#include
-
-#include "../../components/initialize_clock_sensor.hpp"
-
-class UserComponents : public InstalledComponents {
- public:
- UserComponents(const Dynamics *dynamics, Structure *structure, const LocalEnvironment *local_environment,
- const GlobalEnvironment *global_environment, const SimulationConfiguration *configuration, ClockGenerator *clock_generator,
- const unsigned int spacecraft_id);
- ~UserComponents();
- libra::Vector<3> GenerateForce_b_N();
- libra::Vector<3> GenerateTorque_b_Nm();
- void LogSetup(Logger &logger);
-
- private:
- // Components
- OnBoardComputer *obc_; //!< Onboard Computer
- ClockSensor *clock_sensor_;
-
- // States
- const SimulationConfiguration *configuration_; //!< Simulation settings
- const Dynamics *dynamics_; //!< Dynamics information of the spacecraft
- Structure *structure_; //!< Structure information of the spacecraft
- const LocalEnvironment *local_environment_; //!< Local environment information around the spacecraft
- const GlobalEnvironment *global_environment_; //!< Global environment information
-};
-
-#endif // S2E_SIMULATION_SPACECRAFT_USER_COMPONENTS_HPP_
diff --git a/Tutorials/SampleCodes/clock_sensor/edited_codes/user_satellite.ini b/Tutorials/SampleCodes/clock_sensor/edited_codes/user_satellite.ini
deleted file mode 100644
index 0ded4b56..00000000
--- a/Tutorials/SampleCodes/clock_sensor/edited_codes/user_satellite.ini
+++ /dev/null
@@ -1,139 +0,0 @@
-[ATTITUDE]
-// Attitude propagation mode
-// RK4 : Attitude Propagation with RK4 including disturbances and control torque
-// CONTROLLED : Attitude Calculation with Controlled Attitude mode. All disturbances and control torque are ignored.
-propagate_mode = RK4
-
-// Initialize Attitude mode
-// MANUAL : Initialize Quaternion_i2b manually below
-// CONTROLLED : Initialize attitude with given condition. Valid only when Attitude propagation mode is RK4.
-initialize_mode = MANUAL
-
-// Initial angular velocity at body frame [rad/s]
-initial_angular_velocity_b_rad_s(0) = 0.0
-initial_angular_velocity_b_rad_s(1) = 0.0
-initial_angular_velocity_b_rad_s(2) = 0.0
-
-// Initial quaternion inertial frame to body frame (real part, imaginary part)
-// This value also used in INERTIAL_STABILIZE mode of ControlledAttitude
-initial_quaternion_i2b(0) = 0.0
-initial_quaternion_i2b(1) = 0.0
-initial_quaternion_i2b(2) = 0.0
-initial_quaternion_i2b(3) = 1.0
-
-// Initial torque at body frame [Nm]
-// Note: The initial torque added just for the first propagation step
-initial_torque_b_Nm(0) = +0.000
-initial_torque_b_Nm(1) = -0.000
-initial_torque_b_Nm(2) = 0.000
-
-[CONTROLLED_ATTITUDE]
-// Mode definitions
-// INERTIAL_STABILIZE
-// SUN_POINTING
-// EARTH_CENTER_POINTING
-// VELOCITY_DIRECTION_POINTING
-// ORBIT_NORMAL_POINTING
-main_mode = INERTIAL_STABILIZE
-sub_mode = SUN_POINTING
-
-// Pointing direction @ body frame for main pointing mode
-main_pointing_direction_b(0) = 1.0
-main_pointing_direction_b(1) = 0.0
-main_pointing_direction_b(2) = 0.0
-
-// Pointing direction @ body frame for sub pointing mode
-// main_pointing_direction_b and sub_pointing_direction_b should separate larger than 30 degrees.
-sub_pointing_direction_b(0) = 0.0
-sub_pointing_direction_b(1) = 0.0
-sub_pointing_direction_b(2) = 1.0
-
-
-[ORBIT]
-calculation = ENABLE
-logging = ENABLE
-
-// Orbit propagation mode
-// RK4 : RK4 propagation with disturbances and thruster maneuver
-// SGP4 : SGP4 propagation using TLE without thruster maneuver
-// 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
-propagate_mode = RK4
-
-// Orbit initialize mode for RK4, KEPLER, and ENCKE
-// DEFAULT : Use default initialize method (RK4 and ENCKE use pos/vel, KEPLER uses init_mode_kepler)
-// POSITION_VELOCITY_I : Initialize with position and velocity in the inertial frame
-// ORBITAL_ELEMENTS : Initialize with orbital elements
-initialize_mode = POSITION_VELOCITY_I
-
-// Initial value definition for POSITION_VELOCITY_I initialize mode ////////
-initial_position_i_m(0) = -2111769.7723711144
-initial_position_i_m(1) = -5360353.2254375768
-initial_position_i_m(2) = 3596181.6497774957
-
-initial_velocity_i_m_s(0) = 4200.4344740455268
-initial_velocity_i_m_s(1) = -4637.540129059361
-initial_velocity_i_m_s(2) = -4429.2361258448807
-///////////////////////////////////////////////////////////////////////////
-
-// Initial value definition for ORBITAL_ELEMENTS initialize mode ////////
-semi_major_axis_m = 6794500.0
-eccentricity = 0.0015
-inclination_rad = 0.9012
-raan_rad = 0.1411
-argument_of_perigee_rad = 1.7952
-epoch_jday = 2.458940966402607e6
-///////////////////////////////////////////////////////////////////////////////
-
-
-// Settings for SGP4 ///////////////////////////////////////////////
-// TLE
-// Example: ISS
-tle1=1 25544U 98067A 20076.51604214 .00016717 00000-0 10270-3 0 9005
-tle2=2 25544 51.6412 86.9962 0006063 30.9353 329.2153 15.49228202 17647
-// World Geodetic System
-wgs = 2 // 0: wgs72old, 1: wgs72, 2: wgs84
-//////////////////////////////////////////////////////////////////////////
-
-// Settings for relative orbit propagation ////////////////////////////
-// Relative Orbit Update Method (0 means RK4, 1 means STM)
-relative_orbit_update_method = 0
-// RK4 Relative Dynamics model type (only valid for RK4 update)
-// 0: Hill
-relative_dynamics_model_type = 0
-// STM Relative Dynamics model type (only valid for STM update)
-// 0: HCW
-stm_model_type = 0
-// Initial satellite position relative to the reference satellite in LVLH frame[m]
-// * The coordinate system is defined at [PLANET_SELECTION] in SampleSimBase.ini
-initial_relative_position_lvlh_m(0) = 0.0
-initial_relative_position_lvlh_m(1) = 100.0
-initial_relative_position_lvlh_m(2) = 0.0
-// initial satellite velocity relative to the reference satellite in LVLH frame[m/s]
-initial_relative_velocity_lvlh_m_s(0) = 0.0
-initial_relative_velocity_lvlh_m_s(1) = 0.0
-initial_relative_velocity_lvlh_m_s(2) = 0.0
-// information of reference satellite
-reference_satellite_id = 1
-///////////////////////////////////////////////////////////////////////////////
-
-// Settings for Encke mode ///////////
-error_tolerance = 0.0001
-///////////////////////////////////////////////////////////////////////////////
-
-
-[THERMAL]
-calculation = DISABLE
-debug = 0
-thermal_file_directory = ../../data/initialize_files/thermal_csv_files/
-
-[SETTING_FILES]
-local_environment_file = ../../data/initialize_files/user_satellite_local_environment.ini
-disturbance_file = ../../data/initialize_files/user_satellite_disturbance.ini
-structure_file = ../../data/initialize_files/user_satellite_structure.ini
-
-
-[COMPONENT_FILES]
-// Users can add the path for component initialize files here.
-clock_sensor_file = ../../data/initialize_files/components/clock_sensor.ini
diff --git a/Tutorials/SampleCodes/clock_sensor/initialize_clock_sensor.cpp b/Tutorials/SampleCodes/clock_sensor/initialize_clock_sensor.cpp
deleted file mode 100644
index 4983f487..00000000
--- a/Tutorials/SampleCodes/clock_sensor/initialize_clock_sensor.cpp
+++ /dev/null
@@ -1,19 +0,0 @@
-
-/**
- * @file initialize_clock_sensor.cpp
- * @brief Initialize function for ClockSensor class
- */
-
-#include "initialize_clock_sensor.hpp"
-
-#include
-
-ClockSensor InitClockSensor(ClockGenerator* clock_generator, const SimulationTime& simulation_time, const std::string file_name) {
- IniAccess ini_file(file_name);
-
- const double bias_sec = ini_file.ReadDouble("ClockSensor", "bias_sec");
- const int prescaler = ini_file.ReadInt("ClockSensor", "prescaler");
- ClockSensor clock_sensor(prescaler, clock_generator, simulation_time, bias_sec);
-
- return clock_sensor;
-}
diff --git a/Tutorials/SampleCodes/clock_sensor/initialize_clock_sensor.hpp b/Tutorials/SampleCodes/clock_sensor/initialize_clock_sensor.hpp
deleted file mode 100644
index 5c50dc8a..00000000
--- a/Tutorials/SampleCodes/clock_sensor/initialize_clock_sensor.hpp
+++ /dev/null
@@ -1,20 +0,0 @@
-/**
- * @file initialize_clock_sensor.hpp
- * @brief Initialize function for ClockSensor class
- */
-
-#ifndef S2E_COMPONENTS_INITIALIZE_CLOCK_SENSOR_HPP_
-#define S2E_COMPONENTS_INITIALIZE_CLOCK_SENSOR_HPP_
-
-#include "clock_sensor.hpp"
-
-/**
- * @fn InitGyroSensor
- * @brief Initialize functions for gyro sensor without power port
- * @param [in] clock_generator: Clock generator
- * @param [in] simulation_time: Simulation time information
- * @param [in] file_name: Path to the initialize file
- */
-ClockSensor InitClockSensor(ClockGenerator *clock_generator, const SimulationTime &simulation_time, const std::string file_name);
-
-#endif // S2E_COMPONENTS_INITIALIZE_CLOCK_SENSOR_HPP_
diff --git a/Tutorials/SampleCodes/control_algorithm/component_method_real/data/gyro_sensor_xxx.ini b/Tutorials/SampleCodes/control_algorithm/component_method_real/data/gyro_sensor_xxx.ini
deleted file mode 100644
index d5755a62..00000000
--- a/Tutorials/SampleCodes/control_algorithm/component_method_real/data/gyro_sensor_xxx.ini
+++ /dev/null
@@ -1,50 +0,0 @@
-[GYRO_SENSOR_1]
-prescaler = 1
-
-// Quaternion from body frame to component frame
-// Including misalignment
-quaternion_b2c(0) = 0.0
-quaternion_b2c(1) = 0.0
-quaternion_b2c(2) = 0.0
-quaternion_b2c(3) = 1.0
-
-[SENSOR_BASE_GYRO_SENSOR_1]
-// Scale Factor Matrix (3×3)
-// (0) = (0,0), (1) = (0,1), (2) = (0,2),
-scale_factor_c(0) = 1.0
-scale_factor_c(1) = 0.0
-scale_factor_c(2) = 0.0
-scale_factor_c(3) = 0.0
-scale_factor_c(4) = 1.0
-scale_factor_c(5) = 0.0
-scale_factor_c(6) = 0.0
-scale_factor_c(7) = 0.0
-scale_factor_c(8) = 1.0
-
-// Constant bias noise at component frame [rad/s]
-constant_bias_c_rad_s(0) = 1.0e-3
-constant_bias_c_rad_s(1) = -1.0e-3
-constant_bias_c_rad_s(2) = 2.0e-3
-
-// Standard deviation for random walk noise[rad/s]
-random_walk_standard_deviation_c_rad_s(0) = 0.0
-random_walk_standard_deviation_c_rad_s(1) = 0.0
-random_walk_standard_deviation_c_rad_s(2) = 0.0
-
-// Limit of random walk noise[rad/s]
-random_walk_limit_c_rad_s(0) = 0.0
-random_walk_limit_c_rad_s(1) = 0.0
-random_walk_limit_c_rad_s(2) = 0.0
-
-// Standard deviation of normal random noise[rad/s]
-normal_random_standard_deviation_c_rad_s(0) = 0.0e-3
-normal_random_standard_deviation_c_rad_s(1) = 0.0e-3
-normal_random_standard_deviation_c_rad_s(2) = 0.0e-3
-
-// Range [rad/s]
-range_to_constant_rad_s = 5.0 // smaller than Range_to_zero
-range_to_zero_rad_s = 10.0
-
-[POWER_PORT]
-minimum_voltage_V = 3.3 // V
-assumed_power_consumption_W = 1.0 //W
diff --git a/Tutorials/SampleCodes/control_algorithm/component_method_real/data/reaction_wheel_xxx.ini b/Tutorials/SampleCodes/control_algorithm/component_method_real/data/reaction_wheel_xxx.ini
deleted file mode 100644
index beba51e4..00000000
--- a/Tutorials/SampleCodes/control_algorithm/component_method_real/data/reaction_wheel_xxx.ini
+++ /dev/null
@@ -1,65 +0,0 @@
-[REACTION_WHEEL_1]
-// prescaler defines update period of thie component
-// update period = prescaler * step sec
-prescaler = 1
-// prescaler for calculation of RW jitter
-// To calculate the jitter, set the update cycle to about 0.1 ms.
-fast_prescaler = 1
-
-// Moment of inertia of the rotor [kgm^2]
-moment_of_inertia_kgm2 = 5.0e-6
-// Maximum torque [Nm]
-max_output_torque_Nm = 0.001
-// Maximum angular velocity [rpm]
-// The RW can drive (-max_angular_velocity, +max_angular_velocity)
-max_angular_velocity_rpm = 6000.0
-
-// How to determine the direction of RW (DIRECTION or QUATERNION)
-// If you want to consider the phase of RW strictly (e.g. RW jitter), specify QUATERNION.
-// If you do not need to consider the phase of the RW rotation, specify DIRECTION.
-direction_determination_mode = DIRECTION
-// Quaternion from body frame to component frame
-// Definition of component frame : wheel rotation axis = (0 0 1)^T. plus means direction of rotation (output torque is minus direction)
-quaternion_b2c(0) = 0
-quaternion_b2c(1) = 0.70710678118
-quaternion_b2c(2) = 0
-quaternion_b2c(3) = 0.70710678118
-// Direction of axis of the RW at the body fixied frame
-// plus means direction of rotation (output torque is minus direction)
-direction_b(0) = 1.0
-direction_b(1) = 0.0
-direction_b(2) = 0.0
-
-// Position of RW at body frame [m]
-position_b_m(0) = 1.0
-position_b_m(1) = 0.0
-position_b_m(2) = 0.0
-// The control deray[s]
-dead_time_s = 1.0
-// Coefficient of first order lag for driving case
-first_order_lag_coefficient(0) = 2.0
-first_order_lag_coefficient(1) = 0.0
-first_order_lag_coefficient(2) = 0.0
-// Coefficient of first order lag for coasting case
-coasting_lag_coefficient(0) = 2.0
-coasting_lag_coefficient(1) = 0.0
-coasting_lag_coefficient(2) = 0.0
-// For drive initialize
-// They should be zero for normal case
-initial_motor_drive_flag = 0
-initial_angular_velocity_rad_s = 0.0
-
-//Parameters for calculate RW jitter
-jitter_calculation = DISABLE
-jitter_logging = DISABLE
-radial_force_harmonics_coefficient_file = ../../data/sample/initialize_files/components/rw_disturbance_csv_files/radial_force_harmonics_coefficients.csv
-radial_torque_harmonics_coefficient_file = ../../data/sample/initialize_files/components/rw_disturbance_csv_files/radial_torque_harmonics_coefficients.csv
-harmonics_degree = 12
-considers_structural_resonance = DISABLE
-structural_resonance_frequency_Hz = 585.0 //[Hz]
-damping_factor = 0.1 //[ ]
-bandwidth = 0.001 //[ ]
-
-[POWER_PORT]
-minimum_voltage_V = 3.3 // V
-assumed_power_consumption_W = 1.0 //W
diff --git a/Tutorials/SampleCodes/control_algorithm/component_method_real/data/user_satellite.ini b/Tutorials/SampleCodes/control_algorithm/component_method_real/data/user_satellite.ini
deleted file mode 100644
index 360a626b..00000000
--- a/Tutorials/SampleCodes/control_algorithm/component_method_real/data/user_satellite.ini
+++ /dev/null
@@ -1,140 +0,0 @@
-[ATTITUDE]
-// Attitude propagation mode
-// RK4 : Attitude Propagation with RK4 including disturbances and control torque
-// CONTROLLED : Attitude Calculation with Controlled Attitude mode. All disturbances and control torque are ignored.
-propagate_mode = RK4
-
-// Initialize Attitude mode
-// MANUAL : Initialize Quaternion_i2b manually below
-// CONTROLLED : Initialize attitude with given condition. Valid only when Attitude propagation mode is RK4.
-initialize_mode = MANUAL
-
-// Initial angular velocity at body frame [rad/s]
-initial_angular_velocity_b_rad_s(0) = 0.02
-initial_angular_velocity_b_rad_s(1) = 0.0
-initial_angular_velocity_b_rad_s(2) = 0.0
-
-// Initial quaternion inertial frame to body frame (real part, imaginary part)
-// This value also used in INERTIAL_STABILIZE mode of ControlledAttitude
-initial_quaternion_i2b(0) = 0.0
-initial_quaternion_i2b(1) = 0.0
-initial_quaternion_i2b(2) = 0.0
-initial_quaternion_i2b(3) = 1.0
-
-// Initial torque at body frame [Nm]
-// Note: The initial torque added just for the first propagation step
-initial_torque_b_Nm(0) = +0.000
-initial_torque_b_Nm(1) = -0.000
-initial_torque_b_Nm(2) = 0.000
-
-[CONTROLLED_ATTITUDE]
-// Mode definitions
-// INERTIAL_STABILIZE
-// SUN_POINTING
-// EARTH_CENTER_POINTING
-// VELOCITY_DIRECTION_POINTING
-// ORBIT_NORMAL_POINTING
-main_mode = INERTIAL_STABILIZE
-sub_mode = SUN_POINTING
-
-// Pointing direction @ body frame for main pointing mode
-main_pointing_direction_b(0) = 1.0
-main_pointing_direction_b(1) = 0.0
-main_pointing_direction_b(2) = 0.0
-
-// Pointing direction @ body frame for sub pointing mode
-// main_pointing_direction_b and sub_pointing_direction_b should separate larger than 30 degrees.
-sub_pointing_direction_b(0) = 0.0
-sub_pointing_direction_b(1) = 0.0
-sub_pointing_direction_b(2) = 1.0
-
-
-[ORBIT]
-calculation = ENABLE
-logging = ENABLE
-
-// Orbit propagation mode
-// RK4 : RK4 propagation with disturbances and thruster maneuver
-// SGP4 : SGP4 propagation using TLE without thruster maneuver
-// 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
-propagate_mode = RK4
-
-// Orbit initialize mode for RK4, KEPLER, and ENCKE
-// DEFAULT : Use default initialize method (RK4 and ENCKE use pos/vel, KEPLER uses init_mode_kepler)
-// POSITION_VELOCITY_I : Initialize with position and velocity in the inertial frame
-// ORBITAL_ELEMENTS : Initialize with orbital elements
-initialize_mode = POSITION_VELOCITY_I
-
-// Initial value definition for POSITION_VELOCITY_I initialize mode ////////
-initial_position_i_m(0) = -2111769.7723711144
-initial_position_i_m(1) = -5360353.2254375768
-initial_position_i_m(2) = 3596181.6497774957
-
-initial_velocity_i_m_s(0) = 4200.4344740455268
-initial_velocity_i_m_s(1) = -4637.540129059361
-initial_velocity_i_m_s(2) = -4429.2361258448807
-///////////////////////////////////////////////////////////////////////////
-
-// Initial value definition for ORBITAL_ELEMENTS initialize mode ////////
-semi_major_axis_m = 6794500.0
-eccentricity = 0.0015
-inclination_rad = 0.9012
-raan_rad = 0.1411
-argument_of_perigee_rad = 1.7952
-epoch_jday = 2.458940966402607e6
-///////////////////////////////////////////////////////////////////////////////
-
-
-// Settings for SGP4 ///////////////////////////////////////////////
-// TLE
-// Example: ISS
-tle1=1 25544U 98067A 20076.51604214 .00016717 00000-0 10270-3 0 9005
-tle2=2 25544 51.6412 86.9962 0006063 30.9353 329.2153 15.49228202 17647
-// World Geodetic System
-wgs = 2 // 0: wgs72old, 1: wgs72, 2: wgs84
-//////////////////////////////////////////////////////////////////////////
-
-// Settings for relative orbit propagation ////////////////////////////
-// Relative Orbit Update Method (0 means RK4, 1 means STM)
-relative_orbit_update_method = 0
-// RK4 Relative Dynamics model type (only valid for RK4 update)
-// 0: Hill
-relative_dynamics_model_type = 0
-// STM Relative Dynamics model type (only valid for STM update)
-// 0: HCW
-stm_model_type = 0
-// Initial satellite position relative to the reference satellite in LVLH frame[m]
-// * The coordinate system is defined at [PLANET_SELECTION] in SampleSimBase.ini
-initial_relative_position_lvlh_m(0) = 0.0
-initial_relative_position_lvlh_m(1) = 100.0
-initial_relative_position_lvlh_m(2) = 0.0
-// initial satellite velocity relative to the reference satellite in LVLH frame[m/s]
-initial_relative_velocity_lvlh_m_s(0) = 0.0
-initial_relative_velocity_lvlh_m_s(1) = 0.0
-initial_relative_velocity_lvlh_m_s(2) = 0.0
-// information of reference satellite
-reference_satellite_id = 1
-///////////////////////////////////////////////////////////////////////////////
-
-// Settings for Encke mode ///////////
-error_tolerance = 0.0001
-///////////////////////////////////////////////////////////////////////////////
-
-
-[THERMAL]
-calculation = DISABLE
-debug = 0
-thermal_file_directory = ../../data/initialize_files/thermal_csv_files/
-
-[SETTING_FILES]
-local_environment_file = ../../data/initialize_files/user_satellite_local_environment.ini
-disturbance_file = ../../data/initialize_files/user_satellite_disturbance.ini
-structure_file = ../../data/initialize_files/user_satellite_structure.ini
-
-
-[COMPONENT_FILES]
-// Users can add the path for component initialize files here.
-gyro_file = ../../data/initialize_files/components/gyro_sensor_xxx.ini
-reaction_wheel_file = ../../data/initialize_files/components/reaction_wheel_xxx.ini
diff --git a/Tutorials/SampleCodes/control_algorithm/component_method_real/src/components/user_on_board_computer.cpp b/Tutorials/SampleCodes/control_algorithm/component_method_real/src/components/user_on_board_computer.cpp
deleted file mode 100644
index fb583539..00000000
--- a/Tutorials/SampleCodes/control_algorithm/component_method_real/src/components/user_on_board_computer.cpp
+++ /dev/null
@@ -1,27 +0,0 @@
-/**
- * @file user_on_board_computer.hpp
- * @brief User defined on board computer
- */
-
-#include "user_on_board_computer.hpp"
-
-UserOnBoardComputer::UserOnBoardComputer(ClockGenerator* clock_generator, UserComponents& components)
- : Component(1, clock_generator), components_(components) {}
-
-UserOnBoardComputer::~UserOnBoardComputer() {}
-
-void UserOnBoardComputer::MainRoutine(const int time_count) {
- UNUSED(time_count);
- // Sensor inputs
- const libra::Vector<3> gyro_omega_c = components_.GetGyroSensor().GetMeasuredAngularVelocity_c_rad_s();
- // const double rw_rpm = components_.GetReactionWheel().GetAngularVelocity_rpm(); // An example of RW rotation speed observation
-
- // Control Algorithm
- const double Kp = 5e-3;
- double torque = -1.0 * Kp * gyro_omega_c(0);
-
- // Actuator outputs
- components_.GetReactionWheel().SetDriveFlag(true);
- components_.GetReactionWheel().SetVelocityLimit_rpm(8000.0);
- components_.GetReactionWheel().SetTargetTorque_b_Nm(torque);
-}
diff --git a/Tutorials/SampleCodes/control_algorithm/component_method_real/src/components/user_on_board_computer.hpp b/Tutorials/SampleCodes/control_algorithm/component_method_real/src/components/user_on_board_computer.hpp
deleted file mode 100644
index 71e53776..00000000
--- a/Tutorials/SampleCodes/control_algorithm/component_method_real/src/components/user_on_board_computer.hpp
+++ /dev/null
@@ -1,46 +0,0 @@
-/**
- * @file user_on_board_computer.hpp
- * @brief User defined on board computer
- */
-
-#ifndef S2E_COMPONENTS_USER_ON_BOARD_COMPUTER_HPP_
-#define S2E_COMPONENTS_USER_ON_BOARD_COMPUTER_HPP_
-
-#include
-#include
-
-#include "../simulation/spacecraft/user_components.hpp"
-
-class UserComponents;
-
-/*
- * @class UserOnBoardComputer
- * @brief Class to emulate user defined on board computer
- */
-class UserOnBoardComputer : public Component {
- public:
- /**
- * @fn UserOnBoardComputer
- * @brief Constructor
- * @param [in] clock_generator: Clock generator
- * @param [in] components: Component list
- */
- UserOnBoardComputer(ClockGenerator* clock_generator, UserComponents& components);
-
- /**
- * @fn ~UserOnBoardComputer
- * @brief Destructor
- */
- ~UserOnBoardComputer();
-
- protected:
- UserComponents& components_; //!< Component list
-
- /**
- * @fn MainRoutine
- * @brief Override Component::Main function
- */
- void MainRoutine(const int time_count);
-};
-
-#endif // S2E_COMPONENTS_USER_ON_BOARD_COMPUTER_HPP_
diff --git a/Tutorials/SampleCodes/control_algorithm/component_method_real/src/simulation/user_components.cpp b/Tutorials/SampleCodes/control_algorithm/component_method_real/src/simulation/user_components.cpp
deleted file mode 100644
index 793d84ad..00000000
--- a/Tutorials/SampleCodes/control_algorithm/component_method_real/src/simulation/user_components.cpp
+++ /dev/null
@@ -1,58 +0,0 @@
-/**
- * @file user_components.cpp
- * @brief An example of user side components management installed on a spacecraft
- */
-
-#include "user_components.hpp"
-
-#include
-
-UserComponents::UserComponents(const Dynamics *dynamics, Structure *structure, const LocalEnvironment *local_environment,
- const GlobalEnvironment *global_environment, const SimulationConfiguration *configuration,
- ClockGenerator *clock_generator, const unsigned int spacecraft_id)
- : configuration_(configuration),
- dynamics_(dynamics),
- structure_(structure),
- local_environment_(local_environment),
- global_environment_(global_environment) {
- // Common
- IniAccess iniAccess = IniAccess(configuration_->spacecraft_file_list_[spacecraft_id]);
- const double compo_step_sec = global_environment_->GetSimulationTime().GetComponentStepTime_s();
-
- obc_ = new UserOnBoardComputer(clock_generator, *this);
-
- // Initialize of GyroSensor class
- std::string file_name = iniAccess.ReadString("COMPONENT_FILES", "gyro_file");
- configuration_->main_logger_->CopyFileToLogDirectory(file_name);
- gyro_sensor_ = new GyroSensor(InitGyroSensor(clock_generator, 1, file_name, compo_step_sec, dynamics));
-
- // Initialize of ReactionWheel class
- file_name = iniAccess.ReadString("COMPONENT_FILES", "reaction_wheel_file");
- configuration_->main_logger_->CopyFileToLogDirectory(file_name);
- reaction_wheel_ = new ReactionWheel(InitReactionWheel(clock_generator, 1, file_name, dynamics->GetAttitude().GetPropStep_s(), compo_step_sec));
-}
-
-UserComponents::~UserComponents() {
- delete gyro_sensor_;
- delete reaction_wheel_;
- // OBC must be deleted the last since it has com ports
- delete obc_;
-}
-
-Vector<3> UserComponents::GenerateForce_b_N() {
- // There is no orbit control component, so it remains 0
- Vector<3> force_b_N(0.0);
- return force_b_N;
-}
-
-Vector<3> UserComponents::GenerateTorque_b_Nm() {
- // No attitude control component
- Vector<3> torque_b_Nm(0.0);
- torque_b_Nm = reaction_wheel_->GetOutputTorque_b_Nm();
- return torque_b_Nm;
-}
-
-void UserComponents::LogSetup(Logger &logger) {
- logger.AddLogList(gyro_sensor_);
- logger.AddLogList(reaction_wheel_);
-}
diff --git a/Tutorials/SampleCodes/control_algorithm/component_method_real/src/simulation/user_components.hpp b/Tutorials/SampleCodes/control_algorithm/component_method_real/src/simulation/user_components.hpp
deleted file mode 100644
index b3498836..00000000
--- a/Tutorials/SampleCodes/control_algorithm/component_method_real/src/simulation/user_components.hpp
+++ /dev/null
@@ -1,51 +0,0 @@
-/**
- * @file sample_components.hpp
- * @brief An example of user side components management installed on a spacecraft
- */
-
-#ifndef S2E_SIMULATION_SPACECRAFT_USER_COMPONENTS_HPP_
-#define S2E_SIMULATION_SPACECRAFT_USER_COMPONENTS_HPP_
-
-#include
-#include
-#include
-#include
-#include
-
-// include for components
-#include
-#include
-
-#include "../../components/user_on_board_computer.hpp"
-
-class UserOnBoardComputer;
-
-class UserComponents : public InstalledComponents {
- public:
- UserComponents(const Dynamics *dynamics, Structure *structure, const LocalEnvironment *local_environment,
- const GlobalEnvironment *global_environment, const SimulationConfiguration *configuration, ClockGenerator *clock_generator,
- const unsigned int spacecraft_id);
- ~UserComponents();
- libra::Vector<3> GenerateForce_b_N();
- libra::Vector<3> GenerateTorque_b_Nm();
- void LogSetup(Logger &logger);
-
- // Getter
- inline GyroSensor &GetGyroSensor() { return *gyro_sensor_; }
- inline ReactionWheel &GetReactionWheel() { return *reaction_wheel_; }
-
- private:
- // Components
- UserOnBoardComputer *obc_; //!< Onboard Computer
- GyroSensor *gyro_sensor_; //!< Gyro sensor
- ReactionWheel *reaction_wheel_; //!< Reaction wheel
-
- // States
- const SimulationConfiguration *configuration_; //!< Simulation settings
- const Dynamics *dynamics_; //!< Dynamics information of the spacecraft
- Structure *structure_; //!< Structure information of the spacecraft
- const LocalEnvironment *local_environment_; //!< Local environment information around the spacecraft
- const GlobalEnvironment *global_environment_; //!< Global environment information
-};
-
-#endif // S2E_SIMULATION_SPACECRAFT_USER_COMPONENTS_HPP_
\ No newline at end of file
diff --git a/Tutorials/SampleCodes/control_algorithm/direct_method/user_satellite.cpp b/Tutorials/SampleCodes/control_algorithm/direct_method/user_satellite.cpp
deleted file mode 100644
index c39949a1..00000000
--- a/Tutorials/SampleCodes/control_algorithm/direct_method/user_satellite.cpp
+++ /dev/null
@@ -1,48 +0,0 @@
-/**
- * @file user_satellite.cpp
- * @brief An example of user side spacecraft class
- */
-
-#include "user_satellite.hpp"
-
-#include "user_components.hpp"
-
-UserSatellite::UserSatellite(const SimulationConfiguration *simulation_configuration, const GlobalEnvironment *global_environment,
- const unsigned int spacecraft_id)
- : Spacecraft(simulation_configuration, global_environment, spacecraft_id) {
- components_ =
- new UserComponents(dynamics_, structure_, local_environment_, global_environment, simulation_configuration, &clock_generator_, spacecraft_id);
-}
-void UserSatellite::Update(const SimulationTime *simulation_time) {
- dynamics_->ClearForceTorque();
-
- // Update local environment and disturbance
- local_environment_->Update(dynamics_, simulation_time);
- disturbances_->Update(*local_environment_, *dynamics_, simulation_time);
-
- // Control algorithm
- ControlAlgorithm();
-
- // Add generated force and torque by disturbances
- dynamics_->AddAcceleration_i_m_s2(disturbances_->GetAcceleration_i_m_s2());
- dynamics_->AddTorque_b_Nm(disturbances_->GetTorque_b_Nm());
- dynamics_->AddForce_b_N(disturbances_->GetForce_b_N());
-
- // Propagate dynamics
- dynamics_->Update(simulation_time, &(local_environment_->GetCelestialInformation()));
-}
-
-void UserSatellite::ControlAlgorithm(void) {
- // Sensing
- Vector<3> observed_omega_b_rad_s = dynamics_->GetAttitude().GetAngularVelocity_b_rad_s();
-
- // Control algorithm
- Vector<3> control_torque_b_Nm(0.0);
- Vector<3> control_force_b_N(0.0);
- double Kp = 5.0e-3;
- control_torque_b_Nm = -1.0 * Kp * observed_omega_b_rad_s;
-
- // Generate force and torque
- dynamics_->AddTorque_b_Nm(control_torque_b_Nm);
- dynamics_->AddForce_b_N(control_force_b_N);
-}
diff --git a/Tutorials/SampleCodes/control_algorithm/direct_method/user_satellite.hpp b/Tutorials/SampleCodes/control_algorithm/direct_method/user_satellite.hpp
deleted file mode 100644
index 404afcf6..00000000
--- a/Tutorials/SampleCodes/control_algorithm/direct_method/user_satellite.hpp
+++ /dev/null
@@ -1,40 +0,0 @@
-/**
- * @file user_satellite.hpp
- * @brief An example of user side spacecraft class
- */
-
-#ifndef S2E_SIMULATION_SPACECRAFT_USER_SATELLITE_HPP_
-#define S2E_SIMULATION_SPACECRAFT_USER_SATELLITE_HPP_
-
-#include
-
-#include "user_components.hpp"
-
-/**
- * @class UserSatellite
- * @brief An example of user side spacecraft class
- */
-class UserSatellite : public Spacecraft {
- public:
- /**
- * @fn UserSatellite
- * @brief Constructor
- */
- UserSatellite(const SimulationConfiguration *simulation_configuration, const GlobalEnvironment *global_environment,
- const unsigned int spacecraft_id);
-
- /**
- * @fn Update
- * @brief Override Spacecraft::Update
- */
- virtual void Update(const SimulationTime *simulation_time);
-
- private:
- /**
- * @fn ControlAlgorithm
- * @brief Control algorithm
- */
- void ControlAlgorithm(void);
-};
-
-#endif // S2E_SIMULATION_SPACECRAFT_USER_SATELLITE_HPP_
\ No newline at end of file
diff --git a/Tutorials/SampleCodes/monte_carlo_simulation/s2e_user.cpp b/Tutorials/SampleCodes/monte_carlo_simulation/s2e_user.cpp
deleted file mode 100644
index 68eccacf..00000000
--- a/Tutorials/SampleCodes/monte_carlo_simulation/s2e_user.cpp
+++ /dev/null
@@ -1,96 +0,0 @@
-/**
- * @file s2e_user.cpp
- * @brief The main file of S2E-USER
- */
-
-#ifdef WIN32
-#define _WINSOCKAPI_ // stops windows.h including winsock.h
-#include
-#include
-#endif
-
-#include
-#include
-#include
-#include
-
-// Simulator includes
-#include "library/logger/initialize_log.hpp"
-
-// Add custom include files
-#include <./simulation/monte_carlo_simulation/initialize_monte_carlo_simulation.hpp>
-
-#include "./simulation/case/user_case.hpp"
-
-void print_path(std::string path) {
-#ifdef WIN32
- std::cout << path << std::endl;
-#else
- const char *rpath = realpath(path.c_str(), NULL);
- if (rpath) {
- std::cout << rpath << std::endl;
- free((void *)rpath);
- }
-#endif
-}
-
-#ifdef WIN32
-int main(int argc, _TCHAR *argv[])
-#else
-int main(int argc, char *argv[])
-#endif
-{
- using namespace std::chrono;
-
- system_clock::time_point start, end;
- start = system_clock::now();
-
- std::string data_path = "../../data/";
- std::string ini_file = "../../data/initialize_files/user_simulation_base.ini";
-
- // Parsing arguments: SatAttSim [ini_file]
- if (argc == 0) {
- std::cout << "Usage: SatAttSim [ini file path]" << std::endl;
- return EXIT_FAILURE;
- }
- if (argc > 1) {
- data_path = std::string(argv[1]);
- if (data_path.back() != '/') data_path += "/";
- }
- if (argc > 2) {
- ini_file = std::string(argv[2]);
- }
-
- MonteCarloSimulationExecutor *mc_simulator = InitMonteCarloSimulation(ini_file);
- Logger *log_mc_simulator = InitMonteCarloLog(ini_file, mc_simulator->IsEnabled());
-
- std::cout << "Starting simulation..." << std::endl;
- std::cout << "\tData path: ";
- print_path(data_path);
- std::cout << "\tIni file: ";
- print_path(ini_file);
-
- while (mc_simulator->WillExecuteNextCase()) {
- auto simulation_case = UserCase(ini_file, *mc_simulator, log_mc_simulator->GetLogPath());
- // Initialize
- log_mc_simulator->AddLogList(&simulation_case);
- if (mc_simulator->GetNumberOfExecutionsDone() == 0) log_mc_simulator->WriteHeaders();
- simulation_case.Initialize();
-
- // Main
- log_mc_simulator->WriteValues(); // log initial value
- simulation_case.Main();
- mc_simulator->AtTheEndOfEachCase();
- log_mc_simulator->WriteValues(); // log final value
- log_mc_simulator->ClearLogList();
- }
-
- delete log_mc_simulator;
- delete mc_simulator;
-
- end = system_clock::now();
- double time = static_cast(duration_cast(end - start).count() / 1000000.0);
- std::cout << std::endl << "Simulation execution time: " << time << "sec" << std::endl << std::endl;
-
- return EXIT_SUCCESS;
-}
diff --git a/Tutorials/SampleCodes/monte_carlo_simulation/user_case.cpp b/Tutorials/SampleCodes/monte_carlo_simulation/user_case.cpp
deleted file mode 100644
index 1e3a4109..00000000
--- a/Tutorials/SampleCodes/monte_carlo_simulation/user_case.cpp
+++ /dev/null
@@ -1,54 +0,0 @@
-/**
- * @file user_case.cpp
- * @brief Example of user defined simulation case
- */
-
-#include "user_case.hpp"
-
-#include <./simulation/monte_carlo_simulation/simulation_object.hpp>
-
-UserCase::UserCase(const std::string initialize_base_file, MonteCarloSimulationExecutor &monte_carlo_simulator, const std::string log_path)
- : SimulationCase(initialize_base_file, monte_carlo_simulator, log_path), monte_carlo_simulator_(monte_carlo_simulator) {}
-
-UserCase::~UserCase() { delete spacecraft_; }
-
-void UserCase::InitializeTargetObjects() {
- // Instantiate the target of the simulation
- // `spacecraft_id` corresponds to the index of `spacecraft_file` in simulation_base.ini
- const int spacecraft_id = 0;
- spacecraft_ = new UserSatellite(&simulation_configuration_, global_environment_, spacecraft_id);
-
- // Register the log output
- spacecraft_->LogSetup(*(simulation_configuration_.main_logger_));
-
- // Monte Carlo Simulation
- monte_carlo_simulator_.SetSeed();
- monte_carlo_simulator_.RandomizeAllParameters();
- SimulationObject::SetAllParameters(monte_carlo_simulator_);
- monte_carlo_simulator_.AtTheBeginningOfEachCase();
-}
-
-void UserCase::UpdateTargetObjects() {
- // Spacecraft Update
- spacecraft_->Update(&(global_environment_->GetSimulationTime()));
-}
-
-std::string UserCase::GetLogHeader() const {
- std::string str_tmp = "";
-
- str_tmp += WriteScalar("elapsed_time", "s");
- str_tmp += WriteVector("spacecraft_angular_velocity", "b", "rad/s", 3);
- str_tmp += WriteVector("spacecraft_quaternion", "i2b", "-", 4);
-
- return str_tmp;
-}
-
-std::string UserCase::GetLogValue() const {
- std::string str_tmp = "";
-
- str_tmp += WriteScalar(global_environment_->GetSimulationTime().GetElapsedTime_s());
- str_tmp += WriteVector(spacecraft_->GetDynamics().GetAttitude().GetAngularVelocity_b_rad_s(), 3);
- str_tmp += WriteQuaternion(spacecraft_->GetDynamics().GetAttitude().GetQuaternion_i2b());
-
- return str_tmp;
-}
diff --git a/Tutorials/SampleCodes/monte_carlo_simulation/user_case.hpp b/Tutorials/SampleCodes/monte_carlo_simulation/user_case.hpp
deleted file mode 100644
index 6398b51b..00000000
--- a/Tutorials/SampleCodes/monte_carlo_simulation/user_case.hpp
+++ /dev/null
@@ -1,60 +0,0 @@
-/**
- * @file user_case.hpp
- * @brief Example of user defined simulation case
- */
-
-#ifndef S2E_SIMULATION_CASE_USER_CASE_HPP_
-#define S2E_SIMULATION_CASE_USER_CASE_HPP_
-
-#include <./simulation/case/simulation_case.hpp>
-#include <./simulation/monte_carlo_simulation/monte_carlo_simulation_executor.hpp>
-
-#include "../spacecraft/user_satellite.hpp"
-
-/**
- * @class UserCase
- * @brief An example of user defined simulation case
- */
-class UserCase : public SimulationCase {
- public:
- /**
- * @fn UserCase
- * @brief Constructor
- */
- UserCase(const std::string initialize_base_file, MonteCarloSimulationExecutor &monte_carlo_simulator, const std::string log_path);
- /**
- * @fn ~UserCase
- * @brief Destructor
- */
- virtual ~UserCase();
-
- /**
- * @fn GetLogHeader
- * @brief Override function of GetLogHeader
- */
- virtual std::string GetLogHeader() const;
- /**
- * @fn GetLogValue
- * @brief Override function of GetLogValue
- */
- virtual std::string GetLogValue() const;
-
- private:
- UserSatellite *spacecraft_; //!< Instance of spacecraft
-
- MonteCarloSimulationExecutor &monte_carlo_simulator_;
-
- /**
- * @fn InitializeTargetObjects
- * @brief Override function of InitializeTargetObjects in SimulationCase
- */
- void InitializeTargetObjects();
-
- /**
- * @fn UpdateTargetObjects
- * @brief Override function of Main in SimulationCase
- */
- void UpdateTargetObjects();
-};
-
-#endif // S2E_SIMULATION_CASE_USER_CASE_HPP_
diff --git a/Tutorials/SampleCodes/monte_carlo_simulation/user_simulation_base.ini b/Tutorials/SampleCodes/monte_carlo_simulation/user_simulation_base.ini
deleted file mode 100644
index d19c0fab..00000000
--- a/Tutorials/SampleCodes/monte_carlo_simulation/user_simulation_base.ini
+++ /dev/null
@@ -1,124 +0,0 @@
-[TIME]
-// Simulation start time [UTC]
-simulation_start_time_utc = 2020/01/01 12:00:00.0
-
-// Simulation duration [sec]
-simulation_duration_s = 200
-
-// Simulation step time [sec]
-// Minimum time step for the entire simulation
-simulation_step_s = 0.1
-
-// Attitude Update Period [sec]
-// Attitude is updated at the period specified here
-attitude_update_period_s = 0.1 // should be larger than 'simulation_step_s'
-
-// Attitide Δt for Runge-Kutt method [sec]
-// This must be smaller than 'attitude_update_period_s'
-attitude_integral_step_s = 0.001
-
-// Orbit Update Period [sec]
-// Orbit is updated at the period specified here
-orbit_update_period_s = 0.1 // should be larger than 'simulation_step_s'
-
-// Orbit Δt for Runge-Kutta method [sec]
-// This must be smaller than 'orbit_ppdate_period_s'
-orbit_integral_step_s = 0.1
-
-// Thermal Update Period [sec]
-// Thermal is updated at the period specified here
-thermal_update_period_s = 0.1 // should be larger than 'simulation_step_s'
-
-// Thermal Δt for Runge-Kutta method [sec]
-// This must be smaller than 'thermal_update_period_s'
-thermal_integral_step_s = 0.1
-
-// Component Update Period [sec]
-component_update_period_s = 0.1 // should be larger than 'simulation_step_s'
-
-// Log Output Period [sec]
-log_output_period_s = 0.1 // should be larger than 'simulation_step_s'
-
-// Simulation speed
-// 0: as fast as possible, 1: real-time, >1: faster than real-time, <1: slower than real-time
-simulation_speed_setting = 0
-
-
-[MONTE_CARLO_EXECUTION]
-// Whether Monte-Carlo Simulation is executed or not
-monte_carlo_enable = ENABLE
-
-// Whether you want output the log file for each step
-log_enable = ENABLE
-
-// Number of execution
-number_of_executions = 3
-
-[MONTE_CARLO_RANDOMIZATION]
-parameter(0) = attitude0.angular_velocity_b_rad_s
-attitude0.angular_velocity_b_rad_s.randomization_type = CartesianUniform
-attitude0.angular_velocity_b_rad_s.mean_or_min(0) = 0.0
-attitude0.angular_velocity_b_rad_s.mean_or_min(1) = 0.0
-attitude0.angular_velocity_b_rad_s.mean_or_min(2) = 0.0
-attitude0.angular_velocity_b_rad_s.sigma_or_max(0) = 0.05817764 // 3-sigma = 10 [deg/s]
-attitude0.angular_velocity_b_rad_s.sigma_or_max(1) = 0.05817764 // 3-sigma = 10 [deg/s]
-attitude0.angular_velocity_b_rad_s.sigma_or_max(2) = 0.05817764 // 3-sigma = 10 [deg/s]
-
-
-[CELESTIAL_INFORMATION]
-// Whether global celestial information is logged or not
-logging = ENABLE
-
-// Definition of Inertial frame
-inertial_frame = J2000
-// The center object is also used to define the gravity constant of the center body
-center_object = EARTH
-aberration_correction = NONE
-
-// Earth Rotation model
-// Idle:no motion, Simple:rotation only, Full:full-dynamics
-rotation_mode = Simple
-
-// Definition of calculation celestial bodies
-number_of_selected_body = 3
-selected_body_name(0) = EARTH
-selected_body_name(1) = SUN
-selected_body_name(2) = MOON
-selected_body_name(3) = MERCURY
-selected_body_name(4) = VENUS
-selected_body_name(5) = MARS
-selected_body_name(6) = JUPITER
-selected_body_name(7) = SATURN
-selected_body_name(8) = URANUS
-selected_body_name(9) = NEPTUNE
-selected_body_name(10) = PLUTO
-
-[CSPICE_KERNELS]
-// CSPICE Kernel files definition
-tls = ../../../ExtLibraries/cspice/generic_kernels/lsk/naif0010.tls
-tpc1 = ../../../ExtLibraries/cspice/generic_kernels/pck/de-403-masses.tpc
-tpc2 = ../../../ExtLibraries/cspice/generic_kernels/pck/gm_de431.tpc
-tpc3 = ../../../ExtLibraries/cspice/generic_kernels/pck/pck00010.tpc
-bsp = ../../../ExtLibraries/cspice/generic_kernels/spk/planets/de430.bsp
-
-
-[HIPPARCOS_CATALOGUE]
-catalogue_file_path = ../../../ExtLibraries/HipparcosCatalogue/hip_main.csv
-max_magnitude = 3.0 // Max magnitude to read from Hip catalog
-calculation = DISABLE
-logging = DISABLE
-
-
-[RANDOMIZE]
-// Seed of randam. When this value is 0, the seed will be varied by time.
-rand_seed = 0x11223344
-
-
-[SIMULATION_SETTINGS]
-// Whether the ini files are saved or not
-save_initialize_files = ENABLE
-
-number_of_simulated_spacecraft = 1
-number_of_simulated_ground_station = 0
-spacecraft_file(0) = ../../data/initialize_files/user_satellite.ini
-log_file_save_directory = ../../data/logs/
diff --git a/Tutorials/SampleCodes/multiple_satellites/data/user_satellite1.ini b/Tutorials/SampleCodes/multiple_satellites/data/user_satellite1.ini
deleted file mode 100644
index 8f106654..00000000
--- a/Tutorials/SampleCodes/multiple_satellites/data/user_satellite1.ini
+++ /dev/null
@@ -1,139 +0,0 @@
-[ATTITUDE]
-// Attitude propagation mode
-// RK4 : Attitude Propagation with RK4 including disturbances and control torque
-// CONTROLLED : Attitude Calculation with Controlled Attitude mode. All disturbances and control torque are ignored.
-propagate_mode = RK4
-
-// Initialize Attitude mode
-// MANUAL : Initialize Quaternion_i2b manually below
-// CONTROLLED : Initialize attitude with given condition. Valid only when Attitude propagation mode is RK4.
-initialize_mode = MANUAL
-
-// Initial angular velocity at body frame [rad/s]
-initial_angular_velocity_b_rad_s(0) = 0.0
-initial_angular_velocity_b_rad_s(1) = 0.0
-initial_angular_velocity_b_rad_s(2) = 0.0
-
-// Initial quaternion inertial frame to body frame (real part, imaginary part)
-// This value also used in INERTIAL_STABILIZE mode of ControlledAttitude
-initial_quaternion_i2b(0) = 0.0
-initial_quaternion_i2b(1) = 0.0
-initial_quaternion_i2b(2) = 0.0
-initial_quaternion_i2b(3) = 1.0
-
-// Initial torque at body frame [Nm]
-// Note: The initial torque added just for the first propagation step
-initial_torque_b_Nm(0) = +0.000
-initial_torque_b_Nm(1) = -0.000
-initial_torque_b_Nm(2) = 0.000
-
-[CONTROLLED_ATTITUDE]
-// Mode definitions
-// INERTIAL_STABILIZE
-// SUN_POINTING
-// EARTH_CENTER_POINTING
-// VELOCITY_DIRECTION_POINTING
-// ORBIT_NORMAL_POINTING
-main_mode = INERTIAL_STABILIZE
-sub_mode = SUN_POINTING
-
-// Pointing direction @ body frame for main pointing mode
-main_pointing_direction_b(0) = 1.0
-main_pointing_direction_b(1) = 0.0
-main_pointing_direction_b(2) = 0.0
-
-// Pointing direction @ body frame for sub pointing mode
-// main_pointing_direction_b and sub_pointing_direction_b should separate larger than 30 degrees.
-sub_pointing_direction_b(0) = 0.0
-sub_pointing_direction_b(1) = 0.0
-sub_pointing_direction_b(2) = 1.0
-
-
-[ORBIT]
-calculation = ENABLE
-logging = ENABLE
-
-// Orbit propagation mode
-// RK4 : RK4 propagation with disturbances and thruster maneuver
-// SGP4 : SGP4 propagation using TLE without thruster maneuver
-// 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
-propagate_mode = RK4
-
-// Orbit initialize mode for RK4, KEPLER, and ENCKE
-// DEFAULT : Use default initialize method (RK4 and ENCKE use pos/vel, KEPLER uses init_mode_kepler)
-// POSITION_VELOCITY_I : Initialize with position and velocity in the inertial frame
-// ORBITAL_ELEMENTS : Initialize with orbital elements
-initialize_mode = POSITION_VELOCITY_I
-
-// Initial value definition for POSITION_VELOCITY_I initialize mode ////////
-initial_position_i_m(0) = -2111769.7723711144
-initial_position_i_m(1) = -5360353.2254375768
-initial_position_i_m(2) = 3596181.6497774957
-
-initial_velocity_i_m_s(0) = 4200.4344740455268
-initial_velocity_i_m_s(1) = -4637.540129059361
-initial_velocity_i_m_s(2) = -4429.2361258448807
-///////////////////////////////////////////////////////////////////////////
-
-// Initial value definition for ORBITAL_ELEMENTS initialize mode ////////
-semi_major_axis_m = 6794500.0
-eccentricity = 0.0015
-inclination_rad = 0.9012
-raan_rad = 0.1411
-argument_of_perigee_rad = 1.7952
-epoch_jday = 2.458940966402607e6
-///////////////////////////////////////////////////////////////////////////////
-
-
-// Settings for SGP4 ///////////////////////////////////////////////
-// TLE
-// Example: ISS
-tle1=1 25544U 98067A 20076.51604214 .00016717 00000-0 10270-3 0 9005
-tle2=2 25544 51.6412 86.9962 0006063 30.9353 329.2153 15.49228202 17647
-// World Geodetic System
-wgs = 2 // 0: wgs72old, 1: wgs72, 2: wgs84
-//////////////////////////////////////////////////////////////////////////
-
-// Settings for relative orbit propagation ////////////////////////////
-// Relative Orbit Update Method (0 means RK4, 1 means STM)
-relative_orbit_update_method = 0
-// RK4 Relative Dynamics model type (only valid for RK4 update)
-// 0: Hill
-relative_dynamics_model_type = 0
-// STM Relative Dynamics model type (only valid for STM update)
-// 0: HCW
-stm_model_type = 0
-// Initial satellite position relative to the reference satellite in LVLH frame[m]
-// * The coordinate system is defined at [PLANET_SELECTION] in SampleSimBase.ini
-initial_relative_position_lvlh_m(0) = 0.0
-initial_relative_position_lvlh_m(1) = 100.0
-initial_relative_position_lvlh_m(2) = 0.0
-// initial satellite velocity relative to the reference satellite in LVLH frame[m/s]
-initial_relative_velocity_lvlh_m_s(0) = 0.0
-initial_relative_velocity_lvlh_m_s(1) = 0.0
-initial_relative_velocity_lvlh_m_s(2) = 0.0
-// information of reference satellite
-reference_satellite_id = 1
-///////////////////////////////////////////////////////////////////////////////
-
-// Settings for Encke mode ///////////
-error_tolerance = 0.0001
-///////////////////////////////////////////////////////////////////////////////
-
-
-[THERMAL]
-calculation = DISABLE
-debug = 0
-thermal_file_directory = ../../data/initialize_files/thermal_csv_files/
-
-[SETTING_FILES]
-local_environment_file = ../../data/initialize_files/user_satellite1_local_environment.ini
-disturbance_file = ../../data/initialize_files/user_satellite1_disturbance.ini
-structure_file = ../../data/initialize_files/user_satellite1_structure.ini
-
-
-[COMPONENT_FILES]
-// Users can add the path for component initialize files here.
-
diff --git a/Tutorials/SampleCodes/multiple_satellites/data/user_satellite1_disturbance.ini b/Tutorials/SampleCodes/multiple_satellites/data/user_satellite1_disturbance.ini
deleted file mode 100644
index 20796de2..00000000
--- a/Tutorials/SampleCodes/multiple_satellites/data/user_satellite1_disturbance.ini
+++ /dev/null
@@ -1,48 +0,0 @@
-[GEOPOTENTIAL]
-// Enable only when the center object is defined as the Earth
-calculation = DISABLE
-logging = ENABLE
-degree = 4
-coefficients_file_path = ../../../ExtLibraries/GeoPotential/egm96_to360.ascii
-
-
-[MAGNETIC_DISTURBANCE]
-// Enable only when the center object is defined as the Earth
-calculation = ENABLE
-logging = ENABLE
-
-
-[AIR_DRAG]
-// Enable only when the center object is defined as the Earth
-calculation = ENABLE
-logging = ENABLE
-
-// Condition of air drag
-wall_temperature_degC = 30 // Surface Temperature[degC]
-molecular_temperature_degC = 3 // Atmosphere Temperature[degC]
-molecular_weight_g_mol = 18.0 // Molecular weight of the thermosphere[g/mol]
-
-
-[SOLAR_RADIATION_PRESSURE_DISTURBANCE]
-calculation = ENABLE
-logging = ENABLE
-
-
-[GRAVITY_GRADIENT]
-calculation = ENABLE
-logging = ENABLE
-
-
-[THIRD_BODY_GRAVITY]
-calculation = DISABLE
-logging = ENABLE
-
-// The number of gravity-generating bodies other than the central body
-number_of_third_body = 1
-
-// List of gravity-generating bodies other than the central body
-// All these bodies must be included in the "selected_body_name" of "[CelestialInformation]"
-third_body_name(0) = SUN
-third_body_name(1) = MOON
-third_body_name(2) = MARS
-
diff --git a/Tutorials/SampleCodes/multiple_satellites/data/user_satellite1_local_environment.ini b/Tutorials/SampleCodes/multiple_satellites/data/user_satellite1_local_environment.ini
deleted file mode 100644
index af2ff61e..00000000
--- a/Tutorials/SampleCodes/multiple_satellites/data/user_satellite1_local_environment.ini
+++ /dev/null
@@ -1,35 +0,0 @@
-[MAGNETIC_FIELD_ENVIRONMENT]
-calculation = ENABLE
-logging = ENABLE
-coefficient_file = ../../../s2e-core/src/library/external/igrf/igrf13.coef
-magnetic_field_random_walk_standard_deviation_nT = 10.0
-magnetic_field_random_walk_limit_nT = 400.0
-magnetic_field_white_noise_standard_deviation_nT = 50.0
-
-
-[SOLAR_RADIATION_PRESSURE_ENVIRONMENT]
-calculation = ENABLE
-logging = ENABLE
-
-
-[ATMOSPHERE]
-calculation = ENABLE
-logging = ENABLE
-
-// Atmosphere model
-// STANDARD: Model using scale height, NRLMSISE00: NRLMSISE00 model
-model = STANDARD
-nrlmsise00_table_file = ../../../ExtLibraries/nrlmsise00/table/SpaceWeather.txt
-// Whether using user-defined f10.7 and ap value
-// Ref of f10.7: https://www.swpc.noaa.gov/phenomena/f107-cm-radio-emissions
-// Ref of ap: http://wdc.kugi.kyoto-u.ac.jp/kp/kpexp-j.html
-is_manual_parameter_used = ENABLE
-manual_daily_f107 = 150.0 // User defined f10.7 (1 day)
-manual_average_f107 = 150.0 // User defined f10.7 (30 days average)
-manual_ap = 3.0 // User defined ap
-air_density_standard_deviation = 0.0 // Standard deviation of the air density
-
-
-[LOCAL_CELESTIAL_INFORMATION]
-logging = ENABLE
-
diff --git a/Tutorials/SampleCodes/multiple_satellites/data/user_satellite1_structure.ini b/Tutorials/SampleCodes/multiple_satellites/data/user_satellite1_structure.ini
deleted file mode 100644
index 19c771ce..00000000
--- a/Tutorials/SampleCodes/multiple_satellites/data/user_satellite1_structure.ini
+++ /dev/null
@@ -1,116 +0,0 @@
-//
-// The origin of all vectors defined here is the body-fixed frame.
-// Users can define the origin of the body-fixed frame by themselves.
-// If users want to define the origin as the center of gravity, they need to set center_of_gravity_b_m = zero vector.
-// If users want to define the origin as a specific point, they need to set all vectors to suit their definition carefully.
-//
-
-[KINEMATIC_PARAMETERS]
-// Inertia Tensor @ body fixed frame [kg・m2]
-inertia_tensor_kgm2(0) = 0.1 // I_xx
-inertia_tensor_kgm2(1) = 0.0 // I_xy
-inertia_tensor_kgm2(2) = 0.0 // I_xz
-inertia_tensor_kgm2(3) = 0.0 // I_yx
-inertia_tensor_kgm2(4) = 0.1 // I_yy
-inertia_tensor_kgm2(5) = 0.0 // I_yz
-inertia_tensor_kgm2(6) = 0.0 // I_zx
-inertia_tensor_kgm2(7) = 0.0 // I_zy
-inertia_tensor_kgm2(8) = 0.1 // I_zz
-
-mass_kg = 14
-
-// Position vector of the center of gravity @ the body frame [m]
-center_of_gravity_b_m(0) = 0.01
-center_of_gravity_b_m(1) = 0.01
-center_of_gravity_b_m(2) = 0.01
-
-[SURFACES]
-number_of_surfaces = 6
-
-// Area of each surface [m^2]
-area_0_m2 = 0.25
-area_1_m2 = 0.25
-area_2_m2 = 0.25
-area_3_m2 = 0.25
-area_4_m2 = 0.25
-area_5_m2 = 0.25
-
-// Position vector of each surface geometric center @ body frame [m]
-position_0_b_m(0) = 0.25
-position_0_b_m(1) = 0.0
-position_0_b_m(2) = 0.0
-position_1_b_m(0) = -0.25
-position_1_b_m(1) = 0.0
-position_1_b_m(2) = 0.0
-position_2_b_m(0) = 0.0
-position_2_b_m(1) = 0.25
-position_2_b_m(2) = 0.0
-position_3_b_m(0) = 0.0
-position_3_b_m(1) = -0.25
-position_3_b_m(2) = 0.0
-position_4_b_m(0) = 0.0
-position_4_b_m(1) = 0.0
-position_4_b_m(2) = 0.25
-position_5_b_m(0) = 0.0
-position_5_b_m(1) = 0.0
-position_5_b_m(2) = -0.25
-
-// Normal vector of each surface @ body frame
-normal_vector_0_b(0) = 1.0
-normal_vector_0_b(1) = 0.0
-normal_vector_0_b(2) = 0.0
-normal_vector_1_b(0) = -1.0
-normal_vector_1_b(1) = 0.0
-normal_vector_1_b(2) = 0.0
-normal_vector_2_b(0) = 0.0
-normal_vector_2_b(1) = 1.0
-normal_vector_2_b(2) = 0.0
-normal_vector_3_b(0) = 0.0
-normal_vector_3_b(1) = -1.0
-normal_vector_3_b(2) = 0.0
-normal_vector_4_b(0) = 0.0
-normal_vector_4_b(1) = 0.0
-normal_vector_4_b(2) = 1.0
-normal_vector_5_b(0) = 0.0
-normal_vector_5_b(1) = 0.0
-normal_vector_5_b(2) = -1.0
-
-// Total reflectance for the Sun spectrum
-reflectivity_0 = 0.4
-reflectivity_1 = 0.4
-reflectivity_2 = 0.4
-reflectivity_3 = 0.4
-reflectivity_4 = 0.4
-reflectivity_5 = 0.4
-
-// Specularity for the Sun spectrum
-specularity_0 = 0.4
-specularity_1 = 0.4
-specularity_2 = 0.4
-specularity_3 = 0.4
-specularity_4 = 0.4
-specularity_5 = 0.4
-
-// Specularity for air drag
-air_specularity_0 = 0.4
-air_specularity_1 = 0.4
-air_specularity_2 = 0.4
-air_specularity_3 = 0.4
-air_specularity_4 = 0.4
-air_specularity_5 = 0.4
-
-[RESIDUAL_MAGNETIC_MOMENT]
-// Constant component of Residual Magnetic Moment(RMM) [A・m^2]
-rmm_constant_b_Am2(0) = 0.04
-rmm_constant_b_Am2(1) = 0.04
-rmm_constant_b_Am2(2) = 0.04
-
-// RMM Random Walk Speed [A・m^2]
-rmm_random_walk_speed_Am2 = 1.0E-5
-
-// RMM Random Walk Limit [A・m^2]
-rmm_random_walk_limit_Am2 = 1.0E-3
-
-// RMM White Noise Standard deviation [A・m^2]
-rmm_white_noise_standard_deviation_Am2 = 5.0E-5
-
diff --git a/Tutorials/SampleCodes/multiple_satellites/data/user_satellite2.ini b/Tutorials/SampleCodes/multiple_satellites/data/user_satellite2.ini
deleted file mode 100644
index 56f2dc3b..00000000
--- a/Tutorials/SampleCodes/multiple_satellites/data/user_satellite2.ini
+++ /dev/null
@@ -1,139 +0,0 @@
-[ATTITUDE]
-// Attitude propagation mode
-// RK4 : Attitude Propagation with RK4 including disturbances and control torque
-// CONTROLLED : Attitude Calculation with Controlled Attitude mode. All disturbances and control torque are ignored.
-propagate_mode = RK4
-
-// Initialize Attitude mode
-// MANUAL : Initialize Quaternion_i2b manually below
-// CONTROLLED : Initialize attitude with given condition. Valid only when Attitude propagation mode is RK4.
-initialize_mode = MANUAL
-
-// Initial angular velocity at body frame [rad/s]
-initial_angular_velocity_b_rad_s(0) = 0.0
-initial_angular_velocity_b_rad_s(1) = 0.0
-initial_angular_velocity_b_rad_s(2) = 0.0
-
-// Initial quaternion inertial frame to body frame (real part, imaginary part)
-// This value also used in INERTIAL_STABILIZE mode of ControlledAttitude
-initial_quaternion_i2b(0) = 0.0
-initial_quaternion_i2b(1) = 0.0
-initial_quaternion_i2b(2) = 0.0
-initial_quaternion_i2b(3) = 1.0
-
-// Initial torque at body frame [Nm]
-// Note: The initial torque added just for the first propagation step
-initial_torque_b_Nm(0) = +0.000
-initial_torque_b_Nm(1) = -0.000
-initial_torque_b_Nm(2) = 0.000
-
-[CONTROLLED_ATTITUDE]
-// Mode definitions
-// INERTIAL_STABILIZE
-// SUN_POINTING
-// EARTH_CENTER_POINTING
-// VELOCITY_DIRECTION_POINTING
-// ORBIT_NORMAL_POINTING
-main_mode = INERTIAL_STABILIZE
-sub_mode = SUN_POINTING
-
-// Pointing direction @ body frame for main pointing mode
-main_pointing_direction_b(0) = 1.0
-main_pointing_direction_b(1) = 0.0
-main_pointing_direction_b(2) = 0.0
-
-// Pointing direction @ body frame for sub pointing mode
-// main_pointing_direction_b and sub_pointing_direction_b should separate larger than 30 degrees.
-sub_pointing_direction_b(0) = 0.0
-sub_pointing_direction_b(1) = 0.0
-sub_pointing_direction_b(2) = 1.0
-
-
-[ORBIT]
-calculation = ENABLE
-logging = ENABLE
-
-// Orbit propagation mode
-// RK4 : RK4 propagation with disturbances and thruster maneuver
-// SGP4 : SGP4 propagation using TLE without thruster maneuver
-// 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
-propagate_mode = RK4
-
-// Orbit initialize mode for RK4, KEPLER, and ENCKE
-// DEFAULT : Use default initialize method (RK4 and ENCKE use pos/vel, KEPLER uses init_mode_kepler)
-// POSITION_VELOCITY_I : Initialize with position and velocity in the inertial frame
-// ORBITAL_ELEMENTS : Initialize with orbital elements
-initialize_mode = POSITION_VELOCITY_I
-
-// Initial value definition for POSITION_VELOCITY_I initialize mode ////////
-initial_position_i_m(0) = -2111769.7723711144
-initial_position_i_m(1) = -5360353.2254375768
-initial_position_i_m(2) = 3596181.6497774957
-
-initial_velocity_i_m_s(0) = 4200.4344740455268
-initial_velocity_i_m_s(1) = -4637.540129059361
-initial_velocity_i_m_s(2) = -4429.2361258448807
-///////////////////////////////////////////////////////////////////////////
-
-// Initial value definition for ORBITAL_ELEMENTS initialize mode ////////
-semi_major_axis_m = 6794500.0
-eccentricity = 0.0015
-inclination_rad = 0.9012
-raan_rad = 0.1411
-argument_of_perigee_rad = 1.7952
-epoch_jday = 2.458940966402607e6
-///////////////////////////////////////////////////////////////////////////////
-
-
-// Settings for SGP4 ///////////////////////////////////////////////
-// TLE
-// Example: ISS
-tle1=1 25544U 98067A 20076.51604214 .00016717 00000-0 10270-3 0 9005
-tle2=2 25544 51.6412 86.9962 0006063 30.9353 329.2153 15.49228202 17647
-// World Geodetic System
-wgs = 2 // 0: wgs72old, 1: wgs72, 2: wgs84
-//////////////////////////////////////////////////////////////////////////
-
-// Settings for relative orbit propagation ////////////////////////////
-// Relative Orbit Update Method (0 means RK4, 1 means STM)
-relative_orbit_update_method = 0
-// RK4 Relative Dynamics model type (only valid for RK4 update)
-// 0: Hill
-relative_dynamics_model_type = 0
-// STM Relative Dynamics model type (only valid for STM update)
-// 0: HCW
-stm_model_type = 0
-// Initial satellite position relative to the reference satellite in LVLH frame[m]
-// * The coordinate system is defined at [PLANET_SELECTION] in SampleSimBase.ini
-initial_relative_position_lvlh_m(0) = 0.0
-initial_relative_position_lvlh_m(1) = 100.0
-initial_relative_position_lvlh_m(2) = 0.0
-// initial satellite velocity relative to the reference satellite in LVLH frame[m/s]
-initial_relative_velocity_lvlh_m_s(0) = 0.0
-initial_relative_velocity_lvlh_m_s(1) = 0.0
-initial_relative_velocity_lvlh_m_s(2) = 0.0
-// information of reference satellite
-reference_satellite_id = 1
-///////////////////////////////////////////////////////////////////////////////
-
-// Settings for Encke mode ///////////
-error_tolerance = 0.0001
-///////////////////////////////////////////////////////////////////////////////
-
-
-[THERMAL]
-calculation = DISABLE
-debug = 0
-thermal_file_directory = ../../data/initialize_files/thermal_csv_files/
-
-[SETTING_FILES]
-local_environment_file = ../../data/initialize_files/user_satellite2_local_environment.ini
-disturbance_file = ../../data/initialize_files/user_satellite2_disturbance.ini
-structure_file = ../../data/initialize_files/user_satellite2_structure.ini
-
-
-[COMPONENT_FILES]
-// Users can add the path for component initialize files here.
-
diff --git a/Tutorials/SampleCodes/multiple_satellites/data/user_satellite2_disturbance.ini b/Tutorials/SampleCodes/multiple_satellites/data/user_satellite2_disturbance.ini
deleted file mode 100644
index 20796de2..00000000
--- a/Tutorials/SampleCodes/multiple_satellites/data/user_satellite2_disturbance.ini
+++ /dev/null
@@ -1,48 +0,0 @@
-[GEOPOTENTIAL]
-// Enable only when the center object is defined as the Earth
-calculation = DISABLE
-logging = ENABLE
-degree = 4
-coefficients_file_path = ../../../ExtLibraries/GeoPotential/egm96_to360.ascii
-
-
-[MAGNETIC_DISTURBANCE]
-// Enable only when the center object is defined as the Earth
-calculation = ENABLE
-logging = ENABLE
-
-
-[AIR_DRAG]
-// Enable only when the center object is defined as the Earth
-calculation = ENABLE
-logging = ENABLE
-
-// Condition of air drag
-wall_temperature_degC = 30 // Surface Temperature[degC]
-molecular_temperature_degC = 3 // Atmosphere Temperature[degC]
-molecular_weight_g_mol = 18.0 // Molecular weight of the thermosphere[g/mol]
-
-
-[SOLAR_RADIATION_PRESSURE_DISTURBANCE]
-calculation = ENABLE
-logging = ENABLE
-
-
-[GRAVITY_GRADIENT]
-calculation = ENABLE
-logging = ENABLE
-
-
-[THIRD_BODY_GRAVITY]
-calculation = DISABLE
-logging = ENABLE
-
-// The number of gravity-generating bodies other than the central body
-number_of_third_body = 1
-
-// List of gravity-generating bodies other than the central body
-// All these bodies must be included in the "selected_body_name" of "[CelestialInformation]"
-third_body_name(0) = SUN
-third_body_name(1) = MOON
-third_body_name(2) = MARS
-
diff --git a/Tutorials/SampleCodes/multiple_satellites/data/user_satellite2_local_environment.ini b/Tutorials/SampleCodes/multiple_satellites/data/user_satellite2_local_environment.ini
deleted file mode 100644
index af2ff61e..00000000
--- a/Tutorials/SampleCodes/multiple_satellites/data/user_satellite2_local_environment.ini
+++ /dev/null
@@ -1,35 +0,0 @@
-[MAGNETIC_FIELD_ENVIRONMENT]
-calculation = ENABLE
-logging = ENABLE
-coefficient_file = ../../../s2e-core/src/library/external/igrf/igrf13.coef
-magnetic_field_random_walk_standard_deviation_nT = 10.0
-magnetic_field_random_walk_limit_nT = 400.0
-magnetic_field_white_noise_standard_deviation_nT = 50.0
-
-
-[SOLAR_RADIATION_PRESSURE_ENVIRONMENT]
-calculation = ENABLE
-logging = ENABLE
-
-
-[ATMOSPHERE]
-calculation = ENABLE
-logging = ENABLE
-
-// Atmosphere model
-// STANDARD: Model using scale height, NRLMSISE00: NRLMSISE00 model
-model = STANDARD
-nrlmsise00_table_file = ../../../ExtLibraries/nrlmsise00/table/SpaceWeather.txt
-// Whether using user-defined f10.7 and ap value
-// Ref of f10.7: https://www.swpc.noaa.gov/phenomena/f107-cm-radio-emissions
-// Ref of ap: http://wdc.kugi.kyoto-u.ac.jp/kp/kpexp-j.html
-is_manual_parameter_used = ENABLE
-manual_daily_f107 = 150.0 // User defined f10.7 (1 day)
-manual_average_f107 = 150.0 // User defined f10.7 (30 days average)
-manual_ap = 3.0 // User defined ap
-air_density_standard_deviation = 0.0 // Standard deviation of the air density
-
-
-[LOCAL_CELESTIAL_INFORMATION]
-logging = ENABLE
-
diff --git a/Tutorials/SampleCodes/multiple_satellites/data/user_satellite2_structure.ini b/Tutorials/SampleCodes/multiple_satellites/data/user_satellite2_structure.ini
deleted file mode 100644
index 19c771ce..00000000
--- a/Tutorials/SampleCodes/multiple_satellites/data/user_satellite2_structure.ini
+++ /dev/null
@@ -1,116 +0,0 @@
-//
-// The origin of all vectors defined here is the body-fixed frame.
-// Users can define the origin of the body-fixed frame by themselves.
-// If users want to define the origin as the center of gravity, they need to set center_of_gravity_b_m = zero vector.
-// If users want to define the origin as a specific point, they need to set all vectors to suit their definition carefully.
-//
-
-[KINEMATIC_PARAMETERS]
-// Inertia Tensor @ body fixed frame [kg・m2]
-inertia_tensor_kgm2(0) = 0.1 // I_xx
-inertia_tensor_kgm2(1) = 0.0 // I_xy
-inertia_tensor_kgm2(2) = 0.0 // I_xz
-inertia_tensor_kgm2(3) = 0.0 // I_yx
-inertia_tensor_kgm2(4) = 0.1 // I_yy
-inertia_tensor_kgm2(5) = 0.0 // I_yz
-inertia_tensor_kgm2(6) = 0.0 // I_zx
-inertia_tensor_kgm2(7) = 0.0 // I_zy
-inertia_tensor_kgm2(8) = 0.1 // I_zz
-
-mass_kg = 14
-
-// Position vector of the center of gravity @ the body frame [m]
-center_of_gravity_b_m(0) = 0.01
-center_of_gravity_b_m(1) = 0.01
-center_of_gravity_b_m(2) = 0.01
-
-[SURFACES]
-number_of_surfaces = 6
-
-// Area of each surface [m^2]
-area_0_m2 = 0.25
-area_1_m2 = 0.25
-area_2_m2 = 0.25
-area_3_m2 = 0.25
-area_4_m2 = 0.25
-area_5_m2 = 0.25
-
-// Position vector of each surface geometric center @ body frame [m]
-position_0_b_m(0) = 0.25
-position_0_b_m(1) = 0.0
-position_0_b_m(2) = 0.0
-position_1_b_m(0) = -0.25
-position_1_b_m(1) = 0.0
-position_1_b_m(2) = 0.0
-position_2_b_m(0) = 0.0
-position_2_b_m(1) = 0.25
-position_2_b_m(2) = 0.0
-position_3_b_m(0) = 0.0
-position_3_b_m(1) = -0.25
-position_3_b_m(2) = 0.0
-position_4_b_m(0) = 0.0
-position_4_b_m(1) = 0.0
-position_4_b_m(2) = 0.25
-position_5_b_m(0) = 0.0
-position_5_b_m(1) = 0.0
-position_5_b_m(2) = -0.25
-
-// Normal vector of each surface @ body frame
-normal_vector_0_b(0) = 1.0
-normal_vector_0_b(1) = 0.0
-normal_vector_0_b(2) = 0.0
-normal_vector_1_b(0) = -1.0
-normal_vector_1_b(1) = 0.0
-normal_vector_1_b(2) = 0.0
-normal_vector_2_b(0) = 0.0
-normal_vector_2_b(1) = 1.0
-normal_vector_2_b(2) = 0.0
-normal_vector_3_b(0) = 0.0
-normal_vector_3_b(1) = -1.0
-normal_vector_3_b(2) = 0.0
-normal_vector_4_b(0) = 0.0
-normal_vector_4_b(1) = 0.0
-normal_vector_4_b(2) = 1.0
-normal_vector_5_b(0) = 0.0
-normal_vector_5_b(1) = 0.0
-normal_vector_5_b(2) = -1.0
-
-// Total reflectance for the Sun spectrum
-reflectivity_0 = 0.4
-reflectivity_1 = 0.4
-reflectivity_2 = 0.4
-reflectivity_3 = 0.4
-reflectivity_4 = 0.4
-reflectivity_5 = 0.4
-
-// Specularity for the Sun spectrum
-specularity_0 = 0.4
-specularity_1 = 0.4
-specularity_2 = 0.4
-specularity_3 = 0.4
-specularity_4 = 0.4
-specularity_5 = 0.4
-
-// Specularity for air drag
-air_specularity_0 = 0.4
-air_specularity_1 = 0.4
-air_specularity_2 = 0.4
-air_specularity_3 = 0.4
-air_specularity_4 = 0.4
-air_specularity_5 = 0.4
-
-[RESIDUAL_MAGNETIC_MOMENT]
-// Constant component of Residual Magnetic Moment(RMM) [A・m^2]
-rmm_constant_b_Am2(0) = 0.04
-rmm_constant_b_Am2(1) = 0.04
-rmm_constant_b_Am2(2) = 0.04
-
-// RMM Random Walk Speed [A・m^2]
-rmm_random_walk_speed_Am2 = 1.0E-5
-
-// RMM Random Walk Limit [A・m^2]
-rmm_random_walk_limit_Am2 = 1.0E-3
-
-// RMM White Noise Standard deviation [A・m^2]
-rmm_white_noise_standard_deviation_Am2 = 5.0E-5
-
diff --git a/Tutorials/SampleCodes/multiple_satellites/data/user_simulation_base.ini b/Tutorials/SampleCodes/multiple_satellites/data/user_simulation_base.ini
deleted file mode 100644
index f12a7c7f..00000000
--- a/Tutorials/SampleCodes/multiple_satellites/data/user_simulation_base.ini
+++ /dev/null
@@ -1,136 +0,0 @@
-[TIME]
-// Simulation start time [UTC]
-simulation_start_time_utc = 2020/01/01 12:00:00.0
-
-// Simulation duration [sec]
-simulation_duration_s = 200
-
-// Simulation step time [sec]
-// Minimum time step for the entire simulation
-simulation_step_s = 0.1
-
-// Attitude Update Period [sec]
-// Attitude is updated at the period specified here
-attitude_update_period_s = 0.1 // should be larger than 'simulation_step_s'
-
-// Attitide Δt for Runge-Kutt method [sec]
-// This must be smaller than 'attitude_update_period_s'
-attitude_integral_step_s = 0.001
-
-// Orbit Update Period [sec]
-// Orbit is updated at the period specified here
-orbit_update_period_s = 0.1 // should be larger than 'simulation_step_s'
-
-// Orbit Δt for Runge-Kutta method [sec]
-// This must be smaller than 'orbit_ppdate_period_s'
-orbit_integral_step_s = 0.1
-
-// Thermal Update Period [sec]
-// Thermal is updated at the period specified here
-thermal_update_period_s = 0.1 // should be larger than 'simulation_step_s'
-
-// Thermal Δt for Runge-Kutta method [sec]
-// This must be smaller than 'thermal_update_period_s'
-thermal_integral_step_s = 0.1
-
-// Component Update Period [sec]
-component_update_period_s = 0.1 // should be larger than 'simulation_step_s'
-
-// Log Output Period [sec]
-log_output_period_s = 0.1 // should be larger than 'simulation_step_s'
-
-// Simulation speed
-// 0: as fast as possible, 1: real-time, >1: faster than real-time, <1: slower than real-time
-simulation_speed_setting = 0
-
-
-[MONTE_CARLO_EXECUTION]
-// Whether Monte-Carlo Simulation is executed or not
-monte_carlo_enable = DISABLE
-
-// Whether you want output the log file for each step
-log_enable = ENABLE
-
-// Number of execution
-number_of_executions = 100
-
-
-[MONTE_CARLO_RANDOMIZATION]
-parameter(0) = attitude0.debug
-attitude0.debug.randomization_type = CartesianUniform
-attitude0.debug.mean_or_min(0) = 0.0
-attitude0.debug.mean_or_min(1) = 0.0
-attitude0.debug.mean_or_min(2) = 0.0
-attitude0.debug.sigma_or_max(0) = 10.0
-attitude0.debug.sigma_or_max(1) = 10.0
-attitude0.debug.sigma_or_max(2) = 10.0
-
-parameter(1) = attitude0.omega_b
-attitude0.omega_b.randomization_type = NoRandomization
-attitude0.omega_b.mean_or_min(0) = 0.0
-attitude0.omega_b.mean_or_min(1) = 0.0
-attitude0.omega_b.mean_or_min(2) = 0.0
-attitude0.omega_b.sigma_or_max(0) = 0.05817764 // 3-sigma = 10 [deg/s]
-attitude0.omega_b.sigma_or_max(1) = 0.05817764 // 3-sigma = 10 [deg/s]
-attitude0.omega_b.sigma_or_max(2) = 0.05817764 // 3-sigma = 10 [deg/s]
-
-
-[CELESTIAL_INFORMATION]
-// Whether global celestial information is logged or not
-logging = ENABLE
-
-// Definition of Inertial frame
-inertial_frame = J2000
-// The center object is also used to define the gravity constant of the center body
-center_object = EARTH
-aberration_correction = NONE
-
-// Earth Rotation model
-// Idle:no motion, Simple:rotation only, Full:full-dynamics
-rotation_mode = Simple
-
-// Definition of calculation celestial bodies
-number_of_selected_body = 3
-selected_body_name(0) = EARTH
-selected_body_name(1) = SUN
-selected_body_name(2) = MOON
-selected_body_name(3) = MERCURY
-selected_body_name(4) = VENUS
-selected_body_name(5) = MARS
-selected_body_name(6) = JUPITER
-selected_body_name(7) = SATURN
-selected_body_name(8) = URANUS
-selected_body_name(9) = NEPTUNE
-selected_body_name(10) = PLUTO
-
-[CSPICE_KERNELS]
-// CSPICE Kernel files definition
-tls = ../../../ExtLibraries/cspice/generic_kernels/lsk/naif0010.tls
-tpc1 = ../../../ExtLibraries/cspice/generic_kernels/pck/de-403-masses.tpc
-tpc2 = ../../../ExtLibraries/cspice/generic_kernels/pck/gm_de431.tpc
-tpc3 = ../../../ExtLibraries/cspice/generic_kernels/pck/pck00010.tpc
-bsp = ../../../ExtLibraries/cspice/generic_kernels/spk/planets/de430.bsp
-
-
-[HIPPARCOS_CATALOGUE]
-catalogue_file_path = ../../../ExtLibraries/HipparcosCatalogue/hip_main.csv
-max_magnitude = 3.0 // Max magnitude to read from Hip catalog
-calculation = DISABLE
-logging = DISABLE
-
-
-[RANDOMIZE]
-// Seed of randam. When this value is 0, the seed will be varied by time.
-rand_seed = 0x11223344
-
-
-[SIMULATION_SETTINGS]
-// Whether the ini files are saved or not
-save_initialize_files = ENABLE
-
-number_of_simulated_spacecraft = 2
-spacecraft_file(0) = ../../data/initialize_files/user_satellite1.ini
-spacecraft_file(1) = ../../data/initialize_files/user_satellite2.ini
-number_of_simulated_ground_station = 0
-log_file_save_directory = ../../data/logs/
-
diff --git a/Tutorials/SampleCodes/multiple_satellites/src/user_case.cpp b/Tutorials/SampleCodes/multiple_satellites/src/user_case.cpp
deleted file mode 100644
index e9ff29c6..00000000
--- a/Tutorials/SampleCodes/multiple_satellites/src/user_case.cpp
+++ /dev/null
@@ -1,41 +0,0 @@
-/**
- * @file user_case.cpp
- * @brief Example of user defined simulation case
- */
-
-#include "user_case.hpp"
-
-UserCase::UserCase(const std::string initialise_base_file) : SimulationCase(initialise_base_file) {}
-
-UserCase::~UserCase() {
- delete spacecraft0_;
- delete spacecraft1_;
-}
-
-void UserCase::InitializeTargetObjects() {
- // Instantiate the target of the simulation
- // `spacecraft_id` corresponds to the index of `spacecraft_file` in simulation_base.ini
- spacecraft0_ = new UserSatellite(&simulation_configuration_, global_environment_, 0);
- spacecraft1_ = new UserSatellite(&simulation_configuration_, global_environment_, 1);
-
- // Register the log output
- spacecraft0_->LogSetup(*(simulation_configuration_.main_logger_));
- spacecraft1_->LogSetup(*(simulation_configuration_.main_logger_));
-}
-
-void UserCase::UpdateTargetObjects() {
- // Spacecraft Update
- spacecraft0_->Update(&(global_environment_->GetSimulationTime()));
- spacecraft1_->Update(&(global_environment_->GetSimulationTime()));
-}
-
-std::string UserCase::GetLogHeader() const {
- std::string str_tmp = "";
- return str_tmp;
-}
-
-std::string UserCase::GetLogValue() const {
- std::string str_tmp = "";
-
- return str_tmp;
-}
diff --git a/Tutorials/SampleCodes/multiple_satellites/src/user_case.hpp b/Tutorials/SampleCodes/multiple_satellites/src/user_case.hpp
deleted file mode 100644
index 5718ec40..00000000
--- a/Tutorials/SampleCodes/multiple_satellites/src/user_case.hpp
+++ /dev/null
@@ -1,58 +0,0 @@
-/**
- * @file user_case.hpp
- * @brief Example of user defined simulation case
- */
-
-#ifndef S2E_SIMULATION_CASE_USER_CASE_HPP_
-#define S2E_SIMULATION_CASE_USER_CASE_HPP_
-
-#include <./simulation/case/simulation_case.hpp>
-
-#include "../spacecraft/user_satellite.hpp"
-
-/**
- * @class UserCase
- * @brief An example of user defined simulation case
- */
-class UserCase : public SimulationCase {
- public:
- /**
- * @fn UserCase
- * @brief Constructor
- */
- UserCase(const std::string initialise_base_file);
- /**
- * @fn ~UserCase
- * @brief Destructor
- */
- virtual ~UserCase();
-
- /**
- * @fn GetLogHeader
- * @brief Override function of GetLogHeader
- */
- virtual std::string GetLogHeader() const;
- /**
- * @fn GetLogValue
- * @brief Override function of GetLogValue
- */
- virtual std::string GetLogValue() const;
-
- private:
- UserSatellite *spacecraft0_; //!< Instance of spacecraft
- UserSatellite *spacecraft1_; //!< Instance of spacecraft
-
- /**
- * @fn InitializeTargetObjects
- * @brief Override function of InitializeTargetObjects in SimulationCase
- */
- void InitializeTargetObjects();
-
- /**
- * @fn UpdateTargetObjects
- * @brief Override function of Main in SimulationCase
- */
- void UpdateTargetObjects();
-};
-
-#endif // S2E_SIMULATION_CASE_USER_CASE_HPP_
diff --git a/Tutorials/SampleCodes/s2e-user/CMakeLists.txt b/Tutorials/SampleCodes/s2e-user/CMakeLists.txt
deleted file mode 100644
index c2a58c35..00000000
--- a/Tutorials/SampleCodes/s2e-user/CMakeLists.txt
+++ /dev/null
@@ -1,174 +0,0 @@
-## General Settings
-cmake_policy(SET CMP0048 NEW)
-project(S2E_USER
- LANGUAGES CXX
- DESCRIPTION "s2e-user: A sample of S2E User Side"
- VERSION 6.0.0
-)
-
-cmake_minimum_required(VERSION 3.13)
-
-# build config
-option(USE_HILS "Use HILS" OFF)
-option(USE_C2A "Use C2A" OFF)
-
-# preprocessor
-if(WIN32)
- add_definitions(-DWIN32)
-endif()
-
-## set directory path
-set(S2E_CORE_DIR ../s2e-core)
-if(NOT DEFINED EXT_LIB_DIR)
- set(EXT_LIB_DIR ../ExtLibraries)
-endif()
-set(CSPICE_DIR ${EXT_LIB_DIR}/cspice)
-set(NRLMSISE00_DIR ${EXT_LIB_DIR}/nrlmsise00)
-
-if(NOT DEFINED FLIGHT_SW_DIR)
- set(FLIGHT_SW_DIR ../FlightSW)
-endif()
-if(NOT DEFINED C2A_NAME)
- set(C2A_NAME "c2a_oss")
-endif()
-
-## options to use C2A
-if(USE_C2A)
- set(C2A_DIR ${FLIGHT_SW_DIR}/${C2A_NAME})
- message("C2A dir: ${C2A_DIR}")
- add_definitions(-DUSE_C2A)
- add_definitions(-DSILS_FW)
- #include_directories of C2A
- include_directories(${C2A_DIR}/src)
- include_directories(${S2E_CORE_DIR}/src/interface/sils)
-
- #add subdirectory
- add_subdirectory(${C2A_DIR} C2A)
-endif()
-
-## options to use HILS
-if(USE_HILS AND WIN32)
- add_definitions(-DUSE_HILS)
- ## winsock2
- SET (CMAKE_FIND_LIBRARY_SUFFIXES ".lib")
- find_library(WS2_32_LIB ws2_32.lib)
- message("path for winsock2 is")
- message(${WS2_32_LIB})
-endif()
-
-## include directories of s2e-core
-include_directories(${CSPICE_DIR}/include)
-include_directories(${NRLMSISE00_DIR}/src)
-include_directories(${S2E_CORE_DIR}/src)
-
-## add_subdirectories
-add_subdirectory(${S2E_CORE_DIR}/src/components s2e_core/components)
-add_subdirectory(${S2E_CORE_DIR}/src/disturbances s2e_core/disturbances)
-add_subdirectory(${S2E_CORE_DIR}/src/dynamics s2e_core/dynamics)
-add_subdirectory(${S2E_CORE_DIR}/src/environment/global s2e_core/environment/global)
-add_subdirectory(${S2E_CORE_DIR}/src/environment/local s2e_core/environment/local)
-add_subdirectory(${S2E_CORE_DIR}/src/library s2e_core/library)
-add_subdirectory(${S2E_CORE_DIR}/src/simulation s2e_core/simulation)
-
-set(SOURCE_FILES
- src/s2e_user.cpp
- src/simulation/case/user_case.cpp
- src/simulation/spacecraft/user_satellite.cpp
- src/simulation/spacecraft/user_components.cpp
-)
-# Create executable file
-add_executable(${PROJECT_NAME} ${SOURCE_FILES})
-
-## cspice library
-if(CYGWIN)
- SET (CMAKE_FIND_LIBRARY_SUFFIXES ".so" ".a")
- set(CSPICE_LIB_DIR ${CSPICE_DIR}/cspice_cygwin/lib)
-elseif(UNIX)
- if(BUILD_64BIT)
- set(CSPICE_LIB_DIR ${CSPICE_DIR}/cspice_unix64/lib)
- else()
- set(CSPICE_LIB_DIR ${CSPICE_DIR}/cspice_unix/lib)
- endif()
-endif()
-
-if(WIN32)
- SET (CMAKE_FIND_LIBRARY_SUFFIXES ".lib")
- find_library(CSPICE_LIB
- NAMES cspice.lib csupport.lib
- PATHS ${CSPICE_DIR}/cspice_msvs/lib)
-else()
- find_library(CSPICE_LIB
- NAMES cspice.a csupport.a
- PATHS ${CSPICE_LIB_DIR})
-endif()
-if(NOT CSPICE_LIB)
- message(FATAL_ERROR "cspice not found in ${CSPICE_LIB_DIR}")
-endif()
-
-## nrlmsise00 library
-if(CYGWIN)
- SET (CMAKE_FIND_LIBRARY_SUFFIXES ".a")
- find_library(NRLMSISE00_LIB
- NAMES libnrlmsise00.a
- PATHS ${NRLMSISE00_DIR}/lib)
-elseif(UNIX)
- if(BUILD_64BIT)
- find_library(NRLMSISE00_LIB
- NAMES libnrlmsise00.a
- PATHS ${NRLMSISE00_DIR}/lib64)
- else()
- find_library(NRLMSISE00_LIB
- NAMES libnrlmsise00.a
- PATHS ${NRLMSISE00_DIR}/lib)
- endif()
-elseif(WIN32)
- SET (CMAKE_FIND_LIBRARY_SUFFIXES ".lib")
- find_library(NRLMSISE00_LIB
- NAMES libnrlmsise00.lib
- PATHS ${NRLMSISE00_DIR}/lib)
-endif()
-if(NOT NRLMSISE00_LIB)
- message(FATAL_ERROR "nrlmsise00 not found in ${EXT_LIB_DIR}")
-endif()
-
-## Linking libraries
-set(S2E_LIBRARIES
- IGRF WRAPPER_NRLMSISE00 INIH SGP4 UTIL OPTICS RELATIVE_ORBIT_MODELS ORBIT_MODELS GEODESY MATH
-)
-# Initialize link
-target_link_libraries(COMPONENT DYNAMICS GLOBAL_ENVIRONMENT LOCAL_ENVIRONMENT LIBRARY)
-target_link_libraries(DYNAMICS GLOBAL_ENVIRONMENT LOCAL_ENVIRONMENT SIMULATION LIBRARY)
-target_link_libraries(DISTURBANCE DYNAMICS GLOBAL_ENVIRONMENT LOCAL_ENVIRONMENT LIBRARY)
-target_link_libraries(SIMULATION DYNAMICS GLOBAL_ENVIRONMENT LOCAL_ENVIRONMENT DISTURBANCE LIBRARY)
-target_link_libraries(GLOBAL_ENVIRONMENT ${CSPICE_LIB} LIBRARY)
-target_link_libraries(LOCAL_ENVIRONMENT GLOBAL_ENVIRONMENT ${CSPICE_LIB} LIBRARY)
-target_link_libraries(LIBRARY ${NRLMSISE00_LIB})
-
-target_link_libraries(${PROJECT_NAME} DYNAMICS)
-target_link_libraries(${PROJECT_NAME} DISTURBANCE)
-target_link_libraries(${PROJECT_NAME} SIMULATION)
-target_link_libraries(${PROJECT_NAME} GLOBAL_ENVIRONMENT LOCAL_ENVIRONMENT)
-target_link_libraries(${PROJECT_NAME} COMPONENT)
-
-## C2A integration
-if(USE_C2A)
- target_link_libraries(${PROJECT_NAME} C2A)
-endif()
-
-## HILS
-if(USE_HILS)
- target_link_libraries(${PROJECT_NAME} ${WS2_32_LIB})
- set_target_properties(${PROJECT_NAME} PROPERTIES COMMON_LANGUAGE_RUNTIME "")
- set_target_properties(COMPONENT PROPERTIES COMMON_LANGUAGE_RUNTIME "")
- set_target_properties(DYNAMICS PROPERTIES COMMON_LANGUAGE_RUNTIME "")
- set_target_properties(DISTURBANCE PROPERTIES COMMON_LANGUAGE_RUNTIME "")
- set_target_properties(SIMULATION PROPERTIES COMMON_LANGUAGE_RUNTIME "")
- set_target_properties(GLOBAL_ENVIRONMENT PROPERTIES COMMON_LANGUAGE_RUNTIME "")
- set_target_properties(LOCAL_ENVIRONMENT PROPERTIES COMMON_LANGUAGE_RUNTIME "")
-endif()
-
-## Cmake debug
-message("Cspice_LIB: " ${CSPICE_LIB})
-message("nrlmsise00_LIB: " ${NRLMSISE00_LIB})
-
-include(${S2E_CORE_DIR}/common.cmake)
diff --git a/Tutorials/SampleCodes/s2e-user/CMakeSettings.json b/Tutorials/SampleCodes/s2e-user/CMakeSettings.json
deleted file mode 100644
index 54477e50..00000000
--- a/Tutorials/SampleCodes/s2e-user/CMakeSettings.json
+++ /dev/null
@@ -1,17 +0,0 @@
-{
- "configurations": [
- {
- "name": "Win32",
- "generator": "Visual Studio 17 2022",
- "configurationType": "Debug",
- "inheritEnvironments": [
- "msvc_x86"
- ],
- "buildRoot": "${thisFileDir}\\CMakeBuilds",
- "installRoot": "${env.USERPROFILE}\\CMakeBuilds\\${workspaceHash}\\install\\${name}",
- "cmakeCommandArgs": "",
- "buildCommandArgs": "",
- "ctestCommandArgs": ""
- }
- ]
-}
\ No newline at end of file
diff --git a/Tutorials/SampleCodes/s2e-user/data/initialize_files/components/gyro_sensor_xxx.ini b/Tutorials/SampleCodes/s2e-user/data/initialize_files/components/gyro_sensor_xxx.ini
deleted file mode 100644
index 84f8948a..00000000
--- a/Tutorials/SampleCodes/s2e-user/data/initialize_files/components/gyro_sensor_xxx.ini
+++ /dev/null
@@ -1,50 +0,0 @@
-[GYRO_SENSOR_1]
-prescaler = 10
-
-// Quaternion from body frame to component frame
-// Including misalignment
-quaternion_b2c(0) = 0.0
-quaternion_b2c(1) = 0.0
-quaternion_b2c(2) = 0.0
-quaternion_b2c(3) = 1.0
-
-[SENSOR_BASE_GYRO_SENSOR_1]
-// Scale Factor Matrix (3×3)
-// (0) = (0,0), (1) = (0,1), (2) = (0,2),
-scale_factor_c(0) = 1.0
-scale_factor_c(1) = 0.0
-scale_factor_c(2) = 0.0
-scale_factor_c(3) = 0.0
-scale_factor_c(4) = 1.0
-scale_factor_c(5) = 0.0
-scale_factor_c(6) = 0.0
-scale_factor_c(7) = 0.0
-scale_factor_c(8) = 1.0
-
-// Constant bias noise at component frame [rad/s]
-constant_bias_c_rad_s(0) = 1.0e-3
-constant_bias_c_rad_s(1) = -1.0e-3
-constant_bias_c_rad_s(2) = 2.0e-3
-
-// Standard deviation for random walk noise[rad/s]
-random_walk_standard_deviation_c_rad_s(0) = 0.0
-random_walk_standard_deviation_c_rad_s(1) = 0.0
-random_walk_standard_deviation_c_rad_s(2) = 0.0
-
-// Limit of random walk noise[rad/s]
-random_walk_limit_c_rad_s(0) = 0.0
-random_walk_limit_c_rad_s(1) = 0.0
-random_walk_limit_c_rad_s(2) = 0.0
-
-// Standard deviation of normal random noise[rad/s]
-normal_random_standard_deviation_c_rad_s(0) = 1e-3
-normal_random_standard_deviation_c_rad_s(1) = 1e-3
-normal_random_standard_deviation_c_rad_s(2) = 1e-3
-
-// Range [rad/s]
-range_to_constant_rad_s = 5.0 // smaller than Range_to_zero
-range_to_zero_rad_s = 10.0
-
-[POWER_PORT]
-minimum_voltage_V = 3.3 // V
-assumed_power_consumption_W = 1.0 //W
diff --git a/Tutorials/SampleCodes/s2e-user/data/initialize_files/user_satellite.ini b/Tutorials/SampleCodes/s2e-user/data/initialize_files/user_satellite.ini
deleted file mode 100644
index 619e1d77..00000000
--- a/Tutorials/SampleCodes/s2e-user/data/initialize_files/user_satellite.ini
+++ /dev/null
@@ -1,138 +0,0 @@
-[ATTITUDE]
-// Attitude propagation mode
-// RK4 : Attitude Propagation with RK4 including disturbances and control torque
-// CONTROLLED : Attitude Calculation with Controlled Attitude mode. All disturbances and control torque are ignored.
-propagate_mode = RK4
-
-// Initialize Attitude mode
-// MANUAL : Initialize Quaternion_i2b manually below
-// CONTROLLED : Initialize attitude with given condition. Valid only when Attitude propagation mode is RK4.
-initialize_mode = MANUAL
-
-// Initial angular velocity at body frame [rad/s]
-initial_angular_velocity_b_rad_s(0) = 0.0
-initial_angular_velocity_b_rad_s(1) = 0.0
-initial_angular_velocity_b_rad_s(2) = 0.0
-
-// Initial quaternion inertial frame to body frame (real part, imaginary part)
-// This value also used in INERTIAL_STABILIZE mode of ControlledAttitude
-initial_quaternion_i2b(0) = 0.0
-initial_quaternion_i2b(1) = 0.0
-initial_quaternion_i2b(2) = 0.0
-initial_quaternion_i2b(3) = 1.0
-
-// Initial torque at body frame [Nm]
-// Note: The initial torque added just for the first propagation step
-initial_torque_b_Nm(0) = +0.000
-initial_torque_b_Nm(1) = -0.000
-initial_torque_b_Nm(2) = 0.000
-
-[CONTROLLED_ATTITUDE]
-// Mode definitions
-// INERTIAL_STABILIZE
-// SUN_POINTING
-// EARTH_CENTER_POINTING
-// VELOCITY_DIRECTION_POINTING
-// ORBIT_NORMAL_POINTING
-main_mode = INERTIAL_STABILIZE
-sub_mode = SUN_POINTING
-
-// Pointing direction @ body frame for main pointing mode
-main_pointing_direction_b(0) = 1.0
-main_pointing_direction_b(1) = 0.0
-main_pointing_direction_b(2) = 0.0
-
-// Pointing direction @ body frame for sub pointing mode
-// main_pointing_direction_b and sub_pointing_direction_b should separate larger than 30 degrees.
-sub_pointing_direction_b(0) = 0.0
-sub_pointing_direction_b(1) = 0.0
-sub_pointing_direction_b(2) = 1.0
-
-
-[ORBIT]
-calculation = ENABLE
-logging = ENABLE
-
-// Orbit propagation mode
-// RK4 : RK4 propagation with disturbances and thruster maneuver
-// SGP4 : SGP4 propagation using TLE without thruster maneuver
-// 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
-propagate_mode = RK4
-
-// Orbit initialize mode for RK4, KEPLER, and ENCKE
-// DEFAULT : Use default initialize method (RK4 and ENCKE use pos/vel, KEPLER uses init_mode_kepler)
-// POSITION_VELOCITY_I : Initialize with position and velocity in the inertial frame
-// ORBITAL_ELEMENTS : Initialize with orbital elements
-initialize_mode = POSITION_VELOCITY_I
-
-// Initial value definition for POSITION_VELOCITY_I initialize mode ////////
-initial_position_i_m(0) = -2111769.7723711144
-initial_position_i_m(1) = -5360353.2254375768
-initial_position_i_m(2) = 3596181.6497774957
-
-initial_velocity_i_m_s(0) = 4200.4344740455268
-initial_velocity_i_m_s(1) = -4637.540129059361
-initial_velocity_i_m_s(2) = -4429.2361258448807
-///////////////////////////////////////////////////////////////////////////
-
-// Initial value definition for ORBITAL_ELEMENTS initialize mode ////////
-semi_major_axis_m = 6794500.0
-eccentricity = 0.0015
-inclination_rad = 0.9012
-raan_rad = 0.1411
-argument_of_perigee_rad = 1.7952
-epoch_jday = 2.458940966402607e6
-///////////////////////////////////////////////////////////////////////////////
-
-
-// Settings for SGP4 ///////////////////////////////////////////////
-// TLE
-// Example: ISS
-tle1=1 25544U 98067A 20076.51604214 .00016717 00000-0 10270-3 0 9005
-tle2=2 25544 51.6412 86.9962 0006063 30.9353 329.2153 15.49228202 17647
-// World Geodetic System
-wgs = 2 // 0: wgs72old, 1: wgs72, 2: wgs84
-//////////////////////////////////////////////////////////////////////////
-
-// Settings for relative orbit propagation ////////////////////////////
-// Relative Orbit Update Method (0 means RK4, 1 means STM)
-relative_orbit_update_method = 0
-// RK4 Relative Dynamics model type (only valid for RK4 update)
-// 0: Hill
-relative_dynamics_model_type = 0
-// STM Relative Dynamics model type (only valid for STM update)
-// 0: HCW
-stm_model_type = 0
-// Initial satellite position relative to the reference satellite in LVLH frame[m]
-// * The coordinate system is defined at [PLANET_SELECTION] in SampleSimBase.ini
-initial_relative_position_lvlh_m(0) = 0.0
-initial_relative_position_lvlh_m(1) = 100.0
-initial_relative_position_lvlh_m(2) = 0.0
-// initial satellite velocity relative to the reference satellite in LVLH frame[m/s]
-initial_relative_velocity_lvlh_m_s(0) = 0.0
-initial_relative_velocity_lvlh_m_s(1) = 0.0
-initial_relative_velocity_lvlh_m_s(2) = 0.0
-// information of reference satellite
-reference_satellite_id = 1
-///////////////////////////////////////////////////////////////////////////////
-
-// Settings for Encke mode ///////////
-error_tolerance = 0.0001
-///////////////////////////////////////////////////////////////////////////////
-
-
-[THERMAL]
-calculation = DISABLE
-debug = 0
-thermal_file_directory = ../../data/initialize_files/thermal_csv_files/
-
-[SETTING_FILES]
-local_environment_file = ../../data/initialize_files/user_satellite_local_environment.ini
-disturbance_file = ../../data/initialize_files/user_satellite_disturbance.ini
-structure_file = ../../data/initialize_files/user_satellite_structure.ini
-
-
-[COMPONENT_FILES]
-// Users can add the path for component initialize files here.
diff --git a/Tutorials/SampleCodes/s2e-user/data/initialize_files/user_satellite_disturbance.ini b/Tutorials/SampleCodes/s2e-user/data/initialize_files/user_satellite_disturbance.ini
deleted file mode 100644
index 32da0bd1..00000000
--- a/Tutorials/SampleCodes/s2e-user/data/initialize_files/user_satellite_disturbance.ini
+++ /dev/null
@@ -1,47 +0,0 @@
-[GEOPOTENTIAL]
-// Enable only when the center object is defined as the Earth
-calculation = DISABLE
-logging = ENABLE
-degree = 4
-coefficients_file_path = ../../../ExtLibraries/GeoPotential/egm96_to360.ascii
-
-
-[MAGNETIC_DISTURBANCE]
-// Enable only when the center object is defined as the Earth
-calculation = ENABLE
-logging = ENABLE
-
-
-[AIR_DRAG]
-// Enable only when the center object is defined as the Earth
-calculation = ENABLE
-logging = ENABLE
-
-// Condition of air drag
-wall_temperature_degC = 30 // Surface Temperature[degC]
-molecular_temperature_degC = 3 // Atmosphere Temperature[degC]
-molecular_weight_g_mol = 18.0 // Molecular weight of the thermosphere[g/mol]
-
-
-[SOLAR_RADIATION_PRESSURE_DISTURBANCE]
-calculation = ENABLE
-logging = ENABLE
-
-
-[GRAVITY_GRADIENT]
-calculation = ENABLE
-logging = ENABLE
-
-
-[THIRD_BODY_GRAVITY]
-calculation = DISABLE
-logging = ENABLE
-
-// The number of gravity-generating bodies other than the central body
-number_of_third_body = 1
-
-// List of gravity-generating bodies other than the central body
-// All these bodies must be included in the "selected_body_name" of "[CelestialInformation]"
-third_body_name(0) = SUN
-third_body_name(1) = MOON
-third_body_name(2) = MARS
diff --git a/Tutorials/SampleCodes/s2e-user/data/initialize_files/user_satellite_local_environment.ini b/Tutorials/SampleCodes/s2e-user/data/initialize_files/user_satellite_local_environment.ini
deleted file mode 100644
index 09921765..00000000
--- a/Tutorials/SampleCodes/s2e-user/data/initialize_files/user_satellite_local_environment.ini
+++ /dev/null
@@ -1,34 +0,0 @@
-[MAGNETIC_FIELD_ENVIRONMENT]
-calculation = ENABLE
-logging = ENABLE
-coefficient_file = ../../../s2e-core/src/library/external/igrf/igrf13.coef
-magnetic_field_random_walk_standard_deviation_nT = 10.0
-magnetic_field_random_walk_limit_nT = 400.0
-magnetic_field_white_noise_standard_deviation_nT = 50.0
-
-
-[SOLAR_RADIATION_PRESSURE_ENVIRONMENT]
-calculation = ENABLE
-logging = ENABLE
-
-
-[ATMOSPHERE]
-calculation = ENABLE
-logging = ENABLE
-
-// Atmosphere model
-// STANDARD: Model using scale height, NRLMSISE00: NRLMSISE00 model
-model = STANDARD
-nrlmsise00_table_file = ../../../ExtLibraries/nrlmsise00/table/SpaceWeather-v1.2.txt
-// Whether using user-defined f10.7 and ap value
-// Ref of f10.7: https://www.swpc.noaa.gov/phenomena/f107-cm-radio-emissions
-// Ref of ap: http://wdc.kugi.kyoto-u.ac.jp/kp/kpexp-j.html
-is_manual_parameter_used = ENABLE
-manual_daily_f107 = 150.0 // User defined f10.7 (1 day)
-manual_average_f107 = 150.0 // User defined f10.7 (30 days average)
-manual_ap = 3.0 // User defined ap
-air_density_standard_deviation = 0.0 // Standard deviation of the air density
-
-
-[LOCAL_CELESTIAL_INFORMATION]
-logging = ENABLE
\ No newline at end of file
diff --git a/Tutorials/SampleCodes/s2e-user/data/initialize_files/user_satellite_structure.ini b/Tutorials/SampleCodes/s2e-user/data/initialize_files/user_satellite_structure.ini
deleted file mode 100644
index b7c707cb..00000000
--- a/Tutorials/SampleCodes/s2e-user/data/initialize_files/user_satellite_structure.ini
+++ /dev/null
@@ -1,115 +0,0 @@
-//
-// The origin of all vectors defined here is the body-fixed frame.
-// Users can define the origin of the body-fixed frame by themselves.
-// If users want to define the origin as the center of gravity, they need to set center_of_gravity_b_m = zero vector.
-// If users want to define the origin as a specific point, they need to set all vectors to suit their definition carefully.
-//
-
-[KINEMATIC_PARAMETERS]
-// Inertia Tensor @ body fixed frame [kg・m2]
-inertia_tensor_kgm2(0) = 0.1 // I_xx
-inertia_tensor_kgm2(1) = 0.0 // I_xy
-inertia_tensor_kgm2(2) = 0.0 // I_xz
-inertia_tensor_kgm2(3) = 0.0 // I_yx
-inertia_tensor_kgm2(4) = 0.1 // I_yy
-inertia_tensor_kgm2(5) = 0.0 // I_yz
-inertia_tensor_kgm2(6) = 0.0 // I_zx
-inertia_tensor_kgm2(7) = 0.0 // I_zy
-inertia_tensor_kgm2(8) = 0.1 // I_zz
-
-mass_kg = 14
-
-// Position vector of the center of gravity @ the body frame [m]
-center_of_gravity_b_m(0) = 0.01
-center_of_gravity_b_m(1) = 0.01
-center_of_gravity_b_m(2) = 0.01
-
-[SURFACES]
-number_of_surfaces = 6
-
-// Area of each surface [m^2]
-area_0_m2 = 0.25
-area_1_m2 = 0.25
-area_2_m2 = 0.25
-area_3_m2 = 0.25
-area_4_m2 = 0.25
-area_5_m2 = 0.25
-
-// Position vector of each surface geometric center @ body frame [m]
-position_0_b_m(0) = 0.25
-position_0_b_m(1) = 0.0
-position_0_b_m(2) = 0.0
-position_1_b_m(0) = -0.25
-position_1_b_m(1) = 0.0
-position_1_b_m(2) = 0.0
-position_2_b_m(0) = 0.0
-position_2_b_m(1) = 0.25
-position_2_b_m(2) = 0.0
-position_3_b_m(0) = 0.0
-position_3_b_m(1) = -0.25
-position_3_b_m(2) = 0.0
-position_4_b_m(0) = 0.0
-position_4_b_m(1) = 0.0
-position_4_b_m(2) = 0.25
-position_5_b_m(0) = 0.0
-position_5_b_m(1) = 0.0
-position_5_b_m(2) = -0.25
-
-// Normal vector of each surface @ body frame
-normal_vector_0_b(0) = 1.0
-normal_vector_0_b(1) = 0.0
-normal_vector_0_b(2) = 0.0
-normal_vector_1_b(0) = -1.0
-normal_vector_1_b(1) = 0.0
-normal_vector_1_b(2) = 0.0
-normal_vector_2_b(0) = 0.0
-normal_vector_2_b(1) = 1.0
-normal_vector_2_b(2) = 0.0
-normal_vector_3_b(0) = 0.0
-normal_vector_3_b(1) = -1.0
-normal_vector_3_b(2) = 0.0
-normal_vector_4_b(0) = 0.0
-normal_vector_4_b(1) = 0.0
-normal_vector_4_b(2) = 1.0
-normal_vector_5_b(0) = 0.0
-normal_vector_5_b(1) = 0.0
-normal_vector_5_b(2) = -1.0
-
-// Total reflectance for the Sun spectrum
-reflectivity_0 = 0.4
-reflectivity_1 = 0.4
-reflectivity_2 = 0.4
-reflectivity_3 = 0.4
-reflectivity_4 = 0.4
-reflectivity_5 = 0.4
-
-// Specularity for the Sun spectrum
-specularity_0 = 0.4
-specularity_1 = 0.4
-specularity_2 = 0.4
-specularity_3 = 0.4
-specularity_4 = 0.4
-specularity_5 = 0.4
-
-// Specularity for air drag
-air_specularity_0 = 0.4
-air_specularity_1 = 0.4
-air_specularity_2 = 0.4
-air_specularity_3 = 0.4
-air_specularity_4 = 0.4
-air_specularity_5 = 0.4
-
-[RESIDUAL_MAGNETIC_MOMENT]
-// Constant component of Residual Magnetic Moment(RMM) [A・m^2]
-rmm_constant_b_Am2(0) = 0.04
-rmm_constant_b_Am2(1) = 0.04
-rmm_constant_b_Am2(2) = 0.04
-
-// RMM Random Walk Speed [A・m^2]
-rmm_random_walk_speed_Am2 = 1.0E-5
-
-// RMM Random Walk Limit [A・m^2]
-rmm_random_walk_limit_Am2 = 1.0E-3
-
-// RMM White Noise Standard deviation [A・m^2]
-rmm_white_noise_standard_deviation_Am2 = 5.0E-5
diff --git a/Tutorials/SampleCodes/s2e-user/data/initialize_files/user_simulation_base.ini b/Tutorials/SampleCodes/s2e-user/data/initialize_files/user_simulation_base.ini
deleted file mode 100644
index 66d7af6d..00000000
--- a/Tutorials/SampleCodes/s2e-user/data/initialize_files/user_simulation_base.ini
+++ /dev/null
@@ -1,134 +0,0 @@
-[TIME]
-// Simulation start time [UTC]
-simulation_start_time_utc = 2020/01/01 12:00:00.0
-
-// Simulation duration [sec]
-simulation_duration_s = 200
-
-// Simulation step time [sec]
-// Minimum time step for the entire simulation
-simulation_step_s = 0.1
-
-// Attitude Update Period [sec]
-// Attitude is updated at the period specified here
-attitude_update_period_s = 0.1 // should be larger than 'simulation_step_s'
-
-// Attitide Δt for Runge-Kutt method [sec]
-// This must be smaller than 'attitude_update_period_s'
-attitude_integral_step_s = 0.001
-
-// Orbit Update Period [sec]
-// Orbit is updated at the period specified here
-orbit_update_period_s = 0.1 // should be larger than 'simulation_step_s'
-
-// Orbit Δt for Runge-Kutta method [sec]
-// This must be smaller than 'orbit_ppdate_period_s'
-orbit_integral_step_s = 0.1
-
-// Thermal Update Period [sec]
-// Thermal is updated at the period specified here
-thermal_update_period_s = 0.1 // should be larger than 'simulation_step_s'
-
-// Thermal Δt for Runge-Kutta method [sec]
-// This must be smaller than 'thermal_update_period_s'
-thermal_integral_step_s = 0.1
-
-// Component Update Period [sec]
-component_update_period_s = 0.1 // should be larger than 'simulation_step_s'
-
-// Log Output Period [sec]
-log_output_period_s = 0.1 // should be larger than 'simulation_step_s'
-
-// Simulation speed
-// 0: as fast as possible, 1: real-time, >1: faster than real-time, <1: slower than real-time
-simulation_speed_setting = 0
-
-
-[MONTE_CARLO_EXECUTION]
-// Whether Monte-Carlo Simulation is executed or not
-monte_carlo_enable = DISABLE
-
-// Whether you want output the log file for each step
-log_enable = ENABLE
-
-// Number of execution
-number_of_executions = 100
-
-
-[MONTE_CARLO_RANDOMIZATION]
-parameter(0) = attitude0.debug
-attitude0.debug.randomization_type = CartesianUniform
-attitude0.debug.mean_or_min(0) = 0.0
-attitude0.debug.mean_or_min(1) = 0.0
-attitude0.debug.mean_or_min(2) = 0.0
-attitude0.debug.sigma_or_max(0) = 10.0
-attitude0.debug.sigma_or_max(1) = 10.0
-attitude0.debug.sigma_or_max(2) = 10.0
-
-parameter(1) = attitude0.omega_b
-attitude0.omega_b.randomization_type = NoRandomization
-attitude0.omega_b.mean_or_min(0) = 0.0
-attitude0.omega_b.mean_or_min(1) = 0.0
-attitude0.omega_b.mean_or_min(2) = 0.0
-attitude0.omega_b.sigma_or_max(0) = 0.05817764 // 3-sigma = 10 [deg/s]
-attitude0.omega_b.sigma_or_max(1) = 0.05817764 // 3-sigma = 10 [deg/s]
-attitude0.omega_b.sigma_or_max(2) = 0.05817764 // 3-sigma = 10 [deg/s]
-
-
-[CELESTIAL_INFORMATION]
-// Whether global celestial information is logged or not
-logging = ENABLE
-
-// Definition of Inertial frame
-inertial_frame = J2000
-// The center object is also used to define the gravity constant of the center body
-center_object = EARTH
-aberration_correction = NONE
-
-// Earth Rotation model
-// Idle:no motion, Simple:rotation only, Full:full-dynamics
-rotation_mode = Simple
-
-// Definition of calculation celestial bodies
-number_of_selected_body = 3
-selected_body_name(0) = EARTH
-selected_body_name(1) = SUN
-selected_body_name(2) = MOON
-selected_body_name(3) = MERCURY
-selected_body_name(4) = VENUS
-selected_body_name(5) = MARS
-selected_body_name(6) = JUPITER
-selected_body_name(7) = SATURN
-selected_body_name(8) = URANUS
-selected_body_name(9) = NEPTUNE
-selected_body_name(10) = PLUTO
-
-[CSPICE_KERNELS]
-// CSPICE Kernel files definition
-tls = ../../../ExtLibraries/cspice/generic_kernels/lsk/naif0010.tls
-tpc1 = ../../../ExtLibraries/cspice/generic_kernels/pck/de-403-masses.tpc
-tpc2 = ../../../ExtLibraries/cspice/generic_kernels/pck/gm_de431.tpc
-tpc3 = ../../../ExtLibraries/cspice/generic_kernels/pck/pck00010.tpc
-bsp = ../../../ExtLibraries/cspice/generic_kernels/spk/planets/de430.bsp
-
-
-[HIPPARCOS_CATALOGUE]
-catalogue_file_path = ../../../ExtLibraries/HipparcosCatalogue/hip_main.csv
-max_magnitude = 3.0 // Max magnitude to read from Hip catalog
-calculation = DISABLE
-logging = DISABLE
-
-
-[RANDOMIZE]
-// Seed of randam. When this value is 0, the seed will be varied by time.
-rand_seed = 0x11223344
-
-
-[SIMULATION_SETTINGS]
-// Whether the ini files are saved or not
-save_initialize_files = ENABLE
-
-number_of_simulated_spacecraft = 1
-number_of_simulated_ground_station = 0
-spacecraft_file(0) = ../../data/initialize_files/user_satellite.ini
-log_file_save_directory = ../../data/logs/
diff --git a/Tutorials/SampleCodes/s2e-user/data/logs/.gitkeep b/Tutorials/SampleCodes/s2e-user/data/logs/.gitkeep
deleted file mode 100644
index e69de29b..00000000
diff --git a/Tutorials/SampleCodes/s2e-user/src/s2e_user.cpp b/Tutorials/SampleCodes/s2e-user/src/s2e_user.cpp
deleted file mode 100644
index 1751142c..00000000
--- a/Tutorials/SampleCodes/s2e-user/src/s2e_user.cpp
+++ /dev/null
@@ -1,77 +0,0 @@
-/**
- * @file s2e_user.cpp
- * @brief The main file of S2E-USER
- */
-
-#ifdef WIN32
-#define _WINSOCKAPI_ // stops windows.h including winsock.h
-#include
-#include
-#endif
-
-#include
-#include
-#include
-#include
-
-// Simulator includes
-#include "library/logger/logger.hpp"
-
-// Add custom include files
-#include "./simulation/case/user_case.hpp"
-
-void print_path(std::string path) {
-#ifdef WIN32
- std::cout << path << std::endl;
-#else
- const char *rpath = realpath(path.c_str(), NULL);
- if (rpath) {
- std::cout << rpath << std::endl;
- free((void *)rpath);
- }
-#endif
-}
-
-#ifdef WIN32
-int main(int argc, _TCHAR *argv[])
-#else
-int main(int argc, char *argv[])
-#endif
-{
- using namespace std::chrono;
-
- system_clock::time_point start, end;
- start = system_clock::now();
-
- std::string data_path = "../../data/";
- std::string ini_file = "../../data/initialize_files/user_simulation_base.ini";
-
- // Parsing arguments: SatAttSim [ini_file]
- if (argc == 0) {
- std::cout << "Usage: SatAttSim [ini file path]" << std::endl;
- return EXIT_FAILURE;
- }
- if (argc > 1) {
- data_path = std::string(argv[1]);
- if (data_path.back() != '/') data_path += "/";
- }
- if (argc > 2) {
- ini_file = std::string(argv[2]);
- }
-
- std::cout << "Starting simulation..." << std::endl;
- std::cout << "\tData path: ";
- print_path(data_path);
- std::cout << "\tIni file: ";
- print_path(ini_file);
-
- auto simulation_case = UserCase(ini_file);
- simulation_case.Initialize();
- simulation_case.Main();
-
- end = system_clock::now();
- double time = static_cast(duration_cast(end - start).count() / 1000000.0);
- std::cout << std::endl << "Simulation execution time: " << time << "sec" << std::endl << std::endl;
-
- return EXIT_SUCCESS;
-}
diff --git a/Tutorials/SampleCodes/s2e-user/src/simulation/case/user_case.cpp b/Tutorials/SampleCodes/s2e-user/src/simulation/case/user_case.cpp
deleted file mode 100644
index 8a64d6a4..00000000
--- a/Tutorials/SampleCodes/s2e-user/src/simulation/case/user_case.cpp
+++ /dev/null
@@ -1,36 +0,0 @@
-/**
- * @file user_case.cpp
- * @brief Example of user defined simulation case
- */
-
-#include "user_case.hpp"
-
-UserCase::UserCase(const std::string initialise_base_file) : SimulationCase(initialise_base_file) {}
-
-UserCase::~UserCase() { delete spacecraft_; }
-
-void UserCase::InitializeTargetObjects() {
- // Instantiate the target of the simulation
- // `spacecraft_id` corresponds to the index of `spacecraft_file` in simulation_base.ini
- const int spacecraft_id = 0;
- spacecraft_ = new UserSatellite(&simulation_configuration_, global_environment_, spacecraft_id);
-
- // Register the log output
- spacecraft_->LogSetup(*(simulation_configuration_.main_logger_));
-}
-
-void UserCase::UpdateTargetObjects() {
- // Spacecraft Update
- spacecraft_->Update(&(global_environment_->GetSimulationTime()));
-}
-
-std::string UserCase::GetLogHeader() const {
- std::string str_tmp = "";
- return str_tmp;
-}
-
-std::string UserCase::GetLogValue() const {
- std::string str_tmp = "";
-
- return str_tmp;
-}
diff --git a/Tutorials/SampleCodes/s2e-user/src/simulation/case/user_case.hpp b/Tutorials/SampleCodes/s2e-user/src/simulation/case/user_case.hpp
deleted file mode 100644
index ee99b864..00000000
--- a/Tutorials/SampleCodes/s2e-user/src/simulation/case/user_case.hpp
+++ /dev/null
@@ -1,57 +0,0 @@
-/**
- * @file user_case.hpp
- * @brief Example of user defined simulation case
- */
-
-#ifndef S2E_SIMULATION_CASE_USER_CASE_HPP_
-#define S2E_SIMULATION_CASE_USER_CASE_HPP_
-
-#include <./simulation/case/simulation_case.hpp>
-
-#include "../spacecraft/user_satellite.hpp"
-
-/**
- * @class UserCase
- * @brief An example of user defined simulation case
- */
-class UserCase : public SimulationCase {
- public:
- /**
- * @fn UserCase
- * @brief Constructor
- */
- UserCase(const std::string initialise_base_file);
- /**
- * @fn ~UserCase
- * @brief Destructor
- */
- virtual ~UserCase();
-
- /**
- * @fn GetLogHeader
- * @brief Override function of GetLogHeader
- */
- virtual std::string GetLogHeader() const;
- /**
- * @fn GetLogValue
- * @brief Override function of GetLogValue
- */
- virtual std::string GetLogValue() const;
-
- private:
- UserSatellite *spacecraft_; //!< Instance of spacecraft
-
- /**
- * @fn InitializeTargetObjects
- * @brief Override function of InitializeTargetObjects in SimulationCase
- */
- void InitializeTargetObjects();
-
- /**
- * @fn UpdateTargetObjects
- * @brief Override function of Main in SimulationCase
- */
- void UpdateTargetObjects();
-};
-
-#endif // S2E_SIMULATION_CASE_USER_CASE_HPP_
diff --git a/Tutorials/SampleCodes/s2e-user/src/simulation/spacecraft/user_components.cpp b/Tutorials/SampleCodes/s2e-user/src/simulation/spacecraft/user_components.cpp
deleted file mode 100644
index cad3fc6b..00000000
--- a/Tutorials/SampleCodes/s2e-user/src/simulation/spacecraft/user_components.cpp
+++ /dev/null
@@ -1,41 +0,0 @@
-/**
- * @file user_components.cpp
- * @brief An example of user side components management installed on a spacecraft
- */
-
-#include "user_components.hpp"
-
-#include
-
-UserComponents::UserComponents(const Dynamics *dynamics, Structure *structure, const LocalEnvironment *local_environment,
- const GlobalEnvironment *global_environment, const SimulationConfiguration *configuration,
- ClockGenerator *clock_generator, const unsigned int spacecraft_id)
- : configuration_(configuration),
- dynamics_(dynamics),
- structure_(structure),
- local_environment_(local_environment),
- global_environment_(global_environment) {
- obc_ = new OnBoardComputer(clock_generator);
-}
-
-UserComponents::~UserComponents() {
- // OBC must be deleted the last since it has com ports
- delete obc_;
-}
-
-Vector<3> UserComponents::GenerateForce_b_N() {
- // There is no orbit control component, so it remains 0
- Vector<3> force_b_N(0.0);
- return force_b_N;
-}
-
-Vector<3> UserComponents::GenerateTorque_b_Nm() {
- // No attitude control component
- Vector<3> torque_b_Nm(0.0);
- return torque_b_Nm;
-}
-
-void UserComponents::LogSetup(Logger &logger) {
- // Users can set log output when they need component log
- UNUSED(logger);
-}
diff --git a/Tutorials/SampleCodes/s2e-user/src/simulation/spacecraft/user_components.hpp b/Tutorials/SampleCodes/s2e-user/src/simulation/spacecraft/user_components.hpp
deleted file mode 100644
index a9146e40..00000000
--- a/Tutorials/SampleCodes/s2e-user/src/simulation/spacecraft/user_components.hpp
+++ /dev/null
@@ -1,41 +0,0 @@
-/**
- * @file sample_components.hpp
- * @brief An example of user side components management installed on a spacecraft
- */
-
-#ifndef S2E_SIMULATION_SPACECRAFT_USER_COMPONENTS_HPP_
-#define S2E_SIMULATION_SPACECRAFT_USER_COMPONENTS_HPP_
-
-#include
-#include
-#include
-#include
-#include
-
-// include for components
-#include
-
-class UserComponents : public InstalledComponents {
- public:
- UserComponents(const Dynamics *dynamics, Structure *structure, const LocalEnvironment *local_environment,
- const GlobalEnvironment *global_environment, const SimulationConfiguration *configuration, ClockGenerator *clock_generator,
- const unsigned int spacecraft_id);
- ~UserComponents();
- libra::Vector<3> GenerateForce_b_N();
- libra::Vector<3> GenerateTorque_b_Nm();
- void LogSetup(Logger &logger);
-
- private:
- // Components
- OnBoardComputer *obc_; //!< Onboard Computer
-
- // States
- const SimulationConfiguration *configuration_; //!< Simulation settings
- const Dynamics *dynamics_; //!< Dynamics information of the spacecraft
- Structure *structure_; //!< Structure information of the spacecraft
- const LocalEnvironment *local_environment_; //!< Local environment information around the spacecraft
- const GlobalEnvironment *global_environment_; //!< Global environment information
-};
-
-#endif // S2E_SIMULATION_SPACECRAFT_USER_COMPONENTS_HPP_
-
diff --git a/Tutorials/SampleCodes/s2e-user/src/simulation/spacecraft/user_satellite.cpp b/Tutorials/SampleCodes/s2e-user/src/simulation/spacecraft/user_satellite.cpp
deleted file mode 100644
index b69491b1..00000000
--- a/Tutorials/SampleCodes/s2e-user/src/simulation/spacecraft/user_satellite.cpp
+++ /dev/null
@@ -1,15 +0,0 @@
-/**
- * @file user_satellite.cpp
- * @brief An example of user side spacecraft class
- */
-
-#include "user_satellite.hpp"
-
-#include "user_components.hpp"
-
-UserSatellite::UserSatellite(const SimulationConfiguration *simulation_configuration, const GlobalEnvironment *global_environment,
- const unsigned int spacecraft_id)
- : Spacecraft(simulation_configuration, global_environment, spacecraft_id) {
- components_ =
- new UserComponents(dynamics_, structure_, local_environment_, global_environment, simulation_configuration, &clock_generator_, spacecraft_id);
-}
diff --git a/Tutorials/SampleCodes/s2e-user/src/simulation/spacecraft/user_satellite.hpp b/Tutorials/SampleCodes/s2e-user/src/simulation/spacecraft/user_satellite.hpp
deleted file mode 100644
index 83c6b9a4..00000000
--- a/Tutorials/SampleCodes/s2e-user/src/simulation/spacecraft/user_satellite.hpp
+++ /dev/null
@@ -1,30 +0,0 @@
-/**
- * @file user_satellite.hpp
- * @brief An example of user side spacecraft class
- */
-
-#ifndef S2E_SIMULATION_SPACECRAFT_USER_SATELLITE_HPP_
-#define S2E_SIMULATION_SPACECRAFT_USER_SATELLITE_HPP_
-
-#include
-#include "user_components.hpp"
-
-/**
- * @class UserSatellite
- * @brief An example of user side spacecraft class
- */
-class UserSatellite : public Spacecraft
-{
-public:
- /**
- * @fn UserSatellite
- * @brief Constructor
- */
- UserSatellite(const SimulationConfiguration *simulation_configuration, const GlobalEnvironment *global_environment,
- const unsigned int spacecraft_id);
-
-private:
-};
-
-#endif // S2E_SIMULATION_SPACECRAFT_USER_SATELLITE_HPP_
-
- 
- 
- 
+ 
diff --git a/Specifications/Dynamics/Spec_Orbit.md b/Specifications/Dynamics/Spec_Orbit.md
index a8203225..c914294a 100644
--- a/Specifications/Dynamics/Spec_Orbit.md
+++ b/Specifications/Dynamics/Spec_Orbit.md
@@ -27,7 +27,7 @@
- This setting works only for `RK4`, `KEPLER`, and `ENCKE` mode.
- Set the orbit information in the ini file
- You can see the details in the documents for each orbit propagation mode.
- - The definition of the coordinate system is decided in `PlanetSelect.ini`
+ - The definition of the coordinate system is decided at `[CELESTIAL_INFORMATION]` section in `sample_simulation_base.ini`.
## 2. Explanation of Algorithm
In the Orbit base class provides the following common functions for every propagator.
diff --git a/Specifications/Dynamics/Spec_RelativeOrbit.md b/Specifications/Dynamics/Spec_RelativeOrbit.md
index f1c925dd..3c994f91 100644
--- a/Specifications/Dynamics/Spec_RelativeOrbit.md
+++ b/Specifications/Dynamics/Spec_RelativeOrbit.md
@@ -58,7 +58,7 @@
+ Add the name of the dynamics model to `StmModel` enum in `relative_orbit_models.hpp`.
+ Add the function to calculate the system matrix as `CalcHcwStm`in `relative_orbit_models.hpp`.
- + Edit the `CalculateSTM` function in `relative_orbit.hpp`.
+ + Edit the `CalculateStm` function in `relative_orbit.hpp`.
## 2. Explanation of Algorithm
@@ -69,20 +69,11 @@
2. inputs and outputs
+ input
- * `initial_relative_position_lvlh_m`, `initial_relative_velocity_lvlh_m_s`
+ * `relative_position_lvlh_m`, `relative_velocity_lvlh_m_s`
- The initial state of the satellite
* `gravity_constant_m3_s2`
- The gravity constant of the reference celestial body $\mu$
- * `reference_sat_initial_orbit`
- - The initial orbit of the reference satellite
- - NOTE: This is used only for the initialization.
- * `current_jd`
- - The initial Julian day
- * `timestep`
- - RK4 propagation timestep
- * `wgs`
- - Type of the World Geometric System
- * `init_time`
+ * `initial_time_s`
- Initial simulation time (default value is 0)
+ output
* none
@@ -102,7 +93,7 @@
- The type of relative dynamics model
* `reference_sat_orbit`
- The orbit of the reference satellite
- * `mu`
+ * `gravity_constant_m3_s2`
- The gravity constant $\mu$
+ output
* none
@@ -111,10 +102,10 @@
4. note
-1. `CalculateSTM`
+1. `CalculateStm`
1. overview
- + The `CalculateSTM` function is used only inside the `RelativeOrbit` class. This function calls the system matrix calculation function according to `stm_model_type`.
+ + The `CalculateStm` function is used only inside the `RelativeOrbit` class. This function calls the system matrix calculation function according to `stm_model_type`.
2. inputs and outputs
+ input
@@ -122,7 +113,7 @@
- The type of relative dynamics model
* `reference_sat_orbit`
- The orbit of the reference satellite
- * `mu`
+ * `gravity_constant_m3_s2`
- The gravity constant $\mu$
* `elapsed_sec`
- Elapsed simulation time
@@ -137,13 +128,13 @@
1. overview
+ The `CalculateHillSystemMatrix` function calculates the system matrix of the Hill equation.
- + This function is declared in `RelativeOrbitModels.h` and is used by the
+ + This function is declared in `relative_orbit_models.hpp` and is used by the
2. inputs and outputs
+ input
* `orbit_radius`
- Radius of the reference satellite orbit $R$
- * `mu`
+ * `gravity_constant_m3_s2`
- The gravity constant $\mu$
+ output
* `system_matrix`
@@ -172,17 +163,17 @@
4. note
-1. `CalculateHCWSTM`
+1. `CalculateHcwStm`
1. overview
- + The `CalculateHCWSTM` function calculates the Hill-Clohessy-Wiltshire STM.
- + This function is declared in `RelativeOrbitModels.h` and is used by the
+ + The `CalculateHcwStm` function calculates the Hill-Clohessy-Wiltshire STM.
+ + This function is declared in `relative_orbit_models.hpp` and is used by the
2. inputs and outputs
+ input
* `orbit_radius`
- Radius of the reference satellite orbit $R$
- * `mu`
+ * `gravity_constant_m3_s2`
- The gravity constant $\mu$
* `elapsed_sec`
- Elapsed simulation time
@@ -223,62 +214,60 @@
2. conditions for the verification
1. input files
- Initialization files for the two satellites were prepared.
- - `Sat0.ini`
- - `Sat1.ini`
+ - `satellite0.ini`
+ - `satellite1.ini`
2. initial values
- - The orbit of the reference satellite (Sat0) is GEO. The initial position of the satellite (Sat1) is $(0\mathrm{m}, 100\mathrm{m}, 0\mathrm{m})^\mathrm{T}$ in LVLH frame. The orbit was propagated for 86400 sec (the period of GEO).
- - `Sat0.ini`
+ - The orbit of the reference satellite (satellite0) is GEO. The initial position of the satellite (satellite1) is $(0\mathrm{m}, 100\mathrm{m}, 0\mathrm{m})^\mathrm{T}$ in LVLH frame. The orbit was propagated for 86400 sec (the period of GEO).
+ - `satellite0.ini`
```
- propagate_mode = 0
+ propagate_mode = RK4
//Information used for orbital propagation by the Runge-Kutta method///////////
//initial satellite position[m]
//＊The coordinate system is defined in PlanetSelect.ini
- init_position(0) = 4.2164140100E+07 //radius of GEO
- init_position(1) = 0
- init_position(2) = 0
+ initial_position_i_m(0) = 4.2164140100E+07 //radius of GEO
+ initial_position_i_m(1) = 0
+ initial_position_i_m(2) = 0
//initial satellite velocity[m/s]
//＊The coordinate system is defined in PlanetSelect.ini
- init_velocity(0) = 0
- init_velocity(1) = 3.074661E+03 //Speed of a spacecraft in GEO
- init_velocity(2) = 0
+ initial_velocity_i_m_s(0) = 0
+ initial_velocity_i_m_s(1) = 3.074661E+03 //Speed of a spacecraft in GEO
+ initial_velocity_i_m_s(2) = 0
///////////////////////////////////////////////////////////////////////////////
```
- - `Sat1.ini`
+ - `satellite1.ini`
```
- propagate_mode = 2
+ propagate_mode = RELATIVE
//Information used for relative orbit propagation//////////////////////////////
//Relative Orbit Update Method (0 means RK4, 1 means STM)
- update_method = 0
- //RK4 Relative Dynamics model type (only valid for RK4 update)
- //0: Hill
+ relative_orbit_update_method = 0
+ // RK4 Relative Dynamics model type (only valid for RK4 update)
+ // 0: Hill
relative_dynamics_model_type = 0
- //STM Relative Dynamics model type (only valid for STM update)
- //0: HCW
+ // STM Relative Dynamics model type (only valid for STM update)
+ // 0: HCW
stm_model_type = 0
- //initial satellite position relative to the reference satellite in LVLH frame[m]
- //＊The coordinate system is defined in PlanetSelect.ini
- init_relative_position_lvlh(0) = 0.0
- init_relative_position_lvlh(1) = 100.0
- init_relative_position_lvlh(2) = 0.0
- //initial satellite velocity relative to the reference satellite in LVLH frame[m/s]
- //＊The coordinate system is defined in PlanetSelect.ini
- init_relative_velocity_lvlh(0) = 0.0
- init_relative_velocity_lvlh(1) = 0.0
- init_relative_velocity_lvlh(2) = 0.0
- //information of reference satellite
- reference_sat_id = 0
- reference_sat_ini_file = ../../data/ini/Sat0.ini
+ // Initial satellite position relative to the reference satellite in LVLH frame[m]
+ // * The coordinate system is defined at [PLANET_SELECTION] in SampleSimBase.ini
+ initial_relative_position_lvlh_m(0) = 0.0
+ initial_relative_position_lvlh_m(1) = 100.0
+ initial_relative_position_lvlh_m(2) = 0.0
+ // initial satellite velocity relative to the reference satellite in LVLH frame[m/s]
+ initial_relative_velocity_lvlh_m_s(0) = 0.0
+ initial_relative_velocity_lvlh_m_s(1) = 0.0
+ initial_relative_velocity_lvlh_m_s(2) = 0.0
+ // information of reference satellite
+ reference_satellite_id = 0
///////////////////////////////////////////////////////////////////////////////
```
3. results
- - The position of Sat1 seen from Sat0 in the inertia frame was calculated.
+ - The position of satellite1 seen from satellite0 in the inertia frame was calculated.