diff --git a/.github/workflows/build.yml b/.github/workflows/build.yml
index 346dbb7..541276c 100644
--- a/.github/workflows/build.yml
+++ b/.github/workflows/build.yml
@@ -8,7 +8,7 @@ on:
   pull_request:
 
 env:
-  S2E_CORE_VERSION: v5.0.0
+  S2E_CORE_VERSION: v6.0.0
   C2A_CORE_VERSION: develop
 
 jobs:
@@ -101,7 +101,7 @@ jobs:
         shell: cmd
         run: |
           cl.exe
-          cmake -G "Visual Studio 17 2022" -A Win32 -DCMAKE_CONFIGURATION_TYPES:STRING="Debug" -DEXT_LIB_DIR=../s2e-core/ExtLibraries -DFLIGHT_SW_DIR=../c2a-core -DC2A_NAME=Examples/minimum_user_for_s2e -D${{ matrix.use_c2a }}
+          cmake -G "Visual Studio 17 2022" -A Win32 -DCMAKE_CONFIGURATION_TYPES:STRING="Debug" -DEXT_LIB_DIR=../s2e-core/ExtLibraries -DFLIGHT_SW_DIR=../c2a-core -DC2A_NAME=Examples/minimum_user -D${{ matrix.use_c2a }}
           cmake --build . --clean-first
 
   build_s2e_linux:
@@ -181,5 +181,5 @@ jobs:
       - name: build
         working-directory: ./s2e-user
         run: |
-          cmake . -DEXT_LIB_DIR=../s2e-core/ExtLibraries -DFLIGHT_SW_DIR=../c2a-core -DC2A_NAME=Examples/minimum_user_for_s2e -D${{ matrix.use_c2a }} -DUSE_SCI_COM_WINGS=OFF
+          cmake . -DEXT_LIB_DIR=../s2e-core/ExtLibraries -DFLIGHT_SW_DIR=../c2a-core -DC2A_NAME=Examples/minimum_user -D${{ matrix.use_c2a }} -DUSE_SCI_COM_WINGS=OFF
           cmake --build .
diff --git a/.github/workflows/check-format.yml b/.github/workflows/check-format.yml
new file mode 100644
index 0000000..e8bf945
--- /dev/null
+++ b/.github/workflows/check-format.yml
@@ -0,0 +1,49 @@
+name: check format
+
+on:
+  push:
+    branches:
+      - main
+      - develop
+  pull_request:
+    paths:
+      - '.github/workflows/check-format.yml'
+      - '.clang-format'
+      - 'src/**'
+
+jobs:
+  clang-format:
+    runs-on: ubuntu-latest
+
+    steps:
+      - uses: actions/checkout@v3
+        with:
+          fetch-depth: 2
+
+      - name: install clang-format
+        run: |
+          sudo apt-get update
+          sudo apt-get install -y clang-format
+          clang-format --version
+
+      - name: check clang-format version
+        run: |
+          clang-format --version
+          md5sum "$(which git-clang-format)"
+          head "$(which git-clang-format)"
+
+      - name: check format(push)
+        if: github.event_name == 'push'
+        run: |
+          git-clang-format --commit HEAD^ --diff | tee format.patch
+
+      - name: check format(pull_request)
+        if: github.event_name == 'pull_request'
+        run: |
+          git-clang-format --commit ${{ github.event.pull_request.base.sha }} --diff | tee format.patch
+
+      - name: check
+        run: |
+          git apply --allow-empty format.patch
+          git status
+          git diff --exit-code
diff --git a/.github/workflows/labeler.yml b/.github/workflows/labeler.yml
index 85f2bfd..d84c3eb 100644
--- a/.github/workflows/labeler.yml
+++ b/.github/workflows/labeler.yml
@@ -17,7 +17,7 @@ jobs:
       - uses: actions/checkout@v3
 
       - name: Run Labeler
-        uses: crazy-max/ghaction-github-labeler@v3
+        uses: crazy-max/ghaction-github-labeler@v4
         with:
           github-token: ${{ secrets.GITHUB_TOKEN }}
           yaml-file: .github/labels.yml
diff --git a/CMakeLists.txt b/CMakeLists.txt
index 2b7698c..a4fe3b1 100644
--- a/CMakeLists.txt
+++ b/CMakeLists.txt
@@ -2,7 +2,7 @@ cmake_policy(SET CMP0048 NEW)
 project(S2E_FOR_C2A_CORE
   LANGUAGES CXX
   DESCRIPTION "S2E_FOR_C2A_CORE"
-  VERSION 1.0
+  VERSION 2.0.0
 )
 
 cmake_minimum_required(VERSION 3.13)
@@ -39,7 +39,6 @@ if(USE_C2A)
   add_definitions(-DSILS_FW)
   #include_directories of C2A
   include_directories(${C2A_DIR}/src)
-  include_directories(${S2E_CORE_DIR}/src/Interface/SpacecraftInOut)
 
   #add subdirectory
   set(BUILD_C2A_AS_CXX ON)
@@ -62,60 +61,21 @@ set(S2E_DIR ${CMAKE_CURRENT_COURCE_DIR})
 include_directories(${CSPICE_DIR}/include)
 include_directories(${NRLMSISE00_DIR}/src)
 include_directories(${S2E_CORE_DIR}/src)
-include_directories(${S2E_CORE_DIR}/src/Library/math)
-include_directories(${S2E_CORE_DIR}/src/Library/utils)
-include_directories(${S2E_CORE_DIR}/src/Dynamics)
-include_directories(${S2E_CORE_DIR}/src/Disturbance)
-include_directories(${S2E_CORE_DIR}/src/Interface/InitInput)
-include_directories(${S2E_CORE_DIR}/src/Interface/LogOutput)
-include_directories(${S2E_CORE_DIR}/src/Interface/SpacecraftInOut/Ports)
-include_directories(${S2E_CORE_DIR}/src/Simulation)
-include_directories(${S2E_CORE_DIR}/src/Simulation/MCSim)
-include_directories(${S2E_CORE_DIR}/src/Simulation/Spacecraft)
-include_directories(${S2E_CORE_DIR}/src/Simulation/Spacecraft/Structure)
-include_directories(${S2E_CORE_DIR}/src/Simulation/GroundStation)
-include_directories(${S2E_CORE_DIR}/src/Simulation/Case)
-include_directories(${S2E_CORE_DIR}/src/Disturbance)
-include_directories(${S2E_CORE_DIR}/src/Environment/Global)
-include_directories(${S2E_CORE_DIR}/src/Environment/Local)
-include_directories(${S2E_CORE_DIR}/src/Component)
-include_directories(${S2E_CORE_DIR}/src/Component/Abstract)
-include_directories(${S2E_CORE_DIR}/src/Component/AOCS)
-include_directories(${S2E_CORE_DIR}/src/Component/CDH)
-include_directories(${S2E_CORE_DIR}/src/Component/CommGS)
-include_directories(${S2E_CORE_DIR}/src/Component/Mission/Telescope)
-include_directories(${S2E_CORE_DIR}/src/Component/Power)
-include_directories(${S2E_CORE_DIR}/src/Component/Propulsion)
-include_directories(${S2E_CORE_DIR}/src/Component/Thermal)
 
 ## add_subdirectories
-add_subdirectory(${S2E_CORE_DIR}/src/Component S2E_CORE/Component)
-add_subdirectory(${S2E_CORE_DIR}/src/Disturbance S2E_CORE/Disturbance)
-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/RelativeInformation S2E_CORE/RelativeInformation)
-add_subdirectory(${S2E_CORE_DIR}/src/Interface/InitInput S2E_CORE/InitInput)
-add_subdirectory(${S2E_CORE_DIR}/src/Interface/LogOutput S2E_CORE/LogOutput)
-add_subdirectory(${S2E_CORE_DIR}/src/Interface/SpacecraftInOut S2E_CORE/SpacecraftInOut)
-add_subdirectory(${S2E_CORE_DIR}/src/Interface/HilsInOut S2E_CORE/HilsInOut)
-add_subdirectory(${S2E_CORE_DIR}/src/Library/igrf S2E_CORE/igrf)
-add_subdirectory(${S2E_CORE_DIR}/src/Library/inih S2E_CORE/inih)
-add_subdirectory(${S2E_CORE_DIR}/src/Library/math S2E_CORE/math)
-add_subdirectory(${S2E_CORE_DIR}/src/Library/nrlmsise00 S2E_CORE/nrlmsise00)
-add_subdirectory(${S2E_CORE_DIR}/src/Library/sgp4 S2E_CORE/sgp4)
-add_subdirectory(${S2E_CORE_DIR}/src/Library/utils S2E_CORE/utils)
-add_subdirectory(${S2E_CORE_DIR}/src/Library/optics S2E_CORE/optics)
-add_subdirectory(${S2E_CORE_DIR}/src/Library/RelativeOrbit S2E_CORE/RelativeOrbit)
-add_subdirectory(${S2E_CORE_DIR}/src/Library/Orbit S2E_CORE/Orbit)
-add_subdirectory(${S2E_CORE_DIR}/src/Library/Geodesy S2E_CORE/Geodesy)
-add_subdirectory(${S2E_CORE_DIR}/src/Simulation S2E_CORE/Simulation)
+add_subdirectory(${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_for_c2a_core.cpp
-  src/Simulation/Case/c2a_core_sample_case.cpp
-  src/Simulation/Spacecraft/c2a_core_sample_sat.cpp
-  src/Simulation/Spacecraft/c2a_core_sample_components.cpp
+  src/simulation/case/c2a_core_sample_case.cpp
+  src/simulation/spacecraft/c2a_core_sample_satellite.cpp
+  src/simulation/spacecraft/c2a_core_sample_components.cpp
 )
 # Create executable file
 add_executable(${PROJECT_NAME} ${SOURCE_FILES})
@@ -171,22 +131,19 @@ 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 SC_IO RELATIVE_INFO ${S2E_LIBRARIES})
-target_link_libraries(DYNAMICS GLOBAL_ENVIRONMENT LOCAL_ENVIRONMENT SIMULATION ${S2E_LIBRARIES})
-target_link_libraries(DISTURBANCE DYNAMICS GLOBAL_ENVIRONMENT LOCAL_ENVIRONMENT ${S2E_LIBRARIES})
-target_link_libraries(SIMULATION DYNAMICS GLOBAL_ENVIRONMENT LOCAL_ENVIRONMENT DISTURBANCE ${S2E_LIBRARIES})
-target_link_libraries(GLOBAL_ENVIRONMENT ${CSPICE_LIB} ${S2E_LIBRARIES})
-target_link_libraries(LOCAL_ENVIRONMENT GLOBAL_ENVIRONMENT ${CSPICE_LIB} ${S2E_LIBRARIES})
-target_link_libraries(WRAPPER_NRLMSISE00 ${NRLMSISE00_LIB})
+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(${PROJECT_NAME} RELATIVE_INFO)
-target_link_libraries(${PROJECT_NAME} INI_ACC LOG_OUT SC_IO)
 target_link_libraries(${PROJECT_NAME} COMPONENT)
-target_link_libraries(${PROJECT_NAME} HILS_IO)
 
 ## C2A integration
 if(USE_C2A)
@@ -203,8 +160,6 @@ if(USE_HILS)
   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 "")
-  set_target_properties(HILS_IO PROPERTIES COMMON_LANGUAGE_RUNTIME "")
-  set_target_properties(RELATIVE_INFO PROPERTIES COMMON_LANGUAGE_RUNTIME "")
 endif()
 
 ## Cmake debug
diff --git a/README.md b/README.md
index 25c1488..365b294 100644
--- a/README.md
+++ b/README.md
@@ -1,14 +1,14 @@
 # S2E User for C2A Core
 
 ## Overview
-- This repository is an example of S2E User to execute a sample of [minimum C2A](https://github.com/ut-issl/c2a-core/tree/develop/Examples/minimum_user_for_s2e) and to support an operation with WINGS (TBA).
+- This repository is an example of S2E User to execute a sample of [minimum C2A](https://github.com/ut-issl/c2a-core/tree/develop/Examples/minimum_user) and to support an operation with WINGS (TBA).
 - The CI system for c2a-core are using this repository.
 - This is also an example of SILS/HILS test for C2A development.
 
 
 ## Notes
-- Details are described [S2E Document: How to integrate C2A](https://github.com/ut-issl/s2e-documents/blob/main/Tutorials/HowToIntegrateC2A.md).
-- s2e-core [v5.0.0](https://github.com/ut-issl/s2e-core/releases/tag/v5.0.0) is used.
+- Details are described [S2E Document: How to integrate C2A](https://github.com/ut-issl/s2e-documents/blob/develop/Tutorials/HowToIntegrateC2A.md).
+- s2e-core [v6.0.0](https://github.com/ut-issl/s2e-core/releases/tag/v6.0.0) is used.
 
 
 ## Related repositories
@@ -17,14 +17,14 @@
 
 
 ## 概要
-- C2A Core に含まれる [最小限のC2A サンプル](https://github.com/ut-issl/c2a-core/tree/develop/Examples/minimum_user_for_s2e) を SILS で動かし，かつ， WINGS (TBA) によって運用（コマンド操作とテレメトリ受信）できるようにするための最低限の S2E User．
+- C2A Core に含まれる [最小限のC2A サンプル](https://github.com/ut-issl/c2a-core/tree/develop/Examples/minimum_user) を SILS で動かし，かつ， WINGS (TBA) によって運用（コマンド操作とテレメトリ受信）できるようにするための最低限の S2E User．
 - C2A Core の CI にもこの S2E を使っている．
 - C2A 開発を始める際につかう SILS/HILS の雛形にもなりうる．
 
 
 ## C2A in S2E について
-- 詳細は [S2E Document: How to integrate C2A](https://github.com/ut-issl/s2e-documents/blob/main/Tutorials/HowToIntegrateC2A.md) を参照のこと．
-- ここでは，S2E Core のバージョンは [v5.0.0](https://github.com/ut-issl/s2e-core/releases/tag/v5.0.0) を用いる．
+- 詳細は [S2E Document: How to integrate C2A](https://github.com/ut-issl/s2e-documents/blob/develop/Tutorials/HowToIntegrateC2A.md) を参照のこと．
+- ここでは，S2E Core のバージョンは [v6.0.0](https://github.com/ut-issl/s2e-core/releases/tag/v6.0.0) を用いる．
 
 
 ## 関連リポジトリ
diff --git a/data/ini/c2a_core_disturbance.ini b/data/ini/c2a_core_disturbance.ini
deleted file mode 100644
index ee6928e..0000000
--- a/data/ini/c2a_core_disturbance.ini
+++ /dev/null
@@ -1,42 +0,0 @@
-[GEOPOTENTIAL]
-calculation = DISABLE
-logging = DISABLE
-degree = 4
-file_path = ../../../ExtLibraries/GeoPotential/egm96_to360.ascii
-
-
-[MAG_DISTURBANCE]
-calculation = DISABLE
-logging = DISABLE
-
-
-[AIRDRAG]
-calculation = DISABLE
-logging = DISABLE
-// Condition of air drag
-Temp_wall = 30		// Surface Temperature[degC]
-Temp_molecular = 3	// Atmosphere Temperature[degC]
-// Note: they are converted in unit [K] inside the codes
-Molecular = 18.0 // Molecular weight of the thermosphere[g/mol]
-
-
-[SRDIST]
-calculation = DISABLE
-logging = DISABLE
-
-
-[GRAVITY_GRADIENT]
-calculation = DISABLE
-logging = DISABLE
-
-
-[THIRD_BODY_GRAVITY]
-calculation = DISABLE
-logging = DISABLE
-// The number of gravity-generating bodies other than the central body
-num_of_third_body = 0
-// ist of gravity-generating bodies other than the central body
-// All these bodies must be included in the "selected_body" of "PlanetSelect.ini"
-third_body(0) = SUN
-third_body(1) = MOON
-third_body(2) = MARS
diff --git a/data/ini/c2a_core_local_environment.ini b/data/ini/c2a_core_local_environment.ini
deleted file mode 100644
index a5bc2fa..0000000
--- a/data/ini/c2a_core_local_environment.ini
+++ /dev/null
@@ -1,34 +0,0 @@
-[MAG_ENVIRONMENT]
-calculation = DISABLE
-logging = DISABLE
-coeff_file = ../../../s2e-core/src/Library/igrf/igrf13.coef
-mag_rwdev = 10.0     //Random Walk speed[nT]
-mag_rwlimit = 400.0  //Random Walk max limit[nT]
-mag_wnvar = 50.0     //White noise standard deviation [nT]
-
-
-[SRP]
-calculation = DISABLE
-logging = DISABLE
-
-
-[ATMOSPHERE]
-calculation = DISABLE
-logging = DISABLE
-
-// Atmosphere model
-// STANDARD: Model using scale height, NRLMSISE00: NRLMSISE00 model
-model = STANDARD
-nrlmsise00_table_path = ../../../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_param_used = DISABLE
-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
-rho_stddev = 0.0             // Standard deviation of the air density
-
-
-[LOCAL_CELESTIAL_INFORMATION]
-logging = DISABLE
diff --git a/data/ini/c2a_core_sample_sat.ini b/data/ini/c2a_core_sample_sat.ini
deleted file mode 100644
index b6abb0a..0000000
--- a/data/ini/c2a_core_sample_sat.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 = CONTROLLED
-
-// Initial angular velocity at body frame，[rad/s]
-Omega_b(0) = 0.0
-Omega_b(1) = 0.0
-Omega_b(2) = 0.0
-
-// Initial quaternion，i->b，(real part，imaginary part)
-Quaternion_i2b(0) = 0.0
-Quaternion_i2b(1) = 0.0
-Quaternion_i2b(2) = 0.0
-Quaternion_i2b(3) = 1.0
-
-// Initial torque at body frame，[Nm]
-// Note: The initial torque added just for the first propagation step
-Torque_b(0) = +0.000
-Torque_b(1) = -0.000
-Torque_b(2) =  0.000
-
-
-[ControlledAttitude]
-// 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
-pointing_t_b(0) = 0.707
-pointing_t_b(1) = 0.707
-pointing_t_b(2) = 0.0
-
-// Pointing direction @ body frame for sub pointing mode
-// pointing_t_b and pointing_sub_t_b should separate larger than 30 degrees.
-pointing_sub_t_b(0) = 0.0
-pointing_sub_t_b(1) = 0.0
-pointing_sub_t_b(2) = 1.0
-
-
-[ORBIT]
-calculation = DISABLE
-logging = DISABLE
-
-// 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 = SGP4
-
-// TLE definition for SGP4 ///////////////////////////////////////////////
-// 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
-wgs = 2 // 0: wgs72old, 1: wgs72, 2: wgs84
-//////////////////////////////////////////////////////////////////////////
-
-// Initial value definition for RK4 //////////////////////////////////////
-// ＊The coordinate system is defined in PlanetSelect.ini
-// Initial satellite position[m]
-init_position(0) = 4.2164140100E+07  // radius of GEO
-init_position(1) = 0
-init_position(2) = 0
-
-//initial satellite velocity[m/s]
-init_velocity(0) = 0
-init_velocity(1) = 3.074661E+03  // Speed of a spacecraft in GEO
-init_velocity(2) = 0
-///////////////////////////////////////////////////////////////////////////
-
-// Information used 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 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]
-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 = 1
-///////////////////////////////////////////////////////////////////////////////
-
-// Information used for orbital propagation by the Kepler Motion ///////////
-// initialize mode for kepler motion
-// INIT_POSVEL : initialize with position and velocity defined for RK4
-// INIT_OE : initialize with the following orbital elements
-init_mode_kepler = INIT_POSVEL
-// Orbital Elements for INIT_OE
-semi_major_axis_m = 6794500.0
-eccentricity = 0.0015
-inclination_rad = 0.9012
-raan_rad = 0.1411
-arg_perigee_rad = 1.7952
-epoch_jday = 2.458940966402607e6
-///////////////////////////////////////////////////////////////////////////////
-
-
-// Information used for orbital propagation by the Encke Formulation ///////////
-error_tolerance = 0.0001
-// initialize position and vector are same with RK4 setting
-///////////////////////////////////////////////////////////////////////////////
-
-[Thermal]
-IsCalcEnabled=0
-debug=0
-
-[LOCAL_ENVIRONMENT]
-local_env_file = ../../data/ini/c2a_core_local_environment.ini
-
-
-[DISTURBANCE]
-dist_file = ../../data/ini/c2a_core_disturbance.ini
-
-
-[STRUCTURE_FILE]
-structure_file = ../../data/ini/c2a_core_structure.ini
-
-
-[COMPONENTS_FILE]
-// Users can add the path for component initialize files here.
diff --git a/data/ini/c2a_core_sim_base.ini b/data/ini/c2a_core_sim_base.ini
deleted file mode 100644
index 2aa5607..0000000
--- a/data/ini/c2a_core_sim_base.ini
+++ /dev/null
@@ -1,98 +0,0 @@
-[TIME]
-// Simulation start date [UTC]
-StartYMDHMS=2020/01/01 12:00:00.0
-
-// Simulation finish time [sec]
-EndTimeSec=86400
-
-// Simulation step time [sec]
-// Minimum time step for the entire simulation
-StepTimeSec=0.1
-
-// Attitude Update Period [sec]
-// Attitude is updated at the period specified here
-AttitudeUpdateIntervalSec=10 // should be larger than StepTimeSec
-
-// Attitide Δt for Runge-Kutt method [sec]
-// This must be smaller than "AttitudeUpdateIntervalSec"
-AttitudeRKStepSec = 10
-
-// Orbit Update Period [sec]
-// Orbit is updated at the period specified here
-OrbitUpdateIntervalSec = 10 // should be larger than StepTimeSec
-
-// Orbit Δt for Runge-Kutta method [sec]
-// This must be smaller than "OrbitUpdateIntervalSec"
-OrbitRKStepSec = 10
-
-// Thermal Update Period [sec]
-// Thermal is updated at the period specified here
-ThermalUpdateIntervalSec = 10 // should be larger than StepTimeSec
-
-// Thermal Δt for Runge-Kutta method [sec]
-// This must be smaller than "ThermalUpdateIntervalSec"
-ThermalRKStepSec = 10
-
-// Component Update Period [sec]
-CompoUpdateIntervalSec = 0.1 // should be larger than StepTimeSec
-
-// Log Output Period [sec]
-LogOutPutIntervalSec = 10   // should be larger than StepTimeSec
-
-// Simulation speed
-// 0: as fast as possible, 1: real-time, >1: faster than real-time, <1: slower than real-time
-SimulationSpeed = 1
-
-
-[PLANET_SELECTION]
-// Whether global celestial information is logged or not
-logging = DISABLE
-
-// Definition of Inertial frame
-inertial_frame = J2000
-aberration_correction = NONE
-center_object = EARTH
-
-// Earth Rotation model
-// Idle:no motion，Simple:rotation only，Full:full-dynamics
-rotation_mode = Simple
-
-// Definition of calculation celestial bodies
-num_of_selected_body = 2
-selected_body(0) = EARTH
-selected_body(1) = SUN
-selected_body(2) = MOON
-selected_body(3) = MARS
-
-
-[FURNSH_PATH]
-// 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_path = ../../../ExtLibraries/HipparcosCatalogue/hip_main.csv
-max_magnitude = 3.0	// Max magnitude to read from Hip catalog
-calculation = DISABLE
-logging = DISABLE
-
-
-[RAND]
-// Seed of randam. When this value is 0, the seed will be varied by time.
-Rand_Seed = 0x11223344
-
-
-[SIM_SETTING]
-// Whether the ini files are saved or not
-log_inifile = 1
-
-// Initialize files
-// File name must not over 256 characters (defined in initialize.h as MAX_CHAR_NUM)
-// If you want to add a spacecraft, create the corresponding Sat.ini, and specify it as sat_file(1), sat_file(2)... . 
-num_of_simulated_spacecraft = 1
-sat_file(0)   = ../../data/ini/c2a_core_sample_sat.ini
-log_file_path = ../../data/logs/
diff --git a/data/ini/c2a_core_structure.ini b/data/ini/c2a_core_structure.ini
deleted file mode 100644
index 5ef1dfb..0000000
--- a/data/ini/c2a_core_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 cg_b = zero vector.
-// If users want to define the origin as a specific point, they need to set all vectors to suit their definition carefully.
-//
-
-[STRUCTURE]
-// Inertia Tensor @ body fixed frame [kg・m2]
-Iner(0) = 0.1	//I(0,0)
-Iner(1) = 0.0	//I(0,1)
-Iner(2) = 0.0	//I(0,2)
-Iner(3) = 0.0	//I(1,0)
-Iner(4) = 0.1	//I(1,1)
-Iner(5) = 0.0	//I(1,2)
-Iner(6) = 0.0	//I(2,0)
-Iner(7) = 0.0	//I(2,1)
-Iner(8) = 0.1	//I(2,2)
-
-mass = 14 //[kg]
-
-// Position vector of the center of gravity @ the body frame [m]
-cg_b(0) = 0.01
-cg_b(1) = 0.01
-cg_b(2) = 0.01
-
-[SURFACES]
-num_of_surfaces = 6
-
-// Area of each surface [m^2]
-area_0 = 0.25
-area_1 = 0.25
-area_2 = 0.25
-area_3 = 0.25
-area_4 = 0.25
-area_5 = 0.25
-
-// Position vector of each surface geometric center @ body frame [m]
-position_0(0) = 0.25
-position_0(1) = 0.0
-position_0(2) = 0.0
-position_1(0) = -0.25
-position_1(1) = 0.0
-position_1(2) = 0.0
-position_2(0) = 0.0
-position_2(1) = 0.25
-position_2(2) = 0.0
-position_3(0) = 0.0
-position_3(1) = -0.25
-position_3(2) = 0.0
-position_4(0) = 0.0
-position_4(1) = 0.0
-position_4(2) = 0.25
-position_5(0) = 0.0
-position_5(1) = 0.0
-position_5(2) = -0.25
-
-// Normal vector of each surface @ body frame
-normal_0(0) = 1.0
-normal_0(1) = 0.0
-normal_0(2) = 0.0
-normal_1(0) = -1.0
-normal_1(1) = 0.0
-normal_1(2) = 0.0
-normal_2(0) = 0.0
-normal_2(1) = 1.0
-normal_2(2) = 0.0
-normal_3(0) = 0.0
-normal_3(1) = -1.0
-normal_3(2) = 0.0
-normal_4(0) = 0.0
-normal_4(1) = 0.0
-normal_4(2) = 1.0
-normal_5(0) = 0.0
-normal_5(1) = 0.0
-normal_5(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
-
-[RMM]
-// Constant component of Residual Magnetic Moment(RMM) [A・m^2]
-rmm_const_b(0) = 0.04
-rmm_const_b(1) = 0.04
-rmm_const_b(2) = 0.04
-
-// RMM Random Walk Speed [nT]
-rmm_rwdev = 1.0E-5
-
-// RMM Random Walk Limit [nT]
-rmm_rwlimit = 1.0E-3
-
-// RMM White Noise Standard deviation [nT]
-rmm_wnvar = 5.0E-5
diff --git a/data/initialize_files/c2a_core_disturbance.ini b/data/initialize_files/c2a_core_disturbance.ini
new file mode 100644
index 0000000..1320e50
--- /dev/null
+++ b/data/initialize_files/c2a_core_disturbance.ini
@@ -0,0 +1,47 @@
+[GEOPOTENTIAL]
+// Enable only when the center object is defined as the Earth
+calculation = DISABLE
+logging = DISABLE
+degree = 4
+coefficients_file_path = ../../../ExtLibraries/GeoPotential/egm96_to360.ascii
+
+
+[MAGNETIC_DISTURBANCE]
+// Enable only when the center object is defined as the Earth
+calculation = DISABLE
+logging = DISABLE
+
+
+[AIR_DRAG]
+// Enable only when the center object is defined as the Earth
+calculation = DISABLE
+logging = DISABLE
+
+// 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 = DISABLE
+logging = DISABLE
+
+
+[GRAVITY_GRADIENT]
+calculation = DISABLE
+logging = DISABLE
+
+
+[THIRD_BODY_GRAVITY]
+calculation = DISABLE
+logging = DISABLE
+
+// 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/data/initialize_files/c2a_core_local_environment.ini b/data/initialize_files/c2a_core_local_environment.ini
new file mode 100644
index 0000000..01b6e48
--- /dev/null
+++ b/data/initialize_files/c2a_core_local_environment.ini
@@ -0,0 +1,34 @@
+[MAGNETIC_FIELD_ENVIRONMENT]
+calculation = DISABLE
+logging = DISABLE
+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 = DISABLE
+logging = DISABLE
+
+
+[ATMOSPHERE]
+calculation = DISABLE
+logging = DISABLE
+
+// 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 = DISABLE
diff --git a/data/initialize_files/c2a_core_sample_sat.ini b/data/initialize_files/c2a_core_sample_sat.ini
new file mode 100644
index 0000000..03c4d65
--- /dev/null
+++ b/data/initialize_files/c2a_core_sample_sat.ini
@@ -0,0 +1,137 @@
+[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 = CONTROLLED
+
+// 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 = CONTROLLED
+
+// 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) = 0.707
+main_pointing_direction_b(1) = 0.707
+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 = DISABLE
+logging = DISABLE
+
+// 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 = SGP4
+
+// 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/sample/initialize_files/thermal_csv_files/
+
+[SETTING_FILES]
+local_environment_file = ../../data/initialize_files/c2a_core_local_environment.ini
+disturbance_file  = ../../data/initialize_files/c2a_core_disturbance.ini
+structure_file = ../../data//initialize_files/c2a_core_structure.ini
+
+[COMPONENT_FILES]
+// Users can add the path for component initialize files here.
diff --git a/data/initialize_files/c2a_core_sim_base.ini b/data/initialize_files/c2a_core_sim_base.ini
new file mode 100644
index 0000000..642d811
--- /dev/null
+++ b/data/initialize_files/c2a_core_sim_base.ini
@@ -0,0 +1,101 @@
+[TIME]
+// Simulation start time [UTC]
+simulation_start_time_utc = 2020/01/01 12:00:00.0
+
+// Simulation duration [sec]
+simulation_duration_s = 86400
+
+// 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 = 10 // 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 = 10
+
+// Orbit Update Period [sec]
+// Orbit is updated at the period specified here
+orbit_update_period_s = 10 // 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 = 10 
+
+// Thermal Update Period [sec]
+// Thermal is updated at the period specified here
+thermal_update_period_s = 10 // 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 = 10
+
+// 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 = 10   // 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 = 1
+
+
+[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 = 2
+selected_body_name(0) = EARTH
+selected_body_name(1) = SUN
+selected_body_name(2) = MOON
+selected_body_name(3) = MARS
+
+
+[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
+
+// Initialize files
+// File name must not over 1024 characters (defined in initialize_file_access.hpp as kMaxCharLength)
+// If you want to add a spacecraft, create the corresponding spacecraft.ini, and specify it as spacecraft_file(1), spacecraft_file(2), ect.
+// If you want to add a ground station, create the corresponding ground_station.ini, and specify it as ground_station_file(1), ground_station_file(2), ect.
+number_of_simulated_spacecraft = 1
+number_of_simulated_ground_station = 0
+spacecraft_file(0)      = ../../data/initialize_files/c2a_core_sample_sat.ini
+log_file_save_directory = ../../data/sample/logs/
diff --git a/data/initialize_files/c2a_core_structure.ini b/data/initialize_files/c2a_core_structure.ini
new file mode 100644
index 0000000..b7c707c
--- /dev/null
+++ b/data/initialize_files/c2a_core_structure.ini
@@ -0,0 +1,115 @@
+//
+// 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/data/ini/components/.gitkeep b/data/initialize_files/components/.gitkeep
similarity index 100%
rename from data/ini/components/.gitkeep
rename to data/initialize_files/components/.gitkeep
diff --git a/data/ini/scenario/.gitkeep b/data/initialize_files/scenario/.gitkeep
similarity index 100%
rename from data/ini/scenario/.gitkeep
rename to data/initialize_files/scenario/.gitkeep
diff --git a/src/Simulation/Case/c2a_core_sample_case.cpp b/src/Simulation/Case/c2a_core_sample_case.cpp
deleted file mode 100644
index 019e558..0000000
--- a/src/Simulation/Case/c2a_core_sample_case.cpp
+++ /dev/null
@@ -1,66 +0,0 @@
-#include "c2a_core_sample_case.h"
-
-C2aCoreSampleCase::C2aCoreSampleCase(std::string ini_fname)
-: SimulationCase(ini_fname)
-{
-}
-
-C2aCoreSampleCase::~C2aCoreSampleCase()
-{
-  delete spacecraft_;
-}
-
-void C2aCoreSampleCase::Initialize()
-{
-  // Instantiate the target of the simulation
-  const int sat_id = 0;  // `sat_id=0` corresponds to the index of `sat_file` in Simbase.ini
-  spacecraft_ = new C2aCoreSampleSat(&sim_config_, glo_env_, sat_id);
-
-  // Register the log output
-  glo_env_->LogSetup(*(sim_config_.main_logger_));
-  spacecraft_->LogSetup(*(sim_config_.main_logger_));
-
-  // Write headers to the log
-  sim_config_.main_logger_->WriteHeaders();
-
-  // Start the simulation
-  std::cout << "\nSimulationDateTime \n";
-  glo_env_->GetSimTime().PrintStartDateTime();
-
-}
-
-void C2aCoreSampleCase::Main()
-{
-  glo_env_->Reset(); // for MonteCarlo Sim
-  while (!glo_env_->GetSimTime().GetState().finish)
-  {
-    // Logging
-    if (glo_env_->GetSimTime().GetState().log_output)
-    {
-      sim_config_.main_logger_->WriteValues();
-    }
-    // Global Environment Update
-    glo_env_->Update();
-    // Spacecraft Update
-    spacecraft_->Update(&(glo_env_->GetSimTime()));
-    // Debug output
-    if (glo_env_->GetSimTime().GetState().disp_output)
-    {
-      std::cout << "Progresss: " << glo_env_->GetSimTime().GetProgressionRate() << "%\r";
-    }
-  }
-}
-
-std::string C2aCoreSampleCase::GetLogHeader() const
-{
-  std::string str_tmp = "";
-
-  return str_tmp;
-}
-
-std::string C2aCoreSampleCase::GetLogValue() const
-{
-  std::string str_tmp = "";
-
-  return str_tmp;
-}
diff --git a/src/Simulation/Case/c2a_core_sample_case.h b/src/Simulation/Case/c2a_core_sample_case.h
deleted file mode 100644
index 87613d3..0000000
--- a/src/Simulation/Case/c2a_core_sample_case.h
+++ /dev/null
@@ -1,20 +0,0 @@
-#pragma once
-
-#include "SimulationCase.h"
-#include "../Spacecraft/c2a_core_sample_sat.h"
-
-class C2aCoreSampleCase: public SimulationCase
-{
-public:
-  C2aCoreSampleCase(std::string ini_fname);
-  virtual ~C2aCoreSampleCase();
-
-  void Initialize();
-  void Main();
-
-  virtual std::string GetLogHeader() const;
-  virtual std::string GetLogValue() const;
-
-private:
-  C2aCoreSampleSat* spacecraft_;
-};
diff --git a/src/Simulation/Spacecraft/c2a_core_sample_components.cpp b/src/Simulation/Spacecraft/c2a_core_sample_components.cpp
deleted file mode 100644
index 6103af5..0000000
--- a/src/Simulation/Spacecraft/c2a_core_sample_components.cpp
+++ /dev/null
@@ -1,36 +0,0 @@
-#include "c2a_core_sample_components.h"
-
-#include <Interface/InitInput/IniAccess.h>
-
-#ifdef USE_C2A
-#include "src_user/Settings/port_config.h"
-#endif
-
-C2aCoreSampleComponents::C2aCoreSampleComponents(const Dynamics* dynamics, const Structure* structure, const LocalEnvironment* local_env,
-                                                 const GlobalEnvironment* glo_env, const SimulationConfig* config, ClockGenerator* clock_gen)
-    : dynamics_(dynamics), structure_(structure), local_env_(local_env), glo_env_(glo_env), config_(config) {
-#ifdef USE_C2A
-  obc_ = new OBC_C2A(clock_gen, 100);
-
-  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() {
-  // OBC must be deleted the last since it has com ports
-  delete obc_;
-}
-
-Vector<3> C2aCoreSampleComponents::GenerateForce_N_b() {
-  // There is no orbit control component, so it remains 0
-  Vector<3> force_N_b_(0.0);
-  return force_N_b_;
-}
-
-Vector<3> C2aCoreSampleComponents::GenerateTorque_Nm_b() {
-  // No attitude control component
-  Vector<3> torque_Nm_b_(0.0);
-  return torque_Nm_b_;
-}
-
-void C2aCoreSampleComponents::LogSetup(Logger& logger) { UNUSED(logger); }
diff --git a/src/Simulation/Spacecraft/c2a_core_sample_components.h b/src/Simulation/Spacecraft/c2a_core_sample_components.h
deleted file mode 100644
index 8f255de..0000000
--- a/src/Simulation/Spacecraft/c2a_core_sample_components.h
+++ /dev/null
@@ -1,32 +0,0 @@
-#pragma once
-
-#include <Simulation/Spacecraft/InstalledComponents.hpp>
-
-#include "Dynamics.h"
-#include "GlobalEnvironment.h"
-#include "LocalEnvironment.h"
-#include "Vector.hpp"
-
-// include for components
-#include "OBC_C2A.h"
-
-class C2aCoreSampleComponents : public InstalledComponents {
- public:
-  C2aCoreSampleComponents(const Dynamics* dynamics, const Structure* structure, const LocalEnvironment* local_env, const GlobalEnvironment* glo_env,
-                          const SimulationConfig* config, ClockGenerator* clock_gen);
-  ~C2aCoreSampleComponents();
-  libra::Vector<3> GenerateForce_N_b();
-  libra::Vector<3> GenerateTorque_Nm_b();
-  void LogSetup(Logger& logger);
-
- private:
-  // Components
-  OBC_C2A* obc_;
-
-  // References
-  const Dynamics* dynamics_;
-  const Structure* structure_;
-  const LocalEnvironment* local_env_;
-  const GlobalEnvironment* glo_env_;
-  const SimulationConfig* config_;
-};
diff --git a/src/Simulation/Spacecraft/c2a_core_sample_sat.cpp b/src/Simulation/Spacecraft/c2a_core_sample_sat.cpp
deleted file mode 100644
index 1358731..0000000
--- a/src/Simulation/Spacecraft/c2a_core_sample_sat.cpp
+++ /dev/null
@@ -1,8 +0,0 @@
-#include "c2a_core_sample_sat.h"
-
-#include "c2a_core_sample_components.h"
-
-C2aCoreSampleSat::C2aCoreSampleSat(SimulationConfig* sim_config, const GlobalEnvironment* glo_env, const int sat_id)
-    : Spacecraft(sim_config, glo_env, sat_id) {
-  components_ = new C2aCoreSampleComponents(dynamics_, structure_, local_env_, glo_env, sim_config, &clock_gen_);
-}
diff --git a/src/Simulation/Spacecraft/c2a_core_sample_sat.h b/src/Simulation/Spacecraft/c2a_core_sample_sat.h
deleted file mode 100644
index d9215b3..0000000
--- a/src/Simulation/Spacecraft/c2a_core_sample_sat.h
+++ /dev/null
@@ -1,11 +0,0 @@
-#pragma once
-
-#include "Spacecraft.h"
-#include "c2a_core_sample_components.h"
-
-class C2aCoreSampleSat : public Spacecraft
-{
-public:
-  C2aCoreSampleSat(SimulationConfig* sim_config, const GlobalEnvironment* glo_env, const int sat_id);
-private:
-};
diff --git a/src/Component/.gitkeep b/src/components/.gitkeep
similarity index 100%
rename from src/Component/.gitkeep
rename to src/components/.gitkeep
diff --git a/src/s2e_for_c2a_core.cpp b/src/s2e_for_c2a_core.cpp
index d5b1847..84f3f2c 100644
--- a/src/s2e_for_c2a_core.cpp
+++ b/src/s2e_for_c2a_core.cpp
@@ -1,17 +1,21 @@
+/**
+ * @file s2e_for_c2a_core.cpp
+ * @brief The main file of S2E-FOR-C2A-CORE
+ */
+
 // Simulator includes
-#include "Interface/LogOutput/Logger.h"
+#include "library/logger/logger.hpp"
 
 // Add custom include files
-#include "./Simulation/Case/c2a_core_sample_case.h"
+#include "./simulation/case/c2a_core_sample_case.hpp"
 
-// degub print of initialize file path
-void print_path(std::string path)
-{
+// debug print of initialize file path
+void print_path(std::string path) {
 #ifdef WIN32
   std::cout << path << std::endl;
 #else
   const char *rpath = realpath(path.c_str(), NULL);
-  if(rpath) {
+  if (rpath) {
     std::cout << rpath << std::endl;
     free((void *)rpath);
   }
@@ -19,10 +23,9 @@ void print_path(std::string path)
 }
 
 // Main function
-int main()
-{
+int main() {
   // Set initialize file
-  std::string ini_file = "../../data/ini/c2a_core_sim_base.ini";
+  std::string ini_file = "../../data/initialize_files/c2a_core_sim_base.ini";
 
   std::cout << "Starting simulation..." << std::endl;
   std::cout << "\tIni file: ";
diff --git a/src/simulation/case/c2a_core_sample_case.cpp b/src/simulation/case/c2a_core_sample_case.cpp
new file mode 100644
index 0000000..1bbb912
--- /dev/null
+++ b/src/simulation/case/c2a_core_sample_case.cpp
@@ -0,0 +1,37 @@
+/**
+ * @file c2a_core_sample_case.cpp
+ * @brief User defined simulation case for C2A-CORE
+ */
+
+#include "c2a_core_sample_case.hpp"
+
+C2aCoreSampleCase::C2aCoreSampleCase(const std::string initialise_base_file) : SimulationCase(initialise_base_file) {}
+
+C2aCoreSampleCase::~C2aCoreSampleCase() { delete spacecraft_; }
+
+void C2aCoreSampleCase::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 C2aCoreSampleSatellite(&simulation_configuration_, global_environment_, spacecraft_id);
+
+  // Register the log output
+  spacecraft_->LogSetup(*(simulation_configuration_.main_logger_));
+}
+
+void C2aCoreSampleCase::UpdateTargetObjects() {
+  // Spacecraft Update
+  spacecraft_->Update(&(global_environment_->GetSimulationTime()));
+}
+
+std::string C2aCoreSampleCase::GetLogHeader() const {
+  std::string str_tmp = "";
+
+  return str_tmp;
+}
+
+std::string C2aCoreSampleCase::GetLogValue() const {
+  std::string str_tmp = "";
+
+  return str_tmp;
+}
diff --git a/src/simulation/case/c2a_core_sample_case.hpp b/src/simulation/case/c2a_core_sample_case.hpp
new file mode 100644
index 0000000..46009f8
--- /dev/null
+++ b/src/simulation/case/c2a_core_sample_case.hpp
@@ -0,0 +1,57 @@
+/**
+ * @file c2a_core_sample_case.hpp
+ * @brief User defined simulation case for C2A-CORE
+ */
+
+#ifndef S2E_SIMULATION_CASE_C2A_CORE_SAMPLE_CASE_HPP_
+#define S2E_SIMULATION_CASE_C2A_CORE_SAMPLE_CASE_HPP_
+
+#include <./simulation/case/simulation_case.hpp>
+
+#include "../spacecraft/c2a_core_sample_satellite.hpp"
+
+/**
+ * @class C2aCoreSampleCase
+ * @brief User defined simulation case for C2A-CORE
+ */
+class C2aCoreSampleCase : public SimulationCase {
+ public:
+  /**
+   * @fn C2aCoreSampleCase
+   * @brief Constructor
+   */
+  C2aCoreSampleCase(const std::string initialise_base_file);
+  /**
+   * @fn ~C2aCoreSampleCase
+   * @brief Destructor
+   */
+  virtual ~C2aCoreSampleCase();
+
+  /**
+   * @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:
+  C2aCoreSampleSatellite* spacecraft_;  //!< Spacecraft Instance
+
+  /**
+   * @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_C2A_CORE_SAMPLE_CASE_HPP_
diff --git a/src/Simulation/GroundStation/.gitkeep b/src/simulation/ground_station/.gitkeep
similarity index 100%
rename from src/Simulation/GroundStation/.gitkeep
rename to src/simulation/ground_station/.gitkeep
diff --git a/src/simulation/spacecraft/c2a_core_sample_components.cpp b/src/simulation/spacecraft/c2a_core_sample_components.cpp
new file mode 100644
index 0000000..f18e78f
--- /dev/null
+++ b/src/simulation/spacecraft/c2a_core_sample_components.cpp
@@ -0,0 +1,46 @@
+/**
+ * @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 <library/initialize/initialize_file_access.hpp>
+
+#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);
+
+  obc_->ConnectComPort(PORT_CH_RS422_MOBC_EXT, 1024, 1024);  // Connect UART Port
+#endif
+}
+
+C2aCoreSampleComponents::~C2aCoreSampleComponents() {
+  // 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/src/simulation/spacecraft/c2a_core_sample_components.hpp b/src/simulation/spacecraft/c2a_core_sample_components.hpp
new file mode 100644
index 0000000..fd6dda1
--- /dev/null
+++ b/src/simulation/spacecraft/c2a_core_sample_components.hpp
@@ -0,0 +1,66 @@
+/**
+ * @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 <dynamics/dynamics.hpp>
+#include <environment/global/global_environment.hpp>
+#include <environment/local/local_environment.hpp>
+#include <library/math/vector.hpp>
+#include <simulation/spacecraft/installed_components.hpp>
+
+// include for components
+#include <components/real/cdh/on_board_computer_with_c2a.hpp>
+
+/**
+ * @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
+
+  // 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/src/simulation/spacecraft/c2a_core_sample_satellite.cpp b/src/simulation/spacecraft/c2a_core_sample_satellite.cpp
new file mode 100644
index 0000000..56ca4aa
--- /dev/null
+++ b/src/simulation/spacecraft/c2a_core_sample_satellite.cpp
@@ -0,0 +1,15 @@
+/**
+ * @file c2a_core_sample_satellite.cpp
+ * @brief User side spacecraft class for C2A-CORE
+ */
+
+#include "c2a_core_sample_satellite.hpp"
+
+#include "c2a_core_sample_components.hpp"
+
+C2aCoreSampleSatellite::C2aCoreSampleSatellite(const SimulationConfiguration* simulation_configuration, const GlobalEnvironment* global_environment,
+                                               const unsigned int spacecraft_id)
+    : Spacecraft(simulation_configuration, global_environment, spacecraft_id) {
+  components_ =
+      new C2aCoreSampleComponents(dynamics_, structure_, local_environment_, global_environment, simulation_configuration, &clock_generator_);
+}
diff --git a/src/simulation/spacecraft/c2a_core_sample_satellite.hpp b/src/simulation/spacecraft/c2a_core_sample_satellite.hpp
new file mode 100644
index 0000000..f0d0da8
--- /dev/null
+++ b/src/simulation/spacecraft/c2a_core_sample_satellite.hpp
@@ -0,0 +1,29 @@
+/**
+ * @file c2a_core_sample_satellite.hpp
+ * @brief User side spacecraft class for C2A-CORE
+ */
+
+#ifndef S2E_SIMULATION_SPACECRAFT_C2A_CORE_SAMPLE_SATELLITE_HPP_
+#define S2E_SIMULATION_SPACECRAFT_C2A_CORE_SAMPLE_SATELLITE_HPP_
+
+#include <simulation/spacecraft/spacecraft.hpp>
+
+#include "c2a_core_sample_components.hpp"
+
+/**
+ * @class C2aCoreSampleSatellite
+ * @brief User side spacecraft class for C2A-CORE
+ */
+class C2aCoreSampleSatellite : public Spacecraft {
+ public:
+  /**
+   * @fn C2aCoreSampleSat
+   * @brief Constructor
+   */
+  C2aCoreSampleSatellite(const SimulationConfiguration* simulation_configuration, const GlobalEnvironment* global_environment,
+                         const unsigned int spacecraft_id);
+
+ private:
+};
+
+#endif  // S2E_SIMULATION_SPACECRAFT_C2A_CORE_SAMPLE_SATELLITE_HPP_