Update s2e-core v6.0.0

s2e-ff/CMakeLists.txt

@@ -32,55 +32,16 @@ set(NRLMSISE00_DIR ${EXT_LIB_DIR}/nrlmsise00)
 include_directories(${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(${S2E_CORE_DIR}/src/Component/Thermal)
-include_directories(${S2E_CORE_DIR}/src/RelativeInformation)
 
 ## 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/S2eFf.cpp
@@ -163,22 +124,20 @@ 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)
+
 
 ## Cmake debug
 message("Cspice_LIB:  " ${CSPICE_LIB})
@@ -220,7 +179,7 @@ if(GOOGLE_TEST)
   )
   add_executable(${TEST_PROJECT_NAME} ${TEST_FILES})
   target_link_libraries(${TEST_PROJECT_NAME} gtest gtest_main)
-  target_link_libraries(${TEST_PROJECT_NAME} MATH)
+  target_link_libraries(${TEST_PROJECT_NAME} LIBRARY)
   include_directories(${TEST_PROJECT_NAME})
   add_test(NAME s2e-test COMMAND ${TEST_PROJECT_NAME})
   enable_testing()

s2e-ff/data/ini/FfSat.ini

@@ -4,24 +4,30 @@
 // 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]
+// 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
-Torque_b(0) = +0.000
-Torque_b(1) = -0.000
-Torque_b(2) =  0.000
+initial_torque_b_Nm(0) = +0.000
+initial_torque_b_Nm(1) = -0.000
+initial_torque_b_Nm(2) =  0.000
 
-[ControlledAttitude]
+[CONTROLLED_ATTITUDE]
 // Mode definitions
 // INERTIAL_STABILIZE
 // SUN_POINTING
@@ -32,16 +38,15 @@ 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
+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
-// 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
-
+// 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
@@ -55,28 +60,42 @@ logging = ENABLE
 // 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
 //////////////////////////////////////////////////////////////////////////
 
-// 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//////////////////////////////
+// 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)
@@ -86,57 +105,33 @@ relative_dynamics_model_type = 0
 // 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
+// * 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]
-init_relative_velocity_lvlh(0) = 0.0
-init_relative_velocity_lvlh(1) = 0.0
-init_relative_velocity_lvlh(2) = 0.0
+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_sat_id = 1
+reference_satellite_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 ///////////
+// Settings for Encke mode ///////////
 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/FfSatLocalEnvironment.ini
-
+[THERMAL]
+calculation = DISABLE
+debug = 0
 
-[DISTURBANCE]
-dist_file = ../../data/ini/FfSatDisturbance.ini
-
-
-[STRUCTURE_FILE]
+[SETTING_FILES]
+local_environment_file = ../../data/ini/FfSatLocalEnvironment.ini
+disturbance_file  = ../../data/ini/FfSatDisturbance.ini
 structure_file = ../../data/ini/FfSatStructure.ini
 
-
-[COMPONENTS_FILE]
+[COMPONENT_FILES]
 // Users can add the path for component initialize files here.
 relative_distance_sensor_file = ../../data/ini/Components/RelativeDistanceSensor.ini
 relative_position_sensor_file = ../../data/ini/Components/RelativePositionSensor.ini