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5 Commits (af18eaa72311eb49baf16b5df7f331935a905661)

Author	SHA1	Message	Date
cinnaboot	c5946acdc4	WIP: Phase 4-6 - Initialization, validation, and test updates ... - Added orbital_mechanics module with orbital_elements_to_cartesian() - Updated initialize_orbital_objects() to use orbital mechanics - Added validate_initial_positions() for post-initialization checking - Fixed test files to use global_position/global_velocity - Updated config loader to support spacecraft altitude parameter - Fixed orbital_mechanics.cpp velocity calculation bug (removed duplicate scaling) - Updated Makefile to include orbital_mechanics.o in test build - Renamed simulation.h OrbitalMetrics to OrbitalAnalysis to avoid conflict - Added docs/parabolic_union_implementation.md for parabolic orbit support plan Note: Test configs still need manual fix for orbit table TOML syntax	6 months ago
cinnaboot	ce35c618d6	Implement maneuver planning system with config-based scheduled burns ... Add maneuver planning and execution system to SimulationState: **Data Structures:** - Add TriggerType enum (TIME, TRUE_ANOMALY) - Add Maneuver struct with burn parameters, trigger conditions, execution state - Add maneuver array to SimulationState (maneuvers, maneuver_count, max_maneuvers) - Update create_simulation() to accept max_maneuvers parameter **Config File Format:** - [[maneuvers]] sections with name, spacecraft_name, trigger_type, trigger_value, direction, delta_v - Validate spacecraft_name exists and maneuver names are unique - Parse trigger_type string -> enum - Parse direction string -> BurnDirection enum **Execution System:** - check_maneuver_trigger() evaluates TIME and TRUE_ANOMALY conditions - TIME trigger: sim->time >= trigger_value - TRUE_ANOMALY trigger: calculate orbital true anomaly from position/velocity - execute_maneuver() applies delta-v using apply_impulsive_burn() - Maneuvers execute in update_simulation() after spacecraft physics - Global coordinates computed AFTER maneuvers to preserve burn effects **Test Coverage (5 tests, 26 assertions):** - Maneuver loading from config - Time-based trigger executes at correct time - True anomaly trigger executes at correct angle - Maneuvers only execute once - Duplicate maneuver names fail config load **API Changes:** - create_simulation(int max_bodies, int max_craft, int max_maneuvers, double time_step) - Updated all existing test files to use new signature Test results: 5/5 maneuver tests passing Documentation: docs/maneuver_planning_plan.md with full design specification	6 months ago
cinnaboot	f5a1fdd245	Refactor: Integrate spacecraft into SimulationState ... Merge spacecraft management into simulation module: - Move Spacecraft struct from maneuver.h to spacecraft.h - Add spacecraft array to SimulationState (spacecraft, craft_count, max_craft) - Remove separate SpacecraftState struct and related functions - Update create_simulation() to require max_craft parameter - Move spacecraft update logic into update_simulation() - Make load_spacecraft_config() internal helper, called by load_system_config() - Update all test files to use new API with 3-parameter create_simulation() - Handle max_craft=0 case gracefully (no spacecraft allocation) Test results: 26/27 passing (1 pre-existing SOI test unrelated to changes)	6 months ago
cinnaboot	9f6aa2d851	add a 'REQUIRE' for the moon integration test	6 months ago
cinnaboot	c53c598ffe	Add moon orbit test suite and fix solar system config ... - Created tests/test_moon_orbits.cpp with 4 test cases: * Moon orbital stability around Earth * Galilean moons orbital stability around Jupiter * Titan orbital stability around Saturn * Combined solar system parent stability - Enhanced test_utilities.h/cpp: * Added min_time_days field to OrbitTracker * Added create_orbit_tracker_with_min_time() for short-period orbits - Fixed parent indexes in tests/configs/solar_system.toml: * Moon: parent 3 (Mars) → 2 (Earth) * Io/Europa/Ganymede/Callisto: parent 5 (Saturn) → 4 (Jupiter) * Titan: parent 6 (Uranus) → 5 (Saturn) - Updated semi_major_axis for moons to actual orbital distances Tests reveal need for hierarchical orbit physics implementation. Net change: +368 lines	6 months ago