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4 Commits (200e197b320b9c558fd8e994d07f31c624337725)

Author	SHA1	Message	Date
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	9cfed48b16	fix compiler warnings in test cases	6 months ago
cinnaboot	76619c19eb	Phase 1: Enable root body transitions for patched conics ... Core Changes: - Remove new_parent != -1 check in update_simulation() - Add special handling for root body transitions (parent_index = -1) - Bodies can now transition to/from Sun (root) - Proper coordinate transformation for body->root and root->body transitions Implementation: - Old parent = -1: local = global (no transformation needed) - New parent = -1: global = local (no transformation needed) - find_dominant_body() already handles -1 returns correctly Testing: - Add test_root_body_transitions.cpp with 2 test cases - Test 1: Earth to Sun transition (validates Sun involvement) - Test 2: Round-trip Earth -> Sun -> Mars -> Sun (multi-leg) - Create manual_root_transition.toml config - All 6 assertions passing Results: ✅ Satellites can transition to/from Sun ✅ Multi-leg transitions work (Earth→Sun→Mars→Sun) ✅ Root body transitions validated ✅ Tests pass for patched conics scenarios Files Modified: - src/simulation.cpp (root body transition handling) Files Created: - tests/test_root_body_transitions.cpp (2 test cases) - tests/configs/manual_root_transition.toml - tests/configs/simple_root_transition.toml - tests/configs/interplanetary_transfer.toml Phase 1 Status: COMPLETE ✅ Next: Phase 2 - Adaptive Hysteresis	6 months ago