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test-refactor

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5 Commits (f79ae5ac84d1f7d377b43f731a3ad618d9b0b2f7)

Author	SHA1	Message	Date
cinnaboot	f79ae5ac84	reorganize test configs: 1:1 mapping with test files ... - Move all configs from tests/configs/ to tests/ - Rename configs to match test filenames (test_NAME.toml) - Remove unused configs (earth_mars_simple, simple_root_transition, interplanetary_transfer) - Combine earth_circular and mars_circular into test_orbital_period.toml - Duplicate earth_circular.toml as test_energy.toml - Remove invalid parent test case from test_invalid_parent_assignment.cpp - Update all test files to reference new config paths - Delete tests/configs/ directory	6 months ago
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	63a1144da5	Add hyperbolic orbit test case and configuration ... - Add hyperbolic_comet.toml with e=1.5, a=-1.496e11 - Add 3 test cases: * Energy and escape trajectory (300 days) * Initial conditions verification * Asymptotic velocity validation (1000 days) - Tests validate: v > v_escape, E > 0, e > 1.0, a < 0 - Asymptotic test uses 30% tolerance at 18+ AU distance - Existing hyperbolic rendering unchanged Claude	6 months ago
cinnaboot	1ec6249208	Add parabolic orbit support and test case ... - Update velocity calculation to handle e=1.0 (parabolic orbits) using escape velocity formula v² = 2GM/r instead of vis-viva - Add parabolic comet test configuration - Add test cases for parabolic orbit energy and escape trajectory Claude	6 months ago