- Mark all UI implementation phases as completed in ui_implementation_plan.md
- Add UI body selection to completed items in implementation_plan.md
- Move ui_implementation_summary.md to docs/session_summaries/ for better organization
Add core orbital mechanics calculations and spacecraft spawning infrastructure
for interplanetary trajectory planning. Enables calculation of realistic
transfer orbits with proper departure window timing.
New Module (mission_planning.h/cpp):
- calculate_hohmann_transfer(): Returns transfer orbit parameters
- calculate_angular_position(): Computes body angle in XY plane
- calculate_required_phase_angle(): Calculates optimal launch phase
- check_launch_window(): Tests if current phase allows optimal launch
- wait_for_launch_window(): Fast-forwards to launch window
- spawn_spacecraft_on_transfer(): Creates spacecraft on transfer trajectory
Simulation Extensions (simulation.cpp/h):
- add_body_to_simulation(): Dynamic body creation at runtime
- Properly handles local/global coordinate initialization
- SOI radius calculation for dynamically added bodies
Test Suite:
- test_mission_planning.cpp: Core calculations validated
- test_hohmann_transfer.cpp: Spacecraft spawning verified
- earth_mars_simple.toml: Test configuration for transfers
Validations:
- Transfer parameters match NASA references (±5%)
- Earth→Mars transfer: 259 days, 44.3° phase, 2.94 km/s Δv
- Spacecraft spawns with correct velocity and position
- Launch window detection works (waits ~94 days for optimal window)
Status: Phases 1-3 complete, Phase 4 debugging in progress
(trajectory divergence after first update_simulation() call)
Decisions made:
1. Hysteresis: Adaptive approach (Option B) - prevents oscillation while enabling round-trips
2. Integration timing: Current approach (Option A) - defer half-step optimization to future TODO
3. Test priorities: Create all 3 test cases first - expect failures for unimplemented features
4. Adaptive timesteps: Deferred to later work - focus on SOI transitions first
Updated plan with:
- Decisions Made section documenting all 4 choices
- Updated implementation phases with decisions
- Updated timeline and success criteria
- Marked Phase 5 as deferred
- Ready to begin Phase 1 implementation
- Update hierarchical_frames_plan.md with recent work (Jan 13, 2026)
- Add comprehensive patched conics implementation plan
- Document SOI transition requirements and implementation phases
- Include 4 open questions for strategy discussion
- Add 6 test scenarios for multi-body transitions
- Document success criteria and timeline estimates
Document comprehensive testing of three orbit types:
- Parabolic orbit support (e=1.0) with escape velocity formula
- Hyperbolic orbit testing (e>1.0) with asymptotic velocity
- Simplified SOI transition test (3-body system)
- Hysteresis creates one-way SOI barrier
- 39 new assertions across 8 test cases
- Net +364 lines across 10 files
Claude
Document current progress after completing Phase 2:
- Phase 1 complete: Dual coordinate storage foundation
- Phase 2 complete: Local frame integration working
- Earth Moon test now passing (major success!)
- 7/9 tests passing (up from 6/9)
- Phases 3-5 deferred for future work
Added detailed status, commit references, and notes for future development
Add dual coordinate storage to CelestialBody for hierarchical frames.
Both local (relative to parent) and global (absolute) coordinates maintained.
- Added local_position and local_velocity fields to CelestialBody
- Added initialize_local_coordinates() to convert global→local
- Added compute_global_coordinates() to convert local→global
- Updated config_loader to initialize local coords after velocity calc
- Updated update_simulation() to sync local coords after integration
- Phase 1 complete: foundation for local frame integration
Tests: Same 3 moon failures as before (no regression)
Implements hierarchical_frames_plan.md Phase 1
- Renamed src/bodies.h to src/simulation.h
- Renamed src/bodies.cpp to src/simulation.cpp
- Updated all include references in src/ and tests/
- Updated Makefile to reference simulation.cpp
- Updated documentation references
Claude
Reduced redundancy across documentation files:
- Condensed implementation_plan.md (236→112 lines)
- Condensed test_verification.md (143→62 lines), updated for 4-body test
- Condensed config_assumptions.md (115→44 lines), focused on active issues
- Removed architecture duplication from CLAUDE.md
- Removed common commands from verbose_project_overview.md
- Added 'make test' target to Makefile
Each file now has a clear, distinct purpose with minimal overlap.
🤖 Generated with Claude Code
Document session work including main.cpp refactoring and eccentric orbit
support. Add prioritized TODO list for remaining config file updates and
known issues with moon positions.
🤖 Generated with [Claude Code](https://claude.com/claude-code)
Update README with new 12-field config format and examples showing both
circular and eccentric orbits. Update config_assumptions.md to reflect
fixed issues and new capabilities.
🤖 Generated with [Claude Code](https://claude.com/claude-code)
Document expected orbital positions and velocities for the simple
test case (configs/test_simple.txt):
- Expected orbital periods (Earth 365d, Mars 687d)
- Expected velocities (Earth 29.789 km/s, Mars 24.323 km/s)
- Verification points at quarter/half/full orbit
- Quick test commands
- Acceptable tolerances for numerical integration
Provides reference values to verify simulation accuracy by comparing
actual output against predicted positions and angles.
🤖 Generated with [Claude Code](https://claude.com/claude-code)
Co-Authored-By: Claude Sonnet 4.5 <noreply@anthropic.com>
