Consolidate 9 TEST_CASEs into 5 SCENARIOs with 22 SECTIONs:
- Load orbital parameters from TOML config instead of hardcoded constants
- Use precomputed expected values via precalc_analytical_propagation.py
- Apply tight tolerance constants (REL_TOL, ANG_TOL, R_TOL, V_TOL)
- Remove decorative comment blocks and redundant SCENARIO title comments
- Fix propagate_orbital_elements/orbital_elements_to_cartesian API usage
(both take parent_mass, not mu)
- Add destroy_simulation cleanup to each SCENARIO
New files: precalc_analytical_propagation.py, test_analytical_propagation.toml
Added 6 test files for Newton-Raphson solver and analytical propagation:
- test_cartesian_to_elements_basic.cpp: Tests state vector ↔ orbital elements conversion
- test_newton_raphson_convergence.cpp: Tests Newton-Raphson solver convergence behavior
- test_analytical_propagation_apsides.cpp: Tests propagation through orbital apsides
- test_analytical_propagation_timesteps.cpp: Tests propagation with various timesteps
- test_extreme_eccentricity.cpp: Tests near-parabolic and hyperbolic orbits
- test_precision_boundaries.cpp: Tests exact boundary value handling
Implemented core orbital mechanics functions:
- solve_kepler_equation(): Newton-Raphson solver with 1e-10 tolerance
- get_initial_trial_value(): Series expansion initial guess
- cartesian_to_orbital_elements(): State vectors to orbital elements conversion
- propagate_orbital_elements(): Analytical propagation using Kepler's equation
Updated test plan document with current progress and remaining tests.
Test status: 66 passed, 14 failed (out of 80 test cases)
- Failing tests are expected: implementation needs debugging
- Config validation issues fixed by adjusting orbital parameters
cinnaboot