New modular API:
- solve_kepler_elliptical(M, e): Newton-Raphson for E - e·sin(E) = M
- solve_kepler_hyperbolic(M, e): Solver for H - e·sinh(H) = M
- eccentric_to_true_anomaly(E, e): Convert eccentric to true anomaly
- hyperbolic_to_true_anomaly(H, e): Convert hyperbolic to true anomaly
- mean_anomaly_to_true_anomaly(M, e): Unified wrapper (dispatches based on e)
Changes:
- Renamed solve_kepler_equation() → solve_kepler_elliptical() for clarity
- Extracted KEPLER_TOLERANCE and KEPLER_MAX_ITERATIONS constants
- Separated hyperbolic solver logic from combined function
- Fixed test_newton_raphson_convergence to verify Kepler's equation
(instead of incorrectly expecting E ≈ M for small e)
- Added TODO comment for future cartesian_to_orbital_elements refactoring
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
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