Move all shared tolerance constants to src/test_utilities.h with inline
comments. Update all test files to use header constants instead of local
definitions. Add DRIFT_TOL for parabolic orbit energy checks.
Key changes:
- test_utilities.h: consolidated constants with inline descriptions,
removed per-test doc comments, added DRIFT_TOL=1e-12
- test_cartesian_to_elements_advanced.cpp: use header E_TOL, ANG_TOL,
A_TOL; local A_TOL_LARGE=2e-4 for |a|=1e11 vis-viva error cases
- test_parabolic_orbit.cpp: use V_TOL, E_TOL, REL_TOL, R_TOL, DRIFT_TOL;
add precalculated initial velocity check; remove FIXME ratio test
- test_cartesian_to_elements_basic.cpp, test_extreme_eccentricity.cpp,
test_extreme_orientation_mixed.cpp, test_extreme_timescales.cpp:
migrate remaining local constants to header
- continue.md: update tolerance reference table to match header
- scripts/precalc_parabolic_orbit.py: remove velocity sampling loop
(no longer used by C++ test)
All 624 tests pass.
Config changes:
- 'Slightly_Hyperbolic': e=1.05, a=-1.3e8 (perigee at 6.5e6 m)
- 'Near_Parabolic': e=0.99, a=7.0e8 (perigee at 7e6 m)
Test changes:
- Added check for hyperbolic orbit anomaly limits (|ν| < arccos(-1/e))
- Skip testing ν=π and 3π/2 when they exceed valid range for e>1
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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