@ -9,208 +9,53 @@ Total estimated test files: 11 (reduced from 14 after overlap analysis)
## Current Progress (2026-01-31)
### Completed Tests (6/14 files fully passing)
#### 1. ✅ test_cartesian_to_elements_basic.cpp + .toml
- Status: PASSING (12/12 assertions) - FIXED
- Issue: NaN values in reconstructed radius/velocity
- Fix: Corrected true_anomaly calculation (line 122 in orbital_mechanics.cpp)
- Changed: `r_dot_e / mu` → `r_dot_e / (r_mag * e_mag)`
- Added: cos(ν) clamping to [-1, 1] before acos()
- Config: Moderate eccentricity (e=0.5), zero inclination
- Tests:
- Round-trip conversion: orbital elements → state vectors → orbital elements
- Position/velocity magnitude preservation
- Semi-major axis, eccentricity accuracy
#### 2. ✅ test_newton_raphson_convergence.cpp (NO CONFIG)
- Status: PASSING (28/28 assertions) - FIXED
- Issue: Low eccentricity (e=0.001) test had incorrect expectations
- Fix: Changed test to verify Kepler's equation satisfaction instead of first-order approximation
- Verify: |E - e·sin(E) - M| < 1.0e-10
- Verify: |E - (M + e·sin(M))| < 0.01 ( first-order approximation )
- Code changes: Refactored orbital_mechanics.cpp to separate elliptical/hyperbolic solvers
- Added: `solve_kepler_elliptical()` , `solve_kepler_hyperbolic()`
- Added: `eccentric_to_true_anomaly()` , `hyperbolic_to_true_anomaly()`
- Added: `mean_anomaly_to_true_anomaly()` unified wrapper
- Config: Programmatically varied parameters
- Tests:
- Very low eccentricity (e < 0.01 ) : convergence rate verification
- High eccentricity (0.9 < e < 0 . 99 ) : iteration count limits
- Mean anomaly near π: worst-case convergence
- Large mean anomaly values (M > 1000): periodicity handling
- Eccentricity at boundaries (e = 0.9999, 1.0001)
#### 3. ✅ test_analytical_propagation_apsides.cpp + .toml
- Status: PASSING (5/5 assertions) - FIXED
- Issue: Test measured velocity at same orbital anomaly (both at ν=0)
- Fix: Changed to measure velocity at ν=π/4, then compare to perigee velocity
- Before: Both measurements at ν=0 (perigee)
- After: Measure at ν=π/4, compare to ν=0
- Config: Elliptical orbit (e=0.6, a=2e7)
- Tests:
- Propagation through perigee (velocity maximum)
- Propagation through apogee (velocity minimum)
- At exact orbital period: should return to initial state
- True anomaly accuracy after full orbit
- Vis-viva equation holds at multiple points
#### 4. ✅ test_analytical_propagation_timesteps.cpp + .toml
- Status: PASSING (7/7 assertions) - FIXED
- Issues: 3 test design bugs (tolerance, division by zero, 2π wrapping)
- Fixes:
- Small timestep: Changed to check position error (difference from expected v·dt) instead of absolute position change
- Division by zero: Added check for `expected_pos_error > 1e-6` before calculating relative error
- 2π wrapping: Added circular angular error calculation using `fmin(raw_error, 2π - raw_error)`
- Config: Standard orbit (e=0.4, a=1.5e7)
- Tests:
- Large timesteps: dt > 1 orbit period
- Very small timesteps: dt < 1 second
- Accuracy vs. timestep size relationship
- Mean anomaly accumulation over long propagation
#### 3. ✅ test_extreme_eccentricity.cpp + .toml
- Status: PASSING (28/28 assertions) - FIXED
- Issue: Config validation failing for spacecraft too close to parent
- Fix:
- Config: Fixed "Near_Parabolic" (e=0.99, a=7.0e8) and "Slightly_Hyperbolic" (e=1.05, a=-1.3e8)
- Test: Added validation to skip testing ν outside valid range for e>1
- For e>1: valid ν must satisfy |ν| < arccos ( -1 / e )
- For e=1.05: max |ν| ≈ 2.83 rad (162°)
- Code changes: Added `validate_true_anomaly_ranges()` to config_validator.cpp
- Checks hyperbolic orbits for true anomaly validity
- Validates ν is within asymptote boundaries for e>1
- Config: Multiple spacecraft (e=0.99, e=0.95, e=1.05)
- Tests:
- Numerical stability near e=1.0
- Hyperbolic solver switching
- Velocity magnitude accuracy
- Period calculation (or lack thereof for e≥1)
#### 5. ✅ test_precision_boundaries.cpp + .toml
- Status: PASSING (15/15 assertions) - FIXED
- Issues: 2 bugs (1 test bug, 1 implementation bug)
- Fixes:
- Test bug: Removed incorrect Z-coordinate check for polar orbit
- Test expected Z = r·sin(i), which assumes motion along Z-axis
- Actual position at perigee is on X-axis, so Z=0 is correct
- Implementation bug: Fixed circular orbit velocity calculation in orbital_elements_to_cartesian()
- Changed from constant velocity `vx=0, vy=v_mag`
- To correct rotating velocity `vx=-v·sin(ν), vy=v·cos(ν)`
- Angular momentum now properly conserved (error: 1.2e-14% instead of 41.4%)
- Code changes: Refactored orbital_elements_to_cartesian()
- Added inline comments for each orbit type (circular/elliptical/parabolic/hyperbolic)
- Consolidated calculation of semi-latus rectum p before velocity section
- Reduced velocity calculation from 16 lines to 10 lines
- Eliminated duplicate p = a·(1-e²) calculation
- Config: Multiple boundary cases (e=0, i=π/2, i=π)
- Tests:
- Eccentricity at exactly 0
- Inclination at 0°, 90°, 180°
- Semi-major axis sign change
- Angular momentum conservation
### Completed Tests (8/14 files fully passing)
#### 1. ✅ test_cartesian_to_elements_basic.cpp + .toml: Round-trip conversion with fixed true anomaly calculation (PASSING 12/12)
#### 2. ✅ test_newton_raphson_convergence.cpp: Convergence across eccentricity ranges with separated solvers (PASSING 28/28)
#### 3. ✅ test_analytical_propagation_apsides.cpp: Propagation through apsides with fixed velocity comparison (PASSING 5/5)
#### 4. ✅ test_analytical_propagation_timesteps.cpp: Timestep validation with fixed test design bugs (PASSING 7/7)
#### 5. ✅ test_extreme_eccentricity.cpp: Near-parabolic/hyperbolic boundaries with validation fixes (PASSING 28/28)
#### 6. ✅ test_precision_boundaries.cpp: Boundary value handling with fixed circular orbit velocity (PASSING 15/15)
#### 7. ✅ test_cartesian_to_elements_extreme.cpp + .toml: Parabolic test fixed and tolerances tightened (PASSING with 93 tests)
#### 8. ✅ test_cartesian_to_elements_quadrature.cpp + .toml: Argument of periapsis fix with atan2() (PASSING with 93 tests)
### Implementation Summary
**Code Changes:**
- Added to `src/orbital_mechanics.h` : Function declarations for
- `cartesian_to_orbital_elements(Vec3, Vec3, double)`
- `solve_kepler_equation(double, double)`
- `get_initial_trial_value(double, double)`
- `propagate_orbital_elements(const OrbitalElements&, double, double)`
- Modular API (refactored):
- `solve_kepler_elliptical(double, double)`
- `solve_kepler_hyperbolic(double, double)`
- `eccentric_to_true_anomaly(double, double)`
- `hyperbolic_to_true_anomaly(double, double)`
- `mean_anomaly_to_true_anomaly(double, double)`
- Added to `src/orbital_mechanics.cpp` : Full implementations
- Newton-Raphson solver with 1e-10 tolerance, max 50 iterations
- Series expansion initial guess: M + e*sin(M) + (e²/2)*sin(2M)
- Cartesian to orbital elements conversion algorithm
- Fixed: true_anomaly calculation with proper clamping (line 122)
- Fixed: circular orbit velocity calculation (line 40-42)
- Refactored: Separated elliptical/hyperbolic Kepler solvers
- Refactored: Added inline comments to orbital_elements_to_cartesian()
- Removed from `src/test_utilities.h/.cpp` : `propagate_orbital_elements()`
- Added to `src/config_validator.cpp` :
- `validate_true_anomaly_ranges()` - checks hyperbolic anomaly limits
- TODO comment about parabolic tolerance (0.005 too broad)
- Added functions to `src/orbital_mechanics.h` : Newton-Raphson solver, cartesian→elements conversion, modular API (elliptical/hyperbolic solvers), Barker's equation
- Implemented in `src/orbital_mechanics.cpp` : 1e-10 tolerance, max 50 iterations, series expansion initial guess, fixed true_anomaly calculation and circular orbit velocity, parabolic propagation with Barker's equation
- Removed `propagate_orbital_elements()` from `src/test_utilities.h/.cpp`
- Added `validate_true_anomaly_ranges()` to `src/config_validator.cpp`
- Standardized parabolic detection (PARABOLIC_TOLERANCE = 1e-3)
- Fixed argument_of_periapsis calculation using atan2()
**Bug Fixes:**
1. `cartesian_to_orbital_elements()` (line 122): Fixed true_anomaly calculation
- Corrected formula: r_dot_e / (r_mag * e_mag) instead of r_dot_e / mu
- Added clamping: cos(ν) clamped to [-1, 1] before acos()
2. `test_extreme_eccentricity.toml` : Fixed spacecraft parameters
- "Near_Parabolic": e=0.99, a=7.0e8
- "Slightly_Hyperbolic": e=1.05, a=-1.3e8
3. `test_extreme_eccentricity.cpp` : Added hyperbolic anomaly validation
- Skips testing ν=π and 3π/2 for e>1 (outside asymptote boundaries)
4. `test_newton_raphson_convergence.cpp` : Fixed test expectations
- Verifies Kepler's equation: |E - e·sin(E) - M| < 1.0e-10
- Verifies first-order approximation: |E - (M + e·sin(M))| < 0.01
5. `test_analytical_propagation_apsides.cpp` : Fixed velocity comparison logic
- Changed: Measure velocity at ν=π/4, compare to perigee velocity at ν=0
- Before: Both measurements at ν=0 (same anomaly, meaningless comparison)
6. `test_analytical_propagation_timesteps.cpp` : Fixed 3 test design issues
- Small timestep: Check position error instead of absolute position change
- Division by zero: Check expected_pos_error > 1e-6 before calculating relative error
- 2π wrapping: Use fmin(raw_error, 2π - raw_error) for angular error
7. `test_precision_boundaries.cpp` : Removed incorrect Z-coordinate check
- Test expected Z = r·sin(i), which assumes motion along Z-axis
- Actual position at perigee is on X-axis, so Z=0 is correct
8. `orbital_elements_to_cartesian()` (line 40-42): Fixed circular orbit velocity
- Changed from constant velocity vx=0, vy=v_mag
- To correct rotating velocity vx=-v·sin(ν), vy=v·cos(ν)
- Angular momentum now properly conserved (1.2e-14% error instead of 41.4%)
**Test Results:** All 80 tests passing (239,555 assertions)
**Recent Commits:**
- 9d97934 Fix true anomaly calculation in cartesian_to_orbital_elements()
- a46291a Fix test_extreme_eccentricity to skip invalid hyperbolic true anomalies
- 47f156b Add true anomaly validation for hyperbolic orbits in config validator
- 01e5492 Refactor orbital_mechanics: separate elliptical and hyperbolic Kepler solvers
- 5fc7348 Fix test_analytical_propagation_apsides: measure velocity at different anomaly
- 7471d06 Fix test_analytical_propagation_timesteps: tolerance, division by zero, and 2π wrapping
- acfb47a Fix test_precision_boundaries: remove incorrect Z-coordinate check for polar orbit
- 849a212 Fix orbital_elements_to_cartesian: circular orbit velocity and refactor for clarity
- 986a94e Update test plan: document progress on 3 fixed test files
- Fixed true_anomaly calculation: corrected formula and added clamping
- Fixed test_extreme_eccentricity config and validation
- Fixed test_newton_raphson_convergence expectations
- Fixed test_analytical_propagation_apsides velocity comparison
- Fixed 3 test design issues in test_analytical_propagation_timesteps
- Fixed test_precision_boundaries Z-coordinate check
- Fixed orbital_elements_to_cartesian circular orbit velocity
- Standardized parabolic detection across codebase
- Fixed near-parabolic numerical instability in eccentric_to_true_anomaly()
- Fixed argument_of_periapsis quadrature ambiguity with atan2()
- Fixed true_anomaly normalization to handle negative values
- Fixed parabolic test design in test_cartesian_to_elements_extreme.cpp
**Test Results:** All 93 tests passing (239,872 assertions) - includes 11 Barker's equation tests
### Remaining Tests (5 files)
#### 7. ⬜ test_cartesian_to_elements_extreme.cpp + .toml
- Purpose: Edge cases in orbital parameters
- Config: Multiple spacecraft in same config
- Near-circular (e=0.001)
- Highly eccentric (e=0.99)
- Equatorial (i< 0.001 )
- Polar (i≈π/2)
- Retrograde (i>π/2)
- Tests:
- Numerical precision at boundary values
- Degenerate Ω calculation for equatorial
- Rotation singularities for polar
#### 8. ⬜ test_cartesian_to_elements_quadrature.cpp + .toml
- Purpose: Test cartesian→elements conversion at quadrature points
- Config: Spacecraft at true anomalies: 0, π/2, π, 3π/2
- Tests:
- Cross product calculations at quadrants
- Eccentricity vector accuracy
- Position/velocity vector relationships
- NOTE: Tests NEW function (opposite direction of test_inclined_orbits)
#### 9. ⬜ test_hybrid_impulse_burns.cpp + .toml
#### 1. ⬜ test_hybrid_impulse_burns.cpp + .toml
- Purpose: Impulsive burn handling
- Config: Spacecraft with pre-configured maneuvers
- Tests:
@ -264,282 +109,34 @@ Total estimated test files: 11 (reduced from 14 after overlap analysis)
### Cartesian to Orbital Elements (3 files)
#### 1. ✅ test_cartesian_to_elements_basic.cpp + .toml
- Purpose: Basic round-trip conversion accuracy
- Config: Moderate eccentricity, zero inclination orbit
- Tests:
- Round-trip conversion: orbital elements → state vectors → orbital elements
- Position/velocity magnitude preservation
- Semi-major axis, eccentricity accuracy
#### 7. ⬜ test_cartesian_to_elements_extreme.cpp + .toml
- Purpose: Edge cases in orbital parameters
- Config: Multiple spacecraft in same config
- Near-circular (e=0.001)
- Highly eccentric (e=0.99)
- Equatorial (i< 0.001 )
- Polar (i≈π/2)
- Retrograde (i>π/2)
- Tests:
- Numerical precision at boundary values
- Degenerate Ω calculation for equatorial
- Rotation singularities for polar
#### 8. ⬜ test_cartesian_to_elements_quadrature.cpp + .toml
- Purpose: Test cartesian→elements conversion at quadrature points
- Config: Spacecraft at true anomalies: 0, π/2, π, 3π/2
- Tests:
- Cross product calculations at quadrants
- Eccentricity vector accuracy
- Position/velocity vector relationships
- NOTE: Tests NEW function (opposite direction of test_inclined_orbits)
#### 1. ✅ test_cartesian_to_elements_basic.cpp + .toml: Basic round-trip conversion accuracy
#### 7. ✅ test_cartesian_to_elements_extreme.cpp + .toml: Parabolic test fixed and tolerances tightened
#### 8. ✅ test_cartesian_to_elements_quadrature.cpp + .toml: Argument of periapsis fix with atan2()
### Newton-Raphson Solver (1 file)
#### 2. ✅ test_newton_raphson_convergence.cpp (NO CONFIG)
- Purpose: Verify convergence behavior across eccentricity ranges
- Config: Spacecraft with programmatically varied parameters
- Tests:
- Very low eccentricity (e < 0.01 ) : convergence rate verification
- High eccentricity (0.9 < e < 0 . 99 ) : iteration count limits
- Mean anomaly near π: worst-case convergence
- Large mean anomaly values (M > 1000): periodicity handling
- Eccentricity at boundaries (e = 0.9999, 1.0001)
#### 2. ✅ test_newton_raphson_convergence.cpp (NO CONFIG): Convergence behavior across eccentricity ranges
### Analytical Propagation (2 files)
#### 3. ✅ test_analytical_propagation_apsides.cpp + .toml
- Purpose: Propagation through orbital apsides
- Config: Elliptical orbit
- Tests:
- Propagation through perigee (velocity maximum)
- Propagation through apogee (velocity minimum)
- At exact orbital period: should return to initial state
- True anomaly accuracy after full orbit
#### 4. ✅ test_analytical_propagation_timesteps.cpp + .toml
- Purpose: Timestep size validation
- Config: Standard orbit
- Tests:
- Large timesteps: dt > 1 orbit period
- Very small timesteps: dt < 1 second
- Accuracy vs. timestep size relationship
- Mean anomaly accumulation over long propagation
#### 3. ✅ test_analytical_propagation_apsides.cpp + .toml: Propagation through orbital apsides
#### 4. ✅ test_analytical_propagation_timesteps.cpp + .toml: Timestep size validation
## Phase 2: Hybrid Integration
#### 9. ⬜ test_hybrid_impulse_burns.cpp + .toml
- Purpose: Impulsive burn handling
- Config: Spacecraft with pre-configured maneuvers
- Tests:
- Hohmann transfer (2 burns)
- Plane change at nodes (inclination change only)
- Impulsive burns at apsides (perigee/apogee)
- Minimal burns (Δv < 1 m / s )
- Large burns (Δv > orbital velocity)
#### 10. ⬜ test_hybrid_continuous_thrust.cpp + .toml
- Purpose: Continuous thrust integration
- Config: Spacecraft with finite-duration burns
- Tests:
- Continuous low-thrust burns (ion engines)
- Multi-burn sequences
- Numerical vs. analytical mode transitions
- Energy conservation during burns
#### 11. ⬜ test_hybrid_energy_conservation.cpp + .toml
- Purpose: Compare analytical vs. numerical propagation
- Config: Same spacecraft propagated with both methods
- Tests:
- Energy comparison: analytical vs. RK4
- Pre/post burn energy validation
- Long-term energy drift comparison
#### 1. ⬜ test_hybrid_impulse_burns.cpp + .toml: Impulsive burn handling
#### 2. ⬜ test_hybrid_continuous_thrust.cpp + .toml: Continuous thrust integration
#### 3. ⬜ test_hybrid_energy_conservation.cpp + .toml: Analytical vs. numerical propagation comparison
## Extreme Orbits (3 files)
#### 5. ✅ test_extreme_eccentricity.cpp + .toml
- Purpose: Near-parabolic boundary behavior
- Config:
- Highly eccentric (e=0.99)
- Near parabolic (e=0.9999, e=1.0001)
- Tests:
- Numerical stability near e=1.0
- Hyperbolic solver switching
- Velocity magnitude accuracy
- Period calculation (or lack thereof for e≥1)
#### 12. ⬜ test_extreme_orientation_mixed.cpp + .toml
- Purpose: Combined high inclination + high eccentricity
- Config:
- High inclination (i>π/3) + high eccentricity (e>0.8)
- Tests:
- Rotation matrix behavior at extreme combinations
- Ω and ω singularity handling
- Velocity vector orientation
- NOTE: Removed duplicate polar/retrograde tests (covered by test_precision_boundaries)
#### 13. ⬜ test_extreme_timescales.cpp + .toml
- Purpose: Orbital period extremes
- Config:
- Mercury-like orbiter (period ~88 days)
- Very long period orbit (period > 10 years)
- Very low perigee (altitude < 100 km )
- Super-synchronous orbit
- Tests:
- Fast orbits: numerical precision challenges
- Slow orbits: mean anomaly accumulation
- Low altitude: atmospheric boundary (if applicable)
- Long-duration propagation (10+ periods)
#### 5. ✅ test_extreme_eccentricity.cpp + .toml: Near-parabolic boundary behavior
#### 4. ⬜ test_extreme_orientation_mixed.cpp + .toml: Combined high inclination + high eccentricity
#### 5. ⬜ test_extreme_timescales.cpp + .toml: Orbital period extremes
## Numerical Precision (1 file)
#### 6. ✅ test_precision_boundaries.cpp + .toml
- Purpose: Exact boundary value handling
- Config:
- Perfect circle (e=0)
- Polar orbit (i=π/2)
- Retrograde orbit (i=π)
- Zero/very small radius or velocity
- Tests:
- Eccentricity at exactly 0
- Eccentricity at exactly 1 (parabolic)
- Inclination at 0°, 90°, 180°
- Semi-major axis sign change
- Angular momentum conservation
## Overlap Analysis with Existing Tests
### Existing Test Coverage Summary
**Orbital Parameters Currently Tested:**
- Eccentricity: e=0.0 (circular), 0.74 (Molniya), 1.0 (parabolic), 1.5 (hyperbolic)
- Inclination: i=0.0 (equatorial), 1.107 rad (63.4°, Molniya)
- Orbital Periods: 1 day, 10 days, 15.95 days (Titan), 27.3 days (Moon), 60 days, 365 days (Earth), 687 days (Mars), 300-2000 days
**Test Scenarios Currently Tested:**
- Energy conservation (RK4 only)
- Orbital period measurement
- Prograde/retrograde/normal impulsive burns
- Time-based and true anomaly triggers
- Inclined orbits (Molniya)
- Parabolic and hyperbolic orbits
- Moon orbital stability
- SOI transitions (deferred)
- Root body transitions (deferred)
### Test Reduction Applied (Reduced from 14 to 11 files)
**Tests Removed (3 files):**
1. **test_energy_conservation_analytical.cpp** (OPTIONAL - REMOVED)
- Reason: Long-term energy drift testing covered by `test_hybrid_energy_conservation.cpp`
- The hybrid test compares analytical vs RK4 energy, providing stronger validation
2. **test_extreme_orientation.cpp: Polar (i=90°) & Retrograde (i=180°)** (REMOVED)
- Reason: Polar and retrograde boundary cases already covered by `test_precision_boundaries.cpp`
- Only "mixed: high inclination + high eccentricity" case retained
- Renamed to `test_extreme_orientation_mixed.cpp`
3. **test_extreme_orientation.cpp: Original full scope** (REDUCED)
- Reason: Duplicate with existing test_precision_boundaries
- Polar orbit (i=π/2): Already tested in test_precision_boundaries
- Retrograde orbit (i=π): Already tested in test_precision_boundaries
**Overlap Analysis:**
**test_inclined_orbits.cpp** (Molniya: e=0.74, i=63.4°)
- Overlaps: Extreme eccentricity, Extreme orientation
- Gap: Need e=0.99+, retrograde (i>π/2), polar (i=π/2 exactly)
- Note: Does NOT overlap with test_cartesian_to_elements_quadrature (tests opposite conversion direction)
**test_moon_orbits.cpp** (Moon ~27 day period)
- Overlaps: Extreme timescales
- Gap: Need Mercury-like (~88 days), very slow (>10 years)
**test_energy.cpp** (circular orbit energy)
- Overlaps: Energy conservation tests
- Gap: Need analytical propagation validation, method comparison
- Note: test_energy_conservation_analytical removed; hybrid test covers this gap
**test_orbital_period.cpp** (Earth 365 days, Mars 687 days)
- Overlaps: Extreme timescales
- Gap: Need < 10 days , ~ 88 days , > 3650 days
**test_parabolic_orbit.cpp** (e=1.0)
- Overlaps: Extreme eccentricity
- Gap: Need e=0.99, e=0.9999, e=1.0001
**test_hyperbolic_orbit.cpp** (e=1.5)
- Overlaps: Extreme eccentricity
- Gap: Need e=0.9999 near-parabolic boundary
**test_maneuvers.cpp** (prograde/retrograde/normal burns)
- Overlaps: Hybrid impulse burns
- Gap: Need continuous thrust, Hohmann sequence, apsides burns
**test_maneuver_planning.cpp** (time/true anomaly triggers)
- Overlaps: Hybrid impulse burns
- Gap: Need burns at apsides, Hohmann transfer
### Config Sharing Opportunities
**Can Share Configs (Partial Overlap):**
1. **test_extreme_eccentricity** ↔ test_parabolic_orbit/hyperbolic_orbit
- Existing: e=1.0, 1.5
- New: e=0.99, 0.9999, 1.0001
- May need new config for e=0.99, 0.9999 cases
2. **test_hybrid_impulse_burns** ↔ test_maneuvers
- Can reuse burn infrastructure
- New scenarios require separate config (Hohmann, apsides burns)
3. **test_hybrid_energy_conservation** ↔ test_energy
- Different objectives (comparison vs. drift)
- Could share circular orbit config
**Cannot Share Configs (Different Parameters):**
1. **test_extreme_orientation_mixed** vs test_inclined_orbits
- Existing: i=1.107 (63.4°)
- New: Combined high inclination + high eccentricity (unique)
2. **test_cartesian_to_elements_extreme** vs all existing
- New test category (no existing tests)
3. **test_cartesian_to_elements_quadrature** vs test_inclined_orbits
- Tests opposite conversion direction (cartesian→elements vs elements→cartesian)
- Both needed for complete validation
### Unique New Test Categories
**Entirely New Functionality:**
1. Cartesian to orbital elements conversion (Phase 1.1) - 3 tests
2. Newton-Raphson solver convergence (Phase 1.2) - 1 test
3. Analytical propagation accuracy (Phase 1.3) - 2 tests
4. Hybrid continuous thrust integration (Phase 2.2) - 1 test
5. Energy comparison: analytical vs. RK4 (Phase 2.3) - 1 test
6. Propagation through apsides - 1 test
**New Orbital Regimes:**
7. Combined high inclination + high eccentricity - 1 test (reduced from 3 orientation tests)
8. Extremely fast orbits (Mercury-like, < 100 days ) - 1 test
9. Extremely slow orbits (>10 years) - 1 test
10. Boundary values (e=0, i=π/2, i=π) - 1 test (already in test_precision_boundaries)
### Minimal File Count with Sharing
**Final estimate: 11 files** (reduced from 14)
**Reductions applied:**
- Removed test_energy_conservation_analytical.cpp (OPTIONAL, covered by hybrid test)
- Removed duplicate polar/retrograde tests from test_extreme_orientation (covered by test_precision_boundaries)
- Renamed to test_extreme_orientation_mixed.cpp (only tests combined high inclination + eccentricity)
**Recommendation: Keep 11 files**
- Each test has self-documenting config
- Easier to debug isolated failures
- Config reuse doesn't save much (configs are small)
- Clear separation of concerns
- No duplicate test coverage
#### 6. ✅ test_precision_boundaries.cpp + .toml: Exact boundary value handling
## Implementation Priority
@ -558,8 +155,8 @@ Total estimated test files: 11 (reduced from 14 after overlap analysis)
8. ⬜ test_extreme_orientation_mixed.cpp (high inclination + high eccentricity)
9. ⬜ test_extreme_timescales.cpp (fast/slow periods)
10. ✅ test_precision_boundaries.cpp (exact values)
11. ⬜ test_cartesian_to_elements_extreme.cpp (edge cases )
12. ⬜ test_cartesian_to_elements_quadrature.cpp (cartesian→elements conversion )
11. ✅ test_cartesian_to_elements_extreme.cpp (parabolic test fixed and tolerances tightened )
12. ✅ test_cartesian_to_elements_quadrature.cpp (argument of periapsis fix )
13. ✅ test_analytical_propagation_timesteps.cpp (large/small dt)
## Notes
@ -567,8 +164,5 @@ Total estimated test files: 11 (reduced from 14 after overlap analysis)
- Each .cpp file requires corresponding .toml config
- Some test categories can share configs if parameters align
- SOI transition tests deferred per user requirements
- **Test count reduced from 14 to 11 after overlap analysis** (2026-02-01)
- Removed tests:
- test_energy_conservation_analytical.cpp (OPTIONAL - covered by hybrid test)
- Duplicate polar/retrograde tests in test_extreme_orientation (covered by test_precision_boundaries)
- Retained test_cartesian_to_elements_quadrature.cpp (validates NEW function, opposite direction of test_inclined_orbits)
- Test count: 10/14 files fully passing (8/14 previously plus 2 new cartesian_to_elements tests)
- Additional test added: test_barkers_equation.cpp (parabolic propagation, 11 tests)
