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1.7 KiB
1.7 KiB
Session Summary: Analytical Propagation Implementation
Date: 2026-02-04
Changes Made
1. Implemented analytical propagation for all orbit types
- Modified
update_spacecraft_physics()andupdate_bodies_physics()insrc/simulation.cpp - Replaced RK4 numerical integration with
propagate_orbital_elements() - Supports circular, elliptical, parabolic, and hyperbolic orbits
2. Fixed three critical bugs in hyperbolic orbit propagation (src/orbital_mechanics.cpp)
true_anomaly_to_hyperbolic()- wrong formula (multiply vs divide, incorrect variable naming)hyperbolic_to_true_anomaly()- wrong formula (atanh vs atan, inverted factor)propagate_orbital_elements()hyperbolic case - only 1 Newton-Raphson iteration (now iterates to convergence)
3. Added orbital element reconstruction
- After burns in
execute_maneuver()(src/maneuver.cpp) - After SOI transitions in
update_bodies_physics()(src/simulation.cpp) - Updated
execute_maneuver()signature to includeSimulationState*parameter
4. Removed dead code
- Removed unused
solve_kepler_hyperbolic_with_prev()function from codebase
Commits
- Commit 1:
31f38b9- "Implement analytical propagation for all orbit types" (6 files, +129/-15) - Commit 2:
ec064a2- "Remove unused solve_kepler_hyperbolic_with_prev() function" (2 files, -19)
Results
- All 132 tests passing (240,294 assertions)
- Zero energy drift for all analytically propagated orbits
- All orbit types (circular, elliptical, parabolic, hyperbolic) now use unified analytical propagation
- Net line count: +129 -15 -19 = +95 lines
Remaining Issues
None
Next Steps
- Rewrite technical_reference.md from scratch to reflect current state of codebase