vibe coding an orbital mechanics simulation to try out claude code

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cinnaboot 5ebac26118 Implement config-based spacecraft with LEO initialization and impulse burn ... - Add spacecraft body to earth_mars_simple.toml config file - Implement initialize_spacecraft_leo() to set circular LEO at 200km altitude - Implement apply_transfer_burn() for Hohmann transfer impulse burn - Implement calculate_phase_angle() for launch window verification - Add comprehensive test case with SOI transition tracking - Preserve debug printf statements from main branch investigation - LEO initialization verified: position, velocity, energy all correct - Issue identified: delta-v calculation doesn't account for spacecraft LEO phase - Test completes 8/9 assertions (fails post-burn energy check) - Session documented in docs/leospacecraft_impulse_burn_plan.md Next: Fix apply_transfer_burn() to use vector-based delta-v instead of magnitude-based		6 months ago
..
session_summaries	add session summary	6 months ago
TODO	update manual TODO	6 months ago
implementation_plan.md	update implementation_plan to match current project state	6 months ago
leospacecraft_impulse_burn_plan.md	Implement config-based spacecraft with LEO initialization and impulse burn	6 months ago
mission_planning.md	Phase 1-3: Implement mission planning module for Hohmann transfers	6 months ago
patched_conics_plan.md	Record implementation decisions for patched conics	6 months ago