vibe coding an orbital mechanics simulation to try out claude code

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test-refactor

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claudes_game/tests/configs

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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
..
earth_circular.toml	Migrate config system from space-separated to TOML format	6 months ago
earth_mars_simple.toml	Implement config-based spacecraft with LEO initialization and impulse burn	6 months ago
hyperbolic_comet.toml	Add hyperbolic orbit test case and configuration	6 months ago
interplanetary_transfer.toml	Phase 1: Enable root body transitions for patched conics	6 months ago
manual_root_transition.toml	Phase 1: Enable root body transitions for patched conics	6 months ago
mars_circular.toml	Migrate config system from space-separated to TOML format	6 months ago
parabolic_comet.toml	Add parabolic orbit support and test case	6 months ago
simple_root_transition.toml	Phase 1: Enable root body transitions for patched conics	6 months ago
soi_transition.toml	Add simplified SOI transition test case	6 months ago
solar_system.toml	fix moon starting positions in solar_system test config	6 months ago