Remove old hybrid burns test and config (refactored to tests/)

old_tests/test_hybrid_burns.toml

@@ -1,254 +0,0 @@
-# Test Configuration: Hybrid Burns for Analytical Propagation
-# Sun + Earth system with multiple spacecraft for impulse and continuous burn testing
-# Tests the critical workflow: orbital elements → Cartesian → burn → orbital elements
-# and finite-duration burns with mode transitions
-
-[[bodies]]
-name = "Sun"
-mass = 1.989e30
-radius = 6.96e8
-parent_index = -1
-color = { r = 1.0, g = 1.0, b = 0.0 }
-orbit = {
-    semi_major_axis = 0.0,
-    eccentricity = 0.0,
-    true_anomaly = 0.0
-}
-
-[[bodies]]
-name = "Earth"
-mass = 5.972e24
-radius = 6.371e6
-parent_index = 0
-color = { r = 0.0, g = 0.5, b = 1.0 }
-orbit = {
-    semi_major_axis = 1.496e11,
-    eccentricity = 0.0,
-    true_anomaly = 0.0
-}
-
-# ========== IMPULSE BURN SPACECRAFT ==========
-
-# 1. Hohmann Transfer Spacecraft
-# Initial circular LEO orbit (altitude ~400 km)
-# Two maneuvers: apogee raise, circularization
-[[spacecraft]]
-name = "Hohmann_Transfer"
-mass = 1000.0
-parent_index = 1
-orbit = {
-    semi_major_axis = 6.771e6,
-    eccentricity = 0.0,
-    true_anomaly = 0.0,
-    inclination = 0.0,
-    longitude_of_ascending_node = 0.0,
-    argument_of_periapsis = 0.0
-}
-
-[[maneuvers]]
-name = "hohmann_burn_1"
-spacecraft_name = "Hohmann_Transfer"
-trigger_type = "time"
-trigger_value = 0.0
-direction = "prograde"
-delta_v = 2440.0
-
-[[maneuvers]]
-name = "hohmann_burn_2"
-spacecraft_name = "Hohmann_Transfer"
-trigger_type = "time"
-trigger_value = 5400.0
-direction = "prograde"
-delta_v = 1500.0
-
-# 2. Plane Change Spacecraft
-# Initial circular orbit with inclination 0.2 rad
-# One maneuver: normal burn at ascending node to change inclination to 0.4 rad
-[[spacecraft]]
-name = "Plane_Change"
-mass = 1000.0
-parent_index = 1
-orbit = {
-    semi_major_axis = 7.0e6,
-    eccentricity = 0.0,
-    true_anomaly = 0.0,
-    inclination = 0.2,
-    longitude_of_ascending_node = 0.0,
-    argument_of_periapsis = 0.0
-}
-
-[[maneuvers]]
-name = "plane_change_burn"
-spacecraft_name = "Plane_Change"
-trigger_type = "time"
-trigger_value = 0.0
-direction = "normal"
-delta_v = 1400.0
-
-# 3. Periapsis Burn Spacecraft
-# Initial elliptical orbit (e = 0.5)
-# One maneuver: prograde burn at periapsis to raise apoapsis
-[[spacecraft]]
-name = "Periapsis_Burn"
-mass = 1000.0
-parent_index = 1
-orbit = {
-    semi_major_axis = 1.5e7,
-    eccentricity = 0.5,
-    true_anomaly = 0.0,
-    inclination = 0.0,
-    longitude_of_ascending_node = 0.0,
-    argument_of_periapsis = 0.0
-}
-
-[[maneuvers]]
-name = "periapsis_burn"
-spacecraft_name = "Periapsis_Burn"
-trigger_type = "time"
-trigger_value = 0.0
-direction = "prograde"
-delta_v = 500.0
-
-# 4. Apoapsis Burn Spacecraft
-# Initial elliptical orbit (e = 0.5)
-# One maneuver: prograde burn at apoapsis to raise periapsis
-[[spacecraft]]
-name = "Apoapsis_Burn"
-mass = 1000.0
-parent_index = 1
-orbit = {
-    semi_major_axis = 1.5e7,
-    eccentricity = 0.5,
-    true_anomaly = 3.141592653589793,
-    inclination = 0.0,
-    longitude_of_ascending_node = 0.0,
-    argument_of_periapsis = 0.0
-}
-
-[[maneuvers]]
-name = "apoapsis_burn"
-spacecraft_name = "Apoapsis_Burn"
-trigger_type = "time"
-trigger_value = 0.0
-direction = "prograde"
-delta_v = 500.0
-
-# 5. Small Delta-v Burn Spacecraft
-# Initial circular orbit
-# One maneuver: minimal prograde burn (Δv < 1 m/s)
-[[spacecraft]]
-name = "Small_Delta_v"
-mass = 1000.0
-parent_index = 1
-orbit = {
-    semi_major_axis = 7.0e6,
-    eccentricity = 0.0,
-    true_anomaly = 0.0,
-    inclination = 0.0,
-    longitude_of_ascending_node = 0.0,
-    argument_of_periapsis = 0.0
-}
-
-[[maneuvers]]
-name = "small_burn"
-spacecraft_name = "Small_Delta_v"
-trigger_type = "time"
-trigger_value = 0.0
-direction = "prograde"
-delta_v = 0.5
-
-# 6. Large Delta-v Burn Spacecraft
-# Initial circular orbit
-# One maneuver: large prograde burn (Δv > orbital velocity)
-[[spacecraft]]
-name = "Large_Delta_v"
-mass = 1000.0
-parent_index = 1
-orbit = {
-    semi_major_axis = 7.0e6,
-    eccentricity = 0.0,
-    true_anomaly = 0.0,
-    inclination = 0.0,
-    longitude_of_ascending_node = 0.0,
-    argument_of_periapsis = 0.0
-}
-
-[[maneuvers]]
-name = "large_burn"
-spacecraft_name = "Large_Delta_v"
-trigger_type = "time"
-trigger_value = 0.0
-direction = "prograde"
-delta_v = 12000.0
-
-# ========== CONTINUOUS BURN SPACECRAFT ==========
-
-# 1. Low-thrust ion engine spacecraft
-# Initial circular LEO orbit (altitude ~400 km)
-# Simulated continuous burn: 5000 seconds duration, 100 m/s total Δv
-# Split into 100 small burns of 1 m/s each every 50 seconds
-[[spacecraft]]
-name = "Low_Thrust_Ion"
-mass = 1000.0
-parent_index = 1
-orbit = {
-    semi_major_axis = 6.771e6,
-    eccentricity = 0.0,
-    true_anomaly = 0.0,
-    inclination = 0.0,
-    longitude_of_ascending_node = 0.0,
-    argument_of_periapsis = 0.0
-}
-
-# 2. Multi-burn sequence spacecraft
-# Initial circular orbit
-# Simulated continuous burn 1: 2000 seconds, 50 m/s total Δv (20 burns of 2.5 m/s)
-# Simulated continuous burn 2: 3000 seconds, 75 m/s total Δv (30 burns of 2.5 m/s)
-[[spacecraft]]
-name = "Multi_Burn_Sequence"
-mass = 1000.0
-parent_index = 1
-orbit = {
-    semi_major_axis = 7.0e6,
-    eccentricity = 0.0,
-    true_anomaly = 0.0,
-    inclination = 0.0,
-    longitude_of_ascending_node = 0.0,
-    argument_of_periapsis = 0.0
-}
-
-# 3. Mode transition spacecraft
-# Initial elliptical orbit (e = 0.3)
-# Simulated continuous burn: 4000 seconds, 200 m/s total Δv
-# Split into 80 burns of 2.5 m/s each
-# Purpose: Test switching between analytical and numerical modes during burns
-[[spacecraft]]
-name = "Mode_Transition"
-mass = 1000.0
-parent_index = 1
-orbit = {
-    semi_major_axis = 1.2e7,
-    eccentricity = 0.3,
-    true_anomaly = 0.0,
-    inclination = 0.0,
-    longitude_of_ascending_node = 0.0,
-    argument_of_periapsis = 0.0
-}
-
-# 4. Energy conservation spacecraft
-# Initial circular orbit
-# Simulated continuous burn: 6000 seconds, 150 m/s total Δv
-# Split into 120 burns of 1.25 m/s each
-# Purpose: Verify energy conservation during finite-duration burn
-[[spacecraft]]
-name = "Energy_Conservation"
-mass = 1000.0
-parent_index = 1
-orbit = {
-    semi_major_axis = 8.0e6,
-    eccentricity = 0.0,
-    true_anomaly = 0.0,
-    inclination = 0.0,
-    longitude_of_ascending_node = 0.0,
-    argument_of_periapsis = 0.0
-}