# 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
}