# Test Configuration: Hybrid Energy Conservation
# Sun + Earth system with multiple spacecraft for energy conservation testing
# Tests energy comparison between analytical (propagate_orbital_elements) and numerical (RK4) propagation

[[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
}

# 1. Circular orbit spacecraft (LEO, altitude ~400 km)
# Tests energy conservation in simple stable orbit
[[spacecraft]]
name = "Circular_Orbit"
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. Elliptical orbit spacecraft (a = 1.5e7 m, e = 0.5)
# Tests energy conservation in elliptical orbit
# Periapsis = a * (1 - e) = 1.5e7 * 0.5 = 7.5e6 m (above Earth's radius)
[[spacecraft]]
name = "Elliptical_Orbit"
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
}

# 3. High eccentricity spacecraft (a = 4.0e7 m, e = 0.8)
# Tests energy conservation near parabolic boundary
# Periapsis = a * (1 - e) = 4.0e7 * 0.2 = 8.0e6 m (above Earth's radius)
[[spacecraft]]
name = "High_Eccentricity_Orbit"
mass = 1000.0
parent_index = 1
orbit = {
    semi_major_axis = 4.0e7,
    eccentricity = 0.8,
    true_anomaly = 0.0,
    inclination = 0.0,
    longitude_of_ascending_node = 0.0,
    argument_of_periapsis = 0.0
}

# 4. Inclined orbit spacecraft (i = 0.5 rad, altitude ~1000 km)
# Tests energy conservation with 3D orientation
[[spacecraft]]
name = "Inclined_Orbit"
mass = 1000.0
parent_index = 1
orbit = {
    semi_major_axis = 7.371e6,
    eccentricity = 0.0,
    true_anomaly = 0.0,
    inclination = 0.5,
    longitude_of_ascending_node = 0.0,
    argument_of_periapsis = 0.0
}

# 5. Fast orbit spacecraft (LEO, altitude ~200 km)
# Tests energy conservation for fast orbits
[[spacecraft]]
name = "Fast_Orbit"
mass = 1000.0
parent_index = 1
orbit = {
    semi_major_axis = 6.571e6,
    eccentricity = 0.0,
    true_anomaly = 0.0,
    inclination = 0.0,
    longitude_of_ascending_node = 0.0,
    argument_of_periapsis = 0.0
}

# 6. Slow orbit spacecraft (MEO, altitude ~20,000 km)
# Tests energy conservation for slow orbits
[[spacecraft]]
name = "Slow_Orbit"
mass = 1000.0
parent_index = 1
orbit = {
    semi_major_axis = 2.6371e7,
    eccentricity = 0.0,
    true_anomaly = 0.0,
    inclination = 0.0,
    longitude_of_ascending_node = 0.0,
    argument_of_periapsis = 0.0
}