# Test Configuration: Molniya Orbit
# Earth as root body with highly elliptical, highly inclined satellite orbit
# Molniya orbit parameters:
#   - Period: ~718 minutes (~12 hours)
#   - Eccentricity: 0.74
#   - Inclination: 63.4°
#   - Argument of perigee: 270° (apogee at northernmost point)
#   - Perigee altitude: ~600 km
#   - Apogee altitude: ~39,700 km
#   - Semi-major axis: ~26,600 km

[[bodies]]
name = "Earth"
mass = 5.972e24
radius = 6.371e6
parent_index = -1
color = { r = 0.0, g = 0.5, b = 1.0 }
orbit = {
    semi_major_axis = 0.0,
    eccentricity = 0.0,
    true_anomaly = 0.0
}

[[spacecraft]]
name = "Molniya_Satellite"
mass = 1000.0
parent_index = 0
orbit = {
    semi_major_axis = 26540000.0,
    eccentricity = 0.74,
    true_anomaly = 0.0,
    inclination = 1.107,
    longitude_of_ascending_node = 0.0,
    argument_of_periapsis = 4.71
}