# Test Configuration: Molniya Orbit
# Earth as root body with highly elliptical, highly inclined satellite orbit
# Molniya orbit parameters:
#   - Semi-major axis: 26,540 km
#   - Eccentricity: 0.74
#   - Inclination: 63.4 deg
#   - Argument of perigee: 270 deg (apogee at northernmost point)

[[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 }