# Test Configuration: Prograde Burn at Periapsis
# Tests that periapsis distance is preserved during prograde burn

[[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}

[[spacecraft]]
name = "TestSatellite"
mass = 1000.0
parent_index = 1
# Start at periapsis of an elliptical orbit
# a = 10,000 km, e = 0.3
# periapsis = 7,000 km, apoapsis = 13,000 km
orbit = {semi_major_axis=1.0371e7, eccentricity=0.3, true_anomaly=0.0}

[[spacecraft]]
name = "TestSatelliteCrossing"
mass = 1000.0
parent_index = 1
# Start at 90 degrees from periapsis for crossing test
orbit = {semi_major_axis=1.0371e7, eccentricity=0.3, true_anomaly=1.57}

[[maneuvers]]
name = "periapsis_prograde_burn"
spacecraft_name = "TestSatellite"
trigger_type = "true_anomaly"
trigger_value = 0.0
direction = "prograde"
delta_v = 500.0

[[maneuvers]]
name = "periapsis_prograde_burn_2"
spacecraft_name = "TestSatellite"
trigger_type = "true_anomaly"
trigger_value = 0.0
direction = "prograde"
delta_v = 500.0

[[maneuvers]]
name = "periapsis_prograde_burn_crossing"
spacecraft_name = "TestSatelliteCrossing"
trigger_type = "true_anomaly"
trigger_value = 0.0
direction = "prograde"
delta_v = 500.0