sequence = ["prop"]
[state.halo]
x = 3.3332103457598656e5
y = -7.6134322906422603e4
z = -2.0873903263672306e4
vx = 2.5713404516055560e-1
vy = 9.3034950416444684e-1
vz = 3.4629506912683045e-1
frame = "EME2000"
epoch = "2020-01-01T00:00:00.00"
[state.llo]
x = 3.9198721332342143e5
y = -7.4930324786174358e4
z = -7.0226029652694342e4
vx = -6.8030103935078690e-1
vy = 1.9922865304342552
vz = 4.3674176005046117e-1
frame = "EME2000"
epoch = "2020-01-01T00:00:00.00"
[orbital_dynamics.orbital_dyn]
integration_frame = "EME2000"
initial_state = "llo"
point_masses = ["Sun", "Earth", "Jupiter", "Luna"]
accel_models = ["my_models"]
[spacecraft.sc1]
dry_mass = 100.0
fuel_mass = 20.0
orbital_dynamics = "orbital_dyn"
[propagator.prop]
dynamics = "sc1"
stop_cond = "22 days"
output = "my_csv"
tolerance = 1e-9
[accel_models.my_models.harmonics.jgm3_70x70]
frame = "EME2000"
degree = 70
order = 70
file = "data/JGM3.cof.gz"
[accel_models.my_models.harmonics.jggrx]
frame = "iau moon"
degree = 20
order = 20
file = "data/Luna_jggrx_1500e_sha.tab.gz"
[output.my_csv]
filename = "./data/llo.csv"
headers = ["epoch:MjdTai", "x", "y", "z", "vx", "vy", "vz"]